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

Rockwell Collins Inc Information Management System 946 03N1 001

Manual

User Manual for Communication Certification of the Information Management System (IMS-6010) Document Number 946-03N1-001 Revision CAGE Code 0EFD0 Rockwell Collins 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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.©2015RockwellCollins.Allrightsreserved.946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 1STATE 1 - DEVELOPMENT RELEASE 2015-04-22-
 Information Management System IMS-6010 User Manual This manual includes coverage of the following equipment: Unit Model Collins Part Number Information Management System IMS-6010 822-3132-XXX  946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 3STATE 1 - DEVELOPMENT RELEASE 2015-04-22
 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 For product orders or inquiries, please contact: Rockwell Collins, Inc. Customer Response Center 400 Collins Road NE, M/S 133-100 Cedar Rapids, IA 52498-0001946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 4STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-001iTABLE OF CONTENTS Chapter/Para Page LIST OF ILLUSTRATIONS ................................................................................... .iii LIST OF TABLES ............................................................................................ . iv SAFETY SUMMARY ......................................................................................... v 1 General Information .......................................................................................... 1-1 1.1 INTRODUCTION. .................................................................................. 1-1 1.1.1 Equipment Covered. ................................................................................. 1-1 1.1.2 Equipment Specifications.............................................................................. 1-1 1.1.3 Environmental Qualifications. ......................................................................... 1-2 1.2 PURPOSE OF EQUIPMENT. ......................................................................... 1-3 1.3 EQUIPMENT OVERVIEW. .......................................................................... 1-4 1.3.1 Single Board Computer. .............................................................................. 1-4 1.3.2 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 Interconnect CCA. ................................................................................... 1-4 1.3.8 Sim Board CCA. .................................................................................... 1-4 1.4 RELATED PUBLICATIONS. ......................................................................... 1-5 1.5 STORAGE. ......................................................................................... 1-5 2 Install ation .................................................................................................. 2-12.1 GENERAL. .........................................................................................2-12.2 UNPACKING AND INSPECTING EQUIPMENT. ......................................................2-12.3 PRE-INSTALLATION CHECK........................................................................2-12.3.1 Cabling Precautions. .................................................................................2-12.4 PLANNING. ........................................................................................ 2-22.4.1 Installation Configurations.............................................................................2-22.4.2 Strapping Options. ................................................................................... 2-22.4.3 Input Power. ........................................................................................ 2-22.4.4 Cooling Considerations. ..............................................................................2-22.5 CABLING INSTRUCTIONS. ......................................................................... 2-32.5.1 Parts Required. ......................................................................................2-32.5.2 Connector Information. ...............................................................................2-32.5.3 Cable Shields and Cable Shield Grounds................................................................2-42.6 CABLE ASSEMBLY - CONNECTOR J1 PINS.......................................................... 2-42.7 CABLE ASSEMBLY - CONNECTOR J2PINS.......................................................... 2-72.8 CABLE ASSEMBLY - CONNECTOR J3 PINS......................................................... 2-132.9 CABLE ASSEMBLY - CONNECTOR J4 PIN (FUTURE GROWTH).....................................2-132.10 CABLE ASSEMBLY - CONNECTOR J5PINS.........................................................2-132.11 CABLE ASSEMBLY - CONNECTOR J6 PINS......................................................... 2-132.12 INSTALLATION PROCEDURES..................................................................... 2-152.12.1 IMS-6010 Installation and Removal...................................................................2-152.13 TESTING. ......................................................................................... 2-163 Operation ................................................................................................... 3-1 3.1 OPERATION PROCEDURES. ........................................................................ 3-1 3.1.1 Operating Procedures. ................................................................................ 3-1 4 Theory of Operation .......................................................................................... 4-1 946-03N1-001 Rev - 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946-03N1-001iiTABLE OF CONTENTS Chapter/Para Page 4.1 INTRODUCTION TO THEORY OF OPERATION. ..................................................... 4-1 4.2 INFORMATION MANAGEMENT SYSTEM. .......................................................... 4-1 4.3 FUNCTIONAL DESCRIPTION. ...................................................................... 4-1 4.4 SYSTEM INTERFACE. .............................................................................. 4-1 4.4.1 General Information for Connector J1 Signals. .......................................................... 4-1 5 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 Kernel Startup. ......................................................................................5-15.2.4 Application Startup. ..................................................................................5-15.2.5 Additional Functional Checks..........................................................................5-15.3 SELF TEST. ........................................................................................ 5-1GLOSSARY .............................................................................................. .Glossary-1 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 6STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-001iiiLIST OF ILLUSTRATIONS Number Title Page 1-1 IMS-6010 ................................................................................................ 1-1 2-1 IMS-6010 Configuration ................................................................................... 2-2 2-2 J1 Pin Arrangement........................................................................................ 2-8 2-3 J2 Pin Arrangement........................................................................................ 2-9 2-4 RJ45 J6 Front Ethernet Indicator Lights ..................................................................... 2-14 2-5 IMS-6010 Connectors..................................................................................... 2-16 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 7STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-001ivLIST OF TABLES Number Title Page 1-1 IMS-6 010 Equi pment Specifications. ........................................................................ 1-2 1-2 IMS-6010 Environmental Qualifications Form................................................................. 1-2 1-3 IMS Major Components. ................................................................................... 1-4 1-4 Related Publications. ...................................................................................... 1-5 2-1 IMS-6010 Mating Connector Hardware....................................................................... 2-3 2-2 Mating Cable Guidelines For IMS-6010 ...................................................................... 2-4 2-3 J1 Connector Pin Functions. ................................................................................ 2-5 2-4 J2 Connector Pin Functions. ............................................................................... 2-10 2-5 J3 Connector Pin Functions ................................................................................ 2-13 2-6 J5 Connector Pin Functions. ............................................................................... 2-13 2-7 J6 Connector Pin Functions. ............................................................................... 2-15 4-1 Main Input Power Source................................................................................... 4-1 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 8STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-001v 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 com- ponent 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 do or do not contain such hazardous materials, do not open or disassemble components for any reason. 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 oc- cur 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 InformationPage 9STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-001vi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 conductive containers. 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 InformationPage 10STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-0011-1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. The IMS-6010 is covered in this manual. The IMS-6010 is illustrated as such:  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 InformationPage 11STATE 1 - DEVELOPMENT RELEASE 2015-04-22
general information 946-03N1-0011-2Table 1-1. IMS-6010 Equipment Specifications. CHARACTERISTIC SPECIFICATION Certification/Related Documents: Certification RTCA Documents Physical: Size: Height Width Length Weight Cooling Requirements  Electrical: Power Requirements Mounting Information Mating Connector 104.78 mm (4.125 in) max. 146.05 mm (5.750 in) max. 248.54 mm (9.785 in) max. (USB and Ethernet access door in closed position) 1.79 kg (3.95 lb) nominal The IMS has both convectional cooling an internal fan which blows heated air out of the unit. Refer to the Installation chapter for mounting information. 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. Table 1-2. IMS-6010 Environmental Qualifications Form. CONDITIONS DO-160G SECTION AND REV EQUIPMENT QUALIFICATIONS CATEGORIES OF CONDUCTED TESTS TEMPERATURE AND ALTITUDE: TEMPERATURE: GROUND SURVIVAL LOW TEMP OPERATING LOW TEMP GROUND SURVIVAL HIGH TEMP OPERATING HIGH TEMP IN FLIGHT LOSS OF COOLING ALTITUDE 4.0 4.5 4.5.1 4.5.2 4.5.3 4.5.4 4.5.5 4.6.1 A4 -55 °C (-67 °F) -15 °C (+5 °F) +85 °C (+185 °F) +55 °C (+131 °F) V. (30 Minute (+30 °C (+86 °F)) 15, 000 ft 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 12STATE 1 - DEVELOPMENT RELEASE 2015-04-22
general information 946-03N1-0011-3Table 1-2. IMS-6010 Environmental Qualifications Form. - Continued CONDITIONS DO-160G SECTION AND REV EQUIPMENT QUALIFICATIONS CATEGORIES OF CONDUCTED TESTS DECOMPRESSION OVERPRESSURE TEMPERATURE VARIATION HUMIDITY SHOCK: OPERATIONAL CRASH SAFETY VIBRATION WATERPROOFNESS FLUID SUSCEPTIBILITY SAND AND DUST FUNGUS RESISTANCE SALT SPRAY MAGNETIC EFFECT POWER INPUT VOLTAGE SPIKE AUDIO FREQUENCY SUSCEPTIBILITY INDUCED SIGNAL SUSCEPTIBILITY RF SUSCEPTIBILITY EMISSION OF RF ENERGY LIGHTNING INDUCED TRANSIENT SUSCEPTIBILITY LIGHTNING DIRECT EFFECTS ICING ELECTROSTATIC DISCHARGE SUSCEPTIBIL- ITY FLAMMABILITY 4.6.2 4.6.3 5.0 6.0 7.0 7.2 7.3 8.0 9.0 10.0 11.0 12.0 13.0 14.0 15.0 16.0 17.0 18.0 19.0 20.0 21.0 22.0 23.0 24.0 25.0 26.0 50,000 ft 170 kPa B. (5 °C per minute) A. (48 hours) B Tested at 6-g (11 ms duration) Impulse 20-g, sustained 20-g (RBBI)(HR)(SM) E X X X X X Z B and Z. A Z CC KR M (A3)(J3)3 X X A X 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 InformationPage 13STATE 1 - DEVELOPMENT RELEASE 2015-04-22
general information 946-03N1-0011-4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 Interconnect CCA acts as a filter for signals and provides lightning protection for them. 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 Solid State Drive Wireless LAN Adapter PC Base CCA 802 Comm CCA Power Supply CCA Interconnect CCA Sim Board CCA 270-3489-010 270-3499-020 270-3512-010 828-3845-103 828-3846-103 828-3844-103 828-3847-003 828-4292-001 Purchased assembly. Purchased assembly. Purchased assembly. Manufactured circuit card assembly. Manufactured circuit card assembly. Manufactured circuit card assembly. Manufactured circuit card assembly. Manufactured circuit card assembly 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 14STATE 1 - DEVELOPMENT RELEASE 2015-04-22
general information 946-03N1-0011-5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 Rockwell Collins Bonding and Grounding Practices Manual 523-0775254 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 degradation has not affected performance. 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 15STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-0012-1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. Remove all electrical power to the equipment and/or equipment mounts before installing or removing them. 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 InformationPage 16STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-0012-2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. The complete configuration is dependent of the desired connections to ancillary equipment. Figure 2-1 shows a typical configuration:  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 con- duction. If space permits, separate the units from each other to significantly improve reliability. 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 17STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-3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 MATING CONNECTOR BACKSHELL/STRAIN RELIEF DESCRIPTION CPN MIL VENDOR PN CPN MIL VENDOR PN CPN MIL VENDOR PN J1 J2 J3 J4 J5 J6 D38999/20FG35AN D38999/20FG35AN D38999/20FG35AA D38999/20FG35AA 357-7347-010 M39012/28-0018 268-0013-110 RJ-45 JACK 360-0417-010 USB TYPE A D38999/26FG35SN D38999/26FG35SN D38999/26FG35SA D38999/26FG35SA M39012/26-0011 M39012/26-0011 RJ-45 PLUG USB PLUG GLENAIR 400HS001M2107L3 or equivalent 859-6619-160 or equivalent 79 PIN SERIES FOR ETHERNET 79 PIN SERIES FOR SIGNAL AND POWER TNC WLAN 1, MATE IS PLUG FOR RG-400 FRONT PANEL RJ-45 FRONT PANEL USB 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 in- terference. • 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 InformationPage 18STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-4• 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 Ethernet USB Discrete Audio input RF +28VDC & 28VDC_RTN Cable type Tensolite NF24Q100 or equivalent Tensolite NF24Q100 or equivalent 22 gauge or equivalent Twisted, shielded pair, 24 gauge or equivalent RG400 coaxial or equivalent 22 gauge or equivalent Max cable length 73 m 5 m 20 ft Shield config Integral shield, ties to backshell N/A Gnd/Rtn N/A Dedicated power return Referenced to common signal ground 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 InformationPage 19STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-5Table 2-3. J1 Connector Pin Functions. PIN FUNCTION CONNECTION TYPE 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 AFDX CHANNEL A ETHERNET PORT TRANSMIT HIGH AFDX CHANNEL A ETHERNET PORT TRANSMIT LOW RESERVED AFDX CHANNEL A ETHERNET PORT RECEIVE HIGH AFDX CHANNEL A ETHERNET PORT RECEIVE LOW RESERVED USB PORT 1 DATA HIGH USB PORT 1 DATA LOW RESERVED USB PORT 1 +5 VDC POWER (500 ma max) USB PORT 1 POWER RETURN RESERVED AFDX CHANNEL B ETHERNET PORT TRANSMIT HIGH AFDX CHANNELl B ETHERNET PORT TRANSMIT Low RESERVED AFDX CHANNEL B ETHERNET PORT RECEIVE HIGH AFDX CHANNEL B ETHERNET PORT RECEIVE LOW RESERVED ETHERNET PORT 1 TRANSMIT HIGH ETHERNET PORT 1 TRANSMIT LOW RESERVED ETHERNET PORT 1 RECEIVE HIGH ETHERNET PORT 1 RECEIVE LOW RESERVED ETHERNET PORT 2 RECEIVE HIGH RESERVED ETHERNET PORT 2 TRANSMIT HIGH RESERVED RESERVED No connection Power No connection No connection No connection No connection No connection No connection No connection No connection Output Output Input Input Input/Output Input/Output Output Output Output Input Input Output Output Input Input Input Output 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 20STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-6Table 2-3. J1 Connector Pin Functions. - Continued PIN FUNCTION CONNECTION TYPE 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED ETHERNET PORT 2 RECEIVE LOW RESERVED ETHERNET PORT 2 TRANSMIT LOW RESERVED ETHERNET PORT 3 TRANSMIT HIGH ETHERNET PORT 3 TRANSMIT LOW RESERVED ETHERNET PORT 3 RECEIVE HIGH ETHERNET PORT 3 RECEIVE LOW RESERVED ETHERNET PORT 4 TRANSMIT HIGH ETHERNET PORT 4 TRANSMIT LOW RESERVED ETHERNET PORT 4 RECEIVE HIGH ETHERNET PORT 4 RECEIVE LOW RESERVED No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection Input Output Output Output Input Input Output Output Input Input 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 21STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-7Table 2-3. J1 Connector Pin Functions. - Continued PIN FUNCTION CONNECTION TYPE 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 ETHERNET PORT 5 TRANSMIT HIGH RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED ETHERNET PORT 5 TRANSMIT LOW RESERVED ETHERNET PORT 5 RECEIVE HIGH ETHERNET PORT 5 RECEIVE LOW RESERVED No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection No connection Output Output Input Input 2.7. CABLE ASSEMBLY - CONNECTOR J2 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 2-3, and Table 2-4 for Connector J2. 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 InformationPage 22STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-8Figure 2-2. Jl Pin Arrangement TPJ4344_01 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 23STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-9Figure 2-3. J2 Pin Arrangement TPJ4345_01946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 24STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-10 Table 2-4. J2 Connector Pin Functions. PIN FUNCTION CONNECTION TYPE 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 AUDIO IN LEFT HIGH GROUND AUDIO OUT LEFT GROUND VGA VIDEO RED VGA VIDEO GREEN VGA VIDEO BLUE VGA GROUND VGA HORIZONTAL SYNC VGA SYNC GROUND VGA VERTICAL SYNC VGA SERIAL Clock CHASSIS GROUND CHASSIS GROUND CHASSIS GROUND CHASSIS GROUND SPARE +28 VDC PRIMARY POWER INPUT +28 VDC PRIMARY POWER INPUT 28 VDC POWER Return 28 VDC POWER Return SPARE ARINC 429 PORT 2 RECEIVE HIGH SERIAL RS-422 PORT 1 TRANSMIT HIGH SERIAL RS-422 PORT 1 TRANSMIT LOW SPARE GROUND AUDIO IN Left Low AUDIO IN RIGHT HIGH SPARE AUDIO OUT RIGHT VGA RED GROUND VGA GREEN GROUND Reserved/No connection Ground Reserved/No connection Ground  No connect POWER POWER Ground Ground No connection Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved No connection Ground Reserved/No connection Reserved/No connectionNo connection Reserved/No connection Input Output Output Output Output Output Output Output Output Input Input Input Output Output Input Input Output Output Output 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 25STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-11Table 2-4. J2 Connector Pin Functions. - Continued PIN FUNCTION CONNECTION TYPE 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 VGA BLUE GROUND VGA RESERVED VGA +5 VDC SPARE VGA SERIAL DATA DISCRETE IN 1, GENERAL PURPOSE (user defined) DISCRETE IN 2, GENERAL PURPOSE (user defined) DISCRETE IN 3, GENERAL PURPOSE (user defined) DISCRETE IN, WEIGHT ON WHEELS, ACTIVE LOW (dedicated) DISCRETE OUT 1, GENERAL PURPOSE (user defined) DISCRETE OUT 2, GENERAL PURPOSE (user defined) DISCRETE OUT 3, GENERAL PURPOSE (user defined) DISCRETE OUT 4, GENERAL PURPOSE (user defined) ARINC 429 PORT 2 RECEIVE LOW SERIAL RS-422 PORT 1 RECEIVE HIGH SERIAL RS-422 PORT 1 RECEIVE LOW AUDIO IN RIGHT LOW SERIAL RS-422 PORT 2 RECEIVE HIGH SERIAL RS-422 PORT 2 RECEIVE LOW SPARE TEST DISCRETE IN 1, FACTORY RESET LOW TEST DISCRETE IN 2, FACTORY RESET LOW SERIAL RS-232 PORT 1 RECEIVE GROUND No connection Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved No connection  Not implemented/Reserved Ground OutputOutput Output OutputInput Input Input Input Output Output Output Output Input Input Input Input Input Input Input Input Input 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 26STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-12Table 2-4. J2 Connector Pin Functions. - Continued PIN FUNCTION CONNECTION TYPE 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 SERIAL RS-232 PORT 1 TRANSMIT GROUND GROUND ARINC 429 PORT 1 TRANSMIT HIGH ARINC 429 PORT 1 TRANSMIT LOW ARINC 429 PORT 1 RECEIVE HIGH ARINC 429 PORT 1 RECEIVE LOW SERIAL RS-422 PORT 2 TRANSMIT HIGH SERIAL RS-422 PORT 2 TRANSMIT LOW SERIAL RS-422 PORT 4 TRANSMIT LOW SPARE TEST DISCRETE IN 3, WATCHDOG DISABLE LOW TEST DISCRETE IN 4 GROUND SERIAL RS-422 PORT 3 TRANSMIT HIGH SERIAL RS-422 PORT 3 TRANSMIT LOW SERIAL RS-422 PORT 3 RECEIVE HIGH SERIAL RS-422 PORT 3 RECEIVE LOW SERIAL RS-422 PORT 4 TRANSMIT HIGH SERIAL RS-422 PORT 4 RECEIVE HIGH SERIAL RS-422 PORT 4 RECEIVE LOW GROUND Not implemented/Reserved Ground Ground Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved No connection  Ground Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Not implemented/Reserved Ground Output Output Output Input Input Output Output Output Input Input Output Output Input Input Output Input Input 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 27STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-13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 CONNECTION TYPE Center Shield 2.4 GHz RF for WLAN GROUND Ground Input/Output GND 2.9. CABLE ASSEMBLY - CONNECTOR J4 PIN (FUTURE GROWTH). J4 is not installed in the baseline design. NOTE 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. PIN FUNCTION CONNECTION TYPE 1 2 3 4 USB PORT 2 +5VDC POWER, 500 MA CAPABLE USB PORT 2 DATA LOW USB PORT 2 DATA HIGH USB PORT 2 GROUND POWER GROUND Output Input/Output Input/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 InformationPage 28STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-14 Figure 2-4. RJ45 J6 Front Ethernet Indicator Lights 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 29STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-15Table 2-7. J6 Connector Pin Functions. PIN FUNCTION CONNECTION TYPE 1 2 3 4 5 6 7 8 Ethernet port 6 Receive High Ethernet port 6 Receive Low Ethernet port 6 Transmit High Ethernet port 6 Transmit Low No connection No connection No connection No connection Input Input Output Output 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. 2.12.1.1. To install the IMS-6010, perform the steps that follow: 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 InformationPage 30STATE 1 - DEVELOPMENT RELEASE 2015-04-22
installation 946-03N1-0012-16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. Refer to the Maintenance chapter for test procedures for the IMS-6010. 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 31STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-0013-1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. For instruction on how to operate the IMS-6010, go to the M145 Avionics System Operators Guide (CPN 523-0808930). 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 32STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-0014-1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 Com- puter (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. The pins in connector J1 (X) are spare and are reserved in function. They are not connected in the IMS-6010. Table 4-1. Main Input Power Source. INPUT SPECIFICATION VALUE Nominal Input Voltage Maximum Continuous Input Voltage Minimum Continuous Input Voltage Maximum Surge Voltage - 100 ms Maximum Surge Voltage - 1 sec Power Consumption (Max) 28.0 V dc 30.3 V dc 22.0 V dc 47.5 V dc 55 Watts 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 33STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-0015-1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. 5.3. SELF TEST. 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 InformationPage 34STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-001Glossary-1/(Glossary-2 Blank)GLOSSARY 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 RT S R e t u r n To Service STC Supplemental Type Certificate TC Type Certificate USB Universal Serial Bus WLA Wireless LAN Adapter 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 35STATE 1 - DEVELOPMENT RELEASE 2015-04-22
946-03N1-001Glossary-1/(Glossary-2 Blank)946-03N1-001 © Copyright 2015, Rockwell Collins, Inc., All Rights Reserved, Printed in USA 946-03N1-001 Rev - Rockwell Collins Proprietary InformationPage 36STATE 1 - DEVELOPMENT RELEASE 2015-04-22

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