IFE Training Manual

A321/A319/A320 i3000 Inflight Entertainment System Training Manual

NACIL A321/A319/A320 i3000 Training Manual

Training Binder Synopsis This training binder provides information for Engineering and Line Maintenance personnel to gain a good theoretical understanding of the iSeries system and a basic knowledge of the components that make up the system. The binder contains maintenance procedures and basic troubleshooting techniques to permit the student to perform system troubleshooting and return the system to service. This binder is for training purpose only; it is not under document control and will not be updated. The material contained in this binder is to be used as reference material only. Please refer to the appropriate Aircraft Maintenance Manual for aircraft maintenance procedures and current wiring and installation drawings. In case of a discrepancy between this document and any controlled document issued by the aircraft manufacturer such as the aircraft maintenance manual, trouble-shooting manual, or flight crew operating manual or any component maintenance manual issued by Thales Avionics, the controlled document will take precedence over this binder.

The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008

NACIL(I) i3000 LM A3xx Master Apr 2008

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A321/A319/A320 i3000 Training Manual

TABLE OF CONTENTS 1

SYSTEM OVERVIEW.................................................................................................................................. 1-1 1.1 GENERAL OVERVIEW ....................................................................................................................... 1-1 1.2 SERVICES DISTRIBUTION ................................................................................................................ 1-3 1.3 NACIL(I) A321 LAYOUT OF PASSENGER ACCOMMODATIONS (LOPA).................................. 1-6 1.4 NACIL(I) A319 LOPA........................................................................................................................... 1-7 1.5 NACIL(I) A320 LOPA........................................................................................................................... 1-8 1.6 SYSTEM OVERVIEW .......................................................................................................................... 1-9 1.6.1 System Control / Operator Interface.................................................................................................. 1-9 1.6.2 In-Seat Broadcast Audio and Video................................................................................................... 1-9 1.6.3 Video Announcement (VA)............................................................................................................... 1-10 1.6.4 Passenger Address All-Call (PA ALL)............................................................................................. 1-10 1.6.5 Area Passenger Address (Area PA)................................................................................................. 1-10 1.6.6 Pre-Recorded Announcement Machine (PRAM) ............................................................................. 1-10 1.6.7 Boarding Music (BGM) ................................................................................................................... 1-11 1.6.8 Moving Map (MMAP)...................................................................................................................... 1-11 1.6.9 In-Seat Laptop Power ...................................................................................................................... 1-11 1.6.10 Maintenance Functions............................................................................................................... 1-12 1.6.11 Content Management .................................................................................................................. 1-12 1.6.12 Acronyms & Abbreviations ......................................................................................................... 1-13

2

SYSTEM DESCRIPTION............................................................................................................................. 2-1 2.1 2.1.1 2.1.2 2.2 2.3 2.4 2.4.1 2.5 2.6 2.7 2.7.1 2.7.2 2.8 2.9 2.9.1 2.10 2.11 2.12 2.13 2.14 2.15 2.16 2.17 2.18

3

SYSTEM EQUIPMENT ........................................................................................................................ 2-1 Parts List............................................................................................................................................ 2-3 Parts Locations.................................................................................................................................. 2-4 SUBSYSTEMS ...................................................................................................................................... 2-4 POWER-UP............................................................................................................................................ 2-5 INTERACTIVE CABIN MANAGEMENT TERMINAL (ICMT)........................................................ 2-6 RJ45 Ethernet Ports........................................................................................................................... 2-8 USB PORTS........................................................................................................................................... 2-8 CABIN CREW EXPERIENCE.............................................................................................................. 2-9 BROADCAST VIDEO / AUDIO......................................................................................................... 2-11 Broadcast Video............................................................................................................................... 2-11 Broadcast Audio .............................................................................................................................. 2-12 PASSENGER FLIGHT INFORMATION SYSTEM (PFIS) ............................................................... 2-14 PASSENGER ANNOUNCEMENT (PA) ............................................................................................ 2-16 Direct PA ......................................................................................................................................... 2-16 VIDEO ANNOUNCEMENT (VA)...................................................................................................... 2-17 PRE-RECORDED ANNOUNCEMENT (PRAM)............................................................................... 2-18 BOARDING MUSIC (BGM)............................................................................................................... 2-19 DVD PLAYER..................................................................................................................................... 2-19 DECOMPRESSION............................................................................................................................. 2-20 IN-SEAT POWER................................................................................................................................ 2-20 SYSTEM HEARTBEAT MESSAGE .................................................................................................. 2-21 CONTENT MANAGEMENT AND SOFTWARE LOAD.................................................................. 2-23 BUILT-IN TESTS ................................................................................................................................ 2-25

LRU DESCRIPTIONS .................................................................................................................................. 3-1


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A321/A319/A320 i3000 Training Manual 3.1 HEAD-END COMPONENTS ............................................................................................................... 3-1 3.1.1 Inflight Entertainment Center (IFEC)................................................................................................ 3-1 3.1.2 Audio Video Controller (AVC)........................................................................................................... 3-3 3.1.3 Digital Server Unit, Analog Modulated 6 Video / 12 Audio (DSU AM6-12)..................................... 3-8 3.1.4 Video Control Center (VCC) ........................................................................................................... 3-13 3.1.5 interactive Cabin Management Terminal (iCMT) ........................................................................... 3-14 3.1.6 Seat Electronics Box (SEB).............................................................................................................. 3-16 3.1.7 DVD Player ..................................................................................................................................... 3-17 3.2 CABIN DISTRIBUTION..................................................................................................................... 3-18 3.2.1 Area Distribution Box (ADB)........................................................................................................... 3-19 3.2.2 Master Control Unit (MCU) ............................................................................................................ 3-23 3.2.3 Power Wall Disconnect Box (PWDB).............................................................................................. 3-27 3.3 SEAT GROUP COMPONENTS .......................................................................................................... 3-28 3.3.1 Seat Electronics Box (SEB).............................................................................................................. 3-28 3.3.2 Smart Video Display Unit (SVDU) .................................................................................................. 3-33 3.3.3 Digital Passenger Control Unit (DPCU)......................................................................................... 3-37 3.3.4 Intergrated Noise Cancelling Audio Jack........................................................................................ 3-38 3.3.5 In-Seat Power Converter (ISPC) ..................................................................................................... 3-39 3.3.6 Alternating Current Outlet Unit (ACOU) ........................................................................................ 3-40 4

SEAT INTERCONNECT DIAGRAMS....................................................................................................... 4-1 4.1 4.2

5

MAINTENANCE FUNCTIONS................................................................................................................... 5-1 5.1 5.2 5.2.1 5.2.2 5.3 5.4 5.5 5.5.1 5.5.2 5.5.3 5.5.4 5.6 5.6.1 5.6.2 5.6.3 5.7 5.8

6

SEAT INTERCONNECT DIAGRAMS – BUSINESS CLASS ............................................................ 4-2 SEAT INTERCONNECT DIAGRAMS – ECONOMY CLASS ........................................................... 4-5 PORTABLE DATA LOADER (PDL) SETUP ...................................................................................... 5-1 SOFTWARE DOWNLOADING ........................................................................................................... 5-2 Software Download Procedure – PHASE 1....................................................................................... 5-2 Software Download Procedure – PHASE 2...................................................................................... 5-5 CONFIGURATION CHECK................................................................................................................. 5-9 IP SEQUENCE..................................................................................................................................... 5-10 CONTENT MANAGEMENT.............................................................................................................. 5-12 System Content Loading Procedures ............................................................................................... 5-13 Content Menu Screens ..................................................................................................................... 5-14 Detailed Information on Loading .................................................................................................... 5-17 Content Load Control Menu ............................................................................................................ 5-20 TROUBLESHOOTING TOOLS.......................................................................................................... 5-22 Static Tests ....................................................................................................................................... 5-22 BITE Function ................................................................................................................................. 5-23 SW Configuration Consistency Verification .................................................................................... 5-23 METHODOLOGY ............................................................................................................................... 5-23 SYSTEM CHECKS.............................................................................................................................. 5-23

TROUBLESHOOTING ................................................................................................................................ 6-1 6.1 6.2 6.3 6.4 6.4.1 6.4.2

GENERAL ............................................................................................................................................. 6-1 TROUBLESHOOTING PHILOSOPHY................................................................................................ 6-1 CABIN CREW DISCREPANCY........................................................................................................... 6-1 BASIC CHECKS.................................................................................................................................... 6-2 Software download ............................................................................................................................ 6-2 Configuration Check.......................................................................................................................... 6-2



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NACIL A321/A319/A320 i3000 Training Manual 6.4.3 6.5 6.6 6.7 6.7.1 6.7.2 6.7.3 6.8 6.8.1 6.8.2 6.9 6.10 6.11 7

APPENDIX A321 ........................................................................................................................................... 7-1 7.1 7.2 7.3 7.4 7.5 7.5.1 7.5.2 7.5.3 7.5.4 7.5.5 7.6 7.7

8

IP Sequence ....................................................................................................................................... 6-3 TROUBLESHOOTING TOOLS............................................................................................................ 6-3 METHODOLOGY OF TROUBLESHOOTING ................................................................................... 6-4 SYSTEM CHECKS................................................................................................................................ 6-5 Level 1 Courtesy Check ..................................................................................................................... 6-5 Level 2 Courtesy Check ..................................................................................................................... 6-5 Level 3 Courtesy Check ..................................................................................................................... 6-6 TROUBLESHOOTING AUDIO DISTRIBUTION PATHS ................................................................. 6-6 Distribution of Audio Entertainment ................................................................................................. 6-8 Distribution of Video Audio ............................................................................................................... 6-9 DISTRIBUTION OF BOARDING MUSIC AND PRE-RECORDED ANNOUNCEMENTS ........... 6-14 PRACTICAL TIPS............................................................................................................................... 6-16 TROUBLESHOOTING GUIDE .......................................................................................................... 6-18 DATA (SEAT-TO-SEAT CABLING)................................................................................................... 7-1 DATA (ADB 1 TO SEAT GROUPS) .................................................................................................... 7-2 DATA (ADB 2 TO SEAT GROUPS) .................................................................................................... 7-3 DATA (ADB TO WDB/SEB/SVDU/DPCU) ........................................................................................ 7-4 DATA AND RF (SEAT CONFIGURATION NOTES)....................................................................... 7-10 Business-Class First Two Rows (Rows 1 and 2).............................................................................. 7-10 Business Class Last Two Rows (Rows 4 and 5) ............................................................................... 7-11 Economy Class First Three Row (Rows 6, 7 and 8) ........................................................................ 7-12 Economy Class Rows 19, 20 and 21 ................................................................................................ 7-14 Economy Class Last Two Rows (Rows 30 and 31) .......................................................................... 7-16 POWER (SEAT-TO-SEAT CABLING) .............................................................................................. 7-17 POWER (MCUS TO SEAT GROUPS) ............................................................................................... 7-18

APPENDIX A319 ........................................................................................................................................... 8-1 8.1 8.2 8.3 8.4 8.5 8.5.1 8.5.2 8.5.3 8.6 8.7

DATA (SEAT-TO-SEAT CABLING)................................................................................................... 8-1 DATA (ADB 1 TO SEAT GROUPS) .................................................................................................... 8-2 DATA (ADB 2 TO SEAT GROUPS) .................................................................................................... 8-3 DATA (ADB TO WDB/SEB/SVDU/DPCU) ........................................................................................ 8-4 DATA AND RF (SEAT CONFIGURATION NOTES)......................................................................... 8-8 Business Class (Rows 1 and 2) .......................................................................................................... 8-8 Economy Class First Two Rows (Rows 3 and 4) ............................................................................... 8-9 Economy Class Last Two Rows (Rows 20 and 21) .......................................................................... 8-10 POWER (SEAT-TO-SEAT CABLING) .............................................................................................. 8-11 POWER (MCUS TO SEAT GROUPS) ............................................................................................... 8-12



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NACIL A321/A320/A319 i3000 Training Manual 1 1.1

SYSTEM OVERVIEW GENERAL OVERVIEW

The Thales i3000 Inflight Entertainment (IFE) system provides passengers with a state-of-the-art media experience. Each passenger has individual access to the media via touch-screen or passenger control unit installed at each passenger position. The IFE presents a wide variety of digitally-stored media such as movies and music, available to be enjoyed by the passengers over a broadcast network. The system also provides navigation information through moving map technology. NACIL(I) will be installing the Thales i3000 full ship in-seat video system on twenty (20) A321, eighteen (18) A319 and four (4) A320 two-class aircrafts. All A321 and A319 aircrafts will deliver from Airbus in Hamburg, Germany. All A320 aircrafts will deliver from Toulouse, France. The deliveries for A321 aircrafts commence in June, 2007. The delivery for A319 aircrafts begins in October, 2007, and the delivery for A320 aircrafts will begin in February of 2010. This training manual uses the A321 data as the representative IFE installation for the NACIL(I) fleet of narrow-body Airbus aircraft. Wherever possible, A319 and A320 data will be used as well. The i3000 system will be installed per the following functions: For Business Class (B/C) zone passengers: Broadcast audio & video (RF distribution) • Thales In-Route Moving Map™ (PFIS) via in-seat/wall-mount monitors • Safety/company video announcements via in-seat/wall-mount monitors • In-seat/wall-mount video for broadcasted movies/audio • DSU AM6-12 movies • DVD player movies 10.6” individual Smart Video Display Units (SVDU), touch-screen seat-back or wall-mounted Digital Passenger Control Units (DPCU) with volume, channel and mode control In-seat integrated noise canceling audio jacks In-seat laptop/PED power (provided by KID-Systeme) For Economy Class (Y/C) zone passengers: Broadcast audio & video (RF distribution) • Thales In-Route Moving Map™ (PFIS) via in-seat, wall-mount or arm-mount (A321 only) monitors • Safety/company video announcements via in-seat, wall-mount or arm-mount (A321 only) monitors • In-seat, wall-mount or arm-mount (A321 only) video for broadcasted movies/audio • DSU AM6-12 movies • DVD player movies 8.9” individual SVDU, touch-screen, in-seat, wall-mounted or arm-mounted (A321 only) DPCU with volume, channel and mode control The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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In-seat audio jacks

The system users are:

Flight attendants or crew members who configure and maintain proper system operations The passengers who use the system entertainment capabilities The maintenance personnel who configure, troubleshoot, and return the system to service at the gate or during overnight maintenance activities

The NACIL(I) aircraft include two classes of service; Business Class and Economy Class. The i3000 System is installed in both classes. The flight attendant and maintenance interface will be accomplished via an Interactive Cabin Management Terminal (iCMT) which is located and easily accessed in the aircraft cabin. All entertainment media content is uploaded to a Digital Server Unit which is located in the aircraft’s Electronics Bay (EBAY). The Server Unit has 180GB storage capacity. An additional function allows NACIL(I) to play pre-recorded data in the form of video, audio, messages, and announcements via DVD player as a daily update or backup for the entertainment data stored on the IFE system. In-seat video will be displayed on 10.6 inch SVDUs (Smart Video Display Units) in Business Class and 8.9 inch SVDUs in Economy class. These units will be mounted on articulating arms, the back of the next forward seat headrest, or on the bulkhead wall, depending on the installation configuration. Audio is available at each passenger seat through a single pin audio jack for each passenger’s headset. All video and audio selections are initiated with a DPCU (Digital Passenger Control Unit) or the touchscreen SVDU at each seat. The NACIL i3000 system provides the following functionalities:

Interactive Cabin Management Terminal (iCMT) Control In-seat Broadcast Audio and Video Moving Map Public Address (PA) and Video Address (VA) Pre-Recorded Announcement Message (PRAM)/Boarding Music (BGM), (Content stored in DSU AM6-12 and controlled by the iCMT) DVD player control from the iCMT and the DVD player In-seat power for personal electronic devices (Business Class only; provided by KID systems) System control • Response to decompression Maintenance Functions • Content loading • Software download



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NACIL A321/A320/A319 i3000 Training Manual • •

IP sequencing Config Check

The NACIL(I) IFE i3000 system is made up of individual Line Replaceable Units (LRUs) divided into three separate groups; the Head-end, the Cabin Distribution, and the Seat-end components. All of these components are included in the Parts Lists referenced in the pages that follow. The Head-end consists of the components responsible for operation and control of the data flow to the cabin units. The Cabin Distribution units distribute the data throughout cabin to each seat group. The Seat-end components provide functions necessary to decode and demodulate the signals from the Headend, and allow each passenger to control the entertainment services available at each seat.

1.2

SERVICES DISTRIBUTION

The general distribution of Thales IFE entertainment services is configured in both serial and parallel architecture. The Head-end contains the components necessary to control the system, store the content files for entertainment, and communicate with the aircraft equipment. The Head-end components are the AVC, the DSU AM6-12, and the iCMT. The 3rd party equipment includes the DVD Player. The non-IFE aircraft equipment consists of CIDS (Cabin Intercommunication Director System) and the FAP (Flight Attendant Panel). The Cabin Distribution function consists of Distribution Network Modules that connect the Head-end processing units to the Seat-end clients. In the i3000 system the ADBs (Area Distribution Boxes) supply the communication route for entertainment services and operational data to be transmitted throughout the system for BITE. The MCUs (Master Control Units) are the Power Control Modules that distribute aircraft power to the seat-end clients. The Seat-end consists of the clients that receive the entertainment services or IFE-related inputs from the distribution network. These include the SEBs (Seat Electronics Boxes), the SVDUs (Smart Video Display Units), and the passenger control units.



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Figure 1-1 Main Group Division



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NACIL A321/A320/A319 i3000 Training Manual MAIN GROUP DIVISION COMPONENTS



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NACIL A321/A320/A319 i3000 Training Manual 1.3

NACIL(I) A321 LAYOUT OF PASSENGER ACCOMMODATIONS (LOPA)

Economy Class arrangement

First Class arrangement



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NACIL A319 LOPA





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NACIL A320 LOPA





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SYSTEM OVERVIEW

The following section contains descriptions of how the various Thales i3000 LRU’s interact to provide each of the major system functions. It also identifies the LRU that is primarily responsible for a function as well as the inter-LRU signal flow required for successful execution of the function

1.6.1

System Control / Operator Interface

The operator interface and system control web pages reside on either the DSU AM6-12 or the AVC, but the operator accesses them via the Interactive Cabin Management Terminal (iCMT). Acting similar to a PC with a Linux browser, the iCMT retrieves web pages from either the DSU AM6-12 or AVC, which are acting as intranet servers. The active server generates the menu screens on the iCMT. Pressing graphical buttons or scroll bars on the iCMT touch-screen controls system functions. These touch-screen presses are sent via Ethernet to the active server (DSU AM6-12 or AVC) which reacts by sending appropriate screen changes to the iCMT and by initiating any appropriate system functions. The LRU controlling a particular function is the active server for the menu screens associated with that function. Most functions are resident on the DSU AM6-12 (movies, boarding music, etc) and the DSU AM6-12 is the server for those functions. But some functions, such DVD control reside on the AVC. The iCMT automatically “surfs” to the appropriate server as necessary, to provide menu functionality.

1.6.2

In-Seat Broadcast Audio and Video

The Thales i3000 system supports six (6) channels of audio/video entertainment and twelve (12) channels of stereo audio-only. Five of the audio/video channels are hosted on the DSU AM6-12 as are all of the audio channels. One audio/video channel is sourced by the DVD Player via the AVC. The first four audio/video channels each have associated primary and secondary stereo audio, with the primary language on the odd PCU channels and the secondary on the even channels. The audio/video entertainment content files are stored on the hard disk drive of the DSU AM6-12. When playing files, the DSU AM612 reads and decodes the data, generates audio and video signals that are modulated onto one of the CATV channels of an RF carrier which is sent through the AVC to the ADB’s (Area Distribution Boxes). The ADB’s split the RF signal and route it to the WDB’s (Wall Disconnect Boxes) for distribution to strings of SEB’s (Seat Electronics Boxes). Each SEB tunes to the selected audio or video channel and demodulates the signal for each passenger in its seat group. The video signals are then The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL A321/A320/A319 i3000 Training Manual converted to NTSC video and sent to the SVDU’s and the audio signals are presented to the Remote Audio Jack, which provides audio to the passenger via headphones. Audio volume up/down button presses are sent from the DPCU to the SEB, where the output volume level is adjusted.

1.6.3

Video Announcement (VA)

The VA function resides on the AVC and is initiated by the operator via the iCMT VA Control menu. The AVC sends an Ethernet VA Command to the other LRU’s in the IFE system, placing them in VA Mode. The DSU AM6-12 is commanded to playback the appropriate audio/video. The AVC also demodulates the audio and routes it to the aircraft CIDS system for distribution to the cabin speakers.

1.6.4

Passenger Address All-Call (PA ALL)

The AVC receives the PA ALL keyline and PA Audio from the aircraft CIDS system and overlays a 19KHz tone onto the PA Audio signal on the lowest FM Audio channel (88.1 MHz). This channel is modulated onto the RF carrier for distribution to the seats via the ADB. The SEB hardware has a separate FM tuner that specifically monitors the 88.1 MHz channel, looking for the 19KHz tone. When it detects the tone, indicating a PA ALL event, it forces the SEB to route the PA Audio to the headphones. At the same time the AVC sends an Ethernet PA ALL status to the other LRU’s via the Heartbeat Message, placing them in PA Mode. When the DSU AM6-12 enters PA Mode, it pauses all audio and video output channels. The Heartbeat Message also directs the SEB’s to display the “Passenger Address in Progress” screen on the SVDU’s, inhibit channel surfing and display “PA” on the DPCU LCD’s.

1.6.5

Area Passenger Address (Area PA)

The AVC supports up to six Area PA Keyline inputs. When one of these keylines is activated, the Area PA audio will be modulated onto one of six FM Audio channels. The Heartbeat Message from the AVC indicates which Area PA Keyline has been activated and which FM channel is carrying the audio for that keyline. Each SEB refers to its PAVA Map to determine if it is in the zone associated with the Area PA. If it is, it tunes to the appropriate FM audio channel and displays the “Passenger Announcement in Progress” screen on the SVDU’s. Otherwise, it disregards the PA and continues in its current mode.

1.6.6

Pre-Recorded Announcement Machine (PRAM)

The PRAM audio files reside on the DSU AM6-12 hard disk drive. The only pre-recorded messages utilized on the NACIL(I) system are the Decompression, the No Smoking and the Fasten Seat Belt messages. The Decompression message is automatically played by the The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL A321/A320/A319 i3000 Training Manual DSU AM6-12 when it enters “Decompression Mode”, which occurs when the Decompression keyline is activated. The No Smoking and Fasten Seat Belt messages are likewise played from the DSU AM6-12 when their respective keylines are activated by the cockpit crew. The messages are sent from the DSU AM6-12 as base-band audio to the aircraft audio system. The signal is returned as a PA to the AVC, which modulates it onto the CATV carrier for distribution to the seats.

1.6.7

Boarding Music (BGM)

Boarding Music is available through the IFE system. When accessed through the iCMT screen, the DSU AM6-12 provides the Boarding Music function and, has four programs of Boarding Music available, but only one can be played at a time. The operator selects a particular program via the iCMT Boarding Music Control menu from the DSU AM6-12. The boarding music is sent from the DSU AM6-12 as baseband audio to the aircraft CIDS system for distribution to cabin speakers and is not modulated for distribution to the seats.

1.6.8

Moving Map (MMAP)

The Moving Map application displays flight status information over a broadcast channel, which can be selected by the passengers for in-seat viewing. The application displays a graphical representation of the aircraft position over the surface of the earth, textural navigational data and custom graphic images. The Moving Map cycles through displays of maps at five different scales while showing the aircraft flight path and current position. At the end of the map cycle, a custom graphic is displayed and then the map cycle repeats. The Moving Map function resides on one of the Video Clients in the DSU AM6-12. The AVC receives aircraft positioning, altitude and speed data via an ARINC-429 link to the aircraft avionics. The AVC then feeds the data to the DSU AM6-12, which updates the map. The operator enables the Moving Map option via the iCMT. The Moving Map is also available to the seats in conjunction with the Broadcast Audio function in the same manner as other entertainment files.

1.6.9

In-Seat Laptop Power

The Thales i3000 system makes 100 VAC, 60-Hz power available to outlets in each of the Business Class seats for the purpose of powering laptop computers during the flight. The MCU takes the aircraft 3-phase 400 Hz power and distributes it, via the Power Wall Disconnect Boxes, to each columns of SEB’s. The SEB at the head of a column receives the 3-phase power on J1 and routes it directly to the output connector J2 and J3. The next SEB in line is connected to J2 via a cable that has a phase rotation built in, such that each SEB in the string will be shifted one phase from the previous unit. Connector J3 is used to



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NACIL A321/A320/A319 i3000 Training Manual power the ISPC, which is manufactured by KID System, converts the power to single-phase 110 VAC, 60 Hz, which is in turn routed to the AC Outlet in the armrest of the seat. The MCU monitors the power consumed by each of the columns, and according to the settings in the Configuration Module or the GFI, will shut down or limit one or more columns, if the current parameters are exceeded (see the MCU section for more details). Likewise, ISPC monitors it’s outputs to each seat in its seat group and may shut down one or all of its outputs if the safety criteria are not met. The ISPC can also be directed by the MCU to shut down outputs or not allow new users. The ACOU also has built-in safety features designed to prevent shock due to misuse of the outlet.

1.6.10 Maintenance Functions The operator initiates most Thales i3000 System maintenance functions, such as software download and IP sequencing, via the iCMT Maintenance menus. The Software Download function actually resides in the DSU AM6-12 and the IP Sequencing function resides in the AVC. The Content Data loading is discussed in the Content Management section.

1.6.11 Content Management Entertainment Audio/Video Content files such as movies or music are downloaded to the DSU AM6-12 hard disk drive from a laptop PC configured as a Portable Data Loader (PDL). The PDL is connected to the system via the Data loader Port in the VCC and communicates with the IFE system via a 100Base-T Ethernet link. The GUI for the Content Management functions resides on the PDL and controls the system inventory and data transfer functions. The System Inventory is managed according to a System Inventory File (SIF) that contains a listing of all the content files (audio / video) that should be available on the system. It compares the SIF with the content files loaded on the PDL and the DSU AM6-12. Any files listed in the SIF, but missing from the DSU AM6-12 are highlighted in red and will be copied from the PDL to the DSU AM6-12 hard drive. Audio and Video content files are sent from the Thales Content Management Facility in Irvine to the airline as encrypted data on a removable Hard Disk Drive. The airline installs the HDD in the PDL and decrypts the data files. A two-hour movie takes about 20 minutes to decrypt. Once the content is decrypted, the PDL is ready to take to the aircraft to load the data. The PDL must be kept in a secure location to prevent video piracy. The HDD containing the previous contents must be erased prior to shipment back to Irvine. The entire content inventory need not be loaded onto the aircraft at one time. If time does not allow all the files to be transferred, a subset of the files can be loaded at each session until the content is complete. The PDL will recognize what has been loaded previously and will select only the missing files for download.



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NACIL A321/A320/A319 i3000 Training Manual 1.6.12 Acronyms & Abbreviations -AA A/C or AC A/C ACOU ADB ADC AFT AJ ARINC Assy ATSU Aux AVC AVOD BGM BIT BITE Ch. or CH CIDS CMC CMT CRS CTS dB DDP DSU DSU-D2 E-Bay ELA eCTU FAA FAP FAR FDB

Amperes (unit of electrical current) Alternating Current Aircraft Alternating Current Outlet Unit Area Distribution Box Air Data Computer After (rearward) direction or end of the aircraft Audio Jack Aeronautical Radio, Inc. Assembly Air Traffic Service Unit Auxiliary Audio Video Controller Audio/Video On Demand -BBoarding Music (see also BMM) Built-In Test(ing) Built-In Test Equipment -CChannel Cabin Intercommunication Data System Central(ized) Maintenance Computer Cabin (Central) Management Terminal Customer Requirements Specification Component Technical Specification -DDecibel Declaration of Design Performances Digital Server Unit Digital Server Unit, Digital output -EElectronics Bay Electrical Load Analysis Electronic CTU (see also CTU) -FFederal Aviation Administration Flight Attendant Panel Federal Aviation Regulation Floor Disconnect (Distribution) Box



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NACIL A321/A320/A319 i3000 Training Manual FM FMC FMS FWD

Frequency Modulated Flight Management Computer Flight Management System Forward

GFI GIF GMT GND /gnd GUI

Ground Fault Interrupt Graphic Interchange Format Greenwich Mean Time (UTC) Ground Graphic User Interface

-G-

Hz iCMT IFE IFEC IFES INRAJ IP ISPC ISPS JAA JAMCO JAR JPEG kHz KID LCS LED LOPA LRU MB MCU Mbps MHz MPEG msec mV N/A

-Hhertz (cycle per second) (unit of frequency) -IInteractive Cabin Management Terminal Inflight Entertainment (see also PES) Inflight Entertainment Cabinet Inflight Entertainment System Integrated Noise Reduction Audio Jack Internet Protocol In-Seat Power Converter In-Seat Power Supply (System) -JJoint Aviation Authorities – European equivalent of the US FAA JAMCO America, Inc. Joined Airworthiness Requirements Joint Photographic Experts Group -KKilohertz (1000 hertz) OEM -LLandscape Camera System Light Emitting Diode Layout Of Passenger Accommodations (or Arrangements) Line Replaceable Unit -MMegabyte (1 million bytes) Master Control Unit Million bits per second Megahertz (1 million hertz) Moving Pictures Expert Group millisecond (10-3 or 1/1,000 second) Millivolt -NNot applicable (also NA or n/a)



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NACIL A321/A320/A319 i3000 Training Manual NRM NTSC PA PA All PA Area PAX PDL PED PFIS PRAM PWDB RF RJ-45 Rx s S/N SDU SEB Shd SNR SRS SVDU TBC TBD TDPCU TIFS TU TV Tx USB UTC V VA VCC VDU VOD

Noise Reduction Module National Television System Committee -PPassenger Announce(ment), or Passenger (or Public) Address Passenger Announcements simultaneously broadcast throughout the entire cabin space and lavatories. Passenger Announcements directly to one or more selected cabin areas. Passenger Portable Data Loader Portable (or Passenger) Electronic Device Passenger Flight Information System Pre-Recorded Announcement Machine Power Wall Disconnect (Distribution) Box -RRadio Frequency Ethernet connectors (100 Mbps tfr rate) Receive -SSecond(s) Serial Number Satellite Data Unit Seat Electronics Box Shield Signal to Noise Ratio (see also S/N) System Requirement(s) Specification(s) Smart Video Display Unit -TTo Be Confirmed / To Be Completed To Be Determined Tethered Digital Passenger Control Unit Thales Avionics Inflight Systems Tapping Unit Television Transmit -UUniversal Serial Bus -12Mbps tfr rate. Coordinated Universal Time (GMT) -Vvolt Video Announcement, video display announcement (with or without audio) directed to all or selected video screens (see also PA - Passenger Announcement). Video Control Center Video Display Unit Video On Demand



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Apr 2008

NACIL A321/A320/A319 i3000 Training Manual VOL VTR

Volume Video Tape Reproducer

W WDB

Watts or Width Wall Disconnect Box

-W-



Page 1-16

Apr 2008

NACIL A321/A320/A319 i3000 Training Manual 2 2.1

SYSTEM DESCRIPTION SYSTEM EQUIPMENT

Part Number 177716-103 177729-106 177733-102 177900-103 177922-103 177745-106 177792-803 318073-02 177745-106 179036-202/179036203* 180199-203/180199208 177807-F01/177807G01* 177807-F02/177807G02* 178921-102 177745-106 179290-202/179290209* 178850-204/178850212* 178850-205/178850213* 177807-F01/177807G01* 177807-F02/177807G02* 177355-01

Description LRUs & Cabin Distribution Audio Video Controller (AVC) Area Distribution Box (ADB) Wall Disconnect Box (WDB) Digital Server Unit, DSU AM6-12 MCU 3 with Ethernet VCC Seat Electronic Box (SEB) iCMT DVD Player Business Class (B/C) SEB 10.6-inch Seatback SVDU 10.6-inch Wall-mount SVDU DPCU, Side-mount (LH) DPCU, Side-mount (RH) Integrated Noise Reduction Audio Jack Economy Class (Y/C) SEB 8.9-inch Seatback SVDU 8.9-inch Arm-mount SVDU 8.9-inch Wall-mount SVDU DPCU, Side-mount (LH) DPCU, Side-mount (RH) Audio Jack

A321

A319

A320 TBD Linefit

Linefit

Linefit

1 2 8 1 2 1 1 1 1

1 2 8 1 2 1 1 1 1

1 2 8 1 2 1 1 1 1

12

6

12

16

4

16

4

4

4

10

4

10

10

4

10

20

8

20

58

40

42

142

108

114

4

0

0

6

6

6

76

57

60

76

57

60

152

114

120



Page 2-1

Apr 2008

NACIL A321/A320/A319 i3000 Training Manual There are basically three network interfaces in operation when the IFE system is operational; Electrical Power, Ethernet, and RF (Radio Frequency). USB

VCC

DL

USB

i-CMT

A/C Power

DL

VCC SEB

AJ

MCU 1

MCU 2

RS-485

DVD

PED in use light

429 bus CSS/PA AMP discretes

ACOU

ISPC

AVC

SEB

WDB

ADB1

SVDU

i-3000 Typical AJ/ HEADSET

AJ

WDB

ADB2

SEB

USB

DP CU

E-Bay PFIS Audio Video

SEB

DSU AM6-12

Economy Class SEB

100Mbps / Data

AJ

USB

AJ/ HEADSET

DP CU

SEB

Business Class

SVDU

i-3000 Typical

SEB

SEB

Power

RF

Baseband

Figure 2-1 NACIL i3000 System Block Diagram Electrical power is supplied by the aircraft for all IFE operations. Power for components located in the seat groups is also controlled by MCUs (Master Control Units) that monitor and regulate the power available to each seat group. An Ethernet network supplies 100 Mbps (Megabits per second) data transmission capabilities for entertainment services and IFE system operation. On-demand entertainment data originates at the DSU AM6-12 and is routed through ADBs (Area Distribution Boxes) for distribution to the seat groups. Operational system data transmits at 100Mbps throughout the system for integral checks and BITE functions. An RF (Radio Frequency) network supplies broadcast audio and video from the DSU AM 6-12 via coaxial cable through the ADBs to the seat groups; similar to a cable television arrangement.



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Apr 2008

NACILA321/A320/A319 i3000 Training Manual Some audio files are stored on the IFE system or a DVD Player and delivered to the aircraft as base-band for distribution throughout the cabin as a Passenger Announcement (PA) or Video Announcement (VA).

2.1.1

Parts List

The following parts list is a representation of the primary parts installed in the Thales i3000 IFE system. Refer to the Illustrated Parts Catalog issued by Airbus for the line-fit installation. HEAD-END & CABIN DISTRIBUTION Part Number 177716-103 177729-106 177733-102 177900-103 177922-103 177923-301 180850-101 177745-106 177792-803 318073-02 Part Number 177745-106 179036-202 180199-203 177807-F01 177807-F02 178921-102 Part Number 177745-106 179290-202 178850-204 178850-205 177807-F01 177807-F02 177355-01

Description Audio Video Controller (AVC) Area Distribution Box (ADB) Wall Disconnect Box (WDB) Digital Server Unit, DSU AM6-12 MCU 3 w/ Ethernet Programming Module VCC SEB i-Series iCMT DVD Player BUSINESS CLASS Description SEB i-Series 10.6-inch Seatback SVDU 10.6-inch Wall-mount SVDU DPCU, Side-mount (LH) DPCU, Side-mount (RH) Integrated Noise Reduction Audio Jack ECONOMY CLASS Description SEB i-Series 8.9-inch Seatback SVDU 8.9-inch Arm-mount SVDU 8.9-inch Wall-mount SVDU DPCU, Side-mount (LH) DPCU, Side-mount (RH) Audio Jack

A321 1 2 8 1 2 2 1 1 1 1

A319 1 2 8 1 2 2 1 1 1 1

A320 1 2 8 1 2 2 1 1 1 1

A321 12 16 4 10 10 20

A319 6 4 4 4 4 8

A320 12 16 4 10 10 20

A321 58 142 4 6 76 76 152

A319 40 108 0 6 57 57 114

A320 42 114 0 6 60 60 120



Page 2-3

Apr 2008

NACIL A321/A320/A319 i3000 Training Manual 2.1.2

Parts Locations

Due to the fact that the NACIL A321/320/319 are Airbus linefits, the actual location of the LRUs will be determined by Airbus. Thales will be providing the LRUs as well as racks and wiring where necessary and agreed upon by Airbus, NACIL, and Thales Avionics. The components installed, and the related locations are as follows: VCC (Video Control Center): Interactive Cabin Management Terminal (iCMT) 10.4-inch SVDU Seat Electronics Box (SEB) RJ-45 Data loading ports Two type-A USB ports DVD Player Smoke detector Cable assemblies Electronics Bay (Ebay): Audio Video Controller (AVC) Digital Server Unit (DSU AM6-12) Cable assemblies Cabin Distribution: Wall Distribution Boxes (WDB) Master Control Units (MCU) Cabling Business Class: 10.6-inch seat-back or bulkhead mounted SVDU Integrated Noise Canceling Remote Audio Jacks Seat Electronics Boxes (SEB) Digital Passenger Control Units (DPCU) A/C Outlet Units (ACOU) In-Seat Power Converters (ISPC) PED (Personal Electronic Device) In-use lights Economy Class: 8.9-inch seat-back, in-arm, or bulkhead-mounted SVDUs Single pin remote Audio Jacks Seat Electronics Boxes (SEB) Digital Passenger Control Units (DPCU) 2.2

SUBSYSTEMS

The following functions are subsystems of the TopSeries i3000 system. The table below illustrates the subsystems as services that are available throughout the aircraft. All entertainment services are available in Business Class (B/C) and Economy class (E/C). The Passenger Flight Information System (PFIS) is a The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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Apr 2008


E/C

In-seat Audio broadcast entertainment

X

X

In-seat Video broadcast entertainment

X

X

Passenger Flight Information System (Broadcast Moving Map)

X

X

In-seat power

X

Passenger Announcement (Direct PA, PA AREA)

X

X

Video Announcement

X

X

Service Designation

VCC

B/C

broadcast function that allows passengers to view the aircraft position on a Moving Map while in the broadcast modes. The in-seat power function supplied by KID System is available only to the First Class (B/C) passengers.

Health status screens

X

Static Tests

X

DVD Player

X

The Passenger Announcement (PA) and Video Announcement (VA) are functions that can override the entertainment services for important announcements such as safety briefings, or convenience messages such as arrival information. All of the maintenance and interactive functions that pertain to operation and maintenance are available through Interactive Cabin Management Terminal (iCMT) at the Video Control Center (VCC). The DVD Player may be used for pre-recorded announcements, pre-recorded audio/video broadcast, or as a backup to the IFE system.

2.3

POWER-UP

Upon powering-up, each unit of the TopSeries i3000 system initiates a self test routine that: Checks the integrity of the unit itself Determines its MAC and IP address Checks for software configuration conflicts Launches the continuous monitoring processes Checks the equipment interfaces Collects the self test results of all units Keeps all results of the self tests until requested by other units Memorizes failures in non-volatile memory.



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Apr 2008

NACIL A321/A320/A319 i3000 Training Manual LRU or Parameter

Typical boot up time

States during boot up

Initial parameters in IDLE mode

SVDU

6 minutes

Screen stays black

SVDU remains black in IDLE mode (backlight OFF)

N/A

1st state: “00” on the LCD 2nd state: “   ” on the LCD 3rd state: Idle Mode

The DPCU idle mode shall be MMAP channel 1

Screen stays black

The screen shall display the initial/welcome screen. All entertainment functions shall be OFF.

DPCU

MMAP

6 minutes (including head-end boot time) 6 minutes

SEB

2 minutes

iCMT

N/A N/A

N/A The default audio level for PA/VA shall be the PAVADEF.PA_VA_LOW database parameter set to SYSDEF.DEFAULTAUDIOVOLUMEATSEAT value = 18

The table above shows the relationship between the components and the time allowance for the boot-up process. As an example, the iCMT requires approximately 6 minutes to properly boot-up. During that time the screen stays black. After boot-up, the NACIL(I) welcome screen is displayed (Idle mode). All entertainment services to the passengers default to the OFF condition until the crew member activates the services through the iCMT. It is important to allow all LRUs to boot-up completely before accessing the IFE services. Premature interaction prior to boot-up may result in unsatisfactory operation of the services to individual seats, seat groups, and/or all passengers. When condition occurs, a complete system reset is necessary. It is highly

recommended that the operator wait at least 10 minutes before enabling entertainment services. 2.4

INTERACTIVE CABIN MANAGEMENT TERMINAL (ICMT)

The operator interface and system control web pages reside on the DSU AM6-12 or the AVC. The operator accesses the screen via the iCMT located at the VCC. The DSU AM6-12 and the AVC act as intranet server host to the iCMT client, which displays the retrieved web page from the active server. Pressing graphical buttons or scroll bars on the iCMT touch-screen controls system functions. These inputs on the touch-screen are sent via Ethernet to the active server, which reacts by sending appropriate screen changes to the iCMT and by initiating any appropriate system functions.



Page 2-6

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual The LRU controlling a particular function is the active server for the menu screens associated with that function. Most functions are resident on the DSU AM6-12 (movies, boarding music, etc) and the DSU AM6-12 is the server for those functions. But some functions, such as Video Announcement reside on the AVC, which is the server for those screens. The iCMT automatically “surfs” to the appropriate server to provide menu functionality.

USB

VCC

USB

i-CMT

SEB

DVD Player

AVC

ADB1

To other Head-end LRUs

E-Bay

To other cabin LRUs

100Mbps / Data USB

Figure 2-2 iCMT Operation Functions provided on the iCMT include the ON/OFF control, selection of services, System Status, Video Announcements, Seat Control, and maintenance functions. Entertainment services are not available when the maintenance functions are active. The iCMT has a similar visual hierarchical menu structure as that offered to passengers at the SVDUs. It offers system interface via a touch-screen and allows the management of media content provided to all seats or group of seats. The terminal is designed to also permit rapid program updating and maintenance support with RJ-45 Ethernet Ports (not shown) and USB Ports.



Page 2-7

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual

Figure 2-3 Interactive Cabin Management Terminal

2.4.1

RJ45 Ethernet Ports

Two RJ45 Ethernet ports are available for large content uploads. The ports are at the VCC. These ports accommodate an external device, such as a Portable Data Loader or a Laptop Computer to be connected to the IFE system. It is possible to pre-load date sensitive programs that automatically activate when the required date is reached. Additionally, the RJ45 port may also be used to upload operational software and/or download maintenance reports and data files.

2.5

USB PORTS

Two USB ports are available for Type 2 USB inputs. The USB ports can be used to upload smaller data/content files, and download maintenance data such as BITE reports.



Page 2-8

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 2.6

CABIN CREW EXPERIENCE

The Welcome page noted on the right is used by the operator to start/stop entertainment services and perform maintenance diagnostic checks of the IFE system. The Entertainment or Maintenance functions are available by pushing the related button on the iCMT screen. To activate the entertainment services, press the Entertainment button on the Welcome page.

The Services Control screen is then displayed. This screen contains the functionality for entertainment services on the aircraft. Each button provides the crew member with the ability to enable or disable individual services.

The Content Control window enables the cabin crew to choose from the two predefined packages, “Inbound” and “Outbound”, as the source for entertainment services.

Figure 2-4 Content Control window



Page 2-9

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual When a menu selection button is pressed (Services, Sys Status, VA, Seat Control or Boarding Music) it will illuminate to indicate it has been activated. When a service is enabled, the button will illuminate green to show that it has been activated. These operational functions will be demonstrated in the Cabin Crew CBT. The Maintenance functions will be demonstrated later in this manual, and also in a Line Maintenance CBT.



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Apr 2008


BROADCAST VIDEO / AUDIO

2.7.1

Broadcast Video

The broadcast entertainment will be provided to the passengers’ SVDU and headset via the RF (Radio Frequency) network, and the content files are stored on the hard disk drive of the DSU AM6-12. When playing a file, a video client in the DSU AM6-12 reads and decodes the data and generates audio and video signals that are modulated onto one of the CATV channels of an RF carrier, which is sent through the AVC to strings of ADBs. The first ADB in each string splits the RF signal and routes it to three or four strings of SEBs and to the downstream ADB, which again splits to three or four strings of SEBs and terminates the RF signal. Each SEB has a separate CATV tuner for each seat in its seat group. The tuners detect the video channel as selected by the passenger via the DPCU. The SEB then demodulates each selected signal and converts it to audio and NTSC video, which is sent to the SVDU. The audio signals are presented to the passenger INCAJ (Integrated Noise Canceling Audio Jack) which provides audio to the passenger via headphones. Audio volume up and down button commands are sent from the DPCU to the SEB, which adjusts the audio level at the headset.

ADB1

AVC

PFIS Video

SEB

SEB

WDB

ADB2

DSU AM6-12

SVDU

SEB

EBAY AJ DPCU

WDB

USB

RF 100Mbps / Data

SEB

SEB

SEB

SEB

SEB

SEB

SEB

SEB

SEB

SEB

DPCU

USB

SVDU AJ

AJ/ HEADSET

Figure 2-5 Broadcast Audio/Video The NACIL(I) I3000 system supports six channels of broadcast video entertainment; five video clients with associated audio channels, and two channels dedicated to the DVD Player output. The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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Apr 2008


Broadcast Video Mode Channel Map PCU Channel 1 (Video) 2 (Video) 3 (Video) 4 (Video) 5 (Video) 6 (Video) 7 (Video) 8 (Video) 9 (Video) 10 (Video) 11 (Video) 12 (Video)

Source Video Client 1 Video Client 1 Video Client 2 Video Client 2 Video Client 3 Video Client 3 Video Client 4 Video Client 4 Video Client 5 Video Client 5 DVD DVD

RF Channel DSU AM6-12 Ch. 74 DSU AM6-12 Ch. 74 DSU AM6-12 Ch. 75 DSU AM6-12 Ch. 75 DSU AM6-12 Ch. 76 DSU AM6-12 Ch. 76 DSU AM6-12 Ch. 77 DSU AM6-12 Ch. 77 DSU AM6-12 Ch. 78 DSU AM6-12 Ch. 78 DSU AM6-12 Ch. 67 DSU AM6-12 Ch. 67

Entertainment Video Ch 1 Primary Video Ch 1 Secondary Video Ch 2 Primary Video Ch 2 Secondary Video Ch 3 Primary Video Ch 3 Secondary Video Ch 4 Primary Video Ch 4 Secondary Video Ch 5 Primary Video Ch 5 Secondary DVD Ch 1 Primary DVD Ch 1 Secondary

There are two audio channels for each video client. Example: The same video plays on DPCU Channels 1 and 2. However, DPCU Channel 1 plays the related audio in the primary language. DPCU Channel 2 plays the related audio in the secondary language. The DVD Player broadcasts on DPCU channels also: DPCU Channel 11 plays related audio in the primary language, and DPCU Channel 12 plays the related audio in the secondary language.

2.7.2

Broadcast Audio

The NACIL(I) i3000 system supports twelve (12) channels of broadcast FM stereo audio entertainment. The audio programming files reside on the hard disk drive of the DSU AM6-12. When playing the audio files, the audio client in the DSU AM6-12 reads and decodes the data and generates audio signals that are modulated onto one of the FM radio-band channels of the RF carrier, which is sent through the AVC to the ADBs. The ADBs split the RF signal and route it to three or four Wall Disconnect Boxes (WDB), which again split the signal to two (2) strings of SEBs. In this manner, each ADB supports up to eight strings of up to ten SEBs (seat groups). Each SEB has a separate FM radio tuner for each seat in its seat group. When Broadcast Audio Mode is selected, the tuner detects the appropriate FM audio channel as selected by the passenger via the DPCU.



Page 2-12

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual The SEB then demodulates the signal, converts it to baseband audio, and sends it through an INCAJ (Integrated Noise Canceling Audio Jack) which provides audio to the passenger via headphones. Audio volume up-and-down commands are sent from the DPCU to the SEB, where the output volume level is adjusted.

Broadcast Audio Mode Channel Map PCU Channel 1 (Audio) 2 (Audio) 3 (Audio) 4 (Audio) 5 (Audio) 6 (Audio) 7 (Audio) 8 (Audio) 9 (Audio) 10 (Audio) 11 (Audio) 12 (Audio)

Source Audio Client 1 Audio Client 2 Audio Client 3 Audio Client 4 Audio Client 5 Audio Client 6 Audio Client 7 Audio Client 8 Audio Client 9 Audio Client 10 Audio Client 11 Audio Client 12

RF Channel DSU AM6-12 Ch. 13 DSU AM6-12 Ch. 14 DSU AM6-12 Ch. 15 DSU AM6-12 Ch. 16 DSU AM6-12 Ch. 17 DSU AM6-12 Ch. 18 DSU AM6-12 Ch. 19 DSU AM6-12 Ch. 20 DSU AM6-12 Ch. 21 DSU AM6-12 Ch. 22 DSU AM6-12 Ch. 23 DSU AM6-12 Ch. 24

Entertainment Audio Ch 1 Audio Ch 2 Audio Ch 3 Audio Ch 4 Audio Ch 5 Audio Ch 6 Audio Ch 7 Audio Ch 8 Audio Ch 9 Audio Ch 10 Audio Ch 11 Audio Ch 12

The NACIL(I) i3000 system will comply with the following analog requirements for RF performance:

Frequency Response Stereo SNR Mono SNR Stereo Separation Crosstalk THD + Noise

50Hz to 9kHz (+/- 3dB) > 40dB > 50dB > 15dB > 60dB < 2%



Page 2-13

Apr 2008


PASSENGER FLIGHT INFORMATION SYSTEM (PFIS)

The Moving Map application displays flight status information over a broadcast channel, and can be selected for in seat viewing by the passenger by pressing the button for Moving Map on the DPCU.

USB

VCC

USB

i-CMT

SEB

DVD Player

AVC

ADB1

To other Head-end LRUs

E-Bay

To other cabin LRUs

100Mbps / Data USB

Figure 2-6 Moving Map (PFIS) function The Moving Map application displays a graphical representation of the aircraft’s position over the surface of the earth, as well as textural navigational data and custom graphic images. The Moving Map cycles through displays of maps at up to five different scales while showing the aircraft flight path and current position. At the end of the map cycle, a Flight Data page and a custom graphic are displayed and then the map cycle repeats. The display changes at a rate between 5 and 7 seconds.



Page 2-14

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual When a passenger selects the Moving Map mode on the DPCU, 12 channels of moving map video will be provided with 12 audio channels.

Moving Map Mode Channel Map PCU Channel 1 (MMAP) 2 (MMAP) 3 (MMAP) 4 (MMAP) 5 (MMAP) 6 (MMAP) 7 (MMAP) 8 (MMAP) 9 (MMAP) 10 (MMAP) 11 (MMAP) 12 (MMAP)

Source

RF Channel

Entertainment

MMAP with Audio Client 1 MMAP with Audio Client 2 MMAP with Audio Client 3 MMAP with Audio Client 4 MMAP with Audio Client 5 MMAP with Audio Client 6 MMAP with Audio Client 7 MMAP with Audio Client 8 MMAP with Audio Client 9 MMAP with Audio Client 10 MMAP with Audio Client 11 MMAP with Audio Client 12

DSU AM6-12 Ch. 73 DSU AM6-12 Ch. 73 DSU AM6-12 Ch. 73 DSU AM6-12 Ch. 73 DSU AM6-12 Ch. 73 DSU AM6-12 Ch. 73 DSU AM6-12 Ch. 73 DSU AM6-12 Ch. 73 DSU AM6-12 Ch. 73

MMAP Ch 1 MMAP Ch 2 MMAP Ch 3 MMAP Ch 4 MMAP Ch 5 MMAP Ch 6 MMAP Ch 7 MMAP Ch 8 MMAP Ch 9

DSU AM6-12 Ch. 73

MMAP Ch 10

DSU AM6-12 Ch. 73

MMAP Ch 11

DSU AM6-12 Ch. 73

MMAP Ch 12



Page 2-15

Apr 2008


PASSENGER ANNOUNCEMENT (PA)

The PA function is an audio signal provided from the Aircraft Interface (CIDS) to the IFE system in the following categories: Direct PA and Area PA. A PA is active when the PA KL (Key-line) from CIDS is active to the AVC. VCC S EB

i-C M T

ADB1

SVDU

S EB

WDB

T ypical A J/ HEADSET

AJ

PA KL

AVC

C ID S

USB

ADB2

PCU

P A A udio SEB

SEB SEB

SEB

S EB

DSUA M 6-12 SEB

E -B a y

100M bps / D ata

RF

Figure 2-7 Passenger Announcement 2.9.1

Direct PA

When a Direct PA keyline is active: ● a passenger announcement in progress indication will be provided on each SVDU ● all entertainment sources will be placed in their appropriate pause condition ● audio at each headset will be audio provided by CIDS ● DPCU functions will be limited to volume control only. The AVC receives the Direct PA keyline and PA Audio from CIDS and overlays a 19 KHz tone onto the PA Audio signal on the lowest FM Audio channel (88.1 MHz). This channel is modulated onto the RF carrier for distribution to the seats via the ADB. The SEB hardware has a separate FM tuner that specifically monitors the 88.1 MHz channel, looking for the 19 KHz tone. When it detects the tone, indicating a Direct PA, it forces the SEB to route the PA Audio to the headphones. At the same time, the AVC sends an Ethernet Direct PA status to the other LRUs via the Heartbeat Message, placing them in PA Mode. When the DSU AM6-12 enters PA Mode, it pauses all audio and video output channels. The Heartbeat Message also directs the SEBs to output a “Passenger Address in



Page 2-16

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Progress” screen to the SVDU, and inhibit channel surfing. If the SVDU is in Broadcast mode, it is already displaying video from the SEB and so will display the PA screen from the SEB as well.

2.10 VIDEO ANNOUNCEMENT (VA) The Video Announcement service is the simultaneous combination of a Video-PA and Video Override. The IFE system supports a Video-PA service by a keyline and twisted pair signal from the IFE system. The aircraft has been configured into one Video-PA zone. The i3000 supports the VA service by forcing the in-seat displays to present the specified Video Announcement program. VCC SEB

i-CMT

PA KL

AVC

CIDS PA audio

ADB1

PFIS Video

SVDU

SEB

FDB

Typical AJ/ HEADSET

AJ

DSU AM6-12

USB

ADB2

E-Bay

PCU

SEB

SEB SEB

SEB

SEB

SEB

100Mbps / Data RF

Figure 2-8 Video Announcement The VA function resides on the AVC and is initiated by the operator via the iCMT VA Control menu. The VA audio/video files are stored on the DSU AM6-12. The AVC sends an Ethernet VA Command via the heartbeat message to the other LRUs in the IFE system, placing them in VA Mode. A video client in the DSU AM6-12 reads and decodes the data from the hard drive. It then generates audio and video signals that are modulated onto the appropriate CATV channel of the RF carrier which is sent to the AVC. The AVC splits the RF signal and routes it to the ADBs for distribution to the seats, but it also demodulates the RF to create a baseband audio signal that it routes to the Aircraft PA system for distribution to the overhead speakers. The PA system sends the audio back to the AVC’s via the PA audio input. The AVC modulates the audio onto the PA FM Audio channel (88.1 MHz) of the RF carrier which is routed to the ADBs for distribution to the seats.



Page 2-17

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual At the seat groups, the SEBs detect the VA indication in the Heartbeat message and tunes to the VA channel indicated. The video is demodulated and sent to the SVDUs and the audio is presented to the headphones. The SVDUs detect the VA in the Heartbeat message and switch to Broadcast Mode to receive the VA video from the SEB. The DPCUs functionality is limited to minor volume changes. When the VA keyline is active, all currently running in-seat entertainment services pause in the all zones, and each SVDU is forced to present the selected video announcement with the associated audio. The audio will also be heard through the cabin speakers in all zones. If an SVDU is not in use when the VA became active, the SVDU will turn on and present the selected VA. At the conclusion of the presentation, either the entertainment services will resume or the SVDU will turn off again.

2.11 PRE-RECORDED ANNOUNCEMENT (PRAM) The PRAM messages will be downloaded into the system as part of the Content download procedures, and stored on the DSU AM6-12. The Cabin crew will use the iCMT to control the PRAM functions. The iCMT will present the audio corresponding to a selected PRAM message to the CIDS and activate the PRAM keyline for broadcast into the cabin speakers. VCC SEB

i-CMT

PRAM KL

AVC

CIDS PRAM audio

ADB1

PFIS Video

SVDU

SEB

WDB

Typical AJ/ HEADSET

AJ

DSU AM6-12

USB

ADB2

PCU

SEB

E-Bay

SEB SEB

SEB

SEB

SEB

100Mbps / Data RF

Figure 2-9 Pre-Recorded Announcement The A321/320/319 aircraft support the function by providing independent keyline and twisted pair audio signals from the IFE system to CIDS. The controls for all PRAM functions are on the iCMT.



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Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 2.12 BOARDING MUSIC (BGM) The BGM audio will be downloaded into the system as part of the Content download procedures, and stored on the DSU AM6-12. The Cabin crew will use the iCMT to control the BGM functions. The iCMT will present the audio corresponding to a selected BGM message to the CIDS and activate the BGM keyline for broadcast into the cabin speakers. Several channels of BGM are hosted on the DSU AM6-12. The desired music channel is selected for playing by the system operator via the BGM menu on the iCMT. The music is sent from the DSU AM612 as base-band audio to the cabin speakers. Boarding Music is not returned to the AVC and it is not modulated and sent to the seats.

2.13 DVD PLAYER

VCC DVD Player

VCCSEB

iCMT

ADB

AVC

RF Baseband RS-485

E-Bay

Figure 2-10 DVD Function The DVD function includes a single deck DVD player. The DVD is tray-mounted in the Video Control Center and is area cooled. When a disc is loaded into the DVD and PLAY is pressed, the video program will be modulated by the AVC and added to the RF signal delivered to the seat groups. The i3000 IFE system allows control of the DVD player through the iCMT as follows:

Operating the DVD using Video Broadcast 1. Insert a DVD into the player 2. Go to the Services screen, activate Video Broadcast 3. Press DVD switch on the DVD player 4. Press the Play button on the player. Use FF to advance to the desired tract if needed. 5. The DVD media will play on screen on channels 11 and 12 along with other video broadcast from channels 1 through 10.



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Operating the DVD as a Video Announcement 1. Insert a DVD into the player 2. Press DVD switch on the DVD player 3. Press the Play button on the player. Use FF to advance to the desired tract if needed. 4. Go to the VA screen on the iCMT and select DVD. 5. Press the Play button to preview, if needed. 6. Press VA to PAX to activate the VA 7. The DVD media will play on all SVDUs as VA/PA

2.14 DECOMPRESSION

Aircraft discretes

i3000 system

AVC

Decomp KL

E-Bay

Cabin

Figure 2-11 Decompression Decompression occurs when the AVC receives a decompression keyline from the aircraft. When the Decompression keyline is active, the AVC turns off the backlight of all SVDUs and terminates all audio services. Only the PA audio to the headsets remains enabled. After the Decompression keyline is deactivated, all SVDU activity remains in the disabled state until the system is reset.

2.15 IN-SEAT POWER A/C Power

MCU1 AVC

E-Bay

PED in use light

PFDB

ACOU

SEB

SEB

SEB

SEB

ISPC

ACOU

Ethernet Tri-state line Power

Figure 2-12 In-seat Power Supply



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual In-seat power will provide 110 VAC at 60Hz to the passengers for use with their personal electronics devices. The system will provide the power via an ACOU (Alternating Current Outlet Unit) installed at each passenger seat in First Class. The Thales IFE system only interfaces with the in-seat power supply system; all components are procured independently from KID systems. The following requirements are not the responsibility of the Thales IFE system, but are standard requirements for the in-seat power supply system. The TopSeries system supports in-seat power for personal electronic devices. An ACOU (The Alternating Current Outlet Unit at each First Class seat accepts the North American Standard (two terminal non-polarized, two terminal polarized NEMA 1-15P, or three terminal NEMA 5-15P) and European (norm reference EN 50075:1990) connectors. Each ACOU has:

A protective device to ensure that no electricity is provided to the plug unless an appropriate plug device is utilized. An indicator light which informs the passenger of the power mode; degraded mode is yellow, disabled mode is blank or red, active mode is green)

The system also includes an indicator light (PED In-Use light) at every seat group to inform the crew when there is a personal device plugged in.

2.16 SYSTEM HEARTBEAT MESSAGE The AVC outputs a “Heartbeat” message, broadcast via Ethernet to all LRU’s in the system, once per second or immediately whenever something changes. The heartbeat message is used to synchronize functional modes throughout the system. It contains information such as PA and VA modes, timestamp, flight phase, weight-on wheels, etc.

FIELD NAME Sequence

SIZE

FORMAT

DESCRIPTION

2 bytes

23

Timestamp

17 bytes

05/12/01 17:55:32

Change Indicator

1 byte

1

Aircraft ID

6 bytes

8919

2 digit message sequence number, 0099, then rolls-over Year, month, day, hour, minute and second of current time Incremented every time a field, other than one of the first three, is changed. Goes from 0 to 9 then rolls over. Aircraft tail number (or perhaps ICAO number)



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual FIELD NAME Flight Phase

Weight On Wheels System Mode System Submode PA All Call Keyline Area PA Keylines Overhead Monitor Status VA Area Keylines O/H audio forced at Headset VDU forced to O/H program

SIZE

FORMAT

2 bytes

Nn

1 byte

1

2 bytes

Nn

2 bytes

Nn

1 byte

0

6 bytes

010000

6 bytes

010000

6 bytes

010000

6 bytes

010000

6 bytes

010000

DESCRIPTION Decimal flight phase 0 – Unknown 1 – Power On 2 – Preflight 3 – Engine Start 4 – Taxi Out 5 – Takeoff 6 – Initial Climb 7 – Climb 8 – En route Cruise 9 – Descent 10 – Approach/Land 11 – Rollout 12 – Taxi In 13 – Go Around 14 – Engine Shutdown 15 – Unknown State of A/C WOW (0 if off, 1 if on)

State of PA All Call Keyline (0 if off, 1 if on) State of 6 PA Area Keylines (0 if off, 1 if on) State of overhead monitors for each VA area (0 if off, 1 if on) State of VA Area Keylines (0 if off, 1 if on). When on, assumes that VA area audio is available. Indicator as to whether the headset audio should be forced. (0 if no change, 1 if forced to O/H program audio) [VA] Indicator as to whether the VDU should be forced to the O/H program. (0 if no change, 1 if forced to O/H program video) [VA]



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual FIELD NAME VDU forced on

SIZE

FORMAT

DESCRIPTION

6 bytes

010000

Channel Surfing inhibited

6 bytes

010000

PA displayed on PCU Headset volume adjustment range limited Pause interactive servers Area RF Channel

6 bytes

010000

6 bytes

010000

Indicates whether the VDU should be forced on. (0 if no change, 1 if VDU should be turned on) [VA] Indicates whether channel change and other PCU keys should be ignored. (0 if all keystrokes honored, 1 if special keystroke processing required)[PA ALL] Indicates whether PCU LCD display should show “PA”. (0 if no change, 1 if “PA” display required) [PA/VA] Indicates whether headset volume should be limited to defined range (0 if no limit, 1 if volume range active)[PA ALL]

6 bytes

010000

12 bytes

001200000000

12 bytes

001200000000

12 bytes

001200000000

8 bytes

23000000

1 byte

1

Area FM Channel – Primary Area FM Channel – Secondary Special Channel Assignments PAVA Map Sequence Number

Indicates whether interactive servers should be paused (0 if no pause, 1 if interactive servers should be paused) Six 2- digit RF channel numbers for: 1) Tapping Unit/OH Monitors 2) Viewing OH program at seat 3) VA Six 2- digit FM channel numbers for listening to OH program at audio-only seats Six 2-digit FM channel numbers for listening to OH program at audio-only seats Four 2-digit special channel numbers for airline channel-specific data. Indicates the sequence number of the current PAVA Map. Goes from 0 to 9, then rolls over.

2.17 CONTENT MANAGEMENT AND SOFTWARE LOAD Content Management at an airline location is an important step in assuring a successful onboard passenger experience. Content is loaded from a PDL (Portable Data Loader) that connects to one or more of the RJ45 connectors adjacent to the iCMT. Step-by-step procedures in the AMM and applicable Service Bulletins describe methods for loading content. Minimum loading rate will be at least 60Mbits per second using the PDL. The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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VCC VCCSEB iCMT

USB USB DL 1

DL 2

ADB1 DSUAM612

AVC DATA 100Mbps

EBay

Figure 2-13 Content Loading The Content loads to the DSU AM6-12 through the RJ45 connections at the iCMT. Software is loaded to the iSeries LRUs in a two-phase process, in which the code is first uploaded from the CD-ROM on the PDL (Portable Data Loader) to the DSU AM6-12 hard disk drive and then downloaded to individual LRU types or individual LRUs. VCC SEB

i-CMT

USB Type A

USB Type A

To ABD 1 and to the rest of the system

DL

100Mbps / Data USB

Figure 2-14 Software Loading When downloading software, it is important to carefully verify that the correct files to be downloaded were successfully uploaded and that all of the necessary files are selected. An error here could result in missing file or an incompatible file on an LRU type that may prevent further downloads to correct the problem. Daily content upload and fault download capabilities for the system will be provided via two USB ports that are also located adjacent to the iCMT.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Always refer to the Adjustment/Test section in the AMM for step-by-step procedures during any Maintenance interrogation of the i3000 IFE system.

2.18 BUILT-IN TESTS Built-in Tests include a Software Configuration Verification, an Ethernet Communication Test, and a Layout Configuration Report. The following reports are available on the iCMT: ● Communication Check ● Seat Address Check (layout check) ● Configuration Consistency Communications Test This test verifies that each LRU has the ability to communicate with other system components. A communication failure brings up the COMMUNICATIONS CHECK FAILED screen. This screen gives the operator the option to continue BITE testing or to view communication failure details. Layout Configuration Test This test ensures that all seat-end LRUs are correctly installed and have the proper IP address as compared against the stored aircraft configuration database. An incorrect configuration or address brings up the COMMUNICATIONS CHECK FAILED screen and reports that “The Seat-End LRUs have not been properly IP-Sequenced.” The operator is given the option to perform an IP Sequence, to continue BITE testing or to view failure details. Software Configuration Verification Test This test compares the software installed within system LRUs with the Phase 1 image installed. Should software inconsistencies be found, the CONFIG CONSISTENCY CHECK FAILED screen comes up, and reports “Problems were found with the Software Configuration.” The operator is given the option to download the correct software, to continue BITE testing or to view failure details.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 3

LRU DESCRIPTIONS

3.1

HEAD-END COMPONENTS

3.1.1

Inflight Entertainment Center (IFEC)

Thales provides an Inflight Entertainment Cabinet (IFEC) to be installed below the main deck. Airbus is responsible to supply all cooling and smoke detection required in the IFEC. The following components are installed in the IFEC: (1) (1)

Broadcast Digital Server (DSU AM6-12) Audio Video Controller (AVC)

View Looking Aft



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N/A



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 3.1.2

Audio Video Controller (AVC)

The AVC is a head-end interface LRU that provides video modulation, audio modulation, passenger announcement, overhead video system control, and communications with aircraft electronic systems. The AVC incorporates the functions of the traditional audio MUX and overhead video control systems into a single LRU. The AVC provides the following functions: PA ALL call audio distribution System status monitoring System mode control by generating system Heartbeat message Video Announcement (VA) Audio/Video modulation Peripheral control (Airshow) Interface to Aircraft Equipment The size of the AVC is a standard 4 MCU with the electrical interface via a size 2 ARINC 600 compliant connector located on the rear of the LRU, provides the electrical interface. Internally, the unit is modular in construction, consisting of an I/O assembly incorporating the ARINC connector and a backplane, which interfaces to modular circuit cards. These circuit cards provide the following functions:

Control and interface functions Audio and/or video decode Analog buffering and RF modulation/multiplexing of the audio/video signals to combined signals



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Supervisory 8260 Power PC processor to control data flow through the LRU.

Figure 3-1 AVC Functional Block Diagram



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Ethernet Communication The AVC is equipped with 6 ports of Ethernet 100BaseT for communication with other I-Series components. Each port is wired to other LRUs in a star network configuration using shielded dual twisted pair or a single twisted quad coax wire. One Ethernet interface is defined as a primary domain interface and as such may be used as a gateway interface to other Ethernet domains – for example MCU control. The remaining Ethernet interfaces are defined as secondary domain interfaces and as such may be used to interface to other LRUs in the same Ethernet domain – iSeries domain. ARINC-485 Slave Communication The LRU has means for communication on 2 Slave ARINC-485 serial half-duplex multi-drop interface networks. These ports are typically used as slave in the communication protocol but may also be configured as additional masters. These interfaces may be used for AVOD control. ARINC-485 Master Communication The LRU has means for communication on 12 Master only ARINC-485 serial half-duplex multi-drop interface networks. These interfaces provide a communication link to control peripherals on the aircraft, such as the DVD and Landscape Camera. ARINC-429 Communication The LRU has means for transmission and reception of messages using 6 Tx/Rx ARINC-429 serial interfaces. The LRU also has means for reception of messages using 6 Receive Only (RO) ARINC-429 serial interface networks. The six transmit and receive interfaces consist of a double, twisted pair. The ARINC 429 interface allows bi-directional communications between the AVC and peripheral devices. However, data can only flow one way on each twisted pair, from a transmitter to a receiver. The ARINC 429 receive-only interface consists of one twisted pair providing status from peripheral devices. Input Discrete Signals The LRU provides means for a total of sixteen ARINC 720 (current mode) compliant input keylines. They are available for implementing custom features and the dedicated functional keylines that follow: Area PA Keyline Inputs: The AVC is capable of accepting eight Area PA keyline inputs in addition to the one All Call PA keyline. All PA keylines are an active low assertion level. Decompression Keyline: The AVC detects activation of the Decompression keyline. The Decompression keyline occurs in emergency conditions when the aircraft loses cabin pressure. Upon activation the AVC transmits messages to turn off all system monitors. The Decompression keyline has an active low assertion level. Weight on Wheels (WOW) Keyline: The AVC detects the state of the WOW keyline. The WOW keyline is active-low and transitions during take-off and landing conditions. The AVC may use this keyline to log the start and finish of a flight, and to change between Forward and Down looking Landscape camera views. Fasten Seat Belt and No Smoking Keylines: The AVC is capable of accepting the Fasten Seat Belt and No Smoking keylines. These keylines are manually activated by the cockpit crew during flight. These keylines have an active low assertion level. Output Discrete Signals



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual The LRU provides means for a total of ten ARINC 720 (active ground) compliant output keylines. These keylines are diode-isolated allowing attachment to existing or “shared” keylines. They are available for implementing custom features as well as the dedicated functional keylines. The AVC provides six VA output keylines. The output keylines indicate that a video announcement is being performed in a specific area. The VA keylines are active low assertion levels. NTSC Video Inputs The AVC accepts up six 100 ohm differential NTSC Video inputs. These inputs are typically driven by peripheral devices such as VTRs, aircraft cameras, PFIS, etc., and are modulated onto the RF signal which is distributed throughout the system. Audio Inputs The AVC accepts six channels of 600 ohm differential audio from an external video source such as a Video Tape Reproducer or DVD. The audio from can be configured as three stereo pairs or six monos or any combination between. The audio is modulated onto the RF signal for distribution throughout the system. PA Audio Inputs The AVC is capable of receiving up to six 600-ohm differential monaural PA audio inputs and four 70V audio inputs from an ARINC 560 PA System. These audio sources are modulated onto the RF signal, which is distributed to the seats. VA Audio Outputs The AVC provides up to 6 monaural audio outputs with volume control back to the PA system for distribution to the overhead speakers during Video announcements. The interface consists of a differential 50 ohm 0dBM audio output. These outputs are used in conjunction with VA Output Discrete keylines to indicate an active signal at the audio output. Auxiliary Video Output The LRU provides one differential 100 ohm, 1Vpp baseband NTSC video output. RF Input The AVC receives one coaxial 50 ohm RF (550Mhz) input from the DSUAM6-12. The RF input signal is combined with the modulated RF signals generated by the AVC and output at the three RF outputs. RF Outputs The AVC provides three coaxial 50 ohm RF outputs. After the input signal from the RF Input is combined with the modulated RF signals generated by the AVC, it is split into three RF (550 MHz) signals and output at these RF outputs. ARINC Connector J1 – The AVC includes one external connector providing the aircraft and peripheral interfaces to the LRU. The ARINC 600 compliant connector contains three inserts, which provide access to digital signals, analog signals, and power. Connector J2 – (diagnostic connector) is a high density DB-style, 26-pin female connector located on the LRU Front Panel and provides the following interfaces: The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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1 Secondary Domain 100BaseT full duplex Ethernet port 1 RS-232 Communications Port (also available at the ARINC Connector) DC power supply voltages Supervisory processor reset Supervisory processor attention input LRU Status discrete for AC OK, DC OK, BITE OK, SCSI Activity Ethernet Switch status interface Test Mode keyline input

Basic Specifications: FEATURES Dimensions Size Weight Power Consumption Voltage Current Part Number

SPECIFICATIONS 5.0 (W) x 7.85 (H) x 12.52 (D) inches 4 MCU 12.4 pounds 100 Watt (max) 100 to 125 VAC, 400 Hz Single-phase 1.0 Amp RMS (max. at 100 VAC) 177716-104

Cooling Requirements A minimum airflow of 12 CFM at sea level with inlet pressure .15 +/-0.1-inch H2O, and inlet temperature not to exceed +55 ºC. Protective Devices The AVC power supply shall shut down when internal temperature at the main power dissipation component in either power supply exceeds +110ºC. The power supply is independently protected by a 1.5 amp fuse in the primary feed circuit Redundancy and/or Graceful Failure The AVC is designed so that under failure conditions the AVC will not halt system operations. Major components of iSeries are connected through 100BaseT Ethernet using a star network configuration. The configuration provides transparency to the system during failure modes. Failures on the AVC will not be intrusive to other components of the system. The AVC provides a passive interface to the external RF backbone of the system. The internally generated RF signals are passively coupled with external RF signals. An AVC failure will not affect downstream RF availability. Warnings and indicators LED indicators are provided on the AVC front panel. The LEDs; BITE OK, AC OK and DC OK are illuminated green when the AVC is getting AC power and the internal power supplies and Processor board (PCOM) are functioning.



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Digital Server Unit, Analog Modulated 6 Video / 12 Audio (DSU AM6-12)

Figure 3-2 DSU AM6-12 Functional Description The DSU provides video entertainment similar to a Video Tape Reproducer. Instead of video tape, video content is stored on a magnetic hard drive in compressed format compliant with the Motion Pictures Expert Group (MPEG) MPEG-1 or MPEG-2 format. The video data is stored in multiplexed format including video and one to 16 audio tracks in the MPEG-2 transport stream format. The DSU also provides audio entertainment similar to an audio entertainment reproducer. Instead of compact disk or linear magnetic tape, audio content is stored on a magnetic hard drive in compressed format, compliant with the MPEG MP3 audio format. The digital content is stored on a high performance disk drive and is accessed via a wide fast SCSI interface by a supervisory microprocessor contained on the PCOM II Printed Circuit Board Assembly (PCBA). The digital content is streamed via Internet communications protocol (TCP/IP) to client platforms contained on PCBAs in the DSU. Two types of client are implemented; video clients, two per circuit card and audio clients, four per card. Each video client can generate one video output with two associated simultaneous stereo language tracks selected from up to 16 language tracks multiplexed with the video. Each audio client can generate three or four audio outputs. The DSU contains three video client cards for a total of six video clients and six associated dual stereo video/audio outputs. The DSU contains one audio client card for a total of four audio clients and 14 associated audio outputs. Twelve of the audio outputs are general purpose in nature, while the 13th and The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 14th outputs are used to implement PRAM and BGM functions. Since these two aircraft interfaces are generally monaural, MP3 programming for the 13th and 14th audio output are encoded and stored as monaural MP3 and only the left channel of the stereo decoder is connected to the appropriate aircraft PA system input. The video clients are not only digital MPEG video/audio decoders, but are also general purpose PC compatible platforms and may implement customized functions that are displayed as broadcast video channels through the cabin distribution system. A typical example of this use of a video client is the implementation of a Passenger Flight Information (e.g. moving map) channel. Each of the video, video/audio, and audio entertainment channels are buffered and distributed via a backplane and input-output assembly to the ARINC connector as baseband signals. These signals are also distributed by the backplane to modulator PCBAs. The audio client outputs are distributed to a 12channel FM modulator Shop Replaceable Unit (SRU) and the video clients are distributed to a six channel video modulator SRU.

Figure 3-3 DSU AM6-12 Block Diagram The modulators combine the modulated signals into a single output each which is distributed by the backplane to the RF combiner. These modulated signals are mixed with RF input signals from previous



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual LRUs, then output as a single RF output at the ARINC connector to feed the next RF LRU in the distribution hierarchy. The DSU provides six video and associated two stereo audio language tracks under control of the cabin attendant. These may be configured to start and stop with pre-configured content as a group via control means accessible by the cabin attendant at the Cabin Management Terminal (iCMT). Alternatively, some channels may be configured to be individually controlled by a cabin attendant including content selection, language selection, start, stop, fast forward, and rewind. Video and associated audio is paused during an All Call PA event. Broadcast Streaming Audio from Digital Content, Controlled by a Cabin Attendant The DSU provides 12 stereo audio programs under control of the cabin attendant. These may be started and stopped with pre-configured content as a group via control means accessible by the cabin attendant at the CMT. Audio is paused during an All Call PA event. Digital Content and Downloadable Software Repository and Manager The DSU, with it’s large hard drive storage is used to contain both digital video and audio content for playback. It also contains images of all downloadable software for the system. Maintenance personnel, using the CMT, may download LRUs from the repository. To accomplish this, the DSU download manager is triggered by means at the CMT to provide target LRUs with a list of required software by LRU type. Each LRU evaluates the required part number against it’s current load and if different will fetch and install the correct software from the DSU. Download and Configuration Reporting In response to a download request from the download manager, initiated through means at the CMT, the DSU will determine if new software is required by comparing the download request and the current software load. If a download is required, the LRU will fetch and install the required software from any available download repository containing the correct software. The LRU will automatically perform a reboot after exiting the download state. In response to a configuration request from the system configuration manager, initiated through means at the Cabin Management Terminal, the DSU AM6-12 will provide a current list of configuration items for software and hardware. System Level Ethernet Interconnect via the external Ethernet The DSU provides five external Ethernet interfaces used to interconnect the system data distribution network. Although the interconnect design may be customized on a customer and configuration basis, typically the DSU is used to interconnect:

Audio Video Controller First Area Distribution Box Secondary DSU AM6-12 External Systems

Degraded Functionality When any client platform fails, the remaining client platforms will continue to provide service. The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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When the supervisory processor and/or disk drive fail, the clients will locate an external server LRU, if available, and continue to provide service. When the power supply fails, service from the LRU will fail, however, RF channels from a secondary DSU connected through a failed primary DSU will remain available. When the DSU loses the system heartbeat for approximately 10 minutes, video and audio services will be automatically started in an attempt to provide service.

BIT/BITE function The following Built-In Test (BIT) continuous non-intrusive functions are provided: Reporting of Power on Self Test Condition Operational status of all external communication links Operational status of supervisory and client platforms Operational status of power supply The following BITE intrusive functions, executable only by maintenance action at the CMT, are provided: Commanded self test of microprocessor facilities Internal loop-back on all communication interfaces except Ethernet External loop-back on all Ethernet interfaces Signal performance parametric tests for all base-band and RF modulated video and audio signals

NOTE: Intrusive tests will be visible and audible to passengers and are intended for maintenance activities during non-revenue operation of the system. The DSU may be configured to provide the system heartbeat required by all LRUs for consistent system operation. The DSU provides this service only when the AVC fails to provide this service after a reasonable period of time. Passenger Flight Information System (Moving Map) function (Optional) The DSU may be configured to have one video client provide Passenger Flight Information (e.g. moving map). The DSU may either be connected directly to appropriate aircraft sources of navigation information such as flight management data busses, or may receive this data via Ethernet from the AVC which is so connected. Pre-Recorded Announcements (Optional) The DSU may be configured to provide monaural prerecorded announcements to the aircraft PA system, either by activation of customer-defined keylines or via means located at the CMT. Background Music (Optional) The DSU may be configured to provide monaural Background Music to the aircraft PA system, either by activation of customer-defined keylines or via means located at the CMT. Indications



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual The following green LED indicators are located on the front of the DSU. When lit, each LED indicates proper operation of the applicable function. BITE OK AC OK DC OK SCSI System Power-On/Start-up The LRU will complete it’s power on and operating system boot sequence within two minutes of power being applied. This sequence includes Power-On Self Test (POST). The results of POST are made available via the BIT server to the system level BIT collector. When the DSU receives the system heartbeat System Startup mode message it enters a mode consistent with a power and POST cycle, if not already in that condition. Normal Service Functions After DSU power up, and once the DSU establishes that the system is in the normal service state, via a system heartbeat message, the LRU will determine an appropriate state for each service and resume that state using any persistent data stored from the checkpoint server. If no checkpoint data is available, the service will start from the beginning. determined in the following priority:

The service state is

System state interrogation – the current state of the service controls (CMT state) is determined. If this state information is not available; Stored persistent data – the last known service state is used Configuration database – the default state for the service is used

An access method is provided to control the state of each service through the HTTP server and from a utility program usable to build script files. SERVICE

POSSIBLE STATES

Broadcast Video

ON, OFF, PAUSE

Broadcast Audio

ON, OFF, PAUSE

PRAM

PLAY(Message), STOP, PAUSE

BGM

PLAY(Program, Volume), STOP, PAUSE

BIT

MONITOR, PAUSE

Automatic Service Functions The DSU provides a facility to allow implementation of automatic functions. The mode monitor will trigger a script on any change of state of the system heartbeat message. Passenger Announcement The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual The DSU pauses all broadcast video, broadcast audio, PRAM, and BGM programs whenever the PA ALL keyline is active as indicated by the system heartbeat message. Static Test The DSU sets all services to STOP mode when static test mode is indicated in the system heartbeat message. A unique test program for each broadcast video and audio channel, as identified in the configuration database, will then be started to provide an intrusive static test mode of operation to allow maintenance personnel to walk through the aircraft and verify proper operation. Built-In-Test Equipment (BITE) The DSU sets all services to STOP mode when BITE test mode is indicated in the system heartbeat message. The DSU waits for system level BITE functions to be executed as commanded by an external source. Download The DSU sets all services to STOP mode when download mode is indicated in the system heartbeat message. The DSU waits for system level download functions to be executed as commanded by an external source. When download mode is exited as indicated by the system heartbeat message, the DSU will invoke a hardware initiated shutdown of the power supply causing a subsequent reboot. Decompression The DSU sets all services except PRAM to STOP mode when decompression mode is indicated in the system heartbeat message. The DSU activates the PRAM keyline and plays the decompression message within 100 msecs of the decompression discrete. The DSU remains in decompression mode until power is removed, regardless of the system state indicated in the system heartbeat message. System Shutdown When System Shutdown Mode is indicated in the system heartbeat message, the DSU does the following: Sets all services to STOP mode Prepare logs for offload Prepares the DSU for power off (graceful shutdown) Prepares systems for power on during subsequent start up mode. 3.1.4

Video Control Center (VCC)

The following components are installed in the VCC: (1) (1) (1) (2) (2)

Interactive Cabin Management Terminal (iCMT) Seat Electronics Box (SEB) DVD Player RJ45 Ports USB Ports



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DVD Player

USB & RJ45 Ports

iCMT and SEB access

iCMT 3.1.5

interactive Cabin Management Terminal (iCMT)

The interactive Cabin Management Terminal (iCMT) provides the user interface to control the operation of the iSeries Inflight Entertainment System. The GUI is displayed on a 10.4-inch color Flat Panel Touchscreen Display. The unit receives power, VGA video, MPEG-1/MPEG2 streaming video/audio via Ethernet, and system communications via 10/100BaseT Ethernet through the VCC mounted SEB. The iCMT has three major components: a touch screen LCD with backlight, an Interface Printed Circuit Board (PCB) with backlight inverter power supply, and a Processor Printed Circuit Board. The iCMT’s main functions are: Display of selected video signals for Video Preview Function The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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System operator control and interface IFE system peripherals control USB Interfaces Maintenance interface

The iCMT is able to accept a VGA video signal and MPEG-1/MPEG-2 streaming video from the SEB for display on the LCD. The input impedance for both is 100 ohms. The video is sourced by either the AVC (DVD playback) or the DSU AM6-12 (Digital Content) and is routed to the iCMT via output port J8 of ADB1. The CATV signal from the ADB is demodulated by the VCC SEB and sent to the iCMT as a VGA signal. There are manual controls located on the face of the iCMT for brightness Up/Down and iCMT reset. The iCMT operates from SEB-supplied unregulated +32VDC, which is regulated to provide proper power for the LCD, the backlight inverter, and the PCB electronics. The iCMT provides 10/100BaseT Ethernet communication, which supports MPEG-1/MPEG-2 streaming video/audio. The iCMT also provides two USB compatible ports that may be used for Thales approved peripheral or download devices.

BITE The iCMT provides Backlight on/off status and video indicator status via the Ethernet link. Memory test also provides testing of the RAM and Flash memories upon power up or in maintenance mode.



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Seat Electronics Box (SEB)

There is one SEB installed in the VCC, aft of the iCMT. The SEB supplies Data and Power to the iCMT and performs the following functions to allow for iCMT operations.

Forward

Figure 3-4 SEB installed in VCC Audio/Video Demodulation The SEB tunes and demodulates broadcast audio and video from the RF network. The broadcast video is distributed to the iCMT in the NTSC composite video format, RS-170 compliant. The output impedance is set at 100 Ohms ± 5%. The broadcast audio is amplified and distributed to the audio jack or ANR Jack. The audio power delivered to each 300-Ohm transducer element of the EJM is 75-mw minimum at SEB maximum volume setting. Audio volume control The SEB provides audio volume control. At the maximum volume setting, audio output to the RAJ is calibrated to give out 75 mW RMS into each 300 Ohms transducer (1 kHz sine wave). The audio volume control provides 32 attenuation steps. Each step is a 2 dB change for a total of 64 dB change. Audio volume control may be limited during PA operation. SVDU Data Routing The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual The SEB performs data transfer between the 100Base-TX upstream ports and the SVDU downstream ports. Data can be transferred in both half or full-duplex modes. 3.1.7

DVD Player

The DVD Player is a Video Reproducer Unit designed for corporate and business jet aircraft.This unit is capable of playing back two languages simultaneously to allow greater audio flexibility for multi-national venues. In addition to unique audio capabilities, the unit supports both PAL and NTSC video sources and S-Video and composite outputs.

Forward

The DVD Player is DO-160D qualified which ensures the system will operate in extreme temperature conditions and periods of vibration. It can be remotely controlled using either RS232, RS485 (Protocol provided by and compatible with MAS systems) or serial IR controls.



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CABIN DISTRIBUTION

The Cabin LRUs are made up of the LRUs located in the cabin but not installed in the Seat Groups. The power and signal Distribution LRUs make up this group. Included are the Area Distribution Boxes (ADBs), Master Control Units (MCUs), the Wall Disconnect Boxes (WDBs), and the Power Wall Disconnect Boxes (PWDBs).



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Area Distribution Box (ADB)

The in-seat audio/video entertainment is distributed through the ADB to each columns SEBs. The last ADB in the string must have the downstream ADB output connector (J2) terminated. The main purpose of the Area Distribution Box (ADB) is to provide downstream distribution of electronic signals to other components in the IFE system. It provides two different types of distribution: RF and Ethernet. The ADB is an unmanaged IEEE 802.3u compliant 17-port Ethernet switch, which can provide limited management functions. The ADB also functions as an RF equalizer/splitter to provide an acceptable level of RF to the seat components and a passive tap for the other ADBs in the chain. The ADB determines its position in the system by detecting the “Pin-Coded Addressing” in the cable attached to the J1 Connector. By “knowing” its position and reading the configuration data, it can correctly supply addressing information to the SEBs connected to its output connectors.

Figure 3-5 ADB (Area Distribution Box) The ADB provides: Ethernet switching using a programmed routing table Assignment of SEB IP Addresses during IP Sequencing Radio Frequency splitting and equalization ADB External Interface Signals Inputs:

Two 100Base-Tx inputs for the upstream LRU Headend device or other ADB Two 100Base-Tx inputs for additional expansion This is intended for a direct connection to a server when required to support additional bandwidth for AVOD. One RF input with a passive tap on the output side Two Aux RF inputs The Aux signal is intended for local injected RF signals for that zone.



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Apr 2008


One Decompression keyline on the input connector (Active Low).

Outputs: Four Dual column outputs of 100 Base-TX One Aux Dual column output of 100 Base-TX This output can be used as an additional seat column. Four Single Column outputs of RF for SEB columns With the addition of an FDB, each RF output is split into (2) equal level RF outputs providing the ability to have 80 seat groups from ADB (4 ADB x 2 WDB x 10 SEB). There are approximately 10 SEBs per column possible. One Dual column output of 100 Base-TX Daisy chain to additional ADBs. One Single column output of RF for usage as a Telephone/VCC/Remote Terminal Two Column outputs for Tapping Units, maximum number of 4 Tapping Units per output. Each Tapping Unit provides 3 outputs for ARINC 722 monitor. The ADB can provide outputs of up to 24 monitors. Description of External Interfaces

Figure 3-6 ADB Connectors ADB Outputs: J1 J2 J3 J4 J5 J6 J8 J9 J16

Input Connector. Power, Data, RF inputs ADB to ADB. Data, RF Output to Seat Column. Data, RF Output to Seat Column. Data, RF Output to Seat Column. Data, RF Output to Seat Column. Data, RF Output to VCC and WMSEB. Data, RF Output to TU (covered). RF, Data (RS485) Input from AVC, DSU AM6-12.

AC Power Interface The ADB connector and contacts are rated to handle up to 15 amps of current. The ADB requires approximately one amp. The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Seat Electronics Box (SEB) Interface Each ADB is able to interface with up to (4) dual columns of SEBs for a maximum of 80 SEBs per ADB. The ADB has two different types of outputs, RF distribution, and Ethernet. The ADB to SEB data communication is a 100Base-TX Ethernet data network, the transmission medium consists of a quad cable. The ADB operates in this network as a 17-port switch controller, with up to 10 ports for SEB communication. During IP Sequencing, the ADB assigns Ethernet addresses to the SEBs based on the configuration data as shown in Table 7. The configuration data indicates which SEB column is connected to each of the ADB outputs and how many SEBs are in each column. It also defines the seat location of each SEB.

ADB Block Diagram The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Ethernet System Interface Each ADB provides two 100Base-Tx Ethernet interfaces for communications with the LRU directly upstream, which could be the AVC or another ADB. It also provides two 100Base-Tx Ethernet interfaces for communications with the next downstream ADB. The system does not require both inputs to be active to function. Each ADB provides two 100Base-Tx Ethernet interfaces for direct connections with either an aircraft server or a LAN switching device. This provides a separate data path for AVOD providing additional bandwidth to support up to 200 Mbits/sec of data for each ADB. Fifth Port Interface Each ADB has a fifth port (J8) that is identical to the four Column ports used for the SEB. The fifth is intended for use as a phone, wall mount SEB and monitor, crew station, or remote iCMT port. This port can be turned on/off independently of the other ports. The port can also be used as an extra dual seat column port; when utilized in this manner, each ADB can drive up to 100 SEBs. Aircraft Ethernet Distribution System The ADB has two ports of 100Base-Tx on the upstream connector, two ports of 100Base-Tx on the downstream connector and two ports of 100Base-Tx on the Aux connector. The upstream connector is designed to be hooked to the Headend provider of Ethernet service or another ADB, while the downstream connector is designed to be attached to an ADB. When the ports are not used the software turns off the port during system initialization. The two Aux ports of 100Base-Tx are intended for use as high speed local AVOD for the ADB zone. Aircraft Radio Frequency Distribution System The ADB has one Main RF input and two Aux RF inputs for 50 ohms coax. The Main RF input is sent through a passive RF tap to an RF output while the two Aux inputs are combined with the Main RF for the local RF outputs. The Aux inputs are intended for local-zone RF signals like games or video for that zone only. Decompression The AVC detects activation of the Decompression Keyline and notifies other LRUs via the Heartbeat Message distributed via Ethernet to all LRUs. The ADB receives this Heartbeat Message but does not act on it. Input Power The ADB operates on single-phase, 115VAC, 400 Hz AC power. Maximum power consumption is 70 Volts/Amps.

FEATURE

SPECIFICATION

Dimensions

7.86 (W) x 3.90 (H) x 9.25 (D) inches

Weight

5.0 lbs ± 10%

Part Number

177729-104



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Apr 2008


Master Control Unit (MCU)

MCU with output face showing

Figure 3-7 Master Control Unit Functional Description The MCU is a power distribution unit for supplying cabin/in-seat equipment with 115V 400Hz AC power. The input power to the MCU is nominal 115VAC, 3 phases on connector J8. Power input pins and circuitry are designed for minimum 25 amps operating phase current. MCU is able to monitor a minimum of 3 x 25 amps x 115VAC = 8625VA. The MCU also contains two (2) Ethernet ports on connector J9, one for communicating upstream with the IFE system and the other for interfacing with a downstream MCU.

Input Connectors

Figure 3-8 Input Connectors Signal 115 VAC Phase A in 115 VAC Phase B in 115 VAC Phase C in Neutral in Chassis GND Not Used Not Used

Pin number A B C D E F G



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Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Power Input Connector J8 The outputs are configured as follows: 5 columns/ports each 115VAC, 3 phase, 400 Hz. Column 1 to 4 (J1 to J4): Power output port pins and circuitry are designed for 14 amps operating phase current. Column 5 (J5): Power output port pins and circuitry designed for 7.5 amps phase current

MCU INPUTS

Output Connectors

Figure 3-9 Output Connectors Column Output Connector J1, J2, J3, J4, J5 Signal 115 VAC Phase A (out) 115 VAC Phase B (out) 115 VAC Phase C (out) Neutral (out) Data out (control) Not Used

Pin Number A D F B H C, E, G

Although connectors J1 through J5 all have the same pinouts, J5 is keyed differently from J1 –J4. Each MCU column output has over current/short circuit protection, rated at 14 amps maximum – except column 5, which has a maximum of 7.5 amps (per phase).



Page 3-24

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual MCU OUTPUTS

The MCU output power ports are switchable by six (6) discrete inputs on the MCU J6 connector. One (1) discrete is for switching OFF all MCU column outputs and five (5) are for switching each column individually. The MCU provides the following types of circuit protection:

Electronic Fuses Circuit Breakers Ground Fault Interrupter (GFI) Configurable Power Management

Electronic Fuse The electronic fuse provides protection of the internal circuit breaker. Once tripped, the electronic fuse is latched until the next power up, or could be reset via a separate discrete input signal. When an electronic fuse trips, it switches off all three phases of the corresponding port to prevent the GFI from tripping due to unsymmetrical leakage currents. The trip point characteristics are configured via the Configuration Module. A tripped electronic fuse drives a discrete output, which could be used for a trip indication. Circuit Breakers The MCU has five (5) output columns, each providing 3-phase power. Each phase is protected by a circuit breaker on the MCU. A tripped circuit breaker must be manually reset at the MCU. The MCU is located in an overhead bin and would not be resetable in flight.

Ground Fault Interrupter (GFI)

Figure 3-10 Ground Fault Interrupter (GFI) The MCU also provides five (5) Ground-Fault Interrupters (GFI) for each of the output ports. The trip point can be set to levels of 30mA, 50mA, 75mA or 100mA through discrete input encoding. These two (2) discrete lines are found on connector J6.



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Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Discrete Input Discrete Input Leakage GFI 2 GFI 1 Current Open Open 30 mA Open Ground 50 mA Ground Open 75 mA Ground Ground 100 mA

Response Time 30 ms 50 ms 75 ms 100 ms

Once a GFI is tripped, it remains latched until the next power up unless it is reset via a separate discrete input. A tripped GFI drives a discrete output of the MCU, which could be used for a trip indication. Configurable Power Management To allow more power control of a connected PC-Power system, the MCU is capable of measuring the output currents. The MCU has three configurable thresholds, each resulting in a different level of control. The configuration is done via the Configuration Module, which represents a replaceable non-volatile memory containing a customized parameter set for the MCU operation in a certain aircraft. (Refer to the photograph of the configuration module on the next page.) Each output column has a data control line (on connectors J1 to J5 pin H) used to direct how the ISPC controls its ACOUs. The MCU can put each output column into one of the three (3) following states: (1) enable all ACOU’s, (2) disable all ACOU’s, or (3) disable unused ACOUs (restricted mode). The configuration module on the MCU uses a DC voltage level to define the parameters for each column. The signal characteristics of the MCU outputs are described in the table below: SIGNAL STATUS Enabled Restricted mode

MCU OUTPUT Voltage:0 to 6.5V Voltage:9.5 to 14.5V

Disabled

Voltage:17.5 to 28V

STATE Normal operation, enable all power outlets Restricted Mode: system power limit has been reached and further power outlets to be used are disabled. Power disabled, power at outlets is not available.

The configuration module is installed on connector J7. If the configuration module is missing or faulty the MCU will revert to its default parameters.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Pin Coded Address Each MCU has an address defined by address pins on connector J9. The aircraft wiring defines the pincoded address. This MCU address also defines the IP addresses for each MCU. Status Indicators Three (3) rows of status indicators are located on the front face of the MCU. Status indicators 1 and 2 are single LEDs showing power and BITE status of the MCU. Indicators 3 and 4 each have five (5) LEDs showing power and BITE status for each of the five (5) output ports. The indicators are defined in the following table:

3.2.3

STATUS INDICATOR 1

FUNCTION

CONDITIONS

Power State

2

General BITE

3

Port Power State

4

Port BITE

Off = no input power Flash = 1 or 2 phases present On = 3 input phases present Off = fatal BITE fault Flash = minor BITE fault On = normal operation Off = no output power On = all output phases present Off = output BITE fault Flash = electric fuse or GFI tripped On = normal operation

Power Wall Disconnect Box (PWDB)

The PWDB is actually a cable assembly which on one end connects to one of the output columns on the MCU and the other end is a disconnect bracket. The PWDB splits one output column from the MCU into two different columns (or strings) of SEBs and rotates the power phases for each of the SEB columns. The PWDB is often supplied by the airframe manufacturer.



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Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 3.3 3.3.1

SEAT GROUP COMPONENTS Seat Electronics Box (SEB)

Figure 3-11 SEB (Seat Electronics Box) The Seat Electronics Box (SEB) is a seat-end component of the iSeries system. The SEB provides audio/video entertainment, personal external audio/video source interface and laptop connections. The SEB distributes broadcast audio/video from the RF network, and digital interactive audio/video from the 100Base-TX network. Each SEB supports up to three seats and up to 10 SEBs may be daisy-chained in columns. The SEBs main functions are: Audio/Video demodulation Passenger Address (PA) audio distribution Decompression mode Audio volume control SVDU Data Routing Laptop Computer Power Laptop Computer RJ45 interface Passenger Interface (through PCU) BITE function Audio/Video Demodulation The SEB tunes and demodulates broadcast audio and video from the RF network. The SEB video tuning bandwidth is 157.25 to 799.25 MHz. The actual number of available video channels is aircraft configuration dependent. The broadcast video is distributed to the SVDU in the NTSC composite video format, RS-170 compliant. The output impedance is set at 100 Ohms ± 5%. The broadcast audio is amplified and distributed to the audio jack or ANR Jack. The audio power delivered to each 300-Ohm transducer element of the EJM is 75-mw minimum at SEB maximum volume setting. The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Passenger Address (PA) audio distribution The SEB detects activation of the PA output of the AVC and distributes PA audio to the PAX in its seat group. It has a dedicated FM tuner that is always tuned to the PA channel (88.1 MHz). It detects the 19 KHz tone overlaid on the PA audio signal. This is the tone used in radios to indicate the presence of a stereo signal. When the tuner detects the PA tone, it switches the output audio MUX to select the PA Tuner output and pass the PA audio to the audio jack in each seat. During PA, the SEB discards all keystrokes and volume up/down, audio volume control is limited to a predefined range, and a << Passenger Announcement in Progress >> screen is displayed on each attached SVDU. The SEB returns to the previous operating state when PA keyline is de-asserted. RF Input Board

Output Board

Processor Board

Ethernet

3 ports

ENET Dropout

J2 RF Out

8-port 100BaseT Switch

Magnetics

Magnetics

Video

Relay

MII

Ethernet

3 ports

Magnetics

Video

PCI Bus

Ethernet

PS BITE

C o u p l e r

R F

Video

64MB Max. SDRAM

A M P

3-port USB Hub

32MB Disk on Chip

Aud In

J 7 Demodulator

J1

Ext Aud Ext Vid

B

Ext Aud Ext Vid

C

Seat A Tuner, Audio/Video Demodulator/Mux

uP

Combiner /Splitter & AGC

J6

Seat B Tuner, Audio/Video Demodulator/Mux

3-Seat Audio Processor with Audio Mux

USB/5V PCU Aud L & R Ethernet LT USB/5V PCU

A

B

USB/5V PCU Aud L & R

C

SVDU/VDU-A 32VDC

115VAC, 400Hz, J11 3 phase

Fuse

115VAC, 400Hz, J10 3 phase

Fuse

115VAC, 400Hz, 3 phase

Fuse

J9

Ethernet LT

Aud L & R Ethernet LT

Seat C Tuner, Audio/Video DemodulatorMux

Ext Aud Ext Vid

C

Ext. BITE

ENET

RF In

B

Aud In

PC Subsystem PPC405

A

A

Aud In

SVDU/VDU-B 32VDC

PS Module

SVDU/VDU-C 32VDC 32V to 3.3V DC-DC Converter

32V to 5V DC-DC Converter

32V to 12V DC-DC Converter

Rectifier & PFC

PTC

AC Input Board

Figure 3-12 SEB Functional Block Diagram The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Decompression mode The SEB detects the system Decompression State from the Heartbeat Message sent by the AVC, and enters Decompression Mode. SEB decompression mode operations are defined as: • •

All passenger operations are stopped. SVDU backlight power is turned off

The SEB exits from Decompression mode by power on reset, or by detecting the system Idle State in the Heartbeat Message. Audio volume control The SEB provides audio volume control. At the maximum volume setting, audio output to the RAJ is calibrated to give out 75 mW RMS into each 300 Ohms transducer (1 kHz sine wave). The audio volume control provides 32 attenuation steps. Each step is a 2 dB change for a total of 64 dB change. Audio volume control may be limited during PA operation. SVDU Data Routing The SEB performs data transfer between the 100Base-TX upstream ports and the SVDU downstream ports. Data can be transferred in both half or full-duplex modes.

Figure 3-13 Typical under-seat installation Laptop Computer Power The SEB passes the 115 VAC, single-phase 400 Hz power and control signal to the ISPC via the J3 connector. Power is routed directly from the J1 input connector to J2 and J3 output connectors with no electronic components in between. The ISPC then conditions the power for the laptop computer. Laptop Computer RJ45 Interface



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Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual The SEB provides a RJ45 port for laptop computer connectivity. The SEB receives the 100Base-Tx format and forwards it to the SEB upstream ports. Likewise, downstream data to the Laptop computer is sent via the SEB. This data communication allows passengers with an interface-supporting capability to access the Internet or Intranet activities. This feature is not yet software enabled. Passenger Interface Up to three passengers, via passenger controller (DPCU-t, DPCU, and DPCU), are able to control the services provided by the SEB. Passenger control commands include volume up/down, channel up/down, Attendant Call/Reset, Reading Light On/Off, Audio/Video select and On Demand services control. The controller receives five-volt power from the SEB with a maximum current draw of 200 mA. Communications with the SEB complies with the Universal Serial Bus (USB) specification rev 1.1. The transmission medium is one twisted-pair cable connected in a star topology. The SEB operates in this network as a three-port hub and behaves as a host. BITE Function The SEB performs intrusive and non-intrusive tests. Intrusive tests are performed when commanded by the host. Non-intrusive tests are performed periodically during normal operation. Non-Intrusive Test The SEB periodically performs non-intrusive tests that monitor SEB status in flight to verify fault-free system operation. Should a fault be detected, it is recorded in non-volatile memory (NVM) for later investigation on-board and in the workshop. Non-intrusive tests include the following: Main power output lines (3.3, 5 and 12 VDC) within ± 10% tolerance PCU communication port status VDU communication port status Upstream port status Processor operational status PA status Decompression status Intrusive Test The SEB performs intrusive tests initiated from the iCMT when the aircraft is on the ground to identify failures and to allow a speedy system return to service after completion of maintenance actions. Intrusive test shall include the following: All non-intrusive tests Broadcast audio signal availability Broadcast video signal availability Power-On Self Test (POST) The SEB performs a power-on self-test (POST) on initial power-up or after a long power interrupt. When there is no confirmed failure, the unit becomes operational in approximately 3 minutes following the establishment of the power supply. POST consists of the following tests: All tests listed in the non-intrusive test section. Main processor memory test. The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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Application memory content integrity test.

SEB POWER CONNECTORS, J1, J2 & J3 Pin Number

Signal Description

Notes

1

115VAC Phase

2

115VAC Phase

3

115VAC Phase

4

Neutral

5

Passed-through from J1 to J2 and J3.

6

Chassis ground

7

Shield (ground)

In-seat Power Systems Communications Redundant Chassis ground

Input Data Connectors: J4 & J5 External Audio/Video Connector: J6 In Seat Connector: J7



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Apr 2008


Smart Video Display Unit (SVDU)

The 10.6-inch SVDU is installed in Business Class, and the 8.9-inch SVDU is installed in Economy Class. It contains a color Flat Panel Display with electronics that receives power, NTSC (M) video, and Ethernet data (MPEG-1/MPEG-2) from the SEB. The broadcast video data originates in the AVC, the DSU AM6-12, or the DVD Player.

The SVDU is composed of three major components: an LCD with backlight, an Interface PCBA with a backlight inverter power supply and a Processor PCBA. The SVDU is equipped with a local brightness control. SVDU major functions: Brightness Adjustment NTSC (M) Video input Ethernet MPEG Video Entertainment Menuing Backlight Inverter BITE Brightness Adjustment The SVDU has a Brightness Up/Down Control button to the side of the LCD. A Brightness Bar OSD is displayed temporarily when either of the buttons is pressed. Video Input The SVDU accepts an NTSC (M) composite video signal (RS-170 compliant) and MPEG-1/MPEG-2 Ethernet streaming video routed through the SEB from the DSU AM6-12, which it converts to RGB format for display on the LCD. The input impedance for both is 100-ohms differential. The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Backlight Inverter The SVDU has a backlight inverter to operate the LCD lamp. The backlight inverter is a DC-AC converter, which converts 12 VDC from the voltage regulator to 350 VRMS nominal. BITE The SVDU provides basic processor, RAM and Flash Memory tests. In addition, the SVDU provides a temperature sensor for monitoring the main processor’s temperature.

Figure 3-14 SVDU Functional Block Diagram



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Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Hardware Description STPC Consumer II Processor The heart of the SVDU is an STPC Consumer II Processor, which contains a 90MHz fifth-generation x86 Processor Core, an SDRAM controller, a graphics subsystem, a video pipeline, and support logic including PCI, ISA, Local Bus, and IDE controllers with standard I/O interfaces. Also included is an integrated Digital Video Input Port. Memory 512 Kbyte Flash EEPROM 128 Mbyte of SDRAM (Synchronous Dynamic Random Access Memory) 128 Mbyte of Disk-On-Chip (DOC) MPEG Decoder The SVDU contains an MPEG High Performance Video/Audio Decoder capable of both MPEG-1 and MPEG-2 video and audio decoding. This includes Video Decoder, Audio Decoder and a hardware MPEG-2 Transport De-multiplexer. Features include video/audio synchronization, error detection, concealment, and notification. The MPEG Decoder also provides On Screen Display (OSD) and Closed Caption capability. Video Decoder NTSC video decoding to ITU-656 digital video capability includes horizontal and vertical video scaling for randomly sized windows. The NTSC decoder provides Closed Caption capability. 10/100BaseT Ethernet Interface The SVDU provides one 10/100BaseT Ethernet port supporting communications with other LRUs in the system.

Audio Decoder The integrated Audio Codec decodes the audio into right and left stereo channels. The MP3 Audio Decoder decodes compressed MP3 audio files by using an MPEG-1, Layer 3 decoding algorithm. The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Power-on Reset and Voltage Monitor This device provides a reset signal to the microprocessor at power-on and when either the +2.5 VDC, +3.3 VDC or +5 VDC supply voltages drop by 5%. Voltage Regulator The SVDU receives unregulated 32 VDC from the SEB then converts it to +2.5 VDC + 5%, +3.3 VDC ± 5%, +5.0 VDC ± 5%, and +12 VDC + 5% regulated, used by the LCD and the PCB electronics, and +12 VDC ± 5% regulated, used by the backlight inverter. Backlight inverter The SVDU has a backlight inverter to operate the LCD lamp. The backlight current monitor and the microprocessor operate the ON indicator. The backlight inverter is a DC-AC converter, which converts the 12 VDC to 535 VRMS nominal. LCD Resolution The SVDU provides a resolution of 800 x 600 pixels (SVGA). LCD Controller The SVDU provides a Thin Film Transistor (TFT) panel controller that converts analog VGA signals from the STPC Consumer II to a TFT panel output with one pixel per clock and resolution to (800 x 600). The controller supports 3, 4, 6 or 8 bits per pixel up to 16.8 million colors. Basic Specifications Power Weight Dimensions Vertical Viewing Angle Horizontal Viewing Angle

15 Watts max. 3.9 lbs. (4.5 lbs for 10.4”) 9.81”W x 7.65”H x 1.60”D (8.4”) 10.83”W x 8.15”H x 1.60”D (10.4”) Up (viewed from above): 35 degrees Down (viewed from below): 23 degrees 50 degrees left and right (w/o privacy filter)



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Apr 2008


Digital Passenger Control Unit (DPCU)

The DPCU is installed in all Business Class and Economy Class seats. Each DPCU provides the passengers the means to control i4000 entertainment services at the seat. The unit is mounted in a cradlebase assembly compatible with aircraft seats. All buttons and indicators are illuminated to enable viewing in all levels of ambient light.

The DPCU is used in conjunction with Passenger GUI screens that are displayed on the SVDU. The DPCU provided to each passenger will allow the passenger to use the unit for Navigation, Selection, Channel Browsing, and Application Controls. DPCU functionality includes: Volume up/down Channel up/down Mode Selection for Broadcast audio / video, and Moving Map Liquid Crystal Display (LCD). Alphanumeric LCD Display The 2-digit LCD has a limited alpha character set to display the Entertainment System channel number, PA mode and other system information. Numeric characters from 00-99 can be displayed. A VIDEO enunciator on the LCD is activated when the video entertainment mode is selected. An AUDIO enunciator is activated when the audio mode is selected. The letters “PA” are displayed during public address announcements. A “00” indicates inactive communications with the SEB, whereas a “01” verifies active communications.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual USB Interface The USB Interface provides all real-time communications between the DPCU and the SEB. The data format is a Thales-IFS proprietary protocol with DLE insertion using the USB version 1.1 protocol communications interface. 3.3.4

Intergrated Noise Cancelling Audio Jack

Integrated Noise Cancelling Audio Jacks are installed in the Business Class. Single-pin audio jacks are installed in Economy Class. The noise reduction system consists of an integrated noise reduction module that includes the electrical circuits and electrical jacks in a single module. The unit is designed to operate with special noise reduction headsets. When used in conjunction with the special headset, the module provides a reduction of low frequency jet aircraft and other repetitive background noise. Attenuation performance is 12 dB (minimum) between 150 and 400 Hz, with 0 dB attenuation at 50 Hz and 1.2 kHz respectively. The Noise Cancelling Audio Jacks will interface with two prong noise reduction headsets (2.5mm and 3.5mm) or standard single prong headsets. The type of headset used will be detected by the audio jack. If a noise reduction headset is detected, the noise reduction function is automatically invoked.

Output Power Power output per ear is 33 mw nominal on 300 ohm, normal nr mode. If the voltage to the nr is interrupted, the nrm connects the input audio to the headset jacks. The path resistance is nominally 25 ohms. System Interconnect The NRM interface connector P1 is a six-position, single-row, male connector that interfaces to the SEB through the seat harness wiring. The NRM receives power and two channels of audio from the SEB. Control I/O The Control I/O line is always a logic low (or open-circuit), which enables the ANR function. If the headset is ANR type (with microphones), a square-wave is superimposed on the control line. If a conventional headset is in use (without microphones), no square-wave is present and the Noise Reduction mode is automatically disabled. The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Microphone Sensing MIC_L: The left microphone input senses that a microphone is connected to it, or that the jack is open. A shorted jack is the same as a microphone present. MIC_R: The right microphone input senses that a microphone is connected to it, or that the jack is shorted. An open jack is the same as a microphone present. Noise Reduction Jack The Noise Reduction Jack is differentiated from the normal audio jack by two different sized pin jacks. These polarize the jack such that the Noise Cancellation headset cannot be inserted backwards. One jack has the stereo audio signals to the headset (3.5 mm), while the other has the ambient noise audio signal from the headset microphone (2.5mm).

3.3.5

In-Seat Power Converter (ISPC)

The In-Seat Power Converter (ISPC) is designed to provide a constant voltage source to the Personal Electronic Device (PED), normally a laptop computer, via an AC-Outlet Unit (ACOU) which is located in the seat armrest. The ISPC is installed beneath one of the seats in a seat group. The ISPC operates on 115 VAC, 400 Hz, single-phase power received from the MCU via a Power Wall Disconnect Box (PWDB) and a Seat Electronics Box (SEB). The ISPC is directly cabled to the output connector of the SEB located in the same seat group. One ISPC supplies up to three (3) ACOUs with nominal 110 VAC, 60 Hz single-phase power via its Output Connectors (J3, J4, and J5) Continuously monitoring the output power, the ISPC connects or disconnects its associated ACOUs according to the actual power status. Unless all the criteria for safe operation are met, the ISPC will disconnect power to one or all of the Outlet Units. The ISPC has provisions to control a PED Power-in-use Indicator (PPUI), which is a Blue LED located on the aisle-side of each seat group. When illuminated, the PPUI indicates that a PED is connected to an ACOU and is drawing power.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Functional Description The main functional groups are: Input Power Conversion – Converts the 115 VAC, 400 Hz input power to 110 VAC, 60 Hz output power Over-current and Short-circuit Detector – Detects excessive current draw, reports to microprocessor and shuts down only the over-current output. GFI Detector – Detects a Ground Fault and turns off all outputs as a safety precaution. Outlet Current Measurement – Measures output current for each port and reports results to microprocessor. Over-temperature Detector – Measures internal temperature and reports to microprocessor which will shut down the ISPC if thresholds are exceeded. 3.3.6

Alternating Current Outlet Unit (ACOU)

The ACOU is the outlet receptacle that provides power intended for a passenger’s laptop computer. It accommodates either the US-type standard three-pin power plug or the European-type standard two-pin power plug. The ACOU has mechanical child protection features to prevent shock due to misuse of the outlet, such as inserting foreign objects. It also has integrated sensors to release power only if a plug is engaged. The button (see photo) in the center of the outlet must be pressed by the plug body at the time the tines are inserted for power to be released.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual The ACOU is the outlet receptacle that provides power intended for a passenger’s laptop computer. It accommodates either the US-type standard three-pin power plug or the European-type standard two-pin power plug. The ACOU has mechanical child protection features to prevent shock due to misuse of the outlet, such as inserting foreign objects. It also has integrated sensors to release power only if a plug is engaged. The button (see photo) in the center of the outlet must be pressed by the plug body at the time the tines are inserted for power to be released. The ACOU has a multicolor LED indicator to give a visual indication of the system status as shown in the following table: ACOU Status Indicator LED LED INDICATION GREEN AMBER RED OFF OFF

SYSTEM STATUS System Power ENABLED (Power Available) Temporary No Power Available (Power Limitation) System Power DISABLED (via MCU or Aircraft Control) System Power Not Available (A/C Power to MCU Disabled) BITE Indication of the respective ISPC due to an internal Fault

PPUI (PED Power-In-Use Indicator)



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual The PPUI is a BLUE LED indicator that is mounted on the aisle side of each Business Class seat group. It is located such that it is easily visible by the Flight Attendants and indicates whether an Electronic/Electrical device is connected to the Outlet Unit and power is being drawn. The PED (Personal Electronic Device) Power-In-Use Indication is a JAA/FAA Requirement for In-seat PC Power Systems. Note: If the PPUI fails the ISPC will shut down all of its power outputs as a safety precaution. When troubleshooting, if an entire seat group loses power, first try replacing the PPUI before replacing the ISPC.



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SEAT INTERCONNECT DIAGRAMS

The following diagrams illustrate the various seat group configurations as installed in the NACIL(I) A321.

Figure 4-1 NACIL(I) A321 Seat Group Configuration Diagram



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SEAT INTERCONNECT DIAGRAMS – BUSINESS CLASS

The following in diagrams are representative of the LRUs previously discussed, as installed in the Business Class seat groups. The following components are the primary LRUs illustrated:

SEBs SVDUs Audio Jacks DPCUs ISPCs ACOU PED In-use Indicators

Figure 4-2 Business Class - Front row LH (-501) & RH (-502)



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Figure 4-3 Business Class - Standard LH (-503) & RH (-504)



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Figure 4-4 Business Class - Last row LH (-505) & RH (-506)



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SEAT INTERCONNECT DIAGRAMS – ECONOMY CLASS

The following in diagrams are representative of the LRUs previously discussed, as installed in the Economy Class seat groups. The following components are the primary LRUs illustrated:

SEBs SVDUs Audio Jacks DPCUs

Figure 4-5 Economy Class - Front row LH (-501)



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Figure 4-6 Economy Class - Front row RH (-502)



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Figure 4-7 Economy Class - Standard LH (-503) & RH (-504)



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Figure 4-8 Economy Class - Last row LH (-505) & RH (-506)



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Figure 4-9 Economy Class - Row 19 LH (-507)



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Figure 4-10 Economy Class - Row 19 RH (-508)



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Figure 4-11 Economy Class - Rows 8 & 21 LH (-509)



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Figure 4-12 Economy Class - Rows 8 & 21 RH (-510)



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Figure 4-13 Economy Class - Rows 7 & 20 LH (-511)



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Figure 4-14 Economy Class - Rows 7 & 20 RH (-512)



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MAINTENANCE FUNCTIONS

Software Loading and Content Management at the airline location are important steps in assuring a successful onboard passenger experience. There are step-by-step procedures that describe methods for loading software and content, and various functions that allow maintenance personnel to check and troubleshoot the IFE system. If there are any questions about this procedure, please contact your local Thales Representative or call the Thales Content Management Center. Software Loading is a two-phase process in which the code is first uploaded from the CD-ROM on the PDL to the IFE system and then downloaded to individual LRU types or individual LRUs. When downloading software, it is important to carefully verify that the correct files to be downloaded were successfully uploaded and that all of the necessary files are selected. Content Management is an ongoing procedure that is required each time the airline updates its onboard entertainment program. The content to be loaded has been compiled and tested at the Thales Content Management Center in Irvine, California. The equipment needed to perform Software Loading and/or Content Management includes the following: A Portable Data Loader (PDL) Removable Hard Drive or Software Disc Ethernet Cable The following is representative of typical maintenance actions during the Software and/or Content Loading, per a Service Bulletin or AMM procedure. Always refer to the specific Service Bulletin and/or Operator Interface section of the AMM for information regarding the proper procedures.

5.1

PORTABLE DATA LOADER (PDL) SETUP

The PDL is a rugged computer that is designed for easy transit to and from the aircraft. Once the PDL is received the first time, it should be maintained in a safe, locked location when not in use. There is no need to mail it back to Thales unless service is required. Anytime shipping is required, make sure to send it in its black transit case. A removable hard drive and CD/DVD drive are located on the right side of the PDL.



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5.2 5.2.1

SOFTWARE DOWNLOADING Software Download Procedure – PHASE 1

The Phase 1 download process consists of loading selected software components from the distribution media, normally a CD, to the system download server. The Phase 1 download process is used to declare the correct (baseline) software configuration for the aircraft. All subsequent maintenance actions (Download and Configuration Check) use the configuration list created by the Phase 1 download process as the aircraft configuration baseline. From each media, maintenance personnel can select either specific software component (by part number) or groups of software components called packages to be loaded onto the download server. The download server maintains the correct configuration database based on the most recent Phase I software loaded in this manner. Maintenance personnel are provided with the Phase 1 Current Software Configuration screen which identifies the software components LRU, software name and software part number. This The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual list should be verified against the configuration documentation maintained by the airline. components should be deleted.

Extra

When a download is initiated by maintenance personnel, all aircraft loadable software present in the correct configuration list for the selected LRU type is loaded. If an LRU contains a software component which is not on the list, it will be removed from the LRU. If an LRU is missing a software component or has a different component from the list, it will be loaded by the LRU from the download server.



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Software Download Procedure – PHASE 2

The Phase 2 download process uses the correct configuration list created by the Phase 1 download to install the proper software into each system LRU. The Phase 2 download must be performed on each LRU type independently. To perform a Phase 2 download, the maintenance person selects an LRU type to be downloaded and initiates the process. Progress is presented and the user is informed when the process is complete. The system provides for a download on one LRU or for all LRUs of a specified type. The Phase 2 procedure downloads software from the DSU AM6-12 hard disk drive to selected LRU processors. The procedures for downloading to the DSU AM6-12, AVC, ADB, iCMT, IP Sequencing, and SEB are each shown separately. This procedure can be performed from the PDL or the iCMT.

Phase 2 Software Download to DSU AM6-12



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Phase 2 Software Download to AVC

Phase 2 Software Download to ADB



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Phase 2 Software Download to iCMT



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Phase 2 Software Download to SEB

At PDL, from LRU Load screen, select SEB and ALL SELECTED LRUs.

Caution: After First download, all files will not be displayed. Dowload to SEB must be performed two times to ensure all files are displayed.



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CONFIGURATION CHECK



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IP SEQUENCE

In the TopSeries IFE system, the SEBs are not hard-coded or hard-wired with an IP address to indicate their positions within the system. Since each SEB needs to have a unique Ethernet address associated with its seat-group number, the IP Sequencing system was developed. An Ethernet is basically a highspeed LAN. Each Ethernet-capable LRU in the system contains a configuration data file that defines the “map” of all the LRUs. The SEB data include each SEB’s position within which string, connected to which port of which ADB, the seat-group number of that position and the Ethernet address of that seat-group. The IP Sequencing uses the configuration data file to allow each SEB a means of determining its position within the network. Each SEB “passes through” the Ethernet interface to the next downstream SEB in its string, so that in normal operation all the SEBs are connected to the Ethernet network. Each SEB is also equipped with a software-controlled output switch that it uses to disable communications to the downstream LRUs.

When IP Sequencing starts, the ADBs command all the SEBs to set their output switches to the OFF position. The ADB can then communicate with only the first SEB on each string, so it tells the SEB on string one that it is the first position on the first string. The SEB checks the configuration data file to determine its seat group location and its Ethernet address. The ADB then tells the SEB to turn on its output switch, so that it can now talk to the SEB in the second position on string one, and gives that SEB its location, and then turns on its output switch. This continues for each SEB in each string until the entire system is sequenced per the configuration data file. IP Sequencing must be performed whenever an iCMT, SVDU or SEB is replaced. During the IP Sequence process an appropriate address is given to each LRU. The aircraft configuration database is used to determine these addresses. IP Sequencing is a disruptive process in which system components stop communicating to each other for significant periods of time and after which aspects of control and response may be quite different.



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When IP Sequencing is complete, the operator can select an iCMT screen that presents a graphic representation of the results to facilitate troubleshooting.



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CONTENT MANAGEMENT

Content is the entertainment media chosen by the airline to include in the services provided for the passengers. Key terms used in describing the content loading process are defined as follows: Content Download – the process of transferring content from a carry-on loader (like a Portable Data Loader or PDL) to the system. One copy of each required content item is transferred from the loader to one of the system servers. Once one copy has been transferred, the carry-on loader can be disconnected and removed as the content will be distributed to the required servers using the Content Crossload process. Content Crossload – the process of distributing content between multiple system servers. The Content Inventory List (CIL) specifies the content that is desired in each system server. Content crossload uses the CIL to determine the content each server needs and manages the server-to-server transfer (crossload) of this content. Content Inventory List – an ASCII text file that defines the content that is desired in each system server. Active Content – the system supports the loading of more content than is currently to be used by the system. To accomplish this, each content entry in the CIL contains a “scope” field that specifies the parameter of use for the content item. In a typical application, the “scope” represents the month or months of use and the Active selection indicates the current month. Scope – a term used to determine the range of use of a piece of content. Some content may be identified as use forever (such as a safety briefing), some content may be identified as being usable for a specific month, and some content may be identified as being usable for multiple months. Along with the ability to select the “Active” characteristic, this permits a superset of content (such as multiple months) to be loaded onto the system.



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System Content Loading Procedures

1. At PDL, insert media CD/DVD into CD/DVDROM Drive and open Windows Explorer.

1.1

2. In Windows Explorer, transfer files XXX.cil from CD/DVD to folder c:\Thales\Data\Cils of PDL. 3. At PDL, open a browserwindow and access the following URL: http://172.17.1.97/thales/dnldindex.htm 4. At Download Screen, select Update Content.

2.1

5. At CONTENT LOADING MENU Screen, select Content Inventory Selection.

5.1

6. At Collecting Available Content Inventory Lists Screen, observe Progress Bar.

6.1

7. At Content Inventory Selection Screen, select content desired by clicking in small circle to left of Description Column. 8. Press OK. 9. If Active Content Selection Screen is displayed, select desired content and press OK. 10. At Content Inventory Confirmation Screen, select YES, I AM SURE. 11. At Please Wait While the Servers Process the New Content List Screen, observe Progress Bar. 12. At Content Loading Summary Screen, observe Content Flight Readiness Status Window. 13. At Content Loading Summary Screen, observe Current Activity Window. 14. Observe engineering view of crossload pages. 15. At Content Loading Summary Screen, observe Active Content Progress Bar in Content Download Status Window.

Verify media CD/DVD is recognized by operating system. NOTE: Steps 1 and 2 may be ignored if PDL already includes content in its hard drive. Verify that XXX.cil is present in CIL Directory of PDL.

3.1

Verify Download Screen is displayed.

4.1

Verify CONTENT LOADING MENU Screen is displayed. Verify Collecting Available Content Inventory Lists Screen with Progress Bar is displayed. Verify when list of available content inventory is completed, Progress Bar is full and system automatically advances to Content Inventory Selection Screen.

8.1

Active Content Selection Screen may be displayed. 9.1 Verify Content Inventory Confirmation Screen is displayed. 10.1 Verify Please Wait While the Servers Process the New Content List Screen with Progress Bar is displayed. 11.1 Verify when Content List processing is complete, Progress Bar is full and System automatically advances to Content Loading Summary Screen. 12.1 Verify all servers are reporting. 13.1 Verify Download In Progress. 14.1 In engineering view of crossload pages, wait until all files are green. 15.1 When Progress Bar reaches 100%, Content load is complete.



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Content Menu Screens

Content Loading is managed as one of the maintenance “Download” functions. Content loading is accessed via the “Update Content” button on the maintenance “Download” screen. The Content Loading Menu screen identifies the name of the currently selected Content Inventory List (Current Selection) and the parameter for current active content (Active:). On the Content Loading Menu there are four (4) basic selections and a “Back” button to return to the Download menu. Content Inventory Selection – a selection that permits the operator to specify or change the selected Content Inventory List (CIL). This is used when the operator wants to change the definition of the content to be loaded into the system. Change Active Selection – a selection that permits the operator to specify the subset of the loaded or specified content that is to be used on current flights. This is how an operator would indicate that preloaded content (like the next month’s content) is now to be used. While this illustrates a process by which the active selection is changed manually, the system is also capable of changing the active selection based on an aircraft event or combination of events (such as month change while on the ground). Content Loading Status – a selection that permits the operator to view information on the status of transferring content from one or more content loaders like a Portable Data Loader (PDL) and the status of distributing this content to the appropriate system servers. Content Loading Control – an engineering level selection that permits the operator to view and change the features of content loading. These included automatic and manual controls as well as a variety of defaults that can be set up. Content is managed through the use of a file called a Content Inventory List (CIL). The system can have a variety of CILs loaded and available. Only one CIL may be selected at any point in time. The CIL drives the content loading and crossloading process. Content that is not identified in the currently selected CIL is typically deleted from the on-board servers. The Content Download process attempts to obtain one copy of the content identified in the CIL and load it into one of the on-board servers. The Content Crossload process identifies the Content that is to be loaded in each server and seeks to transfer the content from wherever it can be found into the server.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual When the “Change Inventory Selection” selection is made on the Content Loading Menu, the system looks to all servers and potential portable data loaders for available Content Inventory lists. While this search is being performed a progress bar is presented with the title: “Collecting available Content Inventory Lists”. When the collection is complete (about 30 seconds) a Content Inventory Selection screen is presented. The Content Inventory Selection screen identifies the currently selected CIL by title and check in the associated check-box. The screen also indicates the subset of the content that is active. A list of all CIL files that have been found in the system is presented in tabular form (see Figure 3.1). For each CIL, an entry is provided containing the Description (obtained from the file), filename, and number of servers containing the CIL. The currently selected CIL is indicated with a check in the associated check-box. The user can use the associated check-box to select a different CIL. Once a new CIL has been checked and the user presses the OK button, the system starts the process of making the system consistent with the new CIL. Since one of the goals of the content loading process is to make the aircraft operational as fast as possible, it is important to know if the content is divided into subsets and if so, which of the subsets would be Active. Upon exiting the Content Inventory Selection screen with an OK, the Active Content Selection screen illustrated is presented. This screen reflects the newly selected CIL under Selected Content and provides a check-list table of the subsets of the content that can be made active. The user must select one of these subsets as Active and press OK to complete the specification of a new CIL for use.

Since the selection of a new CIL can have such a significant impact on system servers, any change to the CIL is followed by the Content Inventory Confirmation menu. Once the user selects “YES, I AM SURE” confirming the change in CIL choices, a screen is presented with a progress bar and titled “Please wait while the servers process the new content list”. During this process, the system makes sure that all servers have a copy of the newly selected CIL and if appropriate, recognize the subset of the content that is to be Active. Once the data is collected, the content loading process begins and a Content Loading Summery screen is presented.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual As an aid in determining the success of a change in the active content selection, each entry has an indication of the load status of the corresponding subset of content. In the above example both the Nov and Dec subsets are 100% loaded. If some of the content were either not loaded or had not completed the appropriate cross-load, the appropriate percentage would be reflected. Content Loading Summary Screen The primary interface for determining the status of content in the system is illustrated in the Content Loading Summary Screen. This screen is intended to provide to the user all of the high-level status information. Further details are available using the “detail”, “engineering”, and “PDL” selections in the upper left of the screen, but this information is intended for engineering level experts.

The Content Flight Readiness Status window reflects the status of content identified as needed for immediate use (Active Content). It indicates (1) the number of servers that have all content necessary for flight, (2) the number of servers that do not have all of the content necessary for flight, and (3) the number of servers whose status is unknown because they are not currently reporting. A RED/GREEN indicator in the upper right hand corner of the window is GREEN when all active content is available in all servers. The Content Download Status window reflects the overall status of loading content from the PDL. The intent of this window is to indicate to the operator when the PDL is no longer needed (and could therefore be disconnected or removed). It provides one progress bar for obtaining Active Content from the PDL and a second progress bar for obtaining Inactive Content from the PDL. A RED/YELLOW/GREEN indicator in the upper right hand corner of the window is YELLOW when all active content is fully loaded from the PDL and GREEN when all active and inactive content are fully loaded from the PDL. The Content Crossload Status window relects the overall status of distributing content among the system servers. The intent of this window is to indicate to the operator when content distribution is complete. It provides one progress bar for the distribution of Active Content to all servers and a second progress bar for the distribution of Inactive Content to all servers. A RED/YELLOW/GREEN indicator in the upper right hand corner of the window is YELLOW when all Active content is fully distributed and GREEN when all Active and Inactive Content is fully distributed among the servers.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual The Current Activity window indicates whether any content transfer activity is in progress. The Download field indicates whether there is any data transfer activity occurring with the PLD and the Crossload field indicates whether there is any data transfer activity among the servers. A RED/GREEN indicator in the upper right hand corner of the window is GREEN when there is activity underway or activity is complete and all content is available (active and inactive). 5.5.3

Detailed Information on Loading

In the upper left-hand corner of the Content Loading Summary screen are a number of buttons from which further information on Content loading can be obtained. Each of the three selections; detail, engineering, and PDL, are appropriate for use by expert or engineering level personnel. The overall menu flow from the Content Loading Summary screen to the various detail screens is illustrated.



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5.5.3.1

Detail

The Content Loading Detail screen is illustrated below, and shows the load status of each system server. A window is provided for each server indicating the load progress for both Active Content and Inactive Content. For Active Content the progress bar indicates the content that has been transferred in GREEN The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual and the content that has not been transferred in RED. For Inactive Content, the progress par indicates the content that has been transferred in GREEN and the content than has not been transferred in YELLOW. If there is no Inactive Content specified in the CIL, the Inactive Content field is black with N/A as the percentage transferred. A user may select even more detail on a specific server by selecting the window for the desired server. When the server selection is made, the server details screen is presented. Note that the server details screen provides color coded progress bar with GREEN representing the percentage transferred and RED representing the percentage yet to be transferred. Also available is the actual number of bytes transferred and the number of bytes to be transferred.

5.5.3.2

Engineering

The Content Loading Engineering Detail screen is illustrated and indicates the load status of each item of content and its distribution among the system servers. A check-box matrix is presented with each item of content identified on the right-hand side of the matrix and the server number indicated across the top of the matrix. Since this matrix can be quite large, navigation buttons and zoom buttons are provided on the left-hand side of the screen. A legend can also be requested which identifies the methodology used to fill in the matrix entries. The upper left-hand corner of the screen permits the user to select the other levels content loading details available.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 5.5.3.3

PDL (Portable Data Loader)

The PDL Status Page screen illustrated indicates the transfer status from each of configured PDLs. A window is provided for each PDL indicating the load progress for both Active Content and Inactive Content. For Active Content the progress bar indicates the content that has been transferred in GREEN and the content that has not been transferred in RED. For Inactive Content, the progress par indicates the content that has been transferred in GREEN and the content than has not been transferred in YELLOW. If there is no Inactive Content specified in the CIL, the Inactive Content field is black with N/A as the percentage transferred A user may select the details of the contents of a specific PDL by selecting the window of the desired PDL. When the PDL selection is made a list of the content currently located on the PDL is available for review.

5.5.4

Content Load Control Menu

The Content Load Control menu permits an experienced user to change the basic method in which the content load and crossload process operates. While the process has been designed to be capable of being automatic and operator free, there are situations in which it may be desirable for the automatic process to be suspended in favor of more detailed control. The Content Load Control Menu identifies the currently selected CIL (Current Selection: ), the subset of the content that is active (Active:), and the current control state of the load process (Current State: ). The menu also provides four (4) control choices as well as a “Back” button to return to the Content Loading Menu.



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Automatic Enable/Disable – a selection that enables or disables the automatic content load process. When enabled, a system algorithm determines whether it is permissible to perform server crossloading. It is expected that crossloading may not be desired during certain phases of aircraft activity (like when VOD services are enabled) and the automatic Enable feature invokes this level of control. Enable Load/Crossload Unconditionally – a selection that indicates to the system that Crossload should be active at all times irrespective of aircraft mode or activity. The example illustrated in Figure 6 indicates the current setting is “Enabled Unconditionally”. Disable Load/Crossload Unconditionally – a selection that indicates to the system that Crossload should be totally disabled. Engineering Control – a selection that provides access to a detailed level control screen appropriate for engineering personnel.

5.5.4.1

Content Load Control - Engineering Menu

The Content Load Control Engineering Menu provides the engineering level user detailed controls over the Download and Crossload process as well as the ability to make the changes to the process temporary or persistent. Enable Content Download – when checked permits the Download of content from the content loader/PDL. When unchecked, data will not be transferred from the content loader/PDL. Enable Content Crossload – when checked permits the servers to distribute or crossload content among themselves. When unchecked, servers will not obtain content from each other. Enable Content Deletion – when checked, permits the servers to delete any content that is not in the currently selected CIL. When unchecked, the deletion of unreferenced content is inhibited. The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Allow Loading even when VOD is Active – when checked, permits the servers to distribute or crossload content even when the system is actively providing VOD service. These changes can then be specified as temporary with the intent that they the system will revert to the previous settings on a power cycle or that the settings are permanent until changed by subsequent operator action.

5.6

TROUBLESHOOTING TOOLS

Static test is a test designed to permit maintenance personnel to observe and evaluate component performance at various locations around the aircraft. Static test is provided as a tool to address aspects of system or component performance that cannot be performed automatically. Examples of this are audio quality, video quality, video color, pushbutton operation, etc. It is also useful in troubleshooting certain interconnect problems such as misconnected seat column cables. 5.6.1

Static Tests

Currently a VOD static test is performed. This test is initiated by maintenance personnel on the iCMT. Once initiated, all Smart Video Display Units (SVDUs) are turned on and each SVDU initiates the play of a VOD program. The SVDU loops on the VOD program until the test is terminated by maintenance personnel. While Static Test VOD is active, maintenance personnel can perform the following activities: ● Evaluate video and SVDU performance through observation ● Evaluate audio performance at headset audio jack.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Static Test VOD must be terminated by maintenance personnel through action at the iCMT or by removing power from the entire system.

5.6.2

BITE Function

Since a system test can only be accurate if the system is properly configured, the first two tests are related to verifying the system is properly configured. Seat Address Verification A check is made to determine if any of the seat components have changed since the last IP Sequence. If a change is suspected, the operator is informed and provided with the suggestion that IP Sequencing should be performed.

5.6.3

SW Configuration Consistency Verification

A check is made to determine if the software configuration of all the LRUs matches the system configuration as defined by the Phase 1 download process. If the software configuration of the system doesn’t match, the operator is informed and provided with the suggestion that a software download should be performed. Once the proper configuration of the system is established, the location of faults can be properly identified with the IP Comm Testing. This verifies communication among the system components.

5.7

METHODOLOGY

Familiarize yourself with the designed functionality of the system. Whether the system has functions like Video Announcement, Boarding Music (BMM), Safety Demo, Moving Map (MMAP), or PTV, familiarize yourself with the characteristics of each function so you can differentiate between a bug in the system and a designed feature. Breakdown the system to simpler functions to help troubleshoot the problem. For example, if a single seat issue is being evaluated, visualize only the functions related to the seat. An understanding of the system architecture is important in order to accomplish the task.

5.8

SYSTEM CHECKS

At different points during the troubleshooting session, the functionality of the system will need to be checked. Use the different functions of the system to help troubleshoot a problem. Depending on the configuration of the aircraft, some of the system functions, for example Safety Demo, have VA capability.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual The VA function can be used to send video and audio to all the seats so that a quick walk through of the cabin can be performed and a quick check of all the seats made to see if they are functioning properly. Also remember to check the seats after deactivation to see if the seats return to a default state. Be aware of the audio distribution for the aircraft. For example a PA announcement uses a different path to send audio to the overhead speakers than the path to send audio to the seats. This fact will can help determine whether the problem is one LRU as opposed to another.



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TROUBLESHOOTING

6.1

GENERAL

In general, when troubleshooting a problem related to an IFE function, refer to the System Overview and System Description sections. Consider first the LRU responsible for the problematic function, and then think in terms of the systemic signal flow related to that function. If a function or group of functions is missing entirely, then it may be necessary to reboot, reload software, or replace the LRU responsible for the missing function(s). However, if the function is missing or malfunctioning in a section of the aircraft and working in other sections, then consider the Distribution LRUs and cables. Perhaps a cable has come loose from a connector? When troubleshooting data distribution problems, especially those related to IP Sequencing, an accurate “map” of the aircraft showing SEB strings and serial numbers is extremely helpful. Comparing SEB serial numbers and assigned seat group addresses to a map makes isolating a cable or SEB problem fairly easy. Without the map, much more guesswork is involved, possibly requiring under-seat inspection or LRU removal to determine serial numbers. Depending upon the function, iSeries uses different paths for audio distribution. This can be a valuable tool in troubleshooting the system if these paths are well understood. This section includes a review of Audio Distribution paths to ensure a good understanding by repair personnel. Also included is a Practical Tips section, gleaned from actual field experience. 6.2

TROUBLESHOOTING PHILOSOPHY

Troubleshooting is the practice of systematically attacking a problem until it is solved. The essential elements in troubleshooting an electronic system are:

6.3

A basic knowledge of system function. Collection of information about the problem. Definition of the problem. Try to be sure you are attacking the problem not a symptom. Evaluation of possible causes and fixes, the most probable or easiest (often the same) to the least probable or most difficult. Attempt your selected fix or fixes until the problem is resolved. Test system to insure it is repaired. Document all steps and findings. CABIN CREW DISCREPANCY

With any cabin crew discrepancy, the following troubleshooting method is recommended: Analyze the discrepancy. Be sure what you understand the problem to be is what the cabin staff observed. The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Confirm the fault reported. It could be that the fault is operator error, a misunderstanding by the reporting cabin crewmember on how the system functions.

6.4 6.4.1

BASIC CHECKS Software download

Permits software functionality for the TopSeries system to be modified using aircraft loadable software. This permits the system to be upgraded or enhanced without changing the hardware configuration of the aircraft. Software is often provided on multiple media, each of which must be loaded into the system. Software download of the system is divided into two phases: 1. Phase 1 download = installing the proper configuration of software into the download server. 2. Phase 2 download = distributing the software to the required LRUs. System operation has a certain level of hierarchy with respect to maintenance processes including download. Because of this, head-end components should be in configuration first, followed by area components, followed finally by seat components. It is also important that the database be loaded into the ADBs before an IP sequencing operation is performed. For the i3000 system, the typical order should be: 1. DSU AM6-12 2. AVC 3. ADB 4. SEB (ensure IP sequence first if SEB replaced) 5. ICMT 6. SVDU (ensure IP sequence if SVDU replaced)

6.4.2

Configuration Check

Typically runs in the DSU AM6-12. At a minimum, the system must provide configuration information on each system component, which contains aircraft loadable software. Configuration information is transferred from the system component (LRU) to the configuration server (1) when the LRU is powered up and (2) on request from the configuration server. As a minimum, the configuration information transferred from each LRU consists of the following: ● LRU part number ● LRU serial number ● LRU revision level ● LRU mod status ● Non-aircraft loadable software part numbers ● Aircraft loadable software part numbers ● Database part number ● IP address ● MAC address.



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Configuration information can be accessed from any ICMT by navigating to the Config Check maintenance screens. Configuration information can be reviewed or updated by maintenance personnel using these screen. Note that the available configuration information includes hardware configuration information as well as software configuration information. One of the first things that should be performed, during the investigation of a problem, is a Config Check on the LRU in question. If it is a system level problem then the configuration check of the Headend LRUs should be verified as well. One of the most frequent problems that plague complex IFE systems is incorrect software configuration. System software components are designed and tested to work together as a package. If there is a mixture of software components old and new there is no telling how the system will function.

6.4.3

IP Sequence

Causes each seat component to obtain a unique system address corresponding to its location in the aircraft. These addresses are established based on the way the seat components are physically connected to themselves, the Wall Disconnect Boxes (WDB) and the Area Distribution Boxes (ADBs). IP Sequencing must be performed whenever a SEB is changed (for i3000 it is also required whenever an SVDU is changed). During the IP Sequence process, each ADB provides the appropriate system address to each seat component under his control. The aircraft configuration database is used by the ADB to determine these addresses. IP Sequencing is a disruptive process in which system components stop communicating to each other for significant periods of time and after which aspects of control and response may be quite different. When IP Sequencing is complete, the operator can select a screen that presents a graphic of the results. The results are presented in the physical format in which the SEBs are connected but are identified with the aircraft location information to facilitate troubleshooting. Maintenance of an IFE system requires faults to be identified to a specific system component (such as SEB 21ABC) or interface. This requires the system components each to have a unique identification or address from which their location can be derived. Head-end components such as the DSU AM6-12, AVC and ADBs each have their addresses established through pin-coding on the LRU I/O connector. When these LRUs are powered up, their pin coded addresses are interrogated and the LRU uses the appropriate addresses for the physical location as established by the pin coding.

6.5

TROUBLESHOOTING TOOLS

Static Test is a test designed to permit maintenance personnel to observe and evaluate component performance at various locations around the aircraft. Static test is provided as a tool to address aspects of system or component performance that cannot be performed automatically. Examples of this are audio quality, video quality, video color, pushbutton operation, etc. It is also useful in troubleshooting certain interconnect problems such as misconnected seat column cables on the Area Distribution Box (ADB). The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Static Test Broadcast is initiated by maintenance personnel on the ICMT. Once initiated, the system performs the following actions: ● A broadcast video program with associated audio is started in the DSU AM6-12. ● All Video Display Units (SVDU) are turned ON. ● All seats tune to the designated video program. ● Location and Configuration information is presented on the SVDU. ● Location information is presented on the Passenger Control Unit (TPCU) LCD display. While Static Test Broadcast is active, maintenance personnel can perform the following activities: ● Evaluate video and SVDU performance through observation. ● Evaluate audio performance with a headset plugged into the audio jack. ● Confirm the seat row and letter serviced on both the SVDU and TPCU (used to confirm database and interconnect wiring). ● Confirm the seat row location for seatback SVDUs. ● Verify database part number on the SVDU display. Static Test Broadcast must be terminated by maintenance personnel through action at the ICMT or by removing power from the entire system. BITE (Built-In-Test) can only be accurate if the system is properly configured, the first two tests are related to verifying the system is properly configured. Seat Address Verification is a check is made to determine if any of the seat components changed since the last IP Sequence. If a change is indicated, the operator is informed and provided with the suggestion that IP Sequencing should be performed. SW Configuration Consistency Verification is made to determine if the software configuration of all the LRUs matches the system configuration as defined by the Phase 1 download process. If the software configuration of the system doesn’t match, the operator is informed and provided with the suggestion that a software download should be performed. IP Comm Testing checks the communications between the system components is exercised and verified.

6.6

METHODOLOGY OF TROUBLESHOOTING

Find out the channel map definition for the system, each aircraft configuration could potentially be different. This will define the number of audio channels for audio mode and the number of channels for the video mode. The channel map table will also define the source of the channels, whether it is generated from a certain video client in the DSU, or it comes from a VTR, etc. Get familiar with the designed functionality of the system. Whether the system has functions like Boarding Music (BMM), Safety Demo, Moving Map, Services, Main Screen, VTR, Pre-Recorded



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Announcement Machine/Message etc; get familiar with the characteristics of each function so you can differentiate between a bug in the system and a designed feature. Break down the system to simpler functions to help troubleshoot the problem. For example if you are chasing a single seat issue visualize only the functions related to the seat. Your understanding of the system architecture is important for you to be able to do this.

6.7

SYSTEM CHECKS

At different points during the troubleshooting session, you will need to check the functionality of the system. Use the different functions of the system to help you troubleshoot a problem. Depending on the configuration of the aircraft, some of the system functions for example Safety Demo have VA capability. You can use the VA function to send video and audio to all the seats so that you can perform a quick walk through of the cabin and make a quick check of all the seats to see if they are functioning properly. Also, remember to check the seats after deactivation to see if the seats return to a default state. Be aware of the audio distribution for the aircraft. For example, a PA announcement uses a different path to send audio to the overhead speakers than the path to send audio to the seats. This fact will can help you determine whether problem is one LRU as opposed to another. Courtesy Checks The following examples of generic checks can be used to verify system functionality. The checks depend on the aircraft and the system configuration. You can develop your own variation of these checks.

6.7.1

6.7.2

Level 1 Courtesy Check Approximately 10 minutes. Perform a VA using a function like BMM or Movies. Deploy retracts if they are installed. Start at the back and make a quick visual check of the seat and their TPCUs. Verify that each TPCU is displaying the PA indication. If the seat has SVDU’s check that each SVDU is displaying video. Start at the back and make a quick visual check of the retracts. Activate MMAP and confirm its operation. MMAP comes from a different video client in the DSU. Document defective seats. Level 2 Courtesy Check Approximately 20 minutes. Activate Services for both video and audio entertainment. Pick one seat in each zone and verify all the available channels for both audio and video. Sample a few seconds of audio and video. Volume up and down once. Perform a VA using a function like BMM or Movies



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6.8

Start at the back and make a quick visual check of the seat and their TPCUs. Verify that each TPCU is displaying the PA indication. If the seat has SVDU’s check that each SVDU is displaying video. Activate MMAP and confirm its operation. (MMAP comes from a different video client in the DSU) Document defective seats. Level 3 Courtesy Check Approximately 2 hours. Activate Services for both video and audio entertainment. Go to each seat and verify all the available channels for both audio and video. Sample a few seconds of audio and video. Volume up and down once.

TROUBLESHOOTING AUDIO DISTRIBUTION PATHS

The distribution of the various audio signals within iSeries and between iSeries and aircraft systems can be somewhat complicated and confusing. The purpose of this section is to clearly identify the paths taken by each type of audio signal. The focus of this section is on the various broadcast audio signals and does not address AOD or VOD audio distribution. The system components involved in the distribution of audio to the passenger are identified in the figure below. The figure identifies the DSU AM6-12, the AVC, and the SEB as iSeries components. It also identifies the overhead speakers as aircraft system components.



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Audio Mod (6s)

RF Combiner

Audio Client (12s) Audio

Audio Client (2m)

Audio Mod (1s)

Vid Mod (3)

Audio Modulator

AVC

Video Client (6) Audio

External Audio

Overhead Video Audio

Video Tuner (3)

Audio (FM) Demod

External Video

External Audio

PA Audio

Select & Sum

PRAM Vol Ctrl

Video

BMM Vol Ctrl

VA Vol Ctrl

PA Modulator (6m)

PRAM

VTR

BMM

Video Ann

CIDS

Video Modulator (5)

DSU-AM6-12

Video Demod

Headset Vol Ctrl

SEB

PA Speaker

Figure 6-1 iSeries Audio System Components



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Distribution of Audio Entertainment

General audio entertainment is distributed through the iSeries by the AVC The DSU AM6-12 audio clients produce 12 stereo audio entertainment signals, which are modulated onto FM carriers, combined with any internally generated video signal and passed to the AVC. The AVC mixes this external RF signal with internally generated signals and distributes the combined RF signal throughout the aircraft. The SEB FM Demodulator receives this combined RF signal and can select any of the available FM frequencies for presentation to the passenger. The AVC contains the following elements: 3 Video Modulators modulating the video and associated audio from external sources (DVD, landscape camera, etc.)

7 Stereo FM audio Modulators, 6 of which are assigned for audio associated with overhead video programs and one spare for external audio input

3 Video Tuners with dual language, audio demodulators. These tuners are for extracting both languages of audio associated with overhead video programs and providing it to the seats and to the aircraft systems for VA (Video Announcement) Audio Select & Sum and circuit for VA. This circuit has 6 outputs to the aircraft PA system, any of which can select one of the 6 audio signals from the 3 video tuners. Volume control for each of the audio outputs to the aircraft PA system. 6 Monaural FM modulators for the distribution of each of 6 PA inputs from the aircraft PA system. (note the 7th FM modulator for PA all is not illustrated)

The DSU AM6-12 contains the following elements:

6 Video Clients producing 1 video and 2 associated stereo audio signals each 5 Video Modulators modulating the video and associated audio from a video client 12 Audio Clients producing 1 stereo audio entertainment signal each 12 stereo Audio Modulators modulating the audio from the audio clients 2 Audio Clients producing 1 monaural signal with independent volume control

The SEB contains the following elements: Video Demodulator for up to 3 passengers. The Video Tuner is a tuner and Demodulator that tunes to a video channel and can select from one of two audio signals associated with the video program. Audio FM Demodulator for up to 3 passengers. The individual FM demodulators are used to present audio entertainment and Area PA messages. Volume Control for each of 3 passengers.



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Distribution of Video Audio

The AVC video modulator accepts video and audio signals from an external source and modulates them onto the appropriate video carrier. Two audio signals (currently monaural, stereo in the future) are provided with each video program. The modulated signal is provided to the RF combiner in the AVC. Each DSU AM6-12 video client produces 1 video signal and 2 stereo audio signals. These signals are passed to the video modulator where they are modulated onto the appropriate video carrier (audio modulation is currently mono, stereo in the future). The modulated video and audio signals are combined together and passed to the AVC. The AVC uses an RF combiner to mix an external RF signal (from the DSU AM6-12) with internally generated signals and distributes the combined RF signal throughout the aircraft. This combined signal is also provided to the Video Tuners in the AVC for use in extracting the audio associated with an overhead video program. The SEB Video Tuner/Demodulator receives this combined RF signal and can select any of the available Video frequencies for demodulation and presentation to the passenger.



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External Video

Audio Client (2m)

Audio Mod (6s)

RF Combiner



Video Tuner (3)

PA Modulator (6m)

External Audio

External Audio

PA Audio

Select & Sum

PRAM Vol Ctrl

Audio Mod (1s)

Vid Mod (3)

Audio Modulator

Video Client (6)

Video Modulator (5)

AVC

Audio (FM) Demod

Audio

BMM Vol Ctrl

VA Vol Ctrl

Video

BMM

VTR

PRAM

Video Ann

CIDS

DSU-AM6-12

Entertainment Audio from AVC

Video Demod

Headset Vol Ctrl

SEB

PA Speaker

Figure 6-2 Entertainment Audio from AVC



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External Video

Audio Client (2m)

Audio Mod (6s)

RF Combiner



Video Tuner (3)

PA Modulator (6m)

External Audio

External Audio

PA Audio

Select & Sum

PRAM Vol Ctrl

Audio Mod (1s)

Vid Mod (3)

Audio Modulator


BMM Vol Ctrl

VA Vol Ctrl

Video

BMM

VTR

PRAM

Video Ann

CIDS

Video Modulator (5)

AVC

DSU-AM6-12

Entertainment Audio from DSU Audio (FM) Demod

Video Demod

Headset Vol Ctrl

SEB

PA Speaker

Figure 6-3 Entertainment Audio from DSU AM6-12



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Audio Mod (6s)

RF Combiner

Audio (FM) Demod

External Audio

Audio Client (2m)



Video Tuner (3) PA Modulator (6m)

External Video

External Audio

PA Audio

Select & Sum

PRAM Vol Ctrl

Audio Mod (1s)

Vid Mod (3)

Audio Modulator

AVC


BMM Vol Ctrl

VA Vol Ctrl

Video

BMM

VTR

PRAM

Video Ann

CIDS

Video Modulator (5)

DSU-AM6-12

Video Demod

Video Audio from AVC Headset Vol Ctrl

SEB

PA Speaker

Figure 6-4 Video Audio from AVC



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Audio Mod (6s)

RF Combiner

Audio (FM) Demod

External Video

Audio Client (2m)



Video Tuner (3)

PA Modulator (6m)

External Audio

External Audio

PA Audio

Select & Sum

PRAM Vol Ctrl

Audio Mod (1s)

Vid Mod (3)

Audio Modulator

AVC

Video Demod


BMM Vol Ctrl

VA Vol Ctrl

Video

BMM

VTR

PRAM

Video Ann

CIDS

Video Modulator (5)

DSU-AM6-12

Video Audio from DSU (SEB-IV)

Headset Vol Ctrl

SEB

PA Speaker

Figure 6-5 Video Audio from DSU AM6-12



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DISTRIBUTION OF BOARDING MUSIC AND PRE-RECORDED ANNOUNCEMENTS

Boarding Music (BMM) and Pre-Recorded Announcement (PRAM) are handled in a similar way in both the IFE system. Two dedicated audio clients in the DSU AM6-12 produce monaural audio for PRAM and BMM. An independent volume control is provided for each of these outputs. These audio outputs ARE NOT modulated onto FM carriers but are only routed to the aircraft PA system via aircraft wiring. An output keyline (not illustrated) from the DSU AM6-12 is also provided for each audio. When an announcement is activated by the DSU AM6-12, the audio signal is generated and the keyline is activated. These go to CSS where they are evaluated as part of PA system operation. If appropriate, the PA will provide the audio program over the cabin PA speakers and in addition, route the audio signal to the PA modulators in the AVC for distribution as a Passenger Announcement. NOTE: The fundamental requirement is that audio from an IFE system must not interfere with a passenger announcement. This requirement is met by having PA audio override the entertainment audio at the seat. Since the aircraft PA system is making priority selection decisions on the audio to be presented, the IFE system MUST use the audio from PA for the override.

Audio Audio Mod Mod (6s) (1s)

RF Combiner

Video Modulator (5)

PA Modulator (6m)

Audio Mod (6s)

RF Combiner

DSU-AM6-12

Audio (FM) Demod

Boarding Music SEB

PA Speaker

Audio

Audio Client (12s)

Audio Mod (1s)

Vid Mod (3)

Audio Modulator


BMM

External Audio

External Video

PRAM Vol Ctrl

Video Modulator (5)

AVC

DSU-AM6-12

Video Demod

Headset Vol Ctrl

SEB

Audio Client (2m)


Video Tuner (3)

Video Demod

Headset Vol Ctrl

External Audio

PA Audio

AVC

Video

Audio

Audio Modulator

Select & Sum

Audio

External Audio

Vid Mod (3)

BMM Vol Ctrl

VA Vol Ctrl

Video Client (6)

Audio Client (12s)

VTR

Video

PRAM Vol Ctrl

Audio Client (2m)


Video Tuner (3)

Audio (FM) Demod

External Video

External Audio

PA Audio

Select & Sum

Video Ann

BMM

BMM Vol Ctrl

VA Vol Ctrl

PA Modulator (6m)

PRAM

Video Ann

VTR

PRAM

CIDS

CIDS

Pre-Recorded Announcements

PA Speaker

Figure 6-6 Boarding Music Distribution of VA Audio

Figure 6-7 Pre-Recorded Announcement



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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual Video Announcements, often referred to as VA, are one of the most confused aspects of IFE operation. This is primarily due to it’s being a combination of overhead video programming, in-seat video programming, and passenger announcement. In fact, there are two fundamentally different operations that are referred to as VA: Presenting the audio associated with an overhead video program onto the overhead PA speakers. Forcing in-seat video monitors ON and forcing them to a specific video channel. For the purposes of this discussion, it is a requirement that any video program from the IFE system can be selected and presented on the Overhead Video System. In addition, the audio associated with any Overhead Video System presentation must be capable of being presented on the overhead PA speakers. The presentation of an audio signal associated with an overhead video system program, selected from any available video program, is to be considered a Video Announcement or VA.

Audio Mod (6s)

RF Combiner

Audio (FM) Demod

External Audio

Audio Client (2m)



Video Tuner (3) PA Modulator (6m)

External Video

External Audio

PA Audio

Select & Sum

PRAM Vol Ctrl

Audio Mod (1s)

Vid Mod (3)

Audio Modulator

AVC


BMM Vol Ctrl

VA Vol Ctrl

Video

BMM

VTR

PRAM

Video Ann

CIDS

Video Modulator (5)

DSU-AM6-12

Video Demod

Headset Vol Ctrl

SEB

Video Announcement from DSU

PA Speaker

Figure 6-8 Video Announcement from DSU AM 6-12 The information contained hereon is proprietary and confidential to Thales Avionics, Inc., and shall not be used or disclosed in whole or in part, without first obtaining the written permission of Thales Avionics, Inc. © Thales Avionics, Inc. 2008


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NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual As discussed in the distribution of video programs, the modulators in either the or DSU place the modulated video program along with its two associated audio signals onto an appropriate video RF carrier. All RF signals in the system are available at the output of the RF combiner in the AVC. To meet the requirements stated above, the audio for presentation to the PA system as part of a VA must be able to be extracted from any video program in the system. To accomplish this, the AVC contains 3 video tuners whose RF signal comes from the output of the RF combiner (in effect, the AVC contains an SEB). The Video Tuners in the AVC differ from those in an SEB in that both audio signals are demodulated (the SEB only demodulates one). This provides both languages associated with the selected program. The two languages from each of the 3 tuners are provided to two specific functions: 1) a summing/selection network for the PA system and 2) 6 FM stereo modulators for distribution to the seats. The summing/selection network is a 6 audio pair input (12 inputs), 6 audio output network. This network permits each output to be selected (in software) from any one of the audio pair inputs. The selected audio pair is summed (producing monaural from stereo) and provided to the aircraft PA system. A separate volume control is provided for each output from the AVC to CIDS. NOTE: Even though the audio associated with the overhead video program is available from the Video Demodulator, the SEB must switch to the FM demodulator when the Area PA becomes active. This is due to the fact that the actual PA audio may be a different audio signal (Pilot, Attendant, PRAM, etc.) than the overhead video program and the program presented in the headset must not conflict with the program on the PA speakers. One subtle aspect of this operation is the following: from a passenger point of view, when the audio from the overhead video program is selected (non-VA) it takes one path, when it becomes a VA it takes a VERY DIFFERENT path. Volume is very likely to be different (VA should probably be a little louder). Audio quality should also be different (PA systems are typically limited to 50-8,000 Hz whereas overhead video audio provides at least 50-15,000 Hz system response).

6.10 PRACTICAL TIPS

Remember that a seat reset from the iCMT, reboots the SVDU by removing power from the SSVDU and does not reset or reboot the SEB. If DSU/AVC are exhibiting intermittent conditions. Check the ARINC connectors on DSU/AVC tray for seating problems. On new aircraft some ARINC connectors on tray can be tight (due to alignment), and may need adjustment. Terminator plugs are required for ADB, TU, and SEB. If for any reason the ICMT lockups, reset the ICMT by holding down both brightness buttons together for 15 seconds. When replacing an ADB make sure the seat columns are reconnected correctly. If the seat cables are miss-wired IP Sequence will not work properly and certain seats will become inoperative.



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Always make sure before powering up IFE system that the cooling system is also ON. Never operate IFE system without cooling system ON. Make sure power is not interrupted while performing software downloads. Software corruption may occur if power is remove during software downloads. Place placards on CB and GPU. Do not perform PA’s during software downloads. For troubleshooting, try reducing the SEB seat strings by disconnecting SEBs and moving the terminator. You can also bypass SEBs. For troubleshooting purposes, try reducing the ADB strings by disconnecting ADBs and moving terminator. Remember that “broadcast” goes through the SEB via the RF network and VOD goes through the SVDU via Ethernet. Knowing this will help troubleshoot seat problems. When the system is first powered up, be aware that if you start SERVICES before all the seats are up, those seats may come up in an inoperative state. Remember that the software is unique to the aircraft configuration and you cannot use software designed for other configurations. Remember that the ESU is one LRU, but it contains 2 completely stand alone ESU functions. It reports twice on Config Check. If half of the ESU fails completely the ESU will not have the bandwidth to support the whole aircraft and you may get pixilation. If you replace the ICMT, you will require a PDL to load software to the ICMT. A failure of ADB #1 could potentially cause loss of ICMT communication. The VCC SEB is connected to ADB #1. When replacing an SEB only, do the following: • Perform an IP Sequence • Then a phase 2 download to the SEB (SEBs from ATP may need to be downloaded twice) • NOTE: The SVDU is already properly IP Sequenced When replacing an SEB and SVDU on the same seat, do the following: • Perform an IP Sequence • Then a phase 2 download to the SEB (the SEB needs the proper database to IP sequence the SVDU) (SEBs from ATP may need to be downloaded twice) • Perform another IP Sequence • Then a phase 2 download to the SVDU After IP Sequence, the system will indicate DONE. You must wait an additional 4 minutes before attempting a phase 2 download, because the SEBs are not finished rebooting. After a Static Test, you must wait an additional before the system is operational, because the SEBs must finish rebooting. The Galley power in the cockpit switches off or reset the complete IFE system (head-end and seatend).



Page 6-17

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 6.11 TROUBLESHOOTING GUIDE This section is a general list of troubleshooting tips for a typical Thales TopSeries systems, this guide is not specific to a particular model. The guide is in table format and its purpose is to help introduce the line maintenance personnel on steps to take in troubleshooting problems for TopSeries. The guide is composed of 4 columns: 1) LRU/FUNCTION: the LRU or function in question. 2) SYMPTOM: what will be observed. 3) INFORMATION: describes the cause or explanation of the problem. 4) ACTION: the steps needed to resolve the issue. Notice that the previous step must be performed first and the results dictates performing the next step. There are also entries for information only. LRU/ FUNCTION

ACOU

ACOU

ACOU

SYMPTOM ACOU in seat group all GREEN.

ACOU LED does not light up. A single PAX position ACOU LED is RED. Entire seat group of ACOUs are RED.

ACOU

INFORMATION Normal operation: during ISPC bootup, the PPUI lamp will light momentarily and then shut-off. After the PPUI lamp turns-off, then the ACOU LED's should turn from RED to GREEN.

ACTION Information only.

Replace ACOU. A single PAX position ACOU LED turns-on and remains RED and other PAX positions within the same seat group are GREEN. Then the ACOU is faulty. If an entire seat group has ACOUs RED. Ensure there is no load connected to the ACOU. Verify that the seat group's PPUI lamp is not burned out. A burned out PPUI lamp can cause the ACOUs to be RED within that seat group. You can check PPUI lamp is burned out by cycling power to the seat and

Replace ACOU.

1) Ensure there is no load connected to the ACOU. 2) Verify that the seat group's PPUI lamp is not burned out. 3) If lamp does not light, replace the lamp and retest. 4) If lamp is ok, replace a single ACOU at a time



Page 6-18

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual LRU/ FUNCTION

ACOU

ADB

SYMPTOM

INFORMATION

watching the PPUI lamp. If the lamp is ok, it will light at bootup momentarily. If lamp does not light, replace the lamp and retest. This could be caused by an intermittent Entire column connection of the DC Data Control (MCU output Line from the MCU to that column of column) of ACOUs are RED. seats. If the Data Control Line is not connected, all ACOUs on that column will be RED. If continuity of this control line is good, then the MCU may be faulty. No IP sequence If the Ethernet link to ADB #1 has or download problems it will affect the ability to IP possible. sequence and download to all seats

ACTION and retest until all ACOUs are ok.

1) Check cables. 2) Check MCU 3) Replace MCU.

1) Check AVC to ADB#1 link. 2) Check ADB #1 3 Check AVC

No IP sequence or download possible to FWD seats.

IP sequence and download not possible to FWD seats only, AFT seats ok. Ethernet path = AVC to ADB #1 to ADB #2.

1) Check S/W of ADB#1. 2) If ok, replace ADB.

Multiple seat strings not functioning correctly throughout aircraft.

Attempts at IP sequence and download fail at multiple seat group positions. Channels that work on heartbeat messages are not working. If an ADB has a bad output Ethernet port, the whole column will not receive its heartbeat and will not be able to IP sequence. Possible failure could be Ethernet switch in ADB.

1) Check Ethernet distribution path of affected seats 2) Check cabling. 3) Check FDB/ADB 4) Replace ADB.

ADB can exhibit possible kernel corruption.

Replace ADB.

ADB

When repeated downloads fail to seats.

Refer to Data Branch block diagram to determine possible fault areas.

ADB

Not able to IP sequence or download to AFT half of the seats on the aircraft.

1) Check Ethernet cable between affected ADB and last good. 2) If not cable then check software to

ADB

ADB



Page 6-19

Apr 2008


SYMPTOM

INFORMATION

ACTION affected ADB. 3) Replace affected ADB.

AVC

BMM CMT/ICMT

Menus which originate from AVC

Boarding Music Audio. iCMT screen freezes" Normal operation

TDPCU

Isolating TDPCU failures. TDPCU

TDPCU

Welcome screen Second screen after Welcome screen, which contains all buttons for the different functions. VTR menus Camera menus Path = DSU (source) to CSS to AVC and Overhead speakers. iCMT has not booted properly.

For a TDPCU that is communicating with the SEB, disconnecting and reconnecting the TDPCU causes the SEB to crash. It reboots and recovers after 5 minutes by itself. For isolating TDPCU failures, first disconnect and reconnect TDPCU. Then check SEB connections. Then check cable harness.

[blank] Backlight ON

TDPCU did not boot up. TDPCU boot error, failed processor, or bad/missing software.

[blank] Backlight OFF

TDPCU did not boot up. One seat: Bad cable, Failed backlight All seats: No power from SEB

TDPCU

Information only.

Information only. Press both brightness buttons for 15 seconds to reboot iCMT Wait for the SEB to recover or power-cycle the SEB to speed up the process 1) Disconnect and reconnect TDPCU. 2) Check SEB connections. 3) Check cable harness. 1) Reboot by cycling power to SEB. 2)Replace TDPCU 1)Reboot by cycling power to SEB 2)If one seat: inspect cable 3)If cable OK: replace TDPCU 4)If all seats: replace SEB



Page 6-20

Apr 2008


TDPCU

TDPCU

TDPCU

SYMPTOM

INFORMATION

ACTION

Depending on number of digits of TDPCU. ( 0 0 ) You will get one of the following displays.

TDPCU booted OK but cannot talk to SEB. One seat: TDPCU USB port bad, bad cable, SEB USB port. All seats: SEB down, SEB USB inop.

Depending on number of digits of TDPCU LCD. (II) You will get one of the following displays. Depending on number of digits of TDPCU LCD. You will get one of the following displays.

TDPCU talking to SEB but SEB is not talking to head-end LRUs. Should only occur on entire seat group, never a single seat. SEB down, SEB input cable bad.

1)Reboot SEB by cycling power 2)If one seat, inspect cable 3)If cable OK, replace TDPCU 4)If all seats, inspect SEB input cable 5)If cable OK, replace SEB 1)Reboot SEB by cycling power 2)Config Check to see if SEB is reporting 3)Inspect SEB input cable 4)Replace SEB 1)Reboot SEB by cycling power 2)If one seat, inspect cable 3)If cable OK, replace TDPCU 4)If all seats, inspect SEB input cable 5)If cable & TDPCU OK, replace SEB 1) Reboot SEB by cycling power. 2) Config Check to see if SEB is reporting 3) Inspect input cables to SEB and SEB in next seat forward 4) If cables OK, replace SEB 5) Replace SEB in next seat forward 1) Reset DSU. 2) Replace DSU.

displays 03.

Normal - indicates successful initialization. If stuck then something failed after boot-up. One seat: TDPCU USB port, intermittent cable problem All seats: SEB USB or Enet failure, SEB input cable

Depending on number of digits of TDPCU LCD ( I I ).

Economy Class: SEB is unable to talk to SEB in seat ahead (only in i3000/4000 system). Business Class: SEB is unable to find an intranet server. Should only occur on entire seat group. SEB Ethernet not initialized properly, SEB input cable, SEB in next seat forward.

Some menus missing at ICMT.

Welcome screen, second page, VTR, and Camera pages are all working properly. If the following functions are not working properly: Maintenance,

TDPCU

DSU



Page 6-21

Apr 2008


SYMPTOM

INFORMATION

ACTION

BMM, MMAP, Manual Play, Services, and PRAM. These pages are all generated by DSU.

Menus which originate from DSU

Maintenance menus Boarding Music menus Moving Map menus Manual Play Services Menus PRAM Menus Exit Menus

Information only.

"Mounting on PCOMM" error message displayed at ICMT. ICMT is displaying green screen.

DSU has the PCOMM board. Most of the time it will be a PCOMM board failure. Could also be caused by the AVC not being seated correctly. During a warm reboot at the completion of the download of the iCMT, the iCMT internal registers are not properly set to put the hardware back into text mode. Therefore, when the system reboots no text is displayed since the boot procedure does not set the unit into text mode either. VCC SEB supplies connectivity from ICMT to AVC. Ethernet goes from ICMT to AVC to DSU.

1) Reset DSU. 2) Check AVC for proper installation 3) No recovery then replace DSU. Re-set the unit.

Individual video clients can reboot without the entire DSU rebooting.

1) Allow video client to reboot. 2) May need to reset DSU.

DSU

DSU/ AVC

ICMT

ICMT

ICMT

ICMT is not displaying any of the proper screens (WELCOME page). ICMT is displaying gray screen with cross.

1) Check cables and connections. 2) Check RJ45 connection to ICMT.



Page 6-22

Apr 2008


SYMPTOM

INFORMATION

MMAP does not function.

The system takes 6 minutes to boot up, but the MMAP takes another 3 minutes to become functional. Make sure you wait long enough for MMAP to become fully functional.

MMAP

No A/C icon is displayed on MMAP.

Longitude and Latitude is missing. ARINC port 9 information is not being received.

MMAP

No data pages are displayed on MMAP.

Outside air temperature, Ground speed, 1) Check CSS. and altitude data not being received on 2) Check 420 ARINC ARINC 429 ports 7 and 8. 429 ports. 3) Replace 420.

IFE system locked in PA.

Most likely, this will be caused by a sticky button on the crew station handset.

Software disks have different part numbers.

Official Thales software maintenance releases (MR) usually are contained on multiple CD disk. Some of these disks may contain reference to older MR versions.

Whole column of seats not powered. All seats exhibiting FM audio problems.

Circuit breaker of MCU corresponding to the seat column in question is tripped. FM audio source is the DSU. Path = DSU (source) to AVC to SEB to headset. Because all the seats are affected, it may be the AVC or DSU causing the problem.

MMAP

PA

S/W

SEATS

SEATS

ACTION 1) After a power cycle you need to wait 9 minutes before MMAP is functional. 2) CSS needs to be ON or MMAP will not function. 3) 420 needs the 429 navigation data from CSS. 1) Check CSS. 2) Check 420 ARINC 429 ports. 3) Replace 420

1) Check all the crew station handsets. 2) Replace intermittent handset. 3) Check cockpit handset as well. 1) Refer to the service bulletin for confirmation of the proper part numbers. 2) Certain components of the disk set may not have changed and this is why an older part number may be used. Check circuit breakers of MCU. 1) Check AVC. 2) Check DSU.



Page 6-23

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual LRU/ FUNCTION SEATS

SYMPTOM One seat exhibiting FM audio problems. VCCSEB bootup

SEB

Downloading to an SEB using maintenance functions. SEB

SEB random boot-up issue. SEB

INFORMATION Path = DSU (source) to AVC to SEB to Headset. Because only one seat is affected, it probably the SEB, audio jack or a seat cable. Put a spare SEB in the VCC the iCMT will not boot-up until the VCCSEB finishes booting-up. Take an SEB from a seat and put it in the VCC the iCMT will boot-up immediately. An SEB with core software from Thales ATP station installed in the VCC will not allow the 32VDC to the iCMT until the SEB completes its boot-up process (about 1.5 minutes). An SEB taken from a seat with the latest core software will supply 32VDC immediately upon boot-up. In the maintenance section of the CMS menus (Maintenance/Download/Download LRU) there are two ways to perform a download to an LRU; "All Selected LRUs" or "Single LRU.” Single SEB download can only be used to a SEB that has been previously downloaded with the database. Without a proper database, it will not respond to a "Single LRU" download, this process uses the LRU hostname. Entire seat group is effected. No control with TDPCU. TDPCU displaying one of the following: dash video, small 00 or 0, small d or bd. Random event and a power cycle on seat may or may not recover seat.

ACTION 1) Check audio jack. 2) Check seat cable. 3) Check SEB. 1) After installing a new SEB that has not been downloaded too, wait an appropriate amount of time after rebooting the VCC to allow SEB and iCMT to boot-up properly.

1) Do not use the "Single LRU" button. 2) Use instead the "All Selected LRUs" button when loading to an SEB.

1) Try performing a power cycle the seat. 2) Replace SEB



Page 6-24

Apr 2008


SYMPTOM

INFORMATION

SEB IP sequence problems.

IP sequence process uses the Ethernet network.

Various symptoms.

A faulty SSVDU extender cable can exhibit symptoms with SVDU, and TDPCU Path = DVD (source) to AVC to CSS to AVC and Overhead speakers to SEB to headset. Path = DSU (source) to AVC to CSS to AVC and Overhead speakers to SEB to headset. If you disconnect and reconnect SVDU, it will not crash SEB. Video demodulation takes place in the SEB. Loss of vertical sync is more often a bad signal form the SEB than a bad SVDU. OSD is generated by the SEB, not the SVDU.

SEB

SSVDU EXTENDER CABLE

VA with DVD. VA VA with DSU. VA SVDU

SVDU

SVDU

SVDU

Normal operation Video looks like it has a sync problem On-ScreenDisplay (OSD) not displayed. The Brightness OSD is not displayed when Brightness controls are pressed SVDU does not turn-off.

SVDU

WDB

Single seat string not functioning correctly.

ACTION 1) Loop out suspected SEB using seat-to-seat cables and check to see problem is resolved. 2) Replace faulty SEB. 3) Return cables to correct routing. Information only. Information only. Information only. Information only. 1) If no spares: power cycle SEB for possible fix. 2) Otherwise, replace SEB. Replace SEB.

There is no OSD for brightness, because the OSD comes from the SEB and the SVDU does not communicate data to the SEB

Do nothing. Normal operation.

SVDU does not turn-off when you switch between AUDIO and VIDEO modes. Possible fault SSVDU extender cable or SEB. Not able to IP sequence or download to a single seat string.

1) Check SSVDU extender cable. 2) Check SEB. 3) Replace either is faulty. 1) Check connections to FDB. 2) Replace FDB.



Page 6-25

Apr 2008





Page 6-26

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 7 7.1

APPENDIX A321 DATA (SEAT-TO-SEAT CABLING)

ADB 1

ADB 2



Page 7-1

Apr 2008


DATA (ADB 1 TO SEAT GROUPS) AJ SVDU DPCU

Term Plug

AJ SVDU DPCU

To VCC

SEB ROW 1 AC

From AVC

SVDU DPCU

AJ

SVDU

SEB ROW -1 DF

SVDU DPCU

AJ

AJ

SVDU DPCU

AJ

AJ

SVDU

SEB ROW 2

WDB 1 Q2

J2

DPCU

J8

SVDU

SVDU

DPCU

DPCU

SVDU DPCU

Term Plug

J2 J3

J1 J4

J6

AJ

AJ

SVDU

SVDU DPCU

Term Plug

AJ

SVDU DPCU

AJ SVDU DPCU

AJ SVDU DPCU

AJ

Term Plug

SVDU DPCU

SVDU DPCU

AJ

AJ

SEB ROW 7 DE

SVDU AJ DPCU DPCU

SVDU AJ DPCU DPCU

SVDU DPCU

AJ SVDU

SEB ROW 8 DEF

SEB ROW -8 ABC AJ SVDU DPCU

AJ SVDU DPCU

AJ SVDU DPCU

SEB ROW -6 DEF

SVDU DPCU

SEB ROW 8 ABC

AJ SVDU DPCU

Term Plug

SEB ROW 6 DEF

SEB ROW 7 BC

SVDU

AJ

SEB ROW 5

SEB ROW -6 ABC

SVDU DPCU

SVDU DPCU

SVDU DPCU

AJ

SEB ROW 6 ABC

AJ

AJ

SEB ROW 4

AJ

SEB ROW 5

AJ SVDU DPCU

AJ

DPCU

DPCU

J2

SVDU DPCU

AJ SVDU DPCU

AJ

SEB ROW 3

J3

J5

SVDU

DPCU

ADB 1

SEB ROW 4 AJ

WDB 2 Q1

J3

SEB ROW 3 AJ

SVDU DPCU

SEB ROW 2

SVDU

DPCU

Term Plug

SEB ROW 1 DF

SEB ROW -1 AC AJ

AJ SVDU DPCU

AJ SVDU DPCU

SEB ROW -8 DEF

AJ SVDU DPCU

AJ SVDU DPCU

SEB ROW 9 AJ AJ SVDU SVDU DPCU DPCU

AJ SVDU DPCU


AJ SVDU DPCU AJ SVDU

AJ SVDU DPCU

AJ SVDU DPCU

AJ SVDU DPCU

AJ SVDU DPCU


AJ SVDU DPCU



AJ SVDU DPCU


SEB ROW 12 AJ AJ SVDU SVDU

AJ SVDU


Term Plug

To ADB 2

J3

WDB 3

WDB 4

J2

J2 Term

J3 Plug



Page 7-2

Apr 2008


DATA (ADB 2 TO SEAT GROUPS) DPCU DPCU DPCU SEB ROW 13 ABC

Term Plug

AJ SVDU DPCU AJ SVDU

AJ SVDU DPCU

DPCU DPCU DPCU SEB ROW 13 DEF

From ADB 1

AJ SVDU DPCU

AJ SVDU DPCU


AJ SVDU

J3 J2 DPCU

DPCU

W DB 6

J3

DPCU

DPCU

J1

J8 AJ SVDU DPCU

J6


J5

AJ SVDU DPCU AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU

J4

ADB 2 J2

J3

SVDU Term Plug

AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU

AJ SVDU

DPCU DPCU SEB ROW 20 DE AJ AJ SVDU SVDU

DPCU DPCU DPCU SEB ROW 21 ABC

DPCU

DPCU DPCU SEB ROW 21 DEF

SEB ROW -21 AJ SVDU DPCU

AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU

SEB ROW 25

AJ SVDU DPCU

AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU


AJ SVDU


J3 DPCU

DPCU

Term Plug

SEB ROW 25 AJ SVDU DPCU

AJ SVDU DPCU

SVDU

AJ SVDU DPCU

AJ SVDU DPCU

AJ SVDU DPCU

Term Plug

SEB ROW -21

AJ SVDU DPCU

AJ SVDU DPCU

DPCU

WDB 7

WDB 8

J2

J2

J3

SEB ROW 28 AJ AJ AJ SVDU SVDU SVDU DPCU DPCU DPCU

Term Plug

AJ SVDU DPCU

SEB ROW 19

AJ SVDU

DPCU DPCU SEB ROW 20 BC AJ AJ SVDU SVDU

Term Plug

DPCU

AJ SVDU DPCU

SEB ROW 19 AJ SVDU

DPCU

SEB ROW 15

Term Plug

AJ SVDU DPCU


J2

W DB 5


Term Plug

AJ SVDU DPCU

AJ SVDU DPCU

DPCU

AJ SVDU DPCU

DPCU

AJ SVDU DPCU

DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


SEB ROW 31

SEB ROW 31

Term Plug



Page 7-3

Apr 2008


DATA (ADB TO WDB/SEB/SVDU/DPCU) BUSINESS CLASS

ADB # Output #

WDB # Output #

SEB #

1-J6

WDB1-J3

SEB 1AC

1-J6

WDB1-J3

SEB -1AC

1-J6

WDB1-J3

SEB 2AC

1-J6

WDB1-J2

SEB 3AC

1-J6

WDB1-J2

SEB 4AC

1-J6

WDB1-J2

SEB 5AC

1-J4

WDB2-J2

SEB 1DF

1-J4

WDB2-J2

SEB -1DF

1-J4

WDB2-J2

SEB 2DF

1-J4

WDB2-J3

SEB 3DF

1-J4

WDB2-J3

SEB 4DF

1-J4

WDB2-J3

SEB 5DF

SVDU Port

DPCU Port

SVDU Seat Number

1 2 1 2 1 2 1 2 1 2 1 2 1 2 1 2 1 2 1 2 1 2 1 2

1 2 N/A N/A 1 2 1 2 1 2 1 2 1 2 N/A N/A 1 2 1 2 1 2 1 2

1A 1C 2A 2C 3A 3C 4A 4C 5A 5C N/A N/A 1D 1F 2D 2F 3D 3F 4D 4F 5D 5F N/A N/A

DPCU Seat Numbe r 1A 1C N/A N/A 2A 2C 3A 3C 4A 4C 5A 5C 1D 1F N/A N/A 2D 2F 3D 3F 4D 4F 5D 5F

Seat Row 1 1 1 1 2 2 3 3 4 4 5 5 1 1 1 1 2 2 3 3 4 4 5 5

ECONOMY CLASS ADB # Output #

WDB # Output #

SEB #

1-J5

WDB3-J3

SEB 6ABC

1-J5

WDB3-J3

SEB -6ABC

SVDU Port

DPCU Port

SVDU Seat Number

1 2 3 N/A 2 3

1 2 3 N/A N/A N/A

6A 6B 6C N/A 7B 7C

DPCU Seat Numbe r 6A 6B 6C N/A N/A N/A

Seat Row 6 6 6 N/A 6 6



Page 7-4

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual ADB # Output #

WDB # Output #

SEB #

1-J5

WDB3-J3

SEB 7BC

1-J5

WDB3-J3

SEB 8ABC

1-J5

WDB3-J3

SEB -8ABC

1-J5

WDB3-J3

SEB 9ABC

1-J5

WDB3-J3

SEB 10ABC

1-J5

WDB3-J3

SEB 11ABC

1-J5

WDB3-J3

SEB 12ABC

1-J5

WDB3-J2

N/A

1-J3

WDB4-J2

SEB 6DEF

1-J3

WDB4-J2

SEB -6DEF

1-J3

WDB4-J2

SEB 7DE

1-J3

WDB4-J2

SEB 8DEF

1-J3

WDB4-J2

SEB -8DEF

SVDU Port

DPCU Port

SVDU Seat Number

N/A 2 3 1 N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A 1 2 3 1 2 N/A 1 2 N/A N/A N/A 3 1 2 3

N/A 2 3 1 2 3 N/A N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A 1 2 3 N/A N/A N/A 1 2 N/A 1 2 3 N/A N/A N/A

N/A 8B 8C 8A N/A N/A 9A 9B 9C 10 A 10 B 10 C 11 A 11 B 11 C 12 A 12 B 12 C 13 A 13 B 13 C N/A N/A N/A 6D 6E 6F 7D 7E N/A 8D 8E N/A N/A N/A 8F 9D 9E 9F

DPCU Seat Numbe r N/A 7B 7C 8A 8B 8C N/A N/A N/A 9A 9B 9C 10 A 10 B 10 C 11 A 11 B 11 C 12 A 12 B 12 C N/A N/A N/A 6D 6E 6F N/A N/A N/A 7D 7E N/A 8D 8E 8F N/A N/A N/A

Seat Row N/A 7 7 8 8 8 8 8 8 9 9 9 10 10 10 11 11 11 12 12 12 N/A N/A N/A 6 6 6 6 6 N/A 7 7 N/A 8 8 8 8 8 8



Page 7-5

Apr 2008


WDB # Output #

SEB #

1-J3

WDB4-J2

SEB 9DEF

1-J3

WDB4-J2

SEB 10DEF

1-J3

WDB4-J2

SEB 11DEF

1-J3

WDB4-J2

SEB 12DEF

1-J3

WDB4-J3

N/A

2-J6

WDB5-J3

SEB 13ABC

2-J6

WDB5-J3

SEB 14ABC

2-J6

WDB5-J2

SEB 15ABC

2-J6

WDB5-J2

SEB 16ABC

2-J6

WDB5-J2

SEB 17ABC

2-J6

WDB5-J2

SEB 18ABC

2-J6

WDB5-J2

SEB 19ABC

2-J6

WDB5-J2

SEB 20BC

SVDU Port

DPCU Port

SVDU Seat Number

1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A 2 3

1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A 2 3

10 D 10 E 10 F 11 D 11 E 11 F 12 D 12 E 12 F 13 D 13 E 13 F N/A N/A N/A 14 A 14 B 14 C 15 A 15 B 15 C 16 A 16 B 16 C 17 A 17 B 17 C 18 A 18 B 18 C 19 A 19 B 19 C N/A 20 B 20 C N/A 21 B 21 C

DPCU Seat Numbe r 9D 9E 9F 10 D 10 E 10 F 11 D 11 E 11 F 12 D 12 E 12 F N/A N/A N/A 13 A 13 B 13 C 14 A 14 B 14 C 15 A 15 B 15 C 16 A 16 B 16 C 17 A 17 B 17 C 18 A 18 B 18 C 19 A 19 B 19 C N/A 20 B 20 C

Seat Row 9 9 9 10 10 10 11 11 11 12 12 12 N/A N/A N/A 13 13 13 14 14 14 15 15 15 16 16 16 17 17 17 18 18 18 19 19 19 N/A 20 20



Page 7-6

Apr 2008


WDB # Output #

SEB #

2-J4

WDB5-J2

SEB 13DEF

2-J4

WDB5-J2

SEB 14DEF

2-J4

WDB5-J3

SEB 15DEF

2-J4

WDB5-J3

SEB 16DEF

2-J4

WDB5-J3

SEB 17DEF

2-J4

WDB5-J3

SEB 18DEF

2-J4

WDB5-J3

SEB 19DEF

2-J4

WDB5-J3

SEB 20DE

2-J5

WDB7-J3

SEB 21ABC

2-J5

WDB7-J3

SEB -21ABC

2-J5

WDB7-J3

SEB 22ABC

2-J5

WDB7-J3

SEB 23ABC

2-J5

WDB7-J3

SEB 24ABC

SVDU Port

DPCU Port

SVDU Seat Number

1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 N/A 1 N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3

1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 N/A 1 2 3 N/A N/A N/A 1 2 3 1 2 3 1 2 3

14 D 14 E 14 F 15 D 15 E 15 F 16 D 16 E 16 F 17 D 17 E 17 F 18 D 18 E 18 F 19 D 19 E 19 F 20 D 20 E N/A 21 D 21 E N/A 21 A N/A N/A 22 A 22 B 22 C 23 A 23 B 23 C 24 A 24 B 24 C 25 A 25 B 25 C

DPCU Seat Numbe r 13 D 13 E 13 F 14 D 14 E 14 F 15 D 15 E 15 F 16 D 16 E 16 F 17 D 17 E 17 F 18 D 18 E 18 F 19 D 19 E 19 F 20 D 20 E N/A 21 A 21 B 21 C N/A N/A N/A 22 A 22 B 22 C 23 A 23 B 23 C 24 A 24 B 24 C

Seat Row 13 13 13 14 14 14 15 15 15 16 16 16 17 17 17 18 18 18 19 19 19 20 20 N/A 21 21 21 21 21 21 22 22 22 23 23 23 24 24 24



Page 7-7

Apr 2008


WDB # Output #

SEB #

2-J5

WDB7-J3

SEB 25ABC

2-J5

WDB7-J3

SEB 26ABC

2-J5

WDB7-J3

SEB 27ABC

2-J5

WDB7-J2

SEB 28ABC

2-J5

WDB7-J2

SEB 29ABC

2-J5

WDB7-J2

SEB 30ABC

2-J5

WDB7-J2

SEB 31ABC

2-J5

WDB7-J3

SEB 21DEF

2-J5

WDB7-J3

SEB -21DEF

2-J5

WDB7-J3

SEB 22DEF

2-J5

WDB7-J3

SEB 23DEF

2-J5

WDB7-J3

SEB 24DEF

2-J5

WDB7-J3

SEB 25DEF

SVDU Port

DPCU Port

SVDU Seat Number

1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A N/A N/A 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3

1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3

26 A 26 B 26 C 27 A 27 B 27 C 28 A 28 B 28 C 29 A 29 B 29 C 30 A 30 B 30 C 31 A 31 B 31 C N/A N/A N/A N/A N/A 21 F 22 D 22 E 22 F 23 D 23 E 23 F 24 D 24 E 24 F 25 D 25 E 25 F 26 D 26 E 26 F

DPCU Seat Numbe r 25 A 25 B 25 C 26 A 26 B 26 C 27 A 27 B 27 C 28 A 28 B 28 C 29 A 29 B 29 C 30 A 30 B 30 C 31 A 31 B 31 C 21 D 21 E 21 F N/A N/A N/A 22 D 22 E 22 F 23 D 23 E 23 F 24 D 24 E 24 F 25 D 25 E 25 F

Seat Row 25 25 25 26 26 26 27 27 27 28 28 28 29 29 29 30 30 30 31 31 31 21 21 21 21 21 21 22 22 22 23 23 23 24 24 24 25 25 25



Page 7-8

Apr 2008


WDB # Output #

SEB #

2-J5

WDB7-J3

SEB 26DEF

2-J5

WDB7-J3

SEB 27DEF

2-J5

WDB7-J2

SEB 28DEF

2-J5

WDB7-J2

SEB 29DEF

2-J5

WDB7-J2

SEB 30DEF

2-J5

WDB7-J2

SEB 31DEF

SVDU Port

DPCU Port

SVDU Seat Number

1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A

1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3

27 D 27 E 27 F 28 D 28 E 28 F 29 D 29 E 29 F 30 D 30 E 30 F 31 D 31 E 31 F N/A N/A N/A

DPCU Seat Numbe r 26 D 26 E 26 F 27 D 27 E 27 F 28 D 28 E 28 F 29 D 29 E 29 F 30 D 30 E 30 F 31 D 31 E 31 F

Seat Row 26 26 26 27 27 27 28 28 28 29 29 29 30 30 30 31 31 31



Page 7-9

Apr 2008


DATA AND RF (SEAT CONFIGURATION NOTES) Business-Class First Two Rows (Rows 1 and 2)

For SEB 1 connected to ADB 1 seat configuration is local • Video for the 2 seats is provided in its row (SVDU wall-mounted) • Audio for the 2 seats is provided in its row (audio jacks arm mounted) • Control for the 2 seats is provided in its row (DPCU seat arm mounted) • SVDUs are touch-screen

For SEB -1 connected to ADB 1 seat configuration is remote • Video for the 2 seats is provided behind it (SVDU seat-back) • Audio for the 2 seats is provided behind it (audio jacks arm mounted) • SVDUs are touch-screen



Page 7-10

Apr 2008


Business Class Last Two Rows (Rows 4 and 5)

For SEB 5 connected to ADB 1 seat configuration is local • Control for 2 seats is provided in its row (DPCU seat arm-mounted) • There is no video behind it



Page 7-11

Apr 2008


Economy Class First Three Row (Rows 6, 7 and 8)



Page 7-12

Apr 2008



For SEB -6 connected to ADB 1 seat configuration is remote • Video for the 2 seats is provided behind it (SVDU seat-back; seats B, C, D and E) • Audio for the 2 seats is provided behind it (audio jacks arm mounted) • SVDUs are touch-screen

For SEB 7 connected to ADB 1 seat configuration is remote • Video for the 2 (of 3) seats is provided behind it (SVDU seat-back; seats B, C, D and E) • Audio for the 2 (of 3) seats is provided behind it (audio jacks arm mounted) • Control for the 2 seats is provided in its row (DPCU seat arm mounted) • SVDUs are touch-screen

For SEB 8 connected to ADB 1 seat configuration is local • Video for the 1 (of 3) seat is provided in its row (SVDU arm-mounted; seat A and F) • Audio for the 1 (of 3) seat is provided in its row (audio jack arm mounted) • Control for the 3 seats is provided in its row (DPCU seat arm mounted) • SVDUs are touch-screen




Page 7-13

Apr 2008


Economy Class Rows 19, 20 and 21 DPCU 19A

DPCU 19B

DPCU 19C

SEB ROW 19 ABC

Seat-back SVDU/AJ 20B

Seat-back SVDU/AJ 20C

DPCU 20B

DPCU 20C

SEB ROW 20 ABC


Arm-Mounted SVDU/AJ DPCU 21A

SEB ROW 21 ABC

Seat-back SVDU/AJ 22A

DPCU 21B


DPCU 21C

SEB ROW 21 -ABC



For SEB 19 connected to ADB 2 seat configuration is remote • Video for the 2 seats is provided behind it (SVDU seat-back; seats B, C, D and E) • Audio for the 2 seats is provided behind it (audio jacks arm mounted) • Control for 3 seats is provided in its row (DPCU seat arm mounted) • SVDUs are touch-screen

For SEB 20 connected to ADB 2 seat configuration is remote • Video for the 2 (of 3) seats is provided behind it (SVDU seat-back; seats B, C, D and E) • Audio for the 2 (of 3) seats is provided in its row (audio jack arm mounted)



Page 7-14

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual • •

Control for the 3 seats is provided in its row (DPCU seat arm mounted) SVDUs are touch-screen

For SEB 21 connected to ADB 2 seat configuration is local • Video for the 1 (of 3) seat is provided in its row (SVDU arm-mounted; seats A and F) • Audio for the 1 (of 3) seat is provided in its row (audio jack arm mounted) • Control for the 3 seats is provided in its row (DPCU seat arm mounted) • SVDUs are touch-screen




Page 7-15

Apr 2008


Economy Class Last Two Rows (Rows 30 and 31)

For SEB31 connected to ADB 2 seat configuration is local • Control for 3 seats is provided in its row (DPCU seat arm-mounted) • There is no video behind it



Page 7-16

Apr 2008


POWER (SEAT-TO-SEAT CABLING)

MCU1 MCU2



Page 7-17

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 7.7 Term P lug

POWER (MCUS TO SEAT GROUPS) SEB ROW 1 AC

AVC

S E B R O W -1

SEB ROW 1 DF

A /C P ow er

S E B R O W -1

SEB ROW 2

SEB ROW 2

SEB ROW 3

SEB ROW 3

J3

PW B 1

PW B 2

J2 Term P lug Term P lug

J2 J3

SEB ROW 4

SEB ROW 4

SEB ROW 5

SEB ROW 5

SEB ROW 6 ABC

SEB ROW 6 DEF

S E B R O W -6

J9 J1

SEB ROW 7 BC

S E B R O W -8

SEB ROW 8

J3 J7

S E B R O W -8

SEB ROW 9

SEB ROW 9

Term Plug

S E B R O W 10

S E B R O W 10

S E B R O W 11

S E B R O W 11

S E B R O W 12

S E B R O W 12

J3 Term P lug

PW B 3

PW B 4

J2

J2 J3

S E B R O W 13 A B C

S E B R O W 15

S E B R O W 16

S E B R O W 16

J3

PW B 5

PW B 6

J2

J2 J3

S E B R O W 17

S E B R O W 17

S E B R O W 18

S E B R O W 18

S E B R O W 19

S E B R O W 19

S E B R O W 20 B C

S E B R O W 20 D E

S E B R O W 21 A B C

S E B R O W 21 D E F

J8 J4

J9 S E B R O W -21

J1 J2

S E B R O W 23

Term P lug Term P lug

S E B R O W -21

MCU 2

S E B R O W 22

S E B R O W 22

J3 J7

S E B R O W 23

S E B R O W 24

S E B R O W 24

Term Plug

S E B R O W 25

S E B R O W 25

S E B R O W 26

S E B R O W 26

S E B R O W 27

S E B R O W 27

S E B R O W 28

S E B R O W 28

J3

PW B 7

PW B 8

J2

Term P lug

Term P lug

S E B R O W 14

A /C P ow er

S E B R O W 15

Term P lug

Term P lug

S E B R O W 13 D E F

S E B R O W 14

Term P lug

Term P lug

SEB ROW 7 DE

MCU 1 J2 J9

Term P lug

S E B R O W -6

J8 J4

SEB ROW 8

Term P lug

Term P lug

J2 J3

S E B R O W 29

S E B R O W 29

S E B R O W 30

S E B R O W 30

S E B R O W 31

S E B R O W 31

Term P lug



Page 7-18

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 8 8.1

APPENDIX A319 DATA (SEAT-TO-SEAT CABLING)

ADB 1

ADB 2



Page 8-1

Apr 2008


DATA (ADB 1 TO SEAT GROUPS) AJ SVDU DPCU

Term Plug

AJ SVDU DPCU

To VCC

SEB ROW 1 AC

AJ SVDU DPCU

From AVC

SVDU DPCU

AJ

SVDU

SEB ROW -1 DF

SVDU DPCU

AJ

AJ

SVDU DPCU

AJ

AJ

SVDU

SEB ROW 2

J3

WDB 1

WDB 2

J2

Term Plug

AJ SVDU DPCU

ADB 1 J5

SVDU

J3

AJ SVDU DPCU

SEB ROW 3 DEF

AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU


AJ SVDU


WDB 4

DPCU

DPCU

SEB ROW 8 AJ AJ AJ SVDU SVDU SVDU DPCU DPCU DPCU AJ SVDU


AJ SVDU DPCU

AJ SVDU DPCU

J2 J3

J2 DPCU

Term Plug

SEB ROW -3 DEF AJ SVDU DPCU

WDB 3

AJ

AJ SVDU DPCU

AJ SVDU DPCU

J3

Term Plug

AJ SVDU DPCU

J2

SEB ROW -3 ABC AJ SVDU DPCU

AJ

Term Plug

J1 J4

J6

SEB ROW 3 ABC

AJ SVDU DPCU

J2 J3

J8 AJ SVDU DPCU

SVDU DPCU

SEB ROW 2

SVDU

Term Plug AJ SVDU DPCU

Term Plug

SEB ROW 1 DF

SEB ROW -1 AC AJ

AJ SVDU DPCU

DPCU

To ADB 2

DPCU

DPCU

AJ SVDU DPCU


AJ SVDU


Term Plug



Page 8-2

Apr 2008


DATA (ADB 2 TO SEAT GROUPS) DPCU

Term Plug

DPCU

DPCU

DPCU

AJ SVDU DPCU

AJ SVDU DPCU

AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU DPCU


SEB ROW 14 AJ AJ AJ SVDU SVDU SVDU DPCU DPCU DPCU SEB ROW 15 AJ AJ SVDU SVDU


DPCU

DPCU

J2

WDB 6

WDB 5

AJ SVDU

Term Plug DPCU

J8 J6

J1 J4

J5

AJ SVDU DPCU

J2

DPCU

DPCU


ADB 2


J3

DPCU

SEB ROW 16 AJ AJ AJ SVDU SVDU SVDU DPCU DPCU DPCU AJ SVDU DPCU

AJ SVDU DPCU

AJ SVDU DPCU


AJ SVDU DPCU


AJ SVDU


AJ SVDU


J3

AJ SVDU DPCU

DPCU

DPCU

Term Plug


J3

AJ SVDU DPCU

DPCU

Term Plug

J2

J3 Term Plug

Term Plug

DPCU

AJ SVDU DPCU

AJ SVDU

Term Plug

DPCU


From ADB 1

SEB ROW 10

WDB 8

WDB 7

J2 J3

J2


DPCU AJ SVDU DPCU

DPCU

SEB ROW 21

SEB ROW 21

DPCU


Term Plug



Page 8-3

Apr 2008


DATA (ADB TO WDB/SEB/SVDU/DPCU) BUSINESS CLASS

ADB # Output #

WDB # Output #

SEB #

1-J6

WDB1-J3

SEB 1AC

1-J6

WDB1-J3

SEB -1AC

1-J6

WDB1-J3

SEB 2AC

1-J6

WDB1-J2

N/A

1-J4

WDB2-J2

SEB 1DF

1-J4

WDB2-J2

SEB -1DF

1-J4

WDB2-J2

SEB 2DF

1-J4

WDB2-J3

N/A

SVDU Port

DPCU Port

SVDU Seat Number

1 2 1 2 N/A N/A N/A N/A 1 2 1 2 N/A N/A N/A N/A

1 2 N/A N/A 1 2 N/A N/A 1 2 N/A N/A 1 2 N/A N/A

1A 1C 2A 2C N/A N/A N/A N/A 1D 1F 2D 2F N/A N/A N/A N/A

DPCU Seat Numbe r 1A 1C N/A N/A 2A 2C N/A N/A 1D 1F N/A N/A 2D 2F N/A N/A

Seat Row 1 1 1 1 2 2 N/A N/A 1 1 1 1 2 2 N/A N/A

ECONOMY CLASS ADB # Output #

WDB # Output #

SEB #

1-J5

WDB3-J3

SEB 3ABC

1-J5

WDB3-J3

SEB -3ABC

1-J5

WDB3-J3

SEB 4ABC

1-J5

WDB3-J3

SEB 5ABC

SVDU Port

DPCU Port

SVDU Seat Number

1 2 3 1 2 3 1 2 3 1 2 3

1 2 3 N/A N/A N/A 1 2 3 1 2 3

3A 3B 3C 4A 4B 4C 5A 5B 5C 6A 6B 6C

DPCU Seat Numbe r 3A 3B 3C N/A N/A N/A 4A 4B 4C 5A 5B 5C

Seat Row 3 3 3 3 3 3 4 4 4 5 5 5



Page 8-4

Apr 2008


WDB # Output #

SEB #

1-J5

WDB3-J3

SEB 6ABC

1-J5

WDB3-J3

SEB 7ABC

1-J5

WDB3-J2

SEB 8ABC

1-J5

WDB3-J2

SEB 9ABC

1-J3

WDB4-J2

SEB 3DEF

1-J3

WDB4-J2

SEB -3DEF

1-J3

WDB4-J2

SEB 4DE

1-J3

WDB4-J2

SEB 5DEF

1-J3

WDB4-J2

SEB 6DEF

1-J3

WDB4-J2

SEB 7DEF

1-J3

WDB4-J3

SEB 8DEF

1-J3

WDB4-J3

SEB 9DEF

2-J6

WDB5-J3

SEB 10ABC

SVDU Port

DPCU Port

SVDU Seat Number

1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3

1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3

7A 7B 7C 8A 8B 8C 9A 9B 9C 10 A 10 B 10 C 3D 3E 3F 4D 4E 4F 5D 5E 5F 6D 6E 6F 7D 7E 7F 8D 8E 8F 9D 9E 9F 10 D 10 E 10 F 11 A 11 B 11 C

DPCU Seat Numbe r 6A 6B 6C 7A 7B 7C 8A 8B 8C 9A 9B 9C 3D 3E 3F N/A N/A N/A 4D 4E 4F 5D 5E 5F 6D 6E 6F 7D 7E 7F 8D 8E 8F 9D 9E 9F 10 A 10 B 10 C

Seat Row 6 6 6 7 7 7 8 8 8 9 9 9 3 3 3 3 3 3 4 4 4 5 5 5 6 6 6 7 7 7 8 8 8 9 9 9 10 10 10



Page 8-5

Apr 2008


WDB # Output #

SEB #

2-J6

WDB5-J3

SEB 11ABC

2-J6

WDB5-J3

SEB 12ABC

2-J6

WDB5-J3

SEB 13ABC

2-J6

WDB5-J3

SEB 14ABC

2-J6

WDB5-J3

SEB 15ABC

2-J6

WDB5-J2

N/A

2-J4

WDB5-J2

SEB 10DEF

2-J4

WDB5-J2

SEB 11DEF

2-J4

WDB5-J2

SEB 12DEF

2-J4

WDB5-J2

SEB 13DEF

2-J4

WDB5-J2

SEB 14DEF

2-J4

WDB5-J2

SEB 15DEF

2-J4

WDB5-J3

N/A

SVDU Port

DPCU Port

SVDU Seat Number

1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A

1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A

12 A 12 B 12 C 13 A 13 B 13 C 14 A 14 B 14 C 15 A 15 B 15 C 16 A 16 B 16 C N/A N/A N/A 11 D 11 E 11 F 12 D 12 E 12 F 13 D 13 E 13 F 14 D 14 E 14 F 15 D 15 E 15 F 16 D 16 E 16 F N/A N/A N/A

DPCU Seat Numbe r 11 A 11 B 11 C 12 A 12 B 12 C 13 A 13 B 13 C 14 A 14 B 14 C 15 A 15 B 15 C N/A N/A N/A 10 D 10 E 10 F 11 D 11 E 11 F 12 D 12 E 12 F 13 D 13 E 13 F 14 D 14 E 14 F 15 D 15 E 15 F N/A N/A N/A

Seat Row 11 11 11 12 12 12 13 13 13 14 14 14 15 15 15 N/A N/A N/A 10 10 10 11 11 11 12 12 12 13 13 13 14 14 14 15 15 15 N/A N/A N/A



Page 8-6

Apr 2008


WDB # Output #

SEB #

2-J5

WDB7-J3

SEB 16ABC

2-J5

WDB7-J3

SEB 17ABC

2-J5

WDB7-J3

SEB 18ABC

2-J5

WDB7-J3

SEB 19ABC

2-J5

WDB7-J2

SEB 20ABC

2-J5

WDB7-J2

SEB 21ABC

2-J3

WDB8-J2

SEB 16DEF

2-J3

WDB8-J2

SEB 17DEF

2-J3

WDB8-J2

SEB 18DEF

2-J3

WDB8-J2

SEB 19DEF

2-J3

WDB8-J3

SEB 20DEF

2-J3

WDB8-J3

SEB 21DEF

SVDU Port

DPCU Port

SVDU Seat Number

1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A

1 2 3 N/A N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3 1 2 3 N/A N/A N/A 1 2 3 1 2 3 1 2 3 1 2 3

17 A 17 B 17 C 18 A 18 B 18 C 19 A 19 B 19 C 20 A 20 B 20 C 21 A 21 B 21 C N/A N/A N/A 17 D 17 E 17 F 18 D 18 E 18 F 19 D 19 E 19 F 20 D 20 E 20 F 21 D 21 E 21 F N/A N/A N/A

DPCU Seat Numbe r 16 A 16 B 16 C 17 A 17 B 17 C 18 A 18 B 18 C 19 A 19 B 19 C 20 A 20 B 20 C 21 A 21 B 21 C 16 D 16 E 16 F 17 D 17 E 17 F 18 D 18 E 18 F 19 D 19 E 19 F 20 D 20 E 20 F 21 D 21 E 21 F

Seat Row 16 16 16 17 17 17 18 18 18 19 19 19 20 20 20 21 21 21 16 16 16 17 17 17 18 18 18 19 19 19 20 20 20 21 21 21



Page 8-7

Apr 2008


DATA AND RF (SEAT CONFIGURATION NOTES) Business Class (Rows 1 and 2)






Page 8-8

Apr 2008


Economy Class First Two Rows (Rows 3 and 4)



For SEB 4 connected to ADB 1 seat configuration is remote • Control for the 3 seats is provided in its row (DPCU seat arm mounted) • Video for the 3 seats is provided behind it (SVDU seat-back) • Audio for the 3 seats is provided behind it (audio jacks arm mounted) • SVDUs are touch-screen



Page 8-9

Apr 2008


Economy Class Last Two Rows (Rows 20 and 21)




Page 8-10

Apr 2008


POWER (SEAT-TO-SEAT CABLING)

MCU1 MCU2



Page 8-11

Apr 2008

NACIL(I) A321/A320/A319 i3000 Line Maintenance Training Manual 8.7 Term Plug

POWER (MCUS TO SEAT GROUPS) AVC SEB ROW 1 AC

A/C Power

SEB ROW 1 DF SEB ROW -1

SEB ROW -1

SEB ROW 2

SEB ROW 2

J3 Term Plug Term Plug

PWB 2

PWB 1

J2

J2 J3

SEB ROW 3 ABC

J9 J1

SEB ROW -3

J2 J9

J4

SEB ROW 4

J7

SEB ROW 5 SEB ROW 6

SEB ROW 6

J3

PWB 4

PWB 3

J2 J3

J2 SEB ROW 7

SEB ROW 7

SEB ROW 8

SEB ROW 8

SEB ROW 9

SEB ROW 9 SEB ROW 10


SEB ROW 13

SEB ROW 13

SEB ROW 14


J3

PWB 6

PWB 5

J2 J3

J2 J9

SEB ROW 16

MCU 2 J2

J4

SEB ROW 16

J3

SEB ROW 17

J7

PWB 8

PWB 7

Term Plug

SEB ROW 18

SEB ROW 18

J3

Term Plug

J8

J1 SEB ROW 17

J2 J3

J2

Term Plug

Term Plug

SEB ROW 12

SEB ROW 15

Term Plug

Term Plug

SEB ROW 11

A/C Power

SEB ROW 12

Term Plug

Term Plug

SEB ROW -3

J3

SEB ROW 5

Term Plug

Term Plug

SEB ROW 3DEF

J8

MCU 1

SEB ROW 4

Term Plug

Term Plug

SEB ROW 19

SEB ROW 19

SEB ROW 20

SEB ROW 20

SEB ROW 21

SEB ROW 21

Term Plug



Page 8-12

Apr 2008

IFE Training Manual

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