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TO:

HOLDERS OF AIRCRAFT MAINTENANCE MANUAL, ATA NUMBER 44-21-74, REVISION 3, DATED OCT 15/07, FOR THE LAN 767 TOPSERIES™ i4000 SYSTEM. REVISION NUMBER 4, DATED FEB 28/09 HIGHLIGHTS

Descriptions of the changes contained in this revision are listed in the table below. All changes have been incorporated into this complete Revision 4 Aircraft Maintenance Manual document which supersedes the Revision 3 version in its entirety. All technical changes to the content of this manual are identified with change bars in the left hand margin of the document body. CHAPTER/SECTION AND PAGE NUMBER

DESCRIPTION OF CHANGE

EFFECTIVITY

All Pages

Revised to reflect the addition of SUBTASKs for document simplification.

ALL

Title page

Revised to reflect current revision and date along with new Thales logo to include cage code. Revised to reflect the addition of Line Fit aircraft.

ALL

Record of Revisions, Page 1

Revised to reflect current revision and date.

ALL

Service Bulletins List, page 1

Revised to reflect current Service Bulletins added to the Maintenance Practices section.

ALL

List of Effective Pages, Pages

Revised to reflect current pages and date of revision.

ALL

Table of Contents

Revised to reflect the relocation of table of contents to the beginning of each section. Revised to reflect the current contents of the document.

ALL

Introduction Pages, INTRO 3, 4

Revised to Reflect new line fit aircraft added to the configuration List. Revised to reflect current sections and there usage.

ALL

Description and Operation Pages, 5, 6, 11, 12, 14, 15, 17, 18, 19, 20, 24, 25, 31, 34, 36, 43-45, 53-56, 58, 63, 71, 80-85, 110-116, 118, 120, 124-206

Revised to reflect the addition of TOC to the beginning of the section. Revised to reflect detailed descriptions of current Content Loading procedure, Content Summery Static Test, Offload procedures. Revised to reflect reformatting of LRU descriptions to be more component description.

ALL

Component Locations Pages, 1011-1034

Revised to reflect the addition of TOC to the beginning of the section. Revised to reflect current Business Class and Economy Class interconnect diagrams.

ALL

Maintenance Practices, All Pages

Revised to reflect the addition of Table of Contents to the beginning of section. Revised to reflect the addition of section to include all Maintenance Practice Procedures. Revised to reflect the implementation of service bulletins to sustain current software update.

ALL

44-21-74

Highlights Page 1 of 2 Feb 28/09

CHAPTER/SECTION AND PAGE NUMBER

DESCRIPTION OF CHANGE

EFFECTIVITY

Removal/Install

Revised to reflect the addition of Table of Contents to the beginning of section.

ALL

Adjustment Test, All Pages

Revised to reflect new functional test to include a 3 level structure.

ALL

Inspection Check

Revised to reflect the addition of Table of Contents to the beginning of section.

ALL

Cleaning and Painting

Revised to reflect the addition of Table of Contents to the beginning of section.

ALL

44-21-74

Highlights Page 2 of 2 Feb 28/09

Aerospace Division THALES AVIONICS, INC. 58 Discover y Irvine, California 92618-3105 U SA Te l: +1 (949) 790-2500

CAGE Code: 0LWJ2 www.thalesgr oup.com

AIRCRAFT MAINTENANCE MANUAL LAN Airlines B767 Aircraft: 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229, 34626, 34628, 34629, 35229, 35230, 35231, 35696, 35697, 35698, 36710, 36711, 36712

TopSeries™ i4000 System

Control Statement:

The technical data in this document (or file) is controlled for export under the Export Administration Regulations (EAR), 15 CFR Parts 730-774, ECCN: 5E991. Violations of these laws may be subject to fines and penalties under the Export Administration Act.

Proprietary Statement:

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

44-21-74

Initial Issue, Nov 30/05 Revision 4, Feb 28/09 Title Page T-1

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

This page is intentionally blank.

44-21-74

Title Page T- 2 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

TABLE TASK 44-21-74-990-801-A01 RECORD OF REVISIONS REVISION NUMBER

ISSUE DATE

DATE INSERTED

BY

1

Jul 28/06

Jul 28/06

Thales

2

Mar 30/07

Mar 30/07

Thales

3

Oct 15/07

Oct 15/07

Thales

4

Feb 28/09

REVISION NUMBER

EFFECTIVITY ALL

44-21-74

ISSUE DATE

DATE INSERTED

BY

Record of Revisions Page RR 1 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

This page is intentionally blank.

EFFECTIVITY ALL

44-21-74

Record of Revisions Page RR 2 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

TABLE TASK 44-21-74-990-802-A01 RECORD OF TEMPORARY REVISIONS REVISION NUMBER

ISSUE DATE

INSERTION DATE

REMOVAL DATE

INCORPORATOR’S INITIALS

EFFECTIVITY ALL

44-21-74

REMOVER’S INITIALS

Record of Temporary Revisions Page RTR 1 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

This page is intentionally blank.

EFFECTIVITY ALL

44-21-74

Record of Temporary Revisions Page RTR 2 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

TABLE TASK 44-21-74-990-803-A01 SERVICE BULLETIN LIST ORIGINAL ISSUE DATE

SERVICE BULLETIN REVISION NUMBER

DATE INCORPORATED INTO THIS MANUAL

SIL-06-27-06

Jun 27/06

0

Jul 28/06

620130-711-44-001

Mar 14/06

0

Jul 28/06

620130-711-44-002

Mar 15/06

0

Jul 28/06

620130-711-44-004

Jul 12/06

2

Jul 28/06

620130-711-44-005

Jul 13/06

0

Jul 28/06

620130-711-44-006

Jul 25/06

0

Mar 30/07

620130-711-44-007

Sep 12/06

0

Mar 30/07

620130-711-44-008

Nov 2/06

2

Mar 30/07

620130-711-44-009

Mar 29/07

1

Mar 30/07

620130-711-44-010

May 15/07

0

Oct 15/07

620130-711-44-011

Jul 12/07

1

Oct 15/07

620130-712-44-001

Jul 26/06

0

Jul 28/06

620130-712-44-002

Sep 14/06

0

Mar 30/07

620130-712-44-003

Oct 10/06

0

Mar 30/07

620130-712-44-004

Dec 11/06

0

Mar 30/07

620130-712-44-005

May 29/07

0

Oct 15/07

620130-712-44-006

Jul 12/07

1

Oct 15/07

620130-711-44-012

Jan 10/08

0

Feb 28/09

620130-711-44-013

Jan 22/08

0

Feb 28/09

620130-711-44-014

Feb 5/08

0

Feb 28/09

620130-711-44-014

Mar 18/08

1

Feb 28/09

SERVICE BULLETIN NUMBER

EFFECTIVITY ALL

44-21-74

Service Bulletin List Page SBL 1 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

SERVICE BULLETIN LIST ORIGINAL ISSUE DATE

SERVICE BULLETIN REVISION NUMBER

DATE INCORPORATED INTO THIS MANUAL

620130-711-44-014

Mar 26/08

2

Feb 28/09

620130-712-44-007

Jan 22/08

0

Feb 28/09

620130-712-44-008

Feb 8/08

0

Feb 28/09

620130-712-44-008

Mar 25/08

1

Feb 28/09

SERVICE BULLETIN NUMBER

EFFECTIVITY ALL

44-21-74

Service Bulletin List Page SBL 2 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

LIST OF EFFECTIVE PAGES DATE

SUBJECT

PAGE

DATE

T-1 T-2

Feb 28/09 Feb 28/09

Description And Operation (Continued)

Record of Revisions

RR-1 RR*2

Feb 28/09 Feb 28/09

Temporary Revisions

RTR-1 RTR-2

Feb 28/09 Feb 28/09

Service Bulletin List

SBL-1 SBL-2

Feb 28/09 Feb 28/09

List of Effective Pages

LEP-1 LEP-2 LEP-3 LEP-4

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

Description And Operation

1 2 3 4 5 6 7 8 9/10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47/48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

SUBJECT

PAGE

Title Page

*

Indicates pages changed, added, or deleted.

F

Indicates foldout page.

EFFECTIVITY ALL

44-21-74

List of Effective Pages Page LEP 1 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM SUBJECT

PAGE

Description And Operation (Continued)

70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114

DATE

SUBJECT

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

Description And Operation (Continued)

*

Indicates pages changed, added, or deleted.

F

Indicates foldout page.

EFFECTIVITY ALL

44-21-74

PAGE 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137/138 139 140 141 142 143 144 145 146 147/148 149 150 151 152 153 154 155 156 157 158 159 160 161

DATE Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

List of Effective Pages Page LEP 2 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM SUBJECT

PAGE

Description And Operation (Continued)

162 163 164 165 166 167 168 169 170 171 172 173 174 175 176 177 178 179 180 181 182 183 184 185 186 187 188 189 190 191 192 193 194 195 196 197 198 199 200 201 202 203 204 205 206

DATE

SUBJECT

PAGE

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

Component Locations

1001 1002 1003 1004 1005 1006 1007 1008 1009 1010 1011 1012 1013/1014 1015/1016 1017/1018 1019/1020 1021/1022 1023/1024 1025/1026 1027/1028 1029/1030 1031/1032 1033/1034 1035/1036 1037 1038 1039 1040

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

Maintenance Practices

2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

*

Indicates pages changed, added, or deleted.

F

Indicates foldout page.

EFFECTIVITY ALL

44-21-74

DATE

List of Effective Pages Page LEP 3 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM SUBJECT

PAGE

DATE

SUBJECT

PAGE

DATE

Maintenance Practices (Continued)

2017 2018 2019 2020 2021 2022 2023 2024 2025 2026 2027 2028 2029 2030 2031 2032

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

Removal/ Install (Continued)

4029 4030 4031 4032 4033 4034 4035 4036 4037 4038 4039 4040

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

Adjustment Test

4001 4002 4003 4004 4005 4006 4007 4008 4009 4010 4011 4012 4013 4014 4015 4016 4017 4018 4019 4020 4021 4022 4023 4024 4025 4026 4027 4028

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

5001 5002 5003 5004 5005 5006 5007 5008 5009 5010

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

Inspection Check

6001 6002 6003 6004

Feb 28/09 Feb 28/09 Feb 28/09 Feb 28/09

Cleaning and Painting

7001 7002

Feb 28/09 Feb 28/09

Removal/ Install

*

Indicates pages changed, added, or deleted.

F

Indicates foldout page.

EFFECTIVITY ALL

44-21-74

List of Effective Pages Page LEP 4 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

INTRODUCTION TITLE

PAGE

TASK 44-21-74-990-804-A01 1.

General............................................................................................................ INTRO-2

TASK 44-21-74-990-805-A01 2.

Usage Guide ................................................................................................... INTRO-2

TASK 44-21-74-990-806-A01 3.

Warnings, Cautions, and Notes ....................................................................... INTRO-3

TASK 44-21-74-990-807-A01 4.

System Configuration ...................................................................................... INTRO-4

TASK 44-21-74-990-808-A01 5.

Acronym, Abbreviation, and Symbol Definitions .............................................. INTRO-4

TASK 44-21-74-990-809-A01 6.

Aircraft Maintenance Task Oriented Support System ...................................... INTRO-8

EFFECTIVITY ALL

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Page INTRO 1 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

INTRODUCTION TASK 44-21-74-990-804-A01 1.

General NOTE: This document is written to supplement information contained in the Boeing Aircraft Maintenance Manual (AMM). No information in this document is intended to contradict or supersede the Boeing 767 AMM in any way. If this document contains information that conflicts with information in the Boeing 767 AMM, the Boeing 767 AMM shall supersede this document in all instances. A.

This Aircraft Maintenance Manual (AMM) provides line maintenance information for the Thales Avionics, Incorporated, TopSeries™ i4000 System for LAN Airlines, Boeing B767 aircraft.

B.

This manual is accurate to released engineering source data as of the date of publication.

C.

This manual does not include information that is generated, controlled, or installed by other equipment manufacturers.

D.

This manual does not include information that is generated, controlled, or installed by the aircraft manufacturer.

E.

Line maintenance preventive and corrective procedures are based primarily on performing fault isolation, replacement of the Line Replaceable Unit (LRU) and performing operational tests as desired in this manual.

F.

For individual LRU servicing information, refer to associated Component Maintenance Manuals (CMM). Documentation may be requested from Thales Avionics, Incorporated, at the following address: Technical Publications Department Manager 58 Discovery Irvine, CA 92618-3105 USA (949) 595-8510

TASK 44-21-74-990-805-A01 2.

Usage Guide This AMM is written to Air Transport Association (ATA) Specification iSpec2200, Revision 2001.1. Refer to Table of Contents (TOC) to find necessary maintenance procedures or other data. This AMM is applicable for the aircraft serial numbers listed on the title page. A.

System Description and Operation

EFFECTIVITY ALL

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Page INTRO 2 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

Describes purpose and operation of the system and each LRU in the system. B.

Component Locations Identifies locations of system components.

C.

Maintenance Practices Provides Phase Download procedures, Software Listings, and Content Loading Procedures.

D.

Servicing Not Used

E.

Removal/Installation Contains procedures to remove and install each LRU.

F.

Adjustment/Test Provides tests and adjustments to evaluate operational efficiency of system and components.

G.

Inspection/Check Provides physical inspection criteria for various components of the system.

H.

Cleaning/Painting Contains special cleaning and painting requirements for system LRUs.

I.

Repair Not Used

TASK 44-21-74-990-806-A01 3.

Warnings, Cautions, and Notes A.

Warnings Notices preceding potentially dangerous procedures, materials, methods, or processes which must be followed precisely to avoid injury to personnel.

B.

Cautions Notices preceding information or methods and procedures, which must be followed to avoid damage to equipment.

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

C.

Notes Clarification statements following information or methods and procedures.

TASK 44-21-74-990-807-A01 4.

System Configuration All aircraft covered by this manual are Boeing 767 aircraft configured for 221 Passengers (PAX); 30 Business Class and 191 Economy Class seats. Some of the aircraft were linefit at Boeing and some were retrofit by Thales. Refer to the Linefit and Retrofit Tail Number Index below for linefit and retrofit tail number information. Differences in data applicability for the linefit and retrofit aircraft are identified using the Effectivity block in the bottom left corner of each page. Linefit and Retrofit Tail Number Index

RETROFIT

LINEFIT

Registration Number CC-CBJ CC-CDM CC-CDP CC-CEB CC-CRG CC-CRH CC-CRV CC-CZT CC-CZU CC-CZW HC-CGZ LV-BFD LV-BMR CC-CWF CC-CWG CC-CWH CC-CWN CC-CWV CC-CWY CC-CXC CC-CXD CC-CXE CC-CXF CC-CXG CC-CXH

Serial Number 27613 26261 27597 26327 25865 25864 27615 29228 29229 29227 28206 26265 26329 34626 34629 34628 35229 35230 35231 36710 35697 35696 36711 36712 35698

Variable number VN969 VN971 VN966 VN967 VN064 VN063 VN970 VS132 VS133 VS131 VS111 VL-703 VN968 VS901 VS902 VS903 VS904 VS905 VS906 VA907 VS908 VS909 VS910 VS921 VS922

TASK 44-21-74-990-808-A01 EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

5.

Acronym, Abbreviation, and Symbol Definitions The following list defines acronyms, abbreviations, and symbols used in this manual: Acronym, Abbreviation, or Symbol

Definition

AC

Alternating Current

A/C

Aircraft

ACOU

Alternating Current Outlet Unit

ADB

Area Distribution Box

AJ AMM AMTOSS

CMM CMS CMT Conn

Audio Jack Aircraft Maintenance Manual Aircraft Maintenance Task Oriented Support System Audio On Demand Aeronautical Radio Incorporated Audio Reproducer Unit Air Transport Association Air Transport Radio Audio/Video Controller Base Band Video Business Class Broadcast Baseband Frequency Division Multiplexed Background Music Basic Input/Output System Built In Test Built In Test Equipment Boarding Music Machine Centigrade California Circuit Card Assembly Cold Cathode Fluorescent Lamp Communication Control Unit Compact Disc-Read Only Memory Conference European de Posts et Telecommunications Component Maintenance Manual Cabin Management System Cabin Management Terminal Connector

CPU

Central Processing Unit

AOD ARINC ARU ATA ATR AVC BBV B/C B’Cast BFDM BGM BIOS BIT BITE BMM C CA CCA CCFL CCU CD-ROM CEPT

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

Acronym, Abbreviation, or Symbol

Definition

CSS

Cabin Service System

DC

Direct Current

DPCU

Digital Passenger Control Unit

DSP

Digital Signal Processor

DSU

Digital Server Unit

EBAY

Electronics Bay

E/C

Economy Class

ENET

Ethernet

ESD

Electrostatic Discharge

FET

Field Effect Transistors

FF

Fast Forward

FM

Frequency Modulated

GB

Gigabyte(s)

Hz

Hertz

ID

Identification

IFE

Inflight Entertainment

IFES

Inflight Entertainment System

INTRO

Introduction

I/O

Input/Output

IP

Internet Protocol

ISDN

Integrated Services Digital Network

ISPC

In-Seat Power Converter

KBD

Keyboard

kbps

Kilobit Per Second

kg

Kilogram

Lbs

Pounds

LCD

Liquid Crystal Display

LED

Light Emitting Diode

LLC

Limited Liability Corporation

LRU

Line Replaceable Unit

mA

milliampere

Max

Maximum

MB

Megabyte(s)

Mbit

Megabits

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

Acronym, Abbreviation, or Symbol

Definition

Mbps

Megabits per second

MCU

Master Control Unit

MHz

Megahertz

mm

Millimeter

MPEG

Moving Pictures Experts Group

MUX

Multiplexer

No

Number

NRM

Noise Reduction Module

NTSC

National Television Systems Committee

OEB

Overhead Electronics Box

O/H

Overhead

ohm

Unit of Electrical Resistance

OSD

On-Screen Display

PA

Passenger Announce(ment) or Public Address

PAX

Passengers

PC

Personal Computer

PCB

Printed Circuit Board

PDL

Portable Data Loader

PED

Personal Electronic Device

PES

Passenger Entertainment System

PFC

Power Factor Corrector

PFIS

Passenger Flight Information System

PM

Programming Module

POST

Power On Self Test

PRAM

Pre-Recorded Announcement Machine

PS

Power Supply

PSAC

Please Select Another Channel

PSS

Passenger Service System

PWR

Power

RAM

Random Access Memory

Rew

Rewind

RF

Radio Frequency

RF

Reference

RJM

Remote Jack Module

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

Acronym, Abbreviation, or Symbol

Definition

RO

Receive Only

ROM

Read Only Memory

Rx

Receive

SC

Switch Control

SCSI

Small Computer System Interface

SEB

Seat Electronics Box

SRU

Shop Replaceable Unit

STA

Station

THALES

Thales Avionics, Incorporated

TOC

Table Of Contents

TPCU-b

Tethered Passenger Control Unit - Basic

TU

Tapping Unit

Tx

Transmit

UART

Universal Asynchronous Receiver Transmitter

USA

United States of America

USB

Universal Serial Bus

V

Volts

VA

Video2 Announcement

VAC

Volts Alternating Current

VCC

Video Control Center

VDC

Volts Direct Current

VDU

Video Display Unit

VME

Versa Module Eurocard

Vp-p

Volts Peak-to-Peak

VRU

Video Reproducer Unit

VTR

Video Tape Reproducer

W WDB WOW

Watts Wall Disconnect Box Weight-On-Wheels

TASK 44-21-74-990-809-A01 6.

Aircraft Maintenance Task Oriented Support System A.

The Aircraft Maintenance Task-Oriented Support System (AMTOSS) permits the use of electronic data processing of aircraft maintenance data.

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

NOTE:

B.

For detailed information, refer to Aircraft Maintenance Manual section of ATA Specification iSpec2200, Revision 2001.1.The AMTOSS system uses standard and unique number combinations to identify aircraft maintenance tasks and SUBTASKs.

1)

The AMTOSS structure is a logical approach to organizing aircraft maintenance tasks and SUBTASKs.

2)

The AMTOSS numbering system includes ATA chapter-section-subject number as well as a function code and unique identifiers.

3)

The purpose of the AMTOSS numbering system is to provide a means for automated sorting, retrieval, and management of digitized data.

The AMTOSS numbering system is an expansion of the ATA three-element numbering system. An AMTOSS number has seven elements of which the first five elements are mandatory for each task and SUBTASK. The sixth and seventh elements are applied when necessary. This AMM incorporates the use of six of the seven elements (refer to Figure INTRO-1). 1)

Element numbers 1, 2, and 3 Existing ATA numbers. a)

Element number 1 Chapter

b)

Element number 2 Section

c)

Element number 3 Subject

2)

Element number 4 Numerically defines aircraft maintenance function being performed.

3)

Element number 5. Provided to create unique numbers for all tasks or SUBTASKs that are similarly numbered through the first four elements. a)

Tasks are numbered from 801 through 999.

b)

SUBTASKs are numbered 001 through 800.

4)

Element number 6:

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A three-position alphanumeric number that allows for identification of differences in configurations, methods and techniques, variations of standard practice applications, etc. a)

Most tasks in this AMM will use A01 as the sixth element. This indicates that the task applies to all configurations with no variation.

b)

If an S01 is used as the sixth element, it will indicate that a service bulletin applies to the task.

5)

Element number 7: A three-position alphanumeric number reserved for customer use.

Example of an AMTOSS number: TASK 44-XX-XX-700-824-A01

1

ELEMENT NUMBERS 3 2 4 5 6

TASK 44-XX-XX-700-824-A01

CHAPTER SECTION SUBJECT MAINTENANCE FUNCTION 700 = TESTING UNIQUE NO. SUBTASK = 001-800 TASK = 801-899 IDENTIFICATION DIFFERENCES A01 = ALL CONFIGURATIONS

GRAPHIC TASK 44-21-74-990-810-A01 Explanation of Aircraft Maintenance Task-Oriented Support System (AMTOSS) Task Codes Figure INTRO-1

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DESCRIPTION AND OPERATION PAGE

SUBJECT TASK 44-21-74-990-811-A01 1.

General.........................................................................................................................5

SUBTASK 44-21-74-990-001-A01 A. Passenger Services ................................................................................................5 SUBTASK 44-21-74-990-002-A01 B. Cabin Attendant Features .......................................................................................6 SUBTASK 44-21-74-990-003-A01 C. Maintenance Features ............................................................................................6 TASK 44-21-74-990-812-A01 2.

System Architecture .....................................................................................................6

SUBTASK 44-21-74-990-004-A01 A. Head-End Line Replaceable Units (LRUs) ..............................................................6 SUBTASK 44-21-74-990-005-A01 B. Distribution LRUs....................................................................................................7 SUBTASK 44-21-74-990-006-A01 C. Seat-End LRUs.......................................................................................................7 SUBTASK 44-21-74-990-007-A01 D. System Block Diagram............................................................................................7 TASK 44-21-74-990-814-A01 3.

System Functional Description ...................................................................................11

SUBTASK 44-21-74-990-008-A01 A. List of Functions....................................................................................................11 SUBTASK 44-21-74-990-009-A01 B. Operator Interface ................................................................................................11 EFFECTIVITY ALL

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SUBJECT

PAGE

SUBTASK 44-21-74-990-010-A01 C. Broadcast Mode system, In-Seat Audio................................................................ 43 SUBTASK 44-21-74-990-011-A01 D. In-Seat Video Broadcast Mode system, In-Seat Audio ......................................... 44 SUBTASK 44-21-74-990-012-A01 E. In-Seat Video and Audio Control .......................................................................... 44 SUBTASK 44-21-74-990-013-A01 F. Overhead Distributed Video ................................................................................. 52 SUBTASK 44-21-74-990-014-A01 G. Passenger Announcement (PA) ........................................................................... 52 SUBTASK 44-21-74-990-015-A01 H. Video Passenger Announcement ......................................................................... 53 SUBTASK 44-21-74-990-016-A01 I.

Decompression .................................................................................................... 54

SUBTASK 44-21-74-990-017-A01 J. Moving Map.......................................................................................................... 54 SUBTASK 44-21-74-990-018-A01 K. USB for Peripheral Devices.................................................................................. 56 SUBTASK 44-21-74-990-019-A01 L. PED Connectivity ................................................................................................. 56 SUBTASK 44-21-74-990-020-A01 M. Maintenance......................................................................................................... 56 TASK 44-21-74-990-930-A01 4.

Line Replaceable Unit Descriptions.......................................................................... 124

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SUBJECT

PAGE

SUBTASK 44-21-74-990-021-A01 A. Audio/Video Controller (AVC) .............................................................................124 SUBTASK 44-21-74-990-022-A01 B. Digital Server Unit-AM6-12 (DSU-AM6-12) .........................................................127 SUBTASK 44-21-74-990-023-A01 C. Digital Server Unit-D2 (DSU-D2).........................................................................131 SUBTASK 44-21-74-990-024-A01 D. Ethernet Switching Unit-Gigabit (ESU-G)............................................................134 SUBTASK 44-21-74-990-025-A01 E. Area Distribution Box (ADB)................................................................................137 SUBTASK 44-21-74-990-026-A01 F. Master Control Unit (MCU)..................................................................................141 SUBTASK 44-21-74-990-027-A01 G. Programming Module (PM) .................................................................................145 SUBTASK 44-21-74-990-028-A01 H. Tapping Unit (TU) ...............................................................................................147 SUBTASK 44-21-74-990-029-A01 I.

Seat Electronics Box (SEB) ................................................................................150

SUBTASK 44-21-74-990-030-A01 J. Tethered Passenger Control Unit – Basic (TCPU-b)...........................................153 SUBTASK 44-21-74-990-031-A01 K. 15.4 Inch Smart Video Display Unit (SVDU) .......................................................157 SUBTASK 44-21-74-990-032-A01 L. 10.4 Inch Integrated Cabin Management Terminal (iCMT) .................................160 EFFECTIVITY ALL

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SUBJECT

PAGE

SUBTASK 44-21-74-990-033-A01 M. 8.9 Inch Smart Video Display Unit (SVDU) ......................................................... 163 SUBTASK 44-21-74-990-034-A01 N. 8.9 Inch Smart Video Display Unit (SVDU) ......................................................... 166 SUBTASK 44-21-74-990-035-A01 O. Overhead Electronics Box (OEB) ....................................................................... 169 TASK 44-21-74-990-972-A01 5.

System Wiring.......................................................................................................... 172

SUBTASK 44-21-74-990-036-A01 A. VCC Wiring (Retro Fit) ....................................................................................... 172 SUBTASK 44-21-74-990-037-A01 B. System Wiring (Retro Fit) ................................................................................... 191

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DESCRIPTION AND OPERATION TASK 44-21-74-990-811-A01 1.

General The following is a description of the TopSeries™ i4000 Inflight Entertainment System. This system includes items supplied by Thales Avionics, Incorporated only. For information regarding other equipment, refer to the Boeing 767 Aircraft Maintenance Manual (AMM).

SUBTASK 44-21-74-990-001-A01 A.

Passenger Services 1)

Overhead Video Displays a)

Overhead Video is displayed on 8 monitors throughout the aircraft cabin, one wall mounted in Business Class and 7 in Economy Class, one wall mounted and 6 over-aisle, 3 on each side. On retrofit Aircraft there are Cabin Wall mounted 20 inch SVDUs whereas in line fit, there are 15 inch SVDUs.

b)

The overhead video monitors may be used to display broadcast media as selected by the system during auto-play, or manually by the cabin crew. NOTE:

2)

In accordance to LAN, selection overhead video configuration does not allow the audio to be tuned at the seats.

In-Seat Video a)

Smart Video Display Units (SVDUs) are provided at each seat to provide video entertainment as selected by each individual passenger.

b)

Each seat in Business Class contains a 15.4-inch SVDU without touch screen for displaying video entertainment; for front row passengers the SVDUs are mounted in the bulkhead.

c)

Each seat in Economy Class contains an 8.9-inch touch screen SVDU for displaying video entertainment; for front row passengers, the SVDUs are mounted in the bulkhead.

d)

Video entertainment is selected by each passenger using the Tethered Passenger Control Unit - Basic (TPCU-b) mounted in each individual seat, or by using the SVDU touch screen in Economy Class.

3)

In Seat Audio a)

Passenger selectable audio is available to all passengers via headset plugged into the Audio Jack Module (AJM).

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b)

Audio choices include a variety of music channels as well as the audio track associated with the video display.

c)

Audio entertainment is selected by each passenger using the TPCU-b mounted in each individual seat.

d)

Noise canceling features are integrated into the AJM at B/C seats.

SUBTASK 44-21-74-990-002-A01 B.

Cabin Attendant Features 1)

Cabin attendants control the operation of the TopSeries™ i4000 System via the Interactive Cabin Management Terminal (iCMT). The iCMT is mounted in the VCC assembly.

2)

An iCMT is similar to a PC with a Linux browser, and is logged into either the Digital Server Unit (DSU) or the Audio/Video Controller (AVC), which are acting as intranet servers.

3)

System functions are controlled by touching graphical buttons or scroll bars displayed on the iCMT touch-screen.

SUBTASK 44-21-74-990-003-A01 C.

Maintenance Features 1)

Maintenance personnel are able to view LRU failure messages and LRU configuration information on the iCMT.

2)

System software may be loaded using a Portable Data Loader (PDL) plugged into the VCC assembly in conjunction with the iCMT.

TASK 44-21-74-990-812-A01 2.

System Architecture

SUBTASK 44-21-74-990-004-A01 A.

Head-End Line Replaceable Units (LRUs) 1)

Interactive Cabin Management Terminal (iCMT)

2)

Audio/Video Controller (AVC)

3)

Digital Server Unit-AM6-12 (DSU-AM6-12)

4)

Digital Server Unit-D2 (DSU-D2)

5)

Ethernet Switching Unit-Gigabit (ESU-G)

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SUBTASK 44-21-74-990-005-A01 B.

Distribution LRUs 1)

Master Control Unit (MCU)

2)

Programming Module (PM)

3)

Area Distribution Box (ADB)

4)

Tapping Unit (TU)

5)

Overhead Electronics Box (OEB)

SUBTASK 44-21-74-990-006-A01 C.

Seat-End LRUs 1)

Seat Electronics Box (SEB)

2)

Tethered Digital Passenger Control Unit (TPCU-b)

3)

Integrated Noise Canceling Audio Jack Module (AJM); B/C seats only

4)

15.4-inch Smart Video Display Unit (SVDU); seatback and wall-mounted

5)

8.9-inch SVDU; seatback, wall-mount and arm mount.

6)

15-inch Bulkhead Mounted LCD Monitor (Line Fit A/C)

7)

20-inch Bulkhead Mounted LCD Monitor (Retro Fit A/C)

8)

15-inch Over-Aisle

SUBTASK 44-21-74-990-007-A01 D.

System Block Diagram Refer to Figure 1 for a block diagram of the LAN Airlines B767 TopSeries™ i4000 System.

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This page is intentionally blank

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U SB

VCC

AC OU

U SB

A/C Pow er

ISPC

SEB

i- C M T

MCU 1 R J45

R J45

MCU 4

MCU 2

R J45

To Ove rh e a d V id e o D iscretes PSS/PA AM P

429 bus

TU typi cal

AVC

TU PED in us e light

ISPC

PF IS Video

AC O U

R S 485

SVD U

DSU A M 6 -12

SEB

A D B1

Ty pical

AJ/ H EAD SE T

R J45 AJ

D SU-D2 D SU-D2

U SB

AD B2

D SU- D2

U SB

N ote: R J45 only in B /C

PC U

ESU lan s w itc h

A D B4

SEB

SEB

SEB

A D B5 D SU- D2

SEB

A D B6

D SU- D2

VCC

N OT E: 3 Ethernets w ill be supported from the ESU to each AD B.

SEB

100M bps / D ata 100M bps / AVOD Pow er RF

NOTE: Linefit Depicted, Retrofit similar. GRAPHIC TASK 44-21-74-990-813-A01 TopSeries™ i4000 System Block Diagram Figure 1 EFFECTIVITY 34626, 34628, 34629, 35229, 35230, 35231, 35696, 35697, 35698, 36710, 36711, 36712

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TASK 44-21-74-990-814-A01 3.

System Functional Description

SUBTASK 44-21-74-990-008-A01 A.

List of Functions The following is a list of functions included in the TopSeries™ i4000 System: 1)

Operator Interface

2)

In-Seat Audio

3)

In-Seat Video

4)

In-Seat Video and Audio Control

5)

Passenger Service System (PSS)

6)

Games

7)

Overhead Distributed Video

8)

Passenger Announcement

9)

Video Passenger Announcement

10)

Decompression

11)

Moving Map

12)

USB for peripheral devices

13)

PED connectivity, RJ45 ports (Business Class only) NOTE:

PED Power is provide by third party installation.

14)

RJ45 ports

15)

Maintenance

SUBTASK 44-21-74-990-009-A01 B.

Operator Interface

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1)

Operator interface and control of the TopSeries™ i4000 System is achieved using the interactive Cabin Management Terminal (iCMT). i4000 system functions are organized by menu screens that are displayed on the iCMT. These menus enable cabin attendant personnel to enable and disable the various IFE services.

2)

Screen Descriptions Each screen has various components to convey information and provide control of the system. Each screen is described in function, appearance, and component content. The different types of components utilized in the iCMT user screens are described in Table 1.

TABLE TASK 44-21-74-990-815-A01 iCMT Screen Components Table 1 TYPE

DESCRIPTION

Label

Labels an area of screen or window. Labels do not change and are not alterable by user.

Table

Displays system information in tabular form.

Button

Onscreen control of a service or setting which causes a change or initiates a process when touched. Once button is activated, the on-screen color changes to Green or Blue.

Radio Button

Onscreen control for selecting a single choice in a group of choices.

Check Box

Onscreen control for selecting an option or setting.

3)

IFE System Power Activation and Deactivation (Refer to Figure 2)

WARNING: IN THE EVENT OF A GROUND OR AIRBORNE AIRCRAFT EMERGENCY, THE IFE SYSTEM MUST BE COMPLETELY DISABLED PER BOEING 767 AIRPLANE FLIGHT MANUAL PROCEDURES. a)

Under normal conditions, the i4000 IFE system is automatically powered on when power is applied to the aircraft. Power to the entire i4000 IFE system is controlled by the MASTER IFE power switch in the VCC.

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b)

The MASTER IFE switch is a two-position push button switch that lights up. When the switch is lit, power is applied to the i4000 IFE system. When the switch is not lit, power is removed from the i4000 IFE system.

c)

HEAD END POWER Switch (1)

The HEAD END POWER switch controls power to all of the i4000 IFE system head-end LRUs that are located in the VCC assembly.

(2)

The HEAD END POWER switch is a two-position push button switch that lights-up. When the switch is lit, power is applied to the i4000 IFE system head-end LRUs. When the switch is not lit, power is removed from the i4000 IFE system head-end LRUs.

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IFE FAN INOP INDICATOR MASTER IFE POWER SWITCH HEAD END POWER SWITCH

SEAT END POWER

PC POWER SWITCH

VIDEO CONTROL CENTER CONTROL PANEL GRAPHIC TASK 44-21-74-990-816-A01 i4000 IFE System Switches and Indicators, Retrofit A/C Only Figure 2 (Sheet 1 of 2)

EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229, 29229

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d)

SEAT END POWER Switch (1)

On linefit aircraft, when the SEAT END POWER switch is pressed, relays in the power panels are de-energized. This removes power from the MCUs. As a result, the ADBs, TUs, and iCMT all lose power.

(2)

On retrofit aircraft, when the SEAT END POWER switch is pressed, MCU output ports 1-4 are deactivated. The MCUs. ADBs, TUs, and iCMT remain powered.

NOTE: If the Ground Fault Interrupter (GFI) gets tripped on the MCU (indicated by no power down a specific column, and a blinking light on the MCU, the MCU must be power cycled to reset. NOTE: There is a USB port at the VCC panel for easy access, along with another USB port inside a secured box inside the VCC for future development. NOTE: The RJ45 connector sockets at the VCC panel are wired as follows: DATA LOADER 1 connects to ESU DATA LOADER 2 connects to VCC SEB DATA LOADER 3 connects to DSU AM6-12

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MASTER IFE SWITCH

IFE FAN INOP INDICATOR

PC POWER SWITCH

HEAD END POWER SWITCH

SEAT END POWER SWITCH

VIDEO CONTROL CENTER CONTROL PANEL

GRAPHIC TASK 44-21-74-990-817-A01 i4000 IFE System Switches and Indicators, Linefit A/C Only Figure 2 (Sheet 2 of 2) EFFECTIVITY 34626, 34628, 34629, 35229, 35230, 35231, 35696, 35697, 35698, 36710, 36711, 36712

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e)

PC POWER Switch (1)

The PC POWER switch controls power to all of the in-seat power electrical outlets.

(2)

The PC POWER switch is a two-position push button switch that lights-up. When the switch is lit, power is available at the in-seat electrical connectors. When the switch is not lit, power is removed from the in-seat electrical outlets.

f)

All four of the IFE switches are protected by switch guards.

g)

IFE FAN INOP Indicator (1)

The IFE FAN INOP indicator lights-up when the IFE equipment fan is not operating.

(2)

When the IFE FAN INOP indicator lights-up, power should be removed from the i4000 IFE system head-end equipment in order to prevent potential damage to the LRUs. NOTE: The fans that provide cooling air circulation to the IFE are not provided by Thales.

h)

SMOKE TEST Switch

NOTE: The SMOKE TEST switch is not provided by Thales. (1)

i)

The SMOKE TEST switch is a push button switch that activates smoke alarms on the aircraft. The SMOKE TEST switch is protected by switch guard.

ALARM RESET Switch

NOTE: The ALARM RESET switch is not provided by Thales. (1)

4)

The ALARM RESET switch is used to cancel smoke alarms on the aircraft. The ALARM RESET switch is protected by switch guard.

iCMT Welcome screen a)

When the i4000 system finishes booting up, the LAN welcome screen is displayed on the iCMT.

b)

The LAN welcome screen options are described in Table 2, and illustrated in Figure 3.

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TABLE TASK 44-21-74-990-818-A01 Welcome Screen Selections Table 2 TITLE

TYPE

FUNCTION

Entertainment

Button

Launches i4000 System Entertainment Selections

Maintenance

Button

Launches i4000 System Maintenance Mode

Offload

Button

Provides access to usage statistics

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GRAPHIC TASK 44-21-74-990-819-A01 Welcome Screen Figure 3 5)

Services Control Screen (Refer to Figure 4) a)

When the Entertainment button is touched on the LAN welcome screen or when the Services button is touched from any of the other screens, the Auto Play Control (Figure 20) is displayed on the iCMT. This screen provides on and off controls for the various entertainment services available to the passengers.

b)

Audio Broadcast Button Enables/disables regular FM audio media broadcast - all available channels, to the seats.

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GRAPHIC TASK 44-21-74-990-820-A01 Services Control Screen Figure 4 NOTE:

c)

Audio and Video broadcast will be available under failed mode. (Server Offline).

Video Broadcast Button Enables/disables regular movie video media broadcast - all available channels to the seats.

d)

On Demand Button Enables/disables On Demand movie video media broadcast - all available channels to the seats.

e)

Moving Map Button

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Enables/disables moving map channel to the seats. f)

Services Reset Button Allows the user to Cancel or Stop all services in progress. User gets a prompt that asks: Are you sure you want to reset all services? (1)

OK – Cancels all services

(2)

Cancel - Resumes all services enabled

g)

When buttons are enabled, the green light on the button comes on.

h)

If Auto Play script is used then services will be enabled automatically 3 minutes after take off.

i)

If any of these services are not turned on, entertainment will not be functioning at the seats.

j)

During any PA, the passenger SVDUs will show a PA in progress message if video is being presented.

6)

How to Start Services for In Seat Entertainment (Refer to Figure 5) NOTE: When buttons are enabled, they light up green. a)

Touch Services button on left side of iCMT from any screen.

b)

In failure mode touch Audio Broadcast button. This starts all featured audio. Passengers are then able to select the music by selecting the appropriate channel.

c)

In failure mode touch Video Broadcast button. This starts all featured videos. Passengers are then able to select the movie by selecting the appropriate channel.

d)

Touch On Demand button. This enables all on demand entertainment. Passengers are then able to choose on demand services by selecting the appropriate channel.

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GRAPHIC TASK 44-21-74-990-821-A01 Services Start-Up Figure 5 e)

Touch Moving Map button. This starts the moving map. Passengers are then able to choose moving map by selecting the appropriate channel.

f)

Reselecting Video Broadcast will cause a pop-up window to appear on the iCMT screen. The window displays the message: Would you like broadcast video to resume or start over? (Refer to Figure 6). When Resume is touched, the broadcast video selected will resume from the previous point. When Start Over is touched, the selected broadcast video will start over at the beginning.

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GRAPHIC TASK 44-21-74-990-822-A01 Video Broadcast Reselection Options Screen Figure 6 g)

When the Services Reset button is touched, a pop-up window appears on the iCMT and displays: Are you sure you want to restart all services? The user may touch OK which will restart all services and return to the welcome screen, or Cancel which will result in no action by the system (Refer to Figure 7).

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GRAPHIC TASK 44-21-74-990-823-A01 Services Reset Screen Figure 7 7)

System Status Screen (Refer to Figure 8) a)

When the Sys Status button is touched on the iCMT, the Comm Status screen is displayed on the iCMT.

b)

This screen displays units that are not communicating with the system and is generally used for maintenance troubleshooting. Normally, the screen is blank.

c)

Touching the Refresh button queries the system and updates the Details window according to the current system status.

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GRAPHIC TASK 44-21-74-990-824-A01 COMM Status Screen Figure 8 8)

Video Announcement Control Screen (Refer to Figure 9) a)

When the VA button is touched on the iCMT, the VA Select screen is displayed on the iCMT.

b)

This screen provides video announcement selection and volume control capability for the entire aircraft (All).

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GRAPHIC TASK 44-21-74-990-825-A01 Video Announcement Control Screen Figure 9 c)

VA Select drop down menu Allows the cabin attendant to select a video announcement from the list.

d)

PA / VA Status Menu Displays whether the system is in PA or VA mode.

e)

VA Volume Controls Increase and decrease controls for VA volume as well as scales to visually indicate volume levels.

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f)

Preview Window Allows the cabin attendant to view what is playing at seats.

g)

Video Controls Enable the cabin attendant to play, stop, pause, fast forward, and reverse the selected video announcement.

9)

Initiating a Video Announcement (Refer to Figure 10) NOTE: When buttons are enabled or items touched, they light up green.

GRAPHIC TASK 44-21-74-990-826-A01 Initiating a Video Announcement Figure 10

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a)

Select a video from the VA Select window.

b)

Press play (forward arrow) button.

c)

Press VA to PAX button; this broadcasts video and audio to the cabin.

d)

Cabin VA Volume level is controlled by using the + (Volume Increase) or (Volume Decrease) buttons to maintain comfortable audio level. The audio level is displayed on the range indicator bar.

e)

Attendant Volume controls the volume level in the system operator’s headset.

f)

The iCMT provides a picture in picture (PIP) window to monitor the broadcast.

g)

Press stop (square) button to cancel video announcement.

h)

Press VA to PAX button to cancel broadcast. NOTE: When you attempt to initiate a VA while Broadcast video is operating, the Broadcast Movies must be stopped before doing a VA. Stop Broadcast movies now? prompt screen is displayed (Refer to Figure 11). Touching OK stops the Broadcast programming. Touching Cancel enables the Broadcast programming to continue. NOTE: When you attempt to initiate a VA while Autoplay is operating, the Autoplay movies must be stopped before doing a VA. Stop Autoplay now? prompt screen is displayed (Refer to Figure 12). Touching OK stops the Autoplay programming. Touching Cancel enables the Autoplay programming to continue.

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GRAPHIC TASK 44-21-74-990-827-A02 Broadcast Movies Stop Prompt Screen Figure 11

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GRAPHIC TASK 44-21-74-990-828-A03 Autoplay Stop Prompt Screen Figure 12 10)

Seat Control Screen (Refer to Figure 13) a)

When the Seat Control button is touched on the iCMT, the Seat Control screen is displayed on the iCMT.

b)

This screen provides the cabin attendant with the ability to reset the IFE services at any individual seat on the aircraft. This function is utilized when there is a problem with the IFE services at a particular seat.

c)

Seat Selection Window Controls The controls in the Seat Selection window are used by the cabin attendant to select an individual seat number for reset.

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GRAPHIC TASK 44-21-74-990-829-A01 Seat Control Screen Figure 13 d)

Seat Action Reset Button (1)

This button is used to reset IFE services to the seat selected in the Seat Selection window.

(2)

When the Reset button is touched, a pop-up window will appear that reads: Are you sure you want to reset seat xxx? (Refer to Figure 14).

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GRAPHIC TASK 44-21-74-990-830-A01 Seat Reset Screen Figure 14 (3)

When OK is touched, IFE services are reset to the selected seats SVDU and TPCU along with the seat in front of it because they share the same SEB output.

(4)

iCMT display returns to the Seat Control screen.

(5)

When Cancel is touched, the iCMT returns to the Seat Control screen.

(6)

If an erroneous entry is made in the Seat Selection window and the Reset button is subsequently touched, a pop-up window that says: Seat xxx does not exist is displayed on the iCMT (Refer to Figure 15).

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GRAPHIC TASK 44-21-74-990-831-A01 Erroneous Seat Selection Screen Figure 15 11)

Overhead Video Select Screen (Refer to Figure 16) a)

When the Overhead Video button is touched on the iCMT, the Overhead Video Select screen is displayed on the iCMT.

b)

This screen provides the cabin attendant with access to the overhead video controls.

c)

Overhead Video Select Window This window contains a list of available programming selections for display on the overhead monitors. The scroll bar is used to locate the desired option which lights up green when touched.

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GRAPHIC TASK 44-21-74-990-832-A02 Overhead Video Select Screen Figure 16 d)

Overhead Video Button The Overhead Video button starts and stops the selected programming. NOTE: Video Broadcast must be turned on from the Services screen prior to activating the Overhead Video button. If Video Broadcast is not on and the Overhead Video button is touched, the prompt shown in Figure 17 will appear on the iCMT screen.

e)

Attendant Volume Controls Control the audio volume in the headset of the cabin attendant operating the system.

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NOTE:

There is no manual selection of audio to correspond with video, it is automatic.

GRAPHIC TASK 44-21-74-990-833-A03 Turn on Video Broadcast Prompt Screen Figure 17 12)

Flight Info Screen (Refer to Figure 18) a)

When the Flight Info button on the iCMT is touched from any window, the Flight Info screen is displayed on the iCMT.

b)

The cabin attendant uses the flight info screen to enter the Aircraft Tail Number, Flight Number, Departure Airport, and Arrival Airport prior to departure.

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GRAPHIC TASK 44-21-74-990-834-A04 Flight Info Screen Figure 18 c)

Edit Buttons When the Edit button is touched adjacent to any of the information display windows, a keyboard is displayed for data entry (Refer to Figure 19).

d)

SAVE Button When the SAVE button is touched, all displayed information is saved to the flight information database.

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GRAPHIC TASK 44-21-74-990-835-A04 Pop Up Keyboard Screen Figure 19 13)

Auto Play Control Screen (Refer to Figure 20) a)

Auto Play feature was implemented by the airline to automate IFE functions for the cabin attendant. In flight, this feature allows the CA to manage the IFE by simply touching on of the following buttons: (1)

Boarding

(2)

Safety Video

(3)

Decent

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b)

When the Auto Play button on the iCMT is touched from any window, the Auto Play Control screen is displayed on the iCMT (Figure 20).

c)

The Auto Play Control screen provides the cabin attendant with three options of pre-recorded information at the touch of a button.

d)

Boarding Button Starts the Boarding video announcement (Refer to Figure 10). Audio is broadcast to seats and over the PA system.

e)

Safety Video Button Starts the Safety Video broadcast.

GRAPHIC TASK 44-21-74-990-836-A05 Auto Play Control Screen Figure 20 EFFECTIVITY ALL

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f)

Descent Button Descent Button starts the Descent broadcast and script. (1)

Decent Script When button is touched a message to the PAX will be displayed stating that in 5 minutes services will be disabled, after 5 minutes services are disabled and leaving PAX screens in idle mode ( in screen) and MMAP on the overhead screens.

(2)

After landing the "thank you for flying with us" video will be displayed

NOTE: All Video Broadcast must be turned off from the Services screen prior to activating any of the Auto Play Control buttons. If Video Broadcast is on and an Auto Play Control button is touched, the prompt shown in Figure 21 will appear on the iCMT screen. g)

Auto Play Volume Controls Controls the audio volume of the auto play message.

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GRAPHIC TASK 44-21-74-990-837-A06 Shut off Broadcast Prompt Screen Figure 21 14)

PRAM Select Screen (Refer to Figure 22) a)

When the PRAM button is touched on the iCMT, the PRAM Select screen is displayed on the iCMT.

b)

This screen provides the cabin attendant with access to the Pre-Recorded Announcement (PRAM) controls.

c)

PRAM Select Window This window contains a list of available PRAM selections for broadcast. The scroll bar is used to locate the desired option which lights up green when touched.

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GRAPHIC TASK 44-21-74-990-838-A07 PRAM Select Screen Figure 22 d)

Start, Stop, and Volume Controls The arrow button starts the selected PRAM. The square button stops the selected PRAM. The minus and plus buttons control the volume.

15)

BGM Select Screen (Refer to Figure 23) a)

When the Boarding Music button is touched on the iCMT, the BGM Select screen is displayed on the iCMT.

b)

This screen provides the cabin attendant with access to the Boarding Music (BGM) controls.

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GRAPHIC TASK 44-21-74-990-839-A08 BGM Select Screen Figure 23 c)

BGM Select Window This window contains a list of available BGM selections for broadcast. The scroll bar is used to locate the desired option which lights up green when touched.

d)

Start, Stop, and Volume Controls The arrow button starts the selected BGM. The square button stops the selected BGM. The minus and plus buttons control the volume.

16)

Exit Screen (Refer to Figure 24)

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a)

When the EXIT button on the iCMT is touched from any window, the following on-screen message appears prompting the cabin crew to make a choice: All entertainment and VA services will be terminated. Would you like to proceed?

b)

OK Button Cancels all services and return the iCMT to the LAN welcome screen.

c)

Cancel Button Ignores the command to terminate passenger services.

GRAPHIC TASK 44-21-74-990-840-A01 Exit Screen Figure 24

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17)

iSeries Maintenance Access Screen a)

When the Maintenance button is touched from the LAN welcome page, the iSeries Maintenance Access screen is displayed on the iCMT.

b)

For details of the Maintenance Access screen and all of the Maintenance Mode sub-screens go to the Maintenance section of this chapter.

SUBTASK 44-21-74-990-010-A01 C.

Broadcast Mode system, In-Seat Audio (DSU-D2 removed) 1)

There are 14 stereo channels of audio; these are split between in-seat entertainment audio and boarding music. The audio channels are hosted by the DSU-AM6-12.

2)

Audio channel selection is made using the TPCU-b located in each passenger’s seat arm. Table 3 defines the Audio Mode channel mapping for the TPCU-b.

TABLE TASK 44-21-74-990-841-A01 Audio Mode Channel Mapping for the TPCU-b Table 3 TPCU-b CHANNEL

SOURCE

RF CHANNEL

ENTERTAINMENT

1 (AUDIO)

Video Mode

Video Mode

Overhead Video

2 (AUDIO)

Video Mode

Video Mode

Overhead Video

3 (AUDIO)

AUDIO CLIENT 1

DSU-AM6-12 Ch. 13

AUDIO CH 1

4 (AUDIO)

AUDIO CLIENT 2

DSU-AM6-12 Ch. 14

AUDIO CH 2

5 (AUDIO)

AUDIO CLIENT 3

DSU-AM6-12 Ch. 15

AUDIO CH 3

6 (AUDIO)

AUDIO CLIENT 4

DSU-AM6-12 Ch. 16

AUDIO CH 4

7 (AUDIO)

AUDIO CLIENT 5

DSU-AM6-12 Ch. 17

AUDIO CH 5

8 (AUDIO)

AUDIO CLIENT 6

DSU-AM6-12 Ch. 18

AUDIO CH 6

9 (AUDIO)

AUDIO CLIENT 7

DSU-AM6-12 Ch. 19

AUDIO CH 7

10 (AUDIO)

AUDIO CLIENT 8

DSU-AM6-12 Ch. 20

AUDIO CH 8

11 (AUDIO)

AUDIO CLIENT 9

DSU-AM6-12 Ch. 21

AUDIO CH 9

12 (AUDIO)

AUDIO CLIENT 10

DSU-AM6-12 Ch. 22

AUDIO CH 10

13 (AUDIO)

AUDIO CLIENT 11

DSU-AM6-12 Ch. 23

AUDIO CH 11

14 (AUDIO)

AUDIO CLIENT 12

DSU-AM6-12 Ch. 24

AUDIO CH 12

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SUBTASK 44-21-74-990-011-A01 D.

In-Seat Video Broadcast Mode system, In-Seat Audio (DSU-D2 failed or removed) 1)

The in-seat video is displayed as follows: a)

15.4-inch Smart Video Display Units (SVDUs) in Business Class; seatback mounted for all rows except front row; bulkhead mounted for front row.

b)

8.9-inch SVDUs in Economy Class; seatback mounted for all rows except front row; bulkhead mounted for front row.

2)

The in-seat video and audio presentation is controlled by each passenger using the TPCU-b mounted in their seat. Table 4 defines the Video Mode channel mapping for the TPCU-b.

TABLE TASK 44-21-74-990-842-A01 Video Mode Channel Mapping for the TPCU-b Table 4 PCU CHANNEL

SOURCE

RF CHANNEL

ENTERTAINMENT

1 (VIDEO)

VIDEO CLIENT 2

DSU-AM6-12 Ch. 74

VIDEO CH 1 PRIMARY

2 (VIDEO)

VIDEO CLIENT 2

DSU-AM6-12 Ch. 74

VIDEO CH 1 SECOND

3 (VIDEO)

VIDEO CLIENT 3

DSU-AM6-12 Ch. 75

VIDEO CH 2 PRIMARY

4 (VIDEO)

VIDEO CLIENT 3

DSU-AM6-12 Ch. 75

VIDEO CH 2 SECOND

5 (VIDEO)

VIDEO CLIENT 4

DSU-AM6-12 Ch. 76

VIDEO CH 3 PRIMARY

6 (VIDEO)

VIDEO CLIENT 4

DSU-AM6-12 Ch. 76

VIDEO CH 3 SECOND

7 (VIDEO)

VIDEO CLIENT 5

DSU-AM6-12 Ch. 77

VIDEO CH 4 PRIMARY

8 (VIDEO)

VIDEO CLIENT 5

DSU-AM6-12 Ch. 77

VIDEO CH 4 SECOND

9 (VIDEO)

VIDEO CLIENT 6

DSU-AM6-12 Ch. 78

VIDEO CH 5 PRIMARY

10 (VIDEO)

VIDEO CLIENT 6

DSU-AM6-12 Ch. 78

VIDEO CH 5 SECOND

SUBTASK 44-21-74-990-012-A01 E.

In-Seat Video and Audio Control 1)

The individual in-seat video and audio presentation is controlled by each passenger using the TPCU-b mounted in the arm of each seat.

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a)

Each TPCU-b has Xpad controls and function buttons that enable the passenger to navigate through the menu screens to select desired entertainment after entertainment services are enabled by the cabin attendant (Refer to Figure 15).

b)

The PSS functions may be utilized at any time during flight from any entertainment service mode. The PSS function includes the following passenger controls located on the TPCU-b:

c)

(1)

Attendant Call Button

(2)

Attendant Call Cancel Button

(3)

Reading light switch

Controlled via LAN User Scripting by flight attendant: when passengers are boarding the aircraft, the SVDUs display the boarding wallpaper video. The wallpaper is displayed until the cabin attendant manually starts the safety video from the iCMT (Refer to Figure 25). In manual mode, after the safety announcement is completed, the cabin attendant advances the system to the Taxi/Takeoff wallpaper video.

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Cruise

Crew Action

Climb Out Taxi & Take-Off

Idle Mode Safety Video

Boarding Crew Action

Crew Action

VA with Wallpaper1 From DSU-AM-612 Scaled to 16:9 on SVDU, 4:3 on O/H Plays in a loop

VA with Safety Video From DSU-AM6-12 Scaled to 16:9 on SVDU, 4:3 on O/H

Upon Completion of Safety Video

Taxi In Ξ Ξ Ξ

1- Overhead - Moving Map from DSU-AM612 (4:3) 2 – Seats - Idle Mode Graphic

Idle Mode Descent & Landing

3 min. after Take-Off (WOW KL is removed)

Ξ Ξ

Services Enabled Touch Screen to Ξ Begin Transition to Branding Video 1 (VOD) Transition to Lang. Selection Home Page

Pop-up message warning services turn off in 5 minutes

WOW KL is activated Services Disabled except 1- Overhead - Moving Map from DSU-AM612 (4:3) 2 – Seats - Idle Mode Graphic 3 – BGM Thank you video music

Ξ Ξ

Ξ

Services Disabled VA- Thank You Video from DSUAM-612 streamed to all seats and overhead – 16:9 Service Reset

OVHD Video

On

On

On 1

Off

Off

Off

On 1

On

OVHD Audio

On

On

Off

Off

Off

Off

Off

On

Pax Video

Same as VA

Same as VA

On 2

Off

Interactive

Interactive

On 2

Same as VA

Pax Audio

Same as VA

Same as VA

Off

Off

Interactive

Interactive

Off

Same as VA

Allow Broadcast Audio Surf

Allow Broadcast Audio Surf

Transition Manually Initiated by Crew Automated Transition

SVDU Screens Flowchart FIGURE 2

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Rev. 022309

GRAPHIC TASK 44-21-74-990-843-A01

ALL

PreDescent

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d)

Once the aircraft has taken off and the i4000 system services have been enabled by the cabin attendant, (or autoplay script) the SVDUs display the Begin screen (Refer to Figure 26).

GRAPHIC TASK 44-21-74-990-844-A01 Begin Screen Figure 26 e)

When the passenger touches the SVDU screen (Economy Class) or presses the SELECT button on the TPCU-b, the SVDU advances to the Initial Menu language screen after a brief branding video (Refer to Figure 27).

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GRAPHIC TASK 44-21-74-990-845-A01 Initial Menu Language Screen Figure 27 f)

The passenger selects English or Spanish by either touching the screen or by using the Xpad controls on the TPCU-b to highlight the desired selection, then touching the SELECT button.

g)

Once the passenger has selected a language, the SVDU advances to the Main Menu Screen (Refer to Figure 28).

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GRAPHIC TASK 44-21-74-990-846-A01 Main Menu Screen Figure 28 h)

From this screen, the passenger may access any of the enables entertainment services as shown in the Screens Flowchart in Figure 16.

i)

The top bar link on the SVDU is displayed on all primary screens, and may be touched at any time (Refer to Figure 29): MARKETPLACE: Displays the MARKETPLACE menu

GRAPHIC TASK 44-21-74-990-848-A01 Top Bar Link Figure 29 j)

The bottom bar links on the SVDU are displayed on all primary screens and may be selected at any time (Refer to Figure 30):

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(1)

BACK: Displays the previous screen

(2)

HOME: Displays the main menu screen

(3)

LANGUAGE: Displays the language screen

(4)

DO NOT DISTURB: Displays the do not disturb screen

(5)

AUDIO: Displays the audio player

(6)

?: Displays the help screen(s)

GRAPHIC TASK 44-21-74-990-849-A01 Bottom Bar Links Figure 30 2)

Unavailable Service Screen When a passenger attempts to access a service that is unavailable, the Unavailable Service screen is displayed on the SVDU (Refer to Figure 31).

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GRAPHIC TASK 44-21-74-990-850-A01 Unavailable Service Screen Figure 31 SUBTASK 44-21-74-990-013-A01 F.

Overhead Distributed Video 1)

There are five channels available for digital broadcast video data, one of which contains the moving map application. Video is hosted by the DSU-AM6-12, and is distributed to the tapping units via the AVC.

2)

The video is displayed on bulkhead mounted and overaisle LCD monitors distributed throughout the aircraft cabin.

SUBTASK 44-21-74-990-014-A01 G.

Passenger Announcement (PA) 1)

The i4000 system supports two types of PA; Direct PA and Area PA. For each PA area, an audio twisted pair and keyline are provided to the AVC.

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2)

For Direct PA an independent keyline is provided to the i4000 system and the audio twisted pair associated with PA area 1 supplies the announcement audio. There is one area in the LAN B767 to support PA.

3)

A passenger announcement is active when a PA keyline is active.

4)

The system prioritizes audio presented to the passenger headset according to the following priority order from highest to lowest: a)

Direct PA Audio

b)

Area PA Audio

c)

Entertainment Audio

5)

When an Area PA keyline is active and Direct PA keyline is inactive, audio is presented to the passenger headsets.

6)

When an Area PA keyline is active, interactive entertainment services for corresponding PA is placed in pause condition.

7)

When keyline is active, a passenger announcement in progress indication displayed on the TPCU-b and on the SVDU (except when the PA is applied during a VA).

8)

When a PA keyline is active, the audio presented to all passenger headsets is the audio provided by PA on the area 1 input.

9)

When a Direct PA keyline is active, all entertainment sources are placed in pause condition.

10)

When a Passenger Announcement is active, TPCU-b functionality is limited to volume control; reading light control, attendant call, and attendant call cancel control.

SUBTASK 44-21-74-990-015-A01 H.

Video Passenger Announcement 1)

The i4000 system Video PA as follows: Economy Class

2)

The i4000 system supports Video Override function by forcing the appropriate inseat video displays to present the specified video program. Video Announcement is the simultaneous combination of Video PA and Video Override.

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3)

When a Video Override is activated from the iCMT, the seat displays in the selected Video PA area is turned ON and forced to the video channel corresponding to the selected video source.

4)

When a Video Override is active, TPCU-b functionality is limited to volume control, reading light control, and attendant call/call cancel control. NOTE: There is a direct correspondence between Video PA area and overhead video area.

5)

The audio associated with Video PA is broadcast on the passenger headset. This also occurs on the overhead PA system.

SUBTASK 44-21-74-990-016-A01 I.

Decompression 1)

The i4000 system is informed of a decompression event through a keyline from the aircraft system to the AVC.

2)

When the decompression keyline is activated, the i4000 system performs the following actions: a)

Video on all overhead and bulkhead displays is turned off.

b)

Video display backlights on all in-seat display units are turned off.

c)

All in-seat entertainment functions cease.

3)

Both the PA function and the PSS function remain active while the Decompression Keyline is active.

4)

After the Decompression Keyline is deactivated, all video displays and all video projectors remain powered off until the system is reactivated manually.

SUBTASK 44-21-74-990-017-A01 J.

Moving Map 1)

One of the video channels is dedicated to the moving map function. Moving map is a broadcast application that shows a map of the world, where the aircraft has been, where it is going, and the following specific flight information: a)

Distance to destination

b)

Time to destination (Linefit A/C only)

c)

Altitude

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d)

Ground speed

e)

Outside temperature (in Celsius and Fahrenheit)

f)

Local time at destination (Linefit A/C only)

2)

The moving map application provides the following three types of video data to the overhead monitors via a broadcast channel: a)

Graphical representation of the aircraft position over the surface of the earth

b)

Textual navigational data

c)

Custom graphic images

3)

The moving map application cycles through displays of maps at four different scales while showing the aircraft flight path and current position. At the end of each complete map cycle, a custom graphic is displayed and then the map cycle repeats. Select cities are displayed on each map by name as well as points of interest for the passengers. The textual navigation data includes current aircraft longitude, latitude, and ground speed.

4)

Navigational data used by the moving map application is provided to the AVC via ARINC 429 interface. The AVC then forwards NAV data to the DSU-AM6-12 via Ethernet interfaces from the cockpit avionics system.

5)

The maps are color-coded topographical maps of the earth in four scales. Thales generates the maps using color to convey ground elevation information. The map files are provided with the application and are not alterable.

6)

Zoom Levels a)

The scale is the amount of geographical area represented by a unit area on the map display. The largest scale shows most of the earth. As the scale is decreased, closer views of the earth are shown. This is the same concept as increasing the focal length on a variable focal length zoom lens. The different scales are referred to as zoom levels.

b)

The widest level of zoom displays the full flight path in relation to the earth, from city of departure to current location. Intermediate levels of zoom show greater detail of the earth and most recent portion of the flight path that spans the range of the map. The narrowest level of zoom shows the closest detail of the earth within a few minutes of the most recent flight path.

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SUBTASK 44-21-74-990-018-A01 K.

USB for Peripheral Devices Each seat in the B767 aircraft contains a standard Type A USB connector that when connected to the SVDU will cause a momentary disruption in SVDU power due to EMI issues.

SUBTASK 44-21-74-990-019-A01 L.

PED Connectivity Each seat in Economy Class contains an RJ45 connector for Personal Electronic Device (PED) usage.

SUBTASK 44-21-74-990-020-A01 M.

Maintenance 1)

Maintenance functions are initiated by the operator via the iCMT maintenance menus. The Maintenance Menus are accessed by touching Maintenance from the iCMT welcome screen.

2)

Maintenance Access Screen a)

When the Maintenance button is selected on the LAN welcome screen (Refer to figure 3), the Maintenance Access Screen is displayed on the iCMT

b)

The Maintenance Access Screen options are described in Table 5 and illustrated in Figure 32.

TABLE TASK 44-21-74-990-851-A01 Maintenance Access Screen Options Table 5 TITLE

TYPE

FUNCTION

Password Edit Box

Display

Displays the masked key presses from the keypad

Keypad

Buttons

Provides keys for password entry

Enter

Button

Enables entrance to the Maintenance screens after a valid password has been entered

Exit

Button

Returns to the Welcome screen

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GRAPHIC TASK 44-21-74-990-852-A01 Maintenance Access Screen Figure 32 3)

Maintenance Screen a)

When Enter is touched on the Maintenance Access Screen, the Maintenance screen is displayed on the iCMT.

b)

The Maintenance Screen options are described in Table 6 and illustrated in Figure 33.

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-853-A01 Maintenance Screen Options Table 6 TITLE

TYPE

FUNCTION

Download

Button

Displays Download options

Config Check

Button

Displays current system software configuration

IP Sequencing

Button

Displays IP Sequence Menu

Static Test

Button

Provides access to Static Test Menu

Customer Login

Button

Returns to welcome screen

BITE

Button

Not functional

PSS

Button

Advances user to PSS screens

GRAPHIC TASK 44-21-74-990-854-A01 Maintenance Screen Figure 33 EFFECTIVITY ALL

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4)

Download Screen a)

When Download is touched on the Maintenance Screen, the Download screen is displayed on the iCMT.

b)

The Download Screen options are described in Table 7 and illustrated in Figure 34.

TABLE TASK 44-21-74-990-855-A01 Download Screen Options Table 7 TITLE

TYPE

FUNCTION

Update Software

Button

Advances to Current Software Configuration screen

Update Content

Button

Advances to Content Loading Screens

Download LRU

Button

Advances to LRU Load screen

Done

Button

Returns to Maintenance screen

EFFECTIVITY ALL

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NOT ACTIVE

GRAPHIC TASK 44-21-74-990-856-A01 Download Screen Figure 34 5)

Current Software Configuration Screen a)

When the Update Software button is touched on the Download Screen, the Current Software Configuration screen is displayed on the iCMT.

b)

The Current Software Configuration screen options are described in Table 8 and illustrated in Figure 35.

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-857-A01 Current Software Configuration Screen Options Table 8 TITLE

TYPE

FUNCTION

DELETE

Button

Deletes selected items

UPDATE

Button

Updates selected items and advances to Source Selection Screen

DONE

Button

Returns to Download screen

LAN

LAN

GRAPHIC TASK 44-21-74-990-858-A01 Current Software Configuration Screen Figure 35 (Sheet 1 of 2)

EFFECTIVITY ALL

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GRAPHIC TASK 44-21-74-990-859-A01 Current Software Configuration Screen Figure 35 (Sheet 2 of 2) 6)

Software Removal Screen a)

When DELETE is touched on the Current Software Configuration screen, the Software Removal screen is displayed on the iCMT.

b)

The Software Removal screen options are described in Table 9 and illustrated in Figure 36.

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-860-A01 Software Removal Screen Options Table 9 TITLE

TYPE

FUNCTION

Delete

Button

Removes software selected via Check Box from the system and returns to the Current Software Configuration screen

Done

Button

Returns to the Current Software Configuration screen

Check Box

Check Box

Allows for software selection

LAN

LAN

GRAPHIC TASK 44-21-74-990-861-A01 Software Removal Screen Figure 36 (Sheet 1 of 2) EFFECTIVITY ALL

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GRAPHIC TASK 44-21-74-990-862-A01 Software Removal Screen Figure 36 (Sheet 2 of 2) 7)

Source Selection Screen a)

When UPDATE is touched on the Current Software Configuration screen (Figure 36 sheet 2), the Source Selection screen is displayed on the iCMT.

b)

The Source Selection screen options are described in Table 10 and illustrated in Figure 37.

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TABLE TASK 44-21-74-990-863-A01 Source Selection Screen Options Table 10 TITLE

TYPE

FUNCTION

CD/Zip/Floppy Disk/USB (iCMT)

Radio Button

Indicates source selected for download (one selection at a time)

By Package

Button

Advances to Software Load By Package – CD Screen

By File

Button

Advances to Software Load By File – CD Screen

Done

Button

Returns to Download screen

GRAPHIC TASK 44-21-74-990-864-A01 Source Selection Screen Figure 37 EFFECTIVITY ALL

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8)

Software Load By File Screen a)

When the By Package or By File button is touched on the Source Selection screen, the Software Load By File screen is displayed on the iCMT.

b)

The Software Load By File screen options are described in Table 11 and illustrated in Figure 38.

TABLE TASK 44-21-74-990-865-A01 Software Load By File Screen Options Table 11 TITLE

TYPE

FUNCTION

UPDATE

Button

Updates selected items and advances to Download Package Phase 1 Progress screen

DONE

Button

Returns to Source Selection Screen

Check Box

Check Box

Allows for software selection

EFFECTIVITY ALL

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LAN LAN LAN LAN LAN

GRAPHIC TASK 44-21-74-990-866-A01 Software Load by File Screen Figure 38 (Sheet 1 of 2)

EFFECTIVITY ALL

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GRAPHIC TASK 44-21-74-990-867-A01 Software Load by File Screen Figure 38 (Sheet 2 of 2) 9)

Download File Phase 1 Progress Screen a)

When UPDATE is touched on the Software Load By File screen (Figure 39 sheet 2), the Download File Phase 1 Progress screen is displayed on the iCMT (Refer to Figure 39).

b)

When the percent complete indicator reaches 100%, the OK button may be touched to return to the Software Load By File screen.

EFFECTIVITY ALL

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GRAPHIC TASK 44-21-74-990-868-A01 Download File Phase 1 Progress Screen Figure 39 10)

Content Loading Menu Screen a)

When the Update Content button is touched on the Download screen (Refer to Figure 35), the CONTENT LOADING MENU screen is displayed on the iCMT.

b)

The CONTENT LOADING MENU screen options are described in Table 12 and illustrated in Figure 40.

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TABLE TASK 44-21-74-990-869-A01 Content Loading Menu Screen Options Table 12 TITLE

TYPE

FUNCTION

Content Inventory Selection

Button

Displays the list of available content

Content Loading Status

Button

Displays the Content Loading Summary screen

Content Loading Control

Button

Displays the Content Load Control Menu screen

Back

Button

Returns to Download screen (Figure 35)

GRAPHIC TASK 44-21-74-990-870-A01 Content Loading Menu Screen Figure 40

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11)

Content Inventory Selection Screen a)

Content Inventory Selection is 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.

b)

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.

c)

When the “Change Inventory Selection” selection is made on the CONTENT LOADING MENU screen, 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.

d)

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. 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.

e)

f)

When the Content Inventory Selection button is touched on the CONTENT LOADING MENU screen the Content Inventory Selection screen is displayed on the iCMT. The Content Inventory Selection screen options are described in Table 13 and illustrated in Figure 41.

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TABLE TASK 44-21-74-990-871-A01 Content Inventory Selection Screen Options Table 13 TITLE

TYPE

FUNCTION

Content List

Radio Button

Provides selectable list of content

OK

Button

Advances to the Content Inventory Confirmation screen

Cancel

Button

Returns to the CONTENT LOADING MENU screen

LAN LAN LAN

LAN

GRAPHIC TASK 44-21-74-990-872-A01 Content Inventory Selection Screen Figure 41 (Sheet 1 of 2) EFFECTIVITY ALL

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LAN LAN LAN LAN

GRAPHIC TASK 44-21-74-990-873-A01 Content Inventory Selection Screen Figure 41 (Sheet 2 of 2) 12)

Content Inventory Confirmation Screen a)

When the OK button is touched on the Content Inventory Selection screen, the Active Content Selection screen is displayed on the iCMT. When OK is touched, the Content Inventory Confirmation screen is displayed on the iCMT.

b)

The Content Inventory Confirmation screen options are described in Table 14 and illustrated in Figure 42.

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-874-A01 Content Inventory Confirmation Screen Options Table 14 TITLE

TYPE

FUNCTION

Yes, I am sure

Button

Advances to the Content Loading Summary screen

No, I am not sure

Button

Returns to the Content Inventory Selection screen

GRAPHIC TASK 44-21-74-990-875-A01 Content Inventory Confirmation Screen Figure 42 (Sheet 1 of 2)

EFFECTIVITY ALL

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GRAPHIC TASK 44-21-74-990-876-A01 Content Inventory Confirmation Screen Figure 42 (Sheet 2 of 2) 13)

Content Loading Summary Screen a)

When the YES, I AM SURE button is touched on the Content Inventory Confirmation screen or when the Content Loading Status button is touched on the CONTENT LOADING MENU screen (Refer to Figure 41), the Content Loading Summary screen is displayed on the iCMT.

b)

The Content Loading Summary screen options are described in Table 15 and illustrated in Figure 44.

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TABLE TASK 44-21-74-990-877-A01 Content Loading Summary Screen Options Table 15 TITLE

TYPE

FUNCTION

Detail

Button

Advances to the Content Loading Detail screen

Engineering

Button

Advances to Content Loading Engineering Detail screen

PDL

Button

Advances to PDL Status screen

Switch to Files

Button

Switches loading summary from BYTES to files

Exit

Button

Returns to CONTENT LOADING MENU screen

GRAPHIC TASK 44-21-74-990-878-A01 Content Loading Summary Screen Figure 43 EFFECTIVITY ALL

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14)

Content Loading Detail Screen a)

When the detail button is touched on the Content Loading Summary screen, the Content Loading Detail screen is displayed on the iCMT.

b)

The Content Loading Detail screen options are described in Table 16 and illustrated in Figure 44.

TABLE TASK 44-21-74-990-879-A01 Content Loading Detail Screen Options Table 16 TITLE

TYPE

FUNCTION

Summary

Button

Returns to the Content Loading Summary screen (Figure 44)

Engineering

Button

Advances to Content Loading Engineering Detail screen (Figure 47)

PDL

Button

Advances to PDL Status screen (Figure 49)

Ÿ ź

Buttons

(Scroll UP, Scroll DOWN) Selects servers from Content Loading Detail screen listing

Exit

Button

Returns to CONTENT LOADING MENU screen

EFFECTIVITY ALL

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c)

When a server is selected from the Content Loading Detail Screen, a separate Content Loading Detail screen opens bearing selected server name, designation and the list of active files for that server. See Figure 45.

GRAPHIC TASK 44-21-74-990-880-A01 Content Loading Detail Screen Figure 44

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GRAPHIC TASK 44-21-74-990-881-A01 Content Loading Detail Screen Figure 45 15)

Content Loading Engineering Detail Screen a)

When the engineering button is touched on the Content Loading Summary screen, the Content Loading Engineering Detail screen is displayed on the iCMT.

b)

The Content Loading Engineering Detail screen options are described in Table 17 and illustrated in Figure 46.

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-882-A01 Content Loading Engineering Detail Screen Options Table 17 TITLE

TYPE

FUNCTION

Summary

Button

Returns to the Content Loading Summary screen

Detail

Button

Advances to the Content Loading Detail screen

PDL

Button

Advances to PDL Status screen

Switch to Files

Button

Switches loading summary from BYTES to files

Exit

Button

Returns to CONTENT LOADING MENU screen

GRAPHIC TASK 44-21-74-990-883-A01 Content Loading Engineering Detail Screen Figure 46 EFFECTIVITY ALL

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c)

By clicking on show legend on the Content Loading Engineering Detail Screen the Legend detail will show (Refer to Figure 47)

GRAPHIC TASK 44-21-74-990-884-A01 Legend Detail Figure 47 16)

PDL Status Page a)

When the PDL button is touched on the Content Loading Summary screen, the PDL Status Page is displayed on the iCMT.

b)

The PDL Status Page options are described in Table 18 and illustrated in Figure 48.

TABLE TASK 44-21-74-990-885-A01 PDL Status Page Options Table 18 TITLE

TYPE

FUNCTION

Summary

Button

Returns to the Content Loading Summary screen

Detail

Button

Advances to the Content Loading Detail screen

Engineering

Button

Advances to Content Loading Engineering Detail screen

Switch to Files

Button

Switches loading summary from BYTES to files

Exit

Button

Returns to CONTENT LOADING MENU screen

EFFECTIVITY ALL

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GRAPHIC TASK 44-21-74-990-886-A01 PDL Status Page Figure 48 c)

If you click PDL 1, or PDL 2 you will get a list of content files displayed in a separate screen as illustrated in figure 49.

d)

If no PDL is connected or connected improperly, a NO PDLs detected message will pop up on screen as illustrated in figure 50.

e)

If you get NO PDLs detected message, verify the connection to PDL from VCC port.

f)

Continuity check the RJ45 cable and inspect connector pins and sockets at both ends.

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GRAPHIC TASK 44-21-74-990-887-A01 PDL Status Detail Screen Figure 51

EFFECTIVITY ALL

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GRAPHIC TASK 44-21-74-990-888-A01 PDL Fault Screen Figure 52 17)

Content Load Control Menu Screen a)

When the Content Loading Control button is touched on the CONTENT LOADING MENU screen (Refer to Figure 51), the Content Load Control Menu screen is displayed on the iCMT.

b)

The Content Load Control Menu screen options are described in Table 19 and illustrated in Figure 51.

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-889-A01 Content Load Control Menu Screen Options Table 19 TITLE

TYPE

FUNCTION

Automatically Enable/Disable

Button

Automates the load and Crossload process

Enable Load/Crossload Unconditionally

Button

Enables Crossload to the DSU-D2s

Disable Load/Crossload Unconditionally

Button

Disables Crossload to the DSU-D2s

Engineering Control

Button

Advances to Content Load Control Engineering Menu Screen

Back

Button

Returns to CONTENT LOADING MENU screen

EFFECTIVITY ALL

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GRAPHIC TASK 44-21-74-990-890-A01 Content Load Control Menu Screen Figure 51 18)

Content Load Control Engineering Menu Screen a)

When the Engineering Control button is touched on the Content Loading Control Menu screen, the Content Load Control Engineering Menu screen is displayed on the iCMT.

b)

The Content Load Control Engineering Menu screen options are described in Table 20 and illustrated in Figure 52.

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-891-A01 Content Load Control Engineering Menu Screen Options Table 20 TITLE

TYPE

FUNCTION

Enable Content Download

Radio Button

Enables content download to the server

Enable Content Crossload

Radio Button

Enables Crossload to the DSU-D2s

Enable Content Deletion

Radio Button

Disables deletion of content from the server

Allow loading even when VOD is active

Radio Button

Enables content loading while Video-onDemand is active

Apply these settings until next power cycle

Radio Button

Applies the settings selected only until power to the system is cycled

Make these settings persist across power cycles

Radio Button

Applies the settings selected until changes are made

Apply Settings

Button

Applies all selected parameters to the system

Cancel

Button

Cancels all selected parameters and returns the system to its previous condition

Back

Button

Returns to Content Load Control Menu Screen

EFFECTIVITY ALL

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GRAPHIC TASK 44-21-74-990-892-A01 Content Load Control Engineering Menu Screen Figure 52 (Sheet 1 of 2)

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GRAPHIC TASK 44-21-74-990-893-A01 Content Load Control Engineering Menu Screen Figure 52 (Sheet 2 of 2) 19)

LRU Load Screen a)

When the Download LRU button is touched on the Download screen (Refer to Figure 34), the LRU Load screen is displayed on the iCMT.

b)

The LRU Load screen options are described in Table 21 and illustrated in Figure 53.

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-894-A01 LRU Load Screen Options Table 21 TITLE

TYPE

FUNCTION

ALL SELECTED LRUS

Button

Initiates download to all selected LRUs

SINGLE LRU

Button

Initiates download to single LRU

DONE

Button

Returns to Download screen

LAN

LAN LAN

GRAPHIC TASK 44-21-74-990-895-A01 LRU Load Screen Figure 53 (Sheet 1 of 2)

EFFECTIVITY ALL

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LAN

GRAPHIC TASK 44-21-74-990-896-A01 LRU Load Screen Figure 53 (Sheet 2 of 2) 20)

Download Phase 2 Status Screen a)

When ALL SELECTED LRUs or SINGLE LRU buttons are touched on the LRU Load screen, the Download Phase 2 status screen is displayed on the iCMT (Refer to Figure 54).

b)

When the percent complete indicator reaches 100%, the OK button may be touched to advance to the System Config - Detail screen (Refer to Figure 57).

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GRAPHIC TASK 44-21-74-990-897-A01 Download Phase 2 Status Screen Figure 54 21)

Configuration Check Screen a)

When Config Check is touched on the Maintenance screen (Refer to Figure 33), the Configuration Check screen is displayed on the iCMT.

b)

The Configuration Check screen options are described in Table 22 and illustrated in Figure 55.

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-898-A01 Configuration Check Screen Options Table 22 TITLE

TYPE

FUNCTION

Action

Radio Button

Selects action from 2 choices

View Type

Radio Button

Selects view type from 4 choices

Target Group

Radio Button

Selects target group from 8 choices

GO

Button

Advances to Top Level screen

Cancel

Button

Returns to Maintenance screen

GRAPHIC TASK 44-21-74-990-899-A01 Configuration Check Screen Figure 55 EFFECTIVITY ALL

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c)

When GO is touched on the Configuration Check Screen, the Configuration Data screen is displayed on the iCMT (Refer to Figure 56).

d)

When the bar on the Configuration Data screen indicates 100%, touch OK to advance to the System Config - Detail screen (Refer to Figure 57).

GRAPHIC TASK 44-21-74-990-900-A01 Configuration Data Screen Figure 56 22)

System Config - Detail Screen a)

When OK is touched on the Download Phase 2 Status Screen or the Configuration Data screen the System Config - Detail screen is displayed on the iCMT.

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b)

The System Config - Detail screen options are described in Table 23 and illustrated in Figure 58.

TABLE TASK 44-21-74-990-901-A01 System Config - Detail Screen Options Table 23 TITLE

TYPE

FUNCTION

CC Menu

Button

Returns to Configuration Check screen

Top Level

Button

Advances to Top Level screen

Summary

Button

Advances to System Summary screen

Engineering

Button

Advances to System Config – Engineering screen

EFFECTIVITY ALL

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GRAPHIC TASK 44-21-74-990-902-A01 System Config Detail Screen Figure 58 23)

Top Level Screen a)

When the Top Level button is touched on the System Config - Detail screen, the Top Level screen is displayed on the iCMT.

b)

The Top Level screen options are described in Table 24 and illustrated in Figure 59.

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-903-A01 Top Level Screen Options Table 24 TITLE

TYPE

FUNCTION

CC Menu

Button

Returns to Configuration Check screen

Summary

Button

Advances to System Summary screen

Detail

Button

Advances to System Config - Detail screen

Engineering

Button

Advances to System Config – Engineering screen

GRAPHIC TASK 44-21-74-990-904-A01 Top Level Screen Figure 59 24)

System Summary Screen

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a)

When the Summary button is touched on the System Config - Detail screen, the System Summary screen is displayed on the iCMT.

b)

The System Summary screen options are described in Table 25 and illustrated in Figure 60.

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TABLE TASK 44-21-74-990-905-A01 System Summary Screen Options Table 25 TITLE

TYPE

FUNCTION

CC Menu

Button

Returns to Configuration Check screen

Top Level

Button

Advances to Top Level screen

Detail

Button

Advances to System Config - Detail screen

Engineering

Button

Advances to System Config – Engineering screen

GRAPHIC TASK 44-21-74-990-906-A01 System Summary Screen Figure 60 EFFECTIVITY ALL

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25)

System Config – Engineering Screen a)

When the Engineering button is touched on the System Config - Detail screen, the System Config - Engineering screen is displayed on the iCMT.

b)

The System Config - Engineering screen options are described in Table 26 and illustrated in Figure 61.

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TABLE TASK 44-21-74-990-907-A01 System Config – Engineering Screen Options Table 26 TITLE

TYPE

FUNCTION

CC Menu

Button

Returns to Configuration Check screen

Top Level

Button

Advances to Top Level screen

Summary

Button

Advances to System Summary screen

Detail

Button

Advances to System Config - Detail screen

GRAPHIC TASK 44-21-74-990-908-A01 System Config – Engineering Screen Figure 61

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26)

IP Sequence Menu Screens a)

When IP Sequencing is touched on the Maintenance screen (Refer to Figure 34), the IP Sequence Menu screen is displayed on the iCMT.

b)

The IP Sequence Menu screen options are described in Table 27 and illustrated in Figure 62. NOTE:

Refer to MAINTENANCE PRACTICES section for actual IP Sequence Procedure.

TABLE TASK 44-21-74-990-909-A01 IP Sequence Menu Screen Options Table 27 TITLE

TYPE

FUNCTION

IP Sequence 3

Button

Initiates IP sequencing process and advances to IP Sequence Progress screen

Done

Button

Returns to Maintenance screen

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GRAPHIC TASK 44-21-74-990-910-A01 IP Sequence Menu Screen Figure 62 c)

When IP Sequence is touched on the IP Sequence Menu screen, the IP Sequence Progress screen is displayed on the iCMT (Refer to Figure 63).

d)

When the percent complete indicator reaches 100%, the OK button may be touched to proceed to the IP Sequence Report screen (Refer to Figure 64).

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GRAPHIC TASK 44-21-74-990-911-A01 IP Sequence Progress Screen Figure 63

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GRAPHIC TASK 44-21-74-990-912-A01 IP Sequence Report Screen Figure 64 (Sheet 1 of 2)

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GRAPHIC TASK 44-21-74-990-913-A01 IP Sequence Report Screen Figure 64 (Sheet 2 of 2) e) 27)

When the DONE button is touched on the IP Sequence Report screen, the user is returned to the IP Sequence Menu screen

IP Sequencing a)

In the TopSeries™ IFE system, the SEBs does not have any hard-coded or hard-wired addressing to indicate their positions within the system. Since each SEB needs to have a unique Ethernet address associated with its seatgroup number, the IP Sequencing system was developed.

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b)

Each Ethernet-capable LRU in the system contains a configuration data file that defines the map of all the LRUs. The SEB data includes each SEBs position within which string, connected to which port of which ADB, the seatgroup number of that position and the Ethernet address of that seat-group. The IP Sequencing uses the configuration data file to allow each SEB to determine its position within the network.

c)

Each SEB passes through the Ethernet interface to the next downstream SEB in its string, with the last unit in the string providing termination, 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.

d)

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 give the SEB its location, 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.

e)

The IP Sequencing procedure is contained in the ADJUSTMENT/TEST section of this manual. NOTE:

28)

To avoid improper IP sequence procedure insure that SEBs are preloaded prior to IP sequencing.

Static Test Screen a)

When the Static Test button is touched on the Maintenance screen (Refer to Figure 34), the Static Test screen is displayed on the iCMT.

b)

The Static Test screen options are defined in Table 28 and illustrated in Figure 65.

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TABLE TASK 44-21-74-990-907-A01 System Config – Engineering Screen Options Table 26 TITLE

TYPE

FUNCTION

CC Menu

Button

Returns to Configuration Check screen

Top Level

Button

Advances to Top Level screen

Summary

Button

Advances to System Summary screen

Detail

Button

Advances to System Config - Detail screen

GRAPHIC TASK 44-21-74-990-908-A01 System Config – Engineering Screen Figure 61

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26)

IP Sequence Menu Screens a)

When IP Sequencing is touched on the Maintenance screen (Refer to Figure 34), the IP Sequence Menu screen is displayed on the iCMT.

b)

The IP Sequence Menu screen options are described in Table 27 and illustrated in Figure 62. NOTE:

Refer to MAINTENANCE PRACTICES section for actual IP Sequence Procedure.

TABLE TASK 44-21-74-990-909-A01 IP Sequence Menu Screen Options Table 27 TITLE

TYPE

FUNCTION

IP Sequence 3

Button

Initiates IP sequencing process and advances to IP Sequence Progress screen

Done

Button

Returns to Maintenance screen

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GRAPHIC TASK 44-21-74-990-910-A01 IP Sequence Menu Screen Figure 62 c)

When IP Sequence is touched on the IP Sequence Menu screen, the IP Sequence Progress screen is displayed on the iCMT (Refer to Figure 63).

d)

When the percent complete indicator reaches 100%, the OK button may be touched to proceed to the IP Sequence Report screen (Refer to Figure 64).

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GRAPHIC TASK 44-21-74-990-911-A01 IP Sequence Progress Screen Figure 63

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GRAPHIC TASK 44-21-74-990-912-A01 IP Sequence Report Screen Figure 64 (Sheet 1 of 2)

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GRAPHIC TASK 44-21-74-990-913-A01 IP Sequence Report Screen Figure 64 (Sheet 2 of 2) e) 27)

When the DONE button is touched on the IP Sequence Report screen, the user is returned to the IP Sequence Menu screen

IP Sequencing a)

In the TopSeries™ IFE system, the SEBs does not have any hard-coded or hard-wired addressing to indicate their positions within the system. Since each SEB needs to have a unique Ethernet address associated with its seatgroup number, the IP Sequencing system was developed.

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b)

Each Ethernet-capable LRU in the system contains a configuration data file that defines the map of all the LRUs. The SEB data includes each SEBs position within which string, connected to which port of which ADB, the seatgroup number of that position and the Ethernet address of that seat-group. The IP Sequencing uses the configuration data file to allow each SEB to determine its position within the network.

c)

Each SEB passes through the Ethernet interface to the next downstream SEB in its string, with the last unit in the string providing termination, 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.

d)

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 give the SEB its location, 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.

e)

The IP Sequencing procedure is contained in the ADJUSTMENT/TEST section of this manual. NOTE:

28)

To avoid improper IP sequence procedure insure that SEBs are preloaded prior to IP sequencing.

Static Test Screen a)

When the Static Test button is touched on the Maintenance screen (Refer to Figure 34), the Static Test screen is displayed on the iCMT.

b)

The Static Test screen options are defined in Table 28 and illustrated in Figure 65.

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TABLE TASK 44-21-74-990-914-A01 Static Test Screen Options Table 28 TITLE

TYPE

FUNCTION

Static Test Menu

Radio Button

Provides a drop down list of test items

On

Button

Initiates the static test

Off

Button

Stops the static test

Back

Button

Returns to the Maintenance Menu screen

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GRAPHIC TASK 44-21-74-990-915-A01 Static Test Screen Figure 65

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c)

The Drop down menu allows for test selection as shown in figure 66.

GRAPHIC TASK 44-21-74-990-916-A01 Static Test Screen Dropdown Menu Figure 66 d)

VOD This test will play the standard Thales VOD test clip of movie trailers. When initiated each SVDU will wait a random amount of time from 0 to 60 seconds before requesting the playback from their primary server. The test clip is 20 minutes long and will run once. This test is useful for judging network performance and reliability. Since all clients are streaming the same video it is not particularly stressful on the server.

e)

VOD_Random This is much more demanding test and comes closer to actual VOD streaming usage during an actual flight. In this test the SVDUs will randomly choose from the largest 50 MPEG files they find on the server. They will

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wait a random amount of time from 0 to 300 seconds (5 minutes) before requesting the VOD. This test will repeat 5 times before terminating. This test will run for approximately 8 hours or more depending on the content load. f)

Playback Statistics Both VOD_Single and VOD_Random will report playback statistics to the iCMT. The statistics reported while the test is running consist of the following:

g)

Clients reporting As each client initiates the test, it reports to their primary server if present or the secondary if the primary is down.

h)

Play Attempts The number of times a VOD stream is requested from the server.

i)

VODs Started When a VOD streaming request is granted and the movie begins playing this count is incremented.

j)

Startup Failures Sometimes when the server is very busy, a VOD play request is denied. When this happens to a passenger they will see a “Selection not available. Try again later” pop-up message. This count is incremented each time this occurs. The test script will then wait a random amount of time between 0 and 300 seconds before re-requesting the VOD playback.

k)

Playback Quality Once a VOD is started, the test script will monitor the quality of the playback in terms of dropped packets, buffer underruns and buffer overruns. Each time one of these conditions occurs the passenger may experience a visual ‘glitch’ in the playback. The test script keeps track of the glitch count. When the VOD stops playing it will evaluate the quality of the playback based on glitches per hour. The thresholds for these ratings are as follows:

l)

(1)

Good: 0 to 1 glitches per hour

(2)

Fair:

2 to 3 glitches per hour

(3)

Poor:

4 or more glitches per hour

Play Failures

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m)

A VOD is judged to be a failure when it does not run for the expected length of time. Playback failures can occur when the server becomes so busy that it cannot serve the client data for several seconds causing the VOD to stop prematurely or the server or streaming process resets or freezes. It is also possible that corrupt content can cause play failures.

n)

User Interface is as follows: (1)

When the VOD_Single or VOD_Random is initiated from the static test menu the screen in Figure 67 will be displayed.

GRAPHIC TASK 44-21-74-990-917-A01 Static Test Screen Figure 67 (2)

These results are updated every 5 seconds. To stop the test and save the results touch CANCEL. The test will then consolidate the results and present the data as shown in Figure 68.

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GRAPHIC TASK 44-21-74-990-918-A01 Static Test Consolidating Results Screen Figure 68 (3)

The HTML web page of Figure 67 (VodRandomStatusUpdated.htm) and Figure 69 (VodRandomPostStatusUpdated.htm) will be saved to the PDL and a USB memory stick plugged into the iCMT USB offload port if present (Neither of these devices need to be present to run the test). The data will be saved to the vodTest-YYYY_MM_DD-HH_MM directory where YYYY_MM_DD-HH-MM represents the aircraft date and time as provided by 429 labels.

(4)

On the Thales PDLs this directory will be created in the root directory of the C: drive. On the ACA Dell Laptop PDLs this will be created in the ThalesUpload directory of the C: Drive. On the USB memory stick this directory will be created in the root directory.

(5)

After the test is complete and the operator touches the CANCEL button then a page as shown in Figure 69 will be displayed with some consolidated results. This page lists the VOD files that were measured with poor play or failed playback performance as well as the clients that had failed playbacks.

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GRAPHIC TASK 44-21-74-990-919-A01 Static Test Screen Figure 69 This list is useful in seeing if the failures are evenly distributed or if a particular piece of content or client was causing the majority of the failures. As you can see in Figure 69, the file 03200709121413001000.mpg failed 7 times. This indicates that the problem may lie with the content and not the system. (6)

29)

In addition to saving the web pages, data from SVDUs that exhibited poor or failed playbacks will save additional data to the PDL only. These will be saved in directories named Dn_vodTestBuffHistory where ‘n’ is the number of then DSU-D2 that was serving the client. These files can be sent to Thales for analysis.

Content Management a)

Audio and video entertainment content files are downloaded to the DSUAM6-12 hard disk drive and DSU-D2s depending on configuration index list details, from a laptop PC configured as a Portable Data Loader (PDL).

b)

The PDL connects to the i4000 System via the data loader ports located in the VCC, and it communicates to the system via a 100Base-b Ethernet link. Software on the PDL controls the content management and download functions.

c)

Refer to the ADJUSTMENT/TEST section of this manual for the Content Loading Procedures.

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30)

PSS Menu Screen a)

When PSS is touched on the Maintenance screen (Refer to Figure 34), the PSS Menu screen is displayed on the iCMT.

b)

The PSS Menu screen options are described in Table 29 and illustrated in Figure 70. NOTE:

Refer to MAINTENANCE PRACTICES section for actual OEB addressing.

TABLE TASK 44-21-74-990-920-A01 PSS Menu Screen Options Table 29 TITLE

TYPE

FUNCTION

All R/L On

Button

All aircraft reading light on

All R/L Off

Button

All aircraft reading light of

All Call Cancel

Button

Cancels all Call

Row Up arrows

Button

Seat selection up

Row Down arrows

Button

Seat selection down

Back

Button

Previous Screen

Refresh Row

Button

Refreshes current selected seat

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GRAPHIC TASK 44-21-74-990-921-A01 PSS Menu Screen Figure 70 N.

Offload 1)

Offload functions are initiated by the operator via the iCMT. The Offload Menus are accessed by touching Offload from the iCMT welcome screen.

2)

Offload Access Screen a)

When the Offload button is touched on the LAN welcome screen, the Offload Access Screen is displayed on the iCMT

b)

The Offload Access Screen options are described in Table 30 and illustrated in Figure 71.

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TABLE TASK 44-21-74-990-922-A02 Offload Access Screen Options Table 30 TITLE

TYPE

FUNCTION

Password Edit Box

Display

Displays the masked key presses from the keypad

Keypad

Buttons

Provides keys for password entry

Clear

Button

Erases character entry in edit box

Enter

Button

Enables entrance to the Offload screens after a valid password has been entered

Exit

Button

Returns to the Welcome screen

GRAPHIC TASK 44-21-74-990-923-A03 Offload Access Screen Figure 71 EFFECTIVITY ALL

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3)

Usage Stat Offload Access Screen a)

When the Enter button is touched on the Offload Access screen, the Usage Stat Offload Access Screen is displayed on the iCMT

b)

The Usage Stat Offload Access Screen options are described in Table 31 and illustrated in Figure 72. NOTE:

c)

Once 64 flight legs have occurred the system will generate the offloadable file automatically and it will be listed under archive, under 64 legs no archive data will be available.

If Archive file is selected the user is directed to a new screen which will allow the user to select an archived file. The files shall be listed with the most recent first. The files are deleted after they have been stored six months.

TABLE TASK 44-21-74-990-924-A04 Usage Stat Offload Access Screen Options Table 31 TITLE

TYPE

FUNCTION

Tail Number Box

Display

Displays the Tail Number

Edit

Button

Provides pop-up keyboard for Tail Number entry

Current

Button

Advances display to current usage stat screen

Archive

Button

Advances display to archived usage stat screen

Home

Button

Returns to the Welcome screen

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GRAPHIC TASK 44-21-74-990-925-A05 Usage Stat Offload Access Screen Figure 72 d)

When no data is available for offload screen 73 will be shown.

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No Data Available for Offload

GRAPHIC TASK 44-21-74-990-926-A07 No Data Available for Offload Screen Figure 73 e)

When archive is available then the user will be able to select from .tgz files (Refer to Figure 74).

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GRAPHIC TASK 44-21-74-990-927-A07 Usage Stat Offload Screen Figure 74 4)

Usage Stat Offload Progress Screens a)

When the Offload button is touched on the Usage Stat Offload screen, the Usage Stat Offload Progress Screen is displayed on the iCMT (Refer to Figure 75).

b)

The Usage Stat Offload Progress Screen indicates the status of the offload in progress.

c)

When Offload is complete, the Processing Completed screen is displayed (Refer to Figure 76).

d)

When the Exit button is touched from either screen, the iCMT returns to the Welcome screen.

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GRAPHIC TASK 44-21-74-990-928-A08 Usage Stat Offload Progress Screen Figure 75

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GRAPHIC TASK 44-21-74-990-929-A09 Processing Completed Screen Figure 76

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TASK 44-21-74-990-930-A01 4.

Line Replaceable Unit Descriptions

SUBTASK 44-21-74-990-021-A01 A.

Audio/Video Controller (AVC) 1)

Location a)

The AVC (P/N 177716-103) is located in the VCC assembly.

b)

For detailed description and illustrated parts list, refer to the AVC CMM; Thales document number 44-20-26.

2)

Description The AVC provides video modulation, audio modulation, passenger announcement (PA), overhead video system control, and communications. The AVC incorporates the functions of the traditional audio multiplexer (MUX) and overhead video control system into a single LRU. One or two AVCs can be installed in an aircraft depending on the aircraft wiring and the number of channels desired.

3)

External Connectors (Refer to Figure 77) J1 RS-232 Maintenance Port

4)

Indicators (Refer to Table 32 and Figure 77)

TABLE TASK 44-21-74-990-931-A01 Indicators Table 32 CONTROL OR INDICATOR

FUNCTION

BITE OK (LED)

Indicates no failure with BITE

DC Power (LED)

Indicates DC Power is Supplied

AC Power (LED)

Indicates AC Power is Supplied

5)

Leading Particulars, AVC (Refer to Table 33)

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TABLE TASK 44-21-74-990-932-A01 AVC Leading Particulars Table 33 ITEM Dimensions

PARTICULAR Dimensions are in Inches (IN) and Millimeters (mm) in Width (W), Height (H), and Length (L) as follows: 5.000 IN+ .020 IN W / 127mm + 0.5mm W 7.850 IN + .020 IN H / 199.39mm + 0.5mm H 12.515 IN + .040 IN L / 317.88mm + 1.01mm L

Weight

13.5 pounds maximum (6.14 kg)

Power Dissipation

125 Watts maximum

Power Requirement

100VAC to 126 VAC, 400Hz

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RS-232 PORT BITE, AC POWER AND DC POWER INDICATORS

GRAPHIC TASK 44-21-74-990-933-A01 Audio/Video Controller Figure 77 EFFECTIVITY ALL

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SUBTASK 44-21-74-990-022-A01 B.

Digital Server Unit-AM6-12 (DSU-AM6-12) 1)

Location a)

The DSU-AM6-12 (P/N 177900-103) is located in the VCC assembly.

b)

For detailed description and illustrated parts list, refer to the DSU-AM6-12 CMM; Thales document number 44-20-29.

2)

Description The DSU-AM6-12 provides video entertainment similar to a Video Tape Reproducer (VTR). 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.

3)

External Connectors (Refer to Figure 78) a)

J2 SCSI Connector

b)

J3 RS-232 Maintenance Port

4)

Indicators (Refer to Table 34 and Figure 78)

TABLE TASK 44-21-74-990-934-A01 DSU AM6-12 Indicators Table 34 INDICATORS

FUNCTION

DC (LED)

Illuminates when voltage is applied to DSU-AM6-12

AC (LED)

Illuminates when voltage is applied to DSU-AM6-12

SCSI (LED)

Illuminates when the SCSI drive is busy.

BITE OK (LED)

Illuminates when BITE is successful.

5)

Leading Particulars, DSU-AM6-12 (Refer to Table 35)

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TABLE TASK 44-21-74-990-935-A01 Digital Server Unit-AM6-12 Leading Particulars Table 35 ITEM Dimensions

PARTICULAR Dimensions are in Inches (IN) and Millimeters (mm) in Width (W), Height (H),Length (L), and as follows: 10.214 IN + .050 IN W / 259.44mm + 1.27mm W 10.094 IN + .020 IN H / 256.39mm + 0.51mm H 12.530 IN + .030. - .05 IN L / 318.26mm +0.76 – 1.21 L

Weight

28.05 lbs maximum

Cooling

Forced air

Power Requirement

115 VAC, 400 Hz aircraft power

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TOPSERIES™ I4000 SYSTEM

SCSI LED BITE OK LED AC OK LED DC OK LED

GRAPHIC TASK 44-21-74-990-936-A01 Digital Server Unit-AM6-12 Figure 78

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SUBTASK 44-21-74-990-023-A01 C.

Digital Server Unit-D2 (DSU-D2) 1)

Location a)

The DSU-D2 (P/N 177892-102) is located in the VCC.

b)

For detailed description and illustrated parts list, Refer to the applicable Thales CMM: 44-20-35.

2)

Description a)

The DSU-D2 Distributes digital content files made up of MPEG videos, menu-driven databases, interactive games, HTML (HXM), and general eCommerce data.

b)

The DSU provides streaming digital data outputs derived from digital content stored on rotating magnetic memory (i.e., disk drive). The DSU is of a modular construction, with a well-defined external interface. The DSU provides a rack mount electrical and physical interface as specified in Aeronautical Radio Incorporated (ARINC) 600.

3)

External Connectors (Refer to Figure 79) J1 RS-232 Maintenance Port

4)

Indicators (Refer to Table 36, and Figure 79)

TABLE TASK 44-21-74-990-937-A01 Indicators Table 36 INDICATOR

FUNCTION

DC (LED)

When DC Voltage is supplied the LED indicator is lit.

SCSI 1 (LED)

When SCSI Drive is busy the LED will blink.

SCSI 2 (LED)

When SCSI Drive is busy the LED will blink.

FAULT (LED)

If the Bite tests are unsuccessful, this LED will remain ON.

5)

Leading Particulars, DSU - D2 (Refer to Table 37)

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TABLE TASK 44-21-74-990-938-A01 DSU - D2 Leading Particulars Table 37 ITEM Dimensions

PARTICULAR Dimensions are in Inches (IN) and Millimeters (mm) in Width (W), Height (H), and Length (L) as follows: 5.000 IN+ .020 IN W / 127mm + 0.5mm W 7.850 IN + .020 IN H / 199.39mm + 0.5mm H 12.515 IN + .040 IN L / 317.88mm + 1.01mm L

Weight

12.5 pounds (5.67 kg) maximum

Power Dissipation

60 Watts maximum

Power Requirement

115 VAC, 400Hz, single phase

Amps RMS

77 maximum

Minimum Air Flow Requirement

8 CFM bottom to top or 15 CFM top to bottom

Recommended Air Flow

15 CFM bottom to top or 25 CFM top to bottom

EFFECTIVITY ALL

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POWER DRIVE AND FAULT INDICATORS

RS-232 PORT ACCESS

GRAPHIC TASK 44-21-74-990-939-A01 Digital Server Unit-D2 Figure 79 EFFECTIVITY ALL

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SUBTASK 44-21-74-990-024-A01 D.

Ethernet Switching Unit-Gigabit (ESU-G) 1)

Location a)

The ESU-G (P/N 178568-102) is located in the VCC assembly.

b)

For detailed description and illustrated parts list, refer to the ESU-G CMM; Thales document number 44-21-43.

2)

Description a)

The ESU-G is a 4 MCU avionics LRU that contains two complete and independent 24 port managed Ethernet switches. Inside the ESU-G are four plug-in circuit cards in two logical groups.

b)

The ESU-G is used to connect Ethernet devices to form a Local Area Network (LAN) within an airborne avionics environment. Its function is to intercept incoming Ethernet packets, determine their source and destination, then route them in the most efficient way. The ESU-G switches these packets at wire speed, adding minimal latency through the switch. The ESUG accepts downloadable configuration tables based on known addresses within its LAN and switches packets according to the table.

3)

External Connectors (Refer to Figure 80) a)

J1 RS-232 Communications

b)

J2 Fiber Optic Connection

4)

Indicators (Refer to Table 38 and Figure 80)

TABLE TASK 44-21-74-990-940-A01 Indicator Description Table 38 INDICATOR

FUNCTION

RUN (LED)

Red LED Will only be on during processing

POWER (LED)

Green LED will remain on when powered on

EFFECTIVITY ALL

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5)

Leading Particulars, ESU-G (Refer to Table 39)

TABLE TASK 44-21-74-990-941-A01 ESU-G Leading Particulars Table 39 ITEM Dimensions

PARTICULAR Dimensions are in Inches (IN) and Millimeters (mm) in Width (W), Height (H), and Length (L) as follows: 5.000 IN W / 127mm W 7.850 IN H / 199.39mm H 11.072 IN L / 281.22mm L

Weight

13 pounds (5.9 kilograms) maximum

Minimum Air Flow Requirements

8 CFM bottom to top or 12 CFM top to bottom

Recommended Air Flow

14 CFM bottom to top or 20 CFM top to bottom

Power Requirement

115 VAC, 400 Hz, single phase

Power Consumption

72 Watts (Maximum)

Operating Temperature

-15 to 70 degrees Centigrade (DO 160D, Category A2)

Ground Survival Temperature

-55 to +85 degrees Centigrade

Operating Altitude

0 to +50,100 feet

Non-Operating Altitude

-15,000 to +50,100 feet

MTBF, 24 Port Ethernet Switch PCBA

24,000 hours

MTBF, Power Supply

100,000 hours

Relative Humidity

95%

Operational Shock

6 G’s for 11 ms duration on all axis

Vibration

DO 160D Section 8.7.2 Category C and C1

EFFECTIVITY ALL

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GRAPHIC TASK 44-21-74-990-942-A01 Ethernet Switching Unit-Gigabit Figure 80 EFFECTIVITY ALL

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SUBTASK 44-21-74-990-025-A01 E.

Area Distribution Box (ADB) 1)

Location a)

The ADBs (P/N 177730-106) are located in the cabin. There are five ADBs for this i4000 system configuration; the exact locations are determined by Boeing. Refer to the Component Locations section of the Boeing 767 AMM.

b)

For detailed description and illustrated parts list, refer to the ADB CMM; Thales document number 44-21-51.

2)

Description a)

The ADB provides downstream Ethernet and Radio Frequency (RF) distribution to other components of the TopSeries™ i4000 System.

b)

The ADB is an unmanaged 17-port switch that is capable of limited management functions. The ADB functions as an RF equalizer/splitter to provide acceptable levels of RF to the seat group components, and also as a passive tap for the other ADBs in the chain.

3)

External Connectors (Refer to Figure 81) a)

J1 AC power input.

b)

J2 Auxiliary connection

c)

J3 Column Output Connection.

d)

J4 Column Output Connection.

e)

J5 Column Output Connection.

f)

J6 Column Output Connection.

EFFECTIVITY ALL

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g)

J8 Column Output Connection.

h)

J9 Output to Tapping Unit Column Connector

i)

J10 Boeing Standard Interface Connector

j)

J16 Auxiliary connection

4)

Leading Particulars ADB (Refer to Table 40)

TABLE TASK 44-21-74-990-943-A01 Area Distribution Box Leading Particulars Table 40 ITEM Dimensions

PARTICULAR Dimensions are in Inches (IN) and Millimeters (mm) in Length (L), Height (H), and Width (W) as follows: 9.250 IN W / 235mm W 4.96 IN H / 125.9mm H 7.824 IN L / 199mm L

Weight

6.32 lbs (2.90 kg) maximum

Power Requirement

115 VAC, 400 Hz, single phase

Power Consumption

70 VA maximum

Power Factor at Maximum Load

0.97 minimum

Current Consumption

0.33 A

Power Dissipation

36 Watts maximum

Cooling Requirements

Convection DO-160D

EFFECTIVITY ALL

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J16 J2

J1 AC POWER

REAR VIEW

J4

J3

J6 J8 J5 J9 J10

GRAPHIC TASK 44-21-74-990-944-A01 Area Distribution Box (ADB) Figure 81 EFFECTIVITY ALL

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SUBTASK 44-21-74-990-026-A01 F.

Master Control Unit (MCU) 1)

Location a)

The MCUs (P/N 177922-103) are located in the cabin. There are four MCUs for this i4000 system configuration; the locations are determined by Boeing. Refer to the Component Locations section of the Boeing 767 AMM.

b)

For detailed description and illustrated parts list, refer to the MCU CMM; Thales document number 25-20-21.

2)

Description a)

The MCU provides power distribution management.

b)

Power is distributed through five columns. Each column supports three lines of 115 VAC. The current in each column is continuously measured. The MCU monitors total power consumption and limits consumption when the defined limit is reached.

3)

External Connectors (Refer to Figure 82) a)

J1, J2, J3, J4, and J5 AC Outlet Connectors

b)

J6 RS232 Maintenance Port

c)

J7 Programming module connector

d)

J8 Power Input Connector

4)

Indicators (Refer to Table 41 and Figure 83)

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-945-A01 Master Control Unit Indicators Table 41 Port BITE

Port Power Status

General BITE

Power Status

5)

Off

Output BITE fault

Flash

El. Fuse or GFI tripped

On

Normal operation

Off

No output power on all 3 output phase

On

All output phase present

Off

Fatal BITE fault (e.g. GIF, et. Fuse tripped)

Flash

Minor BITE fault

On

Normal operation

Off

No input power

Flash

1 or 2 phases present

On

3 phases present

Leading Particulars (Refer to Table 42)

TABLE TASK 44-21-74-990-946-A01 Master Control Unit Leading Particulars Table 42 ITEM

PARTICULAR

Dimensions

5.90 inches x 6.70 inches x 6.70 inches (150 mm x 170 mm x 170 mm)

Weight

6.61 lbs (3 kg) maximum

Power Requirement

115 VAC, 400 Hz, 25 A, 3 Phase

Power Dissipation

Less than 25 VA

Altitude

Normal operation up to 50,000 ft (15,240 m)

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM J5

J1 J2

J4

J3

J7

J6

J8

LED INDICATORS REFER TO SHEET 2 VIEW A

GRAPHIC TASK 44-21-74-990-947-A01 Master Control Unit Figure 82

EFFECTIVITY ALL

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VIEW A GRAPHIC TASK 44-21-74-990-948-A01 Master Control Indicators Figure 83

EFFECTIVITY ALL

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SUBTASK 44-21-74-990-027-A01 G.

Programming Module (PM) 1)

Location a)

The PMs (P/N 177923-901) are attached to the MCUs.

b)

For detailed description and illustrated parts list, refer to the PM CMM; Thales document number 25-20-30.

2)

Description a)

The PM provides the interface between the MCU and the stored data system.

b)

The PM plugs into J7 of the MCU.

3)

External Connector (Refer to Figure 84) J1 Main I/O Connector

4)

Leading particulars, PM (Refer to Table 43)

TABLE TASK 44-21-74-990-949-A01 PM Leading Particulars Table 43 ITEM

PARTICULAR

Dimensions

1.93 inches x 1.34 inches x 0.43 inches (49 mm x 34 mm x 11 mm)

Weight

0.063 lbs (29 grams) maximum

Altitude

Normal operation up to 50,000 ft (15,240 m)

EFFECTIVITY ALL

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J1

GRAPHIC TASK 44-21-74-990-950-A01 Program Module Figure 84

EFFECTIVITY ALL

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SUBTASK 44-21-74-990-028-A01 H.

Tapping Unit (TU) 1)

Location a)

The TUs (P/N 177832-101) are located in the cabin. There are five TUs for this i4000 system configuration; the locations are determined by Boeing. Refer to the Component Locations section of the Boeing 767 AMM.

b)

For detailed description and illustrated parts list, refer to the TU CMM; Thales document number 44-20-30.

2)

Description The primary function of the TU is downstream distribution to other components in the system. Each TU distributes baseband video outputs derived from an RF source to three Bulkhead Monitors.

3)

External Connectors (Refer to Figure 85) a)

J1 Monitor 1 Connector

b)

J2 Head End Connector

c)

J4 Monitor 2 Connector

d)

J5 Monitor 3 Connector

4)

Leading Particulars, TU (Refer to Table 44)

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-951-A01 TU Leading Particulars Table 44 ITEM Dimensions

PARTICULAR Dimensions are in Inches (IN) and Millimeters (mm) in Length (L), Height (H), and With (W) as follows: 6.89 IN / 175.0 mm L 2.44 IN / 133.4 mm H 5.25 IN / 199mm W

Weight

1.93 pounds (0.875 kilograms) maximum

Cooling

Convection

Power Requirement

115 VAC, 400 Hz, single phase

Power Consumption

6.5 - 16.75 Watts (Maximum)

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM J3

J4 J5

J1

J2

REAR VIEW GRAPHIC TASK 44-21-74-990-952-A01 Tapping Unit Figure 85

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

SUBTASK 44-21-74-990-029-A01 I.

Seat Electronics Box (SEB) 1)

Location a)

There is an SEB (P/N 177745-106) mounted in each seat group, and one SEB mounted in the VCC rack assembly for the iCMT.

b)

For detailed description and illustrated parts list, refer to the SEB CMM; Thales document number 44-21-42.

2)

Description a)

The SEB provides audio/video entertainment, personal external audio video source interface, and laptop/telephony connections.

b)

The SEB distributes broadcast audio/video from the Radio Frequency (RF) network, and digital interactive audio/video from the 100Base-TX network.

c)

Each SEB supports up to three seats. Up to 10 SEBs may be daisy chained together in a column.

3)

Exterior Connectors (Refer to Figure 86) a)

J1 Data In

b)

J2 Data Out

c)

J6 External Audio/Video Connector

d)

J9 Power In

e)

J10 and J11 Power Out

f)

J7 A and J7 B In-Seat Connector

EFFECTIVITY ALL

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4)

Leading particulars, SEB (Refer to Table 45)

TABLE TASK 44-21-74-990-953-A01 SEB Leading Particulars Table 45 ITEM Dimensions

PARTICULAR Dimensions are in Inches (IN) and Millimeters (mm) in Width (W), Height (H), Length (L) and as follows: 2.71 IN W / 68.9mm W 9.20 IN H / 233.7mm H 7.35 IN L / 186.7mm L

Weight

4.2 lbs (1.9 kg) maximum

Power Dissipation

47 W maximum at full load

Power Requirement

115 VAC, 400 Hz, three phase

EFFECTIVITY ALL

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VIEW B

VIEW A

SEE VIEW A

SEE VIEW B

GRAPHIC TASK 44-21-74-990-954-A01 Seat Electronics Box Figure 86

EFFECTIVITY ALL

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SUBTASK 44-21-74-990-030-A01 J.

Tethered Passenger Control Unit – Basic (TCPU-b) 1)

Location a)

There is a TCPU-b/Cradle Cordreel Assembly (P/N 179118-A01) mounted in the arm of each seat.

b)

For detailed description and illustrated parts list, refer to the TCPU-b/Cradle Cordreel Assembly CMM; Thales document number 44-22-14.Location

2)

Description a)

The TCPU-b provides the passengers the means to control i4000 entertainment services at the seat. The TCPU-b provides a credit card reader and controls all entertainment and PSS services. The TCPU-b also provides the means to channel up and down on the broadcast audio and video channels when in Degraded Function. The credit card reader is on the side of the unit.

b)

The unit is mounted in a cradle-base assembly compatible with aircraft seats. A cord reel mechanism is included in the cradle and provides storage and spring tension for the cord reel. All buttons and indicators are illuminated to enable viewing in all levels of ambient light.

c)

The TPCU-b interfaces to the IFE system via its connection to the Seat Electronics Box (SEB). The communications link between the SEB and the TPCU-b(s) is via a Universal Serial Bus (USB) interface. Power and ground are provided from the SEB for the TPCU-b(s) as well. Figure 73 is a block diagram of the SEB/TPCU-b interconnections.

3)

External Connector (Refer to Figure 71) J1 Universal Serial Bus Main I/O connector

4)

Controls and Indicators (Refer to Figure 87)

5)

Leading particulars, TPCU-b (Refer to Table 46)

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-955-A01 TPCU-b Leading Particulars Table 46 ITEM Dimensions

PARTICULAR Weight Dimensions are in Inches (IN) and Millimeters (mm) in Width (W), Height (H), and Length (L) as follows: 10.55 IN / 268.1 mm L 3.11 IN / 78.9 mm W 2.08 IN / 52.9 mm H

Weight (lbs)

1.00 lbs (0.45 kg) maximum

Power Consumption

3.0 Watts maximum

Power Requirement

32 VDC (+ 12%) (100mV ripple max.)

EFFECTIVITY ALL

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VIEW A J1

SEE VIEW A

GRAPHIC TASK 44-21-74-990-956-A01 Tethered Passenger Control Unit, Basic Figure 87 (Sheet 1 of 2)

EFFECTIVITY ALL

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4 WAY CONTROL

POWER

HOME

VOL UP

GAME, FIRE BUTTON

CHANNEL UP

VOL DOWN

CHANNEL DOWN

ATTENDANT CALL CANCEL

READING LIGHT HELP

MOVING MAP

ATTENDANT CALL FAST FWD

REWIND

BRIGHTNESS

PICTURE IN PICTURE STOP

GAME

GAME, FIRE BUTTON PLAY/PAUSE

GRAPHIC TASK 44-21-74-990-957-A01 Tethered Passenger Control Unit, Basic Figure 87 (Sheet 2 of 2)

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

SUBTASK 44-21-74-990-031-A01 K.

15.4 Inch Smart Video Display Unit (SVDU) 1)

Location a)

There is a 15.4 inch SVDU (P/N 178840-301) mounted in the back of every seat in Business Class.

b)

For detailed description and illustrated parts list, Refer to the applicable Thales CMM: 44-21-72.

2)

Description a)

The SVDU contains a Flat Panel Display with electronics. It receives power, National Television System Committee (NTSC) (M) video, and Ethernet data (MPEG-1/MPEG-2 streaming video/audio) from the LRU specified. Each SVDU has full access to the high-speed data network and uses this access to present video graphics, video-on-demand, audio-on-demand, web material, and to play games.

b)

The passengers navigate the various menu screens of the SVDU using the touch screen feature.

3)

External Connectors (Refer to Figure 88) a)

J1 Main I/O Connector

b)

J2 USB Port Keyboard Interface.

c)

J3 USB Port Mouse Interface.

4)

Control (Refer to Table 47 and Figure 88)

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-958-A01 Control Description Table 47 CONTROL

FUNCTION

Brightness Control 5)

Controls brightness for viewing

Leading Particulars, 15.4 Inch SVDU (Refer to Table 48)

TABLE TASK 44-21-74-990-959-A01 15.4 Inch SVDU Leading Particulars Table 48 ITEM Dimensions

PARTICULAR Dimensions are in Inches (IN) and Millimeters (mm) in Length (L), Height (H), and Width (W) as follows: 1.60 IN L / 41 mm L 15.29 IN W / 388 mm W 10.39 IN H / 264 mm H

Weight

7 pounds (3.18 kg) maximum

Power Dissipation

24 W at 32 VDC

Power Requirement

+18 to +36 VDC

LCD Resolution

1280 x 800

LCD Color Depth [bit]

18

Contrast Ratio (min.) (1)

100:1

Viewing Angle [degree] (without privacy filter)

U/D 35/23

Brightness (min.) [cd/m2] *1

100

L/R 50/50

EFFECTIVITY ALL

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FACE VIEW

BRIGHTNESS CONTROL

J1

J2 J3

BOTTOM VIEW GRAPHIC TASK 44-21-74-990-960-A01 15.4 Inch Smart Video Display Unit Figure 88 EFFECTIVITY ALL

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SUBTASK 44-21-74-990-032-A01 L.

10.4 Inch Integrated Cabin Management Terminal (iCMT) 1)

Location a)

There is a 10.4 iCMT (P/N 177792-803).mounted in the VCC

b)

For detailed description and illustrated parts list, Refer to the applicable Thales CMM: 44-21-27.

2)

Description a)

The iCMT contains a 10.4 Flat Panel Display with electronics.

b)

The iCMT receives power, National Television System Committee (NTSC) (M) video, and Ethernet data (MPEG-1/MPEG-2 streaming video/audio) from the Seat Electronics Box (SEB - IV).

c)

In conjunction with the SEB – IV, each SVDU Gen – II has full access to the high-speed data network and uses this access to present video graphics, video-on-demand, audio-on-demand, web material, and to play games

3)

External Connector 10.4 Inch iCMT (Refer to Figure 89) a)

J1 LCD LVDS Interface Connector

b)

J2 USB LCD RGB Interface Connector

c)

J3 LCD Backlight Power Interface

d)

J6 SEB I/O Interface Connector

e)

J15 Maintenance Connector

4)

Control (Refer to Table 49 and Figure 89)

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-961-A01 Control Description Table 49 CONTROL

FUNCTION

Brightness Control

Controls brightness for viewing

TABLE TASK 44-21-74-990-962-A01 5)

Leading Particulars, 10.4 Inch iCMT (Refer to Table 50) 10.4 Inch iCMT Leading Particulars Table 50 ITEM

Dimensions

PARTICULAR Dimensions are in Inches (IN) and Millimeters (mm) in Length (L), Height (H), and Width (W) as follows: 10.55 IN L / 267.9 mm L .397 IN W / 10.99 mm W 8.36 IN H / 212.3 mm H

Weight

3.9 pounds (1.77 kg) maximum

Power Dissipation

Power Requirement

18W at 32VDC (Backlight ON) 15.5 W at 32VDC (Backlight OFF) 18 to 36 VDC (unregulated) 32 VDC nominal

Surge

40V for 100ms

Ripple

100ms Vp-p Max

Vertical Viewing Angle Horizontal Viewing

Upper (Viewed from Above) = 50º Down (Viewed from Below) = 50º Typical left and typical right (combined) = 80º

EFFECTIVITY ALL

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BRIGHTNESS CONTROL

J1 CONNECTOR J15 MAINTENANCE CONNECTOR J1 CONNECTOR J3 CONNECTOR J6 CONNECTOR J2 CONNECTOR

GRAPHIC TASK 44-21-74-990-963-A01 10.4 Interactive Cabin Management Terminal Figure 89

EFFECTIVITY ALL

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SUBTASK 44-21-74-990-033-A01 M.

8.9 Inch Smart Video Display Unit (SVDU) 1)

2)

3)

Location a)

There is 8.9 inch SVDUs (P/N 178850-201) mounted in the arm of every front row seat in Economy Class.

b)

For detailed description and illustrated parts list, Refer to the applicable Thales CMM: 44-21-71.

Description a)

The SVDU contains a Flat Panel Display with electronics. It receives power, National Television System Committee (NTSC) (M) video, and Ethernet data (MPEG-1/MPEG-2 streaming video/audio) from the LRU specified. Each SVDU has full access to the high-speed data network and uses this access to present video graphics, video-on-demand, audio-on-demand, web material, and to play games.

b)

The passengers navigate the various menu screens of the SVDU using the touch screen feature.

External Connectors (Refer to Figure 90) a)

J1 Main I/O Connector

b)

J2 USB Port Keyboard Interface

c)

J3 USB Port Mouse Interface

d)

J40 Maintenance Port

4)

Control (Refer to Table 51 and Figure 90)

EFFECTIVITY 25864, 25865, 26261, 26265, 2632, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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TABLE TASK 44-21-74-990-964-A01 Control Description Table 51 CONTROL

FUNCTION

Brightness Control 5)

Controls brightness for viewing

Leading Particulars, 8.9 Inch SVDU (Refer to Table 52)

TABLE TASK 44-21-74-990-965-A01 8.9 Inch SVDU Unit Leading Particulars Table 52 ITEM Dimensions

PARTICULAR Dimensions are in Inches (IN) and Millimeters (mm) in Length (L), Height (H), and Width (W) as follows: 1.54 IN L / 39 mm L 9.63 IN W / 245 mm W 6.48 IN H / 164 mm H

Weight

3.3 pounds (1.49 kg) maximum

LCD Resolution

1280 x 800

Power Dissipation

13W at 32VDC for -B01 15W at 32VDC for -201

Power Requirement

32 VDC nominal

EFFECTIVITY 25864, 25865, 26261, 26265, 2632, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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BRIGHTNESS CONTROL

J40

J1

J3 J2

GRAPHIC TASK 44-21-74-990-966-A01 8.9 Inch Smart Video Display Unit Figure 90

EFFECTIVITY 25864, 25865, 26261, 26265, 2632, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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SUBTASK 44-21-74-990-034-A01 N.

8.9 Inch Smart Video Display Unit (SVDU) 1)

Location

2)

a)

There is 8.9 inch SVDUs (P/N 179290-201) mounted in the back of each Economy Class seat.

b)

For detailed description and illustrated parts list, Refer to the applicable Thales CMM: 44-21-73.

Description

3)

a)

The SVDU contains a Flat Panel Display with electronics. It receives power, National Television System Committee (NTSC) (M) video, and Ethernet data (MPEG-1/MPEG-2 streaming video/audio) from the LRU specified. Each SVDU has full access to the high-speed data network and uses this access to present video graphics, video-on-demand, audio-on-demand, web material, and to play games.

b)

The passengers navigate the various menu screens of the SVDU using the touch screen feature.

External Connectors (Refer to Figure 91) a)

J1 Main I/O Connector

b)

J2 USB Port Keyboard Interface

c)

J3 USB Port Mouse Interface

d)

J40 Maintenance Port

4)

Control (Refer to Table 53 and Figure 91)

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-967-A01 Control Description Table 53 CONTROL

FUNCTION

Brightness Control 5)

Controls brightness for viewing

Leading Particulars, 8.9 Inch SVDU (Refer to Table 54)

TABLE TASK 44-21-74-990-968-A01 8.9 Inch SVDU Unit Leading Particulars Table 54 ITEM Dimensions

PARTICULAR Dimensions are in Inches (IN) and Millimeters (mm) in Length (L), Height (H), and Width (W) as follows: 1.45 IN L / 36.83 mm L 9.46 IN W / 240 mm W 5.74 IN H / 146 mm H

Weight

3.3 pounds (1.49 kg) maximum

LCD Resolution

1280 x 800

Power Dissipation

13W at 32VDC for -B01 15W at 32VDC for -201

Power Requirement

32 VDC nominal

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

BRIGHTNESS BUTTONS

J3 J2 J1 J40

GRAPHIC TASK 44-21-74-990-969-A01 8.9 Inch Smart Video Display Unit Figure 91 EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

SUBTASK 44-21-74-990-035-A01 O.

Overhead Electronics Box (OEB) 1)

Location

2)

a)

The OEBs (P/N 179130-101) are located throughout the overhead area of the cabin.

b)

For detailed description and illustrated parts list, refer to the OEB CMM; Thales document number 44-22-49.

Description The OEB is a microprocessor based LRU that is used to illuminate and extinguish a specific reading light (three each) and attendant call light (one each) when commanded by the PCU-PSS or TDPCU.

3)

External Connectors (Refer to Figure 92) a)

J1 AC Input from chain RS-485

b)

J2 AC Output to chain RS-485

c)

J3 Is used to illuminate or extinguish up to three reading lights and one row call light.

4)

Leading Particulars OEB (Refer to Table 55)

EFFECTIVITY ALL

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TABLE TASK 44-21-74-990-970-A01 OEB Leading Particulars Table 55 ITEM Dimensions

PARTICULAR Dimensions are in Inches, Width (W), Height (H), and Length (L) as follows: 1.700 IN W 3.450 IN H 3.080 IN L

Weight

0.7 lbs maximum

Power Dissipation

60 Watts maximum

Power Requirement

115 VAC 400 Hz

Cooling Requirements

Convection

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

J1

J3

J2

GRAPHIC TASK 44-21-74-990-971-A01 Overhead Electronics Box Figure 92 EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

TASK 44-21-74-990-972-A01 5.

System Wiring

SUBTASK 44-21-74-990-036-A01 A.

VCC Wiring (Retro Fit) (Refer to Figure 93)

EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-973-A01 VCC Wiring Figure 93 (Sheet 1 of 18)

EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-974-A01 VCC Wiring Figure 93 (Sheet 2 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-975-A01 VCC Wiring Figure 93 (Sheet 3 of 18)

EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-976-A01 VCC Wiring Figure 93 (Sheet 4 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-977-A01 VCC Wiring Figure 93 (Sheet 5 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-978-A01 VCC Wiring Figure 93 (Sheet 6 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-979-A01 VCC Wiring Figure 93 (Sheet 7 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-980-A01 VCC Wiring Figure 93 (Sheet 8 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-981-A01 VCC Wiring Figure 93 (Sheet 9 of 18)

EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-982-A01 VCC Wiring Figure 93 (Sheet 10 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-983-A01 VCC Wiring Figure 93 (Sheet 11 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-984-A01 VCC Wiring Figure 93 (Sheet 12 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-985-A01 VCC Wiring Figure 93 (Sheet 13 of 18)

EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-986-A01 VCC Wiring Figure 93 (Sheet 14 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-987-A01 VCC Wiring Figure 93 (Sheet 15 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-988-A01 VCC Wiring Figure 93 (Sheet 16 of 18)

EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-989-A01 VCC Wiring Figure 93 (Sheet 17 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-990-A01 VCC Wiring Figure 93 (Sheet 18 of 18) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

Page 198 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

SUBTASK 44-21-74-990-037-A01 B.

System Wiring (Retro Fit) (Refer to Figure 94)

EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-991-A01 System Wiring Figure 94 (Sheet 1 of 14)

EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-992-A01 System Wiring Figure 94 (Sheet 2 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

Page 201 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-993-A01 System Wiring Figure 94 (Sheet 3 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

Page 202 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-994-A01 System Wiring Figure 94 (Sheet 4 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

Page 203 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-995-A01 System Wiring Figure 94 (Sheet 5 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

Page 204 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-996-A01 System Wiring Figure 94 (Sheet 6 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

Page 205 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-997-A01 System Wiring Figure 94 (Sheet 7 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

Page 206 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-998-A01 System Wiring Figure 94 (Sheet 8 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

Page 207 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-990-999-A01 System Wiring Figure 94 (Sheet 9 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

Page 208 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-991-801-A01 System Wiring Figure 94 (Sheet 10 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

Page 209 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-991-802-A01 System Wiring Figure 94 (Sheet 11 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-991-803-A01 System Wiring Figure 94 (Sheet 12 of 14)

EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-991-804-A01 System Wiring Figure 94 (Sheet 13 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

Page 212 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

GRAPHIC TASK 44-21-74-991-805-A01 System Wiring Figure 94 (Sheet 14 of 14) EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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This Page is Intentionally Left Blank

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

COMPONENT LOCATIONS SUBJECT

PAGE

TASK 44-21-74-991-806-A01 1.

General...................................................................................................................1002

TASK 44-21-74-991-807-A01 2.

System Equipment Lists .........................................................................................1002

TASK 44-21-74-991-809-A01 3.

TopSeries™ i4000 System Component Locations..................................................1004

SUBTASK 44-21-74-991-809-A01 A.

General...................................................................................................................1004

B.

Video Control Center ..............................................................................................1004

C.

Seat Group Components ........................................................................................1004

D.

Circuit Breakers ......................................................................................................1005

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

COMPONENT LOCATIONS TASK 44-21-74-991-806-A01 1.

General The Thales Avionics, Incorporated TopSeries™ i4000 System entertainment system for the LAN B767 is made up of components that are located in the Video Control Center (VCC), in each of the passenger seat groups, and in the bulkheads and sidewalls of the aircraft cabin.

TASK 44-21-74-991-807-A01 2.

System Equipment List

SUBTASK 44-21-74-991-808-A01 System Equipment List and Applicable Component Maintenance Manuals Table 1001 (Sheet 1 of 3) NOTE:

Retrofit aircraft have OEBs P/N 179130-101 instead of SEBs in seating areas.

ACRONYM

NOMENCLATURE

PART NUMBER

QUANTITY

COMPONENT MAINTENANCE MANUAL

VIDEO CONTROL CENTER COMPONENTS iCMT

Interactive Cabin Management Terminal

177792-803

1

44-21-27

SEB

Seat Electronics Box

177745-106

1

44-21-42

DSU-AM6-12

Digital Server Unit-AM6-12

177900-103

1

44-20-29

AVC

Audio/Video Controller

177716-103

1

44-20-26

DSU-D2

Digital Server Unit-D2

177892-102

4

44-20-35

ESU-G

Ethernet Switching Unit-Gigabit

178568-102

1

44-21-43

VCC Rack

Video Control Center Rack Assembly

179231-101

1

44-21-70

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

System Equipment List and Applicable Component Maintenance Manuals Table 1001 (Sheet 2 of 3) ACRONYM

NOMENCLATURE

PART NUMBER

QUANTITY

COMPONENT MAINTENANCE MANUAL

SEAT GROUP COMPONENTS, BUSINESS CLASS SEB

Seat Electronics Box

177745-106

15

44-21-42

TPCU-b

Tethered Passenger Control Unit - Basic

179118-A01

30

44-22-14

15.4 SVDUIIW

Smart Video Display Unit, 15.4 Inch Wide Screen

178840-301

30

44-21-72

AJM

Integrated Noise Canceling Audio Jack Module

178921-102

30

N/A

SEAT GROUP COMPONENTS, ECONOMY CLASS SEB

Seat Electronics Box

176745-106

87

44-21-42

TPCU-b

Tethered Passenger Control Unit - Basic

179118-A01

191

44-22-14

8.9 SVDUIIW-SB

Smart Video Display Unit, 8.9 Inch, Wide Screen, Seat Back

179290-201

188

44-21-73

8.9 SVDU-IIW

Smart Video Display Unit, 8.9 Inch, Wide Screen, Arm Mount

178850-201

3

44-21-71

AJM

Audio Jack Module

170777-25

191

23-39-03

CABIN DISTRIBUTION COMPONENTS MCU

Master Control Unit

177922-103

4

25-20-21

PM

Programming Module

177923-601

1

25-20-30

PM

Programming Module

177923-602

3

25-20-30

ADB

Area Distribution Box

177730-106

5

44-21-51

FDB

Floor Disconnect Box

172781-01

5

N/A

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

System Equipment List and Applicable Component Maintenance Manuals Table 1001 (Sheet 3 of 3) ACRONYM

NOMENCLATURE

PART NUMBER

QUANTITY

COMPONENT MAINTENANCE MANUAL

CABIN DISTRIBUTION COMPONENTS (CONTINUED) TU

Tapping Unit

177832-101

5

44-20-30

OEB

Overhead Electronics Box

179130-101

98

44-22-49

EFFECTIVITY ALL

44-21-74

Page 1004 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

TASK 44-21-74-991-809-A01 3.

TopSeries™ i4000 System Component Locations A.

General 1)

The i4000 system for aircraft 34626, 34628, 34629, 35229, 35230, 35231, 35696, 35697, 35698, 36710, 36711, 36712 were linefit installed at the Boeing Aircraft Company 767 Aircraft assembly line. Accordingly, the location of the majority of the i4000 system components on these aircraft was determined by Boeing. For locations of the i4000 system components that are not shown herein, refer to the Boeing 767 AMM.

B.

C.

2)

The location of all i4000 LRUs for retrofit aircraft 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229 are shown in this section. For parts breakdown information of the LRUs, refer to the applicable CMM per Table 101.

3)

The location and parts breakdown information for other components of the i4000 system for retrofit aircraft 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229 are shown in the Thales Avionics LAN 767 Aircraft i4000 System Illustrated Parts Catalog (44-22-12).

Video Control Center 1)

-The VCC assembly is located in the F2 galley (Refer to Figure 1002).

2)

Locations of the LRUs and control switches installed in the VCC assembly are shown in Figure 1001.

Seat Group Components 1)

Business Class a)

2)

An interconnect diagram of the Business Class seats is provided in Figure 1002.

Economy Class a)

An interconnect diagram of the Economy Class seats is provided in Figure 1003.

EFFECTIVITY ALL

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Page 1005 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

D.

Circuit Breakers 1)

For locations of the i4000 system circuit breakers for linefit aircraft 34626, 34628, 34629, 35229, 35230, 35231, 35696, 35697, 35698, 36710, 36711, 36712 refer to the Boeing 767 AMM.

2)

The location of the i4000 system circuit breakers for retrofit aircraft 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229 are shown in Figure 1004.

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

VIDEO CONTROL CENTER

ICMT CONTROL PANEL (SEE SHEETS 2 AND 3)

VCC RACK ASSEMBLY (SEE SHEET 5)

GRAPHIC TASK 44-21-74-991-810-A01 Video Control Center LRU Locations Figure 1001 (Sheet 1 of 5)

EFFECTIVITY ALL

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Page 1007 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

MASTER IFE SWITCH

IFE FAN INOP INDICATOR

PC POWER SWITCH

HEAD END POWER SWITCH

SEAT END POWER SWITCH

USB PORT AUDIO JACK MODULE

DATA LOADER PORTS (3X)

AC OUTLET UNIT

VIDEO CONTROL CENTER CONTROL PANEL

GRAPHIC TASK 44-21-74-991-811-A01 Video Control Center LRU Locations, Linefit Figure 1001 (Sheet 2 of 5)

EFFECTIVITY 34626, 34628, 34629, 35229, 35230, 35231, 35696, 35697, 35698, 36710, 36711, 36712

44-21-74

Page 1008 Feb 28/09

THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

IFE FAN INOP INDICATOR MASTER IFE POWER SWITCH HEAD END POWER SWITCH

INOP AUDIO JACK MODULE

USB PORT

DATA LOADER PORT (3X) AC OUTLET UNIT

PC POWER SWITCH

VIDEO CONTROL CENTER CONTROL PANEL GRAPHIC TASK 44-21-74-991-812-A01 Video Control Center LRU Locations, Retrofit Figure 1001 (Sheet 3 of 5)

EFFECTIVITY 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

44-21-74

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SEB FOR THE ICMT

ICMT

VIDEO CONTROL CENTER CONTROL PANEL (BACK VIEW) GRAPHIC TASK 44-21-74-991-813-A01 Video Control Center LRU Locations Figure 1001 (Sheet 4 of 5)

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DSU-D2

VCC RACK ASSEMBLY

DSU-D2

ESU-G

DSU-AM6-12 AVC

GRAPHIC TASK 44-21-74-991-814-A01 Video Control Center LRU Locations Figure 1001 (Sheet 5 of 5)

EFFECTIVITY ALL

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This page is intentionally left blank.

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GRAPHIC TASK 44-21-74-991-815-A01 Business Class Seat Interconnect Diagram Figure 1002 (Sheet 1 of 3)

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GRAPHIC TASK 44-21-74-991-816-A01 Business Class Seat Interconnect Diagram Figure 1002 (Sheet 2 of 3)

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GRAPHIC TASK 44-21-74-991-817-A01 Business Class Seat Interconnect Diagram Figure 1002 (Sheet 3 of 3)

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GRAPHIC TASK 44-21-74-991-818-A01 Economy Class Seat Interconnect Diagram Figure 1003 (Sheet 1 of 9)

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GRAPHIC TASK 44-21-74-991-819-A01 Economy Class Seat Interconnect Diagram Figure 1003 (Sheet 2 of 9)

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GRAPHIC TASK 44-21-74-991-820-A01 Economy Class Seat Interconnect Diagram Figure 1003 (Sheet 3 of 9)

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GRAPHIC TASK 44-21-74-991-821-A01 Economy Class Seat Interconnect Diagram Figure 1003 (Sheet 4 of 9)

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GRAPHIC TASK 44-21-74-991-822-A01 Economy Class Seat Interconnect Diagram Figure 1003 (Sheet 5 of 9)

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GRAPHIC TASK 44-21-74-991-823-A01 Economy Class Seat Interconnect Diagram Figure 1003 (Sheet 6 of 9)

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GRAPHIC TASK 44-21-74-991-824-A01 Economy Class Seat Interconnect Diagram Figure 1003 (Sheet 7 of 9)

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GRAPHIC TASK 44-21-74-991-825-A01 Economy Class Seat Interconnect Diagram Figure 1003 (Sheet 8 of 9)

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GRAPHIC TASK 44-21-74-991-826-A01 Economy Class Seat Interconnect Diagram, Retrofit Figure 1003 (Sheet 9 of 9)

EFFECTIVITY

25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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P37 PANEL

GRAPHIC TASK 44-21-74-991-827-A01 Circuit Breaker Locations, Retrofit Figure 1004 (Sheet 1 of 4)

EFFECTIVITY

25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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P36 PANEL

GRAPHIC TASK 44-21-74-991-828-A01 Circuit Breaker Locations Figure 1004 (Sheet 2 of 4)

EFFECTIVITY

25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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P11-6 PANEL

GRAPHIC TASK 44-21-74-991-829-A01 Circuit Breaker Locations Figure 1004 (Sheet 3 of 4)

EFFECTIVITY

25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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P33 PANEL

2.5

7.5

7.5

7.5

M

7.5

2.5

PASS ENTERTAINMENT

GRAPHIC TASK 44-21-74-991-830-A01 Circuit Breaker Locations Figure 1004 (Sheet 4 of 4)

EFFECTIVITY

25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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MAINTENANCE PRACTICES SUBJECT

PAGE

TASK 44-21-74-991-831-A01 1.

General...................................................................................................................2004

SUBTASK 44-21-74-470-001-A01 H. System Power-Up Procedure............................................................................2007 SUBTASK 44-21-74-470-002-A01 I. PDL Set Up Procedure .......................................................................................2007 TASK 44-21-74-470-801-A01 2.

Phase 1 Software Download Procedure .................................................................2008

SUBTASK 44-21-74-990-038-A01 A. Required Equipment .........................................................................................2008 SUBTASK 44-21-74-470-003-A01 B. Procedure .........................................................................................................2008 SUBTASK 44-21-74-990-039-A01 C. System Software List, Line fit ............................................................................2012 SUBTASK 44-21-74-990-040-A01 D. System Software List, Retro fit ..........................................................................2015 TASK 44-21-74-470-802-A01 3.

Phase 2 Software Download Procedures ...............................................................2018

SUBTASK 44-21-74-470-004-A01 A. Phase 2 Software Download to the DSU-AM6-12 .............................................2018 SUBTASK 44-21-74-470-005-A01 B. Phase 2 Software Download to the AVC ...........................................................2019

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SUBJECT

PAGE

SUBTASK 44-21-74-470-006-A01 C. Phase 2 Software Download to the ESU-G ...................................................... 2020 SUBTASK 44-21-74-470-007-A01 D. Phase 2 Software Download to the ADBs......................................................... 2021 SUBTASK 44-21-74-470-008-A01 E. Phase 2 Software Download to the DSU-D2s ................................................... 2022 SUBTASK 44-21-74-470-009-A01 F. IP Sequencing .................................................................................................. 2022 SUB-TASK 44-21-74-470-803-A01 G. OEB Address Assignment ................................................................................ 2024 SUBTASK 44-21-74-470-010-A01 H. Phase 2 Software Download to the SEBs......................................................... 2024 SUBTASK 44-21-74-470-011-A01 I. Phase 2 Software Download to the SVDU-IIWs ................................................. 2025 SUBTASK 44-21-74-470-012-A01 J. Phase 2 Software Download to TPCU-Bs ......................................................... 2027 SUBTASK 44-21-74-470-013-A01 K. Phase Two Software Download to iCMT........................................................... 2028 SUBTASK 44-21-74-470-014-A01 L. Content Loading Procedure .............................................................................. 2029 SUBTASK 44-21-74-720-001-A01 M. Configuration Check Procedure ................................................................... 2031

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SUBJECT

PAGE

SUBTASK 44-21-74-470-015-A01 N. PDL Shutdown Procedure.................................................................................2032 SUBTASK 44-21-74-470-016-A01 O. Reboot Entire IFE System Procedure ...............................................................2032

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TASK 44-21-74-991-831-A01 1.

General A.

This section contains software download procedures, functional test procedures, and content loading procedures for the TopSeries™ i4000 System.

B.

For Return to Service (RTS) following LRU replacement, or any compromise to the TopSeries™ i4000 System, perform the System Functional Test procedure (paragraph 4).

C.

The procedures in this section are presented in logical order and may be performed sequentially, however, each procedure is written to stand alone.

NOTE: For illustrations of each iCMT screen display described throughout this section, refer to the DESCRIPTION AND OPERATION section of this manual. D.

Software Download Description 1)

Every effort has been made to permit 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. Depending on the specific configuration of the aircraft, software for the system can be provided on a variety of storage media including the following: a)

CD ROM

b)

USB Connection

2)

Software is often provided on multiple media, each of which must be loaded into the system.

3)

Software download of the system is divided into the following two phases: a)

Phase 1 Download Installs the proper configuration of software into the download server.

b)

Phase 2 Download Distributes the software to the required LRUs.

4)

Phase 1 Download Description a)

Phase 1 download process consists of loading selected software components from the distribution media to the system download server.

b)

The Phase 1 download process is used to declare the desired software configuration for the aircraft. All subsequent maintenance actions

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(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 a “desired configuration” database based on the most recent software loaded in this manner. c)

5)

Maintenance personnel are provided with a Phase 1 inventory screen which identifies the software components (by software part number and LRU type) which are in the systems “desired configuration” list. This list should be verified against the configuration documentation maintained by the airline. Extra components should be deleted.

Phase 2 Download Description a)

The Phase 2 download process uses the “desired 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.

b)

When a download is initiated by maintenance personnel, all aircraft loadable software present in the “desired configuration” list for the selected LRU/LRU type is to be 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.

c)

Software download is only required when the software (including database) is changed or when an LRU is replaced. The system will not download a software component if it is already present in the LRU.

d)

System operation has a certain level of hierarchy with respect to maintenance processes including download. Because of this, components should be configured in the following order:

e)

(1)

Head End Components

(2)

Distribution Components

(3)

Seat Components

It is also important that the proper database be loaded into the ADBs before an IP sequencing operation is performed.

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f)

g)

For i4000 system, the order should be as follows: (1)

DSU AM6-12

(2)

AVC

(3)

ESU-G

(4)

ADB

(5)

DSU-D2

(6)

SEB

(7)

SVDU

(8)

TPCU-b

(9)

iCMT

After a Phase 2 download is performed, the configuration information available to Configuration Check is automatically updated to reflect changes which have occurred in the system.

E.

Software is loaded to the TopSeries™ LRU’s in a two-phase process, in which the code is first uploaded from the CD-ROM on the PDL to the DSU AM6-12 hard disk drive and then downloaded to individual LRU types or individual LRU’s.

F.

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 or incompatible files on an LRU type that may prevent further downloads to correct the problem.

G.

IP Sequencing 1)

Description a)

In the i4000 IFE system, the SEBs do not have any hard-coded or hardwired addressing 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.

b)

Each Ethernet-capable LRU in the system contains a configuration data file that defines the “map” of all of the LRUs. The SEB data includes: (1)

The SEBs position within the string where the SEB resides.

(2)

The ADB and port where the SEB is connected.

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(3)

The seat-group number of that position and the Ethernet address of that seat-group.

c)

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 LRU’s.

d)

When IP Sequencing starts, the ADBs command all of the SEBs to set their output switches to the OFF position. The ADB can then communicate with only the first SEB on each string; 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.

SUBTASK 44-21-74-470-001-A01 H.

System Power-Up Procedure 1)

Power up i4000 system. Make sure all IFE Circuit Breakers (CBs) are closed.

2)

Make sure aircraft ventilation cooling is on.

3)

Wait 10 minutes.

4)

At iCMT, verify Welcome Screen is displayed.

SUBTASK 44-21-74-470-002-A01 I.

PDL Set Up Procedure 1)

Connect RJ-45 Ethernet Cable from PDL to Video Control Center (VCC) Rack RJ-45 Coupler, Port 3.

2)

Turn PDL on and wait for system to display desktop.

3)

Insert latest LAN 767 TopSeries™ i4000 System Software CD-ROM for applicable configuration into PDL CD-ROM Drive (Refer to Tables 2001 and 2002).

4)

At Password prompt, type iSeries, then click Enter.

5)

Double-click on Blue Internet Explorer Icon labeled i-Series.

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Verify LAN Welcome Screen is displayed with Entertainment and Maintenance Buttons. TASK 44-21-74-470-801-A01 2.

Phase 1 Software Download Procedure CAUTION: WHILE PERFORMING THIS PROCEDURE, ENSURE THAT

AIRCRAFT POWER IS NOT INTERRUPTED. PLACE IFE WORKIN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. CAUTION: FAILURE TO COMPLY WITH THE DOCUMENTED SOFTWARE DOWNLOAD PROCEDURE COULD RESULT IN SEBs BEING RENDERED INOPERATIVE, AND THE ONLY CORRECTIVE ACTION WOULD BE TO REPLACE EACH LRU. CAUTION: IN ORDER FOR MMAP SOFTWARE AND CONTENT MEDIA TO FUNCTION CORRECTLY, MAKE SURE PDL CONTAINS LATEST HARDWARE CONFIGURATION. SUBTASK 44-21-74-990-038-A01 A.

Required Equipment 1)

PDL containing latest Hardware configuration

2)

Straight Ethernet Cable with RJ-45 Connector

3)

LAN B767 i4000 TopSeries™ System Software, CD-ROM Media 620130-711-15A (for 34626, 34628, 34629, 35229, 35230, 35231, 35696, 35697, 35698, 36710, 36711, 36712) or 620130-712-11-A (for 25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229)

SUBTASK 44-21-74-470-003-A01 B.

Procedure 1)

The Phase One procedure uploads software from the CD-ROM on the PDL to the DSU AM6-12 hard disk drive. The software can be uploaded either by software package or by file.

2)

Old software components left on the Phase 1 directory may be incompatible and cause SEB corruption.

3)

To prevent leaving old software on the Phase 1 list, it is recommended that a deletion of the old Phase 1 list be performed.

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4)

At PDL, from LAN Welcome Screen, click Maintenance. Verify Maintenance Access Screen is displayed.

5)

At PDL, from i-Series Maintenance Access Screen, type 842537 on Keypad, then click Enter. Verify Maintenance Screen is displayed.

6)

At PDL, from Maintenance Screen, click Download. Verify Download Screen is displayed.

7)

At PDL, from Download Screen, click Update Software. Verify Current Software Configuration Screen is displayed.

8)

At PDL, from Current Software Configuration Screen, click DELETE Button. Verify Software Removal Screen is displayed.

9)

At Software Removal Screen, click all files listed by clicking box provided at left side of File Description. Verify a check mark appears in box next to each listed file at left side of File Description.

10)

Click DELETE Button. Verify that, after a few seconds, Software Removal List is completely empty and no files are listed.

11)

At Software Removal Screen, click DONE Button. Verify Current Software Configuration Screen is displayed and list is completely empty.

12)

At PDL, from Current Software Configuration Screen, click UPDATE. Verify Source Selection Screen is displayed.

13)

At PDL, from Source Selection Screen, click CD-ROM source and click By File button or By Package button. a)

If By File button was clicked, verify Software Load By File-CD Screen is displayed with all files listed containing a selection box next to each file.

b)

If By Package button was clicked, verify Software Load By Package-CD Screen is displayed with single box and file.

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14)

If By File Button was clicked, scroll down the screen, and click box next to each listed file, then click UPDATE Button. a)

Verify a check mark appears in box next to each listed file.

b)

Verify Progress Indication Bar is displayed. NOTE:

15)

If By Package Button was clicked, click single selection box shown, then click UPDATE Button. a)

Verify a check mark appears in single selection box.

b)

Verify Progress Indication Bar is displayed. NOTE:

16)

17)

This may take approximately 7 to 10 minutes.

This may take approximately 7 to 10 minutes.

When download is complete and Progress Bar indicates 100%, click OK. a)

Depending on which Button was clicked, verify Software Load By File or Package CD Screen is displayed.

b)

Verify OK status is displayed in Status Bar for files loaded.

Click DONE. a)

Verify Current Software Configuration Screen is displayed.

b)

Verify correct software elements are loaded on DSU AM6-12 per Table 2001 and 2002.

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18)

Click DONE. Verify Download Screen is displayed.

19)

Remove TopSeries™ i4000 System Software CD-ROM from PDL CD-ROM Drive.

20)

Click DONE.

21)

End of Phase 1 Download.

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SUBTASK 44-21-74-990-039-A01 C.

System Software, List Line fit (Refer to Table 2001)

SUBTASK 44-21-74-991-832-A01 System Software List for Linefit Aircraft Table 2001 (Sheet 1 of 3) SOFTWARE DESCRIPTION

DOWNLOAD SCREEN PART NUMBER

LAN B767 LINEFIT SOFTWARE - 620130-711-15-A LAN 767 CONFIG

622406-08

AVC CORE 1

620472-55

AVC CORE 2

620752-64

AVC BASIC APP

620482-10

AVC D/L LINUX KERNEL

620476-02

AVC CABIN GUI

620934-11

DSU CORE 1

620302-62

DSU CORE 2

620422-63

DSU BASIC APP

620312-10

DSU CABIN GUI

620936-12

DSU MMAP CODE

620812-28

DSU LAN MMAP CONFIG

622616-02

DSU MMAP DATA

620814-06

DSU MMAP IMAGES

620815-04

DSU VICL CORE 1

620362-38

DSU VICL CORE 2

620432-38

DSU VICL MMAP LAUNCHER

620892-09

ADB CORE 1

620583-48

ADB CORE 2

620762-48

ADB-106 D/L LINUX KERNEL

620580-03

ADB SPI-WB APP

620600-02

EFFECTIVITY 34626, 34628, 34629, 35229, 35230, 35231, 35696, 35697, 35698, 36710, 36711, 36712

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System Software List for Linefit Aircraft Table 2001 (Sheet 2 of 3) SOFTWARE DESCRIPTION

DOWNLOAD SCREEN PART NUMBER

LAN B767 LINEFIT SOFTWARE - 620130-711-15-A (CONTINUED) SEB CORE 1

620663-71

SEB CORE 2

620772-72

SEB D/L LINUX KERNEL

620688-06

SEB2 D/L DRIVERS

620690-02

SEB RF APP

620676-07

SEB2 SPI APP

620680-02

SVDU-405 D/L RFS

620544-10

SVDU-405 LAN PAX GUI2

622626-01

SVDU-405 GAME MOUNT

620910-06

SVDU-405 CONNECTIVITY APP

620938-13

SVDU-405 GAP

620424-13

SVDU-405 RFS APPS

620716-07

SVDU-405W CORE 1

620558-17

SVDU-405W CORE 2

620560-37

SVDU-405W D/L LINUX KERNEL

620540-04

SVDU-W D/L Drivers

620534-02

ICMT-405 CORE 1

620404-20

ICMT-405 CORE 2

620406-21

ICMT-405 D/L RFS

620408-05

ICMT-405 CABIN GUI

620940-19

ICMT-405 CONNECTIVITY APP

620976-04

ICMT-405 GAP

620420-14

ICMT-405 RFS APPS

620724-07

ICMT-405 LAN767-LF CABIN GUI C

622416-02

DSU-D2 CORE 1

620822-48

EFFECTIVITY 34626, 34628, 34629, 35229, 35230, 35231, 35696, 35697, 35698, 36710, 36711, 36712

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System Software List for Linefit Aircraft Table 2001 (Sheet 3 of 3) SOFTWARE DESCRIPTION

DOWNLOAD SCREEN PART NUMBER

LAN B767 LINEFIT SOFTWARE - 620130-711-12-A (CONTINUED) DSU-D2 CORE 2

620824-54

DSU-D2 D/L RFS

620828-04

DSU-D2 LAN PAX GUI2

622624-03

DSU-D2 CONNECTIVITY APP

620916-08

DSU-D2 GAP

620714-20

DSU-D2 RFS APPS

620720-09

ESUG CORE 1

620434-10

TPCU CORE 1

620220-12

TPCU CORE 2

620224-13

TPCU LAN CONFIG

622410-02

EFFECTIVITY 34626, 34628, 34629, 35229, 35230, 35231, 35696, 35697, 35698, 36710, 36711, 36712

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SUBTASK 44-21-74-990-040-A01 D.

System Software List, Retro fit (Refer to Table 2002)

SUBTASK 44-21-74-991-833-A01 System Software List for Retrofit Aircraft Table 2002 (Sheet 1 of 3) SOFTWARE DESCRIPTION

DOWNLOAD SCREEN PART NUMBER

LAN B767 RETROFIT SOFTWARE - 620130-712-11-A LAN 767-R CONFIG

622407-07

AVC CORE1

620472-55

AVC CORE2

620752-64

AVC LAN BASIC APP

622636-02

AVC D/L LINUX KERNEL

620476-02

AVC GENERIC CABIN GUI

620934-11

DSU CORE1

620302-62

DSU CORE2

620422-63

DSU BASIC APP

620312-10

DSU GENERIC CABIN GUI

620936-12

DSU MMAP CODE

620812-28

DSU LAN 767-R MMAP CONFIG

622638-01

DSU MMAP DATA

620814-06

DSU MMAP IMAGES

620815-04

DSU VICL CORE1

620362-38

DSU VICL CORE2

620432-38

DSU VICL MMAP LAUNCHER

620892-09

ADB CORE1

620583-48

ADB CORE2

620762-48

ADB-106 D/L LINUX KERNEL

620580-03

ADB SPI-WB APP

620600-02

EFFECTIVITY

25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

System Software List for Retrofit Aircraft Table 2002 (Sheet 2 of 3) SOFTWARE DESCRIPTION

DOWNLOAD SCREEN PART NUMBER

LAN B767 RETROFIT SOFTWARE - 620130-712-11-A (CONTINUED) SEB CORE 1

620663-71

SEB CORE 2

620772-72

SEB D/L LINUX KERNEL

620688-06

SEB2 D/L DRIVERS

620690-02

SEB RF APP

620676-07

SEB2 SPI APP

620680-02

SVDU-405 D/L RFS

620544-10

SVDU-W D/L DRIVERS

620534-02

SVDU-405 LAN PAX GUI2

622626-01

SVDU-405 GAME MOUNT

620910-06

SVDU-405 CONNECTIVITY APP

620938-13

SVDU-405 GAP

620424-13

SVDU-RFS APPS

620716-07

SVDU-405W CORE 1

620558-17

SVDU-405W CORE 2

620560-37

SVDU-405W D/L LINUX KERNEL

620540-04

ICMT-405 CORE 1

620404-20

ICMT-405 CORE 2

620406-21

ICMT-405 D/L RFS

620408-05

ICMT CABIN GUI

620940-19

ICMT-405 CONNECTIVITY APP

620976-04

ICMT-405 GAP

620420-14

ICMT-405 RFS APPS

620724-07

ICMT-405 LAN767R CABIN GUI

622414-02

EFFECTIVITY

25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

System Software List for Retrofit Aircraft Table 2002 (Sheet 3 of 3) SOFTWARE DESCRIPTION

DOWNLOAD SCREEN PART NUMBER

LAN B767 RETROFIT SOFTWARE - 620130-712-11-A (CONTINUED) DSU-D2 CORE1

620822-48

DSU-D2 CORE2

620824-54

DSU-D2 D/L RFS

620828-04

DSU-D2 LAN PAX GUI2

622624-03

DSU-D2 CONNECTIVITY APP

620916-08

DSU-D2 GAP

620714-20

DSU-D2 RFS APPS

620720-09

ESU-G CORE1

620434-10

TPCU CORE 1

620220-12

TPCU CORE 2

620224-13

TPCU CONFIG

622410-02

EFFECTIVITY

25864, 25865, 26261, 26265, 26327, 26329, 27597, 27613, 27615, 28206, 29227, 29228, 29229

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

TASK 44-21-74-470-802-A01 3.

Phase 2 Software Download Procedures The Phase 2 procedure is a software download from the DSU AM6-12 hard disk drive to selected LRU processors. The procedures for downloading to the DSU AM6-12, AVC, ESUG, ADBs, DSU-D2s, IP Sequencing, SEBs, SVDUs, TPCU-Bs, and iCMT are presented as separate procedures.

SUBTASK 44-21-74-470-004-A01 A.

Phase 2 Software Download to the DSU-AM6-12 CAUTION: WHILE PERFORMING THIS PROCEDURE, ENSURE THAT

AIRCRAFT POWER IS NOT INTERRUPTED. PLACE IFE WORKIN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. NOTE: The Basic App file is 35MB; it takes approximately 15 minutes for this procedure 1)

At PDL (or iCMT), from Maintenance Screen, click Download. Verify Download Screen is displayed.

2)

From Download Screen, click Download LRU. Verify LRU Load Screen is displayed with old software part numbers.

3)

From LRU Load Screen, click DSU and ALL SELECTED LRU’s. a)

Verify Download Phase 2 Screen with a Progress Bar is displayed.

b)

Wait approximately 30 minutes.

4)

When Progress Bar indicates 100%, click OK. Verify System Config-Detail Screen is displayed.

5)

At System Config-Detail Screen: Verify files were downloaded to the DSU-AM6-12 per Table 2001 or 2002. NOTE:

6)

Verify ICMT-405 LAN767R Cabin GUI, part number 622414-02 line fit, 622414-02 for retro fit airplanes are present.

At System Config-Detail Screen, click CC Menu. Verify Configuration Check Screen is displayed.

EFFECTIVITY ALL

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7)

At Configuration Check Screen, click CANCEL. Verify Maintenance Screen is displayed.

SUBTASK 44-21-74-470-005-A01 B.

Phase 2 Software Download to the AVC CAUTION: WHILE PERFORMING THIS PROCEDURE, ENSURE THAT

AIRCRAFT POWER IS NOT INTERRUPTED. PLACE IFE WORKIN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. 1)

At PDL (or iCMT), from Maintenance Screen, click Download. Verify Download Screen is displayed.

2)

From Download Screen, click Download LRU. Verify LRU Load Screen is displayed.

3)

From LRU Load Screen, click AVC and ALL SELECTED LRU’s. a)

Verify Download Phase 2 Screen with a Progress Bar is displayed.

b)

Verify Status Bar at bottom of Screen disappears.

c)

After 10 to 15 minutes, verify Status Bar at bottom of Screen reappears.

4)

When Progress Bar indicates 100%, click OK. Verify System Config-Detail Screen is displayed. At System Config-Detail Screen:

5)

Verify files were downloaded to the AVC per Table 2001 or 2002.

6)

At System Config Detail Screen, click CC Menu. Verify Configuration Check Screen is displayed.

7)

At Configuration Check Screen, click CANCEL. Verify Maintenance Screen is displayed.

SUBTASK 44-21-74-470-006-A01 C.

Phase 2 Software Download to the ESU-G

EFFECTIVITY ALL

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CAUTION: WHILE PERFORMING THIS PROCEDURE, ENSURE THAT

AIRCRAFT POWER IS NOT INTERRUPTED. PLACE IFE WORKIN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. 1)

At PDL (or iCMT), from Maintenance Screen, click Download. Verify Download Screen is displayed.

2)

From Download Screen, click Download LRU. Verify LRU Load Screen is displayed.

3)

From LRU Load Screen, click ESU and ALL SELECTED LRU’s. a)

Verify Download Phase 2 Screen with a Progress Bar is displayed.

b)

Wait approximately 2 to 3 minutes.

4)

When Progress Bar indicates 100%, click OK. Verify System Config-Detail Screen is displayed.

5)

At System Config-Detail Screen: Verify files were downloaded to the ESU per Table 2001 or 2002.

6)

At System Config Detail Screen, click CC Menu. Verify Configuration Check Screen is displayed.

7)

At Configuration Check Screen, click CANCEL. Verify Maintenance Screen is displayed.

EFFECTIVITY ALL

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SUBTASK 44-21-74-470-007-A01 D.

Phase 2 Software Download to the ADBs CAUTION: WHILE PERFORMING THIS PROCEDURE, ENSURE THAT

AIRCRAFT POWER IS NOT INTERRUPTED. PLACE IFE WORKIN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. 1)

At PDL (or iCMT), from Maintenance Screen, click Download. Verify Download Screen is displayed.

2)

From Download Screen, click Download LRU. Verify LRU Load Screen is displayed.

3)

From LRU Load Screen, click ADB and ALL SELECTED LRUs. NOTE:

Wait 5 minutes for reboot of ADB.

Verify Download Phase 2 Screen with a Progress Bar is displayed. 4)

When Progress Bar indicates 100%, click OK. Verify System Config-Detail Screen is displayed.

5)

At System Config-Detail Screen: Verify files were downloaded to ADB per Table 2001 or 2002.

6)

At System Config-Detail Screen, click CC Menu. Verify Configuration Check Screen is displayed.

7)

At Configuration Check Screen, click Cancel. Verify Maintenance Screen is displayed.

EFFECTIVITY ALL

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SUBTASK 44-21-74-470-008-A01 E.

Phase 2 Software Download to the DSU-D2s CAUTION: WHILE PERFORMING THIS PROCEDURE, ENSURE THAT

AIRCRAFT POWER IS NOT INTERRUPTED. PLACE IFE WORKIN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. 1)

At PDL (or iCMT), from Maintenance Screen, click Download. Verify Download Screen is displayed.

2)

From Download Screen, click Download LRU. Verify LRU Load Screen is displayed.

3)

From LRU Load Screen, click DSU-D2 and ALL SELECTED LRU’s. a)

Verify Download Phase 2 Screen with a Progress Bar is displayed.

b)

Wait approximately 10 minutes.

4)

When Progress Bar indicates 100%, click OK. Verify System Config-Detail Screen is displayed.

5)

At System Config-Detail Screen: Verify files were downloaded to the DSU-D2 per Table 2001 or 2002.

6)

At System Config Detail Screen, click CC Menu. Verify Configuration Check Screen is displayed.

7)

At Configuration Check Screen, click CANCEL.

8)

Verify Maintenance Screen is displayed.

SUBTASK 44-21-74-470-009-A01 F.

IP Sequencing 1)

Procedure

CAUTION: FOLLOWING THE REPLACEMENT OF ANY SEAT-END LRU, WAIT A MINIMUM OF 20 MINUTES AFTER APPLYING POWER BEFORE CARRYING OUT EITHER AN IP SEQUENCE OR A PHASE 2 SOFTWARE EFFECTIVITY ALL

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DOWNLOAD. ALLOW THE IP SEQUENCE OR SOFTWARE DOWNLOAD TO COMPLETE (100%) OR TIMEOUT AND WAIT AN ADDITIONAL 20 MINUTES BEFORE STARTING ANOTHER IP SEQUENCE OR DOWNLOAD. CAUTION: WHILE PERFORMING THIS PROCEDURE, ENSURE THAT

AIRCRAFT POWER IS NOT INTERRUPTED. PLACE IFE WORKIN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. NOTE: IP Sequencing is required only if SEB(s), iCMT, or SVDU(s) were replaced, otherwise proceed to LRU download procedure. When a TPCU has been replaced, an IP sequence is not required. The TPCUs acquire their IP address from the Seat Electronics Box (SEB) during the 20 minute period. Ethernet network connectivity is also established during this time. 2)

At PDL (or iCMT), from Maintenance Screen, click IP Sequencing. Verify IP Sequence Menu Screen is displayed.

3)

At IP Sequence Menu Screen, click IP Sequence. Verify IP Sequence Progress Bar is displayed.

4)

When Progress Bar indicates 100%, click OK. Verify IP Sequence Report Screen reports all SEB highlighted green.

5)

Click Done. Verify IP Sequence Menu is displayed.

6)

Click Done. Verify Maintenance Screen is displayed.

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

SUB-TASK 44-21-74-470-803-A01 G.

OEB Address Assignment 1)

At iCMT, from Maintenance Screen, touch PSS. Verify PSS Maintenance Control Screen is displayed.

2)

At iCMT, from PSS Maintenance Control Screen, touch ASSIGN ADDRS Wait approximately 5 minutes for all OEBs to sequence. NOTE: A clicking noise may be heard while OEBs are sequencing.

3)

At iCMT, from PSS Maintenance Control Screen, touch BACK. Verify Maintenance Screen is displayed.

SUBTASK 44-21-74-470-010-A01 H.

Phase 2 Software Download to the SEBs CAUTION: WHILE PERFORMING THIS PROCEDURE, ENSURE THAT

AIRCRAFT POWER IS NOT INTERRUPTED. PLACE IFE WORKIN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. CAUTION: FOLLOWING THE REPLACEMENT OF ANY SEAT-END LRU, WAIT A MINIMUM OF 20 MINUTES AFTER APPLYING POWER BEFORE CARRYING OUT EITHER AN IP SEQUENCE OR A PHASE 2 SOFTWARE DOWNLOAD. ALLOW THE IP SEQUENCE OR SOFTWARE DOWNLOAD TO COMPLETE (100%) OR TIMEOUT AND WAIT AN ADDITIONAL 20 MINUTES BEFORE STARTING ANOTHER IP SEQUENCE OR DOWNLOAD. 1)

At PDL (or iCMT), from Maintenance Screen, click Download. Verify Download Screen is displayed.

2)

From Download Screen, click Download LRU. Verify LRU Load Screen is displayed.

3)

From LRU Load Screen, click SEB and ALL SELECTED LRUs. Verify Download Phase 2 Screen with Progress Bar is displayed.

EFFECTIVITY ALL

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NOTE:

4)

This may take several minutes depending on size of files being downloaded. Wait until Progress Bar indicates 100% or times out.

When Progress Bar indicates 100%, click OK. Verify System Config-Detail Screen is displayed.

5)

At System Config-Detail Screen: Verify files were downloaded to the SEBs per Table 2001 or 2002. CAUTION:

6)

IF ALL FILES WERE NOT DOWNLOADED TO THE SEB, REPEAT STEPS 1-5.

At System Config-Detail Screen, click CC Menu. Verify Configuration Check Screen is displayed.

7)

At Configuration Check Screen, click Cancel. Verify Maintenance Screen is displayed.

SUBTASK 44-21-74-470-011-A01 I.

Phase 2 Software Download to the SVDU-IIWs (Refer to Table 512) CAUTION: FOLLOWING THE REPLACEMENT OF ANY SEAT-END LRU, WAIT A MINIMUM OF 20 MINUTES AFTER APPLYING POWER BEFORE CARRYING OUT EITHER AN IP SEQUENCE OR A PHASE 2 SOFTWARE DOWNLOAD. ALLOW THE IP SEQUENCE OR SOFTWARE DOWNLOAD TO COMPLETE (100%) OR TIMEOUT AND WAIT AN ADDITIONAL 20 MINUTES BEFORE STARTING ANOTHER IP SEQUENCE OR DOWNLOAD. CAUTION: FAILURE TO PERFORM AN IP SEQUENCE AFTER SVDU REPLACEMENT CAUSES AN IP ADDRESS CONFLICT BETWEEN THE ICMT AND THE NEW SVDU. THIS RESULTS IN ACCESS TO THE SYSTEM BEING BLOCKED AND SUBSEQUENT AIRCRAFT DOWN TIME. CAUTION WHILE PERFORMING THE WORK IN THIS PROCEDURE, ENSURE THAT AIRCRAFT POWER IS NOT INTERRUPTED. PROPERLY PLACE IFE WORK-IN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. CAUTION: SVDU MAY NEED TO BE DOWNLOADED TWICE. DOWNLOAD BY ZONE TO AVOID THIS SCENARIO.

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

1)

At PDL (or iCMT), from Maintenance screen, click Download. Verify Download Screen is displayed.

2)

From Download screen, click Download LRU. Verify LRU Load screen is displayed.

3)

From LRU Load screen, click SVDU and ALL SELECTED LRUs. Verify Download Phase 2 screen with Progress Bar is displayed. NOTE:

4)

This may take several minutes depending on size of files being downloaded. Wait until Progress Bar indicates 100% or times out.

When Progress Bar indicates 100%, click OK. Verify System Config-Detail screen is displayed.

5)

At System Config-Detail screen: Verify files were downloaded per Table 2001 or 2002. CAUTION: AFTER FIRST DOWNLOAD, ALL FILES MAY NOT BE DISPLAYED. DOWNLOAD TO SVDU-IIW MAY NEED TO BE REPEATED TO ENSURE ALL FILES ARE DISPLAYED.

6)

At System Config-Detail screen, click CC Menu. Verify Configuration Check screen is displayed.

7)

At Configuration Check screen, touch CANCEL. Verify Maintenance screen is displayed.

8)

At System Config-Detail screen: Verify files were downloaded per Table 2001 or 2002.

9)

At System Config-Detail screen, touch CC Menu. Verify Configuration Check screen is displayed.

10)

At Configuration Check screen, touch CANCEL. Verify Maintenance screen is displayed.

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

SUBTASK 44-21-74-470-012-A01 J.

Phase 2 Software Download to TPCU-Bs (Refer to Table 513) CAUTION: WHILE PERFORMING THE WORK IN THIS PROCEDURE, ENSURE THAT AIRCRAFT POWER IS NOT INTERRUPTED. PROPERLY PLACE IFE WORK-IN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. CAUTION: FOLLOWING THE REPLACEMENT OF ANY SEAT-END LRU, WAIT A MINIMUM OF 20 MINUTES AFTER APPLYING POWER BEFORE CARRYING OUT EITHER AN IP SEQUENCE OR A PHASE 2 SOFTWARE DOWNLOAD. ALLOW THE IP SEQUENCE OR SOFTWARE DOWNLOAD TO COMPLETE (100%) OR TIMEOUT AND WAIT AN ADDITIONAL 20 MINUTES BEFORE STARTING ANOTHER IP SEQUENCE OR DOWNLOAD. CAUTION: TPCU-B CAN NOT BE HOT SWAPPED. TPCUS MUST RECEIVE IP ADDRESSES FROM THE SEB DURING BOOT UP. 1)

At PDL (or iCMT), from Maintenance Screen, click Download. Verify Download Screen is displayed.

2)

From Download Screen, click Download LRU. Verify LRU Load Screen is displayed.

3)

From LRU Load Screen, click TPCU-B and ALL SELECTED LRUs. Verify Download Phase 2 Screen with a Progress Bar is displayed. NOTE:

4)

This may take several minutes depending on size of files being downloaded. Wait until Progress Bar indicates 100% or Times out.

When Progress Bar indicates 100%, click OK. Verify System Config-Detail Screen is displayed.

5)

At System Config-Detail Screen: Verify files were downloaded to the TPCU-b per Table 2001 or 2002. CAUTION: IF ALL FILES WERE NOT DOWNLOADED TO THE TPCU, REPEAT STEPS 1-5.

6)

At System Config-Detail Screen, click CC Menu. Verify Configuration Check Screen is displayed.

EFFECTIVITY ALL

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7)

At Configuration Check Screen, click Cancel. Verify Maintenance Screen is displayed.

SUBTASK 44-21-74-470-013-A01 K.

Phase Two Software Download to iCMT (Refer to Table 514) CAUTION: WHILE PERFORMING THIS PROCEDURE, ENSURE THAT

AIRCRAFT POWER IS NOT INTERRUPTED. PLACE IFE WORKIN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. CAUTION: FOLLOWING THE REPLACEMENT OF ANY SEAT-END LRU, WAIT A MINIMUM OF 20 MINUTES AFTER APPLYING POWER BEFORE CARRYING OUT EITHER AN IP SEQUENCE OR A PHASE 2 SOFTWARE DOWNLOAD. ALLOW THE IP SEQUENCE OR SOFTWARE DOWNLOAD TO COMPLETE (100%) OR TIMEOUT AND WAIT AN ADDITIONAL 20 MINUTES BEFORE STARTING ANOTHER IP SEQUENCE OR DOWNLOAD. 1)

At PDL (or iCMT), from Maintenance Screen, click Download. Verify Download Screen is displayed.

2)

From Download Screen, click Download LRU. Verify LRU Load Screen is displayed.

3)

From LRU Load Screen, click iCMT and ALL SELECTED LRUs. Verify Download Phase 2 Screen with a Progress Bar is displayed. NOTE:

4)

This may take several minutes depending on size of files being downloaded. Wait until Progress Bar indicates 100% or Times out.

When Progress Bar indicates 100%, click OK. Verify System Config-Detail Screen is displayed. NOTE:

5)

iCMT will reboot.

At System Config-Detail Screen: Verify files were downloaded to the iCMT per Table 2001 or 2002.

6)

At System Config-Detail Screen, click CC Menu. Verify Configuration Check Screen is displayed.

EFFECTIVITY ALL

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7)

At Configuration Check Screen, click Cancel. Verify Maintenance Screen is displayed.

SUBTASK 44-21-74-470-014-A01 L.

Content Loading Procedure CAUTION: WHILE PERFORMING THIS PROCEDURE, ENSURE THAT

AIRCRAFT POWER IS NOT INTERRUPTED. PLACE IFE WORKIN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. 1)

At PDL, from Maintenance Screen, click Download. Verify Download Screen is displayed.

2)

At Download Screen, click Update Content. Verify LRU Load Screen is displayed.

3)

At CONTENT LOADING MENU, click Content Inventory Selection. Verify Collecting Available Content Inventory Lists Screen with Progress Bar is displayed.

4)

At Collecting Available Content Inventory Lists Screen, observe Progress Bar. Verify that when list of available content inventory is compiled, Progress Bar is full and System automatically advances to Content Inventory Selection Screen.

5)

At Content Inventory Selection Screen, select content desired by clicking in small circle to left of Description Column.

6)

Click OK. Active Content Selection Screen may be displayed. NOTE:

7)

If Active Content Selection Screen does not appear, Disregard Action Item 7 and proceed to Observation Item 7.1.

If Active Content Selection Screen is displayed click desired content and click OK. Verify Content Inventory Confirmation Screen is displayed.

8)

At Content Inventory Confirmation Screen, click YES, I AM SURE.

EFFECTIVITY ALL

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Verify Content Inventory Confirmation Screen is displayed. 8)

At Content Inventory Confirmation Screen, click YES, I AM SURE. Verify Please wait while the servers process the new content list Screen with Progress Bar is displayed.

9)

At Please wait while the servers process the new content list Screen, observe Progress Bar. Verify that, when Content List processing is complete, Status Bar is full and System automatically advances to Content Loading Summary Screen.

10)

At Content Loading Summary Screen, observe Content Flight Readiness Status Window. Verify all Servers are reporting.

11)

At Content Loading Summary Screen, observe Current Activity Window. Verify Download and Crossload indicates In Progress.

12)

At Content Loading Summary Screen, observe Active Content Progress Bar in Content Download Status Window. When Progress Bar reaches 100% Content Load is may NOT be complete. NOTE:

13)

14)

This screen will give false indication that load is complete.

If only partial content is available, the line should indicate, No further content available. CAUTION: IT IS IMPORTANT TO WAIT UNTIL ALL FILES FOR MOVING MAP HAVE FINISHED UNTARRING. THIS PROCESS WILL TAKE AT LEAST 25 TO 30 MINUTES. In order to confirm that the files for the Moving Map have finished untarring, use HyperTerminal or a telnet session to query DSU AM6-12. Perform Action Items 15 through 22.

15)

At Log-In Prompt, type root. A Password Prompt will be displayed.

16)

At Password Prompt, type root00. Observe that log-in is successful.

17)

At DSU AM6-12, enter the following command:

EFFECTIVITY ALL

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Verify monitor displays three values. 19)

Type: Is | wc Verify monitor displays three values. NOTE:

If first two values are increasing, files are still untarring, otherwise they are complete.

20)

Type: cd /thales/data/contents/mmap_images/images

21)

Type: Is | wc Verify monitor displays three values.

22)

Type: Is | wc Verify monitor displays three values. NOTE:

If first two values are increasing, files are still untarring, otherwise they are complete.

SUBTASK 44-21-74-720-001-A01 M.

Configuration Check Procedure. CAUTION: WHILE PERFORMING THE WORK IN THIS PROCEDURE, ENSURE THAT AIRCRAFT POWER IS NOT INTERRUPTED. PROPERLY PLACE IFE WORK-IN-PROGRESS PLACARDS ALERTING OTHER MAINTENANCE PERSONNEL NOT TO INTERRUPT AIRCRAFT POWER. 1)

At PDL, from Maintenance Screen, click Config Check. Verify Configuration Check Screen is displayed.

2)

At PDL, under View Type, click Initiate a new configuration check.

3)

At PDL, under View Type, click Engineering.

4)

Under Target Group, click System, then click GO.

5)

Compare displayed software part numbers to current download screen part numbers (Refer to Table 2001 or 2002). If software part numbers for DSU-AM6-12, AVC, ESU-G, ADBs, DSU-D2s, SEBs, SVDUs, TPCU-bs, and iCMT match current download screen part numbers, software download is complete (Refer to Table 2001 or 2002). If not, perform applicable step(s) as required.

EFFECTIVITY ALL

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If software part numbers for DSU-AM6-12, AVC, ESU-G, ADBs, DSU-D2s, SEBs, SVDUs, TPCU-bs, and iCMT match current download screen part numbers, software download is complete (Refer to Table 2001 or 2002). If not, perform applicable step(s) as required. SUBTASK 44-21-74-470-015-A01 N.

PDL Shutdown Procedure 1)

Turn PDL off.

2)

At PDL, disconnect RJ-45 Ethernet Cable from VCC Rack RJ-45 Coupler Port 3.

SUBTASK 44-21-74-470-016-A01 O.

Reboot Entire IFE System Procedure 1)

Before using system for first time and, after loading all LRUs, perform an entire IFE System Reboot as follows:

2)

In Video Control Center (VCC) next to iCMT, toggle MASTER IFE Switch to reboot system. Verify that system reboots properly and LAN Welcome Screen is displayed.

EFFECTIVITY ALL

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REMOVAL/INSTALLATION SUBJECT

PAGE

TASK 44-21-74-991-834-A01 1.

General...................................................................................................................4005

TASK 44-21-74-991-835-A01 2.

Equipment and Materials Required.........................................................................4005

TASK 44-21-74-991-836-A01 3.

Digital Server Unit-AM6-12 (DSU-AM6-12).............................................................4005

SUBTASK 44-21-74-020-001-A01 A. Removal ...........................................................................................................4005 SUBTASK 44-21-74-420-001-A01 B. Installation ........................................................................................................4007 TASK 44-21-74-991-838-A01 4.

Ethernet Switching Unit-Gigabit (ESU-G) ...............................................................4008

SUBTASK 44-21-74-020-002-A01 A. Removal ...........................................................................................................4008 SUBTASK 44-21-74-420-001-A01 B. Installation ........................................................................................................4011 TASK 44-21-74-991-840-A01 5.

Audio/Video Controller (AVC) .................................................................................4012

SUBTASK 44-21-74-020-003-A01 A. Removal ...........................................................................................................4012 SUBTASK 44-21-74-420-001-A01 B. Installation ........................................................................................................4015

EFFECTIVITY ALL

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SUBJECT

PAGE

TASK 44-21-74-991-842-A01 6.

Digital Server Unit-D2 (DSU-D2) ............................................................................ 4016

SUBTASK 44-21-74-020-004-A01 A. Removal ........................................................................................................... 4016 SUBTASK 44-21-74-420-001-A01 B. Installation ........................................................................................................ 4018 TASK 44-21-74-991-844-A01 7.

Interactive Cabin Management Terminal (iCMT) .................................................... 4019

SUBTASK 44-21-74-020-005-A01 A. Removal ........................................................................................................... 4019 SUBTASK 44-21-74-420-001-A01 B. Installation ........................................................................................................ 4021 TASK 44-21-74-991-846-A01 8.

VCC Seat Electronics Box (SEB) ........................................................................... 4022

SUBTASK 44-21-74-020-006-A01 A. Removal ........................................................................................................... 4022 SUBTASK 44-21-74-420-001-A01 B. Installation ........................................................................................................ 4024 TASK 44-21-74-991-848-A01 9.

Master Control Unit (MCU) ..................................................................................... 4025

SUBTASK 44-21-74-020-007-A01 A. Removal ........................................................................................................... 4025

EFFECTIVITY ALL

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SUBJECT

PAGE

SUBTASK 44-21-74-420-001-A01 B. Installation ........................................................................................................4028 TASK 44-21-74-991-850-A01 10.

Tapping Unit (TU) ...................................................................................................4029

SUBTASK 44-21-74-020-008-A01 A. Removal ...........................................................................................................4029 SUBTASK 44-21-74-420-001A-A01 B. Installation ........................................................................................................4032 TASK 44-21-74-991-852-A01 11.

Area Distribution Box (ADB) ...................................................................................4033

SUBTASK 44-21-74-020-009-A01 A. Removal ...........................................................................................................4033 SUBTASK 44-21-74-420-001-A01 B. Installation ........................................................................................................4033 TASK 44-21-74-991-854-A01 12.

Seat-End LRUs.......................................................................................................4037

SUBTASK 44-21-74-420-001-A01 A. General.............................................................................................................4037 SUBTASK 44-21-74-420-001-A01 B. Seat Electronics Box (SEB) Replacement.........................................................4037 SUBTASK 44-21-74-420-001-A01 C. Smart Video Display Unit (SVDU) Replacement ...............................................4038 SUBTASK 44-21-74-420-001-A01 D. Tethered Passenger Control Unit – Basic (TPCU-b) Replacement ...................4038 EFFECTIVITY ALL

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This page is intentionally left blank.

EFFECTIVITY ALL

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REMOVAL/INSTALLATION TASK 44-21-74-991-834-A01 1.

General A.

This section provides removal and installation procedures for TopSeries™ i4000 System LRUs.

B.

Some of the LAN B767 aircraft covered in this manual were line-fit installed with the i4000 system equipment at the Boeing Aircraft Company 767 Aircraft assembly line. For removal and installation procedure of i4000 system components that are not provided herein, refer to the Boeing 767 AMM.

TASK 44-21-74-991-835-A01 2.

Equipment and Materials Required Standard tools

TASK 44-21-74-991-836-A01 3.

Digital Server Unit-AM6-12 (DSU-AM6-12)

SUBTASK 44-21-74-020-001-A01 A.

Removal 1)

Access The DSU-AM6-12 is located in the VCC (Refer to Figure 4001).

2)

Preparation for Removal: a)

Open VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Open VCC PWR 2 circuit breaker on P37 panel.

c)

Open VCC PWR 3 circuit breaker on P37 panel.

3)

Removal Procedure a)

Loosen and release two captive hold down fasteners that secure DSU-AM612 to VCC rack assembly (Refer to figure 4001).

EFFECTIVITY ALL

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VCC RACK ASSEMBLY

DSU-AM6-12

CAPTIVE HOLD DOWN FASTENERS

GRAPHIC TASK 44-21-74-991-837-A01 DSU-AM6-12 Removal and Installation Figure 4001

EFFECTIVITY ALL

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WARNING:

b)

VERIFY POWER IS REMOVED FROM THE DSU-AM6-12 PRIOR TO DISCONNECTING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE DSU-AM6-12.

Gently pull DSU-AM6-12 outward to release rear connectors.

CAUTION: THE DSU-AM6-12 IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE DSU-AM6-12. c)

Carefully slide DSU-AM6-12 out of VCC assembly tray.

d)

Install protective covers on open connectors.

e)

Insert DSU-AM6-12 into protective packaging.

SUBTASK 44-21-74-420-001-A01 B.

Installation 1)

Access The DSU-AM6-12 is located in the VCC (Refer to Figure 4001).

2)

Preparation for Installation a)

Verify VCC PWR 1 circuit breaker on P37 panel is open (Refer to Figure 1004).

b)

Verify VCC PWR 2 circuit breaker on P37 panel is open.

c)

Verify VCC PWR 3 circuit breaker on P37 panel is open.

3)

Installation Procedure CAUTION: THE DSU-AM6-12 IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE DSU-AM6-12. a)

Remove DSU-AM6-12 from protective packaging.

b)

Remove protective covers from applicable DSU-AM6-12 and VCC assembly connectors.

c)

Position DSU-AM6-12 in VCC tray assembly.

WARNING:

VERIFY POWER IS REMOVED FROM THE DSU-AM6-12 PRIOR TO ENGAGING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE DSU-AM6-12.

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d)

Push DSU-AM6-12 back until connectors touch.

e)

Push DSU-AM6-12 carefully to engage rear connectors.

f)

Simultaneously engage and tighten two captive hold-down fasteners.

4)

Follow-On Maintenance a)

Close VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Close VCC PWR 2 circuit breaker on P37 panel.

c)

Close VCC PWR 3 circuit breaker on P37 panel.

d)

Perform Phase 1 Software Download procedure per the ADJUSTMENT/TEST section of this manual.

e)

Perform Phase 2 Software Download to the DSU-AM6-12 per the ADJUSTMENT/TEST section of this manual.

f)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

TASK 44-21-74-991-838-A01 4.

Ethernet Switching Unit-Gigabit (ESU-G)

SUBTASK 44-21-74-020-002-A01 A.

Removal 1)

Access The ESU-G is located in the VCC rack assembly (Refer to Figure 1001).

2)

Preparation for Removal: a)

Open VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Open VCC PWR 2 circuit breaker on P37 panel.

c)

Open VCC PWR 3 circuit breaker on P37 panel.

3)

Removal Procedure a)

Loosen and release two captive hold down fasteners that secure ESU-G to VCC rack assembly (Refer to Figure 4002).

EFFECTIVITY ALL

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VCC RACK ASSEMBLY

ESU-G

CAPTIVE HOLD DOWN FASTENERS

GRAPHIC TASK 44-21-74-991-839-A01 ESU-G Removal and Installation Figure 4002

EFFECTIVITY ALL

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WARNING:

b)

VERIFY POWER IS REMOVED FROM THE ESU-G PRIOR TO DISCONNECTING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE ESU-G.

Gently pull ESU-G outward to release rear connectors.

CAUTION:

THE ESU-G IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE ESU-G.

c)

Carefully slide ESU-G out of VCC assembly tray.

d)

Install protective covers on open connectors.

e)

Insert ESU-G into protective packaging.

SUBTASK 44-21-74-420-001-A01 B.

Installation 1)

Access The ESU-G is located in the VCC rack assembly (Refer to Figure 1001).

2)

Preparation for Installation a)

Verify VCC PWR 1 circuit breaker on P37 panel is open (Refer to Figure 1004).

b)

Verify VCC PWR 2 circuit breaker on P37 panel is open.

c)

Verify VCC PWR 3 circuit breaker on P37 panel is open.

3)

Installation Procedure CAUTION:

THE ESU-G IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE ESU-G.

a)

Remove ESU-G from protective packaging.

b)

Remove protective covers from applicable ESU-G and VCC assembly connectors.

c)

Position ESU-G in VCC tray assembly.

WARNING:

VERIFY POWER IS REMOVED FROM THE ESU-G PRIOR TO ENGAGING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE ESU-G.

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d)

Push ESU-G back until connectors touch.

e)

Push ESU-G carefully to engage rear connectors.

f)

Simultaneously engage and tighten two captive hold-down fasteners.

4)

Follow-On Maintenance a)

Close VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Close VCC PWR 2 circuit breaker on P37 panel.

c)

Close VCC PWR 3 circuit breaker on P37 panel.

d)

Perform Phase 2 Software Download to the ESU-G per the ADJUSTMENT/TEST section of this manual.

e)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

TASK 44-21-74-991-840-A01 5.

Audio/Video Controller (AVC)

SUBTASK 44-21-74-020-003-A01 A.

Removal 1)

Access The AVC is located in the VCC rack assembly (Refer to Figure 1001).

2)

Preparation for Removal: a)

Open VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Open VCC PWR 2 circuit breaker on P37 panel.

c)

Open VCC PWR 3 circuit breaker on P37 panel.

3)

Removal Procedure a)

Loosen and release two captive hold down fasteners that secure AVC to VCC rack assembly (Refer to Figure 4003).

WARNING:

VERIFY POWER IS REMOVED FROM THE AVC PRIOR TO DISCONNECTING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE AVC.

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b)

Gently pull AVC outward to release rear connectors.

VCC RACK ASSEMBLY

AVC

CAPTIVE HOLD DOWN FASTENERS

GRAPHIC TASK 44-21-74-991-841-A01 AVC Removal and Installation Figure 4003 EFFECTIVITY ALL

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CAUTION:

THE AVC IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE AVC.

c)

Carefully slide AVC out of VCC assembly tray.

d)

Install protective covers on open connectors.

e)

Insert AVC into protective packaging.

SUBTASK 44-21-74-420-001-A01 B.

Installation 1)

Access The AVC is located in the VCC rack assembly (Refer to Figure 1001).

2)

Preparation for Installation a)

Verify VCC PWR 1 circuit breaker on P37 panel is open (Refer to Figure 1004).

b)

Verify VCC PWR 2 circuit breaker on P37 panel is open.

c)

Verify VCC PWR 3 circuit breaker on P37 panel is open.

3)

Installation Procedure CAUTION:

THE AVC IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE AVC.

a)

Remove AVC from protective packaging.

b)

Remove protective covers from applicable AVC and VCC assembly connectors.

c)

Position AVC in VCC tray assembly (Refer to Figure 4003).

WARNING:

VERIFY POWER IS REMOVED FROM THE AVC PRIOR TO ENGAGING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE AVC.

d)

Push AVC back until connectors touch.

e)

Push AVC carefully to engage rear connectors.

f)

Simultaneously engage and tighten two captive hold-down fasteners.

EFFECTIVITY ALL

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4)

Follow-On Maintenance a)

Close VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Close VCC PWR 2 circuit breaker on P37 panel.

c)

Close VCC PWR 3 circuit breaker on P37 panel.

d)

Perform Phase 2 Software Download to the AVC per the ADJUSTMENT/TEST section of this manual.

e)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

TASK 44-21-74-991-842-A01 6.

Digital Server Unit-D2 (DSU-D2) NOTE: These are typical procedures for all four DSU-D2s.

SUBTASK 44-21-74-020-004-A01 A.

Removal 1)

Access The DSU-D2s are located in the VCC rack assembly (Refer to Figure 1001).

2)

Preparation for Removal: a)

Open VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Open VCC PWR 2 circuit breaker on P37 panel.

c)

Open VCC PWR 3 circuit breaker on P37 panel.

3)

Removal Procedure a)

Loosen and release two captive hold down fasteners that secure DSU-D2 to VCC rack assembly (Refer to Figure 4004).

WARNING:

b)

VERIFY POWER IS REMOVED FROM THE DSU-D2 PRIOR TO DISCONNECTING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE DSU-D2.

Gently pull DSU-D2 outward to release rear connectors.

EFFECTIVITY ALL

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VCC RACK ASSEMBLY

DSU-D2

CAPTIVE HOLD DOWN FASTENERS

GRAPHIC TASK 44-21-74-991-843-A01 DSU-D2 Removal and Installation Figure 4004 CAUTION:

c)

THE DSU-D2 IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE DSU-D2.

Carefully slide DSU-D2 out of VCC assembly tray.

EFFECTIVITY ALL

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d)

Install protective covers on open connectors.

e)

Insert DSU-D2 into protective packaging.

SUBTASK 44-21-74-420-001-A01 B.

Installation 1)

Access The DSU-D2s are located in the VCC rack assembly (Refer to Figure 1001).

2)

Preparation for Installation a)

Verify VCC PWR 1 circuit breaker on P37 panel is open (Refer to Figure 1004).

b)

Verify VCC PWR 2 circuit breaker on P37 panel is open.

c)

Verify VCC PWR 3 circuit breaker on P37 panel is open.

3)

Installation Procedure CAUTION:

THE DSU-D2 IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE DSU-D2.

a)

Remove DSU-D2 from protective packaging.

b)

Remove protective covers from applicable DSU-D2 and VCC assembly connectors.

c)

Position DSU-D2 in VCC tray assembly.

WARNING:

VERIFY POWER IS REMOVED FROM THE DSU-D2 PRIOR TO ENGAGING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE DSU-D2.

d)

Push DSU-D2 back until connectors touch.

e)

Push DSU-D2 carefully to engage rear connectors.

f)

Simultaneously engage and tighten two captive hold-down fasteners.

4)

Follow-On Maintenance a)

Close VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Close VCC PWR 2 circuit breaker on P37 panel.

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c)

Close VCC PWR 3 circuit breaker on P37 panel.

d)

Perform Phase 2 Software Download to the AVC per the ADJUSTMENT/TEST section of this manual.

e)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

TASK 44-21-74-991-844-A01 7.

Interactive Cabin Management Terminal (iCMT)

SUBTASK 44-21-74-020-005-A01 A.

Removal 1)

Access The iCMT is located in the VCC control panel assembly (Refer to Figure 1001).

2)

Preparation for Removal: a)

Open VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Open VCC PWR 2 circuit breaker on P37 panel.

c)

Open VCC PWR 3 circuit breaker on P37 panel.

3)

Removal Procedure a)

Release captive fasteners and open VCC control panel assembly to access the iCMT.

WARNING:

VERIFY POWER IS REMOVED FROM THE iCMT PRIOR TO DISCONNECTING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE iCMT.

b)

Disconnect electrical connector P1 from iCMT receptacle J1 (Refer to Figure 4005).

c)

Disconnect electrical connector P2 from iCMT receptacle J2.

d)

Disconnect electrical connector P3 from iCMT receptacle J3.

e)

Loosen and release four quarter turn fasteners that secure iCMT mounting bracket to VCC control panel assembly.

EFFECTIVITY ALL

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CAUTION:

THE iCMT IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE iCMT. CONNECTOR P1 CONNECTOR P3 CONNECTOR P2 VCC CONTROL PANEL ASSEMBLY ICMT

MOUNTING BRACKET QUARTER TURN FASTENER (4X)

GRAPHIC TASK 44-21-74-991-845-A01 iCMT Removal and Installation Figure 4005 f)

Remove four screws securing iCMT to mounting bracket. NOTE: The four screws are not all the same size. Identify the particular place where each screw is removed so all screws can be properly installed with the new iCMT.

EFFECTIVITY ALL

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g)

Install protective covers on open connectors.

h)

Insert iCMT into protective packaging.

i)

Install iCMT mounting bracket onto VCC control panel assembly using four quarter turn fasteners if not immediately installing a new iCMT.

SUBTASK 44-21-74-420-001-A01 B.

Installation 1)

Access The iCMT is located in the VCC control panel assembly (Refer to Figure 1001).

2)

Preparation for Installation a)

Verify VCC PWR 1 circuit breaker on P37 panel is open (Refer to Figure 1004).

b)

Verify VCC PWR 2 circuit breaker on P37 panel is open.

c)

Verify VCC PWR 3 circuit breaker on P37 panel is open.

3)

Installation Procedure CAUTION:

THE iCMT IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE iCMT.

a)

Remove iCMT from protective packaging.

b)

Remove protective covers from iCMT and VCC assembly connectors.

c)

If necessary, release the four quarter turn fasteners securing iCMT mounting bracket to the VCC control panel assembly

d)

Attach iCMT to mounting bracket using four screws as identified during the removal procedure.

e)

Position iCMT and mounting bracket so that the iCMT display screen shows in the control panel cutout and the mounting bracket holes are aligned (Refer to Figure 4005).

f)

Secure iCMT mounting bracket to VCC control panel assembly using four quarter turn fasteners.

WARNING:

VERIFY POWER IS REMOVED FROM THE iCMT PRIOR TO ENGAGING ELECTRICAL CONNECTORS. FAILURE TO

EFFECTIVITY ALL

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COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE iCMT. g)

Connect electrical connector P3 to iCMT receptacle J3.

h)

Connect electrical connector P2 to iCMT receptacle J2.

i)

Connect electrical connector P1 to iCMT receptacle J1.

4)

Follow-On Maintenance a)

Close VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Close VCC PWR 2 circuit breaker on P37 panel.

c)

Close VCC PWR 3 circuit breaker on P37 panel.

d)

Perform IP Sequencing Procedure per the ADJUSTMENT/TEST section of this manual.

e)

Perform Phase 2 Software Download to the iCMT per the ADJUSTMENT/TEST section of this manual.

f)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

TASK 44-21-74-991-846-A01 8.

VCC Seat Electronics Box (SEB)

SUBTASK 44-21-74-020-006-A01 A.

Removal 1)

Access The VCC SEB is located in the VCC assembly (Refer to Figure 1001).

2)

Preparation for Removal: a)

Open VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Open VCC PWR 2 circuit breaker on P37 panel.

c)

Open VCC PWR 3 circuit breaker on P37 panel.

EFFECTIVITY ALL

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3)

Removal Procedure a)

Release captive fasteners and open VCC control panel assembly to access the VCC SEB (Refer to Figure 4006). CAPTIVE FASTENER (4X)

CONNECTOR P9

CONNECTOR P2 CONNECTOR P1

VCC SIDE PANEL ASSEMBLY CONNECTOR P9

GRAPHIC TASK 44-21-74-991-847-A01 VCC SEB Removal and Installation Figure 4006 WARNING:

VERIFY POWER IS REMOVED FROM THE SEB PRIOR TO DISCONNECTING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE SEB.

b)

Disconnect electrical connector P2 from SEB receptacle J2.

c)

Disconnect electrical connector P1 from SEB receptacle J1.

d)

Disconnect electrical connector P9 from SEB receptacle J9.

EFFECTIVITY ALL

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e)

Disconnect electrical connector P7 from SEB receptacle J7.

f)

While supporting the SEB, loosen and release four captive fasteners securing SEB to VCC assembly side panel.

CAUTION:

THE SEB IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE SEB.

g)

Install protective covers on open connectors.

h)

Insert SEB into protective packaging.

SUBTASK 44-21-74-420-001-A01 B.

Installation 1)

Access The SEB is located in the VCC assembly (Refer to Figure 101).

2)

Preparation for Installation a)

Verify VCC PWR 1 circuit breaker on P37 panel is open (Refer to Figure 1004).

b)

Verify VCC PWR 2 circuit breaker on P37 panel is open.

c)

Verify VCC PWR 3 circuit breaker on P37 panel is open.

3)

Installation Procedure CAUTION:

THE SEB IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE SEB.

a)

Remove SEB from protective packaging.

b)

Remove protective covers from SEB and VCC assembly connectors.

c)

Position SEB on VCC assembly side panel and secure using four captive fasteners (Refer to Figure 4006).

WARNING:

VERIFY POWER IS REMOVED FROM THE SEB PRIOR TO ENGAGING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE SEB.

d)

Connect electrical connector P7 to SEB receptacle J7.

e)

Connect electrical connector P9 to SEB receptacle J9.

EFFECTIVITY ALL

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f)

Connect electrical connector P1 to SEB receptacle J1.

g)

Connect electrical connector P2 to SEB receptacle J2.

h)

Close VCC control panel assembly and secure using four captive fasteners.

4)

Follow-On Maintenance a)

Close VCC PWR 1 circuit breaker on P37 panel (Refer to Figure 1004).

b)

Close VCC PWR 2 circuit breaker on P37 panel.

c)

Close VCC PWR 3 circuit breaker on P37 panel.

d)

Perform IP Sequencing Procedure per the ADJUSTMENT/TEST section of this manual.

e)

Perform Phase 2 Software Download to the SEB per the ADJUSTMENT/TEST section of this manual.

f)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

TASK 44-21-74-991-848-A01 9.

Master Control Unit (MCU) NOTE: These are typical procedures for all four MCUs.

SUBTASK 44-21-74-020-007-A01 A.

Removal 1)

Access The MCUs are located in the cabin ceiling.

2)

Preparation for Removal: a)

Open applicable MCU circuit breaker on P36 or P37 panel (Refer to Figure 1004).

b)

Gain access to the applicable MCU per Boeing AMM procedures.

3)

Removal Procedure WARNING:

VERIFY POWER IS REMOVED FROM THE MCU PRIOR TO DISCONNECTING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE MCU.

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a)

Unlatch and disconnect all electrical connectors from the MCU receptacles (Refer to Figure 4007).

HEX HEAD SCREW FLAT WASHER LOCK WASHER (4 PLACES) MCU

GRAPHIC TASK 44-21-74-991-849-A01 MCU Removal and Installation Figure 4007 EFFECTIVITY ALL

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NOTE: b)

It is not necessary to remove the Programming Module from receptacle J7.

While supporting the MCU, remove four hex head screws, flat washers, and lock washers attaching MCU to the aircraft.

CAUTION:

THE MCU IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE MCU.

c)

Install protective covers on open connectors.

d)

Insert MCU into protective packaging.

SUBTASK 44-21-74-420-001-A01 B.

Installation 1)

Access The MCUs are located in the cabin ceiling.

2)

Preparation for Installation a)

Verify applicable MCU circuit breaker on P36 or P37 panel is open (Refer to Figure 1004).

b)

Gain access to the applicable MCU per Boeing AMM procedures.

3)

Installation Procedure CAUTION:

THE MCU IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE MCU.

a)

Remove MCU from protective packaging.

b)

Remove protective covers from MCU connectors.

c)

Position MCU on mounting surface with mounting holes aligned.

d)

Secure MCU to aircraft using four hex head screws, flat washers, and lock washers (Refer to Figure 4007).

WARNING:

e)

VERIFY POWER IS REMOVED FROM THE MCU PRIOR TO ENGAGING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE MCU.

Attach electrical connectors to MCU receptacles and secure using the captive latches as applicable.

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f) 4)

Make sure the Programming Module is securely inserted in receptacle J7.

Follow-On Maintenance a)

Close applicable MCU circuit breaker on P36 or P37 panel (Refer to Figure 1004).

b)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

TASK 44-21-74-991-850-A01 10. Tapping Unit (TU) NOTE: These are typical procedures for all five TUs. SUBTASK 44-21-74-020-008-A01 A.

Removal 1)

Access The TUs are located in the cabin ceiling.

2)

Preparation for Removal: a)

Open applicable MCU circuit breaker on P36 or P37 panel (Refer to Figure 1004).

b)

Gain access to the applicable TU per Boeing AMM procedures.

3)

Removal Procedure WARNING:

a)

VERIFY POWER IS REMOVED FROM THE TU PRIOR TO DISCONNECTING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE TU.

Unlatch and disconnect all electrical connectors from the TU receptacles (Refer to Figure 4008). NOTE: The quantity of connectors attached to each TU depends on the number of monitors served by that particular TU.

b)

While supporting the TU with one hand (if necessary), use the other hand to release the four captive fasteners securing TU bracket to the aircraft.

CAUTION:

THE TU IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE TU.

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c)

Install protective covers on open connectors.

d)

Insert TU into protective packaging.

LATCH (10 PLACES)

TU

CAPTIVE FASTENER (4X)

GRAPHIC TASK 44-21-74-991-851-A01 TU Removal and Installation Figure 4008 EFFECTIVITY ALL

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SUBTASK 44-21-74-420-001A-A01 B.

Installation 1)

Access The TUs are located in the cabin ceiling.

2)

Preparation for Installation a)

Verify applicable MCU circuit breaker on P36 or P37 panel is open.

b)

Gain access to the applicable TU per Boeing AMM procedures.

3)

Installation Procedure CAUTION:

THE TU IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE TU.

a)

Remove TU from protective packaging.

b)

Remove protective covers from TU connectors.

c)

Position TU on mounting surface with mounting holes aligned.

d)

Secure TU to aircraft using four captive fasteners (Refer to Figure 4008).

WARNING:

e)

Attach electrical connectors to TU receptacles and secure using the captive latches as applicable. NOTE:

f) 4)

VERIFY POWER IS REMOVED FROM THE TU PRIOR TO ENGAGING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE TU.

The quantity of connectors attached to each TU depends on the number of monitors served by that particular TU.

Make sure the terminator plug is installed; if applicable.

Follow-On Maintenance a)

Close applicable MCU circuit breaker on P36 or P37 panel.

b)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

EFFECTIVITY ALL

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TASK 44-21-74-991-852-A01 11. Area Distribution Box (ADB) NOTE: These are typical procedures for all five ADBs SUBTASK 44-21-74-020-009-A01 A.

Removal 1)

Access The ADBs are located in the cabin ceiling.

2)

Preparation for Removal: a)

Open applicable MCU circuit breaker on P36 or P37 panel (Refer to Figure 1004).

b)

Gain access to the applicable ADB per Boeing AMM procedures.

3)

Removal Procedure WARNING:

VERIFY POWER IS REMOVED FROM THE ADB PRIOR TO DISCONNECTING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE ADB.

a)

Unlatch and disconnect all electrical connectors from the ADB receptacles (Refer to Figure 4009).

b)

While supporting the ADB with one hand (if necessary), remove four hex head screws, flat washers, and lock washers attaching ADB to the aircraft.

CAUTION:

THE ADB IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE ADB.

c)

Install protective covers on open connectors.

d)

Insert ADB into protective packaging.

SUBTASK 44-21-74-420-001-A01 B.

Installation 1)

Access The ADBs are located in the cabin ceiling.

2)

Preparation for Installation a)

Verify applicable MCU circuit breaker on P36 or P37 panel is open (Refer to Figure 1004).

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ADB

HEX HEAD SCREW FLAT WASHER LOCK WASHER (4 PLACES)

GRAPHIC TASK 44-21-74-991-853-A01 ADB Removal and Installation Figure 4009 EFFECTIVITY ALL

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b) 3)

Gain access to the applicable ADB per Boeing AMM procedures.

Installation Procedure CAUTION:

THE ADB IS AN ESD SENSITIVE DEVICE. USE PROPER ESD HANDLING PROCEDURES WHEN HANDLING THE ADB.

a)

Remove ADB from protective packaging.

b)

Remove protective covers from ADB connectors.

c)

Position ADB on mounting surface with mounting holes aligned.

d)

Secure ADB to aircraft using four hex head screws, flat washers, and lock washers (Refer to Figure 4009).

WARNING:

e) 4)

VERIFY POWER IS REMOVED FROM THE ADB PRIOR TO ENGAGING ELECTRICAL CONNECTORS. FAILURE TO COMPLY MAY RESULT IN ELECTRICAL SHOCK TO PERSONNEL AND DAMAGE TO THE ADB.

Attach electrical connectors to ADB receptacles.

Follow-On Maintenance a)

Close applicable MCU circuit breaker on P36 or P37 panel (Refer to Figure 1004).

b)

Perform IP Sequencing Procedure per the ADJUSTMENT/TEST section of this manual.

c)

Perform Phase 2 Software Download to the ADBs per the ADJUSTMENT/TEST section of this manual.

d)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

EFFECTIVITY ALL

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TASK 44-21-74-991-854-A01 12. Seat-End LRUs SUBTASK 44-21-74-420-001-A01 A.

General 1)

These procedures must be followed when replacing seat-end Line Replaceable Units (LRUs) and are intended to be used in addition to the seat manufacturer’s AMM supplemental procedures or Boeing AMM procedures.

2)

By following these time guidelines, the Ethernet network on the aircraft will avoid becoming “flooded,” which could result in a loss of handset communications to the aircraft. If this occurs, the reading light and call function on the TPCU-b will be disabled.

3)

Following the replacement of any seat-end LRU, wait a MINIMUM of 20 minutes after applying power before carrying out either an Internet Protocol (IP) sequence or a software download.

4)

Allow the IP sequence or software download to complete (100%) or timeout and wait an additional 20 minutes before starting another IP sequence or download.

SUBTASK 44-21-74-420-001-A01 B.

Seat Electronics Box (SEB) Replacement 1)

Replace SEB per Boeing AMM or seat manufacturer’s AMM supplement procedures.

2)

Apply power and wait 6-8 minutes.

3)

Observe Sys Status page on iCMT. When it is blank, all LRUs are on the network and ready to work.

4)

Perform IP Sequencing Procedure per the ADJUSTMENT/TEST section of this manual.

5)

Perform Phase 2 Software Download to the SEB per the ADJUSTMENT/TEST section of this manual.

6)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

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SUBTASK 44-21-74-420-001-A01 C.

Smart Video Display Unit (SVDU) Replacement 1)

Replace SVDU per Boeing AMM or seat manufacturer’s AMM supplement procedures.

2)

Apply power and wait 6-8 minutes.

3)

Observe Sys Status page on iCMT. When it is blank, all LRUs are on the network and ready to work.

CAUTION: FAILURE TO PERFORM AN IP SEQUENCE AFTER SVDU REPLACEMENT CAUSES AN IP ADDRESS CONFLICT BETWEEN THE iCMT AND THE NEW SVDU. THIS RESULTS IN ACCESS TO THE SYSTEM BEING BLOCKED AND SUBSEQUENT AIRCRAFT DOWN TIME. 4)

Perform IP Sequencing Procedure per the ADJUSTMENT/TEST section of this manual.

5)

Perform Phase 2 Software Download to the SVDUs per the ADJUSTMENT/TEST section of this manual.

6)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

SUBTASK 44-21-74-420-001-A01 D.

Tethered Passenger Control Unit – Basic (TPCU-b) Replacement 1)

Replace TPCU-b per Boeing AMM or seat manufacturer’s AMM supplement procedures.

2)

Apply power and wait 6-8 minutes for the system to boot.

3)

Observe Sys Status page on iCMT. When it is blank, all LRUs are on the network and ready to work. NOTE: When a TPCU has been replaced, an IP sequence is not required. The TPCUs acquire their IP address from the Seat Electronics Box (SEB) during the 20 minute period. Ethernet network connectivity is also established during this time.

4)

Perform Phase 2 Software Download to the TPCU-b per the ADJUSTMENT/TEST section of this manual.

5)

Perform System Functional Test procedure per the ADJUSTMENT/TEST section of this manual.

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ADJUSTMENT TEST SUBJECT

PAGE

TASK 44-21-74-991-808-A01 1.

General...................................................................................................................5002

TASK 44-21-74-470-806-A01 2.

System Initialization ................................................................................................5002

SUBTASK 44-21-74-470-029-A01 A. System Boot......................................................................................................5002 SUBTASK 44-21-74-470-030-A01 B. Expected Boot Observations .............................................................................5002 TASK 44-21-74-720-802-A01 3.

Functional Test .......................................................................................................5003

SUBTASK 44-21-74-720-002-A01 A. Functional Test Level 1 .....................................................................................5003 SUBTASK 44-21-74-720-003-A01 B. Functional Test Level 2 .....................................................................................5004 SUBTASK 44-21-74-720-004-A01 C. Functional Test Level 3 .....................................................................................5007

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TASK 44-21-74-991-855-A01 1.

General A.

This section contains Final System Test procedures for the TopSeries™ i4000 system.

B.

The procedures in this section are presented in logical order and maybe performed sequentially, however each procedure is meant to stand alone/ NOTE:

for illustration screen display described throughout this section refer to Description and Operation of this manual.

TASK 44-21-74-470-804-A01 2.

System Initialization

SUBTASK 44-21-74-470-017-A01 A.

System Boot 1)

Start-up IFE system.

2)

Measure length of time for each LRU to boot up.

3)

All LRUs should report correctly within 6 minutes.

4)

Make Sure all SVDUs are turned off during power up.

5)

All TPCU-b(s) should boot up and display THALES followed by OD mode.

SUBTASK 44-21-74-470-018-A01 B.

Expected Boot Observations 1)

No audio is heard on headsets at this time.

2)

Noise level is acceptable at this time.

3)

iCMT Welcome Screen is now displayed with ALNAIR logo.

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TASK 44-21-74-720-801-A01 3.

Functional Test

SUBTASK 44-21-74-720-002-A01 A.

Functional Test Level 1 1)

On iCMT touch Entertainment

2)

Enter password at Entertainment Access Screen.

3)

Touch OK Auto Play is displayed by default.

4)

Touch Sys Status a)

Verify Comm Status Screen Displays. (Displays SVDUs currently not on network)

b)

From Comm Status Screen, Record any LRUs listed in LRU dropdown menu.

5)

Touch VA from control bar. a)

Highlight any media selection.

b)

Touch Play

c)

Touch Video to PAX

d)

Perform following step to verify safety video, audio output from iCMT through PAWM, and VA output Keyline is operational: Verify all SVDUs display selected video and corresponding audio is heard over PA speakers.

e)

Record any discrepancies.

6)

If applicable, while video is playing touch PA.

7)

If applicable, touch Passenger Address

8)

If applicable, push Talk from any flight attendant handset.

9)

Perform following to verify PA Keyline safety, and system heartbeat change for video to pause. If applicable, Verify PA overrides entertainment system audio.

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10)

On iCMT touch Maintenance Enter password (11223344) on Maintenance Access Screen

11)

Following sequence is to verify ability of each SVDU to stream video from server: Touch Static Test from Maintenance Screen. a)

On static test screen from drop down menu touch VOD Single.

b)

Then touch ON

c)

Verify all SVDUs have started in VOD NOTE:

If some SVDUs have not it is acceptable to stop and restart the test on the iCMT this media file will last approximately 20 minutes

d)

While walking the cabin test the end of OEB column reading and call lights and ensure the appropriate reading lights, attendant call light, master call light, and chime operate. (Verifies entire OEB column is addressed correctly).

e)

Record any problems discovered.

12)

Discrepancy list Ensure defects are logged as maintenance snags unless time permits remedy.

13)

If time permits Remedy Discrepancies – test per AMM

14)

If no problems occur, end test, otherwise proceed to level 2.

SUBTASK 44-21-74-720-003-A01 B.

Functional Test Level 2 1)

On iCMT touch Entertainment

2)

Enter password at Entertainment Access Screen.

3)

Touch OK Auto Play is displayed by default.

4)

Touch Sys Status a)

Verify Comm Status Screen Displays. (Displays SVDUs currently not on network)

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b) 5)

From Comm Status Screen, Record any LRUs listed in LRU dropdown menu.

Touch VA from control bar. a)

Highlight any media selection.

b)

Touch Play

c)

Touch Video to PAX

d)

Perform following to verify safety video, Audio output from iCMT through PAWM, VA output Keyline, and PA Keyline—safety and system heartbeat change for video to pause are in operational status: Verify all SVDUs display selected video and corresponding audio is heard over PA speakers.

e)

While walking the cabin test the end row of OEB column reading and call lights and ensure the appropriate reading lights, attendant call light, master call light, and chime operate. (Verifies entire OEB column is addressed correctly).

f)

Record any discrepancies.

6)

If applicable, while video is playing touch PA.

7)

If applicable, touch Passenger Address

8)

If applicable, push Talk from any flight attendant handset.

9)

If applicable perform following to verify PA Keyline—safety and system heartbeat change for video to pause: Verify PA overrides entertainment system audio. ()

10)

On iCMT touch Maintenance Enter password (11223344) on Maintenance Access Screen

11)

Touch Config Check (Refer to Maintenance Practices Section 2000 of this manual).

12)

Initiate a full system configuration check. (This could take 10-15 minutes)

13)

Perform following to verify process is correctly sequenced: a)

While process is going inspect each SVDU and ensure color is blue. This color verifies it is on primary Ethernet route.

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b)

14)

Orange indicates secondary route and is indicative of a break in normal Ethernet wiring, or a bad SVDU and PAX position shown on screen matches actual seat number.

Perform following to verify all LRUs are operational: a)

When iCMT displays OK, touch iCMT, and scroll to bottom of report.

b)

Document any non-responsive LRUs.

c)

Touch Summary button from top of Config Check report page and verify all LRUs have correct software listed in AMM or current service bulletin.

d)

Verify following numbers of LRUs are shown and all have correct software:

15)

(1)

ADBs – 5

(2)

AVC – 1

(3)

DSU AM6-12 - 1

(4)

DSU D2s- 2

(5)

SVDUs – 219

(6)

ICMT – 1

(7)

TPCU-b-38

(8)

OEB-98

Touch Static Test from Maintenance Menu. a)

On static test screen from drop down menu touch VOD Single.

b)

Then touch ON

c)

Perform following to verify ability of each SVDU to stream video from server:

d)

Verify all SVDUs have started in VOD. NOTE:

e) 16)

If some SVDUs have not it is acceptable to stop and restart test on iCMT this media file will last approximately 20 minutes

Record any problems discovered.

Discrepancy list Ensure defects are logged as maintenance snags unless time permits remedy.

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17)

If time permits Remedy Discrepancies – test per AMM.

18)

If no problems occurred end test, otherwise move on to level 3.

SUBTASK 44-21-74-720-004-A01 C.

Functional Test Level 3 1)

On iCMT touch Entertainment

2)

Enter password at Entertainment Access Screen.

3)

Touch OK Auto Play Screen is displayed by default.

4)

Touch Sys Status a)

Verify Comm Status Screen Displays. (Displays SVDUs currently not on network)

b)

From Comm Status Screen, Record any LRUs listed in LRU dropdown menu.

5)

Touch VA from control bar. a)

Highlight any media selection.

b)

Touch Play

c)

Touch Video to PAX

d)

Perform following to verify safety video, Audio output from iCMT through PAWM, and VA output Keyline is operational: Verify all SVDUs display selected video and corresponding audio is heard over PA speakers.

e)

While walking the cabin test the end of OEB column reading and call lights and ensure the appropriate reading lights, attendant call light, master call light, and chime operate. (Verifies entire OEB column is addressed correctly).

f)

Record any discrepancies.

6)

If applicable, while video is playing touch PA.

7)

If applicable, touch Passenger Address

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8)

If applicable, push Talk from any flight attendant handset.

9)

If applicable perform following to Verify PA Keyline—safety and system heartbeat change for video to pause: If applicable, Verify PA overrides entertainment system audio.

10)

On iCMT touch Maintenance Enter password (11223344) on Maintenance Access Screen

11)

Touch Config Check (Refer to Maintenance Practices Section 2000 of this manual).

12)

Initiate a full system configuration check. (could take 10-15 minutes)

13)

Perform following to verify process is correctly sequenced. a)

While process is going inspect each SVDU and ensure color is blue. This color verifies it is on primary Ethernet route.

b)

Orange indicates secondary route and is indicative of a break in normal Ethernet wiring, or a bad SVDU and PAX position shown on screen matches actual seat number. .

c)

When iCMT displays OK, touch iCMT, and scroll to bottom of report. This step verifies all LRUs are operational. Document any non-responsive LRUs.

d)

Touch Summary button from top of Config Check report page and verify all LRUs have correct software listed in AMM or current service bulletin.

e)

Verify following numbers of LRUs are shown and all have correct software: (1)

ADBs – 5

(2)

AVC – 1

(3)

DSU AM6-12 - 1

(4)

DSU D2s- 2

(5)

SVDUs – 219

(6)

ICMT – 1

(7)

TPCU-b-38

(8)

OEB-98

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14)

Touch Static Test from Maintenance Menu. a)

On static test screen from drop down menu touch VOD Single.

b)

Then touch ON.

c)

Perform following to verify ability of each SVDU to stream video from server:

d)

Verify all SVDUs have started in VOD. NOTE:

e) 15)

If some SVDUs have not it is acceptable to stop and restart test on iCMT this media file will last approximately 20 minutes.

Record any problems discovered.

Discrepancy list Ensure defects are logged as maintenance snags unless time permits remedy.

16)

If time permits Remedy Discrepancies – test per AMM.

17)

If no problems occurred, end test, otherwise move on to level 3.

18)

For each seat complete following (this can be done during VOD Static Test):

19)

Verify touch screen works (curser follows and is closely aligned to your finger).

20)

Connect a headset to audio Jack and ensure good quality is heard in both ears – ensure volume adjusts from TPCU-b and touch screen. Record any problems discovered.

21)

Discrepancy list Ensure defects are logged as maintenance snags unless time permits remedy.

22)

Remedy Discrepancies – test per AMM (if time permits

23)

If no problems occurred, end test otherwise start from level 1 Functional Test.

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INSPECTION/CHECK SUBJECT

PAGE

TASK 44-21-74-991-809-A01 1.

General...................................................................................................................6002

TASK 44-21-74-210-801-A01 2.

Procedure...............................................................................................................6002

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TASK 44-21-74-991-856-A01 1.

General This section provides inspection/check procedures for the TopSeries™ i4000 system equipment.

TASK 44-21-74-210-801-A01 2.

Procedure Inspection/Check procedures are described in Table 6001

SUBTASK 44-21-74-991-857-A01 Inspection/Check Procedures Table 6001 (Sheet 1 of 2) COMPONENT NOMENCLATURE

METHOD OF INSPECTION

CHECK FOR

CORRECTIVE ACTION

Threaded parts

Visual

Stripped or cross-threaded part resulting in damage to 50% or more of one thread

Replace damaged components

Hardware and software identification labels

Visual

Check for legibility and security

Replace damaged/missing hardware or software identification label(s)

Covers and Panels

Visual

Check for: chipped, burned, or distorted mating surfaces; case and panel cracks or breaks; loose, or missing hardware.

Replace damaged components

Electrical Connectors

Visual

Check for: bent, broken, or loose pins; cracked or broken insulators; broken, loose, or deformed housing; broken pin connectors; dirt and corrosion.

Replace damaged components

EFFECTIVITY ALL

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Inspection/Check Procedures Table 601 (Sheet 2 of 2) COMPONENT NOMENCLATURE Wiring

METHOD OF INSPECTION Visual

CHECK FOR Check for: weak or broken connections; cold solder joints; cracked, chipped, or burned wiring; insulation deterioration; dirt and corrosion.

CORRECTIVE ACTION Replace damaged components

EFFECTIVITY ALL

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CLEANING/PAINTING SUBJECT

PAGE

TASK 44-21-74-991-811-A01 1.

General...................................................................................................................7002

TASK 44-21-74-991-812-A01 2.

Equipment and Materials Required.........................................................................7002

TASK 44-21-74-160-801-A01 3.

Equipment Exterior Cleaning Procedure.................................................................7002

TASK 44-21-74-160-802-A01 4.

SVDU Screen Cleaning Procedure .........................................................................7002

EFFECTIVITY ALL

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THALES AVIONICS, INCORPORATED AIRCRAFT MAINTENANCE MANUAL TOPSERIES™ i4000 SYSTEM

TASK 44-21-74-991-858-A01 1.

General This section provides cleaning and painting instructions.

TASK 44-21-74-991-859-A01 2.

Equipment and Materials Required Standard tools and cleaning materials.

TASK 44-21-74-160-801-A01 3.

Equipment Exterior Cleaning Procedure A.

Use the following general procedures to clean equipment exteriors:

B.

Use a small vacuum or soft brush to remove any accumulated dust or lint.

C.

Clean equipment exteriors using a soft cloth.

TASK 44-21-74-160-802-A01 4.

SVDU Screen Cleaning Procedure Use a small vacuum or soft brush to remove any accumulated dust or lint. CAUTION:

A.

DO NOT USE ABRASIVE MATERIALS (SUCH AS PAPER TOWELS), SOLVENTS, OR CHEMICALS (SUCH AS AMMONIA) ON SCREENS. IF SURFACE OF RETRACTABLE MONITOR SCREEN BECOMES SCRATCHED IT CANNOT BE REPAIRED, THEREFORE IT IS IMPERATIVE THAT THIS CLEANING PROCEDURE IS FOLLOWED. IF SCREEN BECOMES BADLY SCRATCHED, IT MUST BE REPLACED. DO NOT PRESS TOO HARD OR EXCESSIVELY WET THE MONITOR SCREEN.

Clean SVDU screens as follows: 1)

Dampen a lens cleaning tissue sheet or soft cloth with isopropyl alcohol or equivalent substitute (such as the Alglas VDU screen cleaning product).

2)

Gently wipe screen.

3)

Repeat this process until all residue traces are removed from screen.

EFFECTIVITY ALL

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