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Guidance for the Installation and use of Direct broadcast Satellite

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					               WAEA SATELLITE WORKING GROUP




 GUIDANCE FOR THE INSTALLATION AND USE OF A DIRECT

BROADCAST SATELLITE RECEIVE SYSTEM ON AIR TRANSPORT

                          AIRCRAFT




                           Prepared by



                     Satellite Working Group


                      Technology Committee
              World Airline Entertainment Association




               10- Feb-00



                        REVISION STATUS
29 April 1999   Initial Draft                                       R. Jennings, Honeywell, Inc.

23 July 1999    Revised Draft                                       D. Lee, The Boeing Company

23 July 1999    Revised Outline Proposed                            R. Cobden & M. Maritan
                                                                    Canadian Marconi Company

5 Aug 1999      Combined 23 Jul 1999 Revised Draft into new         R. Cobden & M. Maritan
                outline. Added Contents Licensing information       Canadian Marconi Company

5 Oct 1999      Revised Draft with new data on systems, New         D. Lee, The Boeing Company
                Figures, New Cable Definitions, and additional
                sections.

6 Oct 1999      Revisions after meeting with WAEA-WG                D. Lee, The Boeing Company
                Chairman. (Ready for WEB?)
                                                                    Rodger Soucy, Ball Aerospace

8 Nov 1999      Incorporating the approved revisions from the       D. Lee, The Boeing Company
                full WP review during the Satellite Working
                Group meeting in San Diego November 1, 1999.

                                                               th
21 Dec 1999     Incorporated revisions from the November 16         D. Lee, The Boeing Company
                telephone conference, plus additional
                information from emails, meetings, and
                telephone conversations that occurred after the
                meeting.

26 Jan 2000     Finished incorporating the last of the EMAIL        D. Lee, The Boeing Company
                and telephoned updates.

28 Jan 2000     Rolled in updates from the working group            D. Lee, The Boeing Company
                telephone conference on 1/28/00.

4 Feb 2000      Final mark-ups from the Working Group               D. Lee, The Boeing Company
                meeting January 31, 2000. Also added
                appendix summary of ARINC-485 protocol
                additions for Satellite TV applications.

9 Feb 2000      Minor updates to pages 11, 14, and A.               D. Lee, The Boeing Company

10 Feb 2000     Final updates from 2/10/00 Telecon.                 D. Lee, The Boeing Company




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                                                                TABLE OF CONTENTS


1. INTRODUCTION ................................................................................................................................... 1
1.1     Purpose........................................................................................................................................... 1
1.2     Application of Equipment ................................................................................................................ 1
1.2.1     Satellite Broadcast Television ..................................................................................................... 1
1.2.2     Data Capability ............................................................................................................................ 2
1.2.2.1   Data............................................................................................................................................. 2
1.2.2.2   Data Interface (Software) ............................................................................................................ 2
1.2.2.3   Data Interface (Hardware)........................................................................................................... 2
1.3     Performance Attributes ................................................................................................................... 3
1.3.1     Antenna Coverage Volume ......................................................................................................... 3

2. RELATED DOCUMENTS...................................................................................................................... 3
2.1          FAA Standards................................................................................................................................ 3
2.2 ................................................................................................................................................................. 4
2.2          ARINC............................................................................................................................................. 4
2.3 ................................................................................................................................................................. 5
2.3          Radio Technical Commission for Aeronautics (RTCA) .................................................................. 5
2.4          Industry ........................................................................................................................................... 5
2.5          WAEA ............................................................................................................................................. 5
2.6          Aircraft Manufacturer (OEM) Requirements ................................................................................... 5

3. ................................................................................................................................................................... 6

3. SYSTEM ARCHITECTURE................................................................................................................... 6
3.1          Functional System Description ....................................................................................................... 6
Unit Descriptions ........................................................................................................................................... 6
3.2.1 .............................................................................................................................................................. 7
3.2.1           Fuselage or Tail Mounted Antenna ............................................................................................. 7
3.2.1.1         Radome....................................................................................................................................... 7
3.2.1.2         Antenna ....................................................................................................................................... 7
3.2.2           Antenna Positioner and Control Block ........................................................................................ 7
3.2.2.1         Antenna Positioner ...................................................................................................................... 7
3.2.2.2         Antenna Controller ...................................................................................................................... 7
3.2.2.3         Antenna Power Supply................................................................................................................ 7
3.2.3 .............................................................................................................................................................. 8
3.2.3           LNB/LNC ..................................................................................................................................... 8
3.2.3.1         Low Noise Block (LNB) ............................................................................................................... 8
3.2.3.2         Low Noise Converter (LNC) ........................................................................................................ 8
3.2.4           Antenna Switch Unit (ASU) ......................................................................................................... 8
3.2.5           Receiver/Decoder Unit (RDU)..................................................................................................... 8
3.3 ................................................................................................................................................................. 9
3.3          External System Interfaces............................................................................................................. 9
3.3.1           Inertial Reference Unit ................................................................................................................ 9
3.3.1.1         Definition of the ARINC-429 Sign Status Matrix (SSM) Bits: ...................................................... 9
3.3.2 ............................................................................................................................................................ 10
3.3.2           FMS Data .................................................................................................................................. 10
3.3.3           IFE Interfaces............................................................................................................................ 10
3.3.3.1         Control/BITE Interface............................................................................................................... 10
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3.3.3.2          Analog Video/Audio Outputs ..................................................................................................... 10
3.3.3.3          Digital Video/Audio Outputs ...................................................................................................... 10
3.3.4            Power Input ............................................................................................................................... 10

4. ................................................................................................................................................................. 11

4. SYSTEM OPERATION........................................................................................................................ 11
4.1   Antenna Steering Fail-Over Modes............................................................................................... 11
4.2   Channel Selection......................................................................................................................... 11

5. INSTALLATION CONSIDERATIONS ................................................................................................. 11
5.1          Equipment Installation Areas ........................................................................................................ 11
5.1.1           Antenna Installation Area - Fuselage (AIA) ............................................................................... 11
5.1.2           Antenna Installation Area - Tail (AIA) ....................................................................................... 11
5.1.3           Satellite Television Integration Area (STIA) .............................................................................. 11
5.1.4           Cabin Electronics Compartment (CEC) .................................................................................... 12
5.2          Interwiring ..................................................................................................................................... 12
5.2.1 ............................................................................................................................................................ 13
5.2.1           CEC to STIA Wiring Bundle Characteristics ............................................................................. 13
5.3 ............................................................................................................................................................... 14
5.3          Mounting Provisions...................................................................................................................... 14

6. SYSTEM ATE DESIGN ....................................................................................................................... 15
6.1         General ......................................................................................................................................... 15
6.2         Built-In Test Equipment (BITE) ..................................................................................................... 15
6.2.1 ............................................................................................................................................................ 16
6.2.1          BITE Display.............................................................................................................................. 16
6.2.2          Fault Monitor ............................................................................................................................. 16
6.2.3          Self-Test Initiation ..................................................................................................................... 16
6.2.4          BITE Output Formats ................................................................................................................ 16

7. ................................................................................................................................................................. 17

7. OEM Unique Submittal Requirements ............................................................................................. 17
7.1          Electromagnetic Interference (EMI) .............................................................................................. 17
7.2 ............................................................................................................................................................... 19
7.2          The “Floating” IFE Test Setup ...................................................................................................... 19
7.3          ACRONYMS ................................................................................................................................. 20

Standard Installation Configuration Area Work Sheet ............................................................................A

Summary of Content Licensing Issues.....................................................................................................B

Summary of new Type 2 arinc 485 commands for Airborne satellite TV...............................................C




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1.        INTRODUCTION

1.1       Purpose

          This document provides general guidance for the design of a Direct Broadcast Satellite (DBS)
          Receive System (DBSRS) for installation on air transport aircraft. For content licensing issues
          refer to attachment 2.

          This document outlines:

          1) operational concepts for the DBSRS

          2) required interfaces to other aircraft systems

          3) approaches for installation of both fuselage and tail mounted antennas

1.2       Application of Equipment

          The function of the equipment described in this document is the reception and processing of
          signals broadcast from satellites. The frequency of operation will vary depending on the
          system utilized. A survey of current systems includes (but is not limited to) Ku-band, C-band,
          and S-band. Additional details of specific services are detailed below.

1.2.1     Satellite Broadcast Television

          In this application television program content is up-linked from a ground station to a satellite
          and then downlinked from the satellite back towards the earth. Any aircraft operating within
          the broadcast footprint of the satellite can receive the signal if equipped with appropriate
          avionics on board.

          The signal received by the onboard equipment is processed and made available for
          distribution to the passenger on either overhead monitors or individual in-seat video displays.

          Current and future satellite television services include both regional services targeted at the
          direct to home market as well as global systems providing service both over land and water.

          The number of programs (PID – Program Identifiers) that can be selected as well as the
          number of distributed channels which can be fed to the IFE system will depend on the DBS
          broadcast service subscribed to as well as the avionics equipment on-board.

              Broadcast Service
              from Satellite



                      Antenna           DBSRS

                                                Distributed
                         Programs Receiver      Channels       In-Flight
                                  Decoder                      Entertainment
                                                               Distribution

               Attitude information
               from airplane avionics
                                                                               Audio/Video to passenger


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                           U p Link                                     D ow n
                                                                        Link




                                                                                  A ircraft
              G round
              S tation




                         TV program s


1.2.2     Data Capability

1.2.2.1   Data

          •     For the purposes of this document, “Data” will be defined as content that is specially
                decoded to provide additional passenger services other than video and audio sources.
                This could include, but is not limited to applications such as EMAIL and/or Internet
                access.

1.2.2.2   Data Interface (Software)

          •     The data interface should be capable of providing a bi-directional connection between the
                passenger and the ground service. This connection will provide data to the passenger or
                IFE system via a data connection. The application associated with it could be a browser
                linked to the Internet (Worldwide WEB), user EMAIL access, etc.

1.2.2.3   Data Interface (Hardware)

          •     The connection to the seat (passenger) and/or In-Flight Entertainment System should be
                Ethernet 10/100BaseT, Fibre Channel, IEEE-1394, USB, Optical Link, etc. This will
                provide future growth as the path on/off the airplane improves.

          •     The uplink (ground to aircraft) is via the DBSRS and the downlink (Aircraft to ground)
                should be via the existing NATS, TFTS, SATCOM, or other airborne communication
                system. The link described today is inherently asymmetrical having a large pipe onto the
                aircraft (1Mb/s or greater), and a small pipe off the aircraft (9600b/s or less).

          •     Future growth could encompass a purely symmetrical system.



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1.3       Performance Attributes

1.3.1     Antenna Coverage Volume

          To ensure signal reception the antenna should achieve a desired performance over a
          coverage volume (relative to the aircraft's horizontal line of flight) defined by an azimuth range
          of 360° and an elevation range corresponding to the coverage provided by the satellite
          broadcast system utilized. The ideal coverage volume should permit signal reception for all
          normal flight attitudes.

          The following table shows typical scan angles for geostationary satellites.
              Latitude Elevation angle to the satellite        Latitude Elevation angle to the satellite
              0°         90.0°                                 50°       32.7°
              10°        78.2°                                 60°       21.9°
              20°        66.6°                                 70°       11.5°
              30°        55.0°                                 80°       1.3°
              40°        43.7°                                 90°       -8.6°
                  * This table assumes the aircraft is at the same longitude as the satellite.

          With current technology it is very difficult, if not impossible, to design an antenna offering the
          desired constant gain over a complete hemisphere. System suppliers should specify the
          achieved antenna coverage for their antenna system and satellite service.

2.        RELATED DOCUMENTS

          The latest revision of the following documents is pertinent to the design of equipment intended
          to meet this standard, unless otherwise stated.

2.1       FAA Standards
              AC 25-10                               FAA Advisory Circular; “Guidance for installation of
                                                     Miscellaneous, Non-required Electrical Equipment”.

              AC 25-16                               FAA Advisory Circular; “Electrical Fault and Fire
                                                     Protection”.

              AC 25.1309-1A                          FAA Advisory Circular; “System Design and Analysis”.

              CFR Title 14                           Code of Federal Regulations, Title 14, Aeronautics and
                                                     Space.
              MIL-E-5272C (ASG)                      Environmental Testing, Aeronautical and Associated
                                                     Equipment, General Specification.




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2.2       ARINC
              ARINC 404A                Aeronautical Radio Inc., Project Paper 404A, “Air
                                        Transport Equipment Cases and Racking.

              ARINC 413A                Aeronautical Radio Inc., Guidance for Aircraft Electrical
                                        Power Utilization and Transient Protection.
              ARINC 419                 Aeronautical Radio Inc., Digital Data System
                                        Compendium.
              ARINC 429                 Aeronautical Radio Inc., Mark 3 Digital Information
                                        Transfer System.
              ARINC 485                 Aeronautical Radio Inc., Project Paper 485, “Cabin
                                        Management and Entertainment System Part 1 – Head
                                        End Equipment Protocol”
              ARINC 600                 Aeronautical Radio Inc., Project Paper 600, “Air
                                        Transport Avionics Equipment Interfaces”.

              ARINC 604                 Aeronautical Radio Inc., Guidance for Design and Use
                                        of Built In Test Equipment (BITE).

              ARINC 624                 “Onboard Maintenance Systems”
              ARINC 628                 Aeronautical Radio Inc., “Cabin Equipment Interfaces”

              ARINC 746-1               Aeronautical Radio Inc., Project Paper 746-1, “Cabin
                                        Communications System”




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2.3       Radio Technical Commission for Aeronautics (RTCA)



              DO-178B                          Radio Technical Commission for Aeronautics, Software
                                               Considerations for Airborne Equipment


              DO-160D                          Radio Technical Commission for Aeronautics,
                                               “Environmental Conditions and Test Procedures for
                                               Airborne Equipment”.


2.4       Industry
              EIA RS-485                       Electronic Industries Association
              EIA RS-232                       Electronic Industries Association
              EIA RS-422                       Electronic Industries Association
              Ethernet 10BaseT / 100BaseT      IEEE 802.3

2.5       WAEA
              WAEA-395                         World Airline Entertainment Association specification,
                                               “Content Delivery for In-Flight Entertainment”

2.6       Aircraft Manufacturer (OEM) Requirements

          There are additional requirements imposed by the aircraft manufacturers. Satellite TV
          equipment and system suppliers should consult with target airframe manufacturer prior to
          installation and operation.




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3.              SYSTEM ARCHITECTURE

3.1             Functional System Description

                The following functional blocks may be contained within the DBS Receive System. System
                Suppliers may chose to integrate multiple functions into a single LRU.


                                Airborne Satellite TV Receiver System
                                      (General Block Diagram)                                     IRU Data

                                         Power
                    Fuselage or
                                                        Antenna Positioner                        FMS Data
                    Tail Mounted         Control
                                                        and Control block
                    Antenna
                                                                                            Aircraft Power
                                         er
                     RF
                                      Pow ol
                                          ntr
                                        Co
                     LNB/LNC
                                                    l
                                                  ro
                                                nt
                                              Co




                   RF/IF

                         ASU
      Control




                    RF/IF

                 Receiver/Decoder
                 Unit (RDU)                  Audio/Video               In-Flight Entertainment
                 (1-n)                                                 Cabin Distribution System


                                             Control

3.2             Unit Descriptions

                The following sections describe the general function of each of the possible system LRUs.
                Note that some systems may not require all LRUs identified as the functions may be
                integrated into a single LRU.




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3.2.1     Fuselage or Tail Mounted Antenna

3.2.1.1   Radome

          The Radome forms a Radio Frequency (RF) transparent environmental and aerodynamic
          cover over the antenna. In some system implementations the Radome is a separate LRU
          which is removable to provide access to the antenna. In other applications the radome is an
          integral part of the antenna LRU. Also in some applications, the radome is airframe
          dependent whereas in other applications the radome is airframe independent. The radome
          may be implemented as one single part or multiple parts. In some applications, a faring may
          be required.

3.2.1.2   Antenna

          The antenna is the portion of the system that collects or receives the Radio Frequency (RF)
          signal in free space and transitions it to a RF signal within the RF circuitry of the system.
          Typically the antenna will be a directional antenna (i.e. not omni-directional) which must be
          steered in an appropriate direction to receive the desired satellite signal. The antenna could
          consist of an element or elements that provide a fixed antenna beam that is mechanically
          steered, an array of elements that produce a beam that is electronically steered, or a
          combination of the two.

          The Antenna LRU may or may not also include the Radome, the Antenna Positioning Unit, the
          Antenna Power Supply, and/or the Low Noise Block/Low Noise Converter.

3.2.2     Antenna Positioner and Control Block

3.2.2.1   Antenna Positioner

          The Antenna Positioning unit is the interface that positions or steers the Antenna in the
          Azimuth and Elevation planes of operation, allowing the antenna to track the satellite during
          flight.

3.2.2.2   Antenna Controller

          The Antenna Control Unit controls the antenna steering. Typically the ACU uses various
          signal inputs to determine where the antenna should be steered and provides appropriate
          signals to the Antenna Positioner Unit to steer the antenna in the desired direction. The
          antenna controller may use external inputs to determine the current attitude of the airplane.

          The Antenna Control Unit may be a separate LRU or this function may be integrated into one
          of the other system LRUs.

3.2.2.3   Antenna Power Supply

          The Antenna Power Supply provides the appropriate power required by various system LRUs.
          The Antenna Power supply may be implemented as a separate LRU or may be integrated
          within other system LRUs such as the Antenna, the Antenna Positioning/controller Unit or the
          Low Noise Block/Low Noise Converter.

          Output voltages will vary depending on system implementation.



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3.2.3     LNB/LNC

3.2.3.1   Low Noise Block (LNB)

          The Low Noise Block amplifies the signal received by the antenna prior to being fed to the
          Integrated Receiver Decoder.

          The LNB may be a separate LRU or the LNB function may be integrated into another LRU.

3.2.3.2   Low Noise Converter (LNC)

          The Low Noise Converter down converts the received RF signal to a lower I/F frequency that
          can be distributed with less loss.

          The LNC may be a separate LRU or the LNC function may be integrated into another LRU.

3.2.4     Antenna Switch Unit (ASU)

          The Antenna Switch Unit is used in some systems to route the down-converted RF signal
          from the LNB/LNC to multiple interfaces.

3.2.5     Receiver/Decoder Unit (RDU)

          The RDU receives the amplified RF signal from the LNB/LNC or Antenna Switch Unit, and
          processes it as required to provide signals that can be fed to the IFE system for distribution
          within the aircraft cabin. Multiple Receiver/Decoder Units could be used in a system.

          The number of channels and output formats vary from supplier to supplier, but the formats
          currently used are Unmodulated Baseband Video with separate Analog Audio, and Modulated
          “normal” NTSC (standard NTSC signal with audio included).

          In some systems, digital data may also be decoded and distributed by this unit.




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3.3       External System Interfaces

3.3.1     Inertial Reference Unit

          For Airborne TV systems without integrated tracking or GPS capability, navigation data should
          be gathered from one of the Inertial Reference Units (IRU) at the non-essential output bus
          three (IRU bus #3).

          An ARINC 429 databus from the Inertial Reference Unit should provide as a minimum the
          following information to the DBS Receive System:

              Octal   Parameter Name        Data Range         Min        Max         Maximum
              Label                                            Update     Transmit    Transport
                                                               Rate       Interval    Delay

              310     Present Position -    90ºN - 90ºS        20ms       200ms       160ms
                      Latitude (LATO)

              311     Present Position -    180ºE - 180ºW      20ms       200ms       160ms
                      Longitude
                      (LONGO)

              314     True Heading          +/- 180º           50ms       50ms        110ms
                      (HG4T)

              320     Magnetic Heading      +/- 180º           50ms       50ms        110ms
                      (HG4M)

              324     Pitch Angle (PA4)     +/- 180º           20ms       20ms        50ms

              325     Roll Angle (RA4)      +/- 180º           20ms       20ms        50ms

              361     Altitude (Inertial)   +/- 131, 072       40ms       50ms        65ms

3.3.1.1   Definition of the ARINC-429 Sign Status Matrix (SSM) Bits:

                          SSM (Bit 31, Bit 30)              Definition

                          00                                Fail/Warn

                          01                                No Computed Data (NCD)

                          10                                Functional Test

                          11                                Valid Data (Normal
                                                            Operation)




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3.3.2     FMS Data

          Some Satellite TV systems utilize Aircraft ID (Tail ID and Flight Number) in their system
          design. Please note that Aircraft ID (Tail ID and Flight Number) is not accessible from the
          Flight Management System (FMS), the Aircraft Condition Monitoring System (ACMS), or the
          Electronic Interface Unit (EIU) in all airplane configurations. Suppliers and installers should
          verify Aircraft ID availability or identify a work-around prior to installing Satellite TV Systems
          that require this data.

3.3.3     IFE Interfaces

3.3.3.1   Control/BITE Interface

          The DBS Receive System should be designed to interface with an ARINC 485 communication
          bus. This bus should be used for basic functional control of the DBSRS, data load to the
          DBSRS, and to provide DBSRS BITE information to the Cabin Distribution System. Refer to
          Attachment 3 for a summary of the new ARINC 485 commands.

3.3.3.2   Analog Video/Audio Outputs

          The Airborne Satellite TV Receiver system should provide at least one analog stereo audio
          pair for each video output from the system. The delay between video and associated audio
          signals should not be greater than ± 25 ms. The audio cable shields should be grounded at
          the source equipment case ground. The Audio load impedance is 600-ohm balanced.

          The video signals should be transmitted via unbalanced 50-ohm coaxial cables or via
          balanced 100-ohm shielded cables.

3.3.3.3   Digital Video/Audio Outputs

          Systems may also provide for transfer of signals from the Receiver/Decoder Unit to the In-
          Flight Entertainment distribution system in digital format through a digital interface. Details of
          this interface are TBD.

3.3.4     Power Input

          Primary power should be fed to the CEC (see section 5) and distributed to the LRUs within the
          system from that point. In the case of a Tail mounted installation, power could be provided at
          the STIA (see section 5) closest to the Tail installation.

          The system should be designed to use 115VAC 400Hz single-phase power, however, both
          the STIA and CEC will have three-phase 115VAC 400Hz power available. Aircraft power
          supply characteristics, utilization, equipment design limitations and general guidance material
          are set forth in ARINC Report 413A, "Guidance for Aircraft Electrical Power Utilization and
          Transient Protection." The primary power input should be protected by suitable circuit
          breakers.




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4.        SYSTEM OPERATION

4.1       Antenna Steering Fail-Over Modes

          There are many methods of antenna steering implemented in the current supplier designs.
          Each method has its merits. However, a fail-over operation method to track the satellite
          should be implemented for IRS data loss. The system should be able to continue its lock on
          the satellite through momentary IRS data loss, and for on-ground operation when IRU is shut
          down while the Satellite TV receiver system is active.

4.2       Channel Selection

          Depending on the installation, channel selection should be available via the system interface
          panel, wireless remote control, or via RS-485 from the In-Flight Entertainment system.

5.        INSTALLATION CONSIDERATIONS

5.1       Equipment Installation Areas

          The WAEA Satellite Television Working Group has identified three equipment integration
          areas with-in the aircraft. These are the Antenna Integration Area (AIA), the Satellite
          Television Integration Area (STIA), and the Cabin Electronics Compartment (CEC).

5.1.1     Antenna Installation Area - Fuselage (AIA)

          The Fuselage Antenna Installation Area (AIA) is the standardized airborne satellite TV
          antenna fuselage mounting location as defined by the aircraft manufacturer for the target
          aircraft model. Satellite TV equipment located at this location can include radome, faring,
          antenna, positioner, control electronics, etc.

5.1.2     Antenna Installation Area - Tail (AIA)

          The Tail Antenna Installation Area (AIA) is the standardized airborne satellite TV antenna
          vertical fin/tail mounting location as defined by the aircraft manufacturer for the target aircraft
          model. Satellite TV equipment located at this location can include radome, fairing, antenna,
          positioner, control electronics, etc.

5.1.3     Satellite Television Integration Area (STIA)

          The Satellite TV Integration Area (STIA) is the standardized location defined by the aircraft
          manufacturer for airborne satellite TV support equipment. This area shall be co-located as
          close to the antenna fuselage penetration as possible to provide a short run for the RF and
          control cables from the AIA. The STIA should contain shelf mounting provisions for support
          equipment as well as a disconnect mount for the interface cable from the CEC.

          Note: The wiring from the antenna to the STIA is supplier defined.




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5.1.4        Cabin Electronics Compartment (CEC)

             The Cabin Electronics Compartment (CEC) is the location where the electronics that interface
             to the on-board In-Flight Entertainment system reside. The location of the CEC is defined by
             the aircraft manufacturer working with the airline customer.

             Note: The wiring from the STIA to the CEC is defined by the aircraft
                   manufacturer using this document as a guide.

5.2          Interwiring

             To facilitate system installation (recognizing that different LRUs exist among different system
             suppliers) interwiring is described between installation areas on the aircraft. System suppliers
             should design their systems to work with the standard interwiring between the installation
             areas.



                           WAEA TC Proposed standard Installation for
                             Ariborne Satellite Television Systems

                                                                  Antenna Installation Area (AIA)
                                                                  Tail Mounted Antenna
                                                                                                          Antenna




                                                      Antenna Installation Area (AIA)
                                                      Fuselage Mounted Antenna



                                                    Antenna
                                                                                                                 L1'


                                                                          L1

                                  Satellite TV Integration Area (STIA)                    Satellite TV Integration
                                     Fuselage Mounted Antenna                             Area (STIA) Tail Mounted
                                                                               L2         Antenna

                Cabin Electronics Compartment (CEC)
                                                                   L3
                Separate cabinet or located with
                IFE in PWS or Cabinet
                                                                                            Typical Airplane


 Tail mounted antenna system cable length = L1' + L2 + L3
 Fuselage mounted antenna system cable length = L1 + L3




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5.2.1     CEC to STIA Wiring Bundle Characteristics


                        (A)           50-Ohm COAX        See Note 4
              A1                                                                                         A2
                        (B)           50-Ohm COAX        See Note 4
              B1                                                                                         B2
                        (C)           75-Ohm COAX        See Note 5
              C1                                                                                         C2
                        (D)           75-Ohm COAX        See Note 5
              D1                                                                                         D2
                        (E)           75-Ohm COAX        See Note 5
              E1                                                                                         E2
                        (F)           75-Ohm COAX        See Note 5
              F1                                                                                         F2
                         (G)          BMS 13-48 Type 25 Class 4 12AWG    (115VAC 400Hz Phase A)
              1                                                                                          1
                                                                         (115VAC 400Hz Phase B)
              2                                                                                          2
                                                                         (115VAC 400Hz Phase C)
              3                                                                                          3
                                                                         (115VAC 400Hz Return)
              4                                                                                          4

                         (H)          BMS 13-48 Type 25 Class 2 16AWG
              5                                                                                          5
              6                                                                                          6

                         (I)          BMS 13-48 Type 25 Class 2 16AWG
              7                                                                                          7
              8                                                                                          8

                         (J)          BMS 13-48 Type 25 Class 2 16AWG
              9                                                                                          9
              10                                                                                         10

                         (K)          BMS 13-48 Type 25 Class 2 20AWG
              11                                                                                         11
              12                                                                                         12

                         (L)          BMS 13-48 Type 25 Class 2 20AWG
              13                                                                                         13
              14                                                                                         14

                         (M)          BMS 13-48 Type 25 Class 2 20AWG
              15                                                                                         15
              16                                                                                         16

                         (N)          S280W502-3 20AWG     (Reserved for Data)
              17                                                                                         17
              18                                                                                         18


                         (O)          S280W502-3 20AWG     (Reserved for Data)
              19                                                                                         19
              20                                                                                         20




          1. The standard inter-wiring defined between the installation locations
          2. The Space envelops available in the installation location.
          3. Consider total loss figures and phase matching when selecting coax.
          4. 50-ohm coax use BMS13-65 Type OJ, or use 204-15578-1 (FEP 226).
          5. 75-ohm coax use Andrews Cable FSJ4-75A, EMTEQ PFLX175-075, or RG6A.



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5.3       Mounting Provisions

          The following tables outline the possible installation locations for the LRUs within in the
          system. Additional Suppliers use worksheet in Attachment 1. Note: (*) indicates multiple
          locations are possible.

                                  Table 2: LRU Installation Locations

              Supplier A       Supplier B     Supplier C      Supplier D      Supplier E
              Fuselage - Antenna Integration Area
              Luneberg,                      Phased Array     Luneberg,       1D-ESA,
              Positioner                     Antenna          Positioner      Positioner

              Tail - Antenna Integration Area
              11.5” Dish,       12.88” Dish,                  11.65” Dish,
              Positioner,       Gimbal, LNB,                  LNB
                                JCU
              Satellite TV Integration Area
              AIU               PS            LNB, LPC,       LNB, AIU        ACS, IFI
                                              PS, *SPAC       Or
                                                              ACU, SRR
              Cabin Electronics Compartment
              IMU, RDU        RDU          ASU, COTS          MRDU, RDU       MRM
                                           Receivers,
                                           *SPAC
              Wiring
              C,D,E,F,G,K,L   C,D,G,H,I,J  A,B,G,H,I,J,      C,D,G,K,L        C,D,G,K,L
                                           K,L



              Supplier F       Supplier G     Supplier H
              Fuselage - Antenna Integration Area
              Phased Array                    Phased Array
              Antenna                         Antenna,
                                              Positioner
              Tail - Antenna Integration Area
                                11.5” Dish


              Satellite TV Integration Area


              Cabin Electronics Compartment
              IRD, SCU        MRDU         ARU300
                                           *E/E Bay

              Wiring
              A,H,K,L          C,D,G,K,L      A,B,G,H,I,M,
                                              N,O




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6.        SYSTEM ATE DESIGN

6.1       General

          Items of electronic equipment, especially those which process and supply command and/or
          monitoring signals, should have Built-In Test Equipment (BITE). The objective of the BITE is
          to identify the failed LRU with a degree of confidence greater than 95%. The removal rate in
          operation, based on BITE indications, should be such that the MTBUR/MTBF ratio is greater
          than 0.85.

          Generally, the provisions of ARINC Reports 604 and 624 should be applied.

6.2       Built-In Test Equipment (BITE)

          The system described in the document should contain Built in Test Equipment (BITE) capable
          of detecting and annunciating LRU faults or failures which occur within the system that affect
          system availability.

          BITE should automatically test, detect, isolate and record intermittent and steady state
          failures. The BITE should display system condition and indicate any faulty LRUs upon
          activation of the self-test routine. In addition BITE should display faults which have been
          detected.

          Failures occurring within the BITE subsystem should not interfere with normal operation of the
          system.

          COMMENTARY: Sufficient margins should be used in choosing BITE parameters to preclude
          nuisance warnings. Discrepancies in system operation caused by power bus transients, EMI,
          ground handling, servicing interference, abnormal accelerations or turbulence should not be
          recorded as faults.




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6.2.1     BITE Display

          BITE information should be made available on RS-485 data buses for use by the on board
          IFE system. This data will be presented to the maintenance technician on the Attendant
          Control Panel or similar display on board the aircraft. One of the LRUs contained within the
          CEC could also have a System/LRU fault status display on the front panel.

          COMMENTARY: Most users desire an alphanumeric display to present fault information to
          line maintenance personnel. The desire includes presentation of the information in the form
          of easily understandable text - not coded! The airlines do not want the maintenance
          personnel to be burdened with carrying a library of code translations. The airlines would like
          to have the fault analysis capability of BITE using the alphanumeric display equal to or
          surpassing the capability currently realized with shop Automatic Test Equipment.

6.2.2     Fault Monitor

          The results of in-flight or ground operations of BITE should be stored in a non-volatile monitor
          memory. The size of the memory should be sufficient to retain detected faults. The data in
          the monitor memory should include flight identification, fault description and faulty LRU
          identification.

          The contents of the monitor memory should be retrievable by BITE operation or by shop
          maintenance equipment.

6.2.3     Self-Test Initiation

          At the time of equipment turn-on, a power-up self-test should be initiated automatically. In
          addition, the system should, where practical, provide self test capability for troubleshooting
          and installation verification. The initiation of all test sequences should be via RS-485 bus.

6.2.4     BITE Output Formats

          The system should be capable of detecting and reporting faults to the IFE as will be defined in
          the ARINC-485 specification.




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7.        OEM UNIQUE SUBMITTAL REQUIREMENTS

7.1       Electromagnetic Interference (EMI)

          An aircraft has numerous antennas, each one used to perform a specific system function.
          The antennas that are most affected by IFE are the HF and VHF communication antennas.
          Since the HF and VHF are used for voice communication, we must take great care to make
          sure that the entertainment system does not interfere with voice communication on and off the
          aircraft. A “bad” emission in the lab at a frequency that is not in a navigation or
          communication radio’s reception band may not be a problem. These are looked at on a case-
          by-case basis and depend on installation, location, and other factors. Always consult your
          aircraft manufacturer if you are not sure.

          The chart below graphically presents the current Aircraft Electromagnetic Spectrum:

                                                 Aircraft Electromagnetic Spectrum

                                        MARKER       VOR         VHF        GLIDE                             MODE S
                ADF            HF       BEACON     LOCALIZER    COMM.       SLOPE     NATS         DME         TCAS

              190 1750       2  30                 108 118     118 137     328 335                960 1220   1030 1090
              KHz KHz       MHz MHz                MHz MHz      MHz MHz    MHz MHz                MHz MHz     MHz MHz
                                         74.85
                                         75.00                                      849 - 851 (REC)
                                         75.15                                      894 - 896 (XMIT)
                                          MHz                                         MHz

                                                                                                    WX        WX
                GPS         SATCOM       TFTS       S-BAND      C-Band     LRRA        MLS         RADAR     RADAR

                            1525 1661              2.6 3.95    3.95 5.85   4.3      5.03   5.09
                             MHz MHz               GHz GHz     GHz GHz     GHz      GHz    GHz
              1575.42 MHz             1670 - 1675 (REC)                                             5.4       9.3
              2 MHz BW                1800 - 1805 (XMIT)                                            GHz       GHz
                "L1"                  MHz MHz



                   DBS        SKY
                   TV        MEDIA

              10.7   12.7     11.7
              GHz    GHz      GHz



          Any emissions from electronic equipment must not interfere with navigation or communication
          radios or systems. With this in mind, OEMs now require emission testing to the modified DO-
          160D Radio Frequency Emissions limit line.

          •    Inside the fuselage, use the modified DO-160D section 21 Category M limit line with the
               following additions:

               •     An HF interference notch of -10db below the specified curve in the frequency band
                     from 2MHz through 30MHz, and they still require emissions measurements
                     from150KHz to 2MHz (Like those in DO-160C Category Z).




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                    The first chart below is the OEM modified DO-160D Category M emission requirement used
                    for all IFE equipment located inside the fuselage:


                                                Maximum Level of Radiated RF Interference Category M Modified

                          80

                          70
         Level : dB V/m




                          60

                          50

                          40

                          30

                          20
                                                                                    25
                               0.1                     1                    10                   100                  1000               10000
                                                                              Frequency - MHz

                                 Curve definition outside the notches: Limit Level = slope * log(Freq in MHz) + intercept
                                 Category M Modified: For Freq < 2 MHz, slope = -4.558, intercept = 41.372
                                                                Freq > 2 MHz and Freq < 25 MHz , slope = -4.558, intercept =
                                 31.372
                                                                Freq > 25 MHz and Freq < 30 MHz, slope = 15.965, intercept =

                                                                                                      The next
                    chart below is the OEM modified DO-160D Category H emission requirement to be used for
                    all equipment located outside the Fuselage, and now also for all seat end equipment:

                                                 Maximum Level of Radiated RF Interference-Category H Modifed


                          80


                          70

                          60
         Level : dB V/m




                          50


                          40

                          30


                          20
                                                                                     25
                               0.1                     1                    10                    100                  1000               10000
                                                                                 Frequency - MHz
                                     Curve definition outside the notches: Limit Level = slope * log(Freq in MHz) + intercept
                                     Category H Modified: For Freq < 2 MHz, slope = -4.558, intercept = 41.372
                                                                   Freq > 2 MHz and Freq < 25 MHz , slope = -4.558, intercept = 31.372
                                                                   Freq > 25 MHz and Freq < 30 MHz, slope = 15.965, intercept = 2.682
                                                                   Freq > 30 MHz , slope = 15.965, intercept = 12.682



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7.2       The “Floating” IFE Test Setup

          The area on the Electrical Qualification submittals that generate the most discussion and
          debate (read: wailing and gnashing of teeth) is the proper way to setup the IFE equipment for
          electromagnetic testing.

          OEMs now require all equipment that is to be located in a monument (Purser workstation or
          Galley) or is to be located in a seat must be tested in the floated configuration. Thus OEM
          requirements say suspend the equipment above the ground plane during testing and DO-160
          says bond the equipment to the ground plane during testing in the EMI chamber.

          The DO-160 specification was created to test aircraft avionics that were to be mounted in
          either the electronics bay on a well-bonded rack, or in the cockpit. Both of these locations
          provide a good ground directly to the IFE equipment case through the rack or mounting
          hardware. This is not the case with equipment mounted in a monument or in a seat.
          Because the Purser workstation and Galley walls are not conductive, the wires become the
          only ground return. The same is true of the seats. The seat track does not provide a good
          mechanical ground, so again the wires become the ground. Since the goal of testing is to
          verify the equipment will operate in the aircraft environment, the test setup should be adjusted
          to match the aircraft installation as much as possible.


                                                   Typical EUT Test Set-up
                                                                                                            Ground Plane
                                    All wires are 5cm off the ground plane.
                                    The UUT is 0.1m from the edge of the
                                    ground plane and the antenna is
                                    another 0.9m from the edge of the
                                    ground plane (1m away from UUT).

                                                                                         All Power and Chassis Ground
              To Support                                                                 wires shall be 1-Meter in length.
              Equipment



                                                                                                                                        To Lab AC
                                                                                                     LISN                               Power Supply

                                                                                                                                        To Lab DC
                                                                                                     LISN                               Power Supply
                                                                         EUT



              To
              Analyzer                                                           All power leads can be filtered at the wall
                                                                                 prior to the LISNl to prevent coupling
                                                                          1m     unwanted RF into the screen room.



                                                                       Antenna
                           Screen                                                                                              Screen
                           Room                                                                                                Room
                           Wall                                                                                                Wall

          •       All equipment and wires are suspended above the ground plane by 5cm (~2in).
          •       LISN are used on the HI side of power input only.
          •       A 1-meter minimum chassis ground wire is used.

          As a rule, Emissions testing should be run in both the DO-160 “Grounded” and in the
          “Floated” configuration to protect the DBS supplier and the airframe OEM. The results from
          these two test conditions will help the DBS supplier and airframe OEM to design the best
          installation for the target aircraft.


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7.3           ACRONYMS
              Acronym    Definition
              1D-ESA     One Dimension Electronically Scanned Array
              AC         Aircraft Circular
              ACS        Antenna Control System
              AIA        Antenna Integration Area
              AIU        Antenna Interface Unit
              ARINC      Aeronautical Radio Incorporated
              ARU        Airborne Receiver Unit
              ASU        Antenna Switch Unit
              ATA        Aeronautical Television Antenna
              ATE        Automated Test Equipment
              BFE        Buyer Furnished Equipment
              BITE       Built-In Test Equipment
              CAT        Category
              C-Band     Frequency of operation 3.95GHz – 5.85GHz
              CDS        Cabin Distribution System
              CEC        Cabin Electronics Compartment
              CFM        Cubic Feet per Minute
              CG         Center of Gravity
              COTS       Commercial Off The Shelf
              DBS        Direct Broadcast Satellite
              DBSRS      Direct Broadcast Satellite Receive System
              EMC        Electromagnetic Compatibility
              EMI        Electromagnetic Interference
              ESD        Electrostatic Discharge
              EUT        Equipment Under Test
              FAA        Federal Aviation Administration
              FMC        Flight Management Computer
              FMS        Flight Management System
              GPS        Global Positioning System
              HF         High Frequency (2MHz-30MHz)
              ID         Identification
              IEEE       Institute of Electrical & Electronic Engineers
              IF         Intermediate Frequency
              IFE        In Flight Entertainment
              IFI        Intermediate Frequency Interface
              IMU        Intermediate Frequency Multiplexer Unit
              IRD        Integrated Receiver Decoder




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          ACRONYMS (Continued)

              Acronym    Definition
              JCU        JeTVision Control Unit
              Ka-Band    Frequency of operation 25.0GHz – 27.5GHz
              Ku-Band    Frequency of operation 11.7GHz – 12.7GHz
              L-Band     Frequency of operation 1.525GHz – 1.6605GHz
              LISN       Line Impedance Stabilization Network
              LNB        Low Noise Block
              LNC        Low Noise Converter
              LRU        Line Replaceable Unit
              MRDU       Multiple Receiver Decoder Unit
              MRM        Multi-Channel Receiver Decoder Unit
              NTSC       National Television Standards Committee
              OEM        Original Equipment Manufacturer
              PAA        Phased Array Antenna
              PAL        Phase Alternating Line
              PS         Power Supply
              PWS        Purser Work Station
              QTP        Qualification Test Procedure
              QTR        Qualification Test Report
              RDU        Receiver Decoder Unit
              RF         Radio Frequency
              RTCA       Radio Technical Commission of Aeronautics
              S-Band     Frequency of operation 2.6GHz – 3.95GHz
              SCSRD      Standard Cabin Systems Requirements Document, Boeing D6-36440
              SCU        System Control Unit
              SPAC       System Phased Array Controller
              SRR        Satellite Recognition Receiver
              SSM        Sign Status Matrix
              STIA       Satellite Television Integration Area
              TBD        To Be Defined
              TC         Technical Committee
              TV         Television
              USB        Universal Serial Bus
              UUT        Unit Under Test
              VAC        Volts Alternating Current
              VDC        Volts Direct Current
              VHF        Very High Frequency (100MHz – 150MHz)
              WAEA       World Airline Entertainment Association




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                      ATTACHMENT 1 – SUPPLIER CONFIGURATIONS

              STANDARD INSTALLATION CONFIGURATION AREA WORK SHEET




  AIA
                                                                           Antenna
                                                                          Installation
                                                                             Area




  STIA
                                                                            Satellite
                                                                           Television
                                                                          Integration
                                                                             Area




                  A   B   C   D   E   F   G   H   I   J   K   L   M   N   O




                  A   B   C   D   E   F   G   H   I   J   K   L   M   N   O
  CEC


                                                                             Cabin
                                                                          Distribution
                                                                            Center




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                         ATTACHMENT 2 – CONTENT LICENSING ISSUES




          SUMMARY OF CONTENT LICENSING ISSUES

          The right to publicly perform or display video or audio content rests exclusively with the
          copyright owner. Any company wishing to publicly exhibit copyrighted motion pictures or
          audio/visual works must secure licenses to do so.

          In general, the scope granted traditional television and satellite broadcast licenses does not
          include exhibition onboard aircraft. It cannot be assumed that the content licenses granted for
          traditional television and satellite broadcast exhibition automatically grant the right to exhibit
          this content to in-flight audiences.

          Licenses which expressly permit content to be exhibited on in-flight television channels may
          be obtained either from content packagers who acquire those rights for distribution on airlines,
          or directly from the copyright owner of each program. It is incumbent upon the providers of in-
          flight television and satellite services to secure licenses to all programming they provide for
          display onboard aircraft. This principle applies to both commercial and non-commercial
          aircraft.




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                         ATTACHMENT 3 – ARINC 485 Satellite TV Commands


          SUMMARY OF NEW TYPE 2 ARINC 485 COMMANDS FOR AIRBORNE SATELLITE TV

              Supplier             Definition
              Airshow              Enhanced_Configuration_Request (“ECR”)
              Airshow              Enhanced_Configuration_Response (“ERC”)
              Airshow              IRD_Direct_Commands (“IDC”)
              Airshow              IRD_Indirect_Commands (“IIC”)
              Airshow              IRD_Control_Commands (“ICC”)
              Airshow              IRD_OSD_Control (“OCC”)
              Airshow              Manual_Control_Mode (“MMC”)
              Airshow              Automatic_Control_Mode (“MAC”)
              Airshow              Manual_Control (“MIC”)
              Airshow              Command2_Error (“CER”)
              Airshow              STV_Status_Request (“SSR”)
              Airshow              STV_Status_Response (“RSS”)
              Airshow              STV_Status_Change (“RSC”)
              Airshow              STV_Configuration_Request (“SCR”)
              Airshow              STV_Configuration_Response (“SDT”,1,1)
              Airshow              Service_Configuration_Request (“SIR”)
              Airshow              Service_Configuration_Response (“SDT”,1,2)
              Airshow              IRD_Command_List_Request (“ICR”)
              Airshow              IRD_Command_List_Response (“SDT”,1,3)
              Airshow              Flight_Information_Request (“FIR”)
              Airshow              Flight_Information_Response (“RFI”)
              Airshow              Clock_Time_Request (“CTR”)
              Airshow              Clock_Time_Response (“RCT”)
              Airshow              Clock_Time_Set (“SCT”)
              Airshow              BITE_Status_Request (“BSR”)
              Airshow              BITE_Status_Response (“RBS”)
              Airshow              Error_Log_Request (“ELR”)
              Airshow              Error_Log_Response (“REL”)
              Airshow              Error_Log_Clear (“ELC”)




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                             ATTACHMENT 3 – ARINC 485 Satellite TV Commands

           SUMMARY OF NEW TYPE 2 ARINC 485 COMMANDS FOR AIRBORNE SATELLITE TV
              Type 2 Commands          Definition
              Rockwell/Collins         get_system_config
              Rockwell/Collins         set_system_config
              Rockwell/Collins         get_channel_list
              Rockwell/Collins         set_channel_list
              Rockwell/Collins         get_program_mode
              Rockwell/Collins         set_program_mode
              Rockwell/Collins         set_AutoChannel_X
              Rockwell/Collins         set_AutoChannelMode_X
              Rockwell/Collins         get_AutoChannelStatus_X
              Rockwell/Collins         get_powerup_status
              Rockwell/Collins         get_board_count
              Rockwell/Collins         get_signal_quality_X
              Rockwell/Collins         get_primary_status_X
              Rockwell/Collins         get_comm_status
              Rockwell/Collins         get_antenna_status
              Rockwell/Collins         get_current_satellite
              Rockwell/Collins         set_current_satellite
              Rockwell/Collins         reset_system
              Rockwell/Collins         reset_board_X
              Rockwell/Collins         set_channel_X
              Rockwell/Collins         set_IRD_mode_X
              Rockwell/Collins         display_msg_X
              Rockwell/Collins         set_MPG_filter_X
              Rockwell/Collins         check_new_MPG_X
              Rockwell/Collins         get_MPG
              Rockwell/Collins         set_favorite_list_X
              Rockwell/Collins         get_favotite_list_X
              Rockwell/Collins         get_programming_info_X
              Rockwell/Collins         set_av_X
              Rockwell/Collins         show_logo_X
              Rockwell/Collins         show_mini_guide_X
              Rockwell/Collins         remote_control_X

       Honeywell Definitions:

              Satellite Fields            RDU Fields             MRU Fields

               7   6    5 4 3 2 1 0        7 6 5 4 3 2 1 0        7 6 5 4 3 2 1 0
               0   0    0 - satellite 1          0 0 0 - RDU #1               0 0 - MRU #1
               0   0    1 - satellite 2          0 0 1 - RDU #2               0 1 - MRU #2
               0   1    0 - satellite 3          0 1 0 - RDU #3               1 0 - MRU #3
               0   1    1 - satellite 4          0 1 1 - RDU #4               1 1 - MRU #4
               1   0    0 - satellite 5          1 0 0 - reserved
               1   0    1 - satellite 6          1 0 1 - reserved
               1   1    0 - satellite 7          1 1 0 - reserved
               1   1    1 - satellite 8          1 1 1 - reserved




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