Guidance for the Installation and use of Direct broadcast Satellite by wufengmei007

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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

             WAEA TC Specification 0798, Version 1.0




                             Prepared by
                       Satellite Working Group


                        Technology Committee
                World Airline Entertainment Association




   Adopted by the WAEA Technology Committee February 16, 2000

      Adopted by the WAEA Board of Directors March 24, 2000
                                                   WAEA SATELLITE WORKING GROUP




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
3.3.3.2          Analog Video/Audio Outputs.....................................................................................................10
                                                   WAEA SATELLITE WORKING GROUP




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
                               WAEA SATELLITE WORKING GROUP




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
                                WAEA SATELLITE WORKING GROUP




                           Up Link                                      Down
                                                                        Link




                                                                                  Aircraft
              Ground
              Station




                        TV programs


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.
                             WAEA SATELLITE WORKING GROUP



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.
                    WAEA SATELLITE WORKING GROUP




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”
                          WAEA SATELLITE WORKING GROUP




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.
                                    WAEA SATELLITE WORKING GROUP




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
                                             tr
                                        Con
                     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.
                              WAEA SATELLITE WORKING GROUP




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.
                               WAEA SATELLITE WORKING GROUP




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.
                               WAEA SATELLITE WORKING GROUP




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)
                               WAEA SATELLITE WORKING GROUP




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.
                             WAEA SATELLITE WORKING GROUP




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.
                                    WAEA SATELLITE WORKING GROUP



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
                             WAEA SATELLITE WORKING GROUP




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.
                          WAEA SATELLITE WORKING GROUP




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
      Antenna                         Array
                                      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
                          WAEA SATELLITE WORKING GROUP



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.
                               WAEA SATELLITE WORKING GROUP




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.
                                 WAEA SATELLITE WORKING GROUP




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).
                   WAEA SATELLITE WORKING GROUP



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




                                                                                 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:
                                        WAEA SATELLITE WORKING GROUP




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.
                 WAEA SATELLITE WORKING GROUP



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
               WAEA SATELLITE WORKING GROUP



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
                   WAEA SATELLITE WORKING GROUP



               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
                     WAEA SATELLITE WORKING GROUP



              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.
                 WAEA SATELLITE WORKING GROUP



           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”)
                          WAEA SATELLITE WORKING GROUP



                    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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