adash - turbinetracker · p&w engine services adash adhy-g-010-1 cessna model 560 encore &...

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

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

ADASh

Installation Manual

ADHY-G-010-1

For Cessna Model 560 Encore & Ultra

Manual Number ADHY-G-010-1

Preparation Date: August 20, 2007 Prepared By: D Elsemiller

Release Date: February 27, 2008 S Sackos, Manager of Manufacturing Services

Revision Date: February 17, 2010 J Lukens, Applications Engineering

Revision Ltr: C

Pages: 75

Approvals:

P&W Engine Services ADASh ADHY-G-010-1Cessna Model 560 Encore & Ultra

ADHY-G-010-1 Pratt & Whitney Engine Services, Inc. Proprietary i

PREFACE

Disclaimer

Like all instrumentation, the Pratt & Whitney Engine Services, Inc. ADASh

requires knowledgeable interpretation by the pilot.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

hshould

not 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.


ADHY-G-010-1 Pratt & Whitney Engine Services, Inc. Proprietary - ii -

REVISION HISTORY

Rev A C C C C A A A A A A C C C C CRev Statusof Sheets Sheet i ii iii iv v 1 2 3 4 5 6 7 8 9 10 11

Rev C C C C C C C C C C C C C C C CSheet 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27Rev C C C C C C C C C C C C C C C CSheet 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43Rev C C C C C C C C C C C C C C C CSheet 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59Rev C C C C C C C C C C C C C C C CSheet 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75

LOG OF REVISIONS

REV. NO ECO # DESCRIPTION DATE PAGES REVISED

A N/A Initial Release 02/27/2008 All

B 989 Update Parts List. Revise ProcessorInstallation Instructions. Revise 560 Ultra

Pressure Bulkhead Connector Wiring.

02/04/2009 Cover, ii, 7, 9, 11-16,26, 47-54

C 1014 Create New Additional Parts Lists forCessna 560 Ultra. Update Cessna 560 Ultra

Schematic. Correct typographical errors.

02/17/2010 Cover, ii - v, 7 - 75


ADHY-G-010-1 Pratt & Whitney Engine Services, Inc. Proprietary iii

TABLE OF CONTENTS

1 INTRODUCTION.......................................................................................................................................... 11.1 Scope..................................................................................................................................................... 21.2 About This Manual ............................................................................................................................... 21.3 System Description ............................................................................................................................... 31.4 Unpacking the Equipment..................................................................................................................... 31.5 Weight and Balance .............................................................................................................................. 3

2 INSTALLATION AND MAINTENANCE PROCEDURES ........................................................................ 42.1 Standard Practices-Airframe/Powerplant.............................................................................................. 4

2.1.1 Procedure for Wiring Connections .................................................................................................. 42.1.2 Wiring Splices ................................................................................................................................. 52.1.3 Maintenance..................................................................................................................................... 6

2.2 Parts List ............................................................................................................................................... 72.2.1 ADASh by Parts Kits....................................................................................................................... 72.2.2 Components by Kit .......................................................................................................................... 7

3 Installation – Mechanical ............................................................................................................................. 103.1 System Processor ................................................................................................................................ 103.2 Circuit Breaker.................................................................................................................................... 143.3 Harness Installation............................................................................................................................. 15

3.3.1 “J1” Harness Installation ............................................................................................................... 153.3.2 “J2” Harness Installation ............................................................................................................... 153.3.3 “J3” Harness Installation ............................................................................................................... 16

4 INSTALLATION - ELECTRICAL ............................................................................................................. 184.1 Engine / Airframe Sensors .................................................................................................................. 18

4.1.1 Primus 1000 Air Data Computer (Right ADC) Wiring................................................................. 184.1.2 Engine 1 – N1 Indicator................................................................................................................. 184.1.3 Engine 2 – N1 Indicator................................................................................................................. 184.1.4 Engine 1 – N2 Indicator................................................................................................................. 184.1.5 Engine 2 – N2 Indicator................................................................................................................. 194.1.6 Engine 1 – Fuel Flow Indicator ..................................................................................................... 194.1.7 Engine 2 – Fuel Flow Indicator ..................................................................................................... 194.1.8 Engine 1 – ITT Indicator ............................................................................................................... 194.1.9 Engine 2 – ITT Indicator ............................................................................................................... 204.1.10 Weight on Wheels signal ............................................................................................................... 20

4.2 Electrical Power .................................................................................................................................. 214.2.1 Bus (Switched) Power Connection................................................................................................ 21

5 HARNESS CONNECTOR SIGNAL PINOUTS ......................................................................................... 225.1 J1 Harness ........................................................................................................................................... 225.2 J2 Harness ........................................................................................................................................... 225.3 J3 Harness ........................................................................................................................................... 23

6 WIRING DIAGRAM ................................................................................................................................... 246.1 ADASh Connection Chart – 560 Ultra S/N 260 – 538 with Analog Instruments............................... 246.2 ADASh Connection Chart–560 Encore S/N 539 – 625 with Analog Instruments ............................. 256.3 ADASh Connection Chart – 560 Encore S/N 626 – 750 with LCD Instruments ............................... 266.4 Wiring Schematic - Cessna Model 560 Ultra S/N 260 – 538 with Analog Instruments..................... 276.5 Wiring Schematic - Cessna Model 560 Encore S/N 539 – 625 with Analog Instruments.................. 286.6 Wiring Schematic - Cessna Model 560 Encore S/N 626 – 750 with LCD Instruments ..................... 29

7 SYSTEM OPERATION OVERVIEW ........................................................................................................ 307.1 ADASh Functional Description........................................................................................................... 30


ADHY-G-010-1 Pratt & Whitney Engine Services, Inc. Proprietary iv

7.1.1 Engine Run Logging...................................................................................................................... 307.1.2 Cycle Logging ............................................................................................................................... 307.1.3 Event Monitoring and Time History Buffer .................................................................................. 317.1.4 Trend Monitoring .......................................................................................................................... 31

7.2 System Initialization ........................................................................................................................... 317.3 System Modes ..................................................................................................................................... 317.4 Run Mode Description (States)........................................................................................................... 32

8 SYSTEM CONFIGURATION..................................................................................................................... 338.1 Definitions........................................................................................................................................... 338.2 Processor Configuration...................................................................................................................... 35

8.2.1 System Checkout and Sensor Verification .................................................................................... 358.2.2 Calibration Using Test Equipment ................................................................................................ 368.2.3 Calibration Using Aircraft Cockpit Instruments............................................................................ 37

9 AIRCRAFT TESTING................................................................................................................................. 389.1 Aircraft Ground Test ........................................................................................................................... 389.2 Continued Airworthiness Instructions................................................................................................. 41

10 SERVICE ................................................................................................................................................ 4111 SPECIFICATIONS ................................................................................................................................. 42

11.1 System Specifications ......................................................................................................................... 4211.2 Interface Requirements for Aircraft Sensors....................................................................................... 44

12 Appendix A ............................................................................................................................................. 4812.1 ADASh Installation for 560 Encore & Ultra....................................................................................... 4812.2 ADASh Installation for 560 Ultra ....................................................................................................... 5312.3 Circuit Breaker Installation ................................................................................................................. 5612.4 Forward Pressure Bulkhead Connector............................................................................................... 6012.5 Circuit Breaker Connector .................................................................................................................. 6312.6 Wire Routing for 560 Encore.............................................................................................................. 6612.7 Wire Routing for 560 Ultra ................................................................................................................. 71

LIST OF FIGURES

Figure 1: Cessna Model 560 ADASh System Architecture .................................................................................... 3Figure 2: Single or Dual Wire Splices.................................................................................................................... 5Figure 3: Shielded connection (Outer Heat-Shrink Tubing Not Shown) ............................................................... 5Figure 4: ADASh Processor.................................................................................................................................. 10Figure 5: Mounting Bracket Assembly ................................................................................................................ 11Figure 6: Mounting Bracket with ADASh ............................................................................................................ 11Figure 7: Mounting Plate (ADHY-D-049-1)........................................................................................................ 12Figure 8: Existing Nut Plates on Rails.................................................................................................................. 12Figure 9: ADASh Installation Location on 560 Encore (ADASh with DTU Shown) .......................................... 13Figure 10: ADASh Installation Location on 560 Ultra (ADASh with DTU Shown)............................................ 13Figure 11: Circuit Breaker Installation Location (560 Encore Shown)................................................................ 14Figure 12: Forward Pressure Bulkhead Connectors - Looking AFT (Encore shown) ......................................... 17Figure 13: Ground Connector............................................................................................................................... 17Figure 14: Primus 1000 Location (Right ADC) ................................................................................................... 17Figure 15: Airframe/Engine Signal Connections ................................................................................................. 20Figure 16: WOW Diode Orientation .................................................................................................................... 20Figure 17: Circuit Breaker Wiring ....................................................................................................................... 21Figure 18: ADASh Wiring Schematic – Cessna Model 560 Ultra S/N 260 – 538 wih Analog Instruments........ 27Figure 19: ADASh Wiring Schematic – Cessna Model 560 Encore S/N 539 – 625 with Analog Instruments ... 28Figure 20: ADASh Wiring Schematic – Cessna Model 560 Encore S/N 626 – 750 with LCD Instruments ....... 29


ADHY-G-010-1 Pratt & Whitney Engine Services, Inc. Proprietary v

LIST OF TABLES

Table 1: Connection Chart - 560 Ultra S/N 260 – 538 with Analog Instruments ................................................ 24Table 2: Connection Chart – 560 Encore S/N 539 – 625 with Analog Instruments............................................. 25Table 3: Connection Chart - 560 Encore S/N 626 – 750 with LCD Instruments ................................................. 26Table 4: VHF Frequency Table........................................................................................................................... 39Table 5: Electromagnetic Compatibility Test Table............................................................................................. 40Table 6: Ground Test Data ................................................................................................................................... 40

APPENDIX A

Figure A- 1: ADASh Installation for 560 Encore & Ultra – Sheet 1 of 5............................................................. 48Figure A- 2: ADASh Installation for 560 Encore & Ultra – Sheet 2 of 5............................................................. 49Figure A- 3: ADASh Installation for 560 Encore & Ultra – Sheet 3 of 5............................................................. 50Figure A- 4: ADASh Installation for 560 Encore & Ultra – Sheet 4 of 5............................................................. 51Figure A- 5: ADASh Installation for 560 Encore & Ultra – Sheet 5 of 5............................................................. 52Figure A- 6: ADASh for 560 Ultra – Sheet 1 of 3................................................................................................ 53Figure A- 7: ADASh for 560 Ultra – Sheet 2 of 3................................................................................................ 54Figure A- 8: ADASh for 560 Ultra – Sheet 3 of 3................................................................................................ 55Figure A- 9: Circuit Breaker Installation – Sheet 1 of 4....................................................................................... 56Figure A- 10: Circuit Breaker Installation – Sheet 2 of 4..................................................................................... 57Figure A- 11: Circuit Breaker Installation – Sheet 3 of 4..................................................................................... 58Figure A- 12: Circuit Breaker Installation – Sheet 3 of 4..................................................................................... 59Figure A- 13: Forward Pressure Bulkhead Connector – Sheet 1 of 3 .................................................................. 60Figure A- 14: Forward Pressure Bulkhead Connector – Sheet 2 of 3 .................................................................. 61Figure A- 15: Forward Pressure Bulkhead Connector – Sheet 3 of 3 .................................................................. 62Figure A- 16: Circuit Breaker Connector – Sheet 1 of 3...................................................................................... 63Figure A- 17: Circuit Breaker Connector – Sheet 2 of 3...................................................................................... 64Figure A- 18: Circuit Breaker Connector – Sheet 3 of 3...................................................................................... 65Figure A- 19: Wire Routing for 560 Encore – Sheet 1 of 5 ................................................................................. 66Figure A- 20: Wire Routing for 560 Encore – Sheet 2 of 5 ................................................................................. 67Figure A- 21: Wire Routing for 560 Encore – Sheet 3 of 5 ................................................................................. 68Figure A- 22: Wire Routing for 560 Encore – Sheet 4 of 5 ................................................................................. 69Figure A- 23: Wire Routing for 560 Encore – Sheet 5 of 5 ................................................................................. 70Figure A- 24: Wire Routing for 560 Ultra – Sheet 1 of 5 .................................................................................... 71Figure A- 25: Wire Routing for 560 Ultra – Sheet 2 of 5 .................................................................................... 72Figure A- 26: Wire Routing for 560 Ultra – Sheet 3 of 5 .................................................................................... 73Figure A- 27: Wire Routing for 560 Ultra – Sheet 4 of 5 .................................................................................... 74Figure A- 28: Wire Routing for 560 Ultra – Sheet 5 of 5 .................................................................................... 75


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

1 INTRODUCTION

Aircraft and engine maintenance procedures are critical to flight safety and lower operating costs. P&W EngineServices has developed an aircraft data acquisition system known as ADASh to perform two primary functions:

Exceedance Event Recording: The ADASh can monitor critical engine parameters and record instanceswhere they have exceeded preset values (exceedances).

Engine Trend Monitoring: The ADASh can gather and store engine data samples for trend analysis.

The ADASh enables the operator to control, quantify, and manage engine maintenance operations and reducedirect operating costs.

The ADASh is a passive receiver of information. In its data acquisition role it can be configured to record dataautomatically.

Automatic Operation: The system may be configured to automatically record exceedance events andtrends. It may also be configured to record data samples when stable aircraft conditions are achieved. Theseconditions are configurable, and the data gathered may be used for engine trend analysis.

Retrieving Data: Collected data is accessed through a download serial port. Communication with theADASh is achieved through P&W Engine Services Monitor Link Program (MLP), which can be used todownload data and upload system configuration files. The MLP can also be used to assist maintenancepersonnel in performing system diagnostics, calibrations, and real-time live sensor display.

System Configuration: The ADASh system is shipped with a predefined set of software sensorconfigurations, exceedance event specifications, cycle specifications, and engine start/stop definitions.System configurations can be altered to reflect the customer’s operating environment or requirements.

The ADASh is an enhancement to the Pratt & Whitney Engine Services Generation III monitoring system. TheADASh provides four ARINC-429 communications interfaces through which aircraft and engine performancedata can be collected. The ADASh uses these ARINC-429 interfaces to connect to aircraft subsystems, e.g., theair data computer. The ADASh also interfaces to the analog sensors on the aircraft for measuring other airframeand engine parameters not present on the ARINC-429 bus.



1.1 Scope

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

NOTE: To perform an installation, read the system overview, then, complete the preparation sectionchecklist. Find the aircraft wiring diagram and follow the steps described in the mechanical andelectrical assembly sections. Check off each instruction as it is completed. When finished,proceed to post-installation, configuration, and testing sections of the manual.

1.2 About This Manual

This document contains information regarding mechanical and electrical hardware pertaining to the CessnaModel 560 Encore & Ultra.

Mechanical and electrical sections of this manual are made up of instruction lists that take the following form:

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

For All Aircraft:

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

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

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

Wiring Instructions:

Perform the following steps:

010 Trim the cable to length

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

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



1.3 System Description

Figure 1shows the architecture of the ADASh on a Cessna Model 560 Encore & Ultra.

Figure 1: Cessna Model 560 ADASh

System Architecture

1.4 Unpacking the Equipment

Carefully remove each component from the original shipping container. Place each component on a roll-awaycart or suitable workbench in the work area.

1.5 Weight and Balance

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

ADASh Kit Weight lbs. ArmADHY-K-010-1ADHY-K-010-3

3.90 30



2 INSTALLATION AND MAINTENANCE PROCEDURES

INSTALLATION CAUTION:Use of any procedure that does not apply to your specific application could causeunnecessary damage to the aircraft and/or result in a system or product malfunction.

2.1 Standard Practices-Airframe/Powerplant

Prior to installation, be sure that you have read all the installation instructions. Review all manufacturerprovided airframe and powerplant documentation in order to understand installation requirements and technicalcapability of the system.

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

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

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

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

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

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

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

2.1.1 Procedure for Wiring Connections

INSTALLATION CAUTION:The ADAS

hcables have shields that connect to the processor chassis ground. When

terminating the shielded harness at the airframe connection, these shields must be trimmedback and insulated to prevent possible shorting with the signal wires.



2.1.2 Wiring Splices

The use of Raychem™ hermetic style wire splices (Figure 2 and Figure 3) are recommended. When makingconnections between two shielded cables, the shields should also be maintained using Raychem™ or equivalentshield splices. The entire cable splice should be encased in heat shrink tubing when completed.

A general procedure for wire splices (See Figure 2 and Figure 3) is illustrated as follows:

RAYCHEM D-436-37

OR EQUIVALENT

Figure 2: Single or Dual Wire Splices

1. INSERT PREPARED CABLE

2. APPLY HEAT

RAYCHEM

S01-04-R

OR EQUIVALENT

3. SPLICE W IRE AND

SHIELD PIGTAIL

Figure 3: Shielded connection (Outer Heat-Shrink Tubing Not Shown)



2.1.3 Maintenance

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

Care of the processor under normal operation consists of general cleaning and inspection for bracket andconnector security during every major engine or aircraft inspection. Refer to ADASh Instructions for ContinuedAirworthiness, ADHY-G-260-1.

Comments and findings should be forwarded to P&W Engine Services for inclusion into their continuedproduct improvement program.

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

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

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



2.2 Parts List

Care must be taken when handling all parts and equipment. Before opening packages, perform an inventorycheck by comparing the receivables to the appropriate bill of materials. The parts listed below consist of theinstallation kit for the ADASh system for the Cessna Model 560 Encore & Ultra aircraft. Assembly kit numbersare listed in Section 2.2.1 and individual components are detailed by kit numbers in Section 2.2.2.

2.2.1 ADASh by Parts Kits

For Cessna Model 560 Encore (ADASh with DTU) Qty P/N ADHY-K-010-1

Processor Assembly Kit 1 ADHY-K-027-1Wiring Harness Kit 1 ADHY-K-028-1Additional Installation Materials Kit 1 ADHY-K-029-1

For Cessna Model 560 Encore (ADASh Only) Qty P/N ADHY-K-010-3


For Cessna Model 560 Ultra (ADASh with DTU) Qty P/N ADHY-K-010-7


For Cessna Model 560 Ultra (ADASh Only) Qty P/N ADHY-K-010-8


2.2.2 Components by Kit

PROCESSOR ASSEMBLY KIT ADHY-K-027-1

Processor ADHY-A-010-2 Qty 1Mounting Bracket ADHY-D-034-1 Qty 1Bracket, Mounting Plate ADHY-D-049-1 Qty 1Mount, Shock Grommet Isolator 990-00020 Qty 4Washer, Flat, #6 920-00006 Qty 4Nut, Locking, #6-32 MS21042-06 Qty 4100 Reduced Head, Close Tolerance Bolt NAS8602-2 Qty 10Strap, Ground DPU-C-050-1 Qty 1Washer, Flat AN960-8 Qty 10Nut, Elastic Stop MS21044-N08 Qty 6Plug, Finishing 9/16” 990-00121 Qty 1Panel Plug 990-00128 Qty 1

WIRING HARNESS KIT ADHY-K-028-1

Harness, J1 External ADHY-C-031-1 Qty 1Harness, J2 External ADHY-C-032-1 Qty 1Harness, J3 External ADHY-C-033-1 Qty 1



ADDITIONAL MATERIAL INSTALLATION KIT ADHY-K-029-1

Breaker, 2 Amp 990-00131 Qty 1Wire, 24AWG, White M22759/16-24-9 Qty 3’Terminal, Ring #10 400-00030 Qty 2Terminal, Ring #8 400-00139 Qty 2Terminal, Ring #6 400-00029 Qty 2Diode, Inline Junction 300-00064 Qty 1Contact, Pin, Inline Junction 400-00148 Qty 2Contact, Socket, CB Connector 400-00149 Qty 1Contact, Pin, CB Connector 400-00150 Qty 1Contact, Socket, Ground Connector M39029/22-192 Qty 1Contact, Pin, Alumel M39029/87-475 Qty 2Contact, Pin, Chromel M39029/87-476 Qty 2Contact, Socket, Alumel M39029/89-499 Qty 2Contact, Socket, Chromel M39029/89-500 Qty 2







3 Installation – Mechanical

3.1 System Processor

NOTE: For detailed ADASh

installation drawings on the Cessna Model 560 Encore & Ultra refer toAppendix A, Section 12.1 and 12.2.

The processor (Figure 4) collects and interprets data from airframe and engine components. Data is retrieved bythe operator through an RS485 interface connection. The processor does not require access during flight.

The processor measures 3.7” high by 6.6” long by 1.7” deep and weighs 1.4 lbs. (22 oz.). An aluminum bracketwith Lord Aerospace shock mounts is used to mount the processor to the aircraft.

Figure 4: ADASh

Processor

The system processor is mounted to an existing avionics rack in the avionics bay (FS 30). The processor ismounted on the left side of the avionics bay on a 560 Encore model and the right side of the avionics bay on a560 Ultra model. These installations are mirror images of each other. The ADASh will not require accessduring normal operation.

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

010 Reference Figure 5 and assemble the Shock Mounts (990-00020), rectangular finishing plug (990-00128) and circular finishing plug (990-00121) into the processor bracket (ADHY-D-034-1).

020 Reference Figure 6 and install the processor onto the bracket assembly with the supplied hardware.

030 Mark and drill the location of the 4 mounting holes on the supplied mounting plate (Figure 7), using

the dimensions of the existing nut plates on the rails, shown in Figure 8.

NOTE: The 4 mounting holes will need to have a countersink depth of 0.04” at 100º on the top ofthe mounting plate.

040 Attach the mounting plate (ADHY-D-049-1) to the rails using the supplied 100º Reduced Head,Close Tolerance Bolts P/N NAS8602-2.

050 Attach the processor and bracket that was assembled in step 020 onto the mounting plate andensure that the processor does not interfere with wiring or controls. See Figure 9 and Figure 10:

NOTE: The 6 countersunk mounting holes on the bottom of the mounting plate (ADHY-D-049-1)utilize the supplied 100º Reduced Head, Close Tolerance Bolts P/N NAS8602-2.

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



Figure 5: Mounting Bracket Assembly

Figure 6: Mounting Bracket with ADASh



Figure 7: Mounting Plate (ADHY-D-049-1)

Figure 8: Existing Nut Plates on Rails



Figure 9: ADASh

Installation Location on 560 Encore (ADASh

with DTU Shown)

Figure 10: ADASh

Installation Location on 560 Ultra (ADASh

with DTU Shown)



3.2 Circuit Breaker

NOTE: For detailed Circuit Breaker installation drawings on the Cessna Model 560 Encore & Ultra referto Appendix A, Section 12.3

A (1) Amp Circuit Breaker or (2) Amp Circuit Breaker (if used with a DTU) will automatically interrupt theelectrical circuit under abnormal conditions. The circuit breaker will be installed in the Left Circuit BreakerPanel and will be connected to a switched power source, Bus Bar HC005, Essential Bus.

010 Ensure that no power is connected to the aircraft and that the battery cable is disconnected from thebattery.

020 Mount the circuit breaker (Figure 11) directly above the “FLT HR” CB or another vacant location asclose as possible.

030 Identify circuit breakers with proper markings.

Figure 11: Circuit Breaker Installation Location (560 Encore Shown)



3.3 Harness Installation

NOTE: For detailed Wire Routing Drawings on the Cessna Model 560 Encore & Ultra refer toAppendix A, Section 12.6 and 12.7.

Refer to Cessna Model 560 Wiring Diagram Manual (Wiring – Maintenance Practices)

3.3.1 “J1” Harness Installation

The J1 external harness connects to the connector plug on the ADASh processor labeled J1. The harnessprovides aircraft essential bus power to the processor. The individual cables are appropriately labeled.

The ADASh harness should be routed at a distinct separation from existing harnesses using Adel clamps(supplied by installer) until it no longer becomes practical due to the convergence of additional wire harnesses.

010 Connect the J1 harness to the J1 connector on the ADASh

processor.

020 Route the AAV10A22 cable to the Bus Circuit Breaker located on the Left Circuit Breaker panel.This will require using spare pins on an existing forward pressure bulkhead connector (J6 / P6), asshown in Figure 12. This will also require using supplied contacts (P/N 400-00149 and 400-00150)for the circuit breaker panel connector (J131 / P131). Refer to the wiring schematic in section 6.4for pin locations

NOTE: Use the provided M22759/16-24-9 (single conductor non-shielded) wire inside the circuit breakerpanel and label as necessary.

030 Route the AA00A22N cable to an aircraft ground connector (NDC17), as shown in Figure 13. Thiswill require using the supplied contact (P/N M390929/22-192). Refer to the wiring schematic inSection 6.4.


The J2 external harness connects to the connector plug on the ADASh processor labeled J2. The harnessprovides engine and air data to the processor. The individual cables are appropriately labeled.



processor.

020 Route the AAB00B24 cable to the Primus 1000 Air Data Computer (ADC) in the Avionics Bay, asshown in Figure 14. Refer to the wiring schematic in section 6.4 for pin locations.

030 Route the AAP10B24 cable to the Engine 1 N1 Indicator on the instrument panel. This will requireusing spare pins on an existing forward pressure bulkhead connector (J6 / P6), as shown in Figure12. Refer to the wiring schematic in section 6.4 for pin locations


050 Route the AAA25B24 cable to the Engine 1 Fuel Flow Indicator on the instrument panel for aCessna 560 Ultra. This will require using spare pins on an existing forward pressure bulkheadconnector (J6 / P6), as shown in Figure 12. For a Cessna 560 Encore, route the AAA25B24 cableto the Engine 1 Fuel Flow signal at the fwd pressure bulkhead connector (JB724 / PB724), asshown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations.

060 Route the AAA10B24 cable to the Engine 1 ITT Indicator on the instrument panel. This will requireusing supplied alumel and chromel pins on an existing forward pressure bulkhead connector



(J6 / P6), as shown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations

070 Route the AAA11B24 cable to the Engine 2 ITT Indicator on the instrument panel. This will requireusing supplied alumel and chromel pins on an existing forward pressure bulkhead connector (J6 /P6), as shown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations


The J3 external harness connects to the connector plug on the ADASh processor labeled J3. The harnessprovides weight on wheels (WOW) and engine data to the processor. The individual cables are appropriatelylabeled.



processor.

020 Route the AAA26B24 cable to the Engine 1 Fuel Flow Indicator on the instrument panel for aCessna 560 Ultra. This will require using spare pins on an existing forward pressure bulkheadconnector (J6 / P6), as shown in Figure 12. For a Cessna 560 Encore, route the AAA26B24 cableto the Engine 1 Fuel Flow signal at the fwd pressure bulkhead connector (JB724 / PB724), asshown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations.



050 Route the AAD00A24 cable to the Primus 1000 Air Data Computer (ADC) in the Avionics Bay, asshown in Figure 14. Refer to the wiring schematic in section 6.4 for pin locations.



Figure 12: Forward Pressure Bulkhead Connectors - Looking AFT (Encore shown)

Figure 13: Ground Connector

Figure 14: Primus 1000 Location (Right ADC)

JB324 / PB324 (Encore)JB724 / PB724

J6 / P6 (Ultra)



4 INSTALLATION - ELECTRICAL

The ADASh system consists of three external harnesses. The harnesses are appropriately labeled J1 and all wireused meet the specifications of MIL-C-27500.4.1 Engine / Airframe Sensors

4.1.1 Primus 1000 Air Data Computer (Right ADC) Wiring

The ADASh ARINC429 Rx channel 1 will connect to the Right Air Data Computer (ADC) ARINC429 (lowspeed) output and will receive air data (Pressure Altitude, Indicated Airspeed, and Total Air Temperature).

010 Trim the AAB00B24 cable to length.

020 Following the illustration (Figure 15), splice to the right ADC ARINC429 signal using the following pinconfiguration.

Color Right ADC (PN372)WHT Pin 60 (Arinc429 +)WHT/BLU Pin 61 (Arinc429 –)

030 Secure all wiring.

4.1.2 Engine 1 – N1 Indicator

010 Trim the AAP10B24 cable to length.

020 Following the illustration (Figure 15), splice to the N1 signal at the indicator using the pinconfiguration shown.

Cessna Model 560 S/N 260 – 625 Cessna Model 560 S/N 626 – 750Color Eng 1 – N1 Indicator (PI024) Eng 1 – N1 Indicator (PI055)WHT Pin J Pin 68WHT/BLU Pin K Pin 69





Cessna Model 560 S/N 260 – 625 Cessna Model 560 S/N 626 – 750Color Eng 2 – N1 Indicator (PI025) Eng 2 – N1 Indicator (PI056)WHT Pin J Pin 68WHT/BLU Pin K Pin 69





Cessna Model 560 S/N 260 – 625 Cessna Model 560 S/N 626 – 750Color Eng 1 – N2 Indicator (PI026) Eng 1 – N2 Indicator (PI055)WHT Pin Y Pin 70WHT/BLU Pin Z Pin 71







Cessna Model 560 S/N 260 – 625 Cessna Model 560 S/N 626 – 750Color Eng 2 – N2 Indicator (PI026) Eng 2 – N2 Indicator (PI056)WHT Pin Y Pin 71WHT/BLU Pin Z Pin 70


4.1.6 Engine 1 – Fuel Flow Indicator

010 Trim the AAA25B24 cable to length.

020 Following the illustration (Figure 15), splice to the Fuel Flow signal using the pin configurationshown.

Cessna Model 560 S/N 260 – 538 Cessna Model 560 S/N 539 – 750Color Eng 1 – Fuel Flow Signal (PI028) Eng 1 – Fuel Flow Signal (PB724)WHT Pin G Pin 21WHT/BLU Pin P Pin 22


4.1.7 Engine 2 – Fuel Flow Indicator


020 Following the illustration (Figure 15), splice to the Fuel Flow signal at the indicator using the pinconfiguration shown.

Cessna Model 560 S/N 260 – 538 Cessna Model 560 S/N 539 – 750Color Eng 2 – Fuel Flow Signal (PI029) Eng 2 – Fuel Flow Signal (PB724)WHT Pin G Pin 23WHT/BLU Pin P Pin 24


4.1.8 Engine 1 – ITT Indicator


020 Following the illustration (Figure 15), splice to the Thermocouple signal at the indicator using the pinconfiguration shown.

Cessna Model 560 S/N 260 – 625 Cessna Model 560 S/N 626 – 750Color Eng 1 – ITT Indicator (PI024) Eng 2 – ITT Indicator (PI055)RED Pin M (Alumel –) Pin 73 (Alumel –)YEL Pin N (Chromel +) Pin 72 (Chromel +)




4.1.9 Engine 2 – ITT Indicator


020 Following the illustration (Figure 15), splice to the Thermocouple signal at the indicator using the pinconfiguration shown.

Cessna Model 560 S/N 260 – 625 Cessna Model 560 S/N 626 – 750Color Eng 2 – ITT Indicator (PI025) Eng 2 – ITT Indicator (PI056)RED Pin M (Alumel –) Pin 73 (Alumel –)YEL Pin N (Chromel +) Pin 72 (Chromel +)


AIRCRAFT HARNESS SIG +

WHT

WIR

E

SHRINK SLEEVING" Pull Back and Cover Shield "

ADAS-H Marked Cable

WHT/B

LUW

IRE

SIG -

Connector/IndicatorRAYCHEM SPLICE

Figure 15: Airframe/Engine Signal Connections

4.1.10 Weight on Wheels signal

INSTALLATION CAUTION:

The Weight on Wheels (WOW) cable uses a diode to protect the “WOW” circuit if the cable isshorted to ground. This diode must be installed per the installation instructions and wiringdiagram.

010 Trim the “AAD00A24” cable to length.

020 Prepare cable(s) and crimp supplied contacts (p/n 400-00148) onto the cable(s).

030 Connect the 1N4001 (p/n 300-00064) in-line junction diode to the “AAD00A24” cable by insertingthe contact(s) that were crimped in step 020. Refer to Figure 16 for the correct orientation of thediode. The diode must be located as close as possible to the WOW connection point.

040 Splice to the Right ADC for the WOW connection using the following pin configuration shown.

Color Right ADC (PN372)WHT Pin 12 (WOW discrete)


Figure 16: WOW Diode Orientation



4.2 Electrical Power

INSTALLATION CAUTION:The “Bus” power supply must be chosen to provide power to the ADAS

hthrough an entire

engine’s running cycle. This is supplied by the “Essential Bus” directly controlled by theaircraft “battery Switch”Ensure that any connection to aircraft power incorporates a minimal wire length from thepower source to the protection device, fuse or breaker. Recommended length is (6) sixinches or less.Ensure that the wire is protected from shorting out against the airframe or any other sharpobjects during routing. Use spiral wrap or standoffs if necessary.

4.2.1 Bus (Switched) Power Connection

010 Trim the supplied M22759/16-24-9 (single conductor non-shielded) wire AAV10A22 cable to length.

020 Following illustration Figure 17, connect the wire to one side of the supplied breaker.

030 Connect the other end of the breaker to Essential Bus on the Left Circuit Breaker Panel in thecockpit.


Figure 17: Circuit Breaker Wiring



5 HARNESS CONNECTOR SIGNAL PINOUTS

INSTALLATION CAUTION:The “Bus” power supply must be chosen to provide power to the ADAS

hthrough an entire

engine’s running cycle. This is supplied by the “Essential Bus” directly controlled by theaircraft “battery Switch”Before making any wiring connections, verify all connection locations with the aircraftmanufacturer’s wiring diagram manuals.Perform a continuity check on all wires before final connection.Route all harnesses along existing harnesses wherever possible.Cables may be marked with shrink on labels near the terminal end. When you shorten acable behind a label, be sure to re-label it.For detailed Wiring Routing Drawings refer to Appendix A, Section 12.6 and 12.7Refer to Cessna Model 560 Wiring Diagram Manual (Wiring – Maintenance Practices).

5.1 J1 Harness

Connector Pin Harness Wire Color Signal Name Wired To Section 6

1 COND CABLEJ1 F & H WHT 28 VDC Bus Aircraft Bus Pwr

1 COND CABLEJ1 G WHT System Ground Aircraft Ground

5.2 J2 Harness


2 COND CABLEJ2 26 WHT ARINC1 RX HI Primus 1000 “ADC”J2 27 WHT/BLU ARINC1 RX Lo Primus 1000 “ADC”

2 COND CABLEJ2 5 WHT Eng 1 N2 SPD+ Eng 1-N2 IndicatorJ2 6 WHT/BLU Eng 1 N2 SPD- Eng 1-N2 Indicator


2 COND CABLEJ2 2 WHT Eng 1 Wf PPH+ Eng 1-Fuel FlowJ2 4 WHT/BLU Eng 1 Wf PPH- Eng 1-Fuel Flow

2 COND CABLEJ2 11 RED Eng 1 ITT- (Alumel) Eng 1-ITT IndicatorJ2 12 YEL Eng 1 ITT+ (Chromel) Eng 1-ITT Indicator

2 COND CABLEJ2 13 RED Eng 2 ITT- (Alumel) Eng 2-ITT IndicatorJ2 14 YEL Eng 2 ITT+ (Chromel) Eng 2-ITT Indicator



5.3 J3 Harness


2 COND CABLEJ3 26 WHT Eng 2 Wf PPH+ Eng 2-Wf IndicatorJ3 27 WHT/BLU Eng 2 Wf PPH- Eng 2-Wf Indicator



1 COND CABLEJ3 3 WHT WOW (Discrete) Primus 1000 “ADC”



6 WIRING DIAGRAM

6.1 ADASh Connection Chart – 560 Ultra S/N 260 – 538 with Analog Instruments

Cessna Model 560 Ultra S/N 260 – 538 (Analog Instruments)Sensor Wire Labels Aircraft Connection ADASh Connector

LFT CB Panel “Essential Bus” J1A/C Bus AAV10A22

Circuit Breaker Pin F WHT & Pin H WHT

Aircraft Grounding Plug – NDC17 J1Aircraft Ground AA00A22N

Ground Pin G WHT

Engine 1 – N1 Indicator – PI024 J2

Pin J Pin 7 WHTEngine 1 – N1Indicator

AAP10B24

Pin K Pin 8 WHT/BLU



AAP12B24

Pin K Pin 21 WHT/BLU


Pin Y Pin 5 WHTEngine 1 – N2Indicator

AAP11B24

Pin Z Pin 6 WHT/BLU



AAP13B24

Pin Z Pin 23 WHT/BLU

Engine 1 – ITT Indicator – PI024 J2

Pin M Pin 11 REDEngine 1 – ITTIndicator

AAA10B24

Pin N Pin 12 YEL



AAA11B24

Pin N Pin 14 YEL

Engine 1 – Fuel flow Indicator – PI028 J2

Pin G Pin 2 WHTEngine 1 – FuelFlow Indicator

AAA25B24

Pin P Pin 4 WHT/BLU

Engine 2 – Fuel flow Indicator – PI029 J3

Pin G Pin 26 WHTEngine 2 – FuelFlow Indicator

AAA26B24

Pin P Pin 27 WHT/BLU

Right ADC – PN372 J2

Pin 60 Pin 26 WHTPrimus 1000“ADC”

AAB00B24

Pin 61 Pin 27 WHT/BLU

Right ADC – PN372 J3Weight onWheels (WOW)

AAD00A24Pin 12 Pin 3 WHT

Table 1: Connection Chart - 560 Ultra S/N 260 – 538 with Analog Instruments



6.2 ADASh Connection Chart–560 Encore S/N 539 – 625 with Analog Instruments

Cessna Model 560 Encore S/N 539 – 625 (Analog Instruments)Sensor Wire Labels Aircraft Connection ADASh Connector

LFT CB Panel “Essential Bus” J1A/C Bus AAV10A22



Ground Pin G WHT



AAP10B24

Pin K Pin 8 WHT/BLU



AAP12B24

Pin K Pin 21 WHT/BLU



AAP11B24

Pin Z Pin 6 WHT/BLU



AAP13B24

Pin Z Pin 23 WHT/BLU



AAA10B24

Pin N Pin 12 YEL



AAA11B24

Pin N Pin 14 YEL

Engine 1 – Fuel flow – PB724 J2

Pin 21 Pin 2 WHTEngine 1 – FuelFlow Indicator

AAA25B24




AAA26B24




AAB00B24




Table 2: Connection Chart – 560 Encore S/N 539 – 625 with Analog Instruments



6.3 ADASh Connection Chart – 560 Encore S/N 626 – 750 with LCD Instruments

Cessna Model 560 Encore S/N 626 – 750 (LCD Instruments)Sensor Wire Labels Aircraft Connection ADASh Connector

LFT CB Panel “Essential Bus”- J1A/C Bus AAV10A22



Ground Pin G WHT


Pin 68 Pin 7 WHTEngine 1 – N1Indicator

AAP10B24




AAP12B24




AAP11B24


Engine 2 – N2 Indicator – P1056 J3


AAP13B24



Pin 73 Pin 11 REDEngine 1 – ITTIndicator

AAA10B24

Pin 72 Pin 12 YEL


Pin 73 Pin 13 REDEngine 2 – ITTIndicator

AAA11B24

Pin 72 Pin 14 YEL



AAA25B24




AAA26B24




AAB00B24




Table 3: Connection Chart - 560 Encore S/N 626 – 750 with LCD Instruments


ADHY-G-010-1 Pratt & Whitney Engine Services, Inc. Proprietary - 27 -

6.4 Wiring Schematic - Cessna Model 560 Ultra S/N 260 – 538 with Analog Instruments

NOTE 1: Route wire in accordance with Cessna Model 560 Wiring Diagram Manual (Wiring – Maintenance Practices)NOTE 2: For detailed wire routing drawings refer to Appendix A, Section 12.7NOTE 3: Use pin locations shown or locate adjacent spare pins if unavailable on fwd pressure bulkhead and circuit breaker panel connectors.

GP

YZ

JK

12

*A*B

*N*P

HG

JK

LM

*G*H

*FN

*I*J

Y

5

6

YEL

PI027

AAP10B24

WHT/BLU

WHT/BLU

6

6

3RED

AAA26B24

AAA10B24

P6

RED

2

6

5

WHT

WHT/BLU

PN372

RED

WHT/BLU

5

PI024

WHT

Eng 1 - N1 Indicator +Eng 1 - N1 Indicator -

Eng 2 - Fuel F low Indicator +Eng 2 - Fuel F low Indicator -


6

4

WHT

J6

WHT/BLU

WHT

WHT

WHT

REDYEL

Eng 1 N2 SPD +Eng 1 N2 SPD -


ARINC1 RXHI (Low Speed)ARINC1 RXLO (Low Speed)

Eng 1 Fuel Flow +Eng 1 Fuel Flow -

Eng 1 ITT (CH)Eng 1 ITT (AL)


J2 - 37 S

11

56

12

1413

42

87

2726


RS485+RS485 -

AC GNDRun/Conf ig

--

--

AUX BAT+AC BAT+

--AC BUS+

J4 - Lemo

10987

4

6

321

5

AC BUS+

AC BAT+

AC GND

J1 - 15 S

F

H

G

5

Ground Strap

To Processor Bracket

WHT

WHT/BLU

PN372

AAA11B24

Primus 1000 "ADC" +Primus 1000 "ADC" -





WOW (DI-L3)

J3 - 37 SB

2021

2322

2726

3

4

6

5

WHTWHT/BLU

PI029

AAD00A24

YEL

6

AAP12B24

AAA10B24

WHT/BLU

1N4001

DIODE

6

6061

5

5

JK

YZ

6

1

56

AAA26B24

PI026

ALUMEL PIN

5

3 M39029/9-134

QTY

ORG

AAA25B24

4

WHT/BLU

AAP10B24

BRN

ORG

AAP12B24

6

M39029/10-141

3

BASIC

CRIMP TOOL

5

BLK

M39029/4-110

AAP13B24

ALUMEL SOCKET

REF DES

ADAS HybridADHY-A-010-2

AAP11B24

BRNM39029/9-135

AAP13B24

M39029/10-140

M22520/1-01

or

M22520/2-012

Eng 1 - Fuel Flow Indicator +Eng 1 - Fuel Flow Indicator -

2

CHROMEL SOCKET YEL

1

BRN

YEL

M22520/1-01

or

M22520/2-01

DESCRIPTION

PIN BRN9 BLK6

PI024

PART NO.COLOR BANDS

2

Positioner

YELM81969/14-02

(White)

2nd

Primus 1000 "Right ADC"

GRNM39029/5-1155

BRN

3rd

2

6

GRN

22

Eng 2 - ITT Indicator (CH)Eng 2 - ITT Indicator (AL)

AAP11B24

AAA25B24

INSTALLING

TOOL


1st

REMOVAL

TOOL

M81969/14-02

(RED)

9 BRN

5

BRN

CHROMEL PIN

BRN

BRN

SOCKET

WHT/BLU

AAA11B24

WHT

WHT

WHT

WHT

AAB00B24

PI028

YEL

WHT/BLU

5

1

WHT

WHT

PI025

WHT/BLU

PI025

WHT/BLU

REDM39029/22-1927 WHT1 BROWNSOCKET

Fwd Pressure Bulkhead

K503/TH343

2 400-001488 PIN

SOCKET400-001491 9 N/A Tyco p/n 91523-1

or Equivelent

N/AN/A Tyco p/n

305183 or

Equivelent

Tyco p/n

200893-2 or

Equivelent10 PIN400-001501 N/AN/A N/A

N/A N/AN/A M22520/1-02M22520/1-01

7

88

*A*B

*N*P

HG

JK

LM

*G*H

*FN

*I*J

Y


WHT

AA00A22N

5X

Aircraft GroundNDC17

XAAV10A22

WHT

P6J6

WHT 6 AAV10A22

1 AMP CB (ADASh Only)or

2 AMP CB (ADASh with DTU)

LFT CB PanelESSENTIAL BUSBus Bar HC005

NM

9

J131

10

P131

NNNN

NM

1 2

Circuit Breaker Panel

GP

Figure 18: ADASh

Wiring Schematic – Cessna Model 560 Ultra S/N 260 – 538 wih Analog Instruments



6.5 Wiring Schematic - Cessna Model 560 Encore S/N 539 – 625 with Analog Instruments


CD

AB

2122

2324

2

RED1

WHT

YEL

WHT/BLU

WHT/BLUWHT

PB724

GH

MN

FE

KL

Eng 1 - Fuel Flow +Eng 1 - Fuel Flow -

CD

AB

NM

PB324 JB324

NM


YZ




Primus 1000 "Right ADC" +Primus 1000 "Right ADC" -


Eng 2 - Fuel Flow +Eng 2 - Fuel Flow -



JK

12

GH

MN

FE

KL

WHTWHT/BLU

WHT/BLUWHT

YELRED

AAP10B24

WHT

WHTWHT/BLU

WHT/BLUAAP12B24

AAP11B24

AAA11B24

PI026

PI027

AAD00A24PN372

PI024

AAP13B24

AAA10B24

PI025


PI024

AAA25B24

AAA26B24

PI025

PN372AAB00B24

WHT/BLU

YEL

WHT

YEL

WHTWHT/BLU

AAP10B24

RED

RED

WHT/BLU

WHTWHT/BLU

WHT

WHT

AAA11B24

AAP12B24

AAP11B24

AAA10B24

AAP13B24

PB324 JB324

WHT


WHT/BLU







J2 - 37 S

11

56

12

1413

42

87

2726

RS485+RS485 -

AC GNDRun/Conf ig

--

--

AUX BAT+AC BAT+

--AC BUS+

J4 - Lemo

10987

4

6

321

5




WOW (DI-L3)

J3 - 37 SB

2021

2322

2726

3

Ground Strap


1N4001

DIODE

6061

JK

YZ

4

3

5

5

5

5

2

1

5

5

5

5

4

3

6

6

6

6

6

6

6

6

3 M39029/87-475 ALUMEL PIN VIOLET

VIOLET4

QTY

BLKM39029/89-500

M39029/58-363

BASIC

CRIMP TOOL

ALUMEL SOCKET

REF DES

WHT

M39029/87-476 GRN

M22520/1-04

or

M22520/2-10

M39029/89-499

BLK

2

2

CHROMEL SOCKET

YEL

WHT1

PIN ORG

M22520/1-01

or

M22520/2-01

6

DESCRIPTION

9 ORG

COLOR BANDS

2

PART NO. Positioner2nd

GRNM81969/14-02

(White)

5 VIOLETM39029/57-357

GRN

3rd

22

BLU

INSTALLING

TOOL1st

REMOVAL

TOOL

M81969/14-02

(RED)

GRN9

YEL

CHROMEL PIN

SOCKET ORG

BLU

M39029/22-1927 WHT1 REDSOCKET BROWN K503/TH343

82 PIN400-00148

SOCKET400-001491 9 N/A Tyco p/n 91523-1

or Equivelent

N/AN/A

400-00150

Tyco p/n

305183 or

Equivelent

Tyco p/n

200893-2 or

Equivelent10 PIN1 N/AN/A

N/A

N/A


M22520/1-02N/AN/A


M22520/1-01

7

88

AC BUS+

AC BAT+

AC GND

J1 - 15 S

F

H

G


WHT

AA00A22N

5


RRAAV10A22

WHT

WHTPB324JB324

AAV10A226LFT CB PanelESSENTIAL BUSBus Bar HC005


2 AMP CB (ADASh with DTU)J131

9

P131

10NNNN

1 2


Figure 19: ADASh

Wiring Schematic – Cessna Model 560 Encore S/N 539 – 625 with Analog Instruments



6.6 Wiring Schematic - Cessna Model 560 Encore S/N 626 – 750 with LCD Instruments


CD

AB

2122

2324

2

1

YELRED

WHT/BLUWHT

WHTWHT/BLU

PB724

GH

MN

FE

KL


CD

AB

7273

PB324 JB324

7273


7170


Primus 1000 "Right ADC" +Primus 1000 "Right ADC" -







12

6869

GH

MN

FE

KL

WHTWHT/BLU

WHT/BLUWHT

YELRED

AAP10B24

WHT/BLU

WHT/BLUWHT

WHT

AAP12B24

AAP11B24

AAA11B24

PI055

PI056

PN372AAD00A24

PI055

AAP13B24

AAA10B24

PI056


PI055

AAA25B24

AAA26B24

PI056

AAB00B24PN372

YEL

WHTWHT/BLU

WHTWHT/BLU

RED

REDYEL

AAP10B24

WHTWHT/BLU

WHTWHT/BLU

WHT

AAP12B24

AAP11B24

AAP13B24

AAA11B24

JB324

AAA10B24

PB324Fwd Pressure Bulkhead

WHT/BLUWHT







J2 - 37 S

11

56

12

1413

42

87

2726

RS485+RS485 -

AC GNDRun/Conf ig

--

--

AUX BAT+AC BAT+

--AC BUS+

J4 - Lemo

10987

4

6

321

5




WOW (DI-L3)

J3 - 37 SB

2021

2322

2726

3

ALUMEL PIN3 M39029/87-475 VIOLET

VIOLET4

QTY

BLKM39029/89-500

Ground Strap


1N4001

DIODE

WHT

M39029/58-363

BASIC

CRIMP TOOL

ALUMEL SOCKET

REF DES

M39029/87-476 GRN

6061

M22520/1-04

or

M22520/2-10

M39029/89-499

BLK

2

1

2

CHROMEL SOCKET

6869

YEL

WHT

PIN ORG

M22520/1-01

or

M22520/2-01

6

DESCRIPTION

7071

9 ORG

COLOR BANDS

2

PART NO. Positioner2nd

GRNM81969/14-02

(White)

5

3rd

VIOLETM39029/57-357

GRN

3

4

BLU

22

INSTALLING

TOOL1st

REMOVAL

TOOL

M81969/14-02

(RED)

5

5

GRN9

BLU

YEL

CHROMEL PIN

5

5

SOCKET ORG

M39029/22-1927 WHT1 RED

1

2

SOCKET BROWN K503/TH343

5

5

5

5

82 PIN400-00148

SOCKET400-00149

3

4

1 9 N/AN/A

6

6

Tyco p/n 91523-1

or Equivelent

N/A

400-00150

Tyco p/n

305183 or

Equivelent

Tyco p/n

200893-2 or

Equivelent

6

6

10 PIN1 N/AN/A

N/AN/A

N/A

6

6

M22520/1-02N/A M22520/1-01

6

6

7

88


WHT

AA00A22N

5


RRAAV10A22

WHT

JB324

WHTPB324

AAV10A226AC BUS+

AC BAT+

AC GND

J1 - 15 S

F

H

G

LFT CB PanelESSENTIAL BUSBus Bar HC005


2 AMP CB (ADASh with DTU)J131

9

P131

10NNNN

1 2




Figure 20: ADASh

Wiring Schematic – Cessna Model 560 Encore S/N 626 – 750 with LCD Instruments



7 SYSTEM OPERATION OVERVIEW

The ADASh is a dual function instrument that gathers and records engine information from sensors for laterdownloading.

The ADASh is designed to perform the following functions:

Sensor Monitoring

Exceedance/Event Monitoring

Engine Run Logging

Trend Data Collection

Operator Initiated Self-Test

Automatic Self-Test

Data Downloading

Configuration Control

7.1 ADASh Functional Description

7.1.1 Engine Run Logging

The ADASh is capable of recording engine runs with up to 4 different engine run criteria for each engine. Foreach engine run, the following is recorded:

Engine number (if dual engine)

Engine start date and time

Engine run duration

Maximum start temperature

Minimum battery voltage

Start length (“Light Off” to Engine Idle)

Maximum sensor values

Cycle count

7.1.2 Cycle Logging

ADASh can be configured for up to four different types of cycle count types during each engine run.

1. Incremental cycles (sensor based)

2. Duration cycle (sensor based)

3. Peak value cycle (based on one or two sensors)

4. Cumulative valley cycle (sensor based)



7.1.3 Event Monitoring and Time History Buffer

Events: The ADASh can be configured to monitor and record airframe or engine exceedances or events. Up tothirty-two (32) basic Airman’s Flight Manual (AFM) exceedances and operator specific events can beconfigured. Each event is logged independently of engine run logging. Each event records the date and time ofthe event; its duration, average sensor value, and minimum or maximum sensor value. Events can be set tocomprise inputs from either one, two or three sensors.

Time History Buffer: The ADASh continually updates a temporary memory buffer with sampled sensor values.This buffer of sequential data sets is called the Time History Buffer. The amount of data requested from thebuffer is configurable by the user.

By transferring a set of data samples from the buffer to permanent memory, the processor can store data for aperiod before, during, or after an event. The operator can set the point before an event and the point after anevent to log the time history buffer to permanent memory. The maximum time stored by the processor that canbe held by the time history is two minutes.

7.1.4 Trend Monitoring

Engine trend information (data is compatible with P&WC ECTM®) is described as follows:

Autotrend: The ADASh can be configured to initiate an autotrend by defining a stable criteria consisting of upto ten (10) sensors. If the stable criteria are met, the ADASh will initiate a trend automatically.

7.2 System Initialization

The initialization sequence will proceed as follows:

When the processor’s power is first applied the system performs a series of self-tests. The following self-testsare performed during initialization:

Micro Controller Test

Temporary Memory Test

Data Log Memory Test

Program Integrity Test

7.3 System Modes

After Initialization, the processor will enter one of two primary system modes of operation: Run Mode, orConfiguration Mode. For data collection it is operated in Run mode. For communication through thedownload port with a laptop computer for the purposes of data transfer, it is in Configuration Mode.Configuration Mode is entered when a download cable is attached and the cable’s RUN/CONF switch is set toCONF. Run Mode is entered when the cable is not attached, or when it is attached and the RUN/CONF Switchis set to RUN.



7.4 Run Mode Description (States)

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

System States:

1. Normal

2. Maintenance

3. Caution

4. Fault

Definitions: In Normal state, the system is performing normally OR recorded an input programmed to indicate

Normal state.

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

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 to indicate Faultstate.

Trend Mode:The ADASh can be configured to take an automatic trend sample whenever certain engine/flight conditions aremet. Once the trend criteria are met, the system will collect a sample of data for later review by maintenancepersonnel.

Single/Dual Engine Functions:The ADASh monitoring system will monitor and record engine run, trend, cycle, and exceedance information forboth single and dual engine aircraft.



8 SYSTEM CONFIGURATION

The ADASh is a combination of hardware and software designed to have a wide range of application. In order tocorrectly operate with the specific aircraft type it is installed in, the system must first be configured to expect theparticular sensor and signal combinations available on that aircraft as well as the engine type and othernecessary information.

The installer, with the help of a computer and software communication tools, performs configuration andConfiguration. This requires a laptop computer connected to the system with a download cable and runningP&W Engine Services Monitor Link Program (MLP). The MLP gives field personnel the ability to monitorthe sensors in real time (Live Data Display) as well as to alter the configuration data stored by the system.

In addition to MLP, P&W Engine Services offers an Internet based data management and analysis system calledTurbineTracker™. MLP and TurbineTracker™ make it possible to quickly transfer and manage the aircraft’sconfiguration data, as well as operational data (log data) for fleet comparison and analysis. TheTurbineTracker™ website is located at www.turbinetracker.aero. To obtain a TurbineTracker™ useraccount and password, contact P&W Engine Services Help Desk.

Current manuals for both TurbineTracker and MLP are available through the TurbineTracker™ website. Thefollowing sections and instructions for configuration and calibration of the system require familiarity with theMLP and TurbineTracker™ manuals and software. While this section of the installation manual cannot replacethe software manuals, a few of the special terms and concepts used in the configuration and calibrationinstructions are briefly described in this manual. See the software manuals for full descriptions and proceduresfor use of the applicable software product.

8.1 Definitions

Configuration File: An MLP data file that contains engine and sensor information for a specific aircraft. Thisinformation is transmitted to the processor during configuration.

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

Live Data Display: An MLP mode of operation that presents periodically updated aircraft sensor readings inreal time. Live Data Display may be used in flight and on the ground when adjusting the calibration or testingand troubleshooting the system.

Log Data: The stored operational aircraft exceedance, event, cycle, and sensor readings collected by theprocessor. In normal aircraft use, the information gathering function of the system creates Log Data. This data isstored in raw form (a Log File) and can be extracted and further processed into useful information through MLPand TurbineTracker™.

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

MLU: (Monitor Link Unit): Files loaded into MLP that enables MLP to communicate with the ADASh.



One Point Offset Calibration (P2): A method that uses a single reading (or point) to correct (calibrate) asensor signal. A One Point Offset Calibration is a less precise offset method of calibration than a Two PointCalibration. A One Point Offset Calibration is used when the calibration occurs on the low end of a sensor’spotential operating range and a Two Point Calibration cannot be accomplished. To increase the useful precisionof the one point offset method, a reading at the low end of a sensor’s signal range is preferred. For example, if asensor reading is supposed to fall between 10 degrees and 100 degrees, a test reading at 20 degrees will calibratethe system better than one at 70 degrees. If a reading at 0 has been attempted as a One Point Offset Calibration,the system has not been usefully calibrated at all.

NOTE: The One Point Offset Calibration Method only ensures that the low end of a sensor signal’s rangeis calibrated. Never use 0 when accomplishing the One Point Offset Calibration Method.

One Point Slope Calibration (P1): A second method that uses a single reading (or point) to correct (calibrate)a sensor signal. A One Point Slope Calibration is a less precise method of calibration than a Two PointCalibration. A One Point Slope Calibration is used when the calibration occurs on the high end of a sensor’spotential operating range and a Two Point calibration cannot be accomplished. To increase the useful precisionof the one point slope method, a reading at the high end of a sensor’s signal range is preferred. For example, if asensor reading is supposed to fall between 100 and 500, a test reading at 400 will calibrate the system better thanone at 150. If a reading at 0 has been attempted as a One Point Slope Calibration, the system has not beenusefully calibrated at all.

NOTE: The One Point Slope Calibration Method only ensures that the high end of a sensor signal’srange is calibrated. Never use 0 when accomplishing the One Point Slope Calibration Method.

Two Point Calibration (P1 & P2): The most accurate method of calibration, requiring both a low and highvalue to correct (calibrate) a sensor signal. A Two Point Calibration occurs when calibration equipment or themanual sensor calibration methods are used. If a reading at 0 has been attempted as a Two Point Calibration,the system has not been usefully calibrated at all.

NOTE: The Two Point Calibration Method ensures that the low end AND high end of a sensor’s signalrange are calibrated. Never use 0 when accomplishing the Two Point Calibration Method.



8.2 Processor Configuration

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

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

010 Connect the download cable to the download port of the ADASh

to be configured. The cable can onlybe plugged in one way. Connect the other end of the cable to a laptop’s serial or USB port with thecurrent version of the MLP.

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

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

040 Select “Configure Unit” under the MLU Menu.

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

060 Select “Open”. (If you are prompted to retrieve the Log File, retrieve the log data from the processorfirst, and then select “Open.”)

8.2.1 System Checkout and Sensor Verification

After configuration, View Live Data to make sure that all the sensors are operating.

NOTE: Failed Sensors are displayed as 9999.9999. If unexpected values are displayed that are not9999.9999, that means that the sensor signal is being processed incorrectly.

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

NOTE: Although the data will be viewed in real time, the data is stored in a file for future reference.Live data updates once every second.

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


030 Establish a connection to the processor using MLP. If unable to establish a connection, proceed withthe MLP Troubleshooting Procedure in the MLP Manual (P&W Engine Services Monitor Link Program– MLP User’s Guide).

040 Select “Live Data” then “Text View”. Name the “Live Data” file and select “Save.”

050 When prompted by MLP, place the “RUN/CONF “switch in the “Run” position and click “OK.”

060 The sensor values will display and update once a second. A failed sensor will display 9999.9999.Troubleshoot failed sensors using ADAS

hInstructions for Continued Airworthiness Manual (ADHY-G-

260-1).

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

080 When prompted, place the “RUN/CONF” switch in the “CONF” position and click “OK.”



8.2.2 Calibration Using Test Equipment

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

The same test equipment that is used to check cockpit instruments can be used for calibrating the ADASh. Youcan calibrate the ITT sensor using a Barfield tester. The test equipment should be verified to be accurate.

NOTE: Opening MLP for a calibration session will increment the configuration file version by one. Anynumber of sensors may be calibrated during this session without increasing the version numberfurther. Opening, closing, and reopening MLP for calibration multiple times will increment theconfiguration file version each time a sensor is calibrated, and should be avoided.

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


030 Establish a connection to the processor using the MLP. If unable to establish a connection, proceedwith the MLP Troubleshooting Procedure in the MLP Manual (P&W Engine Services Monitor LinkProgram – MLP User’s Guide).

040 Select “Sensor Calibration” under the MLU Menu. Only the Engine Temperature sensors should becalibrated.

050 Select Engine Temperature and perform a Two Point Calibration using a Barfield tester. A value of300°C should be used for P1 and 700°C for P2.

NOTE: If ITT exceeds 700°C during calibration you may illuminate a lamp in the cockpit that willneed to be cleared.

060 After calibration, upload the new configuration file version to your TurbineTracker™ account. It isimportant to keep the processor, MLP, and Turbine Tracker™ configuration versions synchronized.



8.2.3 Calibration Using Aircraft Cockpit Instruments

These instructions require that the installer have a laptop computer with the current version of MLP and that theinstaller has created the required installation configuration file. The current version of MLP and its manual areavailable at the TurbineTracker™ website.

This procedure would be used if the ADASh Fuel Flow reading does not match the aircraft indicator. This willrequire the engines to be run at ground idle and a high power setting (takeoff power if able). These two pointswill be used to calibrate the fuel flow sensors as required.

NOTE: Opening MLP for a calibration session will increment the configuration file version by one. Anynumber of sensors may be calibrated during this session without increasing the version numberfurther. Opening, closing, and reopening MLP for calibration multiple times will increment theconfiguration file version each time a sensor is calibrated, and should be avoided.

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


030 Establish a connection to the processor using the MLP. If unable to establish a connection, proceedwith the MLP Troubleshooting Procedure in the MLP Manual (P&W Engine Services Monitor LinkProgram – MLP User’s Guide).

040 Select “Sensor Calibration” under the MLU Menu. Only the Fuel Flow sensors should be calibrated.

050 Start both Engines.

060 Select Fuel Flow and perform a Two Point Calibration. The Fuel Flow value at ground idle should beused for P1 and a high power setting (takeoff power if able) for P2.

070 After calibration, upload the new configuration file version to your TurbineTracker™ account. It isimportant to keep the processor, MLP, and Turbine Tracker™ configuration versions synchronized.



9 AIRCRAFT TESTING

While following the requirements of FAR 91.407, it is recommended that the aircraft be inspected forairworthiness prior to testing. If the ground and/or flight testing of the modified aircraft are not successfullycompleted, the aircraft should be returned to the original aircraft configuration until the tests are completed andacceptable.

After installation of the ADASh, it is recommended that a ground test be performed to verify the correctoperation of the system in the aircraft. The following sections outline the suggested aircraft and system testprocedures.9.1 Aircraft Ground Test

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

020 Power on all avionics

030 If aircraft is equipped with an Electronic Display Unit for engine and/or air data parameters verify thatthere is no interference caused by the ADAS

h

040 Tune Comm 1 and Comm 2 VHF radios to the frequencies in Table 4 and verify that there is nointerference caused by the ADAS

h. This can normally be conducted by checking for auto squelch

break on each listed frequency.

050 If interference is suspected at any particular frequency, pull the ADASh

circuit breaker to see if theinterference subsides

060 If the aircraft is equipped with a GPS navigation receiver, display the satellite status page and cyclepower on the ADAS

h.

070 Verify that the GPS signal strength is not affected by the operation of the ADASh

080 Tune the #1 and #2 VHF NAV receivers to receive a valid navigational signal from either a VORramp tester or a locally tuned VOR navigation transmitter

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

0100 Cycle power on the ADASh

and verify that there is no effect on the displayed NAV data

0110 If the aircraft is equipped with an autopilot, initiate autopilot self test. This may require pulling, andthen resetting the autopilot circuit breaker with power applied to the ADAS

h

0120 Verify that the autopilot completes a successful self-test.

0130 Survey the aircraft for any other installed equipment that may be affected by interference from theADAS

h. Perform any additional tests as required to determine if the ADAS

hcreates objectionable

interference. This may be accomplished by pulling the ADASh

circuit breaker while observing thesubject equipment. List the additional equipment tested and any observed effects in theElectromagnetic Compatibility Testing Table (See Table 5).

0140 Remove external power from aircraft and start engine.



Frequency Pass/Fail Frequency Pass/Fail

118.00 MHZ 127.00 MHZ

119.00 MHZ 128.00 MHZ

120.00 MHZ 129.00 MHZ

121.00 MHZ 130.00 MHZ

122.00 MHZ 131.00 MHZ

123.00 MHZ 132.00 MHZ

124.00 MHZ 133.00 MHZ

125.00 MHZ 134.00 MHZ

126.00 MHZ 135.00 MHZ

Table 4: VHF Frequency TableEngine Running:

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

020 Establish a connection to the ADASd

processor using MLP. If unable to establish a connection,proceed with the MLP Troubleshooting Procedure in the MLP Manual (P&W Engine ServicesMonitor Link Program – MLP User’s Guide).

NOTE: If a DTU is installed, then you must enter Transparent mode first to connect to the ADASd

processor.

030 Select “Live Data” then “Text View”. Name the “Live Data” file and select “Save.”

040 Start engine

050 If aircraft is equipped with an Electronic Display Unit for engine and air data parameters verify thatthere is no interference caused by the ADAS

h

060 With the engine running and the ADASh

system operational, tune Comm 1 and Comm 2 VHF radiosto the frequencies in Table 4 and verify that there is no interference caused by the ADAS

h. This can

normally be conducted by checking for auto squelch break on each listed frequency

070 If interference is suspected at any particular frequency, pull the ADASh

circuit breaker to see if theinterference subsides.

080 If the aircraft is equipped with a GPS navigation receiver, display the satellite status page and cyclepower on the ADAS

h.

090 Verify that the GPS signal strength is not affected by the operation of the ADASh

0100 Tune the #1 and #2 VHF NAV receivers to receive a valid navigational signal from either a VORramp tester or a locally tuned VOR navigation transmitter

0110 Verify that valid course deviation and a retracted NAV flag are displayed on the HIS or the VORcourse indicator.

0120 Cycle power on the ADASh

and verify that there is no effect on the displayed NAV data

0130 If the aircraft is equipped with an autopilot, initiate autopilot self test. This may require pulling, andthen resetting the autopilot circuit breaker with power applied to the ADAS

h

0140 Verify that the autopilot completes a successful self-test.



0150 Survey the aircraft for any other installed equipment that may be affected by interference from theADAS

h. Perform any additional tests as required to determine if the ADAS

hcreates objectionable

interference. This may be accomplished by pulling the ADASh

circuit breaker while observing thesubject equipment. List the additional equipment tested and any observed effects in theElectromagnetic Compatibility Testing Table (See Table 5).

0160 Stabilize the engine(s) at a convenient partial power setting.

0170 Once the engine readings are stabilized, write down the cockpit instrument values and the Live DataValues in the Ground Test Data Table (See Table 6).

0180 Stop Live Data and shut engines down.

NOTE: If a DTU is installed, you must Stop Live Data and then exit Transparent mode beforeshutting down the engine(s).

Equipment Problem FoundY/N?

CommentsGround Test

CommentsFlight Test

Table 5: Electromagnetic Compatibility Test Table

Comments:

Eng. #1 Eng. #2Ground Test

Cockpit ADASd

Delta Cockpit ADASd

Delta

ITT/TOT

N1/Ng/Nl

N2/Nh

Wf

Bus Voltage

Altitude

Airspeed

Table 6: Ground Test Data

Aircraft Make:

Aircraft Model:

Aircraft Registration Number:

Aircraft S/N:

Test Completed By:



9.2 Continued Airworthiness Instructions

See ADASh Instructions for Continued Airworthiness, ADHY-G-260-1 for troubleshooting the system. If yourequire further assistance, contact the Help Desk:

10 SERVICE

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

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

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

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

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



11 SPECIFICATIONS

11.1 System Specifications

GENERAL

Chassis Size (each): 3.7" x 1.7" x 6.6"

Chassis Weight: 1.4 lbs (22 oz.)

System Weight: Approximately 5 lbs.

POWER REQUIREMENTS

Voltage Range: 11 to 32 VDC

Current Draw < 1.0 A

Power Draw 8 Watts operating

20 mWatts standby

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

Test Performed RTCA Section Level

Temperature Section 4.0 Equipment tested to category C4

- Ground Survival Low Temperature Section 4.5.1 - 55 ºC

- Short Time Operational Low Temperature Section 4.5.1 - 40 ºC

- Operational Low Temperature Section 4.5.2 - 40 ºC

- Ground Survival High Temperature Section 4.5.3 + 85 ºC

- Short Time Operational High Temperature Section 4.5.3 + 85 ºC

- Operational High Temperature Section 4.5.4 + 70 ºC

Altitude Section 4.0 Equipment tested to category C4

- Test up to 55,000 ft Pressure Altitude Section 4.6.1 Equipment tested to category C4

- Decompression Test Section 4.6.2 Equipment tested to category C4

- Overpressure Test Section 4.6.3 Equipment tested to category C4

Temperature Variation Section 5.0 Equipment tested to category B, 5 ºC/Min

Humidity Section 6.0 Equipment tested to category B

Shock Section 7.0 Equipment tested to category B

- Operational Section 7.2 Equipment tested to category B

- Crash Safety Test Section 7.3 Equipment tested to category B

Vibration Section 8.0 Equipment tested to category SB

Explosion Proofness Section 9.0 Equipment tested to category E

Waterproofness Section 10.0 Equipment tested to category R

Fluids Susceptibility Section 11.0 Equipment tested to category F

Sand and Dust Section 12.0 Equipment tested to category D



Fungus Section 13.0 Equipment tested to category F

Salt Spray Section 14.0 Equipment tested to category S

Magnetic Effect Section 15.0 Equipment tested to category Z

Power Input Section 16.0 Equipment tested to category B

Voltage Spikes Section 17.0 Equipment tested to category B

Audio Freq. Susceptibility, Pwr In Section 18.0 Equipment tested to category B

Induced Signal Susceptibility Section 19.0 Equipment tested to category ZC

Radio Freq. Susceptibility Section 20.0 Equipment tested to category R

Radio Freq. Emission Section 21.0 Equipment tested to category L

Lighting Induced Transient Effects Section 22.0 Equipment tested to Category ZZC2

Lightning Direct Effect Section 23.0 Equipment tested to Category X

Electrostatic Discharge Section 25.0 Equipment tested to Category A

DATA INTERFACE

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

SYSTEM SOFTWARE

The ADASh

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

SAMPLE RATE

The ADASh

samples Engine Temperature up to 50 times per second. All other inputs are sampled up to 5 timesper second

DATA STORAGE

System Data: Installation ID / Version

Engine Run Data: Engine Run Date, Engine Run Time, Engine Run Duration, MaximumSensor Values Observed, Cycles Counted, Maximum Start Temp, MinimumBattery Voltage, Start Duration

Exceedance Data: Exceedance Date, Exceedance Time, Exceedance Duration, ExceedanceType, Maximum/Minimum Value Observed, Average Value Observed, TimeHistory Sensor Recording

Trend Sample: Auto Trend, Trend Time, Sensor Max Value Observed, Sensor AverageValue Observed

Flash Storage Memory: 8 MB (Log Data) and 24 MB (Continuous Recording)



11.2 Interface Requirements for Aircraft Sensors

FAULT/CAUTION LAMP

The ADASh may interface with an existing cockpit lamp.

The lamp shall have the following characteristics:

Nominal Voltage +28 VDC

Current 40 mA +/- 10%

Power Dissipation 1.24 Watts

Average Rated Life (0°C) 1,500 Hours

PILOT COMMAND SWITCHThe ADAS

hmay interface with an existing cockpit switch. The input shall have the following characteristics:

Parameter Specification Comments

Input Threshold 0 VDC

> 0 VDC

Switch Depressed

Switch Disengaged

POWER INPUT +28VDCThe ADAS

hrequires power via a 2 Amp circuit breaker, both installed in the Left Hand Circuit Breaker panel.

The input shall have the following characteristics:


Nominal +28 VDC

Typical 20 – 30 VDC

Minimum 11 VDC

Maximum 32 VDC

WEIGHT ON WHEELSThe ADAS

hrequires a discrete signal input to detect actuation of the aircraft hour meter or weight on wheels.

The input shall have the following characteristics:


Input Voltage Range 0 - 30.0 VDC

Input Threshold 5.0 VDC

< OR = 5.0 VDC



ENGINE – TEMPERATUREThe ADAS

hmeasures Engine Temperature using the aircraft’s existing Alumel/Chromel (Type K) assembly. The

input is isolated from ground and isolated from other instruments. The ADASh

measures Engine Temperaturewith the following specifications:


Input Range 0°C to 1098 °C

Accuracy +/- 5 °C Isolation Connections to the thermocoupleare isolated from ground to preventinterference from other indicators.

ENGINE - N1 GAS GENERATOR SPEED (PW535A)The ADAS

hmeasures N1 gas generator speed using the existing aircraft sensors installed on the engine.

Requirements and specs for the N1 sensor type are as follows:


Conversion 100% N1

Range 0 –150%

Voltage output at max engine speed 1.5 and 50 volts pk-pk.

Frequency output scaling 0-6340 Hzequiv 0-15850 RPM

DC Resistance at pins 1&2 and 3&4: 3000Ohms Max

Accuracy +/- 0.2%

Min Req 5%N1

ENGINE - N1 GAS GENERATOR SPEED (JT15D-5A)The ADAS




Conversion 100% N1

Range 0 –150%

Voltage output at max engine speed 5 and 20 volts pk-pk Linear to zero volts at zero speed

Frequency output Scaling 0-6360 HzEquiv 0-15900 RPM

Inductance 460 mH. Max. DC

Resistance 1400 Ohms Max

Accuracy +/- 0.2%

Min Req 5%N1



ENGINE - N1 GAS GENERATOR SPEED (JT15D-5D)The ADAS




Conversion 100% N1

Range 0 –150%





Accuracy +/- 0.2%

Min Req 5%N1

ENGINE – N2 POWER TURBINE SPEED (PW535A)The ADAS

hmeasures N2 power turbine speed using the existing aircraft sensors installed on the engine.



Conversion 100% N2

Range 0 –150%

Voltage output at max engine speed .75 and 50 volts pk-pk.

Frequency output scaling 0-7612 Hzequiv 0-33970 RPM

DC Resistance at pins 1&2 and 3&4: 3000Ohms Max

Accuracy +/- 0.2%

Min Req 5%N1

ENGINE – N2 POWER TURBINE SPEED (JT15D-5A, -5D)The ADAS

hmeasures N2 power turbine speed using the existing aircraft sensors installed on the engine.



Conversion 100% N2

Range 0 –150%





Accuracy +/- 0.2%

Min Req 5%N1



AIRCRAFT - FUEL FLOW SPEEDThe ADASh measures the Fuel Flow speed using the existing sensors installed on the airframe. Requirementsand specs for the Fuel Flow sensor type are as follows:


Range 0 – 1990 pph

Voltage output 0 – 5 VDC at linear flowrate

AIRCRAFT – AIRSPEEDThe ADASh measures the Airspeed using the existing sensors installed on the airframe. This sensor is on theARINC 429 Low Speed Bus and the specs are as follows:


Conversion 300 kn

ARINC Label 206

SDI 2

BNR Range 16384

Resolution .0625

AIRCRAFT – PRESSURE ALTITUDEThe ADASh measures the Pressure Altitude using the existing sensors installed on the airframe. This sensor ison the ARINC 429 Low Speed Bus and the specs are as follows:


Conversion 40,000 ft

ARINC Label 203

SDI 2

BNR Range 131072

Resolution 1

AIRCRAFT – TOTAL AIR TEMPERATUREThe ADASh measures the Total Air Temperature using the existing sensors installed on the airframe. Thissensor is on the ARINC 429 Low Speed Bus and the specs are as follows:


Conversion 10 °C

ARINC Label 211

SDI 2

BNR Range 2048

Resolution .25



12 Appendix A

12.1 ADASh Installation for 560 Encore & Ultra

Figure A- 1: ADASh

Installation for 560 Encore & Ultra – Sheet 1 of 5



Figure A- 2: ADASh




Figure A- 3: ADASh




Figure A- 4: ADASh




Figure A- 5: ADASh




12.2 ADASh Installation for 560 Ultra

Figure A- 6: ADASh

for 560 Ultra – Sheet 1 of 3



Figure A- 7: ADASh




Figure A- 8: ADASh




12.3 Circuit Breaker Installation

Figure A- 9: Circuit Breaker Installation – Sheet 1 of 4



12.4 Forward Pressure Bulkhead Connector

Figure A- 13: Forward Pressure Bulkhead Connector – Sheet 1 of 3



12.5 Circuit Breaker Connector

Figure A- 16: Circuit Breaker Connector – Sheet 1 of 3



12.6 Wire Routing for 560 Encore

Figure A- 19: Wire Routing for 560 Encore – Sheet 1 of 5



12.7 Wire Routing for 560 Ultra

Figure A- 24: Wire Routing for 560 Ultra – Sheet 1 of 5

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