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


                       Technical Committee
              World Airline Entertainment Association




                 DRAFT
                   6-Oct-99
                                         REVISION STATUS




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




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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    Custom Data Source (Receive Only) .......................................................................................... 2
1.3    Performance Attributes ................................................................................................................... 2
1.3.1    Antenna Coverage Volume ......................................................................................................... 2

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

3. ................................................................................................................................................................... 5

3. SYSTEM ARCHITECTURE ................................................................................................................... 5
3.1          General System Description ........................................................................................................... 5
3.2          Unit Descriptions ............................................................................................................................. 5
3.2.1 .............................................................................................................................................................. 6
3.2.1           Radome....................................................................................................................................... 6
3.2.2           Antenna ....................................................................................................................................... 6
3.2.3           Antenna Positioning Unit ............................................................................................................. 6
3.2.4           Antenna Power Supply ................................................................................................................ 6
3.2.5           Low Noise Block (LNB) ............................................................................................................... 6
3.2.6 .............................................................................................................................................................. 7
3.2.6           Antenna Control Unit (ACU) ........................................................................................................ 7
3.2.7           Antenna Switch Unit (ASU) ......................................................................................................... 7
3.2.8           Receiver/Decoder Unit (RDU) ..................................................................................................... 7
3.3 ................................................................................................................................................................. 8
3.3          External System Interfaces ............................................................................................................. 8
3.3.1           Inertial Reference Unit ................................................................................................................ 8
3.3.1.1         Definition of the ARINC-429 Sign Status Matrix (SSM) Bits: ...................................................... 8
3.3.2 .............................................................................................................................................................. 9
3.3.2           Tail ID .......................................................................................................................................... 9
3.3.3           IFE Interfaces .............................................................................................................................. 9
3.3.3.1         Control/BITE Interface................................................................................................................. 9
3.3.3.2         Analog Video/Audio Outputs ....................................................................................................... 9
3.3.3.3         Digital Video/Audio Outputs ........................................................................................................ 9
3.3.4           Power Input ................................................................................................................................. 9

4. ................................................................................................................................................................. 10

4. SYSTEM OPERATION ........................................................................................................................ 10
4.1   Antenna Steering Fail-Over Modes............................................................................................... 10
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4.2           Channel Selection ......................................................................................................................... 10

5. INSTALLATION CONSIDERATIONS ................................................................................................. 10
5.1         Equipment Installation Areas ........................................................................................................ 10
5.1.1          Antenna Installation Area (AIA) ................................................................................................. 10
5.1.2          Antenna Installation Area - Tail (AIA) ....................................................................................... 10
5.1.3          Satellite Television Integration Area .......................................................................................... 10
5.1.4          Cabin Equipment Center (CEC) ................................................................................................ 11
5.2         Interwiring ..................................................................................................................................... 11
5.2.1 ............................................................................................................................................................ 12
5.2.1          CEC to STIA Standard Wiring Bundle Characteristics.............................................................. 12
5.3         Mounting Provisions...................................................................................................................... 12

6. CONTENTS LICENSING..................................................................................................................... 14
6.1   Overview of Issues ....................................................................................................................... 14
6.2   Summary of Licensing Issues ....................................................................................................... 14

7. SYSTEM ATE DESIGN ....................................................................................................................... 15
7.1         General ......................................................................................................................................... 15
7.2         Unit Identification .......................................................................................................................... 15
7.3         Built-In Test Equipment (BITE) ..................................................................................................... 15
7.3.1 ............................................................................................................................................................ 16
7.3.1          BITE Display.............................................................................................................................. 16
7.3.2          Fault Monitor ............................................................................................................................. 16
7.3.3          Self-Test Initiation ..................................................................................................................... 16
7.3.4          BITE Output Formats ................................................................................................................ 16

8. ................................................................................................................................................................. 17

8. Boeing Unique Submittal Requirements ......................................................................................... 17
8.1          Electromagnetic Interference (EMI) Concerns ............................................................................. 17
8.2 ............................................................................................................................................................... 19
8.2          The “Floating” IFE Test Setup ...................................................................................................... 19

9. ................................................................................................................................................................. 20

9.     AIRBUS Unique Submittal Requirements ........................................................................................ 20

10. ............................................................................................................................................................... 21

10.       ACRONYMS..................................................................................................................................... 21

1.     Standard Installation Configuration Area Work Sheet ..................................................................... 1




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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.

             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 Ku, Ka 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 with appropriate avionics on
             board.

             The signal received by the onboard equipment is processed and made available to the on
             board In-Flight Entertainment (IFE) System for distribution to the passenger either on
             overhead monitors or on 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 channels that can be selected as well as the number of selected channels
             which can be fed to the IFE system will depend on the DBS broadcast service selected as
             well as the avionics equipment selected.




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                                Up Link                                     Down
                                                                            Link




                                                                                       Aircraft
              Ground
              Station




                           TV programs


1.2.2        Custom Data Source (Receive Only)

             A description of this service is required.

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 (see below). The ideal coverage volume should permit signal
             reception for all normal flight attitudes (e.g. +20°/-5° of pitch, +25°/-° of roll) except with
             satellites at low elevation angles to the aircraft.

             Commentary: Satellite systems providing limited regional coverage require limited antenna
             scanning capability as compared to global systems which require wide scanning antennas.
             Refer to the following table. (The table below assumes 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°


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             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 antennas.

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 25.1309-1A                           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.




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

             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 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

2.5          WAEA
             WAEA-395                        World Airline Entertainment Association specification,
                                             “Content

2.6          Boeing
             D6-36440                        Standard Cabin System Requirements Document

             D6-44588                        Electrical Requirements for Utilization Equipment
                                             installed on Commercial Transport Airplanes.

             D6-54921                        Equipment Vibration Requirements




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3.           SYSTEM ARCHITECTURE

3.1          General System Description

             The following block diagram shows the Line Replaceable Units (LRU) which may be
             contained within the DBS Receive System. System Suppliers may chose to integrate multiple
             Line Replaceable Units into a single LRU.


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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        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.

3.2.2        Antenna

             The antenna is the portion of the system which collects or receives the Radio Frequency (RF)
             signal in free space and transitions it to an 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.

3.2.3        Antenna Positioning Unit

             The Antenna Positioning unit is the mechanical interface that physically positions or steers the
             Dish or Array Antenna in the Azimuth and Elevation planes of operation, allowing the antenna
             to track the satellite during flight. The Antenna Positioning Unit (if required in the system) is
             always co-located with and attached to the antenna inside the Radome.

3.2.4        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 Unit or the Low
             Noise Block (3.2.5).

             Input and output voltages will vary depending on system implementation.

3.2.5        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 this function may be integrated into the antenna LRU.




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3.2.6        Antenna Control Unit (ACU)

             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 (or directly to the Antenna in some implementations) to
             cause the antenna to steer in the desired direction.

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

3.2.7        Antenna Switch Unit (ASU)

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

3.2.8        Receiver/Decoder Unit (RDU)

             The RDU receives the amplified RF signal from the LNB or Antenna Switch Unit, and
             processes it as required to provide signals which 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 (NTSC or PAL) with separate Analog Audio,
             and Modulated “normal” NTSC (standard NTSC signal with audio included).




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3.3          External System Interfaces

3.3.1        Inertial Reference Unit

             For Airborne TV systems without integrated GPS capability, navigation data shall 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        Tail ID

             Some Satellite TV systems utilize Tail ID in their system design. Please note that Tail ID 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 Tail 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 the ARINC 485 (currently in
             draft form) 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 TBD for details of the ARINC 485 word format.

3.3.3.2      Analog Video/Audio Outputs

             The Airborne Satellite TV Receiver system shall provide 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 TBA.

3.3.4        Power Input

             Primary power should be fed to the CEC 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
             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 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 Equipment Center (CEC).

5.1.1        Antenna Installation Area (AIA)

             Location in aircraft (proximity requirements)
             Space envelope requirements for equipment.
             Cooling Requirements.
             Radome Attributes

5.1.2        Antenna Installation Area - Tail (AIA)

             Location in aircraft (proximity requirements)
             Space envelope requirements for equipment.
             Cooling Requirements.
             Radome Attributes

5.1.3        Satellite Television Integration Area

             Location in aircraft (proximity requirements)
             Space envelope requirements for equipment.
             Cooling Requirements.

             The Satellite TV Integration Areas are co-located close to the antenna fuselage penetration as
             possible. Fuselage and Vertical Fin (Tail) locations are currently being studied to provide the
             Airborne Satellite Television system suppliers with a “standard location” for their installations.
             The plan is to provide a “standardized antenna location for both the fuselage and the tail, and
             to provide “standardized mounts for the STIA equipment.

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



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5.1.4        Cabin Equipment Center (CEC)

             Location in aircraft (proximity requirements)
             Space envelope requirements for equipment.
             Cooling Requirements.

             The Cabin Equipment Center (CMC) is the location where the electronics that interface to the
             on-board In-Flight Entertainment reside. This location is airframe manufacturer defined. The
             location my be the IFE Purser Work Station or other monument.

             Note: The wiring from the STIA to the CEC is defined by the airframe
                   manufacturer.

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.

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                               S r e b t r c dt
                               F P oa t
                                 i
                                 nS br i
                               IE WC e   n
                                                                                y ai l e
                                                                                 pl ra
                                                                                 i  p
                                                                                TcA n


               a otd tn st c e g L L L
                i u a as a et
                l  n   e   e b  h 1 2 3
               Tm e n n y ml l n = '+ +
               ua m e n n y c e g L L
                s e u a as a et
                 e    n  e   e b    h 1 3
               F l g otd tn stml l n = +




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5.2.1        CEC to STIA Standard Wiring Bundle Characteristics



                    tn d b e i ( I t C
                    a rC
                     d
                    S a a Dt nTo C
                         l
                         e f ioS
                           in    A E  )
                                         0mX
                                          -
                                          O A
                                            C
                                         5h O
                3
                1                                                                                  3
                                                                                                   1
                                         0mX
                                          -
                                          O A
                                            C
                                         5h O
                4
                1                                                                                  4
                                                                                                   1
                                         5mX
                                          -
                                          O A
                                            C
                                         7h O
                5
                1                                                                                  5
                                                                                                   1
                                         5mX
                                          -
                                          O A
                                            C
                                         7h O
                6
                1                                                                                  6
                                                                                                   1
                                         M- T 2 ls 1W 1 A0z
                                          S4 y
                                           3  eC  s 6G1 4 )
                                                        V 0
                                         B 1 8p 5a2 A ( 5C H
                 1                                                                                 1
                 2                                                                                 2


                                         M- T 2 ls 1W
                                          S4 y
                                           3  eC  s 6G
                                         B 1 8p 5a2 A
                 3                                                                                 3
                 4                                                                                 4

                                         M- T 2 ls 1W
                                          S4 y
                                           3  eC  s 6G
                                         B 1 8p 5a2 A
                 5                                                                                 5
                 6                                                                                 6

                                         M- T 2 ls 1W
                                          S4 y
                                           3  eC  s 6G
                                         B 1 8p 5a2 A
                 7                                                                                 7
                 8                                                                                 8


                                         2 5 3 A (ev fr a
                                          8 0 0 G se
                                          0 2-     e o t)
                                         S W 2W Rr d D  a
                 9                                                                                 9
                 0
                 1                                                                                 0
                                                                                                   1

                                         2 5 3 A (ev fr a
                                          8 0 0 G se
                                          0 2-     e o t)
                                         S W 2W Rr d D  a
                 1
                 1                                                                                 1
                                                                                                   1
                 2
                 1                                                                                 2
                                                                                                   1




5.3          Mounting Provisions

             The following tables outline the possible installation locations for the LRUs within in the
             system. Where multiple locations are indicated for LRUs suppliers should ensure the LRU
             location is consistent with:

             1. The standard inter-wiring defined between the installation locations

             2. The Space envelops available in the installation location.




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                                 Table 1: LRU Installation Locations

             Supplier A       Supplier B       Supplier C   Supplier D     Supplier E
             Fuselage - Antenna Integration Area
             Daytron                        Phased Array    Daytron        1D-ESA
             DBS-2400,                      Antenna         DBS-2400,      Antenna,
             Positioner                                     Positioner     Positioner

             Tail - Antenna Integration Area
             Daytron DBS-      12.88” Dish,                 11.65” Dish
             2100,             Positioner,
             Positioner,       LNB, JCU
             LNB
             Satellite TV Integration Area
             AIU, IMU          PS            LNB, LPC,      LNB, LPC,      ACS, IFI
                                             PS, SPAC       AIU


             Cabin Equipment Area
             RDU           RDU                 ASU, COTS    RDU            MRM
                                               Receivers




             Supplier F       Supplier G       Supplier H   Supplier I
             Fuselage - Antenna Integration Area
             S-Band                         Phased Array    Phased Array
             Phased Array                   Antenna         Antenna,
             Antenna                                        Positioner

             Tail - Antenna Integration Area
                               EMS
                               DBA-1150
                               11.5” Dish

             Satellite TV Integration Area
             SCU



             Cabin Equipment Area
             IRD           MRDU                             ARU300




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6.           CONTENTS LICENSING

6.1          Overview of Issues

             The United States 1976 Copyright Act (U.S.Code, Title 17) classifies motion pictures in two
             broad categories:

                Private Home Use

                Public Performance

             One of the exclusive rights granted to the copyright holder of a motion picture and other
             audiovisual works and intellectual property is the right to “perform” that motion picture
             “publicly. (Section 106 [4]).

             To perform a motion picture “publicly” under the law means “to perform or display it at a place
             open to the public or at any place where a substantial number of persons outside a normal
             circle of a family and its social acquaintances are gathered.”

             By this definition the IFE market on transport aircraft is a public performance.

             Public performances are broken into two primary groups:

                Theatrical

                Non-Theatrical

             Theatrical is any performance shown in a theater; non-theatrical is any kind of public
             performance-taking place anywhere other than in a theater.

             By this definition the IFE market on transport aircraft is a non-theatrical public performance.

             When a copyright owner licenses its content for use in specific markets, it is common to retain
             its exclusive right to publicly perform its intellectual property. Exceptions to this must be
             clearly written into the licenses granted by copyright owners.

             Exceptions may be made in certain license agreements to permit a television market, defined
             as private home use, to move over the line into certain specific and limited public performance
             markets. The content provider would have to make it possible for the broadcaster to include
             the program in its transmission to the certain specific and limited public performance markets
             by including such rights in the broadcaster’s license.

             Currently the rights for the exhibition onboard transport aircraft are typically not included in
             the TV broadcaster’s license.

             The licenses granted by such distributors to direct broadcast satellite (DBS) services do not
             typically include the right to serve aircraft, and reserve for copyright owners all rights not
             specifically granted in the license.

6.2          Summary of Licensing Issues
             The right to perform or display video or audio content rests exclusively with the copyright
             owner. A company wishing to publicly exhibit copyrighted motion pictures or audio/visual
             works, should secure licenses to do so. The TV market is defined as private home use.
             Exceptions may be made in certain license agreements to permit a TV market to move over
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             the line into certain specific and limited public performance markets. Traditional content
             licensing does not include exhibition onboard aircraft. For an airline to obtain the right to
             transmit onboard via satellite or other means, the content of a TV channel’s separate licenses
             to each program should be obtained from the copyright owner of each program. There may
             be other copyright owners in each territory.

7.           SYSTEM ATE DESIGN

7.1          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 is greater than
             0.85.

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

7.2          Unit Identification

7.3          Built-In Test Equipment (BITE)

             The system described in the document should contain Built in Test Equipment (BITE) capable
             of detecting and annunciation a minimum of TBD % of the faults or failures which occur within
             system.

             BITE should operate continuously during flight. Monitoring of the results should be automatic.
             The 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 during in-flight monitoring.

             No failure occurring within the BITE subsystem should 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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7.3.1        BITE Display

             BITE information should be made available on all applicable 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. As an option, 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.

7.3.2        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 during the
             previous ten flight legs. The data in the monitor memory should include flight leg
             identification, fault description and faulty LRU identification.

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

7.3.3        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.

             COMMENTARY: As an aid to shop maintenance and local trouble-shooting on the line, a self
             test mechanism should be provided on the front panel of one of the system LRUs located
             within the CEC. The momentary depression of the push button on the front panel of the LRU
             should initiate a unit/system self test. The self-test routine should start with an indicator test in
             which all indicator elements are activated simultaneously. If the self-test routine detects a
             fault, the "all on" indication should be deactivated leaving the appropriate "fault" indication
             activated. If no fault is recorded, the "all on" indication should be deactivated leaving the
             "normal" indication visible.

7.3.4        BITE Output Formats

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




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8.           BOEING UNIQUE SUBMITTAL REQUIREMENTS

8.1          Electromagnetic Interference (EMI) Concerns
             An aircraft is covered with 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 mess up
             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:




               Any emissions from electronic equipment must not interfere with navigation or
               communication radios or systems. With this in mind, The Boeing Company now
               requires emission testing to their modified DO-160D Radio Frequency Emissions
               limit line.
                  Inside the fuselage, Boeing requires a modified DO-160D section 21 Category
                   M limit line with the following additions:
                      Boeing added 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 Boeing modified DO-160D Category M emission
                    requirement used for all IFE equipment located inside the fuselage:




                    The next chart below is the Boeing 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:




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8.2          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.

             At Boeing we 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
             Boeing says 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.

             What you have to realize is that 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, we must rely
             on the wires for our ground return. The same is true of the seats. The seat track does not
             provide a good mechanical ground, so again we must rely on the wires for our ground. Since
             the goal of testing is to verify the equipment will operate in the aircraft environment, we must
             adjust the test setup to match the aircraft installation as much as possible.

             As you can see from the illustration below, the test is configured much like the DO-160
             configuration with three major differences:

                                 i
                                Ta T t e
                                y l Us t p
                                 c
                                p ETSe -u                                              All equipment and wires are
                                                         Gd n
                                                         r nl e
                                                         o P
                                                          u a
                                                                                             suspended above the
                           Ar a c f hr nln
                           lw r5 o e upe
                           l i sem g d .
                              e   ft o a
                             Us m e e h
                           T U0 f m doe
                           h T. r t e f
                            e i 1 oh g t
                                                                                        ground
                           r d ed ani
                           o p at n a
                            u a   h e s
                           gnlnn et n
                           ah .m t e oe
                           ne9r hd f
                            or
                            t 0 fm g t
                                 o e eh
                           gnln my m )
                            u a1 a
                           r d e a f U
                           o p ( wo Ur  T.
                                                                                             plane by 5cm (~2in).
                                                 lP rn h i r n
                                                 l o aC so
                                                    e   s
                                                        s u
                                                 A w d a Gd
                  o p
                   So
                   ur
                  T pt

                                                                                    
                                                 i sa 1 t n g
                                                 r h
                                                  e lb- e eh
                                                       M r
                                                 wsl e ei ln.t
                  Em
                  q e
                   u n
                   i
                   p t
                                                                                        LISN are used on the HI side
                                                                     Tb
                                                                     o A
                                                                      L C
                                                                      a                    of power input only.
                                                      IN
                                                      S
                                                      L              o Sl
                                                                      w p
                                                                      e p
                                                                     P r uy

                                                                     o D
                                                                      L C
                                                                      a
                                                                     Tb


                                                                                    
                                                      IN
                                                      L
                                                      S               e p
                                                                      w p
                                                                     o Sl
                                                                     P r uy
                                        E
                                        UT
                                                                                        A 1-meter minimum chassis
                   T
                   o
                    y
                   ne
                   Az
                    l
                    ar                        Awacbt et el
                                              lo l s er
                                              lp r d n fe a w
                                                 e       l
                                                   e a i dt ah l
                                                                                           ground wire is used.
                                              rr hIN r e oi
                                              i o S p nu
                                               o e t et p     n
                                              p t t L lo v c l g
                                         m
                                         1    n t F t cn m
                                               wd it h r r .
                                               a e n ee o
                                              u n Ro s e o



                                        n a
                                        tn
                                         e
                                        An
                       c
                       re
                       Sne                                         Sn
                                                                   c
                                                                   ree
                       o
                       o
                       Rm                                          o
                                                                   o
                                                                   Rm
                       a
                       Wl
                        l                                          a
                                                                   Wl
                                                                    l    C .R 4
                                                                          S E /
                                                                          R 29
                                                                           P / 8
                                                                         S D (2 )
                                                                         yn e
                                                                          Dd
                                                                           a e
                                                                           l
                                                                         bo L




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9.           AIRBUS UNIQUE SUBMITTAL REQUIREMENTS




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10.          ACRONYMS
              AIA            Antenna Integration Area
              ARINC          Aeronautical Radio Incorporated
              ATA            Aeronautical Television Antenna
              BFE            Buyer Furnished Equipment
              BITE           Built-In Test Equipment
              CAT            Category
              CDS            Cabin Distribution System
              CEC            Cabin Equipment Center
              CFM            Cubic Feet per Minute
              CG             Center of Gravity
              DBS            Direct Broadcast Satellite
              DBSRS          Direct Broadcast Satellite Receive System
              EMI            Electromagnetic Interference
              ESD            Electrostatic Discharge
              FMC            Flight Management Computer
              IFE            In Flight Entertainment
              IRD            Integrated Receiver Decoder
              LNB            Low Noise Block
              LRU            Line Replaceable Unit
              NTSC           National Television Systems Committee
              PAL            Phase Alternating Line
              QTP            Qualification Test Procedure
              QTR            Qualification Test Report
              RTCA           Radio Technical Commission of Aeronautics
              SCSRD          Standard Cabin Systems Requirements Document, Boeing D6-
                             36440
              STIA           Satellite Television Integration Area
              TBD            To Be Defined
              VAC            Volts Alternating Current
              VDC            Volts Direct Current




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                           ATTACHMENT 1 – SUPPLIER CONFIGURATIONS

1.           STANDARD INSTALLATION CONFIGURATION AREA WORK SHEET




     AIA-F




     STIA




                             C1 C2 C3 C4 T1 T2 T3 T4    P1   P2




                             C1 C2 C3 C4 T1 T2 T3 T4    P1   P2
     CEC


                                                                       Cabin
                                                                    Distribution
                                                                      Center




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