Rockwell Collins 8223132 Information Management System User Manual 946 03N1 001
Rockwell Collins Inc Information Management System 946 03N1 001
Manual
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| Mirror Download [FCC.gov] | |
| Document ID | 2621284 |
| Application ID | ANiFlSnV7zd7adWu1qVYVg== |
| Document Description | Manual |
| Short Term Confidential | No |
| Permanent Confidential | No |
| Supercede | No |
| Document Type | User Manual |
| Display Format | Adobe Acrobat PDF - pdf |
| Filesize | 78.35kB (979427 bits) |
| Date Submitted | 2015-05-21 00:00:00 |
| Date Available | 2015-05-21 00:00:00 |
| Creation Date | 2015-04-22 11:37:57 |
| Producing Software | Acrobat Distiller 10.1.13 (Windows); modified using iText® 5.1.2 ©2000-2011 1T3XT BVBA |
| Document Lastmod | 2015-04-24 09:28:55 |
| Document Title | Microsoft Word - 946-03N1-001 |
| Document Creator | PScript5.dll Version 5.2.2 |
| Document Author: | mkgudenk |
User Manual for Communication Certification of the Information Management System (IMS-6010) Document Number 946-03N1-001 Revision CAGE Code 0EFD0 Rockwell Collins NOTICE: The contents of this document are proprietary to Rockwell Collins and shall not be disclosed, disseminated, copied, or used except for purposes expressly authorized in writing by Rockwell Collins. The technical data in this document (or file) is controlled for export under the Export Administration Regulations (EAR), 15 CFR Parts 730‐774. Violations of these export laws may be subject to fines and penalties under the Export Administration Act. NAME TITLE APPROVAL Prepared By: Tanner S. Shephard Preparer N/A Approved By: Antoine F. Perez‐Vernon Project Engineer On File Approved By: Pamela M. Cook DAC Engineer On File 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 1 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 © 2015 Rockwell Collins. All rights reserved. Information Management System IMS-6010 User Manual Unit Model Collins Part Number Information Management System IMS-6010 822-3132-XXX 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 3 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 This manual includes coverage of the following equipment: ROCKWELL COLLINS, INC. INSTALLATION MANUAL Export Control Classification Notice (ECCN) for this document is 7E994. PROPRIETARY NOTICE FREEDOM OF INFORMATION ACT (5 USC 552) AND DISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY (18 USC 1905) This document and the information disclosed herein are proprietary data of Rockwell Collins, Inc. Neither this document nor the information contained herein shall be used, reproduced, or disclosed to others without the written authorization of Rockwell Collins, Inc., except to the extent required for installation or maintenance of recipient’s equipment. This document is being furnished in confidence by Rockwell Collins, Inc. The information disclosed herein falls within the exemption (b) (4) of 5 USC 552 and the prohibitions of 18 USC 1905. SOFTWARE COPYRIGHT NOTICE © COPYRIGHT 2015 ROCKWELL COLLINS, INC. ALL RIGHTS RESERVED All software resident in this equipment is protected by copyright. We welcome your comments concerning this manual. Although every effort has been made to keep it free of errors, some may occur. When reporting a specific problem, please describe it briefly and include the manual part number, the paragraph or figure number, and the page number. Send your comments to: Rockwell Collins, Inc. 400 Collins Road NE, M/S 153-250 Cedar Rapids, IA 52498-0001 Rockwell Collins, Inc. Customer Response Center 400 Collins Road NE, M/S 133-100 Cedar Rapids, IA 52498-0001 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 4 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 For product orders or inquiries, please contact: 946-03N1-001 TABLE OF CONTENTS Page Chapter/Para LIST OF ILLUSTRATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .iii LIST OF TABLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . iv SAFETY SUMMARY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1 1.1 1.1.1 1.1.2 1.1.3 1.2 1.3 INTRODUCTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1 Equipment Covered. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1 Equipment Specifications.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1 Environmental Qualifications. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 PURPOSE OF EQUIPMENT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3 EQUIPMENT OVERVIEW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 1.3.1 1.3.2 Single Board Computer. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 Solid State Drive. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 1.3.3 Wireless LAN Adapter. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 1.3.4 Power Supply CCA.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 1.3.5 PC Base CCA.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 1.3.6 802 Comm CCA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 1.3.7 1.3.8 Interconnect CCA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 Sim Board CCA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 1.4 1.5 RELATED PUBLICATIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 STORAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 2.1 GENERAL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 2.2 UNPACKING AND INSPECTING EQUIPMENT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 2.3 PRE-INSTALLATION CHECK.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 Cabling Precautions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 2.3.1 2.4 Installation Configurations.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 2.4.2 2.4.3 Strapping Options. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 Input Power. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 2.4.4 Cooling Considerations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 2.5 CABLING INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 2.5.1 2.5.2 2.5.3 2.6 Parts Required. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Connector Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Cable Shields and Cable Shield Grounds. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 CABLE ASSEMBLY - CONNECTOR J1 PINS.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 2.7 CABLE ASSEMBLY - CONNECTOR J2 PINS.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7 CABLE ASSEMBLY - CONNECTOR J3 PINS.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 CABLE ASSEMBLY - CONNECTOR J4 PIN (FUTURE GROWTH). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 CABLE ASSEMBLY - CONNECTOR J5 PINS.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 CABLE ASSEMBLY - CONNECTOR J6 PINS.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 INSTALLATION PROCEDURES.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 2.8 2.9 2.10 2.11 2.12 2.12.1 IMS-6010 Installation and Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 2.13 TESTING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 3.1 OPERATION PROCEDURES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 3.1.1 PLANNING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 2.4.1 Operating Procedures. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 Theory of Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 5 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 946-03N1-001 TABLE OF CONTENTS Chapter/Para Page 4.1 INTRODUCTION TO THEORY OF OPERATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 4.2 INFORMATION MANAGEMENT SYSTEM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 4.3 4.4 4.4.1 FUNCTIONAL DESCRIPTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 SYSTEM INTERFACE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 General Information for Connector J1 Signals. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 Maintenance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.1 INTRODUCTION TO MAINTENANCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.2 TESTING PROCEDURES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.2.1 Initial Power ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.2.2 Power-on Self Test. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.2.3 5.2.4 5.2.5 5.3 Kernel Startup. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 Application Startup. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 Additional Functional Checks.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 SELF TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 6 ii STATE 1 - DEVELOPMENT RELEASE 2015-04-22 GLOSSARY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Glossary-1 946-03N1-001 LIST OF ILLUSTRATIONS Page Title 1-1 IMS-6010 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1 2-1 2-2 2-3 2-4 2-5 IMS-6010 Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 J1 Pin Arrangement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8 J2 Pin Arrangement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9 RJ45 J6 Front Ethernet Indicator Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 IMS-6010 Connectors. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 7 iii STATE 1 - DEVELOPMENT RELEASE 2015-04-22 Number 946-03N1-001 LIST OF TABLES Page Title 1-2 1-3 1-4 2-1 2-2 2-3 2-4 IMS-6010 Equipment Specifications. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 IMS-6010 Environmental Qualifications Form.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 IMS Major Components. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 Related Publications. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 IMS-6010 Mating Connector Hardware.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Mating Cable Guidelines For IMS-6010 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 J1 Connector Pin Functions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5 J2 Connector Pin Functions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10 2-5 2-6 J3 Connector Pin Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 J5 Connector Pin Functions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 2-7 4-1 J6 Connector Pin Functions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 Main Input Power Source. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 1-1 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 8 iv STATE 1 - DEVELOPMENT RELEASE 2015-04-22 Number 946-03N1-001 SAFETY SUMMARY 1. GENERAL ADVISORIES FOR ALL UNITS. Service personnel are to obey standard safety precautions, such as wearing safety glasses, to prevent personal injury while installing or doing maintenance on this unit. Use care when using sealants, solvents and other chemical compounds. Do not expose to excessive heat or open flame. Use only with adequate ventilation. Avoid prolonged breathing of vapors and avoid prolonged contact with skin. Observe all cautions and warnings given by the manufacturer. Remove all power to the unit before disassembling it. Disassembling the unit with power connected is dangerous to life and may cause voltage transients that can damage the unit. This unit may have components that contain materials (such as beryllium oxide, acids, lithium, radioactive ma- terial, mercury, etc) that can be hazardous to your health. If the component enclosure is broken, handle the component in accordance with OSHA requirements 29CFR 1910.1000 or superseding documents to prevent personal contact with or inhalation of hazardous materials. Since it is virtually impossible to determine which components This unit exhibits a high degree of functional reliability. Nevertheless, users must know that it is not practical to monitor for all conceivable system failures and, however unlikely, it is possible that erroneous operation could occur without a fault indication. The pilot has the responsibility to find such an occurrence by means of crosschecks with redundant or correlated data available in the cockpit. Before handling any unit or unit component, ground the repair operator through a conductive wrist strap or other device that uses a 470 kΩ or 1 MΩ series resistor to prevent operator injury. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 9 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 do or do not contain such hazardous materials, do not open or disassemble components for any reason. 946-03N1-001 Turn off power before disconnecting any unit from wiring. Disconnecting the unit without turning power off may cause voltage transients that can damage the unit. a. De-energize or remove all power, signal sources, and loads used with the unit. b. Place the unit on a work surface that can conduct electricity (is grounded). c. Ground the repair operator through a conductive wrist strap or other device using a 470 kΩ or 1 MΩ series resistor to prevent operator injury. d. Ground any tools (and soldering equipment) that will contact the unit. Contact with the operator's hand is a sufficient ground for hand tools that are electrically isolated. e. All ESDS replacement components are shipped in conductive foam or tubes and must be stored in their shipping containers until installed. f. ESDS devices and assemblies that are removed from a unit must immediately be put on the conductive work surface or in g. Place repaired or disconnected circuit cards in aluminum foil or in plastic bags that have a layer of, or are made with, conductive material. h. Do not touch ESDS devices/assemblies or remove them from their containers until they are needed. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 10 vi STATE 1 - DEVELOPMENT RELEASE 2015-04-22 conductive containers. 946-03N1-001 CHAPTER 1 General Information 1.1. INTRODUCTION. This installation manual provides information for the installation of the Information Management System (IMS-6010) in the aircraft. The Information Management System (IMS) is a standalone Line Replaceable Unit (LRU) that can be utilized in multiple avionics applications. 1.1.1. Equipment Covered. Figure 1-1. IMS-6010 1.1.2. Equipment Specifications. Equipment specifications, physical characteristics, and power requirements for IMS-6010 are listed in Table 1-1. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 11 1-1 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 The IMS-6010 is covered in this manual. The IMS-6010 is illustrated as such: general information 946-03N1-001 Table 1-1. IMS-6010 Equipment Specifications. CHARACTERISTIC SPECIFICATION Certification/Related Documents: Certification RTCA Documents Physical: Size: Height 104.78 mm (4.125 in) max. Width 146.05 mm (5.750 in) max. Length 248.54 mm (9.785 in) max. (USB and Ethernet access door in closed position) 1.79 kg (3.95 lb) nominal Weight The IMS has both convectional cooling an internal fan which blows heated air out of the unit. Cooling Requirements Electrical: Power Requirements Mounting Information Refer to the Installation chapter for mounting information. Mating Connector Refer to the Installation chapter for mating connector information. 1.1.3. Environmental Qualifications. Environmental qualifications for the IMS-6010 are listed in Table 1-2. DO-160G SECTION AND CONDITIONS EQUIPMENT QUALIFICATIONS CATEGORIES OF CONDUCTED TESTS REV TEMPERATURE AND ALTITUDE: 4.0 TEMPERATURE: A4 4.5 GROUND SURVIVAL LOW 4.5.1 -55 °C (-67 °F) OPERATING LOW TEMP 4.5.2 -15 °C (+5 °F) GROUND SURVIVAL HIGH 4.5.3 +85 °C (+185 °F) OPERATING HIGH TEMP 4.5.4 +55 °C (+131 °F) IN FLIGHT LOSS OF 4.5.5 V. (30 Minute (+30 °C (+86 °F)) 4.6.1 15, 000 ft TEMP TEMP COOLING ALTITUDE 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 12 1-2 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 Table 1-2. IMS-6010 Environmental Qualifications Form. general information 946-03N1-001 Table 1-2. IMS-6010 Environmental Qualifications Form. - Continued DO-160G EQUIPMENT QUALIFICATIONS SECTION AND CATEGORIES OF CONDUCTED TESTS REV DECOMPRESSION 4.6.2 50,000 ft OVERPRESSURE 4.6.3 170 kPa TEMPERATURE VARIATION 5.0 B. (5 °C per minute) HUMIDITY 6.0 A. (48 hours) SHOCK: 7.0 OPERATIONAL 7.2 Tested at 6-g (11 ms duration) CRASH SAFETY 7.3 Impulse 20-g, sustained 20-g VIBRATION 8.0 (RBBI)(HR)(SM) WATERPROOFNESS 9.0 FLUID SUSCEPTIBILITY 10.0 SAND AND DUST 11.0 FUNGUS RESISTANCE 12.0 SALT SPRAY 13.0 MAGNETIC EFFECT 14.0 POWER INPUT 15.0 VOLTAGE SPIKE 16.0 B and Z. AUDIO FREQUENCY SUSCEPTIBILITY 17.0 INDUCED SIGNAL SUSCEPTIBILITY 18.0 RF SUSCEPTIBILITY 19.0 CC EMISSION OF RF ENERGY 20.0 KR LIGHTNING INDUCED TRANSIENT SUSCEPTIBILITY 21.0 22.0 (A3)(J3)3 ICING 23.0 ELECTROSTATIC DISCHARGE SUSCEPTIBILITY 24.0 25.0 26.0 LIGHTNING DIRECT EFFECTS FLAMMABILITY 1.2. PURPOSE OF EQUIPMENT. Refer to Table 1-3 for a list of the units included in this manual. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 13 1-3 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 CONDITIONS general information 946-03N1-001 1.3. EQUIPMENT OVERVIEW. The IMS is Dzus-rail mounted LRU that provides a commercial data processing capability. The IMS is capable of transferring maintenance data between off-board commercial PC platforms and the aircraft cockpit. The IMS is used to run on-aircraft software packages that are hosted on the Windows 7 operating system. 1.3.1. Single Board Computer. The SBC provides core X86 processing functionality in a small plug-in module. 1.3.2. Solid State Drive. The Solid State Disk drive provides functionality equivalent to a PC spinning hard disk drive. 1.3.3. Wireless LAN Adapter. The Wireless LAN Adapter provides an interface to 802.11 b/g wireless networks. 1.3.4. Power Supply CCA. The Power Supply CCA is a plug-in card assembly that mates with the Interconnect card. The Power Supply converts the 28 VDC nominal power input to a regulated +5 VDC output for use by the other IMS modules. Included is a housekeeping supply and monitors for temperature, voltage and current. Storage capacitors are charged with sufficient energy to allow the IMS to continue to play through 200 ms power interrupt. 1.3.5. PC Base CCA. The PC Base CCA is a plug-in card assembly that mates with the Interconnect card. The PC Base CCA is a Baseboard for hosting the Physical Layer I/O to support the ETX Computer Module. It provides Discrete I/O, one USB 2.0 port, one Ethernet Maintenance port, and a VGA Test port for use outside of the IMS cabinet. The PC Base CCA provides a PCI Bus, two IDE channels, an I2C/SMBus, and an ISA Bus for use within the IMS cabinet. 1.3.6. 802 Comm CCA. The 802 Comm CCA is a plug-in card assembly that mates with the Interconnect card. The 802 Comm CCA also mates directly via stacking connectors with the PC Base card. The 802 Comm CCA provides seven total Ethernet Ports out of the IMS cabinet; two are dedicated for AFDX channels. The 802 Comm CCA provides 802.11b/g Wireless LAN functionality via a mini-PCI interface to a purchased Wireless Adapter mini-PCI card, which is hosted on the 802 Comm. 1.3.7. Interconnect CCA. The Interconnect CCA attaches via screws into the rear of the IMS chassis structure. The Interconnect CCA provides interconnect between the CCAs and the external connectors. The Interconnect CCA provides lightning protection for the power input. The 1.3.8. Sim Board CCA. The Sim Card CCA is a plug-in card assembly that mates directly with a stacking connector on the Comm CCA. The Sim Board CCA provides 4 SIM card slots for cellular function. Table 1-3. IMS Major Components. Assembly Part Number Description Single Board Computer 270-3489-010 Purchased assembly. Solid State Drive 270-3499-020 Purchased assembly. Wireless LAN Adapter 270-3512-010 Purchased assembly. PC Base CCA 828-3845-103 Manufactured circuit card assembly. 802 Comm CCA 828-3846-103 Manufactured circuit card assembly. Power Supply CCA 828-3844-103 Manufactured circuit card assembly. Interconnect CCA 828-3847-003 Manufactured circuit card assembly. Sim Board CCA 828-4292-001 Manufactured circuit card assembly 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 14 1-4 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 Interconnect CCA acts as a filter for signals and provides lightning protection for them. general information 946-03N1-001 1.4. RELATED PUBLICATIONS. Refer to Table 1-4 for a list of publications related to IMS-6010. Table 1-4. Related Publications. PUBLICATION COLLINS PART NUMBER Rockwell Collins Installation Practices Manual 523-0775254 Rockwell Collins Bonding and Grounding Practices Manual 523-0776007 1.5. STORAGE. The IMS-6010 should be stored in its original packing materials and shipping container. If the unit is to be stored for a long period of time, put the unit in an airtight plastic bag with sufficient desiccant to absorb moisture. At no time should the ambient temperature of the storage area fall below -55 °C (-67 °F) or rise above +85 °C (+185 °F). The relative humidity should never exceed 95 percent. If the unit is stored for an extended period of time, retest the unit prior to returning it to service to ensure that possible component 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 15 1-5 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 degradation has not affected performance. 946-03N1-001 CHAPTER 2 Installation 2.1. GENERAL. This chapter provides information for the installation of the Information Management System (IMS-6010). Procedures must be performed as described below to be sure of proper operation and performance. NOTE The information and instructions provided in this chapter are recommendations and do not necessarily correspond with any actual aircraft installation and wiring. This chapter cannot be used in place of a Supplemental Type Certificate (STC) or Type Certificate (TC). 2.2. UNPACKING AND INSPECTING EQUIPMENT. Unpack the equipment carefully and make a careful visual inspection of the unit for possible shipping damage. All claims for damage should be filed with the transportation company involved. If claims for damage are to be filed, save the original shipping container and materials. If no damage can be detected, replace packing materials in the shipping container and save for future use (for example, storage or reshipment). Perform a visual inspection of the unit and inspect for the following concerns: 1. Look for any damage or corrosion. 2. Make sure all parts are intact and in working order. 3. Check connectors J1, J2, J3, J5, and J6 for any damage, corrosion and broken or bent pins. 2.3. PRE-INSTALLATION CHECK. Prior to installation of unit in the aircraft, make sure the system or equipment that will interface with the IMS-6010 is operating properly and all applicable tests have been performed. Refer to the latest revision of the Component Maintenance Manual (CMM) or Illustrated Parts List (IPL) to perform testing of the unit. In the absence of the CMM/IPL, the Acceptance Test Procedure for the panel variant will be used to perform testing of the unit. 2.3.1. Cabling Precautions. Observe the following precautions during the preparation of the interconnect wiring cables: • Bond and shield all parts of the aircraft electrical system such as generators and ignition systems. • Keep connecting cables away from heavy current carrying circuits, pulse transmitting equipment, and interference sources. • Make all external connections to the system equipment through the designated connector J1, Figure 2-2 and connector J2, and Figure 2-3 and connector J3. The required hardware and connector are supplied if specified. • Suitable wire should be used in accordance with applicable specifications. • Leave slack in cable to allow free movement of equipment, keeping wires from breaking. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 16 2-1 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 Remove all electrical power to the equipment and/or equipment mounts before installing or removing them. 946-03N1-001 2.4. PLANNING. Proper and careful planning prior to installation is essential for reliable performance and easy maintenance. The list that follows is a sample of the points to be considered in planning an installation: 1. Installation location. Allow for adequate airflow for cooling, good bonding to aircraft ground, ease of cable routing, room for single/dual/triple mounting in a location that provides structural rigidity. 2. Installation configuration. 3. Compatibility with other equipment and loading considerations. 2.4.1. Installation Configurations. Figure 2.1. IMS-6010 Configuration 2.4.2. Strapping Options. There are no strapping requirements for the IMS-6010. 2.4.3. Input Power. All power required by the IMS-6010 is provided by the aircraft in which the system is installed. The IMS-6010 requires an input of +28 V dc at 55 watts (max) of power for normal operation. 2.4.4. Cooling Considerations. For IMS-6010 environmental qualification refer to Chapter 1, General Information. 2.4.4.1. Units tightly packed on the equipment rack heat each other through radiation, convection, and sometimes by direct conduction. If space permits, separate the units from each other to significantly improve reliability. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 17 2-2 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 The complete configuration is dependent of the desired connections to ancillary equipment. Figure 2-1 shows a typical configuration: installation 946-03N1-001 2.4.4.2. Even a single unit operates at a much higher temperature in still air than in moving air. Fans, or some other means of moving the air around electronic equipment, are usually a worthwhile investment. If a form of ram air cooling is installed, make certain that rainwater cannot enter and be sprayed on the equipment. 2.5. CABLING INSTRUCTIONS. Make sure that the aircraft battery master switch is turned off before installing any of the interconnect cabling. Failure to do so could cause electrical arcing that might result in damage to the equipment or serious injury to maintenance personnel. Interconnect cables should be prepared in accordance with the interconnect diagrams which are part of approved supplemental type certificate data packages. 2.5.1. Parts Required. Table 2-1 lists the mating connectors, strain reliefs and contacts required to install the IMS-6010. Table 2-1. IMS-6010 Mating Connector Hardware. REF DES LRU CONNECTOR CPN MIL VENDOR PN J1 MATING BACKSHELL/STRAIN CONNECTOR RELIEF CPN MIL VENDOR PN CPN MIL VENDOR PN DESCRIPTION D38999/20FG35AN D38999/20FG35AN D38999/26FG35SN D38999/26FG35SN J2 D38999/20FG35AA D38999/20FG35AA D38999/26FG35SA D38999/26FG35SA J3 357-7347-010 M39012/28-0018 M39012/26-0011 M39012/26-0011 TNC WLAN 1, MATE IS PLUG FOR RG-400 268-0013-110 RJ-45 JACK RJ-45 PLUG FRONT PANEL RJ-45 360-0417-010 USB TYPE A USB PLUG FRONT PANEL USB GLENAIR 400HS001M2107L3 or equivalent 859-6619-160 or equivalent 79 PIN SERIES FOR ETHERNET 79 PIN SERIES FOR SIGNAL AND POWER J5 J6 2.5.2. Connector Information. 2.5.2.1. During preparation of the interconnect cables, observe the precautions that follow: • Read all notes on the drawings and interconnect diagrams prior to fabricating interconnect wiring cables. • Bond and shield all parts of the aircraft electrical system, for example, generator and ignition systems. • Keep the interconnect cables away from circuits carrying heavy current, pulse transmitting equipment, and other sources of interference. • Make all external connections of the equipment through the designated connectors listed on the outline and mounting diagrams. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 18 2-3 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 J4 installation 946-03N1-001 • For balanced connections, use twisted-pair shielded wiring for minimum pickup of electrostatic and magnetic fields. Avoid long runs of wire and keep input and output circuits separated as much as possible. • All interconnect wires and cables should be marked in accordance with the Aircraft Electronics Association (AEA) WireMarking Standard. • Avoid excessive cable lengths, but allow sufficient slack for movement due to vibration. • After installation of the cables in the aircraft, and before installation of the equipment, check to make sure that aircraft power is applied only to the pins specified on the interconnect diagrams and that all other wires and shields are properly terminated. 2.5.3. Cable Shields and Cable Shield Grounds. All wiring and component selections must follow the specification FAA AC43.13-1B and the accepted procedures of the industry. 1. Connect the unit primary DC power-return circuit and chassis ground (if used) to the different ground points in the aircraft. Do not connect these two circuits together at their ground points. Make each wire as short as possible, do not make more than 1 meter (39.37 inches). All power (high) wiring must be a minimum of AWG 22 with the power (ground) wiring AWG 20 unless differently noted. 2. Connect to ground the two ends of the cable that have an external shield unless shown differently. 3. Connect all the cable shields to ground at one ground-point for each, unless shown differently. If the connector backshell is of a metal conductor material and a low impedance bond is made, connect the cable shield to the connector backshell and keep the shields internal to the connector backshell. 4. Connect the cable shield to related pins in the connector when a low-impedance bond is not made to the connector backshell. Alternate scheme gives less shielding and the performance is substantially decreased at the radar and higher frequencies. Table 2-2. Mating Cable Guidelines For IMS-6010 Signal type Cable type Max cable length Shield config Gnd/Rtn Ethernet Tensolite NF24Q100 or equivalent 73 m Integral shield, ties to backshell N/A USB Tensolite NF24Q100 or equivalent 5m Discrete 22 gauge or equivalent Audio input Twisted, shielded pair, 24 gauge or equivalent RF RG400 coaxial or equivalent +28VDC & 28VDC_RTN 22 gauge or equivalent Dedicated power return 20 ft N/A Dedicated power return 2.6. CABLE ASSEMBLY - CONNECTOR J1 PINS. NOTE Different cable assemblies may not be required depending on aircraft configuration. For additional information during the cable assembly and the system overview for the unit interface being used refer to Figure 2-2, Figure 2-4, and Table 2-3 for Connector J1. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 19 2-4 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 Referenced to common signal ground installation 946-03N1-001 Table 2-3. J1 Connector Pin Functions. PIN FUNCTION CONNECTION AFDX CHANNEL A ETHERNET PORT TRANSMIT TYPE Output HIGH AFDX CHANNEL A ETHERNET PORT TRANSMIT Output LOW RESERVED AFDX CHANNEL A ETHERNET PORT RECEIVE Input HIGH AFDX CHANNEL A ETHERNET PORT RECEIVE Input LOW RESERVED USB PORT 1 DATA HIGH Input/Output USB PORT 1 DATA LOW Input/Output RESERVED 10 USB PORT 1 +5 VDC POWER (500 ma max) 11 USB PORT 1 POWER RETURN 12 RESERVED 13 AFDX CHANNEL B ETHERNET PORT TRANSMIT HIGH Output 14 AFDX CHANNELl B ETHERNET PORT TRANSMIT Low Output 15 RESERVED 16 AFDX CHANNEL B ETHERNET PORT RECEIVE HIGH Input 17 AFDX CHANNEL B ETHERNET PORT RECEIVE LOW Input 18 RESERVED 19 ETHERNET PORT 1 TRANSMIT HIGH Output 20 ETHERNET PORT 1 TRANSMIT LOW Output 21 RESERVED 22 ETHERNET PORT 1 RECEIVE HIGH Input 23 ETHERNET PORT 1 RECEIVE LOW Input 24 RESERVED 25 ETHERNET PORT 2 RECEIVE HIGH 26 RESERVED 27 ETHERNET PORT 2 TRANSMIT HIGH 28 RESERVED No connection 29 RESERVED No connection Power Output No connection No connection No connection No connection No connection Input No connection Output Rockwell Collins Proprietary Information Page 20 2-5 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 946-03N1-001 Rev - No connection installation 946-03N1-001 Table 2-3. J1 Connector Pin Functions. - Continued FUNCTION CONNECTION TYPE 30 RESERVED No connection 31 RESERVED No connection 32 RESERVED No connection 33 RESERVED No connection 34 RESERVED No connection 35 RESERVED No connection 36 RESERVED No connection 37 RESERVED No connection 38 RESERVED No connection 39 RESERVED No connection 40 RESERVED No connection 41 RESERVED No connection 42 RESERVED No connection 43 RESERVED No connection 44 RESERVED No connection 45 RESERVED No connection 46 RESERVED No connection 47 RESERVED No connection 48 ETHERNET PORT 2 RECEIVE LOW 49 RESERVED 50 ETHERNET PORT 2 TRANSMIT LOW 51 RESERVED 52 ETHERNET PORT 3 TRANSMIT HIGH Output 53 ETHERNET PORT 3 TRANSMIT LOW Output 54 RESERVED 55 ETHERNET PORT 3 RECEIVE HIGH Input 56 ETHERNET PORT 3 RECEIVE LOW Input 57 RESERVED 58 ETHERNET PORT 4 TRANSMIT HIGH Output 59 ETHERNET PORT 4 TRANSMIT LOW Output 60 RESERVED 61 ETHERNET PORT 4 RECEIVE HIGH Input 62 ETHERNET PORT 4 RECEIVE LOW Input 63 RESERVED 946-03N1-001 Rev - Input No connection Output No connection No connection No connection No connection No connection Rockwell Collins Proprietary Information Page 21 2-6 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 PIN installation 946-03N1-001 Table 2-3. J1 Connector Pin Functions. - Continued PIN FUNCTION CONNECTION TYPE 64 ETHERNET PORT 5 TRANSMIT HIGH 65 RESERVED No connection 66 RESERVED No connection 67 RESERVED No connection 68 RESERVED No connection 69 RESERVED No connection 70 RESERVED No connection 71 RESERVED No connection 72 RESERVED No connection 73 RESERVED No connection 74 RESERVED No connection 75 ETHERNET PORT 5 TRANSMIT LOW 76 RESERVED 77 ETHERNET PORT 5 RECEIVE HIGH Input 78 ETHERNET PORT 5 RECEIVE LOW Input 79 RESERVED Output Output No connection No connection 2.7. CABLE ASSEMBLY - CONNECTOR J2 PINS. NOTE Different cable assemblies may not be required depending on aircraft configuration. DC resistance needs to be 2.5 milli-Ohms maximum between the rear connector shell and the mounting surface(s) where applicable in Figure 2-5 and Figure 2-6. Refer to 523-0775254 Installation Practices Manual and 523- 0776007 Bonding and Grounding Practices. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 22 2-7 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 For additional information during the cable assembly and the system overview for the unit interface being used refer to Figure 2-2, Figure 2-3, and Table 2-4 for Connector J2. TPJ4344_01 Figure 2-2. Jl Pin Arrangement 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 23 2-8 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 installation 946-03N1-001 TPJ4345_01 Figure 2-3. 946-03N1-001 Rev - J2 Pin Arrangement Rockwell Collins Proprietary Information Page 24 2-9 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 installation 946-03N1-001 installation 946-03N1-001 Table 2-4. J2 Connector Pin Functions. FUNCTION CONNECTION TYPE AUDIO IN LEFT HIGH Reserved/No connection GROUND Ground AUDIO OUT LEFT Reserved/No connection GROUND Ground VGA VIDEO RED Output VGA VIDEO GREEN Output VGA VIDEO BLUE Output VGA GROUND VGA HORIZONTAL SYNC Output 10 VGA SYNC GROUND Output 11 VGA VERTICAL SYNC Output 12 VGA SERIAL Clock Output 13 CHASSIS GROUND 14 CHASSIS GROUND 15 CHASSIS GROUND 16 CHASSIS GROUND 17 SPARE No c o n n e c t 18 +28 VDC PRIMARY POWER INPUT POWER Input 19 +28 VDC PRIMARY POWER INPUT POWER Input 20 28 VDC POWER Return Ground 21 28 VDC POWER Return Ground 22 SPARE No connection 23 ARINC 429 PORT 2 RECEIVE HIGH Not implemented/Reserved Input 24 SERIAL RS-422 PORT 1 TRANSMIT HIGH Not implemented/Reserved Output 25 SERIAL RS-422 PORT 1 TRANSMIT LOW Not implemented/Reserved Output 26 SPARE No connection 27 GROUND Ground 28 AUDIO IN Left Low 29 AUDIO IN RIGHT HIGH Reserved/No connection Reserved/No connection 30 SPARE No connection 31 AUDIO OUT RIGHT Reserved/No connection 32 VGA RED GROUND Output 33 VGA GREEN GROUND Output 946-03N1-001 Rev - Rockwell Collins Proprietary Information Input Output Input Input Output Page 25 2-10 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 PIN installation 946-03N1-001 Table 2-4. J2 Connector Pin Functions. - Continued PIN FUNCTION CONNECTION TYPE 34 VGA BLUE GROUND 35 VGA RESERVED 36 VGA +5 VDC 37 SPARE 38 VGA SERIAL DATA Output DISCRETE IN 1, GENERAL Input 39 Output Output Output No connection PURPOSE (user defined) 40 41 DISCRETE IN 2, GENERAL PURPOSE (user defined) Input DISCRETE IN 3, GENERAL Input 42 DISCRETE IN, WEIGHT ON WHEELS, ACTIVE LOW (dedicated) Input 43 DISCRETE OUT 1, GENERAL PURPOSE (user defined) Output 44 DISCRETE OUT 2, GENERAL PURPOSE (user defined) Output 45 DISCRETE OUT 3, GENERAL PURPOSE (user defined) Output 46 DISCRETE OUT 4, GENERAL PURPOSE (user defined) Output 47 ARINC 429 PORT 2 RECEIVE LOW Not implemented/Reserved Input 48 SERIAL RS-422 PORT 1 RECEIVE HIGH Not implemented/Reserved Input 49 SERIAL RS-422 PORT 1 RECEIVE LOW Not implemented/Reserved Input 50 AUDIO IN RIGHT LOW 51 SERIAL RS-422 PORT 2 RECEIVE HIGH Not implemented/Reserved Input 52 SERIAL RS-422 PORT 2 RECEIVE LOW Not implemented/Reserved Input 53 SPARE No connection 54 TEST DISCRETE IN 1, FACTORY RESET LOW Input 55 TEST DISCRETE IN 2, FACTORY RESET LOW Input 56 SERIAL RS-232 PORT 1 RECEIVE Not implemented/Reserved 57 GROUND Ground 946-03N1-001 Rev - Not implemented/Reserved Rockwell Collins Proprietary Information Input Input Page 26 2-11 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 PURPOSE (user defined) installation 946-03N1-001 Table 2-4. J2 Connector Pin Functions. - Continued PIN FUNCTION 58 SERIAL RS-232 PORT 1 TRANSMIT CONNECTION Not implemented/Reserved 59 GROUND Ground 60 GROUND Ground 61 ARINC 429 PORT 1 TRANSMIT Not implemented/Reserved Output Not implemented/Reserved Output 62 ARINC 429 PORT 1 TRANSMIT LOW Output 63 ARINC 429 PORT 1 RECEIVE HIGH Not implemented/Reserved Input 64 ARINC 429 PORT 1 RECEIVE LOW Not implemented/Reserved Input SERIAL RS-422 PORT 2 TRANSMIT Not implemented/Reserved Output 65 HIGH 66 SERIAL RS-422 PORT 2 TRANSMIT LOW Not implemented/Reserved Output 67 SERIAL RS-422 PORT 4 TRANSMIT LOW Not implemented/Reserved Output 68 SPARE No connection 69 TEST DISCRETE IN 3, WATCHDOG DISABLE LOW Input 70 TEST DISCRETE IN 4 Input 71 GROUND Ground 72 SERIAL RS-422 PORT 3 TRANSMIT HIGH Not implemented/Reserved Output 73 SERIAL RS-422 PORT 3 TRANSMIT LOW Not implemented/Reserved Output 74 SERIAL RS-422 PORT 3 RECEIVE HIGH Not implemented/Reserved Input 75 SERIAL RS-422 PORT 3 RECEIVE LOW Not implemented/Reserved Input SERIAL RS-422 PORT 4 TRANSMIT Not implemented/Reserved Output 76 HIGH 77 SERIAL RS-422 PORT 4 RECEIVE HIGH Not implemented/Reserved Input 78 SERIAL RS-422 PORT 4 RECEIVE LOW Not implemented/Reserved Input 79 GROUND Ground 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 27 2-12 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 HIGH TYPE installation 946-03N1-001 2.8. CABLE ASSEMBLY - CONNECTOR J3 PINS. NOTE Antenna coax cable should be no more than 4.7 dB, which equates to approximately 20 feet of RG 400 cable. Table 2-5. J3 Connector Pin Functions PIN FUNCTION Center 2.4 GHz RF for WLAN Shield GROUND CONNECTION TYPE Input/Output Ground GND 2.9. CABLE ASSEMBLY - CONNECTOR J4 PIN (FUTURE GROWTH). NOTE J4 is not installed in the baseline design. The purpose of dual RF connections is to support spatial diversity reception. The J4 connector shall provide a Radio Frequency interface for the 2.4 GHz wireless LAN function. 2.10. CABLE ASSEMBLY - CONNECTOR J5 PINS. The J5 connector provides a USB interface. Table 2-5 provides the connector signal definition. The J5 connector is Samtec USB- AM-S-F-B-SM1, CPN 360-0417-050, (USB Type A). Table 2-6. J5 Connector Pin Functions. FUNCTION CONNECTION POWER TYPE USB PORT 2 +5VDC POWER, 500 MA CAPABLE USB PORT 2 DATA LOW Input/Output USB PORT 2 DATA HIGH Input/Output USB PORT 2 GROUND GROUND Output GND 2.11. CABLE ASSEMBLY - CONNECTOR J6 PINS. The J6 connector provides an Ethernet LAN interface. Table 2-6 provides the connector signal definition. The J6 connector is CPN 358-0042-010 (RJ45 jack). 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 28 2-13 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 PIN Figure 2-4. RJ45 J6 Front Ethernet Indicator Lights 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 29 2-14 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 installation 946-03N1-001 installation 946-03N1-001 Table 2-7. J6 Connector Pin Functions. PIN FUNCTION CONNECTION TYPE Ethernet port 6 Receive High Input Ethernet port 6 Receive Low Input Ethernet port 6 Transmit High Output No connection No connection Output Ethernet port 6 Transmit Low No connection No connection 2.12. INSTALLATION PROCEDURES. This section contains procedures for installing the IMS-6010 in the aircraft. Procedures must be performed as described below to ensure proper operation and performance. 2.12.1. IMS-6010 Installation and Removal. Make sure that the aircraft battery master switch is turned off before installing any equipment, mounts, or intercon- nect cables. Failure to do so could cause electrical arcing that might result in damage to the equipment or serious injury to maintenance personnel. Select the desired location for the unit. 1. Remove electrical power from the aircraft. 2. Make the appropriate cutout (if required). 3. Pull the mating connector assemblies J1, J2, and J3 through the cutout hole. 4. Remove connector covers from mating connectors. 5. Connect P1 to J1 on IMS-6010. 6. Connect P2 to J2 on IMS-6010. 7. Connect P3 to J3 on IMS-6010. 8. Make sure the locking devices are secure to the connectors J1, J2, and J3. 9. Install the unit in the cutout until flush. 10. Tighten the four Dzus fasteners to secure IMS-6010 in place. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 30 2-15 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 2.12.1.1. To install the IMS-6010, perform the steps that follow: installation 946-03N1-001 2.12.1.2. To remove the IMS-6010, perform the steps that follow: 1. Remove electrical power from the aircraft. 2. Loosen the four Dzus fasteners that secure the IMS-6010 in place. 3. Remove the unit from the cutout until clear of mounting surface. 4. Loosen locking device on connector J1. 5. Loosen locking device on connector J2. 6. Loosen locking device on connector J3. 7. Disconnect P3 from J3 on IMS-6010. 8. Disconnect P2 from J2 on IMS-6010. 9. Disconnect P1 from J1 on IMS-6010. 10. If immediately installing a replacement IMS-6010, go to IMS-6010 Installation. If not immediately installing a replacement IMS-6010, go to step 9. 11. Install dust cover on connector J1 to prevent damage to pins. 12. Install dust cover on connector J2 to prevent damage to pins. 13. Install dust cover on connector J3 to prevent damage to pins. 14. Secure J1, J2, and J3 connectors with tie wraps to cables to prevent damage to connectors and other intelligence. 2.13. TESTING. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 31 2-16 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 Refer to the Maintenance chapter for test procedures for the IMS-6010. 946-03N1-001 CHAPTER 3 Operation 3.1. OPERATION PROCEDURES. The IMS-6010 provides the capability for the technician to acquire maintenance data for each LRU for troubleshooting purposes. The DDS software, which is a component of the software load on the IMS-6010, provides the ability to retrieve System Event log files to determine the function of the operating system and the associated DDS applications on the device. 3.1.1. Operating Procedures. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 32 3-1 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 For instruction on how to operate the IMS-6010, go to the M145 Avionics System Operators Guide (CPN 523-0808930). 946-03N1-001 CHAPTER 4 Theory of Operation 4.1. INTRODUCTION TO THEORY OF OPERATION. This chapter presents the Theory of Operation for the IMS-6010. The Theory of Operation is presented in an overview of the entire system and as functional theory for the system unit. 4.2. INFORMATION MANAGEMENT SYSTEM. The IMS-6010 contains the software and hardware to monitor and control the user and equipment interfaces while being the platform from which applications operate. The IMS transfers maintenance data between off-board commercial PC platforms and the aircraft cockpit. The IMS runs on-aircraft software packages that are hosted on the Windows XP operating system. 4.3. FUNCTIONAL DESCRIPTION. The IMS utilizes three purchased commercial-off-the-shelf (COTS) modules for its core functionality; a Single Board Computer (SBC), a Solid State Drive (SSD), and a Wireless LAN Adapter (WLA). Three plug-in circuit card assemblies (CCAs) provide further functions: the Power Supply CCA, the PC Base CCA and the 802 Comm CCA. The Interconnect CCA acts as backplane for the LRU. 4.4. SYSTEM INTERFACE. The IMS provides a link to the avionics system via two non-redundant AFDX Ethernet channels. Other Ethernet interfaces allow for maintenance connection points around the aircraft, and interface to printer. The following input/output signals are located on the rear connectors J1 and J2 of the unit. All output control signals are capable of sinking 100 mA (Maximum), unless otherwise noted. Front panel connectors on the IMS allow for an operator to insert a commercial USB memory stick into the unit, or to connect a laptop computer via RJ45 jack. Remote Ethernet connection points may be implemented in the aircraft, which will allow dataload or maintenance access. The WLA and external antenna provide 802.11 wireless LAN function for maintenance access. 4.4.1. General Information for Connector J1 Signals. Table 4-1. Main Input Power Source. INPUT SPECIFICATION VALUE Nominal Input Voltage 28.0 V dc Maximum Continuous Input Voltage 30.3 V dc Minimum Continuous Input Voltage 22.0 V dc Maximum Surge Voltage - 100 ms Maximum Surge Voltage - 1 sec 47.5 V dc Power Consumption (Max) 55 Watts 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 33 4-1 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 The pins in connector J1 (X) are spare and are reserved in function. They are not connected in the IMS-6010. 946-03N1-001 CHAPTER 5 Maintenance 5.1. INTRODUCTION TO MAINTENANCE. This chapter provides the procedures for the post-installation check of the Information Management System (IMS-6010) in the aircraft. 5.2. TESTING PROCEDURES. Procedures provided herein are oriented for the IMS-6010. Interfacing equipment will need to be verified for their correct operation using test procedures from the related manufacturers. 5.2.1. Initial Power ON. On each power-up of the unit, the boot loader initializes the hardware, performs a power-on self test sequence, and the kernel startup followed by the application software. 5.2.2. Power-on Self Test. After the initialization of the hardware, the power-on self test is performed by the boot loader. Selective test of the RAM space and an OS image CRC check is performed. Successful test continues by the boot loader to the kernel startup. 5.2.3. Kernel Startup. During the kernel startup, the USB status LED located on the front panel is YELLOW, indicating the successful completion followed by the application startup. 5.2.4. Application Startup. During the application startup, the USB status LED located on the front panel is GREEN, indicating the successful completion followed by the USB port readiness. 5.2.5. Additional Functional Checks. After the installation of the IMS-6010 in the aircraft, make sure the equipment that interfaces with the unit is energized. Refer to the last revision of the IMS CMM to do the Return-To-Service (RTS) test if there is a problem with the unit. Use the latest revision of the Acceptance Test Procedure to do the test if there is no CMM to use. The IMS supports self-test functions. These are implemented through IMS software programs. The IMS hardware shall provide features that facilitate the self test functions: • Power on self test functions of Single Board Computer (SBC). • Self diagnostic functions of Single State Device (SSD). • Self diagnostic functions of WLA. • Regulated power voltage monitoring for over & under voltage. • Temperature monitoring for over and under operating temperature. • Non-volatile memory in SSD to store fault data. 946-03N1-001 Rev - Rockwell Collins Proprietary Information Page 34 5-1 STATE 1 - DEVELOPMENT RELEASE 2015-04-22 5.3. SELF TEST. 946-03N1-001 Term Definition AEA Aircraft Electronics Association AFDX Avionics Full Duplex Switched Ethernet AFIS Airborne Flight Information System ARINC Aeronautical Radio, Incorporated CCA Circuit Card Assembly CDU Control Display Unit CPN Collins Part Number DBU Data Base Unit DMU Data Management Unit ETX Embedded Technology eXtended FADEC Full Authority Digital Engine Control FMC Flight Management Computer FMS Flight Management System FSU File Server Unit IFIS Integrated Flight Information System LAN Local Area Network LED Light Emitting Diode LRU Line Replaceable Unit MCDU Multifunction Control Display Unit MDC Maintenance Diagnostic Computer MFD Multifunction Display MTBF Mean Time Between Failure N/A Not Applicable RTS Return To Service STC Supplemental Type Certificate TC Type Certificate USB Universal Serial Bus WLA Wireless LAN Adapter 946-03N1-001 Rev - Rockwell Collins Proprietary Information Glossary-1/(Glossary-2 Page 35 Blank) STATE 1 - DEVELOPMENT RELEASE 2015-04-22 GLOSSARY 946-03N1-001 © Copyright 2015, Rockwell Collins, Inc., All Rights Reserved, Printed in USA 946-03N1-001 Rev - Rockwell Collins Proprietary Information Glossary-1/(Glossary-2 Page 36 Blank) STATE 1 - DEVELOPMENT RELEASE 2015-04-22 946-03N1-001
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