p&w engine services, inc. adas daas-g-010-5 · exceedance event recording: the adasd can...

P&W ENGINE SERVICES, INC. ADASd DAAS-G-010-5Hawker Beechcraft Models B200 ; B200C ; 300 ; B300 ; B300C

DAAS-G-010-5 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. ADASd shouldnot be used as a primary guide monitoring the Aircraft and Engine manufacturers operating limits. Pratt & Whitney EngineServices, Inc. is not liable for any damages resulting from the use of this product.


DAAS-G-010-5 Pratt & Whitney Engine Services, Inc. Proprietary ii

REVISION HISTORY

Rev Statusof Sheets

Rev B C B B B B B B B B B B B B B BSheet i ii iii iv v 1 2 3 4 5 6 7 8 9 10 11Rev B B B B B B B B B B B B C B B BSheet 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27Rev B B B B B B B B B B B B B B B BSheet 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43Rev B B B B B B B B B B B B B B B BSheet 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59Rev B B B B B B B B B B B B B B B BSheet 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75Rev B B BSheet 76 77 78

LOG OF REVISIONS

REV. NO ECO # DESCRIPTION DATE PAGES REVISED

A N/A Initial Release 9/22/2008 All

B N/A Update Aircraft Models to B200, B200C,300, B300, B300C

01/13/2010 All

C 1140 Correct Fault Lamp ConXall ConnectorPinout (Discrete Mount)

10/03/2012 Cover, ii, 24


DAAS-G-010-5 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 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 Pressure Bulkhead Fitting .............................................................................................................. 113.3 Cockpit Components...................................................................................................................... 13

3.3.1 TREND Switch / Fault Lamp and Download Port ...................................................................... 133.3.2 Circuit Breaker – Essential Bus.................................................................................................. 153.3.3 Circuit Breaker – Battery Bus .................................................................................................... 15

3.4 Harness Installation........................................................................................................................ 183.4.1 “J1” Harness Installation............................................................................................................ 183.4.2 “J2” Harness Installation............................................................................................................ 18

4 INSTALLATION - ELECTRICAL......................................................................................................... 194.1 Cockpit Components...................................................................................................................... 194.2 Airframe Components .................................................................................................................... 21

4.2.1 Pro Line 21 – L-GP-5 ARINC429 Wiring .................................................................................. 214.2.2 Pro Line 21 – L-DCU-3 HS 429 ARINC429 Wiring .................................................................. 21

4.3 Electrical Power ............................................................................................................................. 224.3.1 Battery Power Connection ......................................................................................................... 224.3.2 Bus (Switched) Power Connection ............................................................................................. 22

4.4 Final Installation Notes .................................................................................................................. 235 HARNESS CONNECTOR SIGNAL PINOUTS ..................................................................................... 24

5.1 J1 Harness ..................................................................................................................................... 245.2 J2 Harness ..................................................................................................................................... 25

6 WIRING DIAGRAM.............................................................................................................................. 266.1 ADASd Connection Chart.............................................................................................................. 266.2 Wiring Schematic – B200 and B200C (Center Console Mount) ...................................................... 276.3 Wiring Schematic – B200 and B200C (Discrete Mount)................................................................. 286.4 Wiring Schematic – 300, B300, and B300C (Center Console Mount) ............................................. 296.5 Wiring Schematic – 300, B300, and B300C (Discrete Mount) ........................................................ 30

7 SYSTEM OPERATION OVERVIEW .................................................................................................... 317.1 ADASd Functional Description ...................................................................................................... 31

7.1.1 Engine Run Logging .................................................................................................................. 317.1.2 Cycle Logging ........................................................................................................................... 317.1.3 Event Monitoring and Time History Buffer ................................................................................ 32


DAAS-G-010-5 Pratt & Whitney Engine Services, Inc. Proprietary iv

7.1.4 Trend Monitoring ...................................................................................................................... 327.2 System Initialization and Lamp State Description........................................................................... 327.3 System Modes................................................................................................................................ 337.4 Run Mode Description (States)....................................................................................................... 33

8 SYSTEM CONFIGURATION................................................................................................................ 358.1 Definitions ..................................................................................................................................... 358.2 Processor Configuration................................................................................................................. 36

8.2.1 System Checkout and Sensor Verification.................................................................................. 369 AIRCRAFT TESTING ........................................................................................................................... 37

9.1 Aircraft Ground Test ...................................................................................................................... 379.2 Continued Airworthiness Instructions............................................................................................. 40

10 SERVICE .......................................................................................................................................... 4110.1 Customer Support .......................................................................................................................... 41

11 SPECIFICATIONS............................................................................................................................ 4211.1 System Specifications .................................................................................................................... 4211.2 Interface Requirements for Aircraft Sensors ................................................................................... 44

12 Appendix A........................................................................................................................................ 4512.1 ADASd Installation........................................................................................................................ 4512.2 Pressure Bulkhead Fitting .............................................................................................................. 5012.3 TREND / Switch Fault Lamp and Download Port (Discrete Mount Option).................................... 5412.4 TREND / Switch Fault Lamp and Download Port (Center Console Option).................................... 5812.5 Circuit Breaker Installation (Essential Bus) .................................................................................... 6212.6 Circuit Breaker Installation for B200, B200C (Battery Bus) ........................................................... 6512.7 Circuit Breaker Installation for 300, B300, B300C (Battery Bus).................................................... 6812.8 Wire Routing for B200, B200C...................................................................................................... 7112.9 Wire Routing for 300, B300, B300C .............................................................................................. 75

LIST OF FIGURES

Figure 1: Hawker Beechcraft Model 200 & 300 Series ADASd System Architecture ......................................... 3Figure 2: Single or Dual Wire Splices ............................................................................................................... 5Figure 3: Shielded connection (Outer Heat-Shrink Tubing Not Shown)............................................................. 5Figure 4: ADASd Processor .............................................................................................................................. 9Figure 5: ADASd Mounting Bracket (DPU-A-082-1) ...................................................................................... 10Figure 6: Processor to Bracket Installation ...................................................................................................... 10Figure 7: ADASd Installation Location ........................................................................................................... 10Figure 8: Typical Clear Bay Areas of Fwd Pressure Bulkhead (looking aft)..................................................... 11Figure 9: Typical Pressure Bulkhead Fitting Installation.................................................................................. 12Figure 10: Typical Discrete Component Mount Installation............................................................................. 13Figure 11: Center Console Mount Assembly ................................................................................................... 14Figure 12: Center Console Mount – Typical Installation.................................................................................. 14Figure 13: Copilot Circuit Breaker Panel......................................................................................................... 15Figure 14: Battery/Emergency Bus Access Panel ............................................................................................ 16Figure 15: A228 Box Assembly – Battery Power Bus ..................................................................................... 16Figure 16: Pilot Circuit Breaker Panel............................................................................................................. 17Figure 17: TREND Switch / Fault Lamp and Download Port Connector Wiring.............................................. 19Figure 18: TREND Switch and Lamp Connector Wiring................................................................................. 20Figure 19: Download Port Connector .............................................................................................................. 20Figure 20: ARINC429 Connections ................................................................................................................ 21Figure 21: Circuit Breaker Wiring................................................................................................................... 22Figure 22: ADASd Wiring Schematic – B200 and B200C (Center Console Mount) ......................................... 27


DAAS-G-010-5 Pratt & Whitney Engine Services, Inc. Proprietary v

Figure 23: ADASd Wiring Schematic – B200 and B200C (Discrete Mount).................................................... 28Figure 24: ADASd Wiring Schematic – 300, B300, and B300C (Center Console Mount) ................................ 29Figure 25: ADASd Wiring Schematic – 300, B300, and B300C (Discrete Mount) ........................................... 30

LIST OF TABLES

Table 1: ADASd Connection Chart.................................................................................................................. 26Table 2: VHF Frequency Table....................................................................................................................... 38Table 3: Electromagnetic Compatibility Test Table......................................................................................... 39Table 4: Ground Test Data.............................................................................................................................. 39

APPENDIX A

Figure A- 1: ADASd Installation – Sheet 1 of 5............................................................................................... 45Figure A- 2: ADASd Installation – Sheet 2 of 5............................................................................................... 46Figure A- 3: ADASd Installation – Sheet 3 of 5............................................................................................... 47Figure A- 4: ADASd Installation – Sheet 4 of 5............................................................................................... 48Figure A- 5: ADASd Installation – Sheet 5 of 5............................................................................................... 49Figure A- 6: Pressure Bulkhead Fitting – Sheet 1 of 4 ..................................................................................... 50Figure A- 7: Pressure Bulkhead Fitting – Sheet 2 of 4 ..................................................................................... 51Figure A- 8: Pressure Bulkhead Fitting – Sheet 3 of 4 ..................................................................................... 52Figure A- 9: Pressure Bulkhead Fitting – Sheet 4 of 4 ..................................................................................... 53Figure A- 10: TREND / Switch Fault Lamp and Download Port (Discrete Mount Option) – Sheet 1 of 4 ........ 54Figure A- 11: TREND / Switch Fault Lamp and Download Port (Discrete Mount Option) – Sheet 2 of 4 ........ 55Figure A- 12: TREND / Switch Fault Lamp and Download Port (Discrete Mount Option) – Sheet 3 of 4 ........ 56Figure A- 13: TREND / Switch Fault Lamp and Download Port (Discrete Mount Option) – Sheet 4 of 4 ........ 57Figure A- 14: TREND / Switch Fault Lamp and Download Port (Center Console Option) – Sheet 1 of 4......... 58Figure A- 15: TREND / Switch Fault Lamp and Download Port (Center Console Option) – Sheet 2 of 4......... 59Figure A- 16: TREND / Switch Fault Lamp and Download Port (Center Console Option) – Sheet 3 of 4......... 60Figure A- 17: TREND / Switch Fault Lamp and Download Port (Center Console Option) – Sheet 4 of 4......... 61Figure A- 18: Circuit Breaker Installation (Essential Bus) – Sheet 1 of 3 ......................................................... 62Figure A- 19: Circuit Breaker Installation (Essential Bus) – Sheet 2 of 3 ......................................................... 63Figure A- 20: Circuit Breaker Installation (Essential Bus) – Sheet 3 of 3 ......................................................... 64Figure A- 21: Circuit Breaker Installation for B200, B200C (Battery Bus) – Sheet 1 of 3 ................................ 65Figure A- 22: Circuit Breaker Installation for B200, B200C (Battery Bus) – Sheet 2 of 3 ................................ 66Figure A- 23: Circuit Breaker Installation for B200, B200C (Battery Bus) – Sheet 3 of 3 ................................ 67Figure A- 24: Circuit Breaker Installation for 300, B300, B300C (Battery Bus) – Sheet 1 of 3 ........................ 68Figure A- 25: Circuit Breaker Installation for 300, B300, B300C (Battery Bus) – Sheet 2 of 3 ........................ 69Figure A- 26: Circuit Breaker Installation for 300, B300, B300C (Battery Bus) – Sheet 3 of 3 ........................ 70Figure A- 27: Wire Routing for B200, B200C – Sheet 1 of 4........................................................................... 71Figure A- 28: Wire Routing for B200, B200C – Sheet 2 of 4........................................................................... 72Figure A- 29: Wire Routing for B200, B200C – Sheet 3 of 4........................................................................... 73Figure A- 30: Wire Routing for B200, B200C – Sheet 4 of 4........................................................................... 74Figure A- 31: Wire Routing for 300, B300, B300C – Sheet 1 of 4 ................................................................... 75Figure A- 32: Wire Routing for 300, B300, B300C – Sheet 2 of 4 ................................................................... 76Figure A- 33: Wire Routing for 300, B300, B300C – Sheet 3 of 4 ................................................................... 77Figure A- 34: Wire Routing for 300, B300, B300C – Sheet 4 of 4 ................................................................... 78

REFERENCE DOCUMENTS

DAAS-G-260-5 “ADASd Instructions for Continued Airworthiness”MLP User’s Guide “P&W Engine Services Monitor Link Program”


DAAS-G-010-5 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 ADASd to perform two primary functions:

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.

Cockpit Indication: The ADASd can be configured to warn the pilot of a prior exceedenc on start up orshutdown, and provide system self-test indication.

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.

Manual Operation: The pilot can quickly record a dataset from all sensors by pressing a cockpit-mountedTREND switch.

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 to the serial data buson 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 HawkerBeechcraft Models B200, B200C, 300, B300, and B300C aircraft equipped with the Rockwell Collins Pro Line21, Integrated Display System (IDS).

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 1 shows the architecture of the ADASd on a Hawker Beechcraft Model 200 & 300 series aircraftequipped with the Rockwell Collins Pro Line 21, Integrated Display System (IDS).

Figure 1: Hawker Beechcraft Model 200 & 300 Series 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. Althoughthe system weight is less than 6 pounds (excluding miscellaneous hardware not supplied with the kit – e.g.clamps, tie wraps, etc.), P&W Engine Services suggests that the installer weigh each kit individually and recordthe weight prior to installation. During the installation, save all items that are not installed on the aircraft, forexample: cable that has been trimmed to length and any plastic or paper bags that individual components werepackaged in. After the completion of the installation, weigh all materials that were not installed on the aircraft.Subtract this weight from the weight of the kit prior to the installation. This will give you the total systemweight that is installed on the aircraft. The information needed is shown below:

ADASd Kit Weight lbs. ArmDAAS-K-010-8 5.61 74DAAS-K-010-10 5.61 74DAAS-K-010-11 5.36 74DAAS-K-010-12 5.36 74

NOTE: Arm location is for typical installations only and should be verified at time of install.



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-260-5.

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 Hawker Beechcraft Model200 & 300 Series aircraft. Assembly kit numbers are listed in Section 2.2.1 and individual components aredetailed by kit numbers in Section 2.2.2.

2.2.1 ADASd by Parts Kits

For Hawker Beechcraft Models B200, B200C, 300, B300, B300C (ADASd Only)With Pedestal Display Qty P/N DAAS-K-010-8

Processor Assembly Kit 1 DAAS-K-027-3Center Console Mount Kit 1 TWIN-K-027-2Wiring Harness Kit 1 DAAS-K-028-2Additional Installation Materials Kit 1 DAAS-K-029-5

For Hawker Beechcraft Models B200, B200C, 300, B300, B300C (ADASd with DTU)With Pedestal Display Qty P/N DAAS-K-010-10

Processor Assembly Kit 1 DAAS-K-027-3Center Console Mount Kit 1 TWIN-K-027-2Wiring Harness Kit 1 DAAS-K-028-2Additional Installation Materials Kit 1 DAAS-K-029-6

For Hawker Beechcraft Models B200, B200C, 300, B300, B300C (ADASd Only)With Individual Display Qty P/N DAAS-K-010-11

Processor Assembly Kit 1 DAAS-K-027-3Cockpit Fault Lamp and Download Port Kit 1 DPU-K-046-3Wiring Harness Kit 1 DAAS-K-028-2Additional Installation Materials Kit 1 DAAS-K-029-5

For Hawker Beechcraft Models B200, B200C, 300, B300, B300C (ADASd with DTU)With Individual Display Qty P/N DAAS-K-010-12

Processor Assembly Kit 1 DAAS-K-027-3Cockpit Fault Lamp and Download Port Kit 1 DPU-K-046-3Wiring Harness Kit 1 DAAS-K-028-2Additional Installation Materials Kit 1 DAAS-K-029-6

2.2.2 Components by Kit

PROCESSOR ASSEMBLY KIT DAAS-K-027-3

Processor DAAS-A-010-1 Qty 1Mounting Bracket DPU-A-082-1 Qty 1Shock Mount, Shock Grommet Isolators, Lord 990-00020 Qty 4Washer, Processor MountFlat, #6 920-00006 Qty 4Nut, Locking, Processor Mount#6-32 MS21042-06 Qty 4Screw, #10-32 x 3/8 MS35207-261 Qty 6Strap, Ground DPU-C-050-1 Qty 1Insert NAS1836-3-09 Qty 6Washer, Flat 3/16” AN960-10 Qty 6

CENTER CONSOLE MOUNT KIT TWIN-K-027-2

Assy., Cockpit Trend Switch TWIN-A-064-2 Qty 1Connector, Hi-Density MS24308/2-11F Qty 1Backshell 400-00038 Qty 1Screw, Lock Post 990-00052 Qty 1



COCKPIT FAULT LAMP AND DOWNLOAD PORT KIT DPU-K-046-3

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

WIRING HARNESS KIT DAAS-K-028-2

Cable AssyHarness, J1 External DAAS-C-038-1 Qty 1HarnessCable Assy, J2 External DAAS-C-039-1 Qty 1

ADDITIONAL MATERIAL INSTALLATION KIT DAAS-K-029-5

Doubler, Pressure Bulkhead ADAS-D-059-1 Qty 1Grommet, Pressure Bulkhead 990-00035 Qty 1Breaker, 1 Amp 990-00032 Qty 2Terminal, Ring #10 400-00030 Qty 3Terminal, Ring #8 400-00139 Qty 1Terminal, Ring #6 400-00029 Qty 4

ADDITIONAL MATERIAL INSTALLATION KIT DAAS-K-029-6

Doubler, Pressure Bulkhead ADAS-D-059-1 Qty 1Grommet, Pressure Bulkhead 990-00035 Qty 1Breaker, 2 Amp 990-00041 Qty 1Breaker, 1 Amp 990-00032 Qty 1Terminal, Ring #10 400-00030 Qty 3Terminal, Ring #8 400-00139 Qty 1Terminal, Ring #6 400-00029 Qty 4



3 INSTALLATION – MECHANICAL

3.1 System Processor

NOTE: For detailed ADASd

installation drawings on the Hawker Beechcraft Model 200 & 300 Series referto Appendix A, Section 12.1.

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 left forward top shelf of the avionics bay (Fuselage Station 74.0) usingthe supplied mounting bracket (Figure 5). The ADASd will not require access during normal operation.


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 Assemble the ADASd

processor to the mounting bracket shown in Figure 6 and test fit in a proper

location within the aircraft (Figure 7) to ensure that the processor does not interfere with wiring orcontrols.

020 When a location has been determined for the ADASd, mark the location of the 6 mounting holes and

drill to accommodate a potted-in style insert.

030 Remove a ¼ inch of the adjacent core material without damaging the panel skins.

040 Clean out all loose material.

050 Using Dexter / Hysol’s EA934NA epoxy paste adhesive, or equivalent, completely fill each section ofPanel where the honeycomb (core) was removed around the insert.

The requirements for a suitable equivalent paste adhesive are:

1. A pot life long enough to perform the assembly.2. Sag resistance (thixotropic).3. A room temperature cure.4. An adhesive appropriate for aircraft structural metal bonding with mechanical properties equal

to or greater than EA 934NA.

060 With the inserts installed allow the adhesive to cure.

070 Mount the system processor and bracket to the aircraft using the provided hardware.

080 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: ADASd

Mounting Bracket (DPU-A-082-1)

Figure 6: Processor to Bracket Installation

Figure 7: ADASd

Installation Location

ADASdNo. 1 DCUConnector 7710P1



3.2 Pressure Bulkhead Fitting

NOTE: For detailed Pressure Bulkhead Fitting installation drawings on the Hawker Beechcraft Model 200& 300 Series refer to Appendix A, Section 12.2.

The ADASd uses a Raychem™ pressure bulkhead fitting for routing the harnesses into the aircraft, as shown inFigure 9. Depending on the aircraft and what equipment is installed you may or may not need a doubler(ADAS-D-059-1). Reference Figure 8 for typical clear bay areas numbered 1 through 22.

Installation Caution:

No doubler is required if installing the feed through in bay 11, 12, 13, or 14. Any otherclear bay indicated in Figure 8 requires the supplied doubler. If a doubler already existson the bulkhead it may be used in place of the supplied doubler.

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

Maintain .25” edge distance between doubler outer circumference and pressurebulkhead supporting structure and/or pressure bulkhead bonded doublers (bay locationsother then 11 through 14).

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

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

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

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

Figure 8: Typical Clear Bay Areas of Fwd Pressure Bulkhead (looking aft)



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

010 Drill a 1.34” hole into the pressure bulkhead in bay 11, 12, 13, or 14 as specified in Figure 8 or anyother bay if a doubler already exists.

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

Pressure Bulkhead Connector Installation in Any Bay Except 11, 12, 13, or 14 and doubler does notalready exists:

010 Using the doubler (ADAS-D-059-1) as a guide, mark and drill 12 #21 holes through a clear bay onthe forward pressure bulkhead.

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

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

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

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

Figure 9: Typical Pressure Bulkhead Fitting Installation

PressureBulkhead Fitting



3.3 Cockpit Components

The following is the description and function of the cockpit components and indicator

3.3.1 TREND Switch / Fault Lamp and Download Port

The ADASd has a single TREND Switch / Fault lamp and download port (Figure 10 and Figure 11). TheTREND switch consists of a .75˝ x .75˝ square push-to-test combination lamp and the download port consist of a 19/32” serial download connector. The TREND switch/fault lamp, download port, and connector are availablein a pre-wired center-console mount assembly (TWIN-A-064-2), or as a discrete component kit (TWIN-K-045-2).

The lamp is mounted on the console and is used to initiate a processor loop back test or initiate a manual trendsample. Fault indications are displayed to the operator through the on/off or flashing status of the lamp.

The ADASd single cockpit display assembly fastens to a standard center console opening with Dzus™ fasteners.

Cockpit Display (Discrete Component Mount):

NOTE: For detailed Cockpit Display (Discrete Mount) installation drawings on the Hawker BeechcraftModel 200 & 300 Series refer to Appendix A, Section 12.3.

NOTE: The Cockpit Display (Discrete Mount) may also be mounted in the Center Console as an alternatelocation.

010 Following Figure 10, mark and punch a .75” square hole for mounting of the system TRENDswitch/fault lamp.

020 Install the TREND switch/fault lamp into the instrument panel.

030 Following Figure 10, mark and drill out 19/32” hole for the data download port in the instrumentpanel.

040 Install the download port using Loctite® Blue on the threads of the download port.

Figure 10: Typical Discrete Component Mount Installation

TREND Lamp &Download Port



Single Cockpit Display (Center Console Mount Assembly):

NOTE: For detailed Cockpit Display (Center Console Mount) installation drawings on the HawkerBeechcraft Model 200 & 300 Series refer to Appendix A, Section 12.4.

010 Remove blanking plate on center pedestal.

020 Install the provided Center Console Mount Assembly (Figure 11) in place of the blanking plate onthe pedestal (Figure 12).

TREND

Figure 11: Center Console Mount Assembly

Figure 12: Center Console Mount – Typical Installation



3.3.2 Circuit Breaker – Essential Bus

NOTE: For detailed Essential Bus Circuit Breaker installation drawings on the Hawker Beechcraft Model200 & 300 Series refer to Appendix A, Section 12.5.

The supplied 1 Amp circuit breaker will automatically interrupt the electrical circuit under abnormal conditions.The circuit breaker will be installed in the copilot’s circuit breaker panel and will be connected to a switchedpower source, Essential Bus..

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

020 Gain access to the copilot’s circuit breaker panel.

030 Mount the circuit breaker in an unused location on the copilot’s Circuit Breaker Panel. See Figure13.

040 Identify circuit breaker with proper markings.

Figure 13: Copilot Circuit Breaker Panel

3.3.3 Circuit Breaker – Battery Bus

B200 and B200C Aircraft Only:

NOTE: For detailed Battery Bus Circuit Breaker installation drawings on the Hawker Beechcraft Model200 Series refer to Appendix A, Section 12.6.

The supplied 1 Amp Circuit Breaker or 2 Amp Circuit Breaker (if used with a DTU) will automatically interruptthe electrical circuit under abnormal conditions. The circuit breaker will be installed in the A228 Battery PowerBus Box Assembly, located in the right wing and will be connected to a “Hot” 28VDC power source.


020 Gain access to the Battery/Emergency Bus Access Panel located on the bottom of the right wing, asshown in Figure 14.

030 Mount the circuit breaker in an unused location in the A228 Battery Power Bus Box Assembly, asshown in Figure 15.


ADASd Bus Circuit Breaker



Figure 14: Battery/Emergency Bus Access Panel

Figure 15: A228 Box Assembly – Battery Power Bus

Battery/Emergency BusAccess Panel

ADASd Battery BusCircuit Breaker



300, B300, and B300C Aircraft Only:

NOTE: For detailed Battery Bus Circuit Breaker installation drawings on the Hawker Beechcraft Model300 Series refer to Appendix A, Section 12.7.

The supplied 1 Amp Circuit Breaker or 2 Amp Circuit Breaker (if used with a DTU) will automatically interruptthe electrical circuit under abnormal conditions. The circuit breaker will be installed in the pilot’s circuitbreaker panel and will be connected to a “Hot” 28VDC power source.


060 Gain access to the pilot’s circuit breaker panel.

070 Mount the circuit breaker in an unused location in the pilot’s circuit breaker panel, as shown inFigure 16.


Figure 16: Pilot Circuit Breaker Panel

ADASd Battery BusCircuit Breaker



3.4 Harness Installation

NOTE: Refer to Hawker Beechcraft Wiring Diagram Manual (Wiring – Maintenance Practices)

For detailed Wire Routing Drawings on the Hawker Beechcraft Model 200 & 300 Series refer toAppendix A, Section 12.8 & 12.9.

3.4.1 “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 “AAV00A24” cable to the “Hot” 28VDC Battery connection (Figure 15 or Figure 16). Referto the wiring schematic.

030 Route the “AAV10A24” cable to the Bus Circuit Breaker located on the copilot’s circuit breaker panel(Figure 13). Refer to the wiring schematic.

040 Route the “AAV31A24” cable to the Bus Circuit Breaker located on the copilot’s circuit breaker panel(Figure 13). Refer to the wiring schematic.

050 Route the “AAB00B24” cable to the No. 1 DCU, connector 7710P1 in the avionics bay (Figure 7).Refer to the wiring schematic.

060 Route the “AAB01B24” cable to the No. 1 DCU, connector 7710P1 in the avionics bay (Figure 7).Refer to the wiring schematic.

070 Route the “AAV30E24” cable to the TREND / Fault Switch located in the center console (Figure 12).Refer to the wiring schematic

080 Route the “AA00A24N” cable to an aircraft grounding stud. Refer to the wiring schematic.

3.4.2 “J2” Harness Installation

The J2 external harness connects to the connector plug on the ADASdprocessor labeled J2. The harness

provides a means to download the data from the ADASd

to a computer using the Monitor Link Program (MLP).

010 Connect the J2 harness to the J2 connector on the ADASd

processor.

020 Route the Comm Cable “AAB40D24” to the Download Port located in the center console (Figure 12).Refer to the wiring schematic



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 Cockpit Components

The ADASd TREND switch and download port may be mounted in either a center console assembly orindividually (discrete component).

Center Console Mount:

Wiring Notes:

The following tools are recommended for connector assembly: Crimp Tool (M22520/2-01), Locator(M22520/2-06), and insertion/removal tool (M81969/1-04). These tools can be purchased at a standard avionicssupplier.

Wiring Instructions

010 Trim the AAV30E24 and AAB40D24 cables to length, and slide the connector backshell onto thecables.

020 Refer to the illustration Figure 17 and connect the cables to the included High Density (HD) 15 pinconnector using the socket configuration shown.

030 Assemble the backshell to the connector, connect it to the Center-Console Assembly, and secure allwiring.

Figure 17: TREND Switch / Fault Lamp and Download Port Connector Wiring



Discrete Mount:

Wiring Notes:

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


The TREND switch and the download port cables both use 6 pin connectors. The TRENDswitch cable uses a socket connector (6SG type) and the download port cable uses a pinconnector (6PG type). Be sure to use the correct connector with the appropriate cable.

010 Trim the “AAV30E24” cable to length, and slide the correct ConXall™ connector backshell partsonto the cable.

020 Refer to the illustration Figure 18 and connect the cable to the included ConXall™ connector usingthe socket configuration shown. Splice a short wire lead to the cable shield with a shrink-on soldersleeve to make the Pin 6 shield connection, upper and middle.

030 Assemble the backshell to the connector, connect it to the lamp, and secure all wiring.

Figure 18: TREND Switch and Lamp Connector Wiring

040 Trim the download port connector “AAB40D24” cable to length, and slide the correct ConXall™connector backshell parts onto the cable.

050 Refer to the illustration Figure 19, and connect the cable to the included ConXall™ plug connectorusing the illustrated pin configuration. Pin 1 is identified by a dimple. Pin 6 has no connection.

060 Assemble the backshell to the connector, connect it to the port, and secure all wiring.

Figure 19: Download Port Connector



4.2 Airframe Components

4.2.1 Pro Line 21 – L-GP-5 ARINC429 Wiring

The ADASd Rx channel 1 will connect to the Pro Line 21 L-GP-5 high speed ARINC429 output at the No. 1Data Concentrator Unit (DCU). The ADASd will receive data from the following sensors: Pressure Altitude,Indicated Airspeed, Total Air Temperature, WOW, Longitudinal and Lateral Acceleration.

010 Trim the “AAB00B24” cable to length.

020 Following the illustration (Figure 20), splice to the No. 1 DCU connector (7710P1) ARINC429 signalusing the pin configuration shown.

Color No. 1 DCUWHT 7710P1 – Pin 18 (FS111F22WHT)WHT/BLU 7710P1 – Pin 43 (FS111F22BLU)

4.2.2 Pro Line 21 – L-DCU-3 HS 429 ARINC429 Wiring

The ADASd Rx channel 3 will connect to the Pro-Line 21 R-DCU-3 high speed ARINC429 output at the No. 1Data Concentrator Unit (DCU). The ADASd will receive data from the following sensors: ITT, N1, N2, Tq, Wf,Np, Oil Temp, and Oil Pressure.

010 Trim the “AAB01B24” cable to length.

020 Following the illustration (Figure 20), splice to the No. 1 DCU connector (7710P1) ARINC429 signalusing the pin configuration shown.

Color No. 1 DCUWHT 7710P1 – Pin 2 (1TL107A22WHT)WHT/BLU 7710P1 – Pin 30 (1TL107A22BLU)

AIRCRAFT HARNESS SIG +

WHT

WIR

E

SHRINK SLEEVING" Pull Back and Cover Shield "

ARINC 429 Marked Cable

WHT/

BLUW

IRE

SIG -

ConnectorRAYCHEM SPLICE

Figure 20: ARINC429 Connections



4.3 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.

4.3.1 Battery Power Connection

010 Trim the AAV00A24 cable to length.

020 Following illustration Figure 21, connect the white wire to one side of the supplied breaker.

030 Connect the other end of the breaker to a “Hot” 28 VDC power.

040 Secure all wiring.

4.3.2 Bus (Switched) Power Connection

010 Trim the AAV10A24 cable to length.

020 Following illustration Figure 21, connect the white wire to one side of the supplied breaker.

030 Connect the other end of the breaker to a switched power source on the Right Circuit Breaker Panelin the cockpit.

040 Secure all wiring.

Figure 21: Circuit Breaker Wiring



4.4 Final Installation Notes

010 Route and secure all wires making sure engine / aircraft control movements will not be affected bythe ADAS

dwiring. Properly dress all splices and shield terminations. Make sure wire harness will

not come in contact with sharp sections of the aircraft.

020 After successful completion of all ground tests, pot the processor harness Raychem™ bulkheadconnector (see Section 3.2) with PRC (MC236 B-1/2) and heat shrink the fitting.



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.

Refer to Hawker Beechcraft Model 200 & 300 Series Wiring Diagram Manual (Wiring –Maintenance Practices)

For detailed Wire Routing Drawings on the Hawker Beechcraft Model 200 & 300 Series,refer to Appendix A, Section 12.8 & 12.9

5.1 J1 Harness

Connector Pin Harness Wire Color Signal Name Wired To Section 6

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

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

1 COND CABLEJ1 1 WHT 28 VDC Bus Aircraft Bus Pwr, 1 Amp CB

1 COND CABLEJ1 3 WHT System Ground Aircraft Ground

2 COND CABLEJ1 13 WHT ARINC 1 RXHI No. 1 DCU (7710P1 - Pin 18)J1 14 WHT/BLU ARINC 1 RXLO No. 1 DCU (7710P1 - Pin 43)

2 COND CABLEJ1 17 WHT ARINC 3 RXHI No. 1 DCU (7710P1 – Pin 2)J1 18 WHT/BLU ARINC 3 RXLO No. 1 DCU (7710P1 – Pin 30)

5 COND CABLE (Center Console Mount)J1 -- WHT Lamp Pwr Center Console (Pin 1)J1 3 WHT/BLU Lamp Ground Center Console (Pin 2)J1 24 WHT/GRN Lamp Drv Center Console (Pin 3)J1 23 WHT/ORG Trend Center Console (Pin 4)J1 32 WHT/RED DISC OUT 1 Center Console (tied back)

5 COND CABLE (Discrete Mount)J1 -- WHT Lamp Pwr ConXall (Pin 1)J1 3 WHT/BLU Lamp Ground ConXall (Pin 2)J1 24 WHT/GRN Lamp Drv ConXall (Pin 4)J1 23 WHT/ORG Trend ConXall (Pin 3)J1 32 WHT/RED DISC OUT 1 ConXall (tied back)

1 COND CABLEJ1 -- WHT Lamp Pwr Aircraft Bus Pwr, 1 Amp CB



5.2 J2 Harness

Connector Pin Harness Wire Color Signal Name Wired To Section 6

4 COND CABLE (Center Console Mount)J2 1 WHT/ORG GSE 485 B+ Center Console (Pin 9)J2 2 WHT GSE 485 A- Center Console (Pin 10)J2 3 WHT/BLU 28VDC RTN Center Console (Pin 11)J2 4 WHT/GRN RUN/CONF Center Console (Pin 12)

4 COND CABLE (Discrete Mount)J2 1 WHT/ORG GSE 485 B+ ConXall (Pin 1)J2 2 WHT GSE 485 A- ConXall (Pin 2)J2 3 WHT/BLU 28VDC RTN ConXall (Pin 3)J2 4 WHT/GRN RUN/CONF ConXall (Pin 4)



6 WIRING DIAGRAM

6.1 ADASd Connection Chart

Hawker Beechcraft Models B200 ; B200C ; 300 ; B300 ;B300CSensor Wire Labels Aircraft Connection ADASd Connector

A/C Batt(200 Series)

AAV00A24A228 Box Assy. – Battery Power Bus“W1” - Hot 28VDC J1

Circuit Breaker Pin 4 WHT

A/C Batt(300 Series)

AAV00A24A124 Panel Assy. Fuel Control“W17” - Hot 28VDC J1

Circuit Breaker - W103 Pin 4 WHT

A/C Bus AAV10A24

RHT CB Panel “Essential Bus” J1

Circuit Breaker Pin 1 WHT

AAV31A24 Circuit Breaker Pin 1 WHT (Fault Lamp)

Aircraft Ground AA00A24NAircraft Grounding Stud J1

Avionics Bay Pin 3 WHT

Pro Line 21 –No. 1 DCUL-GP-5 429

AAB00B24

No. 1 DCU – 7710P1 J1

Pin 18 – FS111F22WHT Pin 13 WHT

Pin 43 – FS111F22BLU Pin 14 WHT/BLU

Pro Line 21 –No. 1 DCUL-DCU-3 429

AAB01B24

No. 1 DCU – 7710P1 J1

Pin 2 – 1TL107A22WHT Pin 17 WHT

Pin 30 – 1TL107A22BLU Pin 18 WHT/BLU

Fault Lamp(Center ConsoleMount)

AAV30E24

Center Console Connector – HD 15 Pin J1

Pin 1 Pin 1 WHT (A/C Bus)

Pin 2 Pin 3 WHT/BLU

Pin 3 Pin 24 WHT/GRN

Pin 4 Pin 23 WHT/ORG

Download Port(Center ConsoleMount)

AAB40D24

Center Console Connector – HD 15 Pin J2

Pin 9 Pin 1 WHT/ORG

Pin 10 Pin 2 WHT

Pin 11 Pin 3 WHT/BLU

Pin 12 Pin 4 WHT/GRN

Fault Lamp(Discrete Mount)

AAV30E24

ConXall Connector – Female 6 Pin J1Pin 1 Pin 1 WHT (A/C Bus)Pin 2 Pin 3 WHT/BLUPin 3 Pin 23 WHT/ORGPin 4 Pin 24 WHT/GRN

Download Port(Discrete Mount)

AAB40D24

ConXall Connector – Male 6 Pin J2Pin 1 Pin 1 WHT/ORGPin 2 Pin 2 WHTPin 3 Pin 3 WHT/BLUPin 4 Pin 4 WHT/GRN

Table 1: ADASd

Connection Chart


DAAS-G-010-5 Pratt & Whitney Engine Services, Inc. Proprietary - 27 -

6.2 Wiring Schematic – B200 and B200C (Center Console Mount)

NOTE 1: Route wire in accordance with Hawker Beechcraft Model 200 Series Wiring Diagram Manual (Wiring – Maintenance Practices)

WHT/RED

WHT

WHT

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

J1.10

MICROSWITCH PTT Lamp 1 +Lamp 1 -SW1-NO

SW1-COMMSW1-NCSW2-NO

SW2-COMMSW2-NC

Female

1234

9101112

WHT/BLU

WHT/ORG

WHT

WHT

WHT/GRN

AA00A24N

AAB40D24

WHT

WHT

ESSENTIAL BUS

AAV10A24

AAV00A24

HD 15 Pin

Connector

ADASd PROCESSOR

COMM PORT

1 AMP CB

PFEN

GSE-485 B+GSE-485 A-28V RETURNRUN/CONF28V BAT28V AUX

28V BUS

J2-LEMO

56

10

43

12

9

GROUND STRAP

TREND

LAMP_DRV

+28V BUS

+28V AUX

28V RETURN

+28V BAT

ARINC1 RXHI

ARINC1 RXLO

GPOUT1

ARINC3 RXHI

ARINC3 RXLO

J1-37 S

13

24

14

1

3

42

2332

1718

Male

1234

9101112

RHT CB Panel

(Switched Pwr)

TREND LAMP

AAV30E24

AAV31A24

AAB00B24

1 AMP CB (ADASd Only)or

2 AMP CB (ADASd with DTU)

WHTWHT/BLU

WHT AAB01B24WHT/BLU

230

1843

No. 1 DCU7710P1

WHT/GRNWHT/ORG

BATTERY

WHT/BLU

A228 Box Assembly - Battery Power Bus

"W1" - Hot 28 VDC1 2

1 2

1TL107A22WHT1TL107A22BLU

FS111A22BLUFS111A22WHT

L-DCU-3 HS 429 BL-DCU-3 HS 429 A

L-GP-5 429 BL-GP-5 429 A

Figure 22: ADASd

Wiring Schematic – B200 and B200C (Center Console Mount)



6.3 Wiring Schematic – B200 and B200C (Discrete Mount)


Male

123456

Female

123456

6 Pin ConXall

Connector

WHT

WHT

WHT/RED

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

J1.10



SW2-COMMSW2-NC

Female

123456

WHT/GRNWHT/BLU

WHT/ORG AAB40D24

WHT

WHT

AA00A24N

WHT

ESSENTIAL BUS

WHT

AAV00A24

AAV10A24

ADASd PROCESSOR

6 Pin ConXall

Connector

1 AMP CB

COMM PORT

PFEN


28V BUS

J2-LEMO

56

10

43

12

9

GROUND STRAP

LAMP_DRV

TREND

+28V BUS

+28V AUX

28V RETURN

+28V BAT

ARINC1 RXHI

ARINC1 RXLO

GPOUT1

ARINC3 RXHI

ARINC3 RXLO

J1-37 S

13

23

14

1

3

42

2432

1718

RHT CB Panel

(Switched Pwr)

TREND LAMP

AAV30E24

AAV31A24

AAB00B24

1 AMP CB (ADASd Only)or

2 AMP CB (ADASd with DTU)

WHTWHT/BLU

WHT AAB01B24WHT/BLU

230

1843

No. 1 DCU7710P1

WHT/ORGWHT/GRN

BATTERY

WHT/BLU

A228 Box Assembly - Battery Power Bus

"W1" - Hot 28 VDC1 2

1 2

1TL107A22BLU1TL107A22WHT

FS111A22WHTFS111A22BLU

L-DCU-3 HS 429 B

L-GP-5 429 BL-GP-5 429 A

L-DCU-3 HS 429 A

Male

123456

Figure 23: ADASd

Wiring Schematic – B200 and B200C (Discrete Mount)



6.4 Wiring Schematic – 300, B300, and B300C (Center Console Mount)


WHT

WHT

WHT/RED

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

J1.10



SW2-COMMSW2-NC

Female

1234

9101112

WHT/ORG

WHT/GRNWHT/BLU

AAB40D24

WHT

WHT

AA00A24N

WHT

ESSENTIAL BUS

WHT AAV10A24

AAV00A24

ADASd PROCESSOR

HD 15 Pin

Connector

1 AMP CB

COMM PORT

PFEN


28V BUS

J2-LEMO

56

10

43

12

9

GROUND STRAP

TREND

LAMP_DRV

+28V BUS

+28V AUX

28V RETURN

+28V BAT

ARINC1 RXHI

ARINC1 RXLO

GPOUT1

ARINC3 RXHI

ARINC3 RXLO

J1-37 S

13

24

14

1

3

42

2332

1718

Male

1234

9101112

RHT CB Panel

(Switched Pwr)

TREND LAMP

AAV30E24

AAV31A24

AAB00B24

1 AMP CB (ADASd On ly)

or2 AMP CB (ADASd with DTU)

WHTWHT/BLU

WHT AAB01B24WHT/BLU

230

1843

No. 1 DCU

7710P1

WHT/GRNWHT/ORG

A124 Panel Assembly - Fuel Control

"W17" - Hot 28 VDC

BATTERY

WHT/BLU

1 2

1 2

1TL107A22WHT1TL107A22BLU


L-GP-5 429 A

L-DCU-3 HS 429 AL-DCU-3 HS 429 B

L-GP-5 429 B

Figure 24: ADASd

Wiring Schematic – 300, B300, and B300C (Center Console Mount)



6.5 Wiring Schematic – 300, B300, and B300C (Discrete Mount)


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

J1.10

PFEN


28V BUS

J2-LEMO

56

10

43

12

9

LAMP_DRV

TREND

+28V BUS

+28V AUX

28V RETURN

+28V BAT

ARINC1 RXHI

ARINC1 RXLO

GPOUT1

ARINC3 RXHI

ARINC3 RXLO

J1-37 S

13

23

14

1

3

42

2432

1718

230

1843

1 2

1 2

Male

123456

Female

123456

Female

123456

Male

123456



SW2-COMMSW2-NC

N o. 1 DC U7710P1

WHT/GRNWHT/ORGWHT/BLU

BATTERY

A124 Panel Assembly - Fuel Control

"W17" - Hot 28 VDC

1TL107A22BLU1TL107A22WHT

WHT

WHT

WHT/RED

AA00A24N


WHT

AAB 40D24WHT/ORG

WHT/BLUWHT/GRN

WHT

ESSENTIAL BUS

WHT

WHT

L-DCU-3 HS 429 BL-DCU-3 HS 429 A

L-GP-5 429 AL-GP-5 429 B

6 Pin ConXall

Connector

6 Pin ConXall

Connector

TREND LAMP

AAV00A24

AAV10A24

GROUND STRAP

COMM PORT

1 AMP C B

ADASd PROCESSOR

AAV30E24

RHT CB Panel

(Switched Pwr)

AAB 01B24WHT

AAB 00B24WHTWHT/BLU

AAV31A24

1 AMP C B (AD ASd Only)or

2 AMP C B (AD ASd with DTU)WHT/BLU

Figure 25: ADASd

Wiring Schematic – 300, B300, and B300C (Discrete Mount)



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 sensorvalues. This buffer of sequential data sets is called the Time History Buffer. The amount of data requested fromthe buffer 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:

Manual Trend: Pressing the TREND switch when the engine is running will initiate a manual trend. TheADASd will take a snapshot of all sensors for a pre-defined duration (default is 5 seconds but is configurable)and record the maximum values and average values for all sensors during the entire duration. The TRENDswitch will flash during the entire duration of the trend.

Autotrend: The ADASd can be configured to initiate a trend automatically without pressing the Trend /Switch. The ADASd can be configured to initiate an autotrend by defining a stable criteria consisting of up toten (10) sensors. If the stable criteria are met, the ADASd will initiate a trend automatically. The Trend /Switch will flash during the entire duration of the trend.The ADASd can be configured to initiate an autotrendby defining a stable criteria consisting of up to ten (10) sensors. If the stable criteria are met, the ADASd willinitiate a trend automatically.

7.2 System Initialization and Lamp State Description

When the system initializes, the fault lamp will indicate the various stages of the process. The initializationsequence will proceed as follows:

When the processor’s power is first applied, the fault lamp will illuminate for 1 to 5 seconds while the systemperforms a series of self-tests. The following self-tests are performed during initialization:

Micro Controller Test

Lamp Test (momentary flicker)

Temporary Memory Test

Data Log Memory Test

Program Integrity Test



If any of these tests fail, the processor will restart the initialization cycle. The lamp will extinguish briefly andilluminate for a period until the test failure is repeated. This cycle will continue until the processor power isremoved. The illumination of the lamp will be a period of ON followed by a very brief OFF, repeated every 5seconds, or less.

If the initial self-tests do not fail, the processor will normally extinguish the lamp for approximately 1 to 5seconds, indicating completion of the self-test phase. It will then proceed to check for:

A Matching Engine Configuration Value

This test is performed as follows: if the hard-wired engine/sensor/system configuration does not match theexpected software value stored internally, the lamp will illuminate solid. This type of fault indication may notactually indicate a problem with the installation. It may result simply from a processor factory reset, whichcleared the last stored configuration value. Such a fault can be corrected by loading a configuration file usingthe P&W Engine Services Monitor Link Program (MLP).

NOTE: If the engine configurations do not match, the system will be in Fault State.

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

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 lamp display.

System States:

1. Normal

2. Maintenance

3. Caution

4. Fault

Definitions:

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

Fault Lamp Display:

Lamp Out – Normal State:This is the normal condition of the ADASd when all systems checks have passed.



Lamp Flashing (pressing button will turn lamp off) – Maintenance State:When the ADASd is in Maintenance State, the processor memory is 100% full and will NOT function as anexceedance monitor.

Lamp Flashing (pressing button will NOT turn lamp off) – Caution State:When the ADASd is in Caution State, the system has detected a previous flight exceedance.

Lamp Solid – Fault State:When the ADASd is in Fault State, the system has detected a fault condition that WILL affect its ability tofunction as an exceedance monitor.

Note: The ADASd will extinguish any of the above lamp conditions once an engine has started.Once the engine has been started, or either engine has started in a dual engine aircraft, the ADASd lamp is usedto display trend and exceedance information to the pilot and/or crew as follows:

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. During this trend sample the ADASd lamp will flash at a slow (1 Hz) rate. Pressing the TRENDswitch will manually initiate the same trend data sample.

Exceedance Mode:Exceedance Mode is defined as anytime the aircraft or engine has met the criteria defined for an exceedance andwhere the pilot and/or crew should be alerted. These exceedances are typically torque or temperatureexceedances. Exceedance Mode is displayed to the pilot via a 2 HZ lamp flash. The exceedance can beconfigured such that Exceedance Mode can be acknowledged by pressing the TREND switch. If configuredthis way, the Exceedance Mode lamp display will extinguish when the TREND switch is pressed.

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. All interface to the pilot and/or crew is done through a single cockpitmounted TREND switch/fault lamp. If the pilot and/or crew are notified during an exceedance by the lamp, thepilot and/or crew must use standard aircraft/engine instrumentation to determine the cause of the exceedanceand take corrective action as appropriate



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 expectthe particular 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.Connect the other end of the cable to the serial port on a laptop computer with the current version ofMLP.

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 2 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 Table 3).



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 2: VHF Frequency Table

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 radiosto the frequencies in Table 2 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 Table 3).

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 4).

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 3: Electromagnetic Compatibility Test Table

Comments:

Ground Test Eng. #1 Eng. #2

Cockpit ADASd

Delta Cockpit ADASd

Delta

ITT/TOT

N1/Ng/Nl

N2/Nh

Np

Wf

Bus Voltage

Altitude

Airspeed

Table 4: Ground Test Data



Aircraft Make:

Aircraft Model:

Aircraft Registration Number:

Aircraft S/N:

Test Completed By:

Test Completed Date:

9.2 Continued Airworthiness Instructions

See ADASd Instructions for Continued Airworthiness, DAAS-G-260-5 for troubleshooting the system. If yourequire further assistance, contact the Help Desk:



10 SERVICE

10.1 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 Installation

Figure A- 1: ADASd

Installation – Sheet 1 of 5



Figure A- 2: ADASd




Figure A- 3: ADASd




Figure A- 4: ADASd




Figure A- 5: ADASd




12.2 Pressure Bulkhead Fitting

Figure A- 6: Pressure Bulkhead Fitting – Sheet 1 of 4



12.3 TREND / Switch Fault Lamp and Download Port (Discrete Mount Option)

Figure A- 10: TREND / Switch Fault Lamp and Download Port (Discrete Mount Option) – Sheet 1 of 4



12.4 TREND / Switch Fault Lamp and Download Port (Center Console Option)

Figure A- 14: TREND / Switch Fault Lamp and Download Port (Center Console Option) – Sheet 1 of 4



12.5 Circuit Breaker Installation (Essential Bus)

Figure A- 18: Circuit Breaker Installation (Essential Bus) – Sheet 1 of 3



12.6 Circuit Breaker Installation for B200, B200C (Battery Bus)

Figure A- 21: Circuit Breaker Installation for B200, B200C (Battery Bus) – Sheet 1 of 3



12.7 Circuit Breaker Installation for 300, B300, B300C (Battery Bus)

Figure A- 24: Circuit Breaker Installation for 300, B300, B300C (Battery Bus) – Sheet 1 of 3



12.8 Wire Routing for B200, B200C

Figure A- 27: Wire Routing for B200, B200C – Sheet 1 of 4



12.9 Wire Routing for 300, B300, B300C

Figure A- 31: Wire Routing for 300, B300, B300C – Sheet 1 of 4

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