ADAS h. Installation Manual. For Cessna Model 560 Encore & Ultra. Pratt & Whitney Engine Services, Inc. 249 Vanderbilt Ave Norwood, MA 02062

Transcription

1 Pratt & Whitney Engine Services, Inc. 249 Vanderbilt Ave Norwood, MA ADAS h Installation Manual ADHY-G For Manual Number ADHY-G Preparation Date: August 20, 2007 Prepared By: D Elsemiller Release Date: February 27, 2008 Approvals: S Sackos, Manager of Manufacturing Services Revision Date: February 17, 2010 J Lukens, Applications Engineering Revision Ltr: C Pages: Vanderbilt Ave. Norwood, MA 02062, Phone , Fax

2 Disclaimer PREFACE Like all instrumentation, the Pratt & Whitney Engine Services, Inc. ADAS h requires knowledgeable interpretation by the pilot. Any recommendations and operating procedures contained in this manual shall not supersede the Aircraft or Engine manufacturer recommendations, operating procedures, or limits. The Pratt & Whitney Engine Services, Inc. ADAS h should not be used as a primary guide monitoring the Aircraft and Engine manufacturers operating limits. Pratt & Whitney Engine Services, Inc. is not liable for any damages resulting from the use of this product. Proprietary Information Notice This manual contains proprietary information that is protected by copyright, and all rights are reserved. No portion of this document may be copied, photocopied, reproduced by any means, or translated into another language without the prior written permission of Pratt & Whitney Engine Services, Inc. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary i

3 REVISION HISTORY Rev Status Rev A C C C C A A A A A A C C C C C of Sheets Sheet i ii iii iv v Rev C C C C C C C C C C C C C C C C Sheet Rev C C C C C C C C C C C C C C C C Sheet Rev C C C C C C C C C C C C C C C C Sheet Rev C C C C C C C C C C C C C C C C Sheet LOG OF REVISIONS REV. NO ECO # DESCRIPTION DATE PAGES REVISED A N/A Initial Release 02/27/2008 All B 989 Update Parts List. Revise Processor Installation Instructions. Revise 560 Ultra Pressure Bulkhead Connector Wiring. C 1014 Create New Additional Parts Lists for 560 Ultra. Update 560 Ultra Schematic. Correct typographical errors. 02/04/2009 Cover, ii, 7, 9, 11-16, 26, /17/2010 Cover, ii - v, 7-75 ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary - ii -

4 TABLE OF CONTENTS 1 INTRODUCTION Scope About This Manual System Description Unpacking the Equipment Weight and Balance INSTALLATION AND MAINTENANCE PROCEDURES Standard Practices-Airframe/Powerplant Procedure for Wiring Connections Wiring Splices Maintenance Parts List ADASh by Parts Kits Components by Kit Installation Mechanical System Processor Circuit Breaker Harness Installation J1 Harness Installation J2 Harness Installation J3 Harness Installation INSTALLATION - ELECTRICAL Engine / Airframe Sensors Primus 1000 Air Data Computer (Right ADC) Wiring Engine 1 N1 Indicator Engine 2 N1 Indicator Engine 1 N2 Indicator Engine 2 N2 Indicator Engine 1 Fuel Flow Indicator Engine 2 Fuel Flow Indicator Engine 1 ITT Indicator Engine 2 ITT Indicator Weight on Wheels signal Electrical Power Bus (Switched) Power Connection HARNESS CONNECTOR SIGNAL PINOUTS J1 Harness J2 Harness J3 Harness WIRING DIAGRAM ADASh Connection Chart 560 Ultra S/N with Analog Instruments ADASh Connection Chart 560 Encore S/N with Analog Instruments ADASh Connection Chart 560 Encore S/N with LCD Instruments Wiring Schematic - Model 560 Ultra S/N with Analog Instruments Wiring Schematic - Model 560 Encore S/N with Analog Instruments Wiring Schematic - Model 560 Encore S/N with LCD Instruments SYSTEM OPERATION OVERVIEW ADAS h Functional Description ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary iii

5 7.1.1 Engine Run Logging Cycle Logging Event Monitoring and Time History Buffer Trend Monitoring System Initialization System Modes Run Mode Description (States) SYSTEM CONFIGURATION Definitions Processor Configuration System Checkout and Sensor Verification Calibration Using Test Equipment Calibration Using Aircraft Cockpit Instruments AIRCRAFT TESTING Aircraft Ground Test Continued Airworthiness Instructions SERVICE SPECIFICATIONS System Specifications Interface Requirements for Aircraft Sensors Appendix A ADASh Installation for 560 Encore & Ultra ADASh Installation for 560 Ultra Circuit Breaker Installation Forward Pressure Bulkhead Connector Circuit Breaker Connector Wire Routing for 560 Encore Wire Routing for 560 Ultra LIST OF FIGURES Figure 1: Model 560 ADAS h System Architecture... 3 Figure 2: Single or Dual Wire Splices... 5 Figure 3: Shielded connection (Outer Heat-Shrink Tubing Not Shown)... 5 Figure 4: ADAS h Processor Figure 5: Mounting Bracket Assembly Figure 6: Mounting Bracket with ADAS h Figure 7: Mounting Plate (ADHY-D-049-1) Figure 8: Existing Nut Plates on Rails Figure 9: ADAS h Installation Location on 560 Encore (ADAS h with DTU Shown) Figure 10: ADAS h Installation Location on 560 Ultra (ADAS h with DTU Shown) Figure 11: Circuit Breaker Installation Location (560 Encore Shown) Figure 12: Forward Pressure Bulkhead Connectors - Looking AFT (Encore shown) Figure 13: Ground Connector Figure 14: Primus 1000 Location (Right ADC) Figure 15: Airframe/Engine Signal Connections Figure 16: WOW Diode Orientation Figure 17: Circuit Breaker Wiring Figure 18: ADAS h Wiring Schematic Model 560 Ultra S/N wih Analog Instruments Figure 19: ADAS h Wiring Schematic Model 560 Encore S/N with Analog Instruments Figure 20: ADAS h Wiring Schematic Model 560 Encore S/N with LCD Instruments ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary iv

6 LIST OF TABLES Table 1: Connection Chart Ultra S/N with Analog Instruments Table 2: Connection Chart 560 Encore S/N with Analog Instruments Table 3: Connection Chart Encore S/N with LCD Instruments Table 4: VHF Frequency Table Table 5: Electromagnetic Compatibility Test Table Table 6: Ground Test Data APPENDIX A Figure A- 1: ADAS h Installation for 560 Encore & Ultra Sheet 1 of Figure A- 2: ADAS h Installation for 560 Encore & Ultra Sheet 2 of Figure A- 3: ADAS h Installation for 560 Encore & Ultra Sheet 3 of Figure A- 4: ADAS h Installation for 560 Encore & Ultra Sheet 4 of Figure A- 5: ADAS h Installation for 560 Encore & Ultra Sheet 5 of Figure A- 6: ADAS h for 560 Ultra Sheet 1 of Figure A- 7: ADAS h for 560 Ultra Sheet 2 of Figure A- 8: ADAS h for 560 Ultra Sheet 3 of Figure A- 9: Circuit Breaker Installation Sheet 1 of Figure A- 10: Circuit Breaker Installation Sheet 2 of Figure A- 11: Circuit Breaker Installation Sheet 3 of Figure A- 12: Circuit Breaker Installation Sheet 3 of Figure A- 13: Forward Pressure Bulkhead Connector Sheet 1 of Figure A- 14: Forward Pressure Bulkhead Connector Sheet 2 of Figure A- 15: Forward Pressure Bulkhead Connector Sheet 3 of Figure A- 16: Circuit Breaker Connector Sheet 1 of Figure A- 17: Circuit Breaker Connector Sheet 2 of Figure A- 18: Circuit Breaker Connector Sheet 3 of Figure A- 19: Wire Routing for 560 Encore Sheet 1 of Figure A- 20: Wire Routing for 560 Encore Sheet 2 of Figure A- 21: Wire Routing for 560 Encore Sheet 3 of Figure A- 22: Wire Routing for 560 Encore Sheet 4 of Figure A- 23: Wire Routing for 560 Encore Sheet 5 of Figure A- 24: Wire Routing for 560 Ultra Sheet 1 of Figure A- 25: Wire Routing for 560 Ultra Sheet 2 of Figure A- 26: Wire Routing for 560 Ultra Sheet 3 of Figure A- 27: Wire Routing for 560 Ultra Sheet 4 of Figure A- 28: Wire Routing for 560 Ultra Sheet 5 of ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary v

7 1 INTRODUCTION Aircraft and engine maintenance procedures are critical to flight safety and lower operating costs. P&W Engine Services has developed an aircraft data acquisition system known as ADAS h to perform two primary functions: Exceedance Event Recording: The ADAS h can monitor critical engine parameters and record instances where they have exceeded preset values (exceedances). Engine Trend Monitoring: The ADAS h can gather and store engine data samples for trend analysis. The ADAS h enables the operator to control, quantify, and manage engine maintenance operations and reduce direct operating costs. The ADAS h is a passive receiver of information. In its data acquisition role it can be configured to record data automatically. Automatic Operation: The system may be configured to automatically record exceedance events and trends. It may also be configured to record data samples when stable aircraft conditions are achieved. These conditions 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 the ADAS h is achieved through P&W Engine Services Monitor Link Program (MLP), which can be used to download data and upload system configuration files. The MLP can also be used to assist maintenance personnel in performing system diagnostics, calibrations, and real-time live sensor display. System Configuration: The ADAS h system is shipped with a predefined set of software sensor configurations, exceedance event specifications, cycle specifications, and engine start/stop definitions. System configurations can be altered to reflect the customer s operating environment or requirements. The ADAS h is an enhancement to the Pratt & Whitney Engine Services Generation III monitoring system. The ADAS h provides four ARINC-429 communications interfaces through which aircraft and engine performance data can be collected. The ADAS h uses these ARINC-429 interfaces to connect to aircraft subsystems, e.g., the air data computer. The ADAS h also interfaces to the analog sensors on the aircraft for measuring other airframe and engine parameters not present on the ARINC-429 bus. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 1

8 1.1 Scope The purpose of this document is to provide users of this product with P&W Engine Services approved installation instructions. Any deviation from the procedures described within this document could result in a failure 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 section checklist. Find the aircraft wiring diagram and follow the steps described in the mechanical and electrical 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. 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. The locking 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 are performed. 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 tie holders, etc.) are not included with the installation kit. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 2

9 1.3 System Description Figure 1shows the architecture of the ADAS h on a. 1.4 Unpacking the Equipment Figure 1: Model 560 ADAS h System Architecture Carefully remove each component from the original shipping container. Place each component on a roll-away cart or suitable workbench in the work area. 1.5 Weight and Balance Calculating weight and balance of the ADAS h after installation is the responsibility of the installer. The information needed is shown below: ADAS h Kit Weight lbs. Arm ADHY-K ADHY-K ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 3

10 2 INSTALLATION AND MAINTENANCE PROCEDURES INSTALLATION CAUTION: Use of any procedure that does not apply to your specific application could cause unnecessary 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 manufacturer provided airframe and powerplant documentation in order to understand installation requirements and technical capability 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 B "Acceptable Methods, Techniques, and Practices - Aircraft Inspection and Repair" and with FAA Advisory Circular A "Acceptable Methods, Techniques and Practices - Aircraft Alterations" 2. Read all instructions completely before beginning any installation. Only qualified mechanics or avionics technicians shall perform the installation. 3. All aircraft systems interfacing with the P&W Engine Services ADAS h must be checked for full functionality before installation begins. 4. All illustrated mounting locations should be used as a general guide for mounting. Locations shown in illustrations may be altered to fit special individual installation requirements as needed, provided accepted structural procedures and practices are followed. 5. Refer to the manufacturer s manual for approved locations or cautions for clamping hoses and cables, or modifying the aircraft structure Procedure for Wiring Connections INSTALLATION CAUTION: The ADAS h cables have shields that connect to the processor chassis ground. When terminating the shielded harness at the airframe connection, these shields must be trimmed back and insulated to prevent possible shorting with the signal wires. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 4

11 2.1.2 Wiring Splices The use of Raychem hermetic style wire splices (Figure 2 and Figure 3) are recommended. When making connections between two shielded cables, the shields should also be maintained using Raychem or equivalent shield 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 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) ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 5

12 2.1.3 Maintenance The P&W Engine Services ADAS h has been designed with the latest solid-state technology. The only component that has a limited life span is the internal battery. This battery, under normal operating conditions, is expected to last 10 years. If the battery is discharged, the processor must be returned to P&W Engine Services for battery replacement. Care of the processor under normal operation consists of general cleaning and inspection for bracket and connector security during every major engine or aircraft inspection. Refer to ADAS h Instructions for Continued Airworthiness, ADHY-G Comments and findings should be forwarded to P&W Engine Services for inclusion into their continued product improvement program. In the event that the ADAS h must be returned for service, contact the P&W Engine Services Help Desk for a Returned Material Authorization (RMA) number. When you receive the RMA number, include it 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 are experiencing. This will greatly assist our technicians in rapidly identifying the problem. After service, the processor will be returned to you or your dealer with the shipping prepaid. Pratt & Whitney Engine Services, Inc. Help Desk 249 Vanderbilt Ave. Norwood, MA (781) Fax: (781) TurbineTrackerSupport@altairavionics.aero ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 6

13 2.2 Parts List Care must be taken when handling all parts and equipment. Before opening packages, perform an inventory check by comparing the receivables to the appropriate bill of materials. The parts listed below consist of the installation kit for the ADAS h system for the aircraft. Assembly kit numbers are listed in Section and individual components are detailed by kit numbers in Section ADASh by Parts Kits For Model 560 Encore (ADAS h with DTU) Qty P/N ADHY-K Processor Assembly Kit 1 ADHY-K Wiring Harness Kit 1 ADHY-K Additional Installation Materials Kit 1 ADHY-K For Model 560 Encore (ADAS h Only) Qty P/N ADHY-K Processor Assembly Kit 1 ADHY-K Wiring Harness Kit 1 ADHY-K Additional Installation Materials Kit 1 ADHY-K For Model 560 Ultra (ADAS h with DTU) Qty P/N ADHY-K Processor Assembly Kit 1 ADHY-K Wiring Harness Kit 1 ADHY-K Additional Installation Materials Kit 1 ADHY-K For Model 560 Ultra (ADAS h Only) Qty P/N ADHY-K Processor Assembly Kit 1 ADHY-K Wiring Harness Kit 1 ADHY-K Additional Installation Materials Kit 1 ADHY-K Components by Kit PROCESSOR ASSEMBLY KIT ADHY-K Processor ADHY-A Qty 1 Mounting Bracket ADHY-D Qty 1 Bracket, Mounting Plate ADHY-D Qty 1 Mount, Shock Grommet Isolator Qty 4 Washer, Flat, # Qty 4 Nut, Locking, #6-32 MS Qty Reduced Head, Close Tolerance Bolt NAS Qty 10 Strap, Ground DPU-C Qty 1 Washer, Flat AN960-8 Qty 10 Nut, Elastic Stop MS21044-N08 Qty 6 Plug, Finishing 9/ Qty 1 Panel Plug Qty 1 WIRING HARNESS KIT ADHY-K Harness, J1 External ADHY-C Qty 1 Harness, J2 External ADHY-C Qty 1 Harness, J3 External ADHY-C Qty 1 ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 7

14 ADDITIONAL MATERIAL INSTALLATION KIT ADHY-K Breaker, 2 Amp Qty 1 Wire, 24AWG, White M22759/ Qty 3 Terminal, Ring # Qty 2 Terminal, Ring # Qty 2 Terminal, Ring # Qty 2 Diode, Inline Junction Qty 1 Contact, Pin, Inline Junction Qty 2 Contact, Socket, CB Connector Qty 1 Contact, Pin, CB Connector Qty 1 Contact, Socket, Ground Connector M39029/ Qty 1 Contact, Pin, Alumel M39029/ Qty 2 Contact, Pin, Chromel M39029/ Qty 2 Contact, Socket, Alumel M39029/ Qty 2 Contact, Socket, Chromel M39029/ Qty 2 ADDITIONAL MATERIAL INSTALLATION KIT ADHY-K Breaker, 1 Amp Qty 1 Wire, 24AWG, White M22759/ Qty 3 Terminal, Ring # Qty 2 Terminal, Ring # Qty 2 Terminal, Ring # Qty 2 Diode, Inline Junction Qty 1 Contact, Pin, Inline Junction Qty 2 Contact, Socket, CB Connector Qty 1 Contact, Pin, CB Connector Qty 1 Contact, Socket, Ground Connector M39029/ Qty 1 Contact, Pin, Alumel M39029/ Qty 2 Contact, Pin, Chromel M39029/ Qty 2 Contact, Socket, Alumel M39029/ Qty 2 Contact, Socket, Chromel M39029/ Qty 2 ADDITIONAL MATERIAL INSTALLATION KIT ADHY-K Breaker, 2 Amp Qty 1 Wire, 24AWG, White M22759/ Qty 3 Terminal, Ring # Qty 2 Terminal, Ring # Qty 2 Terminal, Ring # Qty 2 Diode, Inline Junction Qty 1 Contact, Pin, Inline Junction Qty 2 Contact, Socket, CB Connector Qty 1 Contact, Pin, CB Connector Qty 1 Contact, Socket, Ground Connector M39029/ Qty 1 Contact, Pin, Alumel M39029/ Qty 2 Contact, Pin, Chromel M39029/ Qty 2 Contact, Socket, Alumel M39029/ Qty 2 Contact, Socket, Chromel M39029/ Qty 2 ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 8

15 ADDITIONAL MATERIAL INSTALLATION KIT ADHY-K Breaker, 1 Amp Qty 1 Wire, 24AWG, White M22759/ Qty 3 Terminal, Ring # Qty 2 Terminal, Ring # Qty 2 Terminal, Ring # Qty 2 Diode, Inline Junction Qty 1 Contact, Pin, Inline Junction Qty 2 Contact, Socket, CB Connector Qty 1 Contact, Pin, CB Connector Qty 1 Contact, Socket, Ground Connector M39029/ Qty 1 Contact, Pin, Alumel M39029/9-134 Qty 2 Contact, Pin, Chromel M39029/9-135 Qty 2 Contact, Socket, Alumel M39029/ Qty 2 Contact, Socket, Chromel M39029/ Qty 2 ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 9

16 3 Installation Mechanical 3.1 System Processor NOTE: For detailed ADAS h installation drawings on the refer to Appendix A, Section 12.1 and The processor (Figure 4) collects and interprets data from airframe and engine components. Data is retrieved by the 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 bracket with Lord Aerospace shock mounts is used to mount the processor to the aircraft. Figure 4: ADAS h Processor The system processor is mounted to an existing avionics rack in the avionics bay (FS 30). The processor is mounted on the left side of the avionics bay on a 560 Encore model and the right side of the avionics bay on a 560 Ultra model. These installations are mirror images of each other. The ADAS h will not require access during normal operation. INSTALLATION CAUTION: Excessive torque on the processor mounting studs can deform the shock mounts. The locking nut should be tightened only to the point of contact with the shock mount. 010 Reference Figure 5 and assemble the Shock Mounts ( ), rectangular finishing plug ( ) and circular finishing plug ( ) into the processor bracket (ADHY-D-034-1). 020 Reference Figure 6 and install the processor onto the bracket assembly with the supplied hardware. 030 Mark and drill the location of the 4 mounting holes on the supplied mounting plate (Figure 7), using the dimensions of the existing nut plates on the rails, shown in Figure 8. NOTE: The 4 mounting holes will need to have a countersink depth of 0.04 at 100º on the top of the mounting plate. 040 Attach the mounting plate (ADHY-D-049-1) to the rails using the supplied 100º Reduced Head, Close Tolerance Bolts P/N NAS Attach the processor and bracket that was assembled in step 020 onto the mounting plate and ensure that the processor does not interfere with wiring or controls. See Figure 9 and Figure 10: NOTE: The 6 countersunk mounting holes on the bottom of the mounting plate (ADHY-D-049-1) utilize the supplied 100º Reduced Head, Close Tolerance Bolts P/N NAS Install ground strap DPU-C between one of the processor mounting studs to the aircraft chassis. Remember to burnish the processor mounting bracket to ensure proper contact of the grounding strap. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 10

17 Figure 5: Mounting Bracket Assembly Figure 6: Mounting Bracket with ADAS h ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 11

18 Figure 7: Mounting Plate (ADHY-D-049-1) Figure 8: Existing Nut Plates on Rails ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 12

19 Figure 9: ADAS h Installation Location on 560 Encore (ADAS h with DTU Shown) Figure 10: ADAS h Installation Location on 560 Ultra (ADAS h with DTU Shown) ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 13

20 3.2 Circuit Breaker NOTE: For detailed Circuit Breaker installation drawings on the refer to Appendix A, Section 12.3 A (1) Amp Circuit Breaker or (2) Amp Circuit Breaker (if used with a DTU) will automatically interrupt the electrical circuit under abnormal conditions. The circuit breaker will be installed in the Left Circuit Breaker Panel and will be connected to a switched power source, Bus Bar HC005, Essential Bus. 010 Ensure that no power is connected to the aircraft and that the battery cable is disconnected from the battery. 020 Mount the circuit breaker (Figure 11) directly above the FLT HR CB or another vacant location as close as possible. 030 Identify circuit breakers with proper markings. Figure 11: Circuit Breaker Installation Location (560 Encore Shown) ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 14

21 3.3 Harness Installation NOTE: For detailed Wire Routing Drawings on the refer to Appendix A, Section 12.6 and Refer to Model 560 Wiring Diagram Manual (Wiring Maintenance Practices) J1 Harness Installation The J1 external harness connects to the connector plug on the ADAS h processor labeled J1. The harness provides aircraft essential bus power to the processor. The individual cables are appropriately labeled. The ADAS h 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 ADAS h processor. 020 Route the AAV10A22 cable to the Bus Circuit Breaker located on the Left Circuit Breaker panel. This will require using spare pins on an existing forward pressure bulkhead connector (J6 / P6), as shown in Figure 12. This will also require using supplied contacts (P/N and ) for the circuit breaker panel connector (J131 / P131). Refer to the wiring schematic in section 6.4 for pin locations NOTE: Use the provided M22759/ (single conductor non-shielded) wire inside the circuit breaker panel and label as necessary. 030 Route the AA00A22N cable to an aircraft ground connector (NDC17), as shown in Figure 13. This will require using the supplied contact (P/N M390929/22-192). Refer to the wiring schematic in Section J2 Harness Installation The J2 external harness connects to the connector plug on the ADAS h processor labeled J2. The harness provides engine and air data to the processor. The individual cables are appropriately labeled. The ADAS h 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 J2 harness to the J2 connector on the ADAS h processor. 020 Route the AAB00B24 cable to the Primus 1000 Air Data Computer (ADC) in the Avionics Bay, as shown in Figure 14. Refer to the wiring schematic in section 6.4 for pin locations. 030 Route the AAP10B24 cable to the Engine 1 N1 Indicator on the instrument panel. This will require using spare pins on an existing forward pressure bulkhead connector (J6 / P6), as shown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations 040 Route the AAP11B24 cable to the Engine 1 N2 Indicator on the instrument panel. This will require using spare pins on an existing forward pressure bulkhead connector (J6 / P6), as shown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations 050 Route the AAA25B24 cable to the Engine 1 Fuel Flow Indicator on the instrument panel for a 560 Ultra. This will require using spare pins on an existing forward pressure bulkhead connector (J6 / P6), as shown in Figure 12. For a 560 Encore, route the AAA25B24 cable to the Engine 1 Fuel Flow signal at the fwd pressure bulkhead connector (JB724 / PB724), as shown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations. 060 Route the AAA10B24 cable to the Engine 1 ITT Indicator on the instrument panel. This will require using supplied alumel and chromel pins on an existing forward pressure bulkhead connector ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 15

22 (J6 / P6), as shown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations 070 Route the AAA11B24 cable to the Engine 2 ITT Indicator on the instrument panel. This will require using supplied alumel and chromel pins on an existing forward pressure bulkhead connector (J6 / P6), as shown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations J3 Harness Installation The J3 external harness connects to the connector plug on the ADAS h processor labeled J3. The harness provides weight on wheels (WOW) and engine data to the processor. The individual cables are appropriately labeled. The ADAS h 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 J3 harness to the J3 connector on the ADAS h processor. 020 Route the AAA26B24 cable to the Engine 1 Fuel Flow Indicator on the instrument panel for a 560 Ultra. This will require using spare pins on an existing forward pressure bulkhead connector (J6 / P6), as shown in Figure 12. For a 560 Encore, route the AAA26B24 cable to the Engine 1 Fuel Flow signal at the fwd pressure bulkhead connector (JB724 / PB724), as shown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations. 030 Route the AAP13B24 cable to the Engine 2 N2 Indicator on the instrument panel. This will require using spare pins on an existing forward pressure bulkhead connector (J6 / P6), as shown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations 040 Route the AAP12B24 cable to the Engine 2 N1 Indicator on the instrument panel. This will require using spare pins on an existing forward pressure bulkhead connector (J6 / P6), as shown in Figure 12. Refer to the wiring schematic in section 6.4 for pin locations 050 Route the AAD00A24 cable to the Primus 1000 Air Data Computer (ADC) in the Avionics Bay, as shown in Figure 14. Refer to the wiring schematic in section 6.4 for pin locations. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 16

23 J6 / P6 (Ultra) JB724 / PB724 JB324 / PB324 (Encore) Figure 12: Forward Pressure Bulkhead Connectors - Looking AFT (Encore shown) Figure 13: Ground Connector Figure 14: Primus 1000 Location (Right ADC) ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 17

24 4 INSTALLATION - ELECTRICAL The ADAS h system consists of three external harnesses. The harnesses are appropriately labeled J1 and all wire used meet the specifications of MIL-C Engine / Airframe Sensors Primus 1000 Air Data Computer (Right ADC) Wiring The ADAS h ARINC429 Rx channel 1 will connect to the Right Air Data Computer (ADC) ARINC429 (low speed) output and will receive air data (Pressure Altitude, Indicated Airspeed, and Total Air Temperature). 010 Trim the AAB00B24 cable to length. 020 Following the illustration (Figure 15), splice to the right ADC ARINC429 signal using the following pin configuration. Color Right ADC (PN372) WHT Pin 60 (Arinc429 +) WHT/BLU Pin 61 (Arinc429 ) 030 Secure all wiring Engine 1 N1 Indicator 010 Trim the AAP10B24 cable to length. 020 Following the illustration (Figure 15), splice to the N1 signal at the indicator using the pin configuration shown. Model 560 S/N Model 560 S/N Color Eng 1 N1 Indicator (PI024) Eng 1 N1 Indicator (PI055) WHT Pin J Pin 68 WHT/BLU Pin K Pin Secure all wiring Engine 2 N1 Indicator 010 Trim the AAP12B24 cable to length. 020 Following the illustration (Figure 15), splice to the N1 signal at the indicator using the pin configuration shown. Model 560 S/N Model 560 S/N Color Eng 2 N1 Indicator (PI025) Eng 2 N1 Indicator (PI056) WHT Pin J Pin 68 WHT/BLU Pin K Pin Secure all wiring Engine 1 N2 Indicator 010 Trim the AAP11B24 cable to length. 020 Following the illustration (Figure 15), splice to the N2 signal at the indicator using the pin configuration shown. Model 560 S/N Model 560 S/N Color Eng 1 N2 Indicator (PI026) Eng 1 N2 Indicator (PI055) WHT Pin Y Pin 70 WHT/BLU Pin Z Pin Secure all wiring. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 18

25 4.1.5 Engine 2 N2 Indicator 010 Trim the AAP13B24 cable to length. 020 Following the illustration (Figure 15), splice to the N2 signal at the indicator using the pin configuration shown. Model 560 S/N Model 560 S/N Color Eng 2 N2 Indicator (PI026) Eng 2 N2 Indicator (PI056) WHT Pin Y Pin 71 WHT/BLU Pin Z Pin Secure all wiring Engine 1 Fuel Flow Indicator 010 Trim the AAA25B24 cable to length. 020 Following the illustration (Figure 15), splice to the Fuel Flow signal using the pin configuration shown. Model 560 S/N Model 560 S/N Color Eng 1 Fuel Flow Signal (PI028) Eng 1 Fuel Flow Signal (PB724) WHT Pin G Pin 21 WHT/BLU Pin P Pin Secure all wiring Engine 2 Fuel Flow Indicator 010 Trim the AAA26B24 cable to length. 020 Following the illustration (Figure 15), splice to the Fuel Flow signal at the indicator using the pin configuration shown. Model 560 S/N Model 560 S/N Color Eng 2 Fuel Flow Signal (PI029) Eng 2 Fuel Flow Signal (PB724) WHT Pin G Pin 23 WHT/BLU Pin P Pin Secure all wiring Engine 1 ITT Indicator 010 Trim the AAA10B24 cable to length. 020 Following the illustration (Figure 15), splice to the Thermocouple signal at the indicator using the pin configuration shown. Model 560 S/N Model 560 S/N Color Eng 1 ITT Indicator (PI024) Eng 2 ITT Indicator (PI055) RED Pin M (Alumel ) Pin 73 (Alumel ) YEL Pin N (Chromel +) Pin 72 (Chromel +) 030 Secure all wiring. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 19

26 4.1.9 Engine 2 ITT Indicator 010 Trim the AAA11B24 cable to length. 020 Following the illustration (Figure 15), splice to the Thermocouple signal at the indicator using the pin configuration shown. Model 560 S/N Model 560 S/N Color Eng 2 ITT Indicator (PI025) Eng 2 ITT Indicator (PI056) RED Pin M (Alumel ) Pin 73 (Alumel ) YEL Pin N (Chromel +) Pin 72 (Chromel +) 030 Secure all wiring. RAYCHEM SPLICE AIRCRAFT HARNESS SIG + Connector/Indicator SHRINK SLEEVING " Pull Back and Cover Shield " WHT WIRE WHT/BLU WIRE SIG - ADAS-H Marked Cable Weight on Wheels signal INSTALLATION CAUTION: Figure 15: Airframe/Engine Signal Connections The Weight on Wheels (WOW) cable uses a diode to protect the WOW circuit if the cable is shorted to ground. This diode must be installed per the installation instructions and wiring diagram. 010 Trim the AAD00A24 cable to length. 020 Prepare cable(s) and crimp supplied contacts (p/n ) onto the cable(s). 030 Connect the 1N4001 (p/n ) in-line junction diode to the AAD00A24 cable by inserting the contact(s) that were crimped in step 020. Refer to Figure 16 for the correct orientation of the diode. The diode must be located as close as possible to the WOW connection point. 040 Splice to the Right ADC for the WOW connection using the following pin configuration shown. Color Right ADC (PN372) WHT Pin 12 (WOW discrete) 050 Secure all wiring. Figure 16: WOW Diode Orientation ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 20

27 4.2 Electrical Power INSTALLATION CAUTION: The Bus power supply must be chosen to provide power to the ADAS h through an entire engine s running cycle. This is supplied by the Essential Bus directly controlled by the aircraft battery Switch Ensure that any connection to aircraft power incorporates a minimal wire length from the power source to the protection device, fuse or breaker. Recommended length is (6) six inches or less. Ensure that the wire is protected from shorting out against the airframe or any other sharp objects during routing. Use spiral wrap or standoffs if necessary Bus (Switched) Power Connection 010 Trim the supplied M22759/ (single conductor non-shielded) wire AAV10A22 cable to length. 020 Following illustration Figure 17, connect the wire to one side of the supplied breaker. 030 Connect the other end of the breaker to Essential Bus on the Left Circuit Breaker Panel in the cockpit. 040 Secure all wiring. Figure 17: Circuit Breaker Wiring ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 21

28 5 HARNESS CONNECTOR SIGNAL PINOUTS INSTALLATION CAUTION: The Bus power supply must be chosen to provide power to the ADAS h through an entire engine s running cycle. This is supplied by the Essential Bus directly controlled by the aircraft battery Switch Before making any wiring connections, verify all connection locations with the aircraft manufacturer 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 a cable behind a label, be sure to re-label it. For detailed Wiring Routing Drawings refer to Appendix A, Section 12.6 and 12.7 Refer to Model 560 Wiring Diagram Manual (Wiring Maintenance Practices). 5.1 J1 Harness Connector Pin Harness Wire Color Signal Name Wired To Section 6 1 COND CABLE J1 F & H WHT 28 VDC Bus Aircraft Bus Pwr 1 COND CABLE J1 G WHT System Ground Aircraft Ground 5.2 J2 Harness Connector Pin Harness Wire Color Signal Name Wired To Section 6 2 COND CABLE J2 26 WHT ARINC1 RX HI Primus 1000 ADC J2 27 WHT/BLU ARINC1 RX Lo Primus 1000 ADC 2 COND CABLE J2 5 WHT Eng 1 N2 SPD+ Eng 1-N2 Indicator J2 6 WHT/BLU Eng 1 N2 SPD- Eng 1-N2 Indicator 2 COND CABLE J2 7 WHT Eng 1 N1 SPD+ Eng 1-N1 Indicator J2 8 WHT/BLU Eng 1 N1 SPD- Eng 1-N1 Indicator 2 COND CABLE J2 2 WHT Eng 1 Wf PPH+ Eng 1-Fuel Flow J2 4 WHT/BLU Eng 1 Wf PPH- Eng 1-Fuel Flow 2 COND CABLE J2 11 RED Eng 1 ITT- (Alumel) Eng 1-ITT Indicator J2 12 YEL Eng 1 ITT+ (Chromel) Eng 1-ITT Indicator 2 COND CABLE J2 13 RED Eng 2 ITT- (Alumel) Eng 2-ITT Indicator J2 14 YEL Eng 2 ITT+ (Chromel) Eng 2-ITT Indicator ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 22

29 5.3 J3 Harness Connector Pin Harness Wire Color Signal Name Wired To Section 6 2 COND CABLE J3 26 WHT Eng 2 Wf PPH+ Eng 2-Wf Indicator J3 27 WHT/BLU Eng 2 Wf PPH- Eng 2-Wf Indicator 2 COND CABLE J3 20 WHT Eng 2 N1 SPD+ Eng 2-N1 Indicator J3 21 WHT/BLU Eng 2 N1 SPD- Eng 2-N1 Indicator 2 COND CABLE J3 22 WHT Eng 2 N2 SPD+ Eng 2-N2 Indicator J3 23 WHT/BLU Eng 2 N2 SPD- Eng 2-N2 Indicator 1 COND CABLE J3 3 WHT WOW (Discrete) Primus 1000 ADC ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 23

30 6 WIRING DIAGRAM 6.1 ADASh Connection Chart 560 Ultra S/N with Analog Instruments Model 560 Ultra S/N (Analog Instruments) Sensor Wire Labels Aircraft Connection ADAS h Connector LFT CB Panel Essential Bus J1 A/C Bus AAV10A22 Circuit Breaker Pin F WHT & Pin H WHT Aircraft Grounding Plug NDC17 J1 Aircraft Ground AA00A22N Ground Pin G WHT Engine 1 N1 Indicator PI024 J2 Engine 1 N1 AAP10B24 Pin J Pin 7 WHT Indicator Pin K Pin 8 WHT/BLU Engine 2 N1 Indicator PI025 J3 Engine 2 N1 AAP12B24 Indicator Pin J Pin 20 WHT Pin K Pin 21 WHT/BLU Engine 1 N2 Indicator PI026 J2 Engine 1 N2 AAP11B24 Indicator Pin Y Pin 5 WHT Pin Z Pin 6 WHT/BLU Engine 2 N2 Indicator PI027 J3 Engine 2 N2 AAP13B24 Pin Y Pin 22 WHT Indicator Pin Z Pin 23 WHT/BLU Engine 1 ITT Indicator PI024 J2 Engine 1 ITT AAA10B24 Pin M Pin 11 RED Indicator Pin N Pin 12 YEL Engine 2 ITT Indicator PI025 J2 Engine 2 ITT AAA11B24 Indicator Pin M Pin 13 RED Pin N Pin 14 YEL Engine 1 Fuel flow Indicator PI028 J2 Engine 1 Fuel AAA25B24 Pin G Pin 2 WHT Flow Indicator Pin P Pin 4 WHT/BLU Engine 2 Fuel flow Indicator PI029 J3 Engine 2 Fuel AAA26B24 Pin G Pin 26 WHT Flow Indicator Pin P Pin 27 WHT/BLU Right ADC PN372 J2 Primus 1000 AAB00B24 ADC Pin 60 Pin 26 WHT Pin 61 Pin 27 WHT/BLU Weight on Right ADC PN372 J3 AAD00A24 Wheels (WOW) Pin 12 Pin 3 WHT Table 1: Connection Chart Ultra S/N with Analog Instruments ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 24

31 6.2 ADASh Connection Chart 560 Encore S/N with Analog Instruments Model 560 Encore S/N (Analog Instruments) Sensor Wire Labels Aircraft Connection ADAS h Connector LFT CB Panel Essential Bus J1 A/C Bus AAV10A22 Circuit Breaker Pin F WHT & Pin H WHT Aircraft Grounding Plug NDC17 J1 Aircraft Ground AA00A22N Ground Pin G WHT Engine 1 N1 Indicator PI024 J2 Engine 1 N1 AAP10B24 Indicator Pin J Pin 7 WHT Pin K Pin 8 WHT/BLU Engine 2 N1 Indicator PI025 J3 Engine 2 N1 AAP12B24 Indicator Pin J Pin 20 WHT Pin K Pin 21 WHT/BLU Engine 1 N2 Indicator PI026 J2 Engine 1 N2 AAP11B24 Pin Y Pin 5 WHT Indicator Pin Z Pin 6 WHT/BLU Engine 2 N2 Indicator PI027 J3 Engine 2 N2 AAP13B24 Pin Y Pin 22 WHT Indicator Pin Z Pin 23 WHT/BLU Engine 1 ITT Indicator PI024 J2 Engine 1 ITT AAA10B24 Indicator Pin M Pin 11 RED Pin N Pin 12 YEL Engine 2 ITT Indicator PI025 J2 Engine 2 ITT AAA11B24 Indicator Pin M Pin 13 RED Pin N Pin 14 YEL Engine 1 Fuel flow PB724 J2 Engine 1 Fuel AAA25B24 Pin 21 Pin 2 WHT Flow Indicator Pin 22 Pin 4 WHT/BLU Engine 2 Fuel flow PB724 J3 Engine 2 Fuel AAA26B24 Pin 23 Pin 26 WHT Flow Indicator Pin 24 Pin 27 WHT/BLU Right ADC PN372 J2 Primus 1000 AAB00B24 ADC Pin 60 Pin 26 WHT Pin 61 Pin 27 WHT/BLU Weight on Right ADC PN372 J3 AAD00A24 Wheels (WOW) Pin 12 Pin 3 WHT Table 2: Connection Chart 560 Encore S/N with Analog Instruments ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 25

32 6.3 ADASh Connection Chart 560 Encore S/N with LCD Instruments Model 560 Encore S/N (LCD Instruments) Sensor Wire Labels Aircraft Connection ADAS h Connector LFT CB Panel Essential Bus - J1 A/C Bus AAV10A22 Circuit Breaker Pin F WHT & Pin H WHT Aircraft Grounding Plug NDC17 J1 Aircraft Ground AA00A22N Ground Pin G WHT Engine 1 N1 Indicator PI055 J2 Engine 1 N1 AAP10B24 Indicator Pin 68 Pin 7 WHT Pin 69 Pin 8 WHT/BLU Engine 2 N1 Indicator PI056 J3 Engine 2 N1 AAP12B24 Indicator Pin 68 Pin 20 WHT Pin 69 Pin 21 WHT/BLU Engine 1 N2 Indicator PI055 J2 Engine 1 N2 AAP11B24 Pin 70 Pin 5 WHT Indicator Pin 71 Pin 6 WHT/BLU Engine 2 N2 Indicator P1056 J3 Engine 2 N2 AAP13B24 Pin 71 Pin 22 WHT Indicator Pin 70 Pin 23 WHT/BLU Engine 1 ITT Indicator PI055 J2 Engine 1 ITT AAA10B24 Indicator Pin 73 Pin 11 RED Pin 72 Pin 12 YEL Engine 2 ITT Indicator PI056 J2 Engine 2 ITT AAA11B24 Indicator Pin 73 Pin 13 RED Pin 72 Pin 14 YEL Engine 1 Fuel flow PB724 J2 Engine 1 Fuel AAA25B24 Pin 21 Pin 2 WHT Flow Indicator Pin 22 Pin 4 WHT/BLU Engine 2 Fuel flow PB724 J3 Engine 2 Fuel AAA26B24 Pin 23 Pin 26 WHT Flow Indicator Pin 24 Pin 27 WHT/BLU Right ADC PN372 J2 Primus 1000 AAB00B24 ADC Pin 60 Pin 26 WHT Pin 61 Pin 27 WHT/BLU Weight on Right ADC PN372 J3 AAD00A24 Wheels (WOW) Pin 12 Pin 3 WHT Table 3: Connection Chart Encore S/N with LCD Instruments ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary 26

33 6.4 Wiring Schematic - Model 560 Ultra S/N with Analog Instruments NOTE 1: Route wire in accordance with Model 560 Wiring Diagram Manual (Wiring Maintenance Practices) NOTE 2: For detailed wire routing drawings refer to Appendix A, Section 12.7 NOTE 3: Use pin locations shown or locate adjacent spare pins if unavailable on fwd pressure bulkhead and circuit breaker panel connectors. Ground Strap To Processor Bracket ADAS Hybrid ADHY-A Circuit Breaker Panel Primus 1000 "ADC" + Primus 1000 "ADC" - Eng 1 - N1 Indicator + Eng 1 - N1 Indicator - Eng 1 - N2 Indicator + Eng 1 - N2 Indicator - PN PI024 J K PI026 Y Z WHT WHT/BLU WHT AAP10B24 WHT/BLU WHT AAP11B24 WHT/BLU Fwd Pressure Bulkhead P6 J6 6 5 G G 6 H H *A *B *A *B 5 5 AAB00B24 WHT AAP10B24 WHT/BLU WHT AAP11B24 WHT/BLU J2-37 S ARINC1 RXHI (Low Speed) ARINC1 RXLO (Low Speed) Eng 1 N1 SPD + Eng 1 N1 SPD - Eng 1 N2 SPD + Eng 1 N2 SPD - J1-15 S AC BUS+ AC BAT+ AC GND F H G Fwd Pressure Bulkhead J6 P6 AAV10A22 WHT 5 6 AAV10A22 X X AA00A22N WHT 7 Aircraft Ground NDC17 WHT 9 J131 NN P131 NN 10 1 AMP CB (ADASh Only) or 2 AMP CB (ADASh with DTU) 1 2 LFT CB Panel ESSENTIAL BUS Bus Bar HC005 Eng 1 - ITT Indicator (CH) Eng 1 - ITT Indicator (AL) PI024 N M YEL RED AAA10B *N *P *N *P 2 1 YEL RED AAA10B Eng 1 ITT (CH) Eng 1 ITT (AL) Eng 2 - ITT Indicator (CH) Eng 2 - ITT Indicator (AL) PI025 N M YEL RED AAA11B J K J K 2 1 YEL RED AAA11B Eng 2 ITT (CH) Eng 2 ITT (AL) Eng 1 - Fuel Flow Indicator + Eng 1 - Fuel Flow Indicator - PI028 G P WHT WHT/BLU AAA25B L M L M 5 5 WHT AAA25B24 WHT/BLU 2 4 Eng 1 Fuel Flow + Eng 1 Fuel Flow - Y Y Eng 2 - Fuel Flow Indicator + Eng 2 - Fuel Flow Indicator - Eng 2 - N2 Indicator + Eng 2 - N2 Indicator - PI029 G P PI027 Y Z WHT AAA26B24 WHT/BLU WHT AAP13B24 WHT/BLU *G *H *F N *G *H *F N WHT AAA26B24 WHT/BLU WHT AAP13B24 WHT/BLU J3-37 SB Eng 2 Fuel Flow + Eng 2 Fuel Flow - Eng 2 N2 SPD + Eng 2 N2 SPD - J4 - Lemo -- AC BUS AUX BAT+ AC BAT+ Run/Conf ig AC GND RS485 - RS Eng 2 - N1 Indicator + Eng 2 - N1 Indicator - PI025 J K WHT AAP12B24 WHT/BLU 6 6 *I *J *I *J 5 5 WHT AAP12B24 WHT/BLU Eng 2 N1 SPD + Eng 2 N1 SPD - Primus 1000 "Right ADC" PN DIODE 8 1N4001 WHT AAD00A24 3 WOW (DI-L3) QTY REF DES 1 2 PART NO. M39029/ ALUMEL SOCKET M39029/ CHROMEL SOCKET 3 M39029/9-134 DESCRIPTION ALUMEL PIN COLOR BANDS 1st 2nd 3rd 9 6 M39029/4-110 PIN BRN BRN BLK BRN BRN BRN YEL YEL ORG 2 4 M39029/9-135 CHROMEL PIN BRN ORG 9 5 M39029/5-115 SOCKET BRN BRN BLK BRN YEL GRN GRN BASIC CRIMP TOOL M22520/1-01 or M22520/2-01 Positioner M22520/1-01 or M22520/ M39029/ SOCKET BROWN WHT RED K503/TH PIN N/A N/A N/A M22520/1-01 M22520/ SOCKET N/A N/A N/A Tyco p/n PIN N/A N/A N/A or Equivelent INSTALLING TOOL M81969/14-02 (RED) Tyco p/n or Equivelent REMOVAL TOOL M81969/14-02 (White) Tyco p/n or Equivelent Figure 18: ADAS h Wiring Schematic Model 560 Ultra S/N wih Analog Instruments ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

34 6.5 Wiring Schematic - Model 560 Encore S/N with Analog Instruments NOTE 1: Route wire in accordance with Model 560 Wiring Diagram Manual (Wiring Maintenance Practices) NOTE 2: For detailed wire routing drawings refer to Appendix A, Section 12.6 NOTE 3: Use pin locations shown or locate adjacent spare pins if unavailable on fwd pressure bulkhead and circuit breaker panel connectors. Ground Strap To Processor Bracket ADAS Hybrid ADHY-A Circuit Breaker Panel Primus 1000 "Right ADC" + Primus 1000 "Right ADC" - Eng 1 - N1 Indicator + Eng 1 - N1 Indicator - Eng 1 - N2 Indicator + Eng 1 - N2 Indicator - PN PI024 J K PI026 Y Z WHT WHT/BLU WHT AAP10B24 WHT/BLU WHT WHT/BLU AAP11B24 Fwd Pressure Bulkhead PB324 JB E F G H E F G H WHT WHT/BLU WHT WHT/BLU AAB00B24 AAP10B24 AAP11B J2-37 S ARINC1 RXHI (Low Speed) ARINC1 RXLO (Low Speed) Eng 1 N1 SPD + Eng 1 N1 SPD - Eng 1 N2 SPD + Eng 1 N2 SPD - J1-15 S AC BUS+ AC BAT+ AC GND F H G AAV10A22 WHT AA00A22N WHT Fwd Pressure Bulkhead 5 JB324 PB324 R R 6 7 Aircraft Ground NDC17 AAV10A22 WHT 9 J131 NN P131 NN 10 1 AMP CB (ADASh Only) or 2 AMP CB (ADASh with DTU) 1 2 LFT CB Panel ESSENTIAL BUS Bus Bar HC005 Eng 1 - ITT Indicator (CH) Eng 1 - ITT Indicator (AL) PI024 N M YEL RED AAA10B M N M N 2 1 YEL RED AAA10B Eng 1 ITT (CH) Eng 1 ITT (AL) Eng 2 - ITT Indicator (CH) Eng 2 - ITT Indicator (AL) PI025 N M YEL RED AAA11B K L K L 2 1 YEL RED AAA11B Eng 2 ITT (CH) Eng 2 ITT (AL) Fwd Pressure Bulkhead PB724 WHT AAA25B24 WHT/BLU 2 4 Eng 1 Fuel Flow + Eng 1 Fuel Flow - Eng 1 - Fuel Flow + Eng 1 - Fuel Flow Eng 2 - N2 Indicator + Eng 2 - N2 Indicator - PI027 Y Z WHT AAP13B24 WHT/BLU Eng 2 - Fuel Flow + Eng 2 - Fuel Flow - C D Fwd Pressure Bulkhead PB324 JB C D 5 WHT WHT/BLU WHT AAA26B24 WHT/BLU AAP13B J3-37 SB Eng 2 Fuel Flow + Eng 2 Fuel Flow - Eng 2 N2 SPD + Eng 2 N2 SPD - J4 - Lemo -- AC BUS AUX BAT+ AC BAT+ Run/Conf ig AC GND RS485 - RS Eng 2 - N1 Indicator + Eng 2 - N1 Indicator - PI025 J K WHT WHT/BLU AAP12B A B A B 5 5 WHT WHT/BLU AAP12B Eng 2 N1 SPD + Eng 2 N1 SPD - PN372 Primus 1000 "Right ADC" 12 DIODE 8 8 1N4001 WHT AAD00A24 3 WOW (DI-L3) QTY REF DES PART NO. DESCRIPTION M39029/ ALUMEL SOCKET M39029/ CHROMEL SOCKET M39029/ CHROMEL PIN COLOR BANDS 1st 2nd 3rd VIOLET 9 6 M39029/ PIN ORG BLU ORG YEL GRN GRN WHT BLK WHT BLK 3 M39029/ ALUMEL PIN YEL VIOLET GRN BLU 5 M39029/ SOCKET ORG GRN VIOLET BASIC CRIMP TOOL M22520/1-01 or M22520/2-01 Positioner M22520/1-04 or M22520/2-10 INSTALLING TOOL M81969/14-02 (RED) 1 7 M39029/ SOCKET BROWN WHT RED K503/TH PIN N/A N/A N/A M22520/1-01 M22520/ SOCKET N/A N/A N/A Tyco p/n Tyco p/n PIN N/A N/A N/A or Equivelent or Equivelent REMOVAL TOOL M81969/14-02 (White) Tyco p/n or Equivelent Figure 19: ADAS h Wiring Schematic Model 560 Encore S/N with Analog Instruments ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

35 6.6 Wiring Schematic - Model 560 Encore S/N with LCD Instruments NOTE 1: Route wire in accordance with Model 560 Wiring Diagram Manual (Wiring Maintenance Practices) NOTE 2: For detailed wire routing drawings refer to Appendix A, Section 12.6 NOTE 3: Use pin locations shown or locate adjacent spare pins if unavailable on fwd pressure bulkhead and circuit breaker panel connectors. Ground Strap To Processor Bracket ADAS Hybrid ADHY-A Circuit Breaker Panel Primus 1000 "Right ADC" + Primus 1000 "Right ADC" - Eng 1 - N1 Indicator + Eng 1 - N1 Indicator - Eng 1 - N2 Indicator + Eng 1 - N2 Indicator - PN PI PI WHT WHT/BLU WHT WHT/BLU WHT WHT/BLU AAP10B24 AAP11B24 Fwd Pressure Bulkhead PB324 JB E F G H E F G H WHT WHT/BLU WHT WHT/BLU AAB00B24 AAP10B24 AAP11B J2-37 S ARINC1 RXHI (Low Speed) ARINC1 RXLO (Low Speed) Eng 1 N1 SPD + Eng 1 N1 SPD - Eng 1 N2 SPD + Eng 1 N2 SPD - J1-15 S AC BUS+ AC BAT+ AC GND F H G AAV10A22 WHT AA00A22N WHT Fwd Pressure Bulkhead 5 JB324 PB324 R R 6 7 Aircraft Ground NDC17 AAV10A22 WHT 9 J131 NN P131 NN 10 1 AMP CB (ADASh Only) or 2 AMP CB (ADASh with DTU) 1 2 LFT CB Panel ESSENTIAL BUS Bus Bar HC005 Eng 1 - ITT Indicator (CH) Eng 1 - ITT Indicator (AL) PI YEL RED AAA10B M N M N 2 1 YEL RED AAA10B Eng 1 ITT (CH) Eng 1 ITT (AL) Eng 2 - ITT Indicator (CH) Eng 2 - ITT Indicator (AL) PI YEL RED AAA11B K L K L 2 1 YEL RED AAA11B Eng 2 ITT (CH) Eng 2 ITT (AL) Fwd Pressure Bulkhead PB724 WHT AAA25B24 WHT/BLU 2 4 Eng 1 Fuel Flow + Eng 1 Fuel Flow - Eng 1 - Fuel Flow Indicator + Eng 1 - Fuel Flow Indicator Eng 2 - N2 Indicator + Eng 2 - N2 Indicator - PI WHT WHT/BLU Eng 2 - Fuel Flow Indicator + Eng 2 - Fuel Flow Indicator - AAP13B24 C D Fwd Pressure Bulkhead 6 6 PB324 JB324 C D 5 5 WHT AAA26B24 WHT/BLU WHT AAP13B24 WHT/BLU J3-37 SB Eng 2 Fuel Flow + Eng 2 Fuel Flow - Eng 2 N2 SPD + Eng 2 N2 SPD - J4 - Lemo -- AC BUS AUX BAT+ AC BAT+ Run/Conf ig AC GND RS485 - RS Eng 2 - N1 Indicator + Eng 2 - N1 Indicator - PI WHT WHT/BLU AAP12B A B A B 5 5 WHT WHT/BLU AAP12B Eng 2 N1 SPD + Eng 2 N1 SPD - Primus 1000 "Right ADC" PN DIODE 8 1N4001 WHT AAD00A24 3 WOW (DI-L3) QTY REF DES PART NO. DESCRIPTION M39029/ ALUMEL SOCKET M39029/ CHROMEL SOCKET M39029/ CHROMEL PIN COLOR BANDS 1st 2nd 3rd VIOLET 9 6 M39029/ PIN ORG BLU ORG GRN WHT BLK WHT BLK 3 M39029/ ALUMEL PIN YEL VIOLET GRN 5 M39029/ SOCKET YEL GRN ORG GRN BLU VIOLET BASIC CRIMP TOOL M22520/1-01 or M22520/2-01 Positioner M22520/1-04 or M22520/ M39029/ SOCKET BROWN WHT RED K503/TH PIN N/A N/A N/A M22520/1-01 M22520/ SOCKET N/A N/A PIN N/A N/A N/A N/A Tyco p/n or Equivelent INSTALLING TOOL M81969/14-02 (RED) Tyco p/n or Equivelent REMOVAL TOOL M81969/14-02 (White) Tyco p/n or Equivelent Figure 20: ADAS h Wiring Schematic Model 560 Encore S/N with LCD Instruments ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

36 7 SYSTEM OPERATION OVERVIEW The ADAS h is a dual function instrument that gathers and records engine information from sensors for later downloading. The ADAS h 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 ADAS h Functional Description Engine Run Logging The ADAS h is capable of recording engine runs with up to 4 different engine run criteria for each engine. For each 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 Cycle Logging ADAS h 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) ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

37 7.1.3 Event Monitoring and Time History Buffer Events: The ADAS h can be configured to monitor and record airframe or engine exceedances or events. Up to thirty-two (32) basic Airman s Flight Manual (AFM) exceedances and operator specific events can be configured. Each event is logged independently of engine run logging. Each event records the date and time of the event; its duration, average sensor value, and minimum or maximum sensor value. Events can be set to comprise inputs from either one, two or three sensors. Time History Buffer: The ADAS h 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 the 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 a period before, during, or after an event. The operator can set the point before an event and the point after an event to log the time history buffer to permanent memory. The maximum time stored by the processor that can be held by the time history is two minutes Trend Monitoring Engine trend information (data is compatible with P&WC ECTM ) is described as follows: Autotrend: The ADAS h can be configured to initiate an autotrend by defining a stable criteria consisting of up to ten (10) sensors. If the stable criteria are met, the ADAS h 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-tests are 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, or Configuration Mode. For data collection it is operated in Run mode. For communication through the download 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 to CONF. Run Mode is entered when the cable is not attached, or when it is attached and the RUN/CONF Switch is set to RUN. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

38 7.4 Run Mode Description (States) There are four possible states for the system in Run Mode. Each state determines the fault. System States: 1. Normal 2. Maintenance 3. Caution 4. Fault Definitions: In Normal state, the system is performing normally OR recorded an input programmed to indicate Normal state. In Maintenance state, the system recorded an input programmed to indicate Maintenance state. In Caution state, the system recorded an input programmed to indicate Caution state. In Fault state, the system has failed OR the system recorded an input programmed to indicate Fault state. Trend Mode: The ADAS h can be configured to take an automatic trend sample whenever certain engine/flight conditions are met. Once the trend criteria are met, the system will collect a sample of data for later review by maintenance personnel. Single/Dual Engine Functions: The ADAS h monitoring system will monitor and record engine run, trend, cycle, and exceedance information for both single and dual engine aircraft. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

39 8 SYSTEM CONFIGURATION The ADAS h is a combination of hardware and software designed to have a wide range of application. In order to correctly operate with the specific aircraft type it is installed in, the system must first be configured to expect the particular sensor and signal combinations available on that aircraft as well as the engine type and other necessary information. The installer, with the help of a computer and software communication tools, performs configuration and Configuration. This requires a laptop computer connected to the system with a download cable and running P&W Engine Services Monitor Link Program (MLP). The MLP gives field personnel the ability to monitor the 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 called TurbineTracker. MLP and TurbineTracker make it possible to quickly transfer and manage the aircraft s configuration data, as well as operational data (log data) for fleet comparison and analysis. The TurbineTracker website is located atwww.turbinetracker.aero. To obtain a TurbineTracker user account and password, contact P&W Engine Services Help Desk. Current manuals for both TurbineTracker and MLP are available through the TurbineTracker website. The following sections and instructions for configuration and calibration of the system require familiarity with the MLP and TurbineTracker manuals and software. While this section of the installation manual cannot replace the software manuals, a few of the special terms and concepts used in the configuration and calibration instructions are briefly described in this manual. See the software manuals for full descriptions and procedures for 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. This information 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 and correspond 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 in real time. Live Data Display may be used in flight and on the ground when adjusting the calibration or testing and troubleshooting the system. Log Data: The stored operational aircraft exceedance, event, cycle, and sensor readings collected by the processor. In normal aircraft use, the information gathering function of the system creates Log Data. This data is stored in raw form (a Log File) and can be extracted and further processed into useful information through MLP and TurbineTracker. MLP (Monitor Link Program): The P&W Engine Services communication program is used to transfer data to and 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 ADAS h. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

40 One Point Offset Calibration (P2): A method that uses a single reading (or point) to correct (calibrate) a sensor signal. A One Point Offset Calibration is a less precise offset method of calibration than a Two Point Calibration. A One Point Offset Calibration is used when the calibration occurs on the low end of a sensor s potential operating range and a Two Point Calibration cannot be accomplished. To increase the useful precision of the one point offset method, a reading at the low end of a sensor s signal range is preferred. For example, if a sensor reading is supposed to fall between 10 degrees and 100 degrees, a test reading at 20 degrees will calibrate the system better than one at 70 degrees. If a reading at 0 has been attempted as a One Point Offset Calibration, the system has not been usefully calibrated at all. NOTE: The One Point Offset Calibration Method only ensures that the low end of a sensor signal s range is calibrated. Never use 0 when accomplishing the One Point Offset Calibration Method. One Point Slope Calibration (P1): A second method that uses a single reading (or point) to correct (calibrate) a sensor signal. A One Point Slope Calibration is a less precise method of calibration than a Two Point Calibration. A One Point Slope Calibration is used when the calibration occurs on the high end of a sensor s potential operating range and a Two Point calibration cannot be accomplished. To increase the useful precision of the one point slope method, a reading at the high end of a sensor s signal range is preferred. For example, if a sensor reading is supposed to fall between 100 and 500, a test reading at 400 will calibrate the system better than one at 150. If a reading at 0 has been attempted as a One Point Slope Calibration, the system has not been usefully calibrated at all. NOTE: The One Point Slope Calibration Method only ensures that the high end of a sensor signal s range is calibrated. Never use 0 when accomplishing the One Point Slope Calibration Method. Two Point Calibration (P1 & P2): The most accurate method of calibration, requiring both a low and high value to correct (calibrate) a sensor signal. A Two Point Calibration occurs when calibration equipment or the manual sensor calibration methods are used. If a reading at 0 has been attempted as a Two Point Calibration, the system has not been usefully calibrated at all. NOTE: The Two Point Calibration Method ensures that the low end AND high end of a sensor s signal range are calibrated. Never use 0 when accomplishing the Two Point Calibration Method. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

41 8.2 Processor Configuration These instructions require that the installer have a laptop computer with the current version of MLP and has created the required installation configuration file. The current version of the MLP and its manual are available from 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 ADAS h to be configured. The cable can only be plugged in one way. Connect the other end of the cable to a laptop s serial or USB port with the current 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 the MLP 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 processor first, and then select Open. ) 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 If unexpected values are displayed that are not , 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 has created the required installation configuration file. The current version of the MLP and its manual are available from 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 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 with the 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 Troubleshoot failed sensors using ADAS h Instructions for Continued Airworthiness Manual (ADHY-G ). 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. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

42 8.2.2 Calibration Using Test Equipment These instructions require that the installer have a laptop computer with the current version of MLP and has created the required installation configuration file. The current version of MLP and its manual are available from the TurbineTracker website. The same test equipment that is used to check cockpit instruments can be used for calibrating the ADAS h. You can calibrate the ITT sensor using a Barfield tester. The test equipment should be verified to be accurate. NOTE: Opening MLP for a calibration session will increment the configuration file version by one. Any number of sensors may be calibrated during this session without increasing the version number further. Opening, closing, and reopening MLP for calibration multiple times will increment the configuration file version each time a sensor is calibrated, and should be avoided. 010 Connect the download cable to the download port. The cable can only be plugged in one way. Connect the other end of the cable to the serial port on a laptop computer with the current version of the MLP. 020 Place the download cable RUN/CONF switch on the cable in the CONF position. 030 Establish a connection to the processor using the MLP. If unable to establish a connection, proceed with the MLP Troubleshooting Procedure in the MLP Manual (P&W Engine Services Monitor Link Program MLP User s Guide). 040 Select Sensor Calibration under the MLU Menu. Only the Engine Temperature sensors should be calibrated. 050 Select Engine Temperature and perform a Two Point Calibration using a Barfield tester. A value of 300 C should be used for P1 and 700 C for P2. NOTE: If ITT exceeds 700 C during calibration you may illuminate a lamp in the cockpit that will need to be cleared. 060 After calibration, upload the new configuration file version to your TurbineTracker account. It is important to keep the processor, MLP, and Turbine Tracker configuration versions synchronized. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

43 8.2.3 Calibration Using Aircraft Cockpit Instruments These instructions require that the installer have a laptop computer with the current version of MLP and that the installer has created the required installation configuration file. The current version of MLP and its manual are available at the TurbineTracker website. This procedure would be used if the ADAS h Fuel Flow reading does not match the aircraft indicator. This will require the engines to be run at ground idle and a high power setting (takeoff power if able). These two points will be used to calibrate the fuel flow sensors as required. NOTE: Opening MLP for a calibration session will increment the configuration file version by one. Any number of sensors may be calibrated during this session without increasing the version number further. Opening, closing, and reopening MLP for calibration multiple times will increment the configuration file version each time a sensor is calibrated, and should be avoided. 010 Connect the download cable to the download port. The cable can only be plugged in one way. Connect the other end of the cable to the serial port on a laptop computer with the current version of the MLP. 020 Place the download cable RUN/CONF switch on the cable in the CONF position. 030 Establish a connection to the processor using the MLP. If unable to establish a connection, proceed with the MLP Troubleshooting Procedure in the MLP Manual (P&W Engine Services Monitor Link Program MLP User s Guide). 040 Select Sensor Calibration under the MLU Menu. Only the Fuel Flow sensors should be calibrated. 050 Start both Engines. 060 Select Fuel Flow and perform a Two Point Calibration. The Fuel Flow value at ground idle should be used for P1 and a high power setting (takeoff power if able) for P After calibration, upload the new configuration file version to your TurbineTracker account. It is important to keep the processor, MLP, and Turbine Tracker configuration versions synchronized. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

44 9 AIRCRAFT TESTING While following the requirements of FAR , it is recommended that the aircraft be inspected for airworthiness prior to testing. If the ground and/or flight testing of the modified aircraft are not successfully completed, the aircraft should be returned to the original aircraft configuration until the tests are completed and acceptable. After installation of the ADAS h, it is recommended that a ground test be performed to verify the correct operation of the system in the aircraft. The following sections outline the suggested aircraft and system test procedures. 9.1 Aircraft Ground Test 010 With external power connected to aircraft, apply external power to the aircraft bus 020 Power on all avionics 030 If aircraft is equipped with an Electronic Display Unit for engine and/or air data parameters verify that there is no interference caused by the ADAS h 040 Tune Comm 1 and Comm 2 VHF radios to the frequencies in Table 4 and verify that there is no interference caused by the ADAS h. This can normally be conducted by checking for auto squelch break on each listed frequency. 050 If interference is suspected at any particular frequency, pull the ADAS h circuit breaker to see if the interference subsides 060 If the aircraft is equipped with a GPS navigation receiver, display the satellite status page and cycle power on the ADAS h. 070 Verify that the GPS signal strength is not affected by the operation of the ADAS h 080 Tune the #1 and #2 VHF NAV receivers to receive a valid navigational signal from either a VOR ramp tester or a locally tuned VOR navigation transmitter 090 Verify that valid course deviation and a retracted NAV flag are displayed on the HIS or the VOR course indicator Cycle power on the ADAS h and verify that there is no effect on the displayed NAV data 0110 If the aircraft is equipped with an autopilot, initiate autopilot self test. This may require pulling, and then resetting the autopilot circuit breaker with power applied to the ADAS h 0120 Verify that the autopilot completes a successful self-test Survey the aircraft for any other installed equipment that may be affected by interference from the ADAS h. Perform any additional tests as required to determine if the ADAS h creates objectionable interference. This may be accomplished by pulling the ADAS h circuit breaker while observing the subject equipment. List the additional equipment tested and any observed effects in the Electromagnetic Compatibility Testing Table (See Table 5) Remove external power from aircraft and start engine. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

45 Frequency Pass/Fail Frequency Pass/Fail MHZ MHZ MHZ MHZ MHZ MHZ MHZ MHZ MHZ MHZ MHZ MHZ MHZ MHZ MHZ MHZ MHZ MHZ Engine Running: Table 4: 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 of MLP. 020 Establish a connection to the ADAS d processor using MLP. If unable to establish a connection, proceed with the MLP Troubleshooting Procedure in the MLP Manual (P&W Engine Services Monitor Link Program MLP User s Guide). NOTE: If a DTU is installed, then you must enter Transparent mode first to connect to the ADAS d processor. 030 Select Live Data then Text View. Name the Live Data file and select Save. 040 Start engine 050 If aircraft is equipped with an Electronic Display Unit for engine and air data parameters verify that there is no interference caused by the ADAS h 060 With the engine running and the ADAS h system operational, tune Comm 1 and Comm 2 VHF radios to the frequencies in Table 4 and verify that there is no interference caused by the ADAS h. This can normally be conducted by checking for auto squelch break on each listed frequency 070 If interference is suspected at any particular frequency, pull the ADAS h circuit breaker to see if the interference subsides. 080 If the aircraft is equipped with a GPS navigation receiver, display the satellite status page and cycle power on the ADAS h. 090 Verify that the GPS signal strength is not affected by the operation of the ADAS h 0100 Tune the #1 and #2 VHF NAV receivers to receive a valid navigational signal from either a VOR ramp tester or a locally tuned VOR navigation transmitter 0110 Verify that valid course deviation and a retracted NAV flag are displayed on the HIS or the VOR course indicator Cycle power on the ADAS h and verify that there is no effect on the displayed NAV data 0130 If the aircraft is equipped with an autopilot, initiate autopilot self test. This may require pulling, and then resetting the autopilot circuit breaker with power applied to the ADAS h 0140 Verify that the autopilot completes a successful self-test. ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

46 0150 Survey the aircraft for any other installed equipment that may be affected by interference from the ADAS h. Perform any additional tests as required to determine if the ADAS h creates objectionable interference. This may be accomplished by pulling the ADAS h circuit breaker while observing the subject equipment. List the additional equipment tested and any observed effects in the Electromagnetic Compatibility Testing Table (See Table 5) Stabilize the engine(s) at a convenient partial power setting Once the engine readings are stabilized, write down the cockpit instrument values and the Live Data Values in the Ground Test Data Table (See Table 6) Stop Live Data and shut engines down. NOTE: If a DTU is installed, you must Stop Live Data and then exit Transparent mode before shutting down the engine(s). Equipment Problem Found Y/N? Comments Ground Test Comments Flight Test Comments: Ground Test Table 5: Electromagnetic Compatibility Test Table Eng. #1 Eng. #2 Cockpit ADAS d Delta Cockpit ADAS d Delta ITT/TOT N1/Ng/Nl N2/Nh Wf Bus Voltage Altitude Airspeed Table 6: Ground Test Data Aircraft Make: Aircraft Model: Aircraft Registration Number: Aircraft S/N: Test Completed By: ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

47 9.2 Continued Airworthiness Instructions See ADAS h Instructions for Continued Airworthiness, ADHY-G for troubleshooting the system. If you require further assistance, contact the Help Desk: 10 SERVICE P&W Engine Services provides customer support in accordance with the product warranty detailed within the customer s sales contract. If you have any questions concerning any P&W Engine Services product, please do not hesitate to contact us. Our Help Desk accepts calls Monday through Friday between 9:00 AM and 5:00 PM EST. Please have your model and serial number ready when you call. Comments and findings should be forwarded to P&W Engine Services for inclusion in our continued product improvement program. In the event that the ADAS h must be returned for service, contact the P&W Engine Services Help Desk for a Returned Material Authorization (RMA) number. When you receive the RMA number, include it 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 are experiencing. This will greatly assist our technicians in rapidly identifying the problem. After service, the processor will be returned to you or your dealer with the shipping prepaid. Pratt & Whitney Engine Services, Inc. Help Desk 249 Vanderbilt Ave. Norwood, MA (781) Fax: (781) TurbineTrackerSupport@altairavionics.aero ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

48 11 SPECIFICATIONS 11.1 System Specifications GENERAL Chassis Size (each): 3.7" x 1.7" x 6.6" Chassis Weight: System Weight: 1.4 lbs (22 oz.) Approximately 5 lbs. POWER REQUIREMENTS Voltage Range: Current Draw Power Draw 11 to 32 VDC < 1.0 A 8 Watts operating 20 mwatts standby ENVIRONMENTAL (ALL TESTS TO RTCA/DO-160E) Test Performed RTCA Section Level Temperature Section 4.0 Equipment tested to category C4 - Ground Survival Low Temperature Section ºC - Short Time Operational Low Temperature Section ºC - Operational Low Temperature Section ºC - Ground Survival High Temperature Section ºC - Short Time Operational High Temperature Section ºC - Operational High Temperature Section ºC Altitude Section 4.0 Equipment tested to category C4 - Test up to 55,000 ft Pressure Altitude Section Equipment tested to category C4 - Decompression Test Section Equipment tested to category C4 - Overpressure Test Section Equipment tested to category C4 Temperature Variation Section 5.0 Equipment tested to category B, 5 ºC/Min Humidity Section 6.0 Equipment tested to category B Shock Section 7.0 Equipment tested to category B - Operational Section 7.2 Equipment tested to category B - Crash Safety Test Section 7.3 Equipment tested to category B Vibration Section 8.0 Equipment tested to category SB Explosion Proofness Section 9.0 Equipment tested to category E Waterproofness Section 10.0 Equipment tested to category R Fluids Susceptibility Section 11.0 Equipment tested to category F Sand and Dust Section 12.0 Equipment tested to category D ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

49 Fungus Section 13.0 Equipment tested to category F Salt Spray Section 14.0 Equipment tested to category S Magnetic Effect Section 15.0 Equipment tested to category Z Power Input Section 16.0 Equipment tested to category B Voltage Spikes Section 17.0 Equipment tested to category B Audio Freq. Susceptibility, Pwr In Section 18.0 Equipment tested to category B Induced Signal Susceptibility Section 19.0 Equipment tested to category ZC Radio Freq. Susceptibility Section 20.0 Equipment tested to category R Radio Freq. Emission Section 21.0 Equipment tested to category L Lighting Induced Transient Effects Section 22.0 Equipment tested to Category ZZC2 Lightning Direct Effect Section 23.0 Equipment tested to Category X Electrostatic Discharge Section 25.0 Equipment tested to Category A DATA INTERFACE Computer Interface: RS-485 Serial or USB Interface, 57,600 Baud SYSTEM SOFTWARE The ADAS h has been designed and tested to RTCA/DO-178B Level C SAMPLE RATE The ADAS h samples Engine Temperature up to 50 times per second. All other inputs are sampled up to 5 times per second DATA STORAGE System Data: Engine Run Data: Exceedance Data: Trend Sample: Flash Storage Memory: Installation ID / Version Engine Run Date, Engine Run Time, Engine Run Duration, Maximum Sensor Values Observed, Cycles Counted, Maximum Start Temp, Minimum Battery Voltage, Start Duration Exceedance Date, Exceedance Time, Exceedance Duration, Exceedance Type, Maximum/Minimum Value Observed, Average Value Observed, Time History Sensor Recording Auto Trend, Trend Time, Sensor Max Value Observed, Sensor Average Value Observed 8 MB (Log Data) and 24 MB (Continuous Recording) ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

50 11.2 Interface Requirements for Aircraft Sensors FAULT/CAUTION LAMP The ADAS h may interface with an existing cockpit lamp. The lamp shall have the following characteristics: Nominal Voltage +28 VDC Current 40 ma +/- 10% Power Dissipation Average Rated Life (0 C) 1.24 Watts 1,500 Hours PILOT COMMAND SWITCH The ADAS h 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 ADAS h 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 Typical Minimum Maximum +28 VDC VDC 11 VDC 32 VDC WEIGHT ON WHEELS The ADAS h requires a discrete signal input to detect actuation of the aircraft hour meter or weight on wheels. The input shall have the following characteristics: Parameter Specification Comments Input Voltage Range Input Threshold VDC 5.0 VDC < OR = 5.0 VDC ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

51 ENGINE TEMPERATURE The ADAS h measures Engine Temperature using the aircraft s existing Alumel/Chromel (Type K) assembly. The input is isolated from ground and isolated from other instruments. The ADAS h measures Engine Temperature with the following specifications: Parameter Specification Comments Input Range 0 C to 1098 C Accuracy +/- 5 C Isolation Connections to the thermocouple are isolated from ground to prevent interference from other indicators. ENGINE - N1 GAS GENERATOR SPEED (PW535A) The ADAS h measures N1 gas generator speed using the existing aircraft sensors installed on the engine. Requirements and specs for the N1 sensor type are as follows: Parameter Specification Comments Conversion 100% N1 Range 0 150% Voltage output at max engine speed Frequency output DC Resistance at pins 1&2 and 3&4: 1.5 and 50 volts pk-pk. scaling Hz equiv RPM 3000Ohms Max Accuracy +/- 0.2% Min Req 5%N1 ENGINE - N1 GAS GENERATOR SPEED (JT15D-5A) The ADAS h measures N1 gas generator speed using the existing aircraft sensors installed on the engine. Requirements and specs for the N1 sensor type are as follows: Parameter Specification Comments Conversion 100% N1 Range 0 150% Voltage output at max engine speed 5 and 20 volts pk-pk Linear to zero volts at zero speed Frequency output Inductance Resistance Scaling Hz Equiv RPM 460 mh. Max. DC 1400 Ohms Max Accuracy +/- 0.2% Min Req 5%N1 ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

52 ENGINE - N1 GAS GENERATOR SPEED (JT15D-5D) The ADAS h measures N1 gas generator speed using the existing aircraft sensors installed on the engine. Requirements and specs for the N1 sensor type are as follows: Parameter Specification Comments Conversion 100% N1 Range 0 150% Voltage output at max engine speed 5 and 20 volts pk-pk Linear to zero volts at zero speed Frequency output Inductance Resistance Scaling Hz Equiv RPM 460 mh. Max. DC 1400 Ohms Max Accuracy +/- 0.2% Min Req 5%N1 ENGINE N2 POWER TURBINE SPEED (PW535A) The ADAS h measures N2 power turbine speed using the existing aircraft sensors installed on the engine. Requirements and specs for the N2 sensor type are as follows: Parameter Specification Comments Conversion 100% N2 Range 0 150% Voltage output at max engine speed Frequency output DC Resistance at pins 1&2 and 3&4:.75 and 50 volts pk-pk. scaling Hz equiv RPM 3000Ohms Max Accuracy +/- 0.2% Min Req 5%N1 ENGINE N2 POWER TURBINE SPEED (JT15D-5A, -5D) The ADAS h measures N2 power turbine speed using the existing aircraft sensors installed on the engine. Requirements and specs for the N2 sensor type are as follows: Parameter Specification Comments Conversion 100% N2 Range 0 150% Voltage output at max engine speed 40 and 80 volts pk-pk Linear to zero volts at zero speed Frequency output Inductance Resistance Scaling Hz Equiv RPM 460 mh. Max. DC 1400 Ohms Max Accuracy +/- 0.2% Min Req 5%N1 ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

53 AIRCRAFT - FUEL FLOW SPEED The ADAS h measures the Fuel Flow speed using the existing sensors installed on the airframe. Requirements and specs for the Fuel Flow sensor type are as follows: Parameter Specification Comments Range pph Voltage output 0 5 VDC at linear flow rate AIRCRAFT AIRSPEED The ADAS h measures the Airspeed using the existing sensors installed on the airframe. This sensor is on the ARINC 429 Low Speed Bus and the specs are as follows: Parameter Specification Comments Conversion 300 kn ARINC Label 206 SDI 2 BNR Range Resolution.0625 AIRCRAFT PRESSURE ALTITUDE The ADAS h measures the Pressure Altitude using the existing sensors installed on the airframe. This sensor is on the ARINC 429 Low Speed Bus and the specs are as follows: Parameter Specification Comments Conversion ARINC Label 203 SDI 2 40,000 ft BNR Range Resolution 1 AIRCRAFT TOTAL AIR TEMPERATURE The ADAS h measures the Total Air Temperature using the existing sensors installed on the airframe. This sensor is on the ARINC 429 Low Speed Bus and the specs are as follows: Parameter Specification Comments Conversion 10 C ARINC Label 211 SDI 2 BNR Range 2048 Resolution.25 ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

54 12 Appendix A 12.1 ADASh Installation for 560 Encore & Ultra Figure A- 1: ADAS h Installation for 560 Encore & Ultra Sheet 1 of 5 ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

55 Figure A- 2: ADAS h Installation for 560 Encore & Ultra Sheet 2 of 5 ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary

56 Figure A- 3: ADAS h Installation for 560 Encore & Ultra Sheet 3 of 5 ADHY-G Pratt & Whitney Engine Services, Inc. Proprietary