adasd - turbinetracker c.pdf · 2006. 12. 1. · cessna model 560xl / xls daas-g-010-4 pratt &...

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

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

ADASd

Installation Manual

DAAS-G-010-4

For Cessna Model 560XL / XLS

Manual Number DAAS-G-010-4

Preparation Date: December 1, 2006 Prepared By: D Elsemiller

Release Date: March 5, 2007 S Sackos, Manager of Manufacturing Services

Revision Date: March 18, 2008 J Lukens, Manager of Applications Engineering

Revision Ltr: C

Pages: 64

Approvals:

P&W ENGINE SERVICES, INC. ADASd DAAS-G-010-4Cessna Model 560XL / XLS

DAAS-G-010-4 Pratt & Whitney Engine Services, Inc. Proprietary i

PREFACE

Disclaimer

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

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

dshould

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.


DAAS-G-010-4 Pratt & Whitney Engine Services, Inc. Proprietary - ii -

REVISION HISTORY

Rev C C C C C C C C C C C 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 CSheet 60 61 62 63 64

LOG OF REVISIONS

REV. NO ECO # DESCRIPTION DATE PAGES REVISED

X1 N/A Initial Draft 12/19/2006 All

X2 N/A Update as required from first installation. 01/24/2007 All

A N/A Initial Release 03/05/2007 Cover, ii, iv, 1, 3, 9, 12,13, 14-17, 19, 33, 34, 36

B N/A Add wire routing drawing and notes perFAA.

04/26/07 Cover, ii, iv, v, 14, 21,23, and 61-64.

C 939 / 943 Add 560XLS bulkhead, circuit breaker,and ADC connector numbers. Update

processor installation dimension. Updateparts list to include terminal lugs and 1 &2 amp circuit breaker (long neck). Update

Aircraft Testing Section. Correcttypographical errors. Update Company

Name and address info.

03/18/2008 All


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TABLE OF CONTENTS

1 INTRODUCTION ..................................................................................................................................... 11.1 Scope....................................................................................................................................................... 21.2 About This Manual ................................................................................................................................. 21.3 System Description ................................................................................................................................. 31.4 Unpacking the Equipment....................................................................................................................... 31.5 Parts List ................................................................................................................................................. 31.6 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 ADASd by Parts Kits....................................................................................................................... 72.2.2 Components by Kit.......................................................................................................................... 7

3 INSTALLATION – MECHANICAL ........................................................................................................ 93.1 System Processor .................................................................................................................................... 93.2 Circuit Breaker...................................................................................................................................... 133.3 Harness Installation............................................................................................................................... 14

3.3.1 “J1” Harness Installation............................................................................................................... 143.3.2 “Y” Cable Installation (Left Engine Diagnostic Port)................................................................... 163.3.3 “Y” Cable Installation (Right Engine Diagnostic Port) ................................................................ 17

4 INSTALLATION - ELECTRICAL......................................................................................................... 194.1 Airframe Components........................................................................................................................... 19

4.1.1 Primus 1000 Air Data Computer (Right ADC) ARINC429 Wiring ............................................. 194.2 Electrical Power.................................................................................................................................... 20

4.2.1 Bus (Switched) Power Connection ............................................................................................... 205 HARNESS CONNECTOR SIGNAL PINOUTS..................................................................................... 21

5.1 J1 Harness ............................................................................................................................................. 216 WIRING DIAGRAM............................................................................................................................... 22

6.1 ADASd Connection Chart..................................................................................................................... 226.2 Wiring Schematic ................................................................................................................................. 23

7 SYSTEM OPERATION OVERVIEW .................................................................................................... 247.1 ADASd Functional Description............................................................................................................. 24

7.1.1 Engine Run Logging ..................................................................................................................... 247.1.2 Cycle Logging ............................................................................................................................... 247.1.3 Event Monitoring and Time History Buffer.................................................................................. 257.1.4 Trend Monitoring .......................................................................................................................... 25

7.2 System Initialization ............................................................................................................................. 257.3 System Modes....................................................................................................................................... 257.4 Run Mode Description (States)............................................................................................................. 26

8 SYSTEM CONFIGURATION ................................................................................................................ 278.1 Definitions ............................................................................................................................................ 278.2 Processor Configuration ....................................................................................................................... 28

8.2.1 System Checkout and Sensor Verification.................................................................................... 289 AIRCRAFT TESTING ............................................................................................................................ 29


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9.1 Aircraft Ground Test............................................................................................................................. 299.2 Continued Airworthiness Instructions .................................................................................................. 31

10 WARRANTY AND SERVICE ............................................................................................................... 3210.1 Warranty ............................................................................................................................................... 3210.2 Customer Support ................................................................................................................................. 32

11 SPECIFICATIONS.................................................................................................................................. 3311.1 System Specifications ........................................................................................................................... 3311.2 Interface Requirements for Aircraft Sensors ........................................................................................ 35

12 APPENDIX A .......................................................................................................................................... 3612.1 ADASd / DTU Installation.................................................................................................................... 3612.2 ADASd (Stand-alone) Installation ........................................................................................................ 4412.3 Circuit Breaker Installation................................................................................................................... 5112.4 Pressure Bulkhead Connector ............................................................................................................... 5512.5 Circuit Breaker Connector .................................................................................................................... 5812.6 Wire Routing......................................................................................................................................... 61

LIST OF FIGURES

FIGURE 1: CESSNA MODEL 560XL/XLS ADASD SYSTEM ARCHITECTURE............................................................................... 3FIGURE 2: SINGLE OR DUAL WIRE SPLICES............................................................................................................................... 5FIGURE 3: SHIELDED CONNECTION (OUTER HEAT-SHRINK TUBING NOT SHOWN).................................................................... 5FIGURE 4: ADAS

DPROCESSOR ................................................................................................................................................. 9

FIGURE 5: BRACKET ASSEMBLY WITH DOWNLOAD PORT, RF SWITCH, AND SHOCK MOUNTS ............................................... 10FIGURE 6: DOWNLOAD AND RF SWITCH CABLES SECURED .................................................................................................... 10FIGURE 7: ADAS

DMOUNTING BRACKET (ADHY-D-026-1) .................................................................................................. 11

FIGURE 8: ADASD

INSTALLATION (ADASD

WITH DTU SHOWN) ............................................................................................ 11FIGURE 9: STANDALONE ADAS

DMOUNTING BRACKET (DPU-D-098-1) ............................................................................... 12

FIGURE 10: CIRCUIT BREAKER INSTALLATION........................................................................................................................ 13FIGURE 11: PRESSURE BULKHEAD CONNECTOR ..................................................................................................................... 15FIGURE 12: LEFT CIRCUIT BREAKER PANEL CONNECTOR....................................................................................................... 15FIGURE 13: GROUNDING STUD................................................................................................................................................ 15FIGURE 14: LEFT DIAGNOSTIC PORT (560XL SHOWN) ........................................................................................................... 16FIGURE 15: RIGHT DIAGNOSTIC PORT (560XL SHOWN) ......................................................................................................... 17FIGURE 16: LEFT AND RIGHT DIAGNOSTIC PORTS (MODEL 560XLS)..................................................................................... 18FIGURE 17: ARINC429 CONNECTIONS ................................................................................................................................... 19FIGURE 18: CIRCUIT BREAKER WIRING .................................................................................................................................. 20FIGURE 19: BUS BAR HC301 .................................................................................................................................................. 20FIGURE 20: ADAS

DWIRING SCHEMATIC ................................................................................................................................ 23

LIST OF TABLES

TABLE 1: VHF FREQUENCY TABLE......................................................................................................................................... 30TABLE 2: ELECTROMAGNETIC COMPATIBILITY TEST TABLE .................................................................................................. 31TABLE 3: GROUND TEST DATA ............................................................................................................................................... 31


DAAS-G-010-4 Pratt & Whitney Engine Services, Inc. Proprietary - v -

APPENDIX A

FIGURE A- 1: ADASD / DTU INSTALLATION – SHEET 1 OF 8................................................................................................... 36FIGURE A- 2: ADASD / DTU INSTALLATION – SHEET 2 OF 8................................................................................................... 37FIGURE A- 3: ADASD / DTU INSTALLATION – SHEET 3 OF 8................................................................................................... 38FIGURE A- 4: ADASD / DTU INSTALLATION – SHEET 4 OF 8................................................................................................... 39FIGURE A- 5: ADASD / DTU INSTALLATION – SHEET 5 OF 8................................................................................................... 40FIGURE A- 6: ADASD / DTU INSTALLATION – SHEET 6 OF 8................................................................................................... 41FIGURE A- 7: ADASD / DTU INSTALLATION – SHEET 7 OF 8................................................................................................... 42FIGURE A- 8: ADASD / DTU INSTALLATION – SHEET 8 OF 8................................................................................................... 43FIGURE A- 9: ADASD (STAND-ALONE) INSTALLATION – SHEET 1 OF 7................................................................................... 44FIGURE A- 10: ADASD (STAND-ALONE) INSTALLATION – SHEET 2 OF 7................................................................................. 45FIGURE A- 11: ADASD (STAND-ALONE) INSTALLATION – SHEET 3 OF 7................................................................................. 46FIGURE A- 12: ADASD (STAND-ALONE) INSTALLATION – SHEET 4 OF 7................................................................................. 47FIGURE A- 13: ADASD (STAND-ALONE) INSTALLATION – SHEET 5 OF 7................................................................................. 48FIGURE A- 14: ADASD (STAND-ALONE) INSTALLATION – SHEET 6 OF 7................................................................................. 49FIGURE A- 15: ADASD (STAND-ALONE) INSTALLATION – SHEET 7 OF 7................................................................................. 50FIGURE A- 16: CIRCUIT BREAKER INSTALLATION – SHEET 1 OF 4 .......................................................................................... 51FIGURE A- 17: CIRCUIT BREAKER INSTALLATION – SHEET 2 OF 4 .......................................................................................... 52FIGURE A- 18: CIRCUIT BREAKER INSTALLATION – SHEET 3 OF 4 .......................................................................................... 53FIGURE A- 19: CIRCUIT BREAKER INSTALLATION – SHEET 4 OF 4 .......................................................................................... 54FIGURE A- 20: PRESSURE BULKHEAD CONNECTOR – SHEET 1 OF 3 ........................................................................................ 55FIGURE A- 21: PRESSURE BULKHEAD CONNECTOR – SHEET 2 OF 3 ........................................................................................ 56FIGURE A- 22: PRESSURE BULKHEAD CONNECTOR – SHEET 3 OF 3 ........................................................................................ 57FIGURE A- 23: CIRCUIT BREAKER CONNECTOR – SHEET 1 OF 3.............................................................................................. 58FIGURE A- 24: CIRCUIT BREAKER CONNECTOR – SHEET 2 OF 3.............................................................................................. 59FIGURE A- 25: CIRCUIT BREAKER CONNECTOR – SHEET 3 OF 3.............................................................................................. 60FIGURE A- 26: WIRE ROUTING – SHEET 1 OF 4 ....................................................................................................................... 61FIGURE A- 27: WIRE ROUTING – SHEET 2 OF 4 ....................................................................................................................... 62FIGURE A- 28: WIRE ROUTING – SHEET 3 OF 4 ....................................................................................................................... 63FIGURE A- 29: WIRE ROUTING – SHEET 4 OF 4 ....................................................................................................................... 64

REFERENCE DOCUMENTS

DAAS-G-260-4 “ADASd Instructions for Continued Airworthiness”MLP User’s Guide “ P&W Engine Services Monitor Link Program”


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1 INTRODUCTION

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

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

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

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

The ADASd 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 theADASd 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 ADASd 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.

Many new aircraft and older aircraft with updated avionics have incorporated flat panel, glass or integratedcockpit displays. Analog information for engine and airframe parameters are collected and converted to serial(typically ARINC429) data which is then transmitted to these displays.

The ADASd is an enhancement to the P&W Engine Services generation III monitoring system. The ADASd

replaces signal conditioning circuitry with an ARINC429 serial interface for use on aircraft (fixed and rotarywing) where engine and airframe sensor information can be monitored from a single or multiple channelARINC429 data stream. The ADASd simplifies the interface to the aircraft by connecting, very simply, to theserial data bus on the aircraft and obtaining sensor information.



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 560XL / XLS.

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 ADASd on a Cessna Model 560XL / XLS.

Figure 1: Cessna Model 560XL/XLS ADASd

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 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.

1.6 Weight and Balance

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

ADASd Kit Weight lbs. Arm Moment inch-lbs/100DAAS-K-010-5 3.90 63.5 2.48DAAS-K-010-6 4.24 63.5 2.69



2 INSTALLATION AND MAINTENANCE PROCEDURES


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 tie holders,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 or avionicstechnicians shall perform the installation.

3. All aircraft systems interfacing with the P&W Engine Services ADASd 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, ormodifying the aircraft structure.

2.1.1 Procedure for Wiring Connections


The ADASd

cables have shields that connect to the processor chassis ground. Whenterminating the shielded harness at the airframe connection, these shields must betrimmed back 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 ADASd 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 ADASd Instructions for ContinuedAirworthiness, DAAS-G-260-4.

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

In the event that the ADASd must be returned for service, contact the Pratt & Whitney Engine Services, Inc.Help Desk for a Returned Material Authorization (RMA) number. When you receive the RMA number, includeit in the package 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 02062Phone: (781) 762-8600Fax: (781) 762-2287E-mail: [email protected]



2.2 Parts List

The parts listed below consist of the installation kits for the ADASd system for the Cessna Model 560XL / XLSaircraft. Assembly kit numbers are listed in Section 2.2.1 and individual components are detailed by kitnumbers in Section 2.2.2.

2.2.1 ADASd by Parts Kits

For Cessna Model 560XL / XLS (ADASd Only) Qty P/N DAAS-K-010-5

Processor Assembly Kit 1 DAAS-K-027-5Wiring Harness Kit 1 DAAS-K-028-4Additional Installation Materials Kit 1 DAAS-K-029-4

For Cessna Model 560XL / XLS(ADASd with DTU) Qty P/N DAAS-K-010-6

Processor Assembly Kit 1 DAAS-K-027-6Wiring Harness Kit 1 DAAS-K-028-4Additional Installation Materials Kit 1 DAAS-K-029-3

2.2.2 Components by Kit

PROCESSOR ASSEMBLY KIT DAAS-K-027-5

Processor DAAS-A-010-1 Qty 1Mounting Bracket DPU-D-098-1 Qty 1Bracket, Stringer ADASd DAAS-D-045-1 Qty 1Mount, Shock Grommet Isolator 990-00020 Qty 4Washer, Flat, #6 920-00006 Qty 4Nut, Locking, #6-32 MS21042-06 Qty 4Screw, #10-32 x ½” MS35207-263 Qty 10Strap, Ground DPU-C-050-1 Qty 1Washer, Flat 3/16” AN960-10 Qty 10Nut, Elastic Stop, 10-32 AN365-1032A Qty 6

PROCESSOR ASSEMBLY KIT DAAS-K-027-6

Processor DAAS-A-010-1 Qty 1Mounting Bracket ADHY-D-026-1 Qty 1Bracket, Stringer ADASd DAAS-D-045-1 Qty 1Mount, Shock Grommet Isolator 990-00020 Qty 4Washer, Flat, #6 920-00006 Qty 4Nut, Locking, #6-32 MS21042-06 Qty 4Screw, #10-32 x ½” MS35207-263 Qty 12Strap, Ground DPU-C-050-1 Qty 1Washer, Flat 3/16” AN960-10 Qty 12Assy., Port Download DPU-A-044-1 Qty 1Assy., Switch ADAS-A-011-1 Qty 1Nut, Elastic Stop, 10-32 AN365-1032A Qty 7Cover, Receptacle 990-00031 Qty 1Screw, #4-40 x ¼” 900-00003 Qty 1Clamp, Loop, Cush, ¼”, BLK MS21919DG4 Qty 1Grommet Strip MS22529/2-3R-10PK Qty 2”Cap, Lens - White 990-00127 Qty 1



WIRING HARNESS KIT DAAS-K-028-4

Harness, J1 External DAAS-C-046-1 Qty 1Cable, Y Citation Excel Eng 1 DAAS-C-047-1 Qty 1Cable, Y Citation Excel Eng 2 DAAS-C-049-1 Qty 1

ADDITIONAL MATERIAL INSTALLATION KIT DAAS-K-029-3

Breaker, 2 Amp 990-00131 Qty 1Screw, #4-40 x ¼” MS35206-213 Qty 4Wire, 24AWG, White M22759/16-24-9 Qty 3’Terminal, Ring #10 400-00030 Qty 3Terminal, Ring #8 400-00139 Qty 1Terminal, Ring #6 400-00029 Qty 2

ADDITIONAL MATERIAL INSTALLATION KIT DAAS-K-029-4

Breaker, 1 Amp 990-00130 Qty 1Screw, #4-40 x ¼” MS35206-213 Qty 4Wire, 24AWG, White M22759/16-24-9 Qty 3’Terminal, Ring #10 400-00030 Qty 3Terminal, Ring #8 400-00139 Qty 1Terminal, Ring #6 400-00029 Qty 2



3 INSTALLATION – MECHANICAL

3.1 System Processor

NOTE: For detailed ADASd

installation drawings on the Cessna Model 560XL / XLS 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: ADASd

Processor

The system processor is mounted on the forward top shelf of the avionics bay (between stations 60 – 65). TheADASd will not require access during normal operation.


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.

Installation Instructions for ADASd with DTU:

010 Reference Figure 5 and assemble the download port (DPU-A-044-1), RF Switch (ADAS-A-011-1),and Shock Mounts (990-00020) into the processor bracket (ADHY-D-026-1).

020 Secure the Download Port and RF Switch cables with provided clamp (MS21919DG4) and nut(AN365-1032A), as shown in Figure 6.

030 Reference Figure 7 and install the processor onto the bracket assembly with the supplied hardware.

040 Using the supplied plate (DAAS-D-045-1) as a template, mark and drill the location of the 6mounting holes (2 for each support beam).

050 Attach the supplied plate (DAAS-D-045-1) to the support beams using the supplied hardware.

060 Attach the processor and bracket that was just assembled onto the supplied plate (DAAS-D-045-1)(Figure 8) and ensure that the processor does not interfere with wiring or controls.

070 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: Bracket Assembly with Download Port, RF Switch, and Shock Mounts

Figure 6: Download and RF Switch Cables Secured



Figure 7: ADASd

Mounting Bracket (ADHY-D-026-1)

Figure 8: ADASd

Installation (ADASd

with DTU Shown)

Plate, Support(DAAS-D-045-1)



Installation Instructions for Standalone ADASd:

010 Reference Figure 9 and install the processor onto the bracket assembly with the supplied hardware.

020 Using the supplied plate (DAAS-D-045-1) as a template, mark and drill the location of the 6mounting holes (2 for each support beam).

030 Attach the supplied plate (DAAS-D-045-1) to the support beams using the supplied hardware.

040 Attach the processor and bracket that was just assembled onto the supplied plate (DAAS-D-045-1)and ensure that the processor does not interfere with wiring or controls.

050 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 9: Standalone ADASd

Mounting Bracket (DPU-D-098-1)



3.2 Circuit Breaker

NOTE: For detailed Circuit Breaker installation drawings on the Cessna Model 560XL / XLS refer toAppendix A, Section 12.3.

The 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 HC301, 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 10) in HC102 or another spare opening if HC102 is used.

030 Identify circuit breakers with proper markings.

Figure 10: Circuit Breaker Installation



3.3 Harness Installation

NOTE: For detailed Wiring Routing Drawings on the Cessna Model 560XL / XLS refer toAppendix A, Section 12.6.

Refer to Cessna Model 560XL Wiring Diagram Manual (Wiring – Maintenance Practices) Section20-10-01.

3.3.1 “J1” Harness Installation

The J1 external harness connects to the connector plug on the ADASd processor labeled J1. The harnessprovides aircraft bus power to the processor, as well as, air and engine data. The individual cables areappropriately labeled.

The ADASd 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 ADASd

processor.

020 Route the “AAV10A24” cable to the Bus Circuit Breaker located on the left circuit breaker panel.This will require going through existing connectors using spare pins on the forward pressurebulkhead connector (Figure 11 and Section 12.4) and circuit breaker panel connector (Figure 12 andSection 12.5). Refer to the wiring schematic in section 6.2 for 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 “AAB01B24” cable to the Primus 1000 (ADC) located on the right side of the avionics bay.Refer to the wiring schematic in Section 6.2.

040 Route the “AAB00B24” cable to the forward pressure bulkhead connector (Figure 11 and Section12.4). Refer to the wiring schematic in Section 6.2 for pin locations.

050 Route the “AAB02B24” cable to the forward pressure bulkhead connector (Figure 11 and Section12.4). Refer to the wiring schematic in Section 6.2 for pin locations.

060 Route the “AA00A24N” cable to an aircraft grounding stud (Figure 13). Refer to the wiringschematic in Section 6.2.



Figure 11: Pressure Bulkhead Connector Figure 12: Left Circuit Breaker Panel Connector

Figure 13: Grounding Stud



3.3.2 “Y” Cable Installation (Left Engine Diagnostic Port)

The DAAS-C-047-1 “Y” cable connects to the Left Engine Diagnostic Port located on the center console. Thiscable will connect in-line with the existing diagnostic port and will allow the ARINC429 engine data to berecorded by the ADASd.

010 Remove the Left Engine Diagnostic Port (GSE 9 Pin D-Sub) from the center console by removingthe two screws. See Figure 14 (560XL) or Figure 16 (560XLS).

020 Connect the Left Engine Diagnostic Port (GSE 9 Pin D-Sub) to the male 9 pin D-Sub on the “Y”cable (DAAS-C-047-1) and secure using supplied hardware (post and screw).

030 Secure the female 9 pin D-Sub on the “Y” cable (DAAS-C-047-1) to the center console using the twoscrews that were removed in step 010.

040 Route the “AAB00B24” cable (LFT Engine Data) to the forward pressure bulkhead connector (Figure11 and section 12.4). Refer to the wiring schematic in Section 6.2 for pin locations.

Figure 14: Left Diagnostic Port (560XL Shown)



3.3.3 “Y” Cable Installation (Right Engine Diagnostic Port)

The DAAS-C-049-1 “Y” cable connects to the Left Engine Diagnostic Port located on the center console. Thiscable will connect in-line with the existing diagnostic port and will allow the ARINC429 engine data to berecorded by the ADASd.

010 Remove the Right Engine Diagnostic Port (GSE 9 Pin D-Sub) from the center console by removingthe two screws. See Figure 15 (560XL) or Figure 16 (560XLS).

020 Connect the Right Engine Diagnostic Port (GSE 9 Pin D-Sub) to the male 9 pin D-Sub on the “Y”cable (DAAS-C-049-1) and secure using supplied hardware (post and screw).

030 Secure the female 9 pin D-Sub on the “Y” cable (DAAS-C-049-1) to the center console using the twoscrews that were removed in step 010.

040 Route the “AAB02B24” cable (RHT Engine Data) to the forward pressure bulkhead connector(Figure 11 and section 12.4). Refer to the wiring schematic in Section 6.2 for pin locations.

Figure 15: Right Diagnostic Port (560XL Shown)



Figure 16: Left and Right Diagnostic Ports (Model 560XLS)

Left Diagnostic PortRight Diagnostic Port



4 INSTALLATION - ELECTRICAL

The ADASd system consists of one external harness. The harness is appropriately labeled J1 and all wire usedmeet the specifications of MIL-C-27500.4.1 Airframe Components

4.1.1 Primus 1000 Air Data Computer (Right ADC) ARINC429 Wiring

The ADASd ARINC429 Rx channel 3 will connect to the low speed ADC ARINC429 output and will receive airdata (Pressure Altitude, True Airspeed, and Total Air Temperature).

010 Trim the “AAB01B24” cable to length.

020 Following the illustration (Figure 17), splice to the Right ADC ARINC429 signal using the pinconfiguration shown.

Color ADC – 560XL ADC – 560XLSWHT PN372 – Pin 60 PN342 – Pin 60WHT/BLU PN372 – Pin 61 PN342 – Pin 61

AIRCRAFT HARNESS SIG +

WHT

WIR

E

SHRINK SLEEVING" Pull Back and Cover Shield "

ARINC 429 Marked Cable

WHT/B

LUW

IRE

SIG -

ConnectorRAYCHEM SPLICE

Figure 17: ARINC429 Connections



4.2 Electrical Power


The “Bus” power supply must be chosen to provide power to the ADASd

through anentire engine’s running cycle. This is supplied by the “Essential Bus” directly controlledby the aircraft “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 othersharp objects 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 “AAV10A24” cable tolength.

020 Following illustration Figure 18, connect the wire to one side of the supplied breaker.

030 Connect the other end of the breaker to Bus Bar HC301 (Figure 19) on the Left Circuit BreakerPanel in the cockpit.

040 Secure all wiring.

Figure 18: Circuit Breaker Wiring

Figure 19: Bus Bar HC301

Bus BarHC301



5 HARNESS CONNECTOR SIGNAL PINOUTS


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 on the Cessna Model 560XL / XLS refer toAppendix A, Section 12.6.

Refer to Cessna Model 560XL Wiring Diagram Manual (Wiring – Maintenance Practices)Section 20-10-01

5.1 J1 Harness

Connector Pin Harness Wire Color Signal Name Wired To Section 6

1 COND CABLE (ADASd Only)J1 1 & 4 WHT 28 VDC Bus Aircraft Bus Pwr, 1 Amp CB

1 COND CABLE (ADASd with DTU)J1 1 & 4 WHT 28 VDC Bus Aircraft Bus Pwr, 2 Amp CB

1 COND CABLEJ1 3 WHT System Ground Aircraft Ground

2 COND CABLEJ1 13 WHT ARINC 1 RXHI LFT Airframe Diag Port (Pin 1)J1 14 WHT/BLU ARINC 1 RXLO LFT Airframe Diag Port (Pin 2)

2 COND CABLEJ1 15 WHT ARINC 2 RXHI RHT Airframe Diag Port (Pin 1)J1 16 WHT/BLU ARINC 2 RXLO RHT Airframe Diag Port (Pin 2)

2 COND CABLE (for 560XL)J1 17 WHT ARINC 3 RXHI ADC #2 PN 372 (Pin 60)J1 18 WHT/BLU ARINC 3 RXLO ADC #2 PN 372 (Pin 61)

2 COND CABLE (for 560XLS)J1 17 WHT ARINC 3 RXHI ADC #2 PN 342 (Pin 60)J1 18 WHT/BLU ARINC 3 RXLO ADC #2 PN 342 (Pin 61)



6 WIRING DIAGRAM

6.1 ADASd Connection Chart

Cessna Model 560XL / XLSSensor Wire Labels Aircraft Connection ADASd Connector

LFT CB Panel “Essential Bus” J1A/C Bus AAV10A24

Breaker HC102 – Bus Bar HC301 Pin 1 WHT & Pin 4 WHT

Aircraft Grounding Stud J1Aircraft Ground AA00A24N

Avionics Bay Pin 3 WHT

Right ADC – PN372 J1

Pin 60 Pin 17 WHTPrimus 1000ADC (560XL)

AAB01B24

Pin 61 Pin 18 WHT/BLU

Right ADC – PN342 J1

Pin 60 Pin 17 WHTPrimus 1000ADC (560XLS)

AAB01B24


Left Diagnostic Port (GSE Port) J1

Pin 1 Pin 13 WHTEngine 1 Data AAB00B24


Right Diagnostic Port (GSE Port) J1

Pin 1 Pin 15 WHTEngine 2 Data AAB02B24




6.2 Wiring Schematic

NOTE 1: Route wire in accordance with Cessna Model 560XL / XLS Wiring Diagram Manual (Wiring – Maintenance Practices) Section 20-10-01

Note 2: For detailed wire routing drawings on the Cessna Model 560XL / XLS refer to Appendix A, Section 12.6

129876543

COMM

MODE

DISC

3 4 5 6 7 8 9 1 2

ARINC

HI

COMM

MODE

DISC

ARINC

LO

BOOT

DISC

DISC

RTN

RX

RTN

TX

RTN

RX

SIG

TX

SIG

AAV10A24

129876543

AAB00B24

AAB02B24

345678912

3 4 5 6 7 8 9 1 2129876543

+28V BUS

28V RETURN

+28V BAT

ARINC1 RXHIARINC1 RXLO

ARINC3 RXHI

ARINC3 RXLO

ARINC2 RXLOARINC2 RXHI

J1-37 S

1718

1

3

4

1516

1413

6061

ENG #1 CenterConsole Test PortDAAS-C-047"Y" Cable

WHT

WHT/BLUARINC

HI

DISC

RTN

ARINC

LO

BOOT

DISC

RX

RTN

RX

SIG

WHTTX

RTN

WHT/BLU

TX

SIG

1 AMP CB (ADASd Only)or

2 AMP CB (ADASd with DTU)

ESSENTIAL BUS

HC 102

1 2

ENG #2 CenterConsole Test PortDAAS-C-049"Y" Cable

A A

ENG #1 Data - Ref. Cessna DwgConnector JC 039

DE

FG

C

DE

FG

C

PN372 (560XL)or

PN342 (560XLS)

JB324 PB324 (560XL)

WHTWHT

WHT/BLUWHT

WHT/BLUWHT

Ground Strap

To Processor Bracket

WHTAA00A24N

P10

ADASd PROCESSOR

DAAS-A-010-1

P5

P7

P9

P4P3

P6

P1P2

P8

J2 - Lemo

AAB02B24

AAB00B24

AAV10A24

NOTE: Use spare pinson CB panel connector.

PC104 JC104 (560XLS)

JC 039

ENG #2 Data - Ref. Cessna DwgConnector JF 038

JF 038

Aircraft Ground

LFT CB Panel

NOTE: Use spare pinson FWD pressurebulkhead connector.

Bus Bar HC301

PC010 JC010 (560XL)

JB334 PB334 (560XLS)

or

or

AAB01B24

Primus 1000"ADC"

WHT/BLU

WHT

Figure 20: ADASd

Wiring Schematic



7 SYSTEM OPERATION OVERVIEW

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

The ADASd 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 ADASd Functional Description

7.1.1 Engine Run Logging

The ADASd 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

ADASd 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 ADASd 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 ADASd 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 ADASd 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 ADASd 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 indicateNormal 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 ADASd 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 ADASd monitoring system will monitor and record engine run, trend, cycle, and exceedance information forboth single and dual engine aircraft.



8 SYSTEM CONFIGURATION

The ADASd 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 ADASd.



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 ADASd

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.

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

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

dInstructions for Continued Airworthiness Manual (DAAS-G-

260-4).

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.”



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 ADASd, 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 air data parameters verify thatthere is no interference caused by the ADAS

d

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

d. 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 ADASd

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

d.

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

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

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

100 Cycle power on the ADASd

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

110 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

d

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

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

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

dcreates objectionable

interference. This may be accomplished by pulling the ADASd

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



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 1: 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 Services MonitorLink Program – MLP User’s Guide).

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

dprocessor.

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

d

060 With the engine running and the ADASd

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

d. 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 ADASd

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

d.

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

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

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

120 Cycle power on the ADASd

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

130 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

d



140 Verify that the autopilot completes a successful self-test

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

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

dcreates objectionable

interference. This may be accomplished by pulling the ADASd

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

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

170 Once the engine readings are stabilized, write down the cockpit instrument values and the Live DataValues in the Ground Test Data Table (See Table 3).

180 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 Found Y/N? Comments Ground Test

Table 2: Electromagnetic Compatibility Test Table

Comments:

Eng. #1 Eng. #2Ground Test

Cockpit ADASd

Delta Cockpit ADASd

Delta

ITT/TOT

N1/Ng/Nl

N2/Nh

Bus Voltage

Altitude

Airspeed

Table 3: Ground Test Data

Aircraft Make:

Aircraft Model:

Aircraft Registration Number:

Aircraft S/N:

Test Completed By:

9.2 Continued Airworthiness Instructions

See ADASd Instructions for Continued Airworthiness, DAAS-G-260-4 for troubleshooting the system. If yourequire further assistance, contact the Help Desk:



10 WARRANTY AND SERVICE

10.1 Warranty

The Pratt & Whitney Engine Services, Inc. ADASd is warranted against defects in materials and workmanshipfor two (2) years from date of purchase. Pratt & Whitney Engine Services, Inc. will, at its option, rebuild orreplace without charge those products that it finds defective. Pratt & Whitney Engine Services, Inc. will not beresponsible for damage caused by improper installation, unauthorized maintenance, abuse, or costs incurred dueto operator troubleshooting. No other warranty is expressed or implied. Pratt & Whitney Engine Services, Inc.is not liable for consequential damages.10.2 Customer Support

Pratt & Whitney Engine Services, Inc. provides customer support in accordance with the product warrantydetailed within the customer’s sales contract. If you have any questions concerning any Pratt & Whitney EngineServices, Inc. product, please do not hesitate to contact us. Our Help Desk accepts calls Monday throughFriday between 9:00 AM and 5:00 PM EST. Please have your model and serial number ready when you call.

Pratt & Whitney Engine Services, Inc.Help Desk249 Vanderbilt Ave.Norwood, MA 02062Phone: (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 D3

- Ground Survival Low Temperature Section 4.5.1 - 55 ºC

- Short Time Operational Low Temperature Section 4.5.1 - 55 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 D3

- Test up to 55,000 ft Pressure Altitude Section 4.6.1 Equipment tested to category D3

- Decompression Test Section 4.6.2 Equipment tested to category D3

- Overpressure Test Section 4.6.3 Equipment tested to category D3

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 R

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 B3F3

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 Interface, 57,600 Baud

SYSTEM SOFTWARE

The ADASd

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

SAMPLE RATE

The ADASd

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 ADASd 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 SWITCH

The ADASd

may 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 +28VDC

The ADASd

requires power via a 2 Amp circuit breaker, both installed in the Left Hand Circuit Breaker panel.The input shall have the following characteristics:

Parameter Specification Comments

Nominal +28 VDC

Typical 20 – 30 VDC

Minimum 11 VDC

Maximum 32 VDC



12 APPENDIX A

12.1 ADASd / DTU Installation

Figure A- 1: ADASd

/ DTU Installation – Sheet 1 of 8



Figure A- 2: ADASd




Figure A- 3: ADASd




Figure A- 4: ADASd




Figure A- 5: ADASd




Figure A- 6: ADASd




Figure A- 7: ADASd




Figure A- 8: ADASd




12.2 ADASd (Stand-alone) Installation

Figure A- 9: ADASd

(Stand-alone) Installation – Sheet 1 of 7



Figure A- 10: ADASd




Figure A- 11: ADASd




Figure A- 12: ADASd




Figure A- 13: ADASd




Figure A- 14: ADASd




Figure A- 15: ADASd




12.3 Circuit Breaker Installation

Figure A- 16: Circuit Breaker Installation – Sheet 1 of 4



12.4 Pressure Bulkhead Connector

Figure A- 20: Pressure Bulkhead Connector – Sheet 1 of 3



12.5 Circuit Breaker Connector

Figure A- 23: Circuit Breaker Connector – Sheet 1 of 3



12.6 Wire Routing

Figure A- 26: Wire Routing – Sheet 1 of 4

adasd - turbinetracker c.pdf · 2006. 12. 1. · cessna model 560xl / xls daas-g-010-4 pratt &...

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