Rockwell Collins 8223132 Information Management System User Manual 946 03N1 001

Rockwell Collins Inc Information Management System 946 03N1 001

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Date Submitted2015-05-21 00:00:00
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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
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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
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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
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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
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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.
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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.
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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.
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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
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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.
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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
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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
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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.
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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.
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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.
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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.
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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
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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
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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.
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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
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installation 946-03N1-001
TPJ4345_01
Figure 2-3.
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J2 Pin Arrangement
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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
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Input
Output
Input
Input
Output
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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
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Input
Input
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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
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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).
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PIN
Figure 2-4. RJ45 J6 Front Ethernet Indicator Lights
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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.
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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.
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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.
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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
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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.
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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
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GLOSSARY
946-03N1-001
© Copyright 2015, Rockwell Collins, Inc.,
All Rights Reserved, Printed in USA
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946-03N1-001

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