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| Document ID | 3476924 |
| Application ID | U8V6PlMkmhHfXUBkeVkTdA== |
| Document Description | User Manual |
| Short Term Confidential | No |
| Permanent Confidential | No |
| Supercede | No |
| Document Type | User Manual |
| Display Format | Adobe Acrobat PDF - pdf |
| Filesize | 455.21kB (5690133 bits) |
| Date Submitted | 2017-07-21 00:00:00 |
| Date Available | 2017-07-21 00:00:00 |
| Creation Date | 2002-08-16 08:13:44 |
| Producing Software | Acrobat Distiller 4.05 for Windows; modified using iText 2.1.7 by 1T3XT |
| Document Lastmod | 2017-06-23 13:02:37 |
| Document Title | SDI:MCS-4000/7000 Multi-Channel SATCOM System:A15-5111-001:Rev 2 |
| Document Author: | Honeywell International |
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION,
AND MAINTENANCE MANUAL
MCS-4000/7000
TEMPORARY REVISION NO. 23-2
TO HOLDERS OF MCS-4000/7000 MULTI-CHANNEL SATCOM SYSTEM SYSTEM DESCRIPTION,
INSTALLATION, AND MAINTENANCE MANUAL 23-20-27, REVISION 2, DATED 5 FEB 2008.
INSERT THIS PAGE AS THE FIRST PAGE OF THE MANUAL.
Temporary
Revision
Number
23-2
Applicable Page Number
1-13
4-5/(4-6 BLANK)
Honeywell – Confidential
THIS COPYRIGHTED WORK AND ALL INFORMATION ARE THE PROPERTY OF HONEYWELL
INTERNATIONAL INC., CONTAIN TRADE SECRETS AND MAY NOT, IN WHOLE OR IN PART, BE USED,
DUPLICATED, OR DISCLOSED FOR ANY PURPOSE WITHOUT PRIOR WRITTEN PERMISSION OF
HONEYWELL INTERNATIONAL INC. ALL RIGHTS RESERVED.
Copyright - Notice
Copyright 2017 Honeywell International Inc. All rights reserved.
UP86308
Honeywell is a registered trademark of Honeywell International Inc.
All other marks are owned by their respective companies.
23-20-27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 1 of 3
20 Jun 2017
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION AND MAINTENANCE MANUAL
MCS-4000/7000
TEMPORARY REVISION NO. 23-1
TO HOLDERS OF MCS-4000/7000 MULTI-CHANNEL SATCOM SYSTEM SYSTEM DESCRIPTION,
INSTALLATION, AND MAINTENANCE MANUAL 23-20-27, REVISION 2, DATED 5 FEB 2008.
INSERT THIS PAGE AS THE FIRST PAGE OF THE MANUAL.
Temporary
Revision
Number
23-1
Applicable Page Number
4-1
4-2
4-3
Copyright - Notice
Copyright 2009 Honeywell International Inc. All rights reserved.
Honeywell is a registered trademark of Honeywell International Inc.
All other marks are owned by their respective companies.
Honeywell – Confidential
UP86308
THIS COPYRIGHTED WORK AND ALL INFORMATION ARE THE PROPERTY OF HONEYWELL
INTERNATIONAL INC., CONTAIN TRADE SECRETS AND MAY NOT, IN WHOLE OR IN PART, BE USED,
DUPLICATED, OR DISCLOSED FOR ANY PURPOSE WITHOUT PRIOR WRITTEN PERMISSION OF
HONEYWELL INTERNATIONAL INC. ALL RIGHTS RESERVED.
23-20-27
Publication Number D200102000060
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 1 of 6
30 Oct 2009
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
Honeywell International Inc.
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U.S.A.
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Telephone: (800) 601--3099 (U.S.A.)
Telephone: (602) 365--3099 (International)
TO HOLDERS OF SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE
MANUAL, PUB. NO. A15--5111--001, MCS 4000/7000 MULTI--CHANNEL
SATCOM SYSTEM
REVISION NO. 002 DATED 5 FEB 2008
This revision replaces some data in the manual. All changed pages have a new date, as identified
in the List of Effective Pages. Revision bars identify the changed data. An “R” adjacent to the
Fig./Item column identifies changes in the Detailed Parts List.
Put the changed pages in the manual and remove and discard all replaced pages. Write the
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Insert Page
Description of Change
T--1 thru T--4
Changed to show the revision date. Expanded the proprietary notice. Changed the
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LEP--1 thru LEP--8
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------
Removed the Business Reply Card (User Registration Card), Customer Response
form, and Report of Possible Data Error form because this data is available on the
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included in the INTRODUCTION.
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INTRO--1 thru
INTRO--10
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Export Notice data. Added a Customer Support paragraph. Changed the sequence
of the INTRODUCTION data. Changed References, Verification Data, and
Acronyms and Abbreviations data.
1--12, 1--14
Corrected references to Figure 1--6 and Figure 1--7.
6--1
Added statement in paragraph 1.A (1) to reference Appendix D system fault codes.
C--8
Corrected reference to Table C--1.
D--1 thru D--146
Added system fault codes as Appendix D.
INDEX--3
Added an index entry for fault codes.
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
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UP86308
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23--20--27
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Honeywell International Inc.
21111 N. 19th Ave.
Phoenix, AZ 85027-2708
U.S.A.
CAGE: 58960
Telephone: (800) 601--3099 (U.S.A.)
Telephone: (602) 365--3099 (International)
System Description, Installation, and
Maintenance Manual
MCS--4000/7000
Multi--Channel SATCOM System
This document contains technical data and is subject to U.S. export regulations. These commodities,
technology, or software were exported from the United States in accordance with the export administration
regulations. Diversion contrary to U.S. law is prohibited.
ECCN: 7E994, no license required.
UP86308
23--20--27
Page T--1
Publication Number D200102000060, Revision 002
(Formerly A15--5111--001)
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Revised 5 Feb 2008
1 Feb 2001
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
Honeywell--Confidential
THIS COPYRIGHTED WORK AND ALL INFORMATION ARE THE PROPERTY OF HONEYWELL
INTERNATIONAL INC., CONTAIN TRADE SECRETS AND MAY NOT, IN WHOLE OR IN PART, BE
USED, DUPLICATED, OR DISCLOSED FOR ANY PURPOSE WITHOUT PRIOR WRITTEN
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UP86308
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23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
6. Term -- This License Agreement is effective until terminated as set forth herein. This License Agreement will
terminate immediately, without notice from Honeywell, if you fail to comply with any provision of this License
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the parties.
Copyright -- Notice
Copyright 2001, 2008, Honeywell International Inc. All rights reserved.
UP86308
Honeywell is a registered trademark of Honeywell International Inc.
All other marks are owned by their respective companies.
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page T--3
5 Feb 2008
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MCS--4000/7000
UP86308
Blank Page
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page T--4
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
RECORD OF REVISIONS
For each revision, put the revised pages in your manual and discard the superseded pages. Write
the revision number and date, date put in manual, and the incorporator’s initials in the applicable
columns on the Record of Revisions. The initial H shows Honeywell is the incorporator.
UP86308
Revision
Number
Revision
Date
Date Put
In Manual
By
30 Aug 2002
30 Aug 2002
5 Feb 2008
5 Feb 2008
Revision
Number
Revision
Date
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Date Put
In Manual
By
Page RR--1
30 Aug 2002
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
UP86308
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23--20--27
Page RR--2
30 Aug 2002
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
RECORD OF TEMPORARY REVISIONS
Instructions on each page of a temporary revision tell you where to put the pages in your manual.
Remove temporary revision pages only when discard instructions are given. For each temporary
revision, put the applicable data in the record columns on this page.
Temporary
Revision
Number
Temporary
Revision
Date
23-1
23-2
Temporary
Revision
Status
Date Put
in Manual
By *
30 OCT 2017
30 OCT 2017
20 JUN 2017
20 JUN 2017
Date
Removed
from Manual
By *
* The initial H in this column shows Honeywell has done this task.
UP86308
** Temporary revisions are incorporated in the manual by normal revision.
23--20--27
Page RTR--1
30 Aug 2002
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
UP86308
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23--20--27
Page RTR--2
30 Aug 2002
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
SERVICE BULLETIN LIST
UP86308
Service Bulletin
Identified
Mod
Date Included
in this Manual
Description
23--20--27
Page SBL--1
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Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Blank Page
23--20--27
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30 Aug 2002
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
LIST OF EFFECTIVE PAGES
Subheading and Page
Date
Title
T--1
T--2
T--3
T--4
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
Record of Revisions
RR--1
RR--2
30 Aug 2002
30 Aug 2002
Record of Temporary Revisions
RTR--1
RTR--2
30 Aug 2002
30 Aug 2002
Service Bulletin List
SBL--1
SBL--2
30 Aug 2002
30 Aug 2002
TC--11
TC--12
TC--13
TC--14
Date
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
5 Feb 2008
Introduction
INTRO--1
INTRO--2
INTRO--3
INTRO--4
INTRO--5
INTRO--6
INTRO--7
INTRO--8
INTRO--9
INTRO--10
System Description
List of Effective Pages
LEP--1
LEP--2
LEP--3
LEP--4
LEP--5
LEP--6
LEP--7
LEP--8
5 Feb 2008
5 Feb 2008
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5 Feb 2008
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5 Feb 2008
5 Feb 2008
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Table of Contents
TC--1
TC--2
TC--3
TC--4
TC--5
TC--6
TC--7
TC--8
TC--9
TC--10
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Subheading and Page
1--1
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F 1--3/1--4
1--5
1--6
1--7
1--8
1--9
1--10
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1--20
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30 Aug 2002
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indicates a changed or added page.
indicates a foldout page.
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page LEP--1
5 Feb 2008
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
Date
Subheading and Page
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System Operation
2--1
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Cabin/Cockpit Communications
3--1
3--2
F 3--3/3--4
3--5
3--6
3--7
3--8
3--9
3--10
3--11
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Mechanical Installation
4--1
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4--3
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F 4--5/4--6
30 Aug 2002
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indicates a changed or added page.
indicates a foldout page.
23--20--27
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Date
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Electrical Installation
5--1
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Testing/Fault Isolation
6--1
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indicates a changed or added page.
indicates a foldout page.
23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
Date
Subheading and Page
6--94
6--95
6--96
6--97
6--98
6--99
6--100
6--101
6--102
6--103
6--104
6--105
6--106
6--107
6--108
6--109
6--110
6--111
6--112
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30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
Maintenance Practices
7--1
7--2
7--3
7--4
7--5
7--6
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
Appendix A
Vendor Equipment
A--1
A--2
A--3
A--4
F A--5/A--6
A--7
A--8
A--9
A--10
A--11
A--12
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A--13/A--14
A--15
A--16
A--17
A--18
A--19
A--20
A--21
A--22
A--23
A--24
A--25
A--26
A--27
A--28
A--29
A--30
Date
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
Appendix B
Installation Procedures For SATCOM Air Filtration
Systems
B--1
B--2
B--3
B--4
B--5
B--6
B--7
B--8
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
Appendix C
Owner Requirements Table
C--1
C--2
C--3
C--4
C--5
C--6
C--7
C--8
C--9
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
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30 Aug 2002
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
Date
Subheading and Page
C--10
C--11
C--12
C--13
C--14
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
Appendix D
Fault Codes
D--1
D--2
D--3
D--4
D--5
D--6
D--7
D--8
D--9
D--10
D--11
D--12
D--13
D--14
D--15
D--16
D--17
D--18
D--19
D--20
D--21
D--22
D--23
D--24
D--25
D--26
D--27
D--28
D--29
D--30
D--31
D--32
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D--33
D--34
D--35
D--36
D--37
D--38
D--39
D--40
D--41
D--42
D--43
D--44
D--45
D--46
D--47
D--48
D--49
D--50
D--51
D--52
D--53
D--54
D--55
D--56
D--57
D--58
D--59
D--61
D--62
D--63
D--64
D--65
D--66
D--67
D--68
D--69
D--70
D--71
D--72
Date
5 Feb 2008
5 Feb 2008
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MCS--4000/7000
Date
Subheading and Page
D--73
D--74
D--75
D--76
D--77
D--78
D--79
D--80
D--81
D--82
D--83
D--84
D--85
D--86
D--87
D--88
D--89
D--90
D--91
D--92
D--93
D--94
D--95
D--96
D--97
D--98
D--99
D--100
D--101
D--102
D--103
D--104
D--105
D--106
D--107
D--108
D--109
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D--110
D--111
D--112
D--113
D--114
D--115
D--116
D--117
D--118
D--119
D--120
D--121
D--122
D--123
D--124
D--125
D--126
D--127
D--128
D--129
D--130
D--131
D--132
D--133
D--134
D--135
D--136
D--137
D--138
D--139
D--140
D--141
D--142
D--143
D--144
D--145
D--146
Date
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© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page LEP--7
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
Date
Subheading and Page
Index
INDEX--1
INDEX--2
INDEX--3
INDEX--4
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30 Aug 2002
Subheading and Page
INDEX--5
INDEX--6
INDEX--7
INDEX--8
Date
30 Aug 2002
30 Aug 2002
30 Aug 2002
30 Aug 2002
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23--20--27
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Page LEP--8
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
TABLE OF CONTENTS
UP86308
Subject
INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. How to Use this Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Weights and Measurements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. Customer Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Honeywell Aerospace Online Technical Publications Web Site . . . . . . . . . . .
B. Complete Customer Care Center . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Honeywell Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Other Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4. Acronyms and Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5. Maximum Permissible Exposure Level . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION 1
SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Aircraft Earth Station . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Space Segment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. Ground Earth Station . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. Terrestrial Data and Voice Networks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. System Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Satellite Data Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. High Power Amplifier . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. Avionics Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4. MCS Component Descriptions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Physical Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Satellite Data Unit (SDU) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. High--Power Amplifier (40 Watt) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. High--Power Amplifier (20 Watt) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. CMA--2200 Intermediate Gain Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F. CMA--2200 Diplexer/Low Noise Amplifier . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page
INTRO--1
INTRO--1
INTRO--1
INTRO--1
INTRO--1
INTRO--2
INTRO--2
INTRO--2
INTRO--2
INTRO--2
INTRO--2
INTRO--3
INTRO--3
INTRO--8
INTRO--8
1--1
1--1
1--1
1--2
1--9
1--9
1--9
1--12
1--12
1--14
1--14
1--19
1--24
1--25
1--25
1--25
1--26
1--30
1--35
1--38
1--40
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G. Radio Frequency Unit Interface Adapter (RFUIA) . . . . . . . . . . . . . . . . . . . . . . .
H. ARINC 429 Data Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
I. Nameplates 3 (SDU and HPA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
J. Software and Hardware Compatibility (SDU and HPA) . . . . . . . . . . . . . . . . . .
SECTION 2
SYSTEM OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. AES Management . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. System Log-On/Log-Off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Automatic Log-On . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Constrained Log-On . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. Log-On Mode Selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. Handover . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F. Log-Off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4. System Software/Database Updates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Software Upload Process . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Validation of the Software Upload File . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5. Owner Requirements Table . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6. ORT Upload/Download Process . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Startup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. ORT Download . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. Control Mode ORT Upload Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. Auto Mode ORT Upload Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7. Circuit-Mode Services . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Circuit-Mode Voice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Circuit-Mode Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8. Packet-Data Services . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9. Dual SATCOM Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Dual System Control/Status Interfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. System Reversion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. Antenna Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--43
1--44
1--44
1--46
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2--1
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2--7
2--8
2--8
2--8
2--9
2--10
2--10
2--11
2--11
2--11
2--11
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E. Cockpit Voice Configurations and Functionality . . . . . . . . . . . . . . . . . . . . . . . . .
10. ACARS/Aircraft Flight Information System (AFIS) Peripheral Function . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION 3
CABIN/COCKPIT COMMUNICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Cabin Communications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Cabin Communications System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Analog Audio Channels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. Cockpit Communications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Headset Off-Hook Signaling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Headset On-Hook Signaling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. Voice Codec Module Audio Switching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. Voice Codec Module Sidetone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F. Voice Interface Module Stored Audio Messages . . . . . . . . . . . . . . . . . . . . . . . .
G. Voice Interface Module Dedication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION 4
MECHANICAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. Mechanical Installation Design . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. LRU Mechanical Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Installation Dependent Considerations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Owner Requirements Table (ORT) Uploading . . . . . . . . . . . . . . . . . . . . . . . . . .
D. Cable Loss Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. Cooling Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F. Vendor Supplied Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION 5
ELECTRICAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. Electrical Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Connector Layout and Contact Arrangement . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Electrical Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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Configuration Pins . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Availability of ARINC 429 SSR MODE S (AES ID) from CMU Ports . . . . . . .
C. FMC Connection to SDU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. ARINC 429 Speed to/from CMU No. 1 and CMU No. 2 . . . . . . . . . . . . . . . . . .
E. Cabin Packet Data Function (CPDF) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F. ARINC 429 BUS Speed of AES ID Input . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
G. Strap Parity (ODD) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
H. Cabin Communications System (CCS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
I. Inertial Reference System (IRS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
J. HPA/Antenna Subsystem Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
K. CFDS/CMC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
L. SDU Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
M. SDU Number . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
N. CMU No. 1 and No. 2 Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
O. MCDU/SCDU No. 1 thru No. 3 Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . .
P. Priority 4 Calls to/from Cockpit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Q. ARINC 429 BUS Speed to SCDU No. 1 / SCDU No. 2 / SCDU No. 3 . . . . . .
R. Cockpit Voice Call Light/Chime Option . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
S. SDU CODEC 1 and CODEC 2 Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
T. Cockpit Hookswitch Signaling Method . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION 6
TESTING/FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Failure Detection and Reporting Levels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. LRU Coverage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. Monitoring and Testing Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F. Failure Recording . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
G. Failure Reporting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
H. Miscellaneous BITE Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
I. Maintenance Activity Log . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. SATCOM Control and Display Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. SCDU Display Terminology and Basic Operation . . . . . . . . . . . . . . . . . . . . . . .
C. SCDU Page Hierarchy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. SCDU Pages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. Maintenance Computer Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Boeing 747--400 CMC/777 OMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Airbus/Douglas CFDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. Central Aircraft Information and Maintenance System . . . . . . . . . . . . . . . . . . .
E. Level I Failure Messages and ATA Reference Numbers . . . . . . . . . . . . . . . . .
4. SCDU for Dual SATCOM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. SATCOM Logical Channels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. SATCOM MAIN MENU (Cross-Talk Bus Failed) . . . . . . . . . . . . . . . . . . . . . . . .
D. SATCOM CHANNEL STATUS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. SATCOM MAINTENANCE Menus . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5. Maintenance Panel Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION 7
MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. Procedure for Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Antenna Weather Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Antenna Hardware . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. General Antenna Removal Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4. Procedure for the LRUs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. LRU Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. LRU Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5. Owner Requirements Table Uploading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6. Instructions for Continued Airworthiness, FAR 25.1529 . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
APPENDIX A
VENDOR EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. Electronic Cable Specialists . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Radio Frequency Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Cable Assembly Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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D. Cable Assembly Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. ARINC 600 Connectors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F. SATCOM Avionics Unit Mounting Hardware . . . . . . . . . . . . . . . . . . . . . . . . . . .
G. SATCOM Hardware Component Kits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
H. Air Filtration Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
I. SATCOM Shelf Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
J. Additional Avionics Installation Components . . . . . . . . . . . . . . . . . . . . . . . . . . .
K. Antenna System Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
L. Cabin Communications System Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . .
M. Wire Harnesses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
N. Complete Integrated SATCOM Installation Kits . . . . . . . . . . . . . . . . . . . . . . . . .
3. Hollingsead International . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Engineering Services . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. LRU Mounting Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. Installation Kit Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4. Signal Conditioning Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Operator Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Control Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. System Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. ARINC 600 Connector Pin Assignments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
APPENDIX B
INSTALLATION PROCEDURES FOR SATCOM AIR FILTRATION SYSTEMS . . . . .
1. Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. Continued Airworthiness . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4. Installation Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Top Mount Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Body--Mounted Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Tray--Mounted Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
APPENDIX C
OWNER REQUIREMENTS TABLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
APPENDIX D
FAULT CODES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--2
A--2
A--4
A--4
A--8
A--9
A--9
A--9
A--9
A--9
A--9
A--10
A--10
A--10
A--10
A--11
A--16
A--16
A--17
A--18
A--19
A--23
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
B--1
B--1
B--1
B--1
B--1
B--2
B--2
B--4
B--4
B--6
B--7
C--1
C--1
C--1
D--1
INDEX--1
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
UP86308
List of Illustrations
Figure
Figure Intro--1.
Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Page
INTRO--1
Figure Intro--2.
Radio Frequency Energy Levels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
INTRO--9
Figure 1-1.
Aviation Satellite Communications System . . . . . . . . . . . . . . . . . . . . .
1--2
Figure 1-2.
Aircraft Earth Station Block Diagram . . . . . . . . . . . . . . . . . . . . . . . . . .
1--3
Figure 1-3.
INMARSAT Four-Region Satellite Coverage . . . . . . . . . . . . . . . . . . .
1--11
Figure 1-4.
MCS Avionics Block Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--17
Figure 1-5.
MCS--4000/7000 SDU Equipment Description . . . . . . . . . . . . . . . . . .
1--19
Figure 1-6.
Satellite Data Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--27
Figure 1-7.
High--Power Amplifier (40 and 20 Watt) . . . . . . . . . . . . . . . . . . . . . . . .
1--31
Figure 1-8.
RFUIA System Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--43
Figure 2-1.
Satellite Audio System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2--14
Figure 2-2.
Dual System Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2--18
Figure 2-3.
HGA + LGA Configuration with Top-Mounted HGA . . . . . . . . . . . . . .
2--21
Figure 2-4.
HGA + LGA Configuration with Side-Mounted HGA . . . . . . . . . . . . .
2--21
Figure 2-5.
HGA + HGA Configuration with Two Top-Mounted HGAs . . . . . . . .
2--22
Figure 2-6.
HGA + HGA Configuration with Two Side-Mounted HGAs . . . . . . .
2--22
Figure 2-7.
HGA + HGA Configuration with One Side-Mounted HGA + One
Top-Mounted HGA (Dissimilar HGA) . . . . . . . . . . . . . . . . . . . . . . . . . .
2--23
Figure 2-8.
LGA + LGA Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2--23
Figure 2-9.
(HGA + LGA) + HGA Configuration with Two Side-Mounted HGAs
2--24
Figure 2-10.
(HGA + LGA) + HGA Configuration with the LGA Paired with
One Side-Mounted HGA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2--25
Figure 2-11.
(HGA + LGA) + HGA Configuration with the LGA Paired with
One Top-Mounted HGA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2--26
Figure 2-12.
(HGA + LGA) + HGA Configuration with Two Top-Mounted
HGAs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2--27
Figure 3--1.
Audio Interfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3--3
Figure 4-1.
Cable Attenuations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4--2
Figure 4-2.
Satellite Data Unit Outline and Installation Diagram . . . . . . . . . . . . .
4--5
Figure 4-3.
40 Watt High Power Amplifier Outline and Installation Diagram . . .
4--7
Figure 4-4.
20 Watt High Power Amplifier Outline and Installation Diagram . . .
4--9
Figure 4-5.
Intermediate Gain Antenna Outline and Installation Diagram . . . . .
4--13
Figure 4-6.
D/LNA Outline and Installation Diagram . . . . . . . . . . . . . . . . . . . . . . .
4--17
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TC--7
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
List of Illustrations (cont)
UP86308
Figure
Page
Figure 4-7.
RFUIA Outline and Installation Diagram . . . . . . . . . . . . . . . . . . . . . . .
4--21
Figure 5-1.
SDU ARINC 600 Connector Layout . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--4
Figure 5-2.
Contact Arrangements for Bottom Insert, SDU ARINC
600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--7
Figure 5-3.
HPA ARINC 600 Connector Layout . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--8
Figure 5-4.
Contact Arrangements for Top Insert, HPA (40 Watt) ARINC
600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--9
Figure 5-5.
Contact Arrangements for Middle Insert, HPA (40 Watt) ARINC
600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--10
Figure 5-6.
Contact Arrangements for Bottom Insert, HPA (40 Watt) ARINC
600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--11
Figure 5-7.
Contact Arrangements for Top Insert, HPA (20 Watt) ARINC
600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--12
Figure 5-8.
Contact Arrangements for Middle Insert, HPA (20 Watt) ARINC
600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--13
Figure 5-9.
Contact Arrangements for Bottom Insert, HPA (20 Watt) ARINC
600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--14
Figure 5-10.
RFUIA ARINC 600 Connector Layout . . . . . . . . . . . . . . . . . . . . . . . . .
5--15
Figure 5-11.
Satellite Data Unit Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . .
5--17
Figure 5-12.
WH--10 Handset Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--20
Figure 5-13.
Four--to--Two Wire Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . .
5--21
Figure 5-14.
Avtech Fax Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--22
Figure 5-15.
HF--SAT Transfer Panel Interface Diagram . . . . . . . . . . . . . . . . . . . . .
5--23
Figure 5-16.
Signal Conditioning Unit Interface Diagram . . . . . . . . . . . . . . . . . . . .
5--24
Figure 5-17.
Maintenance Panel Assembly Interface Diagram . . . . . . . . . . . . . . .
5--25
Figure 5-18.
Intermediate Gain Antenna Interface Diagram . . . . . . . . . . . . . . . . . .
5--27
Figure 5-19.
CMC Top--Mount High Gain Antenna Interface Diagram . . . . . . . . .
5--29
Figure 5-20.
Tecom Top--Mount High Gain Antenna Interface Diagram . . . . . . . .
5--31
Figure 5-21.
Racal Mechanically Steered High Gain Antenna
Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--33
Figure 5-22.
AMT--50 Mechanically Steered High Gain Antenna
Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--35
Figure 5-23.
Dassault Conformal High Gain Antenna Interface Diagram . . . . . .
5--37
Figure 5-24.
Ball Conformal High Gain Antenna Interface Diagram . . . . . . . . . . .
5--39
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TC--8
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
List of Illustrations (cont)
UP86308
Figure
Page
Figure 5-25.
Low Gain Antenna Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . .
5--41
Figure 5-26.
Toyocom Top--Mount High Gain Antenna Interface Diagram . . . . . .
5--43
Figure 6-1.
System BITE Communication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--1
Figure 6-2.
SATCOM SCDU Page Hierarchy . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--25
Figure 6-3.
SATCOM SCDU Main Menu Page . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--26
Figure 6-4.
SATCOM SUBMENU Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--28
Figure 6-5.
SATCOM MAINTENANCE Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--29
Figure 6-6.
TEST Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--31
Figure 6-7.
SATCOM SELF--TEST Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--36
Figure 6-8.
Configuration Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--39
Figure 6-10.
DATA LOADER MENU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--60
Figure 6-11.
LAST LEG REPORT Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--67
Figure 6-12.
PREVIOUS LEG REPORT Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--69
Figure 6-13.
LRU IDENTIFICATION Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--73
Figure 6-14.
TROUBLE SHOOTING DATA Page . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--76
Figure 6-15.
LAST LEG CLASS 3 FAULTS Page . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--78
Figure 6-16.
GROUND REPORT Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--80
Figure 6-17.
GROUND REPORT TROUBLE SHOOTING DATA Page . . . . . . . .
6--82
Figure 6-18.
Configuration Data Pages for Boeing 777 Installation . . . . . . . . . . .
6--86
Figure A--1.1.
ARINC Connectors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--3
Figure A--1.2.
ARINC Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--3
Figure A--1.3.
Dimensions for ECS Tray Assemblies . . . . . . . . . . . . . . . . . . . . . . . . .
A--5
Figure A--1.4.
Dimensions for Hollingsead Tray Assemblies . . . . . . . . . . . . . . . . . . .
A--13
Figure B--1.1.
ECS Top Mount Air Filtration Assembly . . . . . . . . . . . . . . . . . . . . . . . .
B--5
Figure B--1.2.
Front and Side Views Showing Filter Removal . . . . . . . . . . . . . . . . .
B--8
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TC--9
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
UP86308
List of Tables
Table
Table 1-1.
Classes of Installations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Page
1--8
Table 1-2.
Types of RF Channels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--8
Table 1-3.
Ground Earth Stations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--10
Table 1-4.
System Components Supplied by Honeywell . . . . . . . . . . . . . . . . . .
1--12
Table 1-5.
System Components Not Supplied by Honeywell
..............
1--12
Table 1-6.
SDU Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--13
Table 1-7.
HPA (40 Watt) Configurations
...............................
1--13
Table 1-8.
HPA (20 Watt) Configurations
...............................
1--14
Table 1-9.
SDU Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--27
Table 1-10.
SDU DO--160D Environmental Categories . . . . . . . . . . . . . . . . . . . .
1--29
Table 1-11.
HPA (40 Watt) Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--33
Table 1-12.
HPA (40 Watt) DO--160C Environmental Categories . . . . . . . . . . . .
1--34
Table 1-13.
HPA (20 Watt) Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--36
Table 1-14.
HPA (20 Watt) DO--160D Environmental Categories . . . . . . . . . . . .
1--37
Table 1-15.
CMA--2200 Intermediate Gain Antenna Features . . . . . . . . . . . . . .
1--38
Table 1-16.
CMA--2200 IGA Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . .
1--39
Table 1-17.
CMA--2200 IGA DO--160C Environmental Categories . . . . . . . . . .
1--40
Table 1-18.
CMA--2200 D/LNA Features . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--41
Table 1-19.
CMA--2200 D/LNA Leading Particulars . . . . . . . . . . . . . . . . . . . . . . .
1--41
Table 1-20.
CMA--2200 D/LNA DO--160C Environmental Categories . . . . . . . .
1--42
Table 1-21.
RFUIA Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1--44
Table 2-1.
Data Set Upload/Download
.................................
2--8
Table 2-2.
Basic Antenna Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2--20
Table 3-1.
SDU to WH-10 Handset Actions . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3--5
Table 3-2.
Global-Wulfsberg Flitephone WH-10 Commands . . . . . . . . . . . . . . .
3--7
Table 3-3.
Assignment of DTMF Digits in the APBX Interface
.............
3--13
Table 3-4.
SDU to APBX Off-Hook Actions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3--13
Table 3-5.
Stored Audio Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3--16
Table 4-1.
Cable Loss Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4--3
Table 4-2.
Cooling Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4--3
Table 5-1.
ARINC 615 Connector Pin Callouts
..........................
5--2
Table 5-2.
ARINC 600 Connector Requirements . . . . . . . . . . . . . . . . . . . . . . . . .
5--3
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TC--10
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
List of Tables (cont)
UP86308
Table
Page
Table 5-3.
Contact Arrangements for Top Insert, SDU ARINC
600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--5
Table 5-4.
Contact Arrangements for Middle Insert, SDU ARINC
600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--6
Table 5-5.
ICAO Block Strapping . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--19
Table 5-6.
Configuration Pins . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--45
Table 5-7.
Availability of ARINC 429 SSR MODE S (AES ID) from
CMU Ports . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--46
Table 5-8.
FMC Connection to SDU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--48
Table 5-9.
ARINC 429 Speed to/from CMU No. 1 and CMU No. 2
.........
5--48
Table 5-10.
Cabin Packet Data Function (CPDF) . . . . . . . . . . . . . . . . . . . . . . . . .
5--49
Table 5-11.
ARINC 429 Bus Speed of AES ID Input . . . . . . . . . . . . . . . . . . . . . . .
5--49
Table 5-12.
Call Light On (Air/Ground Calls) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--49
Table 5-13.
Strap Parity (ODD) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--49
Table 5-14.
Cabin Communications System (CCS) . . . . . . . . . . . . . . . . . . . . . . . .
5--50
Table 5-15.
Inertial Reference System (IRS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--51
Table 5-16.
HPA/Antenna Subsystem Configuration . . . . . . . . . . . . . . . . . . . . . . .
5--52
Table 5-17.
CFDS/CMC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--53
Table 5-18.
SDU Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--54
Table 5-19.
SDU Number . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--54
Table 5-20.
CMU No. 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--55
Table 5-21.
CMU No. 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--55
Table 5-22.
MCDU/SCDU No. 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--55
Table 5-23.
MCDU/SCDU No. 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--55
Table 5-24.
MCDU/SCDU No. 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--56
Table 5-25.
Priority 4 Calls to/from Cockpit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--56
Table 5-26.
ARINC 429 Bus Speed to SCDU No. 1 / SCDU No. 2/
SCDU No. 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--57
Table 5-27.
Cockpit Voice Call Light/Chime Option . . . . . . . . . . . . . . . . . . . . . . . .
5--57
Table 5-28.
SDU Analog Interface No. 1 Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--58
Table 5-29.
SDU Analog Interface No. 2 Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . .
5--58
Table 5-30.
Cockpit Hookswitch Signaling Method . . . . . . . . . . . . . . . . . . . . . . . .
5--58
Table 6-1.
Levels of Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--3
23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
List of Tables (cont)
UP86308
Table
Page
Table 6-2.
HPA Indicators/Controls
....................................
6--9
Table 6-3.
SDU Indicators/Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--10
Table 6-4.
Level 1 Failure Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--12
Table 6-5.
List of Part Numbers
.......................................
6--17
Table 6-6.
MAR Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--19
Table 6-7.
LS Key/Line Pair Relations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--20
Table 6-8.
Special Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--23
Table 6-9.
System Configuration Pin Mapping . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--39
Table 6-10.
Textual Message Display (Page 6 -- Lines 4 thru 9) . . . . . . . . . . . . .
6--45
Table 6-11.
Textual Message Display (Page 7 -- Lines 4, 5, an 6) . . . . . . . . . . .
6--47
Table 6-12.
Textual Message Display (Page 9 -- Lines 8 and 9) . . . . . . . . . . . . .
6--51
Table 6-13.
Textual Message Display (Page 10 -- Lines 4 and 5) . . . . . . . . . . . .
6--53
Table 6-14.
Textual Message Display (Page 10 -- Lines 8 and 9) . . . . . . . . . . . .
6--53
Table 6-15.
DATA LOADER MENU Page Prompts . . . . . . . . . . . . . . . . . . . . . . . .
6--64
Table 6-16.
LRU Acronyms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--72
Table 6-17.
Boeing Level I Failure Messages and ATA Reference Numbers . .
6--90
Table 6-18.
Airbus Level I (SDU No. 1) Failure Messages and ATA No. . . . . . .
6--93
Table 6-19.
Airbus Level I (SDU No. 2) Failure Messages and ATA No. . . . . . .
6--100
Table 6-20.
McDonnell Douglas Level I Failures Messages and
ATA Reference Numbers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6--106
Table 6-21.
Commissioning and Maintenance Terminal Panel Lamps . . . . . . . .
6--111
Table 7-1.
Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7--1
Table A--1.1.
ECS Cables and Connectors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--2
Table A--1.2.
ECS Attenuators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--2
Table A--1.3.
HP--600 HPA (40W) Hardware Component Kit,
Part No. 998HQS--900--1XX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--7
Table A--1.4.
HP--700 HPA (20W) Hardware Component Kit,
Part No. 998HQS--904--1XX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--7
Table A--1.5.
SD--700 SDU Hardware Component Kit,
Part No. XXXXXX--XXX--1XX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--8
Table A--1.6.
BSU Hardware Component Kit, Part No. 970HQS--903--1XX . . . .
A--8
Table A--1.7.
Tray Assembly Part Numbers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--12
Table A--1.8.
ARINC 429 Data Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--17
23--20--27
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MCS--4000/7000
List of Tables (cont)
UP86308
Table
Page
Table A--1.9.
SCU Discrete Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--17
Table A--1.10.
SCU Error Code . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--18
Table A--1.11.
SCU Manual Signal Selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--19
Table A--1.12.
ARINC 561 Binary Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--20
Table A--1.13.
ARINC 561 BCD Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--20
Table A--1.14.
ARINC 571 Data, ARINC 429 Format . . . . . . . . . . . . . . . . . . . . . . . . .
A--21
Table A--1.15.
ARINC 571 Data, ARINC 419 Format . . . . . . . . . . . . . . . . . . . . . . . . .
A--21
Table A--1.16.
ARINC 404 Data, ARINC 429 Format . . . . . . . . . . . . . . . . . . . . . . . . .
A--21
Table A--1.17.
SCU Attitude Data Inputs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--22
Table A--1.18.
Contact Arrangements for SCU ARINC 600 Connector . . . . . . . . .
A--24
Table A--1.19.
Signal Source Select Lines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--28
Table A--1.20.
SCU Program Pin Combinations . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A--29
Table B--1.1.
Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B--2
Table B--1.2.
Air Filtration Systems from ECS for a Top Mount Assembly . . . . . .
B--2
Table B--1.3.
Air Filtration Systems from ECS for a Body--Mounted Design . . . .
B--3
Table B--1.4.
Air Filtration Systems from ECS for a Tray--Mounted Design . . . . .
B--3
Table C--1.2.
ORT Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C--1
23--20--27
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MCS--4000/7000
UP86308
Blank Page
23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
INTRODUCTION
1. How to Use this Manual
A. General
(1) The purpose of this manual is to help you install, operate, maintain, and troubleshoot
the MCS--4000/7000 Multi--Channel SATCOM System. Common system
maintenance procedures are not presented in this manual. The best established
shop and flight line practices should be used.
(2) This manual gives general system description and installation information for the
MCS--4000/7000 Multi--Channel SATCOM System. It also gives block diagram and
interconnect information to permit a general understanding of the system interface.
(3) Warnings, cautions, and notes in this manual give the data that follows:
• A WARNING gives a condition that, if you do not obey, can cause injury or death.
• A CAUTION gives a condition that, if you do not obey, can cause damage to the
equipment.
• A NOTE gives data to make the work easier or gives direction to go to a
procedure.
(4) Warnings and cautions go before the applicable paragraph or step. Notes follow the
applicable paragraph or step.
(5) All personnel who operate equipment and do the specified maintenance must know
and obey the safety precautions.
B. Symbols
(1) The symbols in Figure Intro--1 identify ESDS and moisture sensitive devices in this
manual, if applicable.
ESDS
Moisture Sensitive
Figure Intro--1.
Symbols
C. Weights and Measurements
UP86308
(1) All weights and measurements are in U.S. and SI (metric) values.
23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
2. Customer Support
A. Honeywell Aerospace Online Technical Publications Web Site
(1) If you have access to the Internet, go to the Honeywell Online Technical Publications
web site at http://portal.honeywell.com/wps/portal/aero to:
• Download or see publications online
• Make an order for a publication
• Tell Honeywell of a possible data error (report a discrepancy) in a publication.
B. Complete Customer Care Center
(1) If you do not have access to the Honeywell Online Technical Publications web site,
send an e--mail message or a fax, or speak to a person at the Complete Customer
Care Center:
• E--mail:
cas--publications--distribution@honeywell.com
• Fax:
602--822--7272
• Phone:
800--601--3099
(U.S.A.)
• Phone:
602--365--3099
(International).
(2) Also, the Complete Customer Care Center is available if you need to:
• Identify a change of address, telephone number, or e--mail address
• Make sure that you get the next revision of this manual.
3. References
A. Honeywell Publications
(1) The list that follows identifies Honeywell publications that are related to this manual:
• ATA No. 23--20--03 (Pub. No. A32--5111--008), HP--600 High Power Amplifier
Component Maintenance Manual
• ATA No. 23--20--25 (Pub No. A09--5111--025), HP--700 Watt High Power Amplifier
Component Maintenance Manual
• ATA No. 23--20--26 (Pub. No. A09--5111--026), SD--700 Satellite Data Unit
Component Maintenance Manual
• Pub. No. A09--1100--001, Handling, Storage, and Shipping Procedures for
Honeywell Avionics Equipment Instruction Manual
B. Other Publications
(1) These publications are standard references:
UP86308
• The United States Government Printing Office (GPO) Style Manual 2000
(available at http://www.gpoaccess.gov/stylemanual/browse.html)
23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
• ANSI/IEEE Std 260 (1978), Standard Letter Symbols for Units of Measurement
(available from the American National Standards Institute, New York, NY)
• ASME Y14.38--1999 (Formerly ASME Y1.1--1989), Abbreviations for Use on
Drawings and in Text (available from the American National Standards Institute,
New York, NY)
• ANSI/IEEE Std 315--1975 (Replaces ANSI Y32.2--1975), Graphic Symbols for
Electrical and Electronics Diagrams (available from the American National
Standards Institute, New York, NY)
• ANSI/IEEE Std 91 (1984), Graphic Symbols for Logic Functions (available from
the American National Standards Institute, New York, NY).
4. Acronyms and Abbreviations
A. General
(1) Refer to the list that follows for acronyms and abbreviations in this manual.
List of Acronyms and Abbreviations
Full Term
UP86308
Term
AAC
Aeronautical Administrative Communications
ACARS
Aircraft Communications Addressing and Reporting System
ACP
audio control panel
ACU
antenna control unit
ADL
airborne data loader
ADS
automatic dependent surveillance
APC
Aeronautical passenger communications
AES
aircraft earth station
AFIS
aircraft flight information system
AMS
audio management system
AMU
audio managment unit
AOC
Aeronautical Operational Control
AOR--E
Atlantic Ocean Region--East
AOR--W
Atlantic Ocean Region--West
APBX
analog private branch exchange
APC
Aeronautical passenger communications
APHONE
analog telephone
APOS
actual power out status
ARINC
Aeronautical Radio, Inc.
23--20--27
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MCS--4000/7000
List of Acronyms and Abbreviations (cont)
UP86308
Term
Full Term
ATA
Air Transport Association
ATC
air traffic control
ATS
air traffic services
BIT
built--in test
BITE
built--in test equipment
BSU
beam steering unit
CAIMS
central aircraft information and maintenance system
CCA
circuit card assembly
CCS
cabin communications system
CF/M
cubic feet per minute
CFDIU
centralized fault display interface unit
CFDS
central fault display system
CGU
communications gateway unit
CLR
clear
CM
continuous monitoring
CMC
central maintenance computer
CMT
commissioning and maintenance terminal
CMU
communications management unit
CPDF
cabin packet data function
CRC
cyclic redundancy check
CTM
cabin telecommunications
CTU
cabin telecommunications unit
D/LNA
diplexer/low noise amplifier
DEL
delete
DIP
dual in--line packaging
DIU
data interface unit
DTE
data terminal equipment
DTMF
dual tone multifrequency
ECS
electronic cable specialists
EIRP
effective isotopic radiated power
23--20--27
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MCS--4000/7000
List of Acronyms and Abbreviations (cont)
UP86308
Term
Full Term
FAX
facsimile
FMC
flight management computer
FWP
fault warning processor
GES
ground earth station
GMT
Greenwich Mean Time
GSDB
GES--specific data broadcast
GSPD
groundspeed
HGA
high gain antenna
HMN
Honeywell Material Number
HPA
high power amplifier
HPR
high power relay
I/O
input/output
ICAO
International Civil Aviation Organization
ID
identification
IGA
intermediate gain antenna
INMARSAT
International Maritime Satellite Organization
INS
inertial navigation system
IOR
Indian Ocean Region
IPC
illustrated parts catalog
IRS
inertial reference system
ISO
International Standards Organization
ISU
initial signal unit
ITU
International Telecommunications Union
LED
light emitting diode
LGA
low gain antenna
LRU
line replaceable unit
LS
line select
MAR
maintenance activity record
MCDU
multifunction control display unit
MCS
MCS--4000/7000 Multi--Channel SATCOM
23--20--27
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MCS--4000/7000
List of Acronyms and Abbreviations (cont)
UP86308
Term
Full Term
MCU
modular concept unit
MEL
minimum equipment list
MTBF
mean--time--between--failure
MU
management unit
NVM
non--volatile memory
OCXO
oven controlled crystal oscillator
OEM
Original Equipment Manufacturer
OMS
onboard maintenance system
ORT
owner requirements table
PABX
private automatic branch exchange
PAST
person--activated self--test
PDL
portable data loader
PF
power factor
PLO
phase--locked oscillator
PMAT
portable maintenance access terminal
POC
power--on counter
POR
Pacific Ocean Region
POST
power--on self--test
PROM
programmable read--only memory
PSTN
Public Switched Telephone Network
PSU
power supply unit
PTT
push--to--talk
RFM
radio frequency module
RFU
radio frequency unit
RFUIA
radio frequency unit interface adapter
RTC
real--time clock
RTCA
radio technical commission for aeronautics
SAL
system address label
SCDU
SATCOM control and display unit
SCPC
single channel per carrier
23--20--27
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MCS--4000/7000
List of Acronyms and Abbreviations (cont)
UP86308
Term
Full Term
SCU
signal conditioning unit
SDI
source destination identifier
SDU
satellite data unit
SITA
Satellite Aircom
SMT
surface mount technology
SRU
shop replaceable unit
SSM
sign--status matrix
TDM
time division multiplex
TDMA
time division multiple access
TIF
terminal interface function
TOTC
total on--time clock
TSPO
time since power--on
TTCM
triple transcoder modem
UTC
universal time coordinated
VCM
voice codec module
VSWR
voltage standing wave ratio
XTB
cross--talk bus
23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
5. Maximum Permissible Exposure Level
A. General
(1) The radio frequency energy generated by the MCS system may be hazardous to
personal health. To eliminate the potential danger, Honeywell recommends that
operators of the MCS system implement safety procedures.
(2) When the MCS system is in operation, personnel should remain at a distance from
the antenna that is greater than the maximum permissible exposure level (MPEL)
radius. Because there are many possible antenna locations, antenna gains, and
system output powers, it is the responsibility of the operator to ascertain the MPEL
radius for their MCS system configuration and train their personnel in safe ground
procedures. The following warnings state Honeywell’s MPEL recommendations for
both high and low gain antennas.
WARNING: TO AVOID POTENTIALLY DANGEROUS EXPOSURE TO RADIO
FREQUENCY ENERGY ABOVE THE ANSI C95.1 LIMIT AND OTHER
WORLD STANDARDS (SEE FIGURE INTRO--2) WHEN USING A HIGH
GAIN ANTENNA (12 dB NOMINAL ANTENNA), DO NOT OPERATE THE
MCS SYSTEM WHEN ANY PERSONNEL ARE WITHIN 8.5 FEET OF THE
ANTENNA OR WITHIN 20 FEET OF THE ANTENNA FOR PERIODS OF
LONGER THAN 3 MINUTES PER HOUR.
WARNING: TO AVOID POTENTIALLY DANGEROUS EXPOSURE TO RADIO
FREQUENCY ENERGY ABOVE THE ANSI C95.1 LIMIT AND OTHER
WORLD STANDARDS (SEE FIGURE INTRO--2) WHEN USING AN
INTERMEDIATE GAIN ANTENNA (6 dB NOMINAL ANTENNA), DO NOT
OPERATE THE MCS SYSTEM WHEN ANY PERSONNEL ARE WITHIN 3
FEET OF THE ANTENNA OR WITHIN 6 FEET OF THE ANTENNA FOR
PERIODS OF LONGER THAN 3 MINUTES PER HOUR.
UP86308
WARNING: TO AVOID POTENTIALLY DANGEROUS EXPOSURE TO RADIO
FREQUENCY ENERGY ABOVE THE ANSI C95.1 LIMIT AND OTHER
WORLD STANDARDS (SEE FIGURE INTRO--2) WHEN USING A LOW
GAIN ANTENNA (0 dB NOMINAL ANTENNA), DO NOT OPERATE THE
MCS SYSTEM WHEN ANY PERSONNEL ARE WITHIN 1.5 FEET OF THE
ANTENNA OR WITHIN 3 FEET OF THE ANTENNA FOR PERIODS OF
LONGER THAN 3 MINUTES PER HOUR.
23--20--27
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MCS--4000/7000
UP86308
Figure Intro--2.
Radio Frequency Energy Levels
23--20--27
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UP86308
Blank Page
23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
SECTION 1
SYSTEM DESCRIPTION
1. Overview
A. General
(1) The MCS--4000/7000 Multi-Channel SATCOM (MCS) system is a mobile avionics
communications system that supplies continuous worldwide voice and data
communications services to and from the aircraft through satellite. The MCS system
interfaces at baseband with various avionics data equipment, as well as with crew
and passenger voice equipment on–board the aircraft. It interfaces with the antenna
subsystem through L--band RF signals that emanate from (and are received by)
satellites in geostationary orbit. These satellites then convey the information to and
from ground stations that interface with the terrestrial telephone network.
(2) The MCS system augments and/or supersedes the present high frequency
transceiver by supplying higher quality voice service and by supplying data services
at higher bit rates needed by some future datalink (ATN) applications, such as
automatic dependent surveillance (ADS) and an international aircraft communications
addressing and reporting system (ACARS). Additional services include cockpit
communications with administrative and operational personnel and with
governmental bodies such as air traffic services (ATS). The system is designed to
ensure that communications for safety and regularity of flight are not delayed by the
transmission and reception of other types of messages.
(3) The MCS--4000/7000 system supports seven communication channels capable of
simultaneous full duplex voice communications and one channel of data
communications. The MCS--4000 system operates identically to the MCS--7000
except four communication channels rather than seven are supplied. Both the
MCS--7000 and MCS--4000 SATCOM systems supply one channel of data
communications. The MCS system accommodates the four categories of
communications:
•
•
•
•
Air traffic control (ATC)
Aeronautical operational control (AOC)
Aeronautical administrative communications (AAC)
Aeronautical passenger communications (APC).
(4) The four communication categories are recognized by the International Civil Aviation
Organization (ICAO) and the International Telecommunications Union (ITU), and
have been assigned priorities for communications purposes.
(5) The total aviation satellite communications system, shown in Figure 1-1, is made up
of the following:
UP86308
•
•
•
•
Aircraft earth station (airborne avionics subsystems and antenna subsystem)
Space segment (satellite network)
Ground earth stations
Terrestrial data and voice networks.
23--20--27
Page 1--1
30 Aug 2002
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MCS--4000/7000 Multi--Channel SATCOM System
Figure 1-1.
Aviation Satellite Communications System
B. Aircraft Earth Station
(1) General
(a) The aircraft earth station (AES) is fully compliant with requirements of
Aeronautical Radio, Inc (ARINC) Characteristics 741/761. Standard interfaces
between the MCS avionics and other aircraft avionics enable the AES to accept
data and voice messages from various sources, encode and modulate this
information onto appropriate RF carrier frequencies, and transmit these carriers
to the space segment for relay to a ground earth station (GES). The AES also
receives RF signals from a GES through the satellite, demodulates these
signals, performs the necessary decoding of the encoded messages, and
outputs the data or voice message for use by either the pilot, copilot,or the
passengers.
(2) AES Components
(a) General
A block diagram of the AES is shown in Figure 1-2. The AES is made up of
the following components:
• MCS avionics
• Antenna subsystem
• Cabin communications services
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• Analog connected telephones
• Cockpit voice sources
• Aircraft avionics.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Figure 1-2.
Aircraft Earth Station Block Diagram
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(b) MCS Avionics
The MCS avionics are made up of the satellite data unit (SDU) and high
power amplifier (HPA). The SDU supplies the interface to all aircraft avionics,
and implements all functionality associated with modulation/demodulation,
error correction, channel rate/frequency selection, and RF translation for
seven communication channels. The SDU supports seven communication
channels capable of simultaneous full duplex voice and data communication
services. The SDU manages the RF link protocols on the satellite side and
supplies the system interface with communications management avionics.
The SDU interface to other aircraft avionics involves the exchange of ARINC
429 and discrete data.
A cockpit audio system conveys cockpit voice to and from the SDU.
Messages requiring cockpit action or initiation appear on the multifunction
control display unit (MCDU) and/or other cockpit annunciators. The
communications management unit (CMU) or equivalent routes packet data
messages to and from the SDU. Cabin communications use either a cabin
communications system (CCS) or an analog equivalent (cabin unit) to supply
voice telephony communication. Enhancements supply facsimile (FAX)
service and secure voice and personal computer modem interfaces.
The SDU supplies all essential services required to accommodate effective
air/ground communications through satellite using the antenna and related
RF components. Both the 40 Watt and 20 Watt HPAs supply linear power
amplification to boost the RF signals up to the power levels required for
transmitting to the satellite. In addition, the 20 Watt HPA (used primarily for
the intermediate gain antenna) supports a beam steering function which
converts tracking and pointing coordinates from the SDU into signals
needed to select the desired (beam) direction towards the satellite.
Two additional LRUs may be required for some aircraft configurations:
• Radio frequency unit interface adapter (RFUIA)
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• Signal conditioning unit (SCU).
The RFUIA is used in place of the radio frequency unit (RFU) in the
MCS--7000 system.
The SCU is used in MCS installations on older generation aircraft having an
inertial navigation system (INS) that does not output navigation data in an
ARINC 429 high speed format which is consistent with the ARINC 704
characteristic.
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(c) Antenna Subsystem
The primary function of the antenna subsystem is to complete the
communication link between the GES, the space segment, and the AES.
The diplexer is a three-port RF device (antenna, transmit, and receive),
which supplies signal routing and filtering functions. Signals in the receive
band are routed from the antenna port to the receive port, and transmit
signals are routed from the transmit port to the antenna port. The low noise
amplifier establishes the noise floor of the communication system by
boosting the signals and noise received from the antenna to a level much
greater than the noise level of subsequent components in the receive path.
The high gain antenna (HGA) and intermediate gain antenna (IGA) transmit
L--band RF signals from the HPA to a satellite, and receive L--band RF
signals from a satellite for the SDU. The low gain antenna (LGA) supplies
backup communications (packet data only) for the high gain antenna or
intermediate gain antenna by supplying low rate packet data communication
services.
The beam steering unit used in the HGA system converts tracking and
pointing coordinates (aircraft relative azimuth and elevation) from the SDU
into signals needed to select the antenna array elements in combinations
that point the antenna beam in the desired direction towards the satellite. An
antenna control unit (ACU) is required for mechanically steered antenna
arrays. The antenna control unit translates digitized beam position data and
beam position change commands from the SDU into a format needed to
position the antenna beam in the desired direction toward the satellite. A
beam steering function is incorporated into the 20 Watt HPA for use with the
IGA.
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(d) Cabin Communications System (CCS)
The CCS, in conjunction with the MCS avionics and a worldwide network of
ground stations, supplies cabin services such as telephone, facsimile, and
other communication interfaces. The CCS is partitioned into two sections:
the cabin telecommunications unit (CTU) and cabin/passenger
communications equipment (digitally connected telephones).
The CTU performs onboard private automatic branch exchange (PABX)
telephony functions letting the digitally connected telephones make the best
use of resources supplied by the MCS avionics. The CTU supplies the
interface between the digitally connected phones and the SDU. A
specialized interface conversion function supplies compatibility between the
ARINC 746 CTU and the ARINC 741/761 SDU. This interface is made up of
a high-speed (CEPT--E1) serial bus pair that accommodates up to 32
digitized voice channels along with status and control information.
The digitally connected phones (handsets) are primarily supplied for
passenger use and can be located throughout the aircraft. The digital
handsets interface indirectly to the satellite communications equipment and
are controlled by the CCS.
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(e) Analog Connected Telephones
(f)
The SDU has provisions to support up to two simultaneous analog audio
channels. Each analog channel supports two interface types:
Global-Wulfsberg Flitephone WH--10 and the analog private branch
exchange (APBX). The WH--10 is a stand-alone handset with a 12-button
keypad. The APBX has analog trunk lines and in-line dual tone
multifrequency (DTMF) signaling.
Cockpit Voice Sources
The SDU supports headset interfaces for cockpit use only. These interfaces
incorporate off-hook/on-hook signaling and dialing through the combination
of a control and display unit (either [SATCOM control and display unit] SCDU
or MCDU), and push-to-talk (PTT) or similar switches. When the PTT switch
is pushed, a microphone audio signal is sent to the selected voice channel
and a discrete signal is sent to the SDU. An audible chime and call lamps
announce call connections.
(g) Aircraft Avionics
Standard interfaces between the MCS avionics and the other aircraft
avionics include the following:
• Communications management unit (CMU), or the management unit (MU)
of the Aircraft Communications Addressing and Reporting System
(ACARS), where installed.
• SATCOM control and display unit (SCDU), where installed, to supply an
interface to the MCS system for system log-on, GES selection, cockpit
voice call setup, data loading, and to access the SATCOM maintenance
pages including fault messages.
• Central fault display system (CFDS), central maintenance computer
(CMC), or on--board maintenance system (OMS), where installed, for fault
reporting.
• The inertial reference system (IRS), where installed, to supply the SDU
with navigation coordinates for positioning the antenna platform.
• Channels are also supplied for voice and data communication with ATC
to support departure clearances by datalink, as well as ADS for non radar
position reporting in oceanic regions.
• There is an ARINC 615 Airborne or portable data loader (ADL or PDL) for
uploading operational software and the owner requirements table (ORT).
Connections are made through front and back panel connectors on the
MCS avionics LRUs.
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• The 24-bit ICAO address identifies the aircraft in which the SDU is
installed. Address pins identified to take on the binary one state must be
left open. Address pins identified to take on the binary zero state must be
wired to address common on the airframe side of the connector. ARINC
429 interface options for the ICAO address are also supplied.
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(3) AES Classifications
(a) Each AES is classified according to the configuration and dynamic capabilities of
its aircraft avionics and antenna subsystem. An AES can be fitted with any
combination of the classes of installations given in Table 1-1.
Table 1-1.
Class
Classes of Installations
Description
A Class 1 AES installation uses a low gain antenna only and supplies low rate
packet-mode data services only.
A Class 2 AES installation uses a high gain antenna or intermediate gain antenna,
and supplies telephony and optional circuit-mode services.
A Class 3 AES installation uses a high gain antenna or intermediate gain antenna,
and supplies telephony services, packet-mode data services, and optional
circuit-mode data services.
A Class 4 AES installation uses a high gain antenna or intermediate gain antenna,
and supplies packet-mode data services only.
(4) GES Communication Links
(a) The MCS avionics supply access to ground-based networks through the ground
earth stations. Each GES supplies system synchronization and coordination
through ground-to-aircraft transmissions. Four types of RF channels are defined
for use with the MCS avionics as given in Table 1-2.
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Table 1-2.
Types of RF Channels
RF Channel
Description
P--Channel
Packet-mode time division multiplex (TDM) channel used in the forward (outbound)
direction (ground-to-aircraft) to carry signaling and packet-mode data. The
transmission is continuous from each GES in the satellite network.
R--Channel
Random access (slotted Aloha) channel used in the return (inbound) direction
(aircraft-to-ground) to carry signaling and packet-mode data, specifically the initial
signals of a transaction (typically request signals).
T--Channel
Reservation time division multiple access (TDMA) channel used in the return
direction only. The receiving GES reserves time slots for transmissions requested
by an AES according to message length. The sending AES transmits the
messages in the reserved time slots.
C--Channel
Circuit-mode single channel per carrier (SCPC) channel used in both forward and
return directions to carry digital voice or data/facsimile traffic. The use of the
channel is controlled by assignment and release signaling at the start and end of
each call or FAX transmission.
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C. Space Segment
(1) The space segment is made up of satellites placed in geostationary orbits to supply
air-ground packet-switched data services and voice communications, both of which
use worldwide standardized conventions and capabilities. The satellites function as
communication transponders to support L--band links to and from the aircraft, and
supply links to and from ground earth stations. The space segment supplier for airline
aeronautical satellite communications is the International Maritime Satellite
Organization (INMARSAT), whose system supplies worldwide coverage. The
four-region satellite system supplied by INMARSAT is shown in Figure 1-3.
D. Ground Earth Station
(1) Each GES has the necessary equipment to communicate with terrestrial networks
and communicate through satellites with the aircraft. The ground earth stations are
designed to supply the airline customer with a diverse routing of national and
international voice and data communications through submarine cable, satellite, and
microwave links to all destinations. Automatic traffic management systems ensure
efficient routing of communications by using optimum links into public switched
telephone networks (PSTN) and avoiding multiple satellite connections whenever
possible.
(2) Ground earth stations are located strategically around the globe to supply
redundancy and diversity in the terrestrial extension of communications. Aircraft are
connected to a GES through an in-view satellite depending on the service
preference settings encoded in the SDU ORT. Some problems may be encountered
when the aircraft flies in polar regions with a latitude greater than 75 degrees.
E.
Terrestrial Data and Voice Networks
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(1) Data and voice services available through satellites and ground earth stations include
9.6 and 4.8 kilobit/second digital voice, and packet-mode data at RF channel rates
ranging from 600 bit/second up to 10.5 kilobit/second. The present worldwide
complement of ground earth stations including location, operator, and coverage
region are summarized in Table 1-3. Aeronautical communications through the
INMARSAT satellites are transmitted to and from the terrestrial phone and data
networks through these ground earth stations. The satellite regions that service these
ground earth stations are shown in Figure 1-4.
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MCS--4000/7000 Multi--Channel SATCOM System
Table 1-3.
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GES Name
Ground Earth Stations
GES ID
SAT ID
Service Provider
Goonhilly--AW
001
000 (AOR--W)
Stratos
Southbury--AW
002
000
Telenor
Eik--AW
004
000
Telenor
Aussaguel--AW
005
000
Satellite Aircom (SITA)
Goonhilly--AE
101
001 (AOR--E)
Stratos
Aussaguel--AE
103
001
SITA
Eik--AE
104
001
Telenor
Sentosa--P
201
002 (POR)
Sing--Tel
Santa Paula--P
202
002
Telenor
Yamaguchi--P
203
002
KDD
Perth--P
205
002
SITA
Eik--I
301
003 (IOR)
Telenor
Nunthaburi--I
302
003
Telenor
Perth--I
305
003
SITA
Yamaguchi--I
306
003
KDD
Sentosa--I
310
003
Sing--Tel
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Figure 1-4.
INMARSAT Four-Region Satellite Coverage
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MCS--4000/7000
2. System Components
A. General
(1) The MCS avionics is comprised of the following components:
• Satellite data unit (SDU)
• High power amplifier (HPA).
(2) These components are compatible with ARINC Characteristic 741. Table 1-4 gives
the MCS system components supplied by Honeywell. Table 1-5 gives the MCS
system components not supplied by Honeywell. Table 1-6 thru Table 1-8 give system
component configuration information.
Table 1-4.
System Components Supplied by Honeywell
Component
Model No.
Honeywell Part No.
Satellite Data Unit
SD--700
7516118--xxyyy
High Power Amplifier (40 W)
HP--600
7516250--xxyyy
High Power Amplifier (20 W)
HP--700
7516251--xxyyy
Figure 1-6
Figure 1-7
Figure 1-7
Diplexer/Low Noise Amplifier -- Aero--I
-- --
7516193--901
Intermediate Gain Antenna
-- --
7516194--901
Radio Frequency Unit Interface Adapter (RFUIA) 1.
-- --
7516222--901
NOTES:
1.
The five digit dash number (xxyyy) corresponds to the hardware/software version of the unit where the first two
digits correspond to the hardware version and the last three digits correspond to the software version.
2.
The RFUIA is installed with the 115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data), or 28 V dc.
Table 1-5.
System Components Not Supplied by Honeywell
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Component
Comments
SDU Installation Equipment (See Note)
ARINC 600 6--MCU tray, cables, connectors, assemblies,
mounting hardware, and kits
HPA (40 W) Installation Equipment
(See Note)
ARINC 600 8--MCU tray, cables, connectors, assemblies,
mounting hardware, and kits
HPA (20 W) Installation Equipment
(See Note)
ARINC 600 4--MCU tray, cables, connectors, assemblies,
mounting hardware, and kits
Signal Conditioning Unit (SCU)
RACAL Part No. 56047--010XX
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TEMPORARY REVISION NO. 23-2
INSERT PAGE 2 OF 3 FACING PAGE 1-13.
Reason:
To add PN 7516118-77010 and PN 7516118-74010, and to change description for PNs
75166118-27020 and -24020 in Table 1-6.
Table 1-6 is changed as follows:
Table 1-6. SDU Configurations
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SDU Part Number
Description
7516118-27010
115 V ac/400 Hz, 7-channel SOU (6 voice, 1 data)
7516118-77010
115 V ac/400 Hz, 7-channel SDU (6 voice, 1 data), Digital RFM
7516118-57010
+28 V dc, 7- channel SOU (6 voice, 1 data)
7516118-24010
115 V ac/400 Hz, 4-channel SOU (3 voice, 1 data)
7516118-74010
115 V ac/400 Hz, 4-channel SDU (3 voice, 1 data), Digital RFM
7516118-54010
+28 V dc, 4- channel SOU (3 voice, 1 data)
7516118-27020
115 V ac/400 Hz, 7-channel SDU (6 voice, 1 data) for Airbus
applications, (HW MOD J contains Digital RFM)
7516118-24020
115 V ac/400 Hz, 4-channel SDU (6 voice, 1 data) for EPIC
applications, (HW MOD J contains Digital RFM)
7516118-27011
115 V ac/400 Hz, 7-channel SOU (6 voice, 1 data) for EPIC
applications
7516118-57011
+28 V dc, 7-channel SOU (6 voice, 1 data) for EPIC applications
7516118-24011
115 V ac/400 Hz, 4-channel SOU (3 voice, 1 data) for EPIC
applications
7516118-54011
+28 V dc, 4- channel SOU (3 voice, 1 data) for EPIC applications
23-20-27
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See TR
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
System Components Not Supplied by Honeywell (cont)
Table 1-5.
Component
Comments
High Gain Antenna Equipment
BAE Systems -- Canada
Ball Aerospace -- USA
Dassault Electroniq -- France
NOTE: Installation of this equipment is dependent on the specific requirements of the operator. Refer to
Appendix A, Vendor Equipment, for additional information.
Table 1-6.
SDU Configurations
SDU Part Number
Description
7516118--27010
115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data)
7516118--57010
+28 V dc, 7--channel SDU (6 voice, 1 data)
7516118--24010
115 V ac/400 Hz, 4--channel SDU (3 voice, 1 data)
7516118--54010
+28 V dc, 4--channel SDU (3 voice, 1 data)
7516118--27020
115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data) for Airbus
applications
7516118--24020
115 V ac/400 Hz, 4--channel SDU (3 voice, 1 data) for Airbus
applications
7516118--27011
115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data) for EPIC
applications
7516118--57011
+28 V dc, 7--channel SDU (6 voice, 1 data) for EPIC applications
7516118--24011
115 V ac/400 Hz, 4--channel SDU (3 voice, 1 data) for EPIC
applications
7516118--54011
+28 V dc, 4--channel SDU (3 voice, 1 data) for EPIC applications
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Table 1-7.
HPA (40 Watt) Configurations
HPA Part No.
Software
Package
7516250--10001
3--channel initial release
7516250--15020
3--channel update with cabin voice
7516250--18033
C0.0
6--channel cabin voice and data (1--data, 5--voice) and fax
(2400/4800 bps)
7516250--18036
C2.0
6--channel cabin voice and data (1--data, 5--voice) and fax
(2400/4800 bps)
7516250--19034
C3.0
Improves log--on capability and reversion; adds maintenance
pages
7516250--19037
C3.5
Adds Boeing 777 capability
Description
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Table 1-7.
HPA (40 Watt) Configurations (cont)
HPA Part No.
Software
Package
7516250--19037
C3.5
Adds Boeing 777 capability
7516250--20050
D2.0
Adds several improvements to BITE, including antenna VSWR
detection reporting and compatibility with hardware Mod D
(Software Mod F); Uses 115 V ac primary power.
7516250--55050
D2.0
Adds several improvements to BITE, including antenna VSWR
detection reporting and compatibility with hardware Mod D
(Software Mod F); Uses 115 V ac primary power.
7516250--60001
3--channel initial release
7516250--60020
3--channel update with cabin voice
7516250--60033
C0.0
6--channel cabin voice and data (1--data, 5--voice) and fax
(2400/4800 bps)
7516250--60050
D2.0
Adds several improvements to BITE, including antenna VSWR
detection reporting and compatibility with hardware Mod D
(Software Mod F); Uses 28 V dc primary power.
Description
NOTE: For the various part numbers, --1XXXX refers to an air transport LRU, while --55XXX and --6XXXX
refers to a business and commuter LRU. The functional descriptions are the same for both.
Table 1-8.
HPA (20 Watt) Configurations
HPA Part Number
Software
Package
7516251--20060
E1.5
20 Watt HPA with Aero--I IGA beam steering functionality; Uses
115 V ac or 28 V dc power supply.
7516251--60060
E1.5
20 Watt HPA with Aero--I IGA beam steering functionality; Uses
115 V ac or 28 V dc power supply.
Description
NOTE: For the various part numbers, --2XXXX refers to an air transport LRU, while --6XXXX refers to a
business and commuter LRU. The functional descriptions are the same for both.
3. System Description
A. General
(1) The system description gives a general overview and summary of the features and
interfaces that the MCS implements. Figure 1-7 is a simplified block diagram of the
MCS system.
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(2) The core of the AES avionics subsystem is the MCS avionics, supporting data, and
voice communications at rates from 600 to 21,000 bits per second. Interfaces to
various aircraft systems including cockpit voice, cabin voice/data, aircraft avionics,
and the antenna subsystem enable the MCS avionics to handle data and voice
messaging functions for the AES.
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(3) The SDU supplies all essential services required to accommodate effective
air/ground communications through satellite, using the antenna and related RF
components. The SDU manages the RF link protocols on the AES side and supplies
the system interface with communications management avionics. The HPA boosts
the signal to be transmitted up to the power levels required for transmission to the
satellite.
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Blank Page
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Figure 1--4.
MCS Avionics Block Diagram
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B. Satellite Data Unit
(1) General
(a) The SDU is the core element of the MCS avionics and is responsible for overall
AES control and monitoring. The unit interfaces to many aircraft avionics (e.g.,
CFDS, primary/secondary IRS, CMU 1/2, MCDU 1/2/3, ADL, etc) and has
operational functionality, including coding and decoding all system voice and
data signals and defining system protocols. The SDU contains six channels
capable of supplying simultaneous full duplex voice communication, one channel
of data 2/3 communication, and RF circuitry sufficient to operate the AES.
Figure 1-5 shows the circuit card assembly (CCA) layout for the MCS--7000
SDU. Removal of one of the triple transcoder modem (TTCM) CCA results in the
MCS--4000 SDU.
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Figure 1-5.
MCS--4000/7000 SDU Equipment Description
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(b) The format for voice/data codes follows the INMARSAT system definitions for
voice and data transmission and reception. The INMARSAT system uses a
digital format for voice and data. The SDU digitizes the voice or data signal and
adds special codes to make the aircraft-to-ground station connection possible.
Voice signals are transmitted at a rate designed to supply high voice quality
(perceived quality is close to that of a good quality public telephone line). When
signal processing is complete, the coded voice/data signal is sent to HPA. The
SDU also controls the protocols for automatic call, setup, and clear-down.
System protocols are defined so the designated GES recognizes it is being
called by the AES.
(c) The SDU houses the voice interface modules and transcoder modems required
for voice and data service, and the RF transmit/receive circuitry needed to
convert modulated baseband signals to an L-band frequency (and vice versa).
All AES satellite signals use digital coding and modulation, which include the
voice circuits. The voice interface modules translate baseband analog voice
signals to and from the 9600 bps or 4800 bps digital coding standard. Efficient
information compression and coding techniques supply high voice quality at an
economical bit rate. The modems, one for each communication channel, perform
all of the physical layer signal processing functions, including
multiplexing/demultiplexing, interleaving/de--interleaving,
scrambling/unscrambling, modulation/demodulation, and Doppler effect
correction.
(d) The SDU system table memory contains the location of all satellites. When a
GES is selected, the SDU uses this location information and aircraft positional
information (through an ARINC 429 interface) from the IRS to compute the
position of the satellite relative to the aircraft. The SDU then transmits pointing
and tracking coordinates (aircraft relative azimuth and elevation) to the beam
steering unit (BSU) to permit optimum signal transmission and reception between
the high gain antenna subsystem and the satellite.
(e) The high gain antenna subsystem translates these steering commands into
control signals to the antenna(s). Once the beam has been steered toward the
satellite, the SDU receives the pilot tone from the satellite transponder through
its receive RF link from the antenna subsystem.
UP86308
(f)
The SDU is now free to route communications data over the satellite link. The
SDU accomplishes this by sending commands to the MU and the CTU. These
commands are sent through ARINC 429 and CEPT E1 interfaces between the
SDU and the MU/CTU. Data is then routed from the MU/CTU to the SDU. In the
SDU, the baseband data modulates RF carriers, which are sent to the HPA for
amplification, and then to the antenna subsystem for transmission to the satellite.
The SDU can adjust the transmission frequency in one-Hertz increments to
compensate for the Doppler shift caused by the speed of the aircraft. The
receive mode is handled in a similar manner. Since the MCS is a full-duplex
system, the transmit and receive signals are processed simultaneously as in
conventional terrestrial telephone equipment.
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(2) Output Power Control
(a) General
The AES output power to the satellite, specified and calculated as effective
isotopic radiated power (EIRP) from the antenna in the direction of the
satellite, is controlled by the SDU as specified in the following paragraphs.
The SDU is capable of controlling up to one HGA HPA, one LGA HPA, or
one IGA HPA. These HPA(s) can be a linear or class C type in any
combination. The SDU does not establish a C-channel voice call using a
class C HGA HPA or through any LGA HPA.
(b) Assumed Initial C-Channel EIRP
The SDU calculates the assumed initial C-channel EIRP as being the lowest
of the currently GES-commanded EIRPs for any/all C-channels in progress.
If there are no C-channels currently in progress, the SDU uses the value in
ORT item xxx, or the value in ORT item xxx reduced by 6 dB if the SDU is
currently logged on through a spot-beam.
(c) Current Reserved EIRP
The SDU calculates the current reserved EIRP as the summation in Watts of
the following EIRPs:
• The power reserved for the R/T-channel transmission, for the highest bit
rate assigned, calculated from the EIRP assigned in the log-on confirm
signal, or the most recent data channel reassignment, if any.
• The GES-assigned EIRPs of all the currently active C-channel carriers, if
any.
• The cockpit reserved channel power if the reservation has been made
through ORT option vii and is not in use. This continuously tracks the
assumed initial C-channel EIRP. If it is in use, then the actual
GES-assigned EIRP is used.
• The power reserved for any C-channel calls in the process of being set
up (i.e., after resources have been allocated but no C-channel
assignment signal has been received). For each such channel, the
assumed initial C-channel EIRP is used.
(d) Current and Projected or Peak-To-Average Power Ratio
UP86308
If the HPA is linear, the SDU calculates the current peak-to-average power
ratio based on the EIRP levels for all the carriers considered in the current
reserved EIRP calculation. The current peak-to-average ratio value is sent to
the HPA periodically, alternating with the projected peak-to-average ratio
(i.e., what the peak-to-average ratio would be if one additional C-channel
were established).
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The SDU waits at least 450 milliseconds after transmitting the HPA
command word before assuming the received HPA maximum available RMS
output power corresponds to the most recently sent peak-to-average ratio in
the HPA command words. The current peak-to-average ratio is sent in order
to calculate the current available EIRP from the returned maximum available
RMS power. The projected peak-to-average ratio is sent in order to
determine (along with other criteria) if an additional C-channel can be
established, if and when it is requested. If all carriers are at the same power
level (not true in general), the peak-to-average ratio is equal to the number
of carriers. If the HPA is class C, the SDU always sends a peak-to-average
ratio equal to 1.
(3) Installation Dependent Considerations
(a) General
The SDU stores the following installation dependent values to enable it to
set the EIRPs accurately:
• SDU to HPA loss (assumed common for both LGA and HGA HPAs)
• HPA to antenna loss (two values are stored, one for the HGA HPA, and a
separate value for the LGA HPA)
• HPA in use is class C, the SDU stores the HPA maximum output power.
(b) SDU to HPA Loss
The SDU stores the calibrated SDU to HPA loss in nonvolatile memory.
When the HPA is linear, this value is calculated once whenever there is an
R--or T--channel burst transmission in the absence of C--channel
transmission. This value is also calculated whenever there is a single
C--channel transmission in the absence of R-- or T--channel, unless the
reported actual power output value in the HPA status word:
• Matches or is less than the minimum reportable actual power value stored
in ORT item xxix
• Matches either the unique code 00100B for at/below measurable range
or 3 dB greater than 40 W or the flag was set indicating the HPA or
modem backoff was limited.
UP86308
When a single measurable carrier (R--/T--or C--channel) is present, the SDU
recalculates the SDU to HPA loss as the actual output power reported by the
HPA, less the HPA nominal gain, plus the HPA backoff, or SDU calculated
RFM power. This value includes the actual cable loss, plus any
uncompensated variation from nominal in the HPA gain, and any variation
from the calibrated RFM output power (due to temperature). This value also
lets the SDU accurately determine the common transmit gain. If the
calibration results in a value outside the range of 10 dB to 30 dB, a failure is
raised for the HGA HPA and LGA HPA.
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(c) HPA to Antenna Loss
The SDU is capable of storing in nonvolatile memory the actual loss (to the
nearest tenth of a dB) between the HPA and the input to the antenna for use
in the power control computation. This loss is the sum of the HPA to diplexer
cable loss, the high power relay loss (if used), the diplexer loss, and the
diplexer to antenna cable loss in an ARINC 741 system. This value is
expected to be between 0.9 and 2.5 dB, but the SDU allows the entry of
values in the range of 0.0 to 5.0 dB. A separate value is maintained and
used for each antenna subsystem.
This loss value is necessary to enable the SDU to accurately set the
antenna EIRPs, and to determine power availability for additional
C-channels. This value is not part of the ORT and is not an option. The
value is estimated/calibrated at the time of system installation or
commissioning, and can vary among otherwise identical installations. It is
inadequate to assume a default of either end of the range, since at the low
end the AES would not necessarily make the return link in marginal
conditions. At the high end, the SDU would radiate all carriers high, wasting
power and prematurely inhibiting further calls from being set up.
(d) Class C HPA Maximum Output Power
When the HPA is class C, the SDU stores the calibrated HPA maximum
output power value in nonvolatile memory. This value is calculated once per
burst when there is a single measurable carrier present, unless the reported
actual power output value in the HPA status word:
• Matches or is less than the minimum reportable actual power value stored
in ORT item xxix
• Matches either the unique code 00100B for at/below measurable range
or 3 dB greater than 40 W; or the flag was set indicating the HPA or
modem backoff was limited.
This value is the actual output power reported by the HPA, plus the HPA
backoff. If the calibration results in a value outside the range of 14 dBW to
21 dBW, a failure is raised for the HGA HPA and LGA HPA.
(4) Antenna Subsystem Selection
UP86308
(a) The purpose of installing both HGA and LGA subsystems simultaneously is to
increase system availability and geographical orientation coverage. When the
SDU has the choice of antenna subsystems (HGA or LGA), either as part of a
single MCS system or in its role as half of a dual system, reversion from HGA to
LGA (and from LGA to HGA) is accomplished by automatic means. Automatic
reversion from the HGA to the LGA occurs only upon failure of the HGA
subsystem. The SDU automatically switches from the LGA to the HGA if the
HGA subsystem reverts to a normal state. In lieu of a physically separate LGA,
an HGA is also usable as a steered LGA when its gain drops below the level
specified by ORT item xxii.
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(b) Loss of reliable communications with a GES normally occurs as a result of
channel degradation. When channel degradation occurs, the AES considers
itself logged-off and searches for another GES. If no GES is found for
communications using the HGA subsystem, automatic switching to the LGA
subsystem does occur. Manual reversion through the SCDU is the only way the
SDU switches from the HGA subsystem to the LGA subsystem.
(c) The purpose of installing an IGA subsystem is to use the spot beam coverage.
The satellite spot beams supply a times 8 (x8) amplification. Less power is
required for C--channel (circuit mode) operation that equates to less cost per
minute of operation.
C. High Power Amplifier
(1) The SDU sends such information as power amplifier on/off commands and
amplification gain commands to the HPA. The bidirectional link carries status and
maintenance information to the SDU such as gain verification, standing wave ratio
data, and indication of dangerous system conditions such as temperature warnings
or power supply failures.
(2) The HPA supplies RF power amplification of the L-band signals generated by the
SDU to a power level required for transmission to the satellite. Because multiple
signals are transmitted through the HPA, the HPA is a linear device (i.e., operating
class AB) capable of amplifying more than one signal at a time. An average of 40
Watts RF output power is developed by the HPA (up to 25 Watts RF power by the 20
Watt HPA) while passing multiple signals without generating excessive
intermodulation products.
(3) In addition to providing RF power amplification, the HPA must control output power to
supply the desired EIRP from the AES. The SDU controls the gain of the Honeywell
HPA over a 25-dB range in 1-dB increments through the ARINC 429 interface. This
lets automatic adjustment of signal strength compensate for a wide variety of
conditions. The HPA also measures output power and available power and reports to
the SDU, which uses the information to determine if additional calls can be
accommodated.
(4) Under favorable propagation conditions, the full output power capability of the HPA is
not required. The HPA automatically consumes less power and dissipates less heat
when full power is not used.
UP86308
(5) The 20 Watt HPA supplies beam steering capabilities previously implemented in the
antenna beam steering unit. Commands are generated to steer the antenna
elements based on the SDU, IRS information, and beam map data stored in the HPA.
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D. Avionics Configurations
(1) The SDU determines the configuration installed on the aircraft, including the
presence of optional peripherals, by examining the system configuration pins. The
SDU supports interaction only with those peripherals indicated as being present by
the configuration pins.
(2) The Aero H+ SATCOM system requires installation of an SDU and 40 Watt HPA, and
supports seven independent simultaneous channels for voice and data
communications. One channel is dedicated to data and system management
transactions. The remaining six channels are available for analog or digital voice
communications.
(3) The Aero I SATCOM system requires installation of an SDU and 20 Watt HPA, and
supports seven independent simultaneous channels for voice and data
communications. One channel is dedicated to data and system management
transactions. The remaining six channels are available for analog voice
communications.
4. MCS Component Descriptions
A. Physical Description
(1) The LRUs are designed to perform reliably under field conditions and to supply ease
of maintenance when required. Each LRU is designed as a modular concept unit
(MCU), as defined by ARINC Characteristic 600, to permit easy replacement of each
shop replaceable unit (SRU). The SRUs use both digital and analog solid state
circuitry constructed using a mixture of surface mount technology (SMT) and dual
in-line packaging (DIP) technology.
(2) All SRUs are built to standards that qualify them for both airline and business aircraft
usage. Adjustment mechanisms are accessible with the SRU installed in the LRU.
These SRUs can be removed to reduce the number of functional channels without
compromising the functionality of the remaining channels.
UP86308
(3) The MCS system components meet the requirements specified in parts A and B of
the Minimum Operational Performance Standards for Aeronautical Mobile Satellite
Services Document, Document No. RTCA/DO--210.
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MCS--4000/7000 Multi--Channel SATCOM System
B. Satellite Data Unit (SDU)
(1) The SDU is packaged as an ARINC 600 6--MCU suitable for mounting in the
equipment bay. The mechanical chassis is constructed of lightweight aluminum alloy
sheet metal; forced air moving through the chassis in an upward or downward
direction supplies internal cooling. Two hold-down clamps enable the unit to be firmly
clamped in the mounting rack. The unit is carried by a fixed C-shaped handle
mounted to the front panel assembly.
(2) The front panel assembly contains a 20-character alphanumeric display for displaying
built-in test equipment (BITE) failure messages, system LRU part numbers, and the
ORT identification. The display remains inactive when its temperature is less than
--10 °C (+14 °F) or greater than +50 °C (+122 °F). The front panel also contains two
momentary action buttons labeled TEST and CM/SCROLL. The TEST button initiates
BITE in the SDU. The CM/SCROLL button lets the alphanumeric display scroll
through the BITE failure messages and the software confirmation numbers.
(3) The front panel also contains an ARINC 615 portable data loader connector and a
primary cell for the real-time clock/calendar function of the processor module.
(4) The rear connector receptacle is a size No. 2 shell assembly (in accordance with
ARINC 600) that engages a mating connector in the mounting rack when the SDU is
installed. The top and middle inserts are type 02 arrangements and the bottom insert
is a type 04 arrangement. Index pin code 04 is used on both the SDU and the
mounting rack connectors.
UP86308
(5) The SDU is shown in Figure 1-6. The SDU leading particulars are given in Table 1-9.
DO--160D environmental categories for the SDU are given in Table 1-10.
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MCS--4000/7000 Multi--Channel SATCOM System
Figure 1-6.
Table 1-9.
Satellite Data Unit
SDU Leading Particulars
Characteristic
Specification
Dimensions (maximum):
• Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7.624 in. (193.65 mm)
• Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7.51 in. (190.75 mm)
• Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
15.26 in. (337.60 mm)
Weight (maximum) . . . . . . . . . . . . . . . . . . . . . . .
21 lb (9.6 kg)
Power Requirements:
• AC Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . .
104 to 122 V ac, 380 to 420 Hz (normal operation)
97 V ac, 360 Hz minimum; 134 V ac, 440 Hz maximum
• DC Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . .
22.0 to 30.3 V dc (normal operation)
UP86308
20.5 V dc minimum, 32.2 V dc maximum
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Table 1-9.
SDU Leading Particulars (cont)
Characteristic
AC Current
Specification
Requirements 1.:
• Nominal at 115 V ac (Current/Power Factor)
1.3 amps/0.70
• Maximum at 104 V ac (Current/Power
Factor) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2.1 amps/0.91
DC Current Requirements:
• Nominal at 28 V dc . . . . . . . . . . . . . . . . . . . . .
3.8 amps
• Maximum at 20.5 V dc . . . . . . . . . . . . . . . . . .
7.0 amps
Circuit Breaker Ratings:
• 115 V ac Circuit Breaker . . . . . . . . . . . . . . . .
3 amp TYPE A
• 28 V dc Circuit Breaker . . . . . . . . . . . . . . . . .
10 amp TYPE A
User Replaceable Parts . . . . . . . . . . . . . . . . . . .
None
Operating Temperature . . . . . . . . . . . . . . . . . . . .
--55 _C (--67 _F) to +70 _C (158 _F)
Operating Altitude . . . . . . . . . . . . . . . . . . . . . . . .
to 70,000 ft (21.34 kilometers)
Cooling Requirements 2.:
• Minimum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
0.15 ± 0.05 in. (3.81 ± 1.27 mm) of water at a flow rate of
72.8 ± 2.0 lb (33.0 ± 0.9 kg) per hour
• Maximum . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
0.25 ± 0.05 in. (6.35 ± 1.27 mm) of water at a flow rate of
96.2 ± 2.0 lb (43.6 ± 0.9 kg) per hour
Power Dissipation 3.:
• Nominal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
105 W
• Maximum . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
198 W
Mating Connectors:
• J1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Radiall Part No. NSXN2P201X004
• J2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Honeywell Part No. 4004295--160, ITT Part No.
KJ6F18A53P
Mounting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ARINC 600 6--MCU Tray Assembly
UP86308
NOTES:
1.
All power factors (PF) are leading.
2.
Refer to Appendix A, Vendor Equipment, for mounting trays with integral cooling fans that meet the cooling
requirements.
3.
The SDU draws an additional 20 W during the first 10 minutes (maximum) of operation at 25_C (77 _F) because of
the OCXO. The OCXO continuously dissipates this additional 20 W at --55 _C (--67 _F).
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Table 1-10.
SDU DO--160D Environmental Categories
Environmental Condition
Category
Temperature and Altitude
Category A2E1/Z (E1) 1.
Temperature Variation
Category B
Humidity
Category A
Shock
Category B
Vibration
Category SB2
Explosion
Category E
Waterproofness
Category X
Fluids Susceptibility
Category X
Sand and Dust
Category X
Fungus Resistance
Category X
Salt Spray
Category X
Magnetic Effect
Category Z
Power Input -- 115 V ac
Category E
Power Input -- 28 V dc
Category BZ 2.
Voltage Spike
Category A
Audio Frequency Susceptibility -- 115 V ac
Category E
Audio Frequency Susceptibility -- 28 V dc
Category Z
Induced Signal Susceptibility
Category Z
Radio Frequency Susceptibility
Category RRR
Radio Frequency Emissions
Category M
Lightning Induced
Category A3E3
Lightning Direct
Category X
Icing
Category X
Electro Static Discharge
Category A
UP86308
NOTES:
1.
E1 -- Operating High Temperature/High Short Time = 70 °C (158 °F).
2.
Z -- The power input requirements for the 28 V dc LRU are category Z except for an emergency operation, in which
case the requirements of category B apply.
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C. High--Power Amplifier (40 Watt)
(1) The HPA is packaged as an ARINC 600 8--MCU suitable for mounting in the
equipment bay or near the antenna system. The mechanical chassis is constructed of
lightweight aluminum alloy sheet metal. Forced air moving through the chassis in an
upward or downward direction supplies internal cooling. Two hold-down clamps let
the unit be firmly clamped in the mounting rack. The unit is carried by a fixed
C-shaped handle mounted to the front panel assembly.
(2) The front panel assembly contains a PTT switch to initiate BITE and a red (FAIL) and
green (PASS) light emitting diode(LED) to indicate BITE status. The front panel also
contains an ARINC 615 portable data loader connector and an RF monitor port.
(3) The rear connector receptacle is a size No. 2 shell assembly (in accordance with
ARINC 600) that engages a mating connector in the mounting rack when the HPA is
installed. The top insert is a type 08 arrangement, the middle insert is a type 05
arrangement, and the bottom insert is a type 04 arrangement. Index pin code 08 is
used on both the HPA and mounting rack connectors.
UP86308
(4) The HPA (40 Watt) is shown in Figure 1-7. The leading particulars for the HPA (40
Watt) are given in Table 1-11. DO--160C environmental categories for the HPA (40
Watt) are given in Table 1-12.
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UP86308
Figure 1-7.
High--Power Amplifier (40 and 20 Watt)
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Table 1-11.
HPA (40 Watt) Leading Particulars
Characteristic
Specification
Dimensions (maximum):
• Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7.813 in. (198.45 mm)
• Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10.22 in. (259.59 mm)
• Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
15.20 in. (386.08 mm)
Weight (maximum) . . . . . . . . . . . . . . . . . . . . . . .
29.15 lb (13.22 kg)
Power Requirements:
• AC Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . .
104 to 122 V ac, 380 to 420 Hz (normal operation)
97 V ac, 360 Hz minimum; 134 V ac,440 Hz maximum
• DC Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . .
22.0 to 30.3 V dc (normal operation)
20.5 V dc minimum, 32.2 V dc maximum
AC Current
Requirements 1.:
• Nominal at 115 V ac (Current/Power Factor)
1.94 amps/0.95
• Maximum at 104 V ac (Current/Power
Factor) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2.2 amps/0.96
DC Current Requirements:
• Nominal at 28 V dc . . . . . . . . . . . . . . . . . . . . .
7.3 amps
• Maximum at 20.5 V dc . . . . . . . . . . . . . . . . . .
8.2 amps
RF Power Output:
• Rated operating power . . . . . . . . . . . . . . . . . .
40 W (multiple carriers)
• Maximum power . . . . . . . . . . . . . . . . . . . . . . .
80 W (short duration, single carrier)
Circuit Breaker Ratings:
• 115 V ac Circuit Breaker . . . . . . . . . . . . . . . .
7.5 amp TYPE A
• 28 V dc Circuit Breaker 2. . . . . . . . . . . . . . . . .
30 amp TYPE A
User Replaceable Parts . . . . . . . . . . . . . . . . . . .
None
Operating Temperature . . . . . . . . . . . . . . . . . . . .
--55 _C (--67 _F) to +70 _C (158 _F)
Operating Altitude . . . . . . . . . . . . . . . . . . . . . . . .
to 70,000 ft (21.34 kilometers)
UP86308
Cooling Requirements 3.:
• Minimum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
0.15 ± 0.05 in. (3.81 ± 1.27 mm) of water at a flow rate of
121.3 ± 2.0 lb (55.0 ± 0.9 kg) per hour
• Maximum . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
0.25 ± 0.05 in. (6.35 ± 1.27 mm) of water at a flow rate of
176.4 ± 2.0 lb (80.0 ± 0.9 kg) per hour
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MCS--4000/7000 Multi--Channel SATCOM System
Table 1-11.
HPA (40 Watt) Leading Particulars (cont)
Characteristic
Specification
Power Dissipation:
• Nominal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
300 W
• Maximum . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
362 W
Mating Connectors:
• J1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Radiall Part No. NSXN2P221X0008
• J2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Honeywell Part No. 4004295--160,
ITT Part No. KJ6F18A53P
• J3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
BNC Plug
Mounting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ARINC 600 8--MCU Tray Assembly
NOTES:
1.
All PF are leading.
2.
Wiring can not exceed 18 V dc drop at 30 amps.
3.
Refer to Appendix A, Vendor Equipment, for mounting trays with integral cooling fans that meet the cooling
requirements.
Table 1-12.
HPA (40 Watt) DO--160C Environmental Categories
UP86308
Environmental Condition
Category
Temperature and Altitude
Category A2E1/Z (E1) 1.
Temperature Variation
Category B
Humidity
Category A
Shock
Category B
Vibration
Category BLMY
Explosion
Category E1
Waterproofness
Category X
Fluids Susceptibility
Category X
Sand and Dust
Category X
Fungus Resistance
Category X
Salt Spray
Category X
Magnetic Effect
Category Z
Power Input -- 115 V ac
Category E
Power Input -- 28 V dc
Category Z 2.
Voltage Spike
Category A
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 1-12.
HPA (40 Watt) DO--160C Environmental Categories (cont)
Environmental Condition
Category
Audio Frequency Susceptibility -- 115 V ac
Category E
Audio Frequency Susceptibility -- 28 V dc
Category Z
Induced Signal Susceptibility
Category Z
Radio Frequency Susceptibility
Category W 3.
Radio Frequency Emissions
Category Z
Lightning Induced
Category K
Lightning Direct
Category X
Icing
Category X
NOTES:
1.
E1 -- Operating High Temperature/High Short Time = 70 °C (158 °F).
2.
Z -- The power input requirements for the 28 V dc LRU are category Z except for an emergency operation, in which
case the requirements of category B apply.
3.
W -- Performance of this test is required to satisfy the HIRF requirements. The LRUs must survive a category W
event without degradation (i.e., regain normal operation at the termination of the HIRF event), and must operate
through (with performance degradation permitted) and after (without performance degradation) a category T event.
D. High--Power Amplifier (20 Watt)
(1) The HPA is packaged as an ARINC 600 4--MCU suitable for mounting in the
equipment bay or near the antenna system. The mechanical chassis is constructed of
lightweight aluminum alloy sheet metal. Forced air moving through the chassis in an
upward or downward direction supplies internal cooling. Two hold-down clamps let
the unit be firmly clamped in the mounting rack. The unit is carried by a fixed
C-shaped handle mounted to the front panel assembly.
(2) The front panel assembly contains a PTT switch to initiate BITE and a red (FAIL) and
green (PASS) LED to indicate BITE status. The front panel also contains an ARINC
615 portable data loader connector.
(3) The rear connector receptacle is a size No. 2 shell assembly (in accordance with
ARINC 600) that engages a mating connector in the mounting rack when the HPA is
installed. The top insert is a type 08 arrangement, the middle insert is a type 05
arrangement, and the bottom insert is a type 04 arrangement. Index pin code 08 is
used on both the HPA and mounting rack connectors.
UP86308
(4) The HPA (20 Watt) is shown in Figure 1-7. The leading particulars for the HPA (20
Watt) are given in Table 1-13. DO--160D environmental categories for the HPA (20
Watt) are given in Table 1-14.
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 1-13.
HPA (20 Watt) Leading Particulars
Characteristic
Specification
Dimensions (maximum):
• Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7.64 in. (194.056 mm)
• Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4.90 in. (124.46 mm)
• Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
15.26 in. (387.604 mm)
Weight (maximum) . . . . . . . . . . . . . . . . . . . . . . .
15.80 lb (7.17 kg)
Power Requirements:
• AC Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . .
104 to 122 V ac, 380 to 420 Hz (normal operation)
97 V ac, 360 Hz minimum; 134 V ac, 440 Hz maximum
• DC Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . .
22.0 to 30.3 V dc (normal operation)
20.5 V dc minimum, 32.2 V dc maximum
AC Current
Requirements 1.:
• Nominal at 115 V ac (Current/Power Factor)
1.94 amps/0.96
• Maximum at 104 V ac (Current/Power
Factor) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2.2 amps/0.96
DC Current Requirements:
• Nominal at 28 V dc . . . . . . . . . . . . . . . . . . . . .
7.3 amps
• Maximum at 20.5 V dc . . . . . . . . . . . . . . . . . .
12 amps
RF Power Output:
• Rated operating power . . . . . . . . . . . . . . . . . .
25.1 W (under all conditions)
• Maximum power . . . . . . . . . . . . . . . . . . . . . . .
25.1 W (under all conditions)
Circuit Breaker Ratings:
• 115 V ac Circuit Breaker . . . . . . . . . . . . . . . .
7.5 amp TYPE A
• 28 V dc Circuit Breaker . . . . . . . . . . . . . . . . .
15 amp TYPE A
User Replaceable Parts . . . . . . . . . . . . . . . . . . .
None
Operating Temperature . . . . . . . . . . . . . . . . . . . .
--15 _C (5 _F) to +70 _C (158 _F)
Operating Altitude . . . . . . . . . . . . . . . . . . . . . . . .
to 55,000 ft (16.76 kilometers)
Cooling Requirements (Minimum) 2. . . . . . . . . .
0.20 ± 0.12 in. (5 ± 3 mm) of water at a flow rate of 72.8 ±
2.0 lb (33.0 ± 0.9 kg) per hour
UP86308
Power Dissipation:
• Nominal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
150 W
• Maximum . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
219 W
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 1-13.
HPA (20 Watt) Leading Particulars (cont)
Characteristic
Specification
Mating Connectors:
• J1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Radiall Part No. NSXN2P221X0008
• J2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Honeywell Part No. 4004295--160, ITT Part No.
KJ6F18A53P
Mounting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ARINC 600 4--MCU Tray Assembly
NOTES:
1.
All PF are leading.
2.
Refer to Appendix A, Vendor Equipment, for mounting trays with integral cooling fans that meet the cooling
requirements.
Table 1-14.
HPA (20 Watt) DO--160D Environmental Categories
UP86308
Environmental Condition
Category
Temperature and Altitude
Category A2E1/Z (E1) 1.
Temperature Variation
Category B
Humidity
Category A
Shock
Category B
Vibration
Category SB2
Explosion
Category E
Waterproofness
Category X
Fluids Susceptibility
Category X
Sand and Dust
Category X
Fungus Resistance
Category X
Salt Spray
Category X
Magnetic Effect
Category Z
Power Input -- 115 V ac
Category E
Power Input -- 28 V dc
Category BZ 2.
Voltage Spike
Category A
Audio Frequency Susceptibility -- 115 V ac
Category E
Audio Frequency Susceptibility -- 28 V dc
Category Z
Induced Signal Susceptibility
Category Z
Radio Frequency Susceptibility
Category RRR 3.
Radio Frequency Emissions
Category M
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 1-14.
HPA (20 Watt) DO--160D Environmental Categories (cont)
Environmental Condition
Category
Lightning Induced
Category A3E3
Lightning Direct
Category X
Icing
Category X
Electrostatic Discharge
Category A
NOTES:
1.
E1 -- Operating High Temperature/High Short Time = 70 °C (158 °F).
2.
BZ -- The power input requirements for the 28 V dc version of the 20 Watt HPA are category Z except for an
emergency operation, in which case the requirements of category B apply.
3.
RRR -- Performance of this test is required to satisfy the HIRF requirements.
E.
CMA--2200 Intermediate Gain Antenna
(1) The Intermediate Gain Antenna supplies a minimum of 6 dB antenna gain (8 dB
nominal) and operates with the 20 W HPA. The IGA is manufactured by BAE
Systems Canada Inc. (formerly Canadian Marconi Company Aerospace) under both
BAE Systems -- Canada Part No. 100--602372--000 and Honeywell Part No.
7516194--901. Features of the IGA are given in Table 1-15.
Table 1-15.
CMA--2200 Intermediate Gain Antenna Features
Characteristic
Specification
Service coverage . . . . . . . . . . . . . . . . . . . . . . . . .
less than 95% of the Inmarsat hemisphere
• Receive . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1525.0 -- 1559.0 MHz
• Transmit . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1626.5 -- 1660.5 MHz
Polarization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Right hand circular
Receive figure of merit (G/T) . . . . . . . . . . . .
--15.5 dB/K typical, --19 dB/K minimum
UP86308
Effective Isotropic Radiated Power (EIRP) 19.5 dBW typical, 16.5 dBW minimum
Phase discontinuity . . . . . . . . . . . . . . . . . . . . .
2.5_ typical, less than 30_ for 99% of all beam
steering increments
Beam switching . . . . . . . . . . . . . . . . . . . . . . . . .
50 µs maximum
Carrier/Multipath . . . . . . . . . . . . . . . . . . . . . . . .
15 dB typical, 10 dB minimum at 5_ elevation; 20 dB
typical,12 dB minimum at 20_ elevation
Satellite discrimination . . . . . . . . . . . . . . . . . .
16 dB typical, 7 dB minimum
Latitude global Inmarsat satellite
coverage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
± 86 degrees
Required antenna gain . . . . . . . . . . . . . . . . . .
6 dB
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 1-15.
CMA--2200 Intermediate Gain Antenna Features (cont)
Characteristic
Specification
Support/Test equipment required . . . . . . . .
None at organizational level
Design characteristics
(RTCA/ARINC/TSO/etc.) . . . . . . . . . . . . . . . .
DO--160C, ARINC 761, MOPS, SARPS
(2) Other features of the CMA--2200 IGA include:
• Inmarsat Generation 3 Spot Beam coverage
• Proven compatibility with ARINC 761 intermediate--gain antenna subsystems
• BIT status reporting.
(3) The leading particulars for the CMA--2200 IGA are given in Table 1-16. DO--160C
environmental categories for the CMA--2200 IGA are given in Table 1-17.
Table 1-16.
CMA--2200 IGA Leading Particulars
Characteristic
Specification
Dimensions (maximum):
• Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3.82 in. (97.0 mm)
• Width:
-- At radome . . . . . . . . . . . . . . . . . . . . . . . . . . .
3.22 in. (81.8 mm)
-- At base . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4.25 in. (108.0 mm)
• Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
29.92 in. (760.0 mm)
Weight (maximum) . . . . . . . . . . . . . . . . . . . . . . .
6 lb (2.7 kg)
Power Requirements . . . . . . . . . . . . . . . . . . . . .
15 V dc, 8 V dc and --80 V dc (7 Watts)
Operating Environment:
• Temperature range (operating) . . . . . . . . . . .
--55_ to +70_ C (--67_
to +158_ F)
• Temperature range (non--operating) . . . . . . .
--55_ to +85_ C (--67_
to +158_ F)
• Operating altitude . . . . . . . . . . . . . . . . . . . . . .
to 70,000 ft (21.34 km)
UP86308
Mating Connectors:
• J1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Circular Connector -- Part No. D38999/26FB35SN
• J2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
TNC JACK -- Mates with TNC plug
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 1-17.
CMA--2200 IGA DO--160C Environmental Categories
Environmental Condition
Category
Temperature and Altitude
E1
In--Flight Loss of Cooling
Temperature Variation
Humidity
Operational Shock and Crash Safety
----
Vibration
Explosion Proofness
Waterproofness
Fluids Susceptibility
Sand and Dust
Fungus Resistance
Salt Spray
Magnetic Effect
Power Input
Voltage Spike
Audio Frequency Conducted Susceptibility
Induced Signal Susceptibility
Radio Frequency Susceptibility
Radio Frequency Emissions
Lightning Induced
XXE3
Lightning Direct Effects
2A
Icing
F.
CMA--2200 Diplexer/Low Noise Amplifier
UP86308
(1) The CMA--2200 Diplexer/Low Noise Amplifier (D/LNA) supplies the RF transmit
(diplexer) and RF receive (low noise amplifier) paths between the HGA, IGA, or LGA
and the HPA and SDU, respectively. The D/LNA is manufactured by BAE Systems -Canada (formerly Canadian Marconi Company Aerospace) under both BAE Systems
-- Canada Part No. 100--602200--001 and the Honeywell Part No. 7516193--901. The
features of the D/LNA are given in Table 1-18.
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 1-18.
CMA--2200 D/LNA Features
Characteristic
Specification
Frequency range:
• Receive . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1525.0 -- 1559.0 MHz
• Transmit . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1626.5 -- 1660.5 MHz
Receive gain . . . . . . . . . . . . . . . . . . . . . . . . . . .
53 dB minimum, 60 dB maximum
Noise figure . . . . . . . . . . . . . . . . . . . . . . . . . . . .
0.8 dB maximum at 25_ C.
Support/Test equipment required . . . . . . . .
None at organizational level
Design characteristics . . . . . . . . . . . . . . . . . .
(RTCA/ARINC/TSO/etc)
DO--160C, ARINC 741/761, MOPS, SARPS
(2) Other features of the CMA--2200:
• Proven compatibility with:
-- ARINC 761 intermediate--gain antenna subsystems
-- ARINC 741 high--gain or low--gain antenna subsystems
• Self--test function.
(3) The leading particulars for the CMA--2200 D/LNA are given in Table 1-19. DO--160C
environmental categories for the CMA--2200 D/LNA are given in Table 1-20.
Table 1-19.
CMA--2200 D/LNA Leading Particulars
Characteristic
Specification
Dimensions (maximum):
• Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2.00 in. (50.8 mm)
• Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7.78 in. (197.6 mm)
• Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
11.59 in. (294.4 mm)
Weight (maximum) . . . . . . . . . . . . . . . . . . . . . . .
6.5 lb (3.0 kg)
Power Requirements . . . . . . . . . . . . . . . . . . . . .
115 V ac, 400 Hz, 150 milliamps maximum
UP86308
Operating Environment:
• Temperature range (operating) . . . . . . . . . . .
--55_ to +70_ C (--67_ F to +158_ F)
• Temperature range (non--operating) . . . . . . .
--55_ to +85_ C (--67_ F to +158_ F)
• Operating altitude . . . . . . . . . . . . . . . . . . . . . .
to 70,000 ft (21.34 km)
23--20--27
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Table 1-20.
CMA--2200 D/LNA DO--160C Environmental Categories
Environmental Condition
Temperature and Altitude
E1
In--Flight Loss of Cooling
Temperature Variation
Humidity
Operational Shock and Crash Safety
----
Vibration
Explosion Proof
E2
Waterproof
Fluids Susceptibility
Sand and Dust
Fungus Resistance
Salt Spray
Magnetic Effect
Power Input
Voltage Spike
Audio Frequency Conducted Susceptibility
Induced Signal Susceptibility
Radio Frequency Susceptibility
Radio Frequency Emissions
Lightning Induced
UP86308
Category
XXE3
Lightning Direct Effects
Icing
23--20--27
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G. Radio Frequency Unit Interface Adapter (RFUIA)
(1) The RFUIA is packaged as an ARINC 600 4--MCU suitable for mounting in the
equipment bay or near the antenna system. It consists of a housing assembly
integrated with an ARINC 600 connector on the back of the unit.
(2) The RFUIA is not an operational unit and it does not contain active internal electronic
components. No aircraft power is needed. This unit is installed in the aircraft in place
of the RFU to complete the RF receive and transmit paths for the MCS--7000 system.
(3) The housing is constructed of lightweight aluminum alloy sheet metal. No forced air
cooling is required. Two hold-down clamps let the unit be firmly clamped in the
mounting rack. The unit is carried by a fixed C-shaped handle mounted to the front
panel assembly.
(4) Figure 1-8 is a block diagram that shows how the RFUIA interfaces to the other
system LRUs. The leading particulars for the CMA--2200 D/LNA are given in
Table 1-21.
UP86308
Figure 1-8.
RFUIA System Interface Diagram
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 1-21.
RFUIA Leading Particulars
Characteristic
Specification
Dimensions (maximum):
• Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
12.76 in. (324.1 mm)
• Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4.90 in. (124.5 mm)
• Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7.64 in. (194.1 mm)
Weight (maximum)
4 lb (1.82 kg)
Power requirements
None
Cooling
Convection, no forced air required
H. ARINC 429 Data Requirements
(1) The MCS system requires ARINC 429 data for antenna pointing, antenna
stabilization, and Doppler frequency correction. If the aircraft does not have an IRS
that supplies this ARINC data, the SCU can be used to convert INS data sources.
Refer to Appendix A, Vendor Equipment, for additional information about the SCU
and the ARINC 429 data requirements.
I.
Nameplates 3 (SDU and HPA)
(1) General
(a) Each LRU has two externally mounted nameplates consisting of:
• Front panel--mounted LRU nameplate
• Second LRU nameplate that reflects the full hardware and software status of
the LRU.
(b) The details of these nameplates are specified in the following paragraphs. See
Figure 1-6 and Figure 1-7 for the location of each nameplate.
(2) Front Panel LRU Nameplate
UP86308
(a) Each front panel LRU nameplate contains each company’s logo (Honeywell and
Racal), the name of the system, and the LRU equipment name.
23--20--27
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(3) LRU Hardware and Software Nameplate
(a) Each LRU hardware and software nameplate contains the following information:
• Name of the company responsible for manufacturing it
• Model number (e.g., SD700, HP600, or HP700)
• LRU equipment name
• LRU hardware part number
• LRU serial number
• Weight
• Applicable DO--160C/DO--160D categories
• FCC identifier
• LRU hardware modification level
• LRU end item part number
• LRU software part number
• Software modification level
• Applicable DO--178A or DO--178B software level.
(b) The model number is a five--digit alphanumeric sequence. The first two digits are
upper--case alphabetic characters in the range AA to ZZ and the last three digits
are numeric characters in the range 100 to 999. The LRU equipment name is
displayed with as many upper--case letters as are required to spell out the
equipment name. The LRU serial number consists of an eight--digit numeric
sequence; the first two digits indicate the year of manufacture, the second two
digits indicate the month of manufacture, and the final four digits indicate how
many LRUs of this type have been manufactured. The range of the last four
digits is 0100 to 9999.
(c) The DO--160C or DO--160D categories applicable to the MCS system consist of
a mix of numeric and upper--case alphabetic characters. See Table 1-10,
Table 1-12, or Table 1-14 for a list of environmental categories applicable to the
MCS LRUs.
(d) The FCC identifier applicable to all MCS LRUs is GB8MCS--4000 or
GB8MCS--7000. The LRU hardware modification level is indicated by the set of
all marked modification level identifiers. Each modification level identifier is a
maximum of two upper--case alphabetic characters that range from A to ZZ, with
letters I, O, Q, and X excluded.
UP86308
(e) The LRU end item part number consists of a seven--digit base part number and a
five--digit dash number. The first two digits of the dash number indicate the LRU’s
hardware configuration and consist of numeric values ranging from 10 to 99. The
last three digits of the dash number reflect the LRU’s software configuration
number and consist of numeric values ranging from 001 to 999.
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(f)
The software modification level consists of a maximum of two upper--case
alphabetic characters ranging from A (or “--”) to ZZ, with letters I, O, Q, and X
excluded. Usage of this nameplate characteristic reflects the implementation of
minor software changes.
(g) The DO--178A or DO--178B software levels applicable to the MCS LRUs is the
level an LRU was certified. This nameplate is capable of being removed and
replaced when a software change is significant enough to require the three--digit
software configuration number be incremented, or a hardware change is
significant enough to require that the two--digit hardware configuration number
be incremented.
J.
Software and Hardware Compatibility (SDU and HPA)
(1) Provisions for a set of discrete wire jumpers (straps) are included in each MCS LRU
to ensure hardware and software compatibility. The code setting for these straps is
manually changed each time a hardware revision is made that is not compatible with
all previously released versions of software. The status of these straps is tested
every time an LRU undergoes a cold start (power--on self--test [POST], or
person--activated self--test [PAST] ), and every time a software load is attempted from
an ARINC 615 portable data loader.
UP86308
(2) The LRU header records in the ARINC 615 data loader software upload file and in
the operational software itself, contain a list of hardware/software compatibility strap
codes with which the software is compatible. This list of codes is compared with the
wired hardware/software compatibility strap code in the LRU; if any of the codes in
the software upload file match the hardware/software compatibility strap code in the
LRU, then the software upload process is allowed (otherwise it is inhibited). Similarly,
if any of the codes in the software itself match the strap code in the LRU, normal LRU
operation is allowed (otherwise it remains in an inert state).
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SECTION 2
SYSTEM OPERATION
1. Overview
A. General
The AES accepts data and voice signals from various sources, encodes the signals,
modulates the information onto the appropriate RF carrier frequencies, and transmits these
carriers to a GES through satellite. The AES also receives RF signals from the satellites,
demodulates and decodes these signals, and outputs data or voice message for passengers
or flight crew members. System operation begins when the P--channel transmission from a
GES in the satellite region is received. The AES then logs onto the GES to establish the
uplink and exchange information. System operation terminates when the AES logs off from
the GES.
2. AES Management
A. General
(1) At any time, different satellite regions can have different satellite configurations. All
satellites have the global beam capability to receive the continuous Psmc--channel
transmission of every GES in view. For a spot beam satellite, each spot beam is
associated with at least one GES having a continuous P--channel transmission.
Selected channels from the Psmc-- and Pd--channels are designated by INMARSAT
for satellite and spot beam selection.
(2) An AES logs onto a GES to enter the satellite communications system and logs off to
terminate its operation in the system. Log-off is initiated automatically or by a user
command issued as part of normal operational procedures.
(3) The AES also logs off before initiating handover. The AES does not log off if
handover is initiated because of degradation or loss of the P--channel. Handover can
be initiated by the flight crew, or can be carried out automatically by the AES without
human intervention. A handover procedure is followed automatically when an AES
needs to change the log-on GES or to access a different satellite.
(4) When an AES receives a higher level instruction, for example a command from the
flight crew, to change its log-on to another GES operating in the same satellite
region, any previously established data communication channels are maintained until
clearing before the handover is carried out. In the case of a user command initiated
satellite-to-satellite handover, the AES ensures all communication channels are clear
prior to starting the handover procedure. If any connections are in progress, the AES
applies time supervision of three minutes and then clears any remaining connections.
(5) Automatic handover is initiated upon detection of Pd--channel link degradation
defined as:
• Error rate rises above 104 over an averaging period of 3 minutes
UP86308
• More than 10 short--term interruptions (loss of P--channel clock synchronization for
less than 10 seconds) in any 3 minute period.
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(6) Automatic handover is also initiated upon detection of loss of the Pd--channel defined
as:
• Loss of clock synchronization for more than 10 seconds
• Log-on renewal procedure is unsuccessful.
(7) A GES-to-GES handover is carried out by logging onto a new GES in the same
satellite region. The required P--channel frequency can be found in the system table.
Each GES maintains an up-to-date status table of all AESs that have logged on.
Each GES also has an inter-GES signaling capability letting the GES set up calls with
any AES operating in the same satellite region as that GES, and manages the AESs
during handover.
(8) If the AES attempts to renew its log-on and fails to log on to its previous GES or to
the preferred alternative GES after a log-on prompt, loss of P--channel quality, or a
log-on renewal request from an application, the AES returns to the latter stages of
the initial search procedure and scans the spot beam primary Pd--channels on its
current satellite to identify an alternative spot beam. The required P--channel
frequencies are found in the system table. Once an alternative spot beam is
identified, the AES renews its log-on automatically to a preferred GES.
(9) During log-on renewal, if the AES is unable to log onto its previous GES or to another
GES in the same satellite region, then the AES enters the search mode to select the
Psmc--channel frequency of a GES operating in a new satellite region. The required
P--channel frequency is found in the system table. Having selected a new suitable
quality Psmc--channel (in another satellite region) and updating the system table for
the new satellite region (if necessary), the AES carries out a log-on procedure with
the new GES.
(10) Each AES maintains a system table stored in nonvolatile memory in the SDU. The
system table contains the satellite and GES identifying information, such as satellite
Psid--channel frequencies, satellite locations and associated GES IDs, and GES
Psmc--channel frequencies. The system table does not lose its contents because of
loss of primary power.
(11) The SDU also maintains a bootstrap system table containing a default set of satellite
and GES identifying information. This information includes satellite Psid--channel
frequencies, satellite location and associated GES IDs, plus satellite inclination and
right ascension, spot beam support, and GES Psmc--channel frequencies that are set
to zero.
UP86308
(12) The bootstrap system table is loaded into the SDU as an inseparable part of the
upload of executable software. The SDU defaults to the bootstrap system table in the
absence of a stored system table, or upon execution of a factory settings restart. The
default data for a satellite is used until that satellite is first accessed, where a
complete update of the data for that satellite takes place. Satellite region blocks that
have not yet been updated over the air are marked with a null revision number.
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3. System Log-On/Log-Off
A. General
(1) Two operational modes are available for AES log-on:
• Automatic
• User commanded (constrained).
(2) In the automatic mode, the AES operation is fully automatic with satellite log-on and
handover procedures occurring without external control. In the user commanded
mode, the flight crew or flight control system is able to select the satellite and GES for
log-on and handover, and can initiate handovers at any time. The automatic mode is
considered the normal mode of operation.
(3) The log-on/log-off of an AES to/from the satellite communications system lets the
GES manage the number of AESs that can receive a P--channel (Pd) and transmit on
each R--channel (Rd). This controls the queuing delays and burst collision
probabilities that can be experienced. When an AES is powered up, it enters a GES
selection mode if the log-on policy is set to automatic. This permits the AES to select
the most preferred GES operating in its visible satellite region (there may be one or
two satellites visible to the AES), and that GES is selected for log-on. If the log-on
policy is not set to automatic, the AES waits for the GES to be selected through the
user commanded mode (or for a reversion to the automatic mode).
(4) After selecting a GES, the AES tries to acquire one of the identifying Psmc--channel
frequencies of the satellite contained in the initial system table. Typically there are
two frequencies per satellite (or group of satellites if several satellites supply service
to essentially one region). The AES receives that Psmc--channel until one of the
system table’s broadcast signal units is received, which permits the AES to determine
whether the revision number of the system table currently stored in the SDU is valid.
If the revision number for the AES is out-of-date, an AES updating procedure is
implemented.
UP86308
(5) When the revision number is verified as correct, the AES checks for any entries in the
satellite spot beam search table. If an entry exists, the AES checks the Pd--channel
frequencies of all spot beams supported by the selected GES to identify the most
applicable spot beam. The AES then determines which Pd--channel has the highest
signal quality. Once this task is complete, the AES is ready to log-on to the satellite
communications system using the selected GES and the optimum spot beam, or the
global beam if the GES does not operate a P--channel in the required spot beam.
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(6) The AES initiates the log-on procedure by tuning to the Psmc--channel (global beam)
of the selected GES and sending a log-on request signal unit on one of the
corresponding Rsmc--channels. If the log-on request signal unit cannot be accepted
by the GES, because of reasons like GES overload, invalid message, unauthorized
access, etc, the GES responds with a log-on reject signal unit, which includes the
cause of the rejection. By returning a log-on confirm signal unit with a different AES
class value, the GES can offer log-on in a different AES class than originally
requested. The AES can either accept log-on in the offered class by continuing the
log-on signaling procedure, or reject log-on by discontinuing the log-on signaling
procedure.
(7) The AES uses the log-on request signal unit to supply the selected GES with its own
identification (a 24-bit ICAO aircraft identification code), plus the identification of the
spot beam where the AES is located. A zero value is used in the spot beam
identification field of the log-on message if:
• No spot beam on the selected satellite
• AES is out of any spot beam coverage area
• Selected GES does not operate a Pd--channel in the required spot beam.
(8) The AES also informs the GES of the number of C--channels the AES is equipped to
handle, the bit rate/coding algorithm in use on the voice channels, and the data bit
rate capability for the R--channels, P--channels, and T--channels. Except for the
number of C--channels and the data bit rate capability, this information is repeated in
the log-on confirm signal unit for use by other GESs.
(9) An AES having circuit-mode data service capability and desiring allocation of
circuit-mode data capable channel units at the GES for every ground-to-air call,
informs the GES of the type of interface required. The interface is either analog
interconnect or digital interconnect. If the GES does not support circuit-mode data
service, it ignores the information. If the GES supports the service, it registers the
information in its log-on AES table and retransmits the information for use by other
GESs.
(10) The AES supplies the GES with its flight identification number at log-on, if the
owner/operator of the AES desires to use the aircraft flight identification as the
address for ground originated calls. The use of this information in the GES depends
upon the services being offered, and therefore is at the discretion of the GES
operator.
UP86308
(11) The AES is given an EIRP setting for Rd--channels in the log-on confirm signal. If a
T--channel is assigned, the AES determines the EIRP for the T--channel in
accordance with the assigned R--channel EIRP and the ratio of the R--channel and
T--channel bit rates. The GES assigns a Pd--channel from the available channels,
taking into account the loadings on the channels, the need to use a P--channel of low
power if possible, and the need to supply some means of recovery from P--channel
degradation or failure. The ability to work with a low power P--channel is determined
by the AES class. If the GES assigns a Pd--channel different than the Psmc--channel,
the GES transmits the new channel frequency to the AES using the P/R--channel
control signaling message following the log-on confirm.
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(12) If the GES is using more than one set of R--channel frequencies and assigns new
Rd--channels to the aircraft, the GES transmits the new channel frequencies (up to
eight) to the AES using the signaling message(s) that follow the log-on confirm. In
addition, the GES transmits from one to four T--channel frequencies to the AES if
data services are supplied. The GES uses the following criteria to determine the
channel and EIRP assignments for data services:
• Satellite in use (its return link sensitivity)
• Class of AES
• Bit rate capability of the AES.
(13) The GES assigns data channels at the highest agreeable bit rate supplied in both the
AES and GES, and supported by the combination of the satellite in use and the class
of AES. Subsequent log-on transactions for handover use Rsmc-- and
Psmc--channels in the same manner as the initial log-on transaction.
B. Automatic Log-On
(1) The SDU supports two types of log-on:
• Automatic
• Constrained mode.
(2) The SDU implements the automatic log-on mode upon user command if the AES is
currently logged-off, AES is logging-on, or AES is logged-on in the constrained mode.
Automatic log-on is also implemented by the SDU, if ORT item i (log-on policy)
indicates automatic at startup. The user command can originate from either the
SCDU, from the analog connected telephone handsets, or from the commissioning
and maintenance terminal (CMT).
(3) When the AES is in the automatic mode, the log-on GES/satellite/spot beam chosen
is based on the GES preference (ORT item iii). A GES with a preference level of zero
is not considered for automatic log-on. The SDU allows the use of tied GES
preferences. The SDU resolves tied preferences by selecting the GESs in
descending order of satellite elevation. During GES selection, the set (as yet untied)
of GESs with the highest preference are initially processed to exclude those GESs
associated with satellites not in view.
UP86308
(4) Satellites are deemed in view if they are above the elevation handover threshold
specified in ORT item xxxix, or their elevation is higher than 1 degree less than the
elevation of the highest satellite. If no IRS data is available and the currently selected
antenna is the low gain antenna, then all satellites are deemed to be in view. The
remainder of the GESs in the preference group are then sorted into a list by satellite
elevation and GES on the highest elevation satellite chosen for initial access. If more
than one GES in the preference group have the same satellite elevation, then those
GESs are ordered by a pseudo-random choice algorithm with a uniform probability
density.
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C. Constrained Log-On
(1) Constrained log-on is where the user manually selects the specific GES to be used
for log-on. The user command can originate from either the SCDU, from the
analog-connected telephone handsets, or from the CMT. The GES preferences
specified in ORT item iii have no effect in the constrained log-on mode, and it is
possible to execute a constrained log-on to a GES with a preference level of zero.
(2) If the user has manually selected the log-on GES, and therefore also selecting the
satellite, the SDU is constrained to search for the specific GES-related satellite Psid
frequency (or frequencies), the set of spot beam Pd frequencies where the selected
GES radiates P--channels, and the selected GES Psmc frequency during the log-on
sequences. If the specific GESs satellite Psid frequencies cannot be acquired, the
SDU takes no action other than to reattempt the acquisition with alternate modems. If
none of the GES-related spot beam Pd frequencies can be acquired, the SDU starts
the GES Psmc frequency search as it would normally do after acquiring a spot beam
frequency. If the GES Psmc frequency cannot be acquired, the SDU reattempts the
acquisition indefinitely. This state of unsuccessful satellite/GES Psmc frequency
acquisition is exited either by the frequency being acquired, or by a user command to
select automatic log-on, by selection of a different satellite/GES, or to log-off.
(3) Once logged-on in this mode with the GES constrained, only spot beam handover
takes place. The user is able to exit this constrained log-on mode by commanding
log-off, by selecting the automatic log-on mode, or by cycling SDU primary power (if
ORT item i log--on policy is auto log--on..
D. Log-On Mode Selection
(1) User selection of the automatic log-on mode while the AES is logging-on in the
constrained mode causes the SDU to abort the current log-on attempt and revert to
the automatic mode. User selection of the automatic log-on mode while the AES is
logged-on in the constrained mode causes the SDU to log-off from the current
constrained GES, and to revert to the automatic mode if there are GESs in view with
higher preference levels than the current log-on GES. User selection of the automatic
mode when the AES is logged-off causes the SDU to implement automatic log-on.
The SDU lets the user command log-off while the AES is logging-on or logged-on in
the constrained or automatic mode.
UP86308
(2) The user is able to change the selected GES if the AES is logging-on or is logged on
in the constrained mode. The user can enter the constrained mode by selecting a
specified GES while the SDU is logging-on or is logged-on in the automatic mode. In
both cases, providing the constrained GES selection is different from the
automatically chosen GES, the SDU either aborts the current log-on attempt or
logs-off from the current GES before attempting to log-on to the new GES, depending
upon the current status.
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E.
Handover
(1) The SDU causes the AES to initiate a handover procedure for the following reasons:
• Automatic handover when the AES is logged-on in the automatic or constrained
mode, because of P--channel degradation.
• Automatic handover when the AES is logged-on in the automatic mode, because
of the log-on satellite being below the elevation handover threshold specified in
ORT item xxxix, with another satellite being at least 1 degree higher than the
log-on satellite for more than 10 seconds.
• Automatic handover as specified in ORT item xxii for 10 seconds because of the
reported HGA Tx gain being less than the threshold value when the AES is
logged-on in the automatic or constrained mode.
• User command to select the constrained mode when the AES is logged-on (or
awaiting log-on acknowledge) in the automatic mode if the constrained selection is
different from the current, automatically selected GES.
• User command to select the constrained mode for a particular GES when the AES
is currently logged-on (or awaiting log-on acknowledge) to a different GES, but
also in the constrained mode.
• User command to select the automatic mode when the AES is logged-on (or
awaiting log-on acknowledge) in the constrained mode if a GES exists with a
higher preference level than the current log-on GES.
• User command to adjust the GES preference levels if the AES is logged-on (or
awaiting log-on acknowledge) in the automatic mode, and the adjustment results
in any GES having a higher preference level than the current log-on GES.
(2) The SDU logs off from the current log-on GES before logging onto the new GES for
all of the above handover stimuli, except for automatic handover because of
P--channel degradation and automatic handover because of the reported HGA Tx
gain being less than the threshold value.
(3) If any modems are being used for circuit--mode voice when a handover to a GES in a
different satellite region occurs, then the SDU terminates the current C--channel calls
with an SLCV cause of 1221x. The SDU also causes a suitable voice pacifier
message (Sorry, your call can no longer be sustained) to be sent to each currently
in-use digital or analog headset to inform each user of the reason for the call
termination. The SDU does not clear down any ongoing C--channel calls if the
handover is local to the current satellite region.
F.
Log-Off
UP86308
(1) Log-off is initiated in the AES by a user command, either from the SCDU, from the
analog-connected telephone handset, or from the CMT. Log-off is also initiated by the
SDU as part of the handover sequence, except for handovers implemented because
of P--channel degradation.
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4. System Software/Database Updates
A. General
(1) Each MCS LRU (SDU and HPA) has an ARINC 615 Airborne Data Loader (ADL) and
PDL port. The SDU and HPA are capable of transferring the data sets listed in
Table 2-1 through these ports.
Table 2-1.
LRU
SDU
HPA
Data Set Upload/Download
Data Set
Upload/Download
Operational Software
Upload Only
Owner Requirements Table
Upload and Download
Event and Failure Logs
Download Only
Maintenance Activity Log
Download Only
Periodic Data Logging (SDU system and
operational parameters)
Download Only
Operational Software
Upload Only
(2) In Table 2-1, upload is defined as the transfer of a data set from the ARINC 615 data
loader to the appropriate LRU. A download is defined as the transfer of a data set
from an appropriate LRU to the ARINC 615 data loader. The data set to be
transferred is independent of the port used. If during a data transfer session the other
port becomes active, the session associated with the initially activated port continues
to completion before initiating any session with the other port. The software upload
function is resident in the bootstrap program and functions independently of any
uploadable software in the LRU.
B. Software Upload Process
(1) The uploading of the software is done by either connecting a PDL to the ARINC 615
connector port on the LRU to be programmed, or (in the case of an ADL) by the user
selecting the LRU to be programmed. With the data loader connected, the Link A
connection is completed.
UP86308
(2) The diskette containing a configuration file and a file containing the software to be
uploaded is inserted into the disk drive of the data loader. The configuration file
contains information for the data loader (ADL or PDL) to configure itself for operation.
All MCS ORT download/upload diskettes contain a configuration file located in the
root directory of the diskette with the filename CONFIG.LDR. The data loader reads
the configuration file and initializes itself according to the parameters read. The data
loader then repeatedly transmits an RTS word.
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(3) With the operational software running, the SDU software upload is initiated only after:
• SDU senses the low impedance state on Link A.
• SDU determines it is not airborne (unless the operational software is not valid
where the on-ground/airborne state is ignored).
• SDU detects receiving an RTS word with a system address label (SAL) equal to
307.
(4) The HPA software is similarly initiated only after the requirements mentioned are
satisfied, except software uploading is also enabled when a valid air/ground status
from the SDU is not available to the LRU.
(5) For the LRUs, the software upload is a single pass process. Upload validation checks
both the LRU and SRU header records for applicability. Each data loader block is
then transferred directly to the program store. When the software upload is
completed, the program store CRC is checked over defined regions of the program
store. If either validation process fails, the software upload process aborts. Further
upload attempts can only be initiated by resetting both the data loader and the LRU.
When successfully validated, the LRU causes the data loader to initiate the transfer
complete function and the LRU remains in the data load state, while the Link A
connection remains intact. When the Link A connection is removed, the HPA
performs a POST and the SDU performs a factory settings restart. A factory settings
restart results in Category C nonvolatile data being set to default values followed by
execution of POST/PAST.
C. Validation of the Software Upload File
(1) The following items are validated when software is loaded:
• First two bytes of each LRU/SRU header record indicates a valid record type for
the record position in the data sequence.
• Company name in the LRU header record must be HONEYWELL/RACAL.
• LRU name and base part number must match the current LRU specification as
given on the LRU nameplates.
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• Software compatibility codes in each SRU ID PROM must appear in the list of
compatible hardware/software codes for every SRU listed in the LRU header.
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5. Owner Requirements Table
A. General
(1) The ORT is stored in nonvolatile memory in the SDU. The ORT contains information
relating to different areas of functionality like log-on and telephony. The ORT does
not lose its contents because of the loss of SDU primary power or as a result of
PAST. All ORT contents are set to default values by a factory settings restart. The
ORT contains all pilot and aircraft operator entered information preserved when the
SDU is powered-down.
(2) Validity of the ORT content is determined by the SDU using a checksum process.
This verification is performed at the time of each power-up. An invalid checksum
results in the SDU reverting to the default values specified in TESTING/FAULT
ISOLATION, ORT default value usage. The contents of the ORT are specified in
Appendix C.
(3) The ORT items are organized into two distinct partitions:
• Secured
• User.
(4) The individual ORT items defined in Table C--1.1 are assigned to a partition by the
designation of secured or user in the attributes column.
(5) The secured partition contains those items the equipment manufacturer, aircraft
manufacturers, and certification authorities have determined to be
configuration-dependent and crucial to the proper operation of the SATCOM system.
The user partition contains all other items of the ORT. The user partition typically
includes items the aircraft operator is able to set or modify, enabling the efficient use
of the equipment in normal operation. A composite ORT file contains all items (both
partitions) in the ORT. This version of ORT is defined to supply a consistent interface
(single ORT file) to those users that do not require the additional security supplied by
the management of two partitions for essential certification.
UP86308
(6) The content of the ORTs in both SDUs in a dual system is intended to be identical.
For the sake of ORT requirements that must be capable of being different in SDUs 1
and 2, the ORT items affected are duplicated within the ORT. Each of those items is
capable of storing separate, independent entries for SDUs 1 and 2, to be used by
each particular SDU as appropriate based on the strapping of its system
configuration pins TP13E/F. The lone SDU in a single system uses the entry for SDU
1 for duplicated items. ORT items not duplicated are said to be common, where the
single entry applies to SDUs 1 and 2 in dual systems as well as to the lone SDU in a
single system.
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6. ORT Upload/Download Process
A. General
(1) Each ORT download/upload diskette contains a configuration file. The configuration
file contains information for the data loader (ADL or PDL) to configure itself for
operation. All MCS ORT download/upload diskettes contain a configuration file
located in the root directory of the diskette with the filename CONFIG.LDR.
(2) The ORT upload/download file is named SDU_ORT.TAB. This file is made up of an
ORT header record followed by the ORT data. The ORT format version in the ORT
header record is an indication of the ORT data contained in the upload/download file.
B. Startup
(1) ORT downloading/uploading is initiated through the SCDU page or the CMT page.
The diskette containing a configuration file is inserted into the data loader, which
reads the configuration files and initializes itself according to the parameters read.
The data loader then repeatedly transmits a POLL word. The LRU detects receiving a
POLL word and initiates the ORT download/upload.
(2) In the event no configuration file is present or the diskette is not formatted, the data
loader solicits a subsystem identification. The SDU does not respond to the
command and the data loader performs a change disk or a read/write fail.
C. ORT Download
(1) The ORT file is transferred using the control mode download sequence. If insufficient
space exists to contain an ORT, the transfer operation terminates. A file name
SDU_ORT.TAB is created on the ORT diskette. This file replaces any existing file with
the same name. An ORT header is written at the head of the file. The ORT format
version written into the header is the latest version supported by the installed
software build. After transferring the header record, the ORT data is written to the file
until the whole data table is transferred. The file is then closed and a load complete
function is commanded. When an error is detected during the ORT download (i.e.,
unable to create file, ARINC 615 transfer failure, etc.) the download process aborts
and an ADL/PDL error status is indicated on the SCDU/CMT.
D. Control Mode ORT Upload Procedures
(1) Upload the ORT through the MCDU (SCDU)
(a) Make sure the ADL switch in the cockpit has SDU (SAT or SATCOM) selected, or
a PDL is connected to the SDU and the MCS system is logged off.
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(b) Insert an ORT diskette containing the ORT file SDU_ORT.TAB, plus the
CONFIG.LDR file into the ADL/PDL.
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(c) Access the SDU data loader menu from the MCDU through the following path:
• MCDU main menu
• SATCOM main menu
• Submenu
• Maintenance (Boeing Aircraft Only)
• Data loader.
(d) Make sure line 1L indicates ready.
(e) Select line 2L (*UPLD OWNER REQS).
(f)
When the MCDU displays CONNECTED, the data upload is complete. Remove
the diskette from the ADL/PDL. Disconnect the ADL/PDL from the SDU and
initiate PAST in the SDU.
(2) Upload the ORT through the CMT
(a) Make sure the PDL is connected to the SDU through the appropriate connector
on the interface cable, and the MCS system is logged off.
(b) Insert an ORT diskette containing the ORT file SDU_ORT.TAB, plus the
CONFIG.LDR file into the PDL.
(c) Access the SDU data loader menu from the CMT by performing the following key
entries from the CMT main menu:
• D (SDU maintenance menu)
• B (data loader menu).
(d) Make sure the data loader menu screen indicates PDL ready.
(e) Select G (load owner requirements table from diskette).
(f)
When the PDL diskette activity stops, push enter and make sure the CMT
displays ADL or PDL CONNECTED. The data upload is complete. Remove the
diskette from the ADL/PDL. Disconnect the PDL from the SDU and initiate PAST
in the SDU.
(3) Upload the ORT through the CMTI (Windows)
(a) Make sure the PDL is connected to the SDU through the appropriate connector
on the interface cable, and the MCS system is logged off.
(b) Insert an ORT diskette containing the ORT file SDU_ORT.TAB, plus the
CONFIG.LDR file into the PDL.
(c) Access the SDU data loader menu from the CMT by performing the following
from the CMTI main menu:
• Select the ORT menu
• Select the ORT Transfer menu
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• Select the PDL to SDU option.
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(d) Make sure the status line indicates Data Transfer in Progress.
(e) When the PDL diskette activity stops, the status line should indicate Transfer
Complete. Remove the diskette from the ADL/PDL. Disconnect the PDL from the
SDU and initiate PAST in the SDU.
E.
Auto Mode ORT Upload Procedure
(1) Make sure the PDL is connected to the SDU through the appropriate connector on
the interface cable, and the MCS system is logged off.
(2) Insert into the PDL an ORT diskette containing a CONFIG.LDR file and a ORT file
created by the ORTool as an Auto Mode, Boeing Mode, or B777 Mode Loader File
Type.
(3) Make sure the status line indicates Data Transfer in Progress.
(4) When the PDL diskette activity stops, the status line should indicate Transfer
Complete. Remove the diskette from the ADL/PDL. Disconnect the PDL from the
SDU and initiate PAST in the SDU.
7. Circuit-Mode Services
A. Circuit-Mode Voice
(1) The SDU supports cockpit and cabin voice services (refer to SYSTEM
DESCRIPTION for a description of cabin/cockpit communications) that use the
INMARSAT aeronautical satellite system. Cockpit voice services use the equipment
currently found on the flight deck (i.e., headsets, call lamps, chime, chime reset,
push-to-talk switches, and audio control panels and audio management systems) as
shown in Figure 2-1. Cabin voice services are accommodated by the following:
• CCS including a CTU interfacing with the SDU.
• Standard interwiring interfaces reserved for cabin audio to supply priority 4
services. These SDU interfaces support analog voice with in-band DTMF dialing
and some discrete signaling.
B. Circuit-Mode Data
(1) General
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(a) Once a call is established and two-way communication exists using a C--channel,
the C--channel can be used for purposes other than the initial (default) purpose
of carrying real-time voice signals using the defined codec standard.
Circuit-mode data services can be used to support a variety of communication
applications like interactive or bulk data communication, encrypted voice/data
communication, and facsimile transmission.
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Figure 2-1.
Satellite Audio System
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(2) Sub-Band Signaling
(a) Support of circuit-mode data services is achieved through the use of sub-band
signaling, and/or primary-band signaling. The call setup sequence for a
circuit-mode data call is identical to a standard telephone call setup sequence,
except when the AES must indicate to the GES circuit-mode data operation can
be invoked at some point during the call. Sub-band signaling circuit-mode data is
implemented using the data interface unit (DIU) technique, which is a
nontransparent design that uses sub-band C--channel capacity for end-to-end
signaling. These signaling transactions require diversion of the input/output (I/O)
bit-stream from the SDU codecs to either a DIU (for PC modem applications) or a
secure voice coding unit.
(3) Primary-Band Signaling
(a) Primary-band circuit-mode data is implemented using the terminal interface
function (TIF) technique, which uses primary-band C--channel capacity for
end-to-end signaling. The TIF is integrated within the SDU codec. All
circuit-mode data activation and deactivation procedures relating to circuit-mode
data operation are automatically performed within the TIF. The TIF
encodes/decodes circuit-mode PC modem data and facsimile data using an
algorithm.
8. Packet-Data Services
A. General
(1) Data services are available in the form of a standard data interface that supports
Data-2 and Data-3 as defined by INMARSAT. Data-3 complies with International
Standards Organization (ISO) standard 8208 for open systems interconnection.
Data-3 permits the operator to connect to the MCS system any data terminal
equipment (DTE) compatible with this international standard. The transmission rate
available to the operator depends on the aircraft equipment, and in particular on the
antenna gain. It also depends on the capabilities of the satellite serving that particular
region of the earth and the GES logged-on to the satellite.
(2) Within the scope of the normal mode of operation, packet mode data messages are
handled by two basic types of data service. Small messages (up to 128 bytes) are
handled by one self-contained message that includes the information required to set
up and clear the circuit as well as the data itself. This connectionless message
traverses the communication link autonomously and quickly.
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(3) Longer messages must be divided into a string of shorter messages for which a
connection-oriented circuit is set up. When the connection is established, all
subsequent data packets carry abbreviated address and control information. This
supplies more efficiency for longer messages and inquiry/response data dialogues
with no limit set on the length of individual messages.
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9. Dual SATCOM Configuration
A. Overview
(1) General
(a) Dual SATCOM configuration is one where two SDUs work together in a
master/slave relationship. This configuration also uses dual antenna systems.
(b) Dual SATCOM systems can be used to supply backup redundancy for
circuit-mode and packet-mode safety communications, or for additional
circuit-mode channel capability, or both. Each system in a dual system has the
capability to function without the other if necessary (as a sole single system while
the other has failed or is disabled), or to work with the other system as a
coordinated pair. There are three distinctions made for dual systems regarding
the SDUs:
(2) No. 1 versus No. 2
(a) This is a static distinction as determined by the programmed state of the SDU
system configuration pin. (No. 1 and No. 2 can also be referred to as left and
right, respectively, on Boeing aircraft.)
(3) Master versus Slave
(a) This is a logical and potentially dynamic distinction. Because an aircraft can have
only one ICAO address assigned to it, dual MCS systems operate with a single
master SDU and the other as slave SDU. Each SDU is capable of providing its
services with no assistance from the other SDU (e.g., when the other SDU is
powered-down). Each SDU is capable of being the master or the slave. There
are never two masters or two slaves (except during brief switching transients and
certain failure plus manual override conditions). The master does not depend on
the slave for any of the services supplied directly by the master.
(b) The master is in control. Only the master is allowed to use the P, R, and T
packet-mode channels for log-on and other satellite system management,
Data--2, Data--3, and GES--specific data broadcast (GSDB) packet-mode data
services, and circuit-mode call setups. The slave (which must be equipped with
an HGA in order to be a true slave from the perspective of offering additional
channel capacity) does not perform log-on or any packet-mode data function, but
is only used to supply additional C-channels for circuit-mode services under
control of the master. The master controls all circuit-mode call setups,
preemptions, and selective releases; normal ongoing slave system call
management (e.g., power control) and call termination are controlled by the
slave SDU.
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(c) In a dual system made up of an HGA and an LGA, if the LGA-equipped SDU is
the master, it cannot use the HGA-equipped system as a slave. The LGA master
must be capable of operation through its LGA and must log-on as a Class 1
AES. If the slave is only equipped with an LGA, it cannot function as a true slave,
but only as a standby backup system for low-rate packet-mode data services,
ready to take over as master in case the original master fails.
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(d) A system is said to be disabled when it is inhibited from making any RF
transmissions. This disabling can be because of a failure or being manually
inhibited through the control interfaces. Any disabled SDU indicates this in bit 12
of its label 276 status word. If a system is not disabled, it is enabled. When one
system is disabled, the other is usually selected, i.e., the selected system is
essentially a single system and cannot use any potential slave resources in the
disabled system. It is possible both systems can be manually disabled for special
purposes like when maintenance or deicing personnel are in close proximity to
the antennas. The master controls the system functional capability indicators and
indicates itself as the master to the MU, cabin packet data function (CPDF), and
CTU. This is true even when both SDUs are disabled (there must still be a
designated master).
(4) This versus Other
(a) This is a relational distinction where this refers to any and all SDUs in dual
systems, and other refers to the companion SDU interfaced to this SDU ARINC
429 cross-talk bus (XTB) and select/disable discretes.
B. Dual System Control/Status Interfaces
(1) Manual and automatic control of the master/slave/select/disable attributes of the two
systems are done by using the XTB between the two SDUs (one high-speed ARINC
429 bus in each direction), and by the dual system select discrete I/O and dual
system disable discrete input discretes, which are cross-wired between the two
SDUs. Figure 2-2 shows a classic wiring diagram.
(2) The select and disable discretes are normally in a high-impedance state. The select
output supplies a low-impedance to ground when it is asserting, and the select and
disable inputs are pulled low to be asserted. An optional external switch can also be
supplied to manually select one system while disabling the other. A switch normally
leaves both discretes open-circuited, enabling fully automatic control. The optional
switch can additionally have the enhanced capability of simultaneously disabling both
systems while selecting neither. Manual control is also supplied through the SCDUs
for cases where the optional external switch is not supplied.
(3) The disable discrete is an input only. It is automatically asserted by the other SDU
select output when attempting to perform an aggressive handover of mastery; it can
also be manually asserted when the crew has determined this system has failed.
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(4) The select discrete is a combination input and open-collector-type output. Activation
of this discrete by the crew indicates this system should be the sole master and it
must not attempt to use the other as a slave. If an SDU detects the other system has
failed, it can activate its own select output, which disables the other system and
typically becomes the sole master.
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Figure 2-2.
Dual System Wiring Diagram
C. System Reversion
(1) General
(a) The dual MCS system can change which SDU is master automatically or
manually. Automatic system reversion of handover of mastery from the current
master to the current slave is done through cooperative, aggressive, and special
handovers.
(2) Automatic System Reversion
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(a) Cooperative handover of mastery is performed through the XTB and does not
make use of the select/disable discretes. The current master continually
assesses the potential service capabilities of each system, including the usage of
the other’s resources as a slave for providing additional voice services. Since
different aircraft owners/operators can value the individual assessed service
capabilities differently, weighting factors are selected in the ORT to reflect the
relative importance of the various capabilities. This flexibility allows all
capabilities to be compared equally, or for any one capability to outweigh all of
the others combined, or any combination between these extremes. When the
current master determines the current slave should become the new master, the
current master indicates it is abdicating its mastery. The slave detects the
abdication of the master and takes over as master.
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(b) Aggressive handover of mastery (used when cooperation is impossible because
of XTB failure, manual intervention, or other reasons) makes use of the
select/disable discretes for mastery handover. An SDU asserts its select output
(connected to the Disable input of the other SDU) and commands Disable Other
SATCOM on its XTB output to the other SDU (in its Dual Control/Status word).
When an SDU detects its disable discrete input has been asserted, or it has
received a Disable Other SATCOM command through the XTB, it immediately
asserts its My Disable Is Asserted bit in its dual control/status word on its XTB
output, and after being so disabled for 1 second or longer, it then inhibits RF
transmissions and asserts its This SDU Is Disabled bit in its dual control/status
word.
(c) If the master SDU main processor resets itself, handover of mastery occurs
when the slave detects XTB inactive (unless the slave is externally disabled).
(3) Manual System Reversion
(a) The cockpit crew can manually select one system as the sole master and disable
the other system using an external select/disable switch or through the SCDU
disable other SATCOM line select key. This permits manual system reversion for
special cases, like undetected failures. Some external select/disable switches
may permit both systems to be disabled simultaneously for special cases
involving close proximity to the SATCOM antennas of maintenance or deicing
personnel.
(b) The SCDU line select key makes use of the XTB as well as the select/disable
discretes to send the appropriate command to the other SDU, thus optimizing the
robustness of this function.
D. Antenna Configurations
(1) A number of dual system antenna configurations can be assembled to address
various user requirements for availability and channel capability, containing various
combinations of LGA--, HGA-- or IGA--equipped systems — i.e., HGA(IGA) +
HGA(IGA), HGA(IGA) + LGA, or LGA + LGA. The IGA equipment can be used
interchangeably (when airplane installation supports) with the HGA equipment. Any
HGA in a dual (or single) system can function as a logically distinct steered LGA
when its gain drops below 7 dB. Also possible is one pseudo-dual system plus one
HGA system —i.e., (HGA+LGA) + HGA.
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(2) The basic configurations supported by the MCS dual system design are as given in
Table 2-2.
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Table 2-2.
SDU No. 1
Basic Antenna Configurations
SDU No. 2
Notes
HGA
LGA
Original ARINC 741 dual system architecture
HGA
HGA
MD--11 and 777 dual standard
LGA
LGA
-- --
HGA + LGA
HGA
SDU No. 1 is pseudo--dual
(3) Some specific examples of these configurations are shown in the following figures .
Only unique combinations (as opposed to permutations) are shown.
(4) Figure 2-3 and Figure 2-4 show the two types of the HGA + LGA configuration. This
configuration is normally capable of providing five circuit-mode channels plus one
(potentially) high-rate packet-mode data channel. It supplies single-point failure
tolerance for low--rate packet-mode data services. Channel unit redundancy within
the HGA system supplies a limited but very flexible degree of failure tolerance for
circuit-mode and high-rate packet-mode services.
(5) Figure 2-5, Figure 2-6, and Figure 2-7 shows the three types of the HGA + HGA
configuration. This configuration is normally capable of providing 10 circuit-mode
channels plus one (potentially) high-rate packet-mode data channel. It supplies
single-point failure tolerance for all grades of all services. Channel unit redundancy
within each half of the dual system supplies a limited but very flexible degree of
failure tolerance for all grades of all services before more serious failures force a
handover of mastery.
(6) Figure 2-8 shows the LGA + LGA configuration. This configuration is capable of
providing only one low-rate packet-mode data channel, and supplies single-point
failure tolerance for that capability.
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(7) Figure 2-9 thru Figure 2-12 shows the different types of the pseudo-dual (HGA +
LGA) + HGA configuration. This configuration contains all of the normal and
failure-tolerance capabilities as the HGA + HGA configuration, and adds the
capability of one low-rate packet-mode data channel in instances where both HGAs
are unusable because of trying to point into keyholes. (The use of dissimilar dual
HGAs, like those shown in Figure 2-7, helps to minimize the need for such a
configuration.)
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Figure 2-3.
HGA + LGA Configuration with Top-Mounted HGA
Figure 2-4.
HGA + LGA Configuration with Side-Mounted HGA
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Figure 2-5.
HGA + HGA Configuration with Two Top-Mounted HGAs
Figure 2-6.
HGA + HGA Configuration with Two Side-Mounted HGAs
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Figure 2-7.
HGA + HGA Configuration with One Side-Mounted HGA + One Top-Mounted
HGA (Dissimilar HGA)
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Figure 2-8.
LGA + LGA Configuration
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Figure 2-9.
(HGA + LGA) + HGA Configuration with Two Side-Mounted HGAs
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Figure 2-10.
(HGA + LGA) + HGA Configuration with the LGA Paired with
One Side-Mounted HGA
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Figure 2-11.
(HGA + LGA) + HGA Configuration with the LGA Paired with
One Top-Mounted HGA
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Figure 2-12.
E.
(HGA + LGA) + HGA Configuration with Two Top-Mounted HGAs
Cockpit Voice Configurations and Functionality
(1) System configuration pins TP13F and TP13J specify the physical wiring for the
codecs of each SDU to the possible interfaces -- a codec/channel can only be
available to the cockpit if the wiring strap is set to Cockpit or Both (and not if the
wiring is to Cabin or Neither).
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(2) An additional issue with dual systems is how to map the potentially available four
physical SDU cockpit voice channels with the one or two (maximum) usable logical
cockpit channels controllable through the audio control panels (ACPs) and the
SCDUs (i.e., as seen by the audio management system [AMS] user). Two
configurations are defined, which are identified by ORT item xlviii (Cockpit Channel
Interface Type for Dual): (1) interfacing each ACP/SCDU logical channel to one
physical channel on one SDU only (fixed), and (2) interfacing an ACP/SCDU logical
channel to one physical channel on each of the two SDUs (shared). Note the
interfacing referred to is conceptual and not necessarily physical -- i.e., for shared,
the physical wiring can be literally paralleled, or it can be simple point-to-point, with
some form of signal splitting/combining or paralleling being performed within the AMS
itself. The system configuration straps for codec wiring let the SDU determine the
physical channels which are candidate channels for each logical channel.
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10. ACARS/Aircraft Flight Information System (AFIS) Peripheral Function
A. General
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(1) The ACARS/AFIS peripheral function lets the SATCOM SDU act like any other
ACARS/AFIS peripheral to receive or send blocks of data from/to ground terminals
on the ARINC/SITA network, e.g., uplink ORTs, and downlink ORTs, call event logs,
data event logs, system management event logs, and failure logs. This functionality
integrates with the satellite subnetwork transfer capability. The requirements are
taken from ARINC 618 for the air-to-ground link and ARINC 620 for the data link
service provider requirements.
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SECTION 3
CABIN/COCKPIT COMMUNICATIONS
1. Cabin Communications
A. General
(1) Cabin communications are done with both digitally connected phones and analog
connected phones (see Figure 3-1). The user interface with digitally connected
phones is handled by the cabin communications system (CCS). The SDU has
provisions to support up to two analog connected channels, one per installed codec.
Each analog channel supports two interface types:
• Global-Wulfsberg Flitephone WH--10
• Analog Private Branch Exchange (APBX).
B. Cabin Communications System
(1) The CCS, in conjunction with the MCS avionics and a worldwide network of ground
stations, supply cabin services like telephone, facsimile, and PC data interfaces. The
CCS is partitioned into two sections:
• Cabin telecommunications unit (CTU)
• Cabin/passenger communications equipment (digitally connected telephones).
(2) The CTU performs on-board PABX telephone functions that let the digitally
connected telephones make the best use of resources supplied by the MCS avionics.
Other functions supplied by the CTU include signal processing (for example,
analog-to-digital and digital-to-analog), dial tone generation, call queuing, call
transfer, call conferencing, and generating pacifier messages (like please hold, your
call is being processed).
UP86308
(3) The CTU supplies the interface between the digitally connected phones and the
SDU. The digital phones (handsets) are primarily supplied for passenger use and
may be located throughout the aircraft. The digital handsets interface indirectly to the
satellite communications equipment and they are controlled by the CCS. Each digital
handset supplies all the normal functions of a domestic telephone. Some handset
types are battery powered and can be used anywhere in the aircraft. When not in
use, handsets are stowed in a holster with a built-in battery charger for recharging the
batteries.
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C. Analog Audio Channels
(1) General
(a) The SDU has provisions to support up to two analog channels. Each audio
channel supports two interface types:
• Global-Wulfsberg Flitephone WH--10
• Analog private branch exchange (APBX).
(b) The WH--10 is a stand-alone handset with a 12-button keypad. The APBX CTU
or handset has analog trunk lines and in-line DTMF signaling. The SDU can
support both analog handsets being connected simultaneously.
(c) Two in-use discrete outputs are supplied for analog channels 1 and 2. These
discretes are asserted (i.e., turn on the call lamps) while the voice codec
associated with that analog channel is in use (off-hook) by the analog handset.
UP86308
(d) These interfaces can be connected to individual or up to five parallel
aircraft-suitable handsets. The interface presented to the SDU must emulate a
single handset. The analog handsets, which can be located in the cabin or
cockpit areas, supply only APC priority (priority 4) level service. This does not
preclude their use for other communications, but the SDU assigns an APC
priority to the call.
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UP86308
Figure 3--1.
Audio Interfaces
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MCS--4000/7000 Multi--Channel SATCOM System
(2) Global-Wulfsberg Flitephone WH--10 Interface
(a) Taking an analog WH--10 handset off-hook results in the following processes.
The SDU to WH--10 handset actions are defined in Table 3-1.
• If the voice codec is being used by another analog phone user, the handset
may be placed in parallel with the other analog phone. Buffering and sidetone
arrangements are supplied by the analog connected phone, not by the
SATCOM equipment.
• If the voice codec is reserved by a headset user, is dedicated to a headset, or
is failed, the analog phone user hears silence.
• If the SDU is not logging-on, logged-on, or in the idle (standby) state, the
analog phone user hears silence.
• If the call barring level is 2 (ORT item xxiv), the SDU performs action 1.
• If sufficient resources are not available due to equipment failure, the SDU
performs action 2.
• If the SDU is logging-on, the SDU performs action 3.
• If the SDU is in the idle (standby) state, the SDU performs action 4.
• If a SDU modem is not available or there is not sufficient power to sustain a
new voice call, or the AES class is currently 1 or 4, the SDU performs action
5.
• Or else the SDU performs action 6 and the respective analog phone channel
is deemed usable for placing a call.
(b) If the system condition, as determined by the SDU, changes from usable (action
6) to unusable while the analog phone is off-hook and a call is not in progress,
then the appropriate handset action is performed to annunciate the new
condition. An analog channel does not change from unusable to usable while the
analog phone is off-hook unless there is a call termination on that channel.
Table 3-1.
SDU to WH-10 Handset Actions
UP86308
Action
Play message 10 as defined in Table 3-5 outgoing calls have been disallowed) followed by
an interrupted dial tone.
Play message 1 as defined in Table 3-5 (equipment failure) followed by an interrupted dial
tone.
Play message 2 as defined in Table 3-5 (attempting satellite access) followed by an
interrupted dial tone.
Play message 3 as defined in Table 3-5 (log-on disabled) followed by an interrupted dial
tone.
Play message 4 as defined in Table 3-5 (channel not available) followed by an interrupted
dial tone.
Play the dial tone.
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(c) The commands given in Table 3-2 are executable from the analog WH--10
handset. The inter-key push time-out is 15 seconds. After this time, a # sign is
automatically appended to the end of the keyed sequence by the SDU, and the
command given by the user is parsed and executed. Commands shown in the
table as not being terminated by a # sign are parsed and executed as soon as
the valid key sequence has been entered. An invalid sequence only generates
voice message 18 (Command rejected) when a # is appended, either by the user
or by the SDU after the 15-second time-out (Table 3-5).
(d) Codec-generated pacifiers or messages issued as a direct result of the user
keying a command start with one second of silence to allow the user enough
time to bring the handset to their ear. During the playing of any codec-generated
messages and pacifiers, receipt of the # key immediately mutes the codec,
aborting the current message sequence. The voice codec plays the appropriate
dial tone (normal or interrupted) as specified in Table 3-2.
UP86308
(e) An inactivity check is implemented so the SDU considers an off-hook channel to
be in the on-hook state if no call has been in progress on that channel and no
DTMF digits have been received for at least 120 seconds, except where
indicated in Table 3-2. A WH--10 handset in this state must have its hookswitch
cycled (i.e., go on-hook, then off-hook) to signal the off-hook state to the SDU.
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Table 3-2.
Command Sequence
Global-Wulfsberg Flitephone WH-10 Commands
Command Description
dddd...#
Dial a short phone number (between 2 and 6 digits – the first two can not be 00).
00dddd...#
Dial a long phone number (between 6 and 18 digits including the two leading
zeros).
*0
Redial the last called phone number
(refer to NOTE).
*m
Dial a stored phone number from memory location m (refer to NOTE).
There are 10 memory locations assigned to each of the two analog (APHONE) channels (ORT item xvi).
Memory location 0 of each channel holds the last number called on that channel. Memory locations 1 thru 9
are user-programmable. If ORT item xxvi is set to TRUE, then the channel memory locations are separate
(i.e., modifying memory locations from a handset connected to channel 1 does not affect the memory
locations assigned to channel 2). However, if ORT item xxvi is set to FALSE, then modifying memory
locations from a handset connected to channel 1 causes channel 2 memory locations to also be modified.
The store phone number memory commands are specified as follows:
**1mdddd...#
This store phone number memory command causes the phone number (dddd...) to
be stored in memory location m. If the call barring level (ORT item xxiv) is 1 or 2,
then message 9 or 10 (dialed calls have been disallowed/outgoing calls have been
disallowed) are played; otherwise, the entered data is checked. A valid command
causes message 17 (command accepted) to be played and the number stored. An
invalid command causes message 18 (command rejected) to be played.
**2#
This announce phone number memory command causes the phone numbers
stored in memory locations 1 thru 9 to be read out using a series of message 19s
(the phone number stored in memory...) for non empty locations, and message 5s
(phone number memory ... is empty.) for empty locations. If this command is
entered through the WH--10 handset, the inactivity check is disabled until the next
key-push or until the next on-hook/off-hook transition.
**2m
This announce phone number memory command causes the phone number in
memory location m to be read out using message 19 (the phone number stored in
memory ...) or message 5 (phone number memory ... is empty.). If m is not
between 1 and 9, then message 18 (command rejected) is played instead. The
digit 0 is announced as oh, not as zero.
UP86308
If the call barring level is 1 or 2 (ORT item xxiv), the SDU plays messages 9 or 10 (dialed calls have been
disallowed/outgoing calls have been disallowed) if an attempt is made to place a call. For all the following
call barring commands, an invalid security code (cccc) causes the command to be rejected and message
18 (command rejected) to be played. If the command is valid, then the action is performed and message 17
(command accepted) is played. The call barring commands are specified as follows:
**30cccc
This command sets the call barring level (ORT item xxiv) to 0, which allows all
outgoing calls.
**31cccc
This command sets the call barring level (ORT item xxiv) to 1, which disallows all
manual dialing of full-length phone numbers (6 to 18 digits starting with 00). No
memory locations can be updated using the store phone number memory
command.
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Table 3-2.
Command Sequence
Global-Wulfsberg Flitephone WH-10 Commands (cont)
Command Description
**32cccc
This command sets the call barring level (ORT item xxiv) to 2, which disallows all
outgoing calls, both manual and stored number. No memory locations can be
updated using the store phone number memory command.
**39cccc nnn nnnn
This command changes the security code to nnnn unless the first four n’s are not
the same as the second four n’s, in which case message 18 (command rejected) is
played.
**4ggg#
This command causes ggg to be the GES ID used in the access request signal unit
for any calls initiated on that channel until the next on-hook.
If ORT item xxiii is set to disable the analog (APHONE) system management commands, the following
commands are rejected; i.e., the SDU responds to the commands with message 18 (Command rejected).
The APHONE system management commands are specified as follows:
**50
This log-off/standby command sets the log-on policy (ORT item i) to User
Commanded Log-on. If already logged-on, the SDU logs off (refer to SYSTEM
OPERATION). If logging-on, the SDU terminates the logging on procedure. If the
command is valid, message 17 (command accepted) is played immediately without
waiting for the log-off to be achieved. If the SDU is already in the standby state,
then message 18 (command rejected) is played.
**51
This auto log-on command sets the log-on policy (ORT item i) to Automatic
Log-on. If the SDU is in the standby state, the SDU initiates the automatic log-on
procedure (refer to SYSTEM OPERATION). If the SDU is in the constrained log-on
mode, a handover stimulus is generated to initiate automatic satellite/GES
selection. If the command is valid, message 17 (command accepted) is played
immediately without waiting for the log-on to be achieved. If the SDU is already in
the automatic mode, message 18 (command rejected) is played.
**52ggg#
These commands set the SDU to the constrained log-on mode for selection of a
specified GES. The log-on policy (ORT item i) is set to Manual Log-on. If the SDU
is not logged-on to the GES ggg (or gggsss as appropriate), the SDU attempts a
log-on to that GES alone. Any other number of digits cause message 18
(command rejected) to be played. If the specified GES does exist in the system
table, then the command is rejected. If the command is valid, message 17
(command accepted) is played immediately without waiting for the log-on to be
achieved. If the SDU is already constrained to GES ggg (or gggsss as
appropriate), then message 18 (command rejected) is played.
**52gggsss#
**59
This log-on status command causes the SDU log-on status to be announced using
message 20 (the SATCOM is in ...). If the SDU is logged-on, message 21
(logged-on to ...) is also played. Digit 0 for the GES and satellite ID is announced
as oh.
If any of the following GES preference commands are determined to be invalid, the SDU plays messages
18 (command rejected); otherwise, if a specific message is not specified, then message 17 (command
accepted) is played. If ORT item xxiii is set to disable the APHONE system management commands, the
next three commands (the preference changing commands) are rejected; i.e., the SDU responds to the
commands with message 18 (command rejected). The GES preference commands are specified as follows.
UP86308
**60
This command sets the preference levels for all GESs to 1.
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Table 3-2.
Command Sequence
**61gggp#
**61gggsssp#
**62ggg#
**62gggsss#
Global-Wulfsberg Flitephone WH-10 Commands (cont)
Command Description
These commands cause the GES with ID ggg (or ggg and assigned to satellite sss)
to be set to preference level p in the system table. The SDU accepts either four or
seven digits following the **61... and preceding the # sign. Any other number of
digits is interpreted to be an invalid command. If no GES listed in the system table
matches the one specified in the command, the command is invalid and the user is
so informed through message 18 (command rejected).
These commands cause all current GES preference levels of 9 to be lowered to 8.
The GES with ID ggg (or ggg and assigned to satellite sss) has its preference level
set to 9. The SDU accepts either three or six digits following the 62... and
preceding the # sign. Any other number of digits is interpreted to be an invalid
command. If no GES listed in the system table matches the one specified in the
command, the command is invalid and the user is so informed through message 18
(command rejected).
**69#
This command causes all GES preference levels to be announced using a
sequence of message 22s (The preference level of GES ID...). If this command is
entered through the WH--10 handset, the inactivity check is disabled until the next
key-push, or until the next on-hook/off-hook transition.
**69ggg#
These commands cause the SDU to announce the preference level of GES ggg or
(ggg and assigned to satellite sss) using message 22 (The preference level of GES
ID...). The SDU accepts either three or six digits following the **69... and preceding
the # sign. Any other number of digits is interpreted to be an invalid command. If no
GES listed in the ORT (item iii) matches the one specified in the command, the
command is invalid and the user is so informed through message 18 (command
rejected).
**69gggsss#
UP86308
If any of the following incoming call management commands are rejected, the SDU plays messages 18
(command rejected); otherwise, if a specific message is not specified, then message 17 (command
accepted) is played. If ORT item xxiii is set to disable the APHONE system management commands, the
following commands are rejected; i.e., the SDU responds to the commands with message 18 (command
rejected). The four DDI CTid commands allow ddd to be up to three decimal digits (including leading zeros,
e.g., 02), validating the number to be within the range of 0 to 999. The incoming call management
commands are specified as follows.
**70#
This command sets ORT item xlv for APHONE Channel 1 to the default value; i.e.,
no CTid assigned.
**70ddd#
This command sets ORT item xlv for APHONE Channel 1 to ddd, Nonexclusive,
unless the configuration straps indicate Channel 1 is not wired for APHONE, or ddd
is already assigned as the CTid for Channel 2, or (in a dual system) ddd is already
assigned to one of the other SDU APHONE channels, in which case, the command
is rejected. Additionally, if ORT item xiii indicates ground-to-air Priority 4 calls are
disallowed, it is adjusted to specify routing to APHONE.
**71ddd#
This command sets ORT item xlv for APHONE Channel 1 to ddd, Exclusive, unless
the configuration straps indicate Channel 1 is not wired for APHONE, or ddd is
already assigned as the CTid for Channel 2, or (in a dual system) ddd is already
assigned to one of the other SDU APHONE channels, in which case, the command
is rejected. Additionally, if ORT item xiii indicates ground-to-air Priority 4 calls are
disallowed, it is adjusted to specify routing to APHONE.
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Table 3-2.
UP86308
Command Sequence
Global-Wulfsberg Flitephone WH-10 Commands (cont)
Command Description
**72#
This command sets ORT item xlv for APHONE Channel 2 to the default value; i.e.,
no CTid assigned.
**72ddd#
This command sets ORT item xlv for APHONE Channel 2 to ddd, Nonexclusive,
unless the configuration straps indicate Channel 2 is not wired for APHONE, or ddd
is already assigned as the CTid for Channel 1, or (in a dual system) ddd is already
assigned to one of the other SDU APHONE channels, in which case, the command
is rejected. Additionally, if ORT item xiii indicates ground-to-air Priority 4 calls are
disallowed, it is adjusted to specify routing to APHONE.
**73ddd#
This command sets ORT item xlv for APHONE Channel 2 to ddd, Exclusive, unless
the configuration straps indicate Channel 2 is not wired for APHONE, or ddd is
already assigned as the CTid for Channel 1, or (in a dual system) ddd is already
assigned to one of the other SDU APHONE channels, in which case, the command
is rejected. Additionally, if ORT item xiii indicates ground-to-air Priority 4 calls are
disallowed, it is adjusted to specify routing to APHONE.
**740#
This command sets ORT item xiii to disallowed and causes message 33 to be
played with the destination announced as disallowed.
**741#
This command sets ORT item xiii to APHONE and causes message 33 to be
played with the destination announced as APHONE, unless no codec channel is
wired for APHONE (as defined by the configuration straps), in which case, the
command is rejected and the ORT item is set to Disallowed.
**742#
This command sets ORT item xiii to DPHONE and causes message 33 to be
played with the destination announced as DPHONE, unless no codec channel is
wired for CCS (as defined by the configuration straps), in which case, the
command is rejected and the ORT item is set to Disallowed.
**743#
This command sets ORT item xiii to headset and causes message 33 to be played
with the destination announced as headset, unless no codec channel is wired for
AMS (as defined by the configuration straps), or if configuration pin TP13A is zero,
in which case, the command is rejected and the ORT item is set to Disallowed.
**750#
This command sets ORT item x to disallow incoming circuit mode data calls and
causes message 34 to be played to announce such calls as disallowed, unless
the SDU is logging on or logged on, in which case, the command is rejected.
**751#
This command sets ORT item x to allow incoming circuit mode data calls and
causes message 34 to be played to announce such calls as allowed, unless the
SDU is logging on or logged on, in which case, the command is rejected.
**79#
This command causes the SDU to announce the DDI CTid assignment for
channels 1 and 2 using message 31, if no ID is assigned, and message 32 if an ID
is assigned, where the type of ID assignment is announced as exclusive or
nonexclusive.
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Table 3-2.
Global-Wulfsberg Flitephone WH-10 Commands (cont)
Command Sequence
Command Description
Legend:
Security code digit (0 thru 9)
Decimal digit (0 thru 9)
GES ID octal digit, where ggg is in range (000 thru 377)
Memory location (1 thru 9)
New security code digit (0 thru 9)
GES preference level (0 thru 9), where 1 is the least preferred and
9 is the most preferred, and 0 indicates never to be selected for
automatic log-on
Satellite ID octal digit, where sss is in range (000 thru 076)
NOTE: There are 10 memory locations for each channel to store phone numbers (0 thru 9). Memory number 0 is used
by the SDU to store the last called phone number.
(3) Call Initiation from Analog (WH--10) Phone
(a) The analog phone user can initiate a call using any of the following commands:
• Short number manual dialing (dd...#). Between two and six digits can be
specified, with the first two digits not 00. The 00 digits are used as the
called–party address.
• Long number manual dialing (00dddd...#). Between seven and 18 digits can
be specified including the leading 00. The 00 digits are used as the
called–party address.
• Last call redial (*0). The last phone number called by an analog phone user
on a channel is used as the called–party address. If the phone number stored
in memory location 0 (i.e., last number called location) is not defined (length
field set to zero), then message 5 (phone number memory ... is empty.) is
played. Otherwise, the phone number is used as the called–party address.
• Stored phone dialing (*m). Parameter m specifies a memory location between
1 and 9. If the phone number stored in memory location m is not defined
(length field set to zero), then message 5 (phone number memory ... is
empty.) is played. Otherwise, the phone number is used as the called–party
address.
(4) Analog Private Branch Exchange (APBX) Interface
(a) General
UP86308
The APBX/SATCOM avionics interface protocol is based on the bidirectional
DTMF tones being signaled in-band. In the APBX-to-SATCOM direction, the
DTMF digits are assigned to the on- and off-hook transitions as specified in
Table 3-3, and are valid only from the APBX handset. All other DTMF digits
are common to both the WH--10 and APBX interfaces.
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Taking an APBX handset off-hook results in the same decisions as specified
for the WH--10 handset. However, the SDU to APBX off--hook actions are
specified in Table 3-4, where the DTMF tone sequence ,
(n is 0, 1, 2, or 4) sent to the APBX handset indicates the
SATCOM channel status:
• An outgoing call cannot be supported (n = 1, 2, or 4) or
• An outgoing call can be attempted (n = 0).
If the channel status indicates a call can be attempted, the SDU accepts any
command determined to be valid from an APBX interface, including the
on-hook DTMF tone. If the channel status indicates a call can not be
attempted, the APBX handset is expected to send the on-hook DTMF tone.
Otherwise, the SDU still accepts any command determined to be valid from
an APBX interface; though the checked B-party address transfer command
is guaranteed to produce a call setup failure. Subsequent to call setup
commands sent to the SDU, call setup progress, failure, and termination
DTMF tone sequences are sent to the APBX handset.
The SDU considers an off-hook channel to be in the on-hook state if no call
has been in progress on that channel and no DTMF signals have been
received for at least 120 seconds. A channel in the on hook state must issue
another DTMF off-hook signal to enable the reentry into the off-hook state.
(b) Checked Credit Card Data Transfer Command
The *2284*c*ddd# command, if valid, loads the transferred three-digit value
into the SDU calling terminal ID buffer. This data is used in place of the
default 000 in the calling terminal field of the call information service address
initial signal unit (ISU) (S5) for any outgoing call setups on this channel until
the next APBX on-hook is received. The command is accepted only if the
modulo 10 sum of all the decimal digits in the command, including 2284, the
three-digit calling terminal ID, and the check digit c is zero.
(c) Checked B-Party Address Transfer Command
UP86308
The *2262*cdddd....# command, if valid, initiates a call setup request to the
GES using the transferred digits dddd... as the B-party address and any
track 2 credit card data stored since the previous on-hook transition on this
channel. The command is only accepted if the modulo 10 sum of all decimal
digits in the command, including 2262 and the check digit c is zero. A valid
command causes the SDU to send the DTMF sequence ,
to the APBX handset. An invalid command causes the SDU to
send the DTMF sequence , to the APBX handset.
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Table 3-3.
Assignment of DTMF Digits in the APBX Interface
DTMF Digit
Low (Hz)
High (Hz)
Meaning
To/From SDU
697
1209
Both
697
1336
Both
697
1477
Both
770
1209
Both
770
1336
Both
770
1477
Both
852
1209
Both
852
1336
Both
852
1477
Both
941
1336
Both
941
1209
*/STX
To
941
1477
#/ETX
To
697
1633
FS/Answer
770
1633
Off--Hook
852
1633
Status
941
1633
On--Hook
Both
To
From
To
NOTE: STX (start sentinel), ETX (end sentinel), and FS (frame separator) are used in the transfer of ISO 7813 track 2
data from the APBX to the SDU.
Table 3-4.
UP86308
Action
SDU to APBX Off-Hook Actions
Description
Play , followed by silence (idle).
Play , followed by silence (failure).
Play , followed by silence (accessing).
Play , followed by silence (idle).
Play , followed by silence (accessing).
Play , followed by silence (available).
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2. Cockpit Communications
A. General
(1) The SDU codecs support headset interfaces for cockpit use only. These interfaces
incorporate 600-ohm, 4-wire, off-hook/on-hook signaling and dialing through the
combination of a control and display unit (either SCDU or MCDU), and (at the user’s
option) PTT, mic-on, or place/end call switches. If used, when the PTT button is
pushed, the microphone audio signal is sent to the selected voice channel; activation
of one of the discretes is signalled to the SDU. Also, an off-hook signal can be sent to
the SDU through the SCDU. An audible chime and call lamps announce a
ground-to-air call.
(2) The cockpit headsets interface with the codecs in the SDU through an audio
management unit (AMU), which is also connected to other aircraft radios. The ACP
associated with the AMU can be capable of selecting either a single or dual voice
channels for the MCS system. When single-channel AMUs are installed, voice
channel 1 is wired to AMU No. 1 and voice channel 2 is wired to AMU No. 2. This
permits operation of two independent channels. When dual-channel AMUs are
installed, voice channels No. 1 and No. 2 are wired in parallel to each AMU, enabling
two voice channels to be shared by the cockpit users.
(3) Two functionally identical voice codec modules (VCM) are installed in the SDU and
designated Codec A and Codec B.
(4) Associated with the SATCOM channels are SCDU pages, call lamps, channel
selection switches, a chime, and a chime reset. The SDU hookswitch signaling can
be supplied:
• When the ACP SATCOM channel select switch is activated
• When a PTT switch is activated
• When signaling through the SCDU, where the SDU hookswitch signaling discrete
is inactive.
(5) Once off-hook, microphone audio is supplied to the selected SATCOM voice channel
and the appropriate signaling is exchanged for call lamp and chime reset.
Conversely, once on-hook, microphone audio is removed from the selected SATCOM
voice channel and the call lamp is turned off.
B. Headset Off-Hook Signaling
(1) The headset is capable of going off-hook (to connect the call and to acknowledge the
call signaling) if the cockpit voice call light output has transitioned for either the
flashing or steady light activation, at which time:
UP86308
• If the latched ACP hookswitch signaling is strapped, the headset is considered
off-hook whenever the cockpit voice mic-on input is activated (connected to
ground).
• If the switched PTT hookswitch signaling is strapped, the headset is considered
off-hook whenever the cockpit voice mic-on input is activated for the first time after
the call light activation for an incoming call, or when the place/end call input is
activated to initiate an outgoing call.
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MCS--4000/7000 Multi--Channel SATCOM System
(2) If ORT item xliii is enabled, the headset is capable of going off-hook when ANSWER
CALL is selected on the SATCOM main menu page (TESTING/FAULT ISOLATION)
after the call light activation and irrespective of hookswitch signaling.
C. Headset On-Hook Signaling
(1) If latched ACP hookswitch signaling is strapped, the headset is placed on-hook when
an open is present on the cockpit voice mic-on input. Regardless of the hookswitch
signaling, the cockpit voice place/end call 1 and 2 discrete inputs place the headset
interface on-hook for cockpit audio channels 1 and 2, respectively, when a call clear
event occurs. If ORT item xliii is enabled, the selection of END CALL or REJECT on
the SATCOM main menu page (TESTING/FAULT ISOLATION) places the headset
interface on-hook. Placing the headset on-hook results in normal call termination.
D. Voice Codec Module Audio Switching
(1) Headsets and analog connected phones interface to the SDU through the VCMs.
Using a switch internal to the modules, each VCM can be connected to one of the
cabin audio interfaces, or to one of the cockpit audio interfaces (or to both). Each
VCM can be switched between either of its audio interfaces as follows:
• Codec A can be used in conjunction with either cabin audio No. 1 (WH--10 or
APBX) or cockpit audio No. 1
• Codec B can be used in conjunction with either cabin audio No. 2 (WH--10 or
APBX) or cockpit audio No. 2.
E.
Voice Codec Module Sidetone
(1) Sidetone is supplied by each VCM. The sidetone level is adjustable for the cockpit
audio, and is set to off for cabin audio. The adjustment range for cockpit sidetone is
from 0 dB below the receive audio to off, with the default value set to 14.1 dB below
the receive audio level. This setting is stored in nonvolatile memory within the SDU.
F.
Voice Interface Module Stored Audio Messages
(1) The VIMs are capable of playing standard telephony supervisory lone signals, DTMF
tones, and voice messages to the headset and analog phone users. These pacifiers
are only sent to the analog interfaces:
• Headset
• WH--10 handsets
• APBX handsets.
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(2) Stored audio messages are summarized in Table 3-5.
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 3-5.
Stored Audio Messages
UP86308
Message No.
Message
Sorry, equipment failure, please refer to the user guide.
Sorry, attempting satellite access, please try later.
Sorry, log-on disabled, please refer to the user guide.
Sorry, no channel available, please try later.
Phone number memory is empty.
Sorry, your call can no longer be sustained, please try later.
Sorry, your call has been preempted, please try later.
Sorry, connection failure, please try later.
Sorry, dialed calls have been disallowed, please refer to the user guide.
10
Sorry, outgoing calls have been disallowed, please refer to the user guide.
11
Sorry, number unobtainable.
12
Sorry, number busy, please try later.
13
Sorry, network congestion, please try later.
14
Sorry, credit card not honored at the ground station.
15
Sorry, access unauthorized.
16
Please wait, connecting your call.
17
Command accepted.
18
Command rejected.
19
The phone stored in memory is ...
20
The SATCOM is in | mode.
21
Logged on to GES ID .
22
The preference level of GES ID on satellite is
.
23
Equipment failure, equipment failure.
24
No channel available, no channel available.
25
Your call can no longer be sustained.
26
Your call has been preempted.
27
Connection failure, connection failure.
28
Number unobtainable, number unobtainable.
29
Number busy, number busy.
30
Network congestion, network congestion.
31
Channel terminal ID is not assigned.
32
Channel terminal ID is .
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 3-5.
Stored Audio Messages (cont)
Message No.
Message
33
Ground-to-air public calls destination set to .
34
Ground-to-air circuit mode data calls are .
G. Voice Interface Module Dedication
(1) Each voice interface module (VIM) has the property of dedication, which is different
from the codec wiring. This property is of value on aircraft that have both headset
and cabin (analog and digital) interface wiring, where contention for codec use can
arise. Each VIM dedication is set to cabin, headset, or automatic through ORT item
vi.
(2) A VIM with its dedication set to automatic can be allocated to a headset call or a
cabin call, and is allocated on a first-come, first-served basis. A VIM can be
reallocated to a headset call of priority 1, 2, or 3 through the preemption mechanism.
A VIM with its dedication set to cabin is dedicated to its cabin (WH--10 or APBX)
interface.
UP86308
(3) A VIM with its dedication set to headset is unusable by the cabin interface. A VIM can
be reallocated to a different headset call of priority 1, 2, or 3 through the preemption
mechanism. ORT item vii (Appendix C) specifies whether a modem and HPA power
should be reserved for a VIM dedicated to headset. This lets the pilot reserve one
channel for cockpit use only.
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UP86308
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SYSTEM DESCRIPTION, INSTALLATION AND MAINTENANCE MANUAL
MCS-4000/7000
TEMPORARY REVISION NO. 23-1
INSERT PAGE 2 OF 6 FACING PAGE 4-1.
Reason:
To add cooling information and to update applicable equipment and figure references.
Steps 1.A.(1), 3.A.(1), and 3.A.(2) are changed as follows:
1. Overview
A. General
(1)
This section contains information on how and where to mount each component of the MCS
system. For new installations, plan the installation in three stages. First, determine the location of
the LRUs in the aircraft. Next, determine the length of RF and electrical interconnections for
selected locations and finally, determine how the LRUs are to be cooled in regards to the
placement of the LRUs.
3. Mechanical Installation Design
UP86308
A. LRU Mechanical Installation
(1)
The SDU and HPA are installed in mounting racks (ARINC 600) typically in the equipment bay of
the aircraft. For a SATCOM installation, the primary installation dependent parameter is the RF
coax cable loss requirements identified in Table 4-1 and cooling requirements identified in
Section E and Table 4-2 of this document. To make sure these requirements are met, some
installations require the HPA(s) be installed in close proximity to the antenna subsystem
components. Refer to the aircraft installation drawings for the location of the SATCOM
equipment. For new installations, refer to Table 4-1 to determine the location of the SATCOM
equipment to make sure the cable loss requirements are met as well as the cooling specifications
in Section E are met.
(2)
Mechanical installation data for the SDU, HPA, HSDU, and RFUIA are shown in Figure 4-2 thru
Figure 4-5.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
SECTION 4
MECHANICAL INSTALLATION
1. Overview
A. General
(1) This section contains information on how and where to mount each component of the
MCS system. For new installations, plan the installation in two stages. First,
determine the location of the LRUs in the aircraft. Next, determine the length of RF
and electrical interconnections for selected locations.
2. Equipment and Materials
A. General
(1) Refer to SYSTEM DESCRIPTION for mounting tray and mating connector
information. For all other components, refer to the applicable Outline and Installation
Diagram in this section.
(2) No additional special equipment or materials, other than those commonly used in the
shop, are required to install the units in existing trays and clamps, and to adjust the
system. Do not over tighten mounting screws. Where torque values are not given, it
is acceptable to finger tighten the mounting screws.
3. Mechanical Installation Design
A. LRU Mechanical Installation
(1) The SDU and HPA are installed in mounting racks (ARINC 600) typically in the
equipment bay of the aircraft. For a SATCOM installation, the primary installation
dependent parameter is the RF coax cable loss requirements identified in Table 4-1.
To make sure these requirements are met, some installations require the HPA(s) be
installed in close proximity to the antenna subsystem components. Refer to the
aircraft installation drawings for the location of the SATCOM equipment For new
installations, refer to Table 4-1 to determine the location of the SATCOM equipment
to make sure the cable loss requirements are met.
UP86308
(2) Mechanical installation data for the SDU, HPA (40 Watt), HPA (20 Watt), IGA ,
D/LNA, and RFUIA are shown in Figure 4-2 thru Figure 4-7.
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MCS--4000/7000 Multi--Channel SATCOM System
CAUTION: BEFORE AN LRU IS INSTALLED, PULL THE CIRCUIT BREAKERS THAT
SUPPLY POWER TO THE LRU TO REMOVE POWER.
CAUTION: MOISTURE AND DIRT CAUSE DAMAGE TO LRUs.
CAUTION: LRU FAILURE RATES INCREASE WITH A RISE IN TEMPERATURE.
INSTALL THE LRUs WITH CLEARANCE; LET THE AIR FLOW ON TOP
AND BOTTOM OF LRUs TO PREVENT OVERHEATING.
CAUTION: MAKE SURE THAT THE LATEST ORT DATABASE SOFTWARE IS
INSTALLED IN THE SDU BEFORE PERFORMING SYSTEM
OPERATIONS.
NOTE: Honeywell/Racal recommend the MCS LRUs be installed so their installation
is level (zero degrees) to the horizontal plane of the aircraft. Compliance with
RTCA/DO--160C has been demonstrated with this orientation.
NOTE: Ambient temperature at the LRU location must be less than 40 °C (104 °F)
during operation for best reliability.
B. Installation Dependent Considerations
(1) Refer to the SYSTEM DESCRIPTION section for the installation dependent
considerations for the SDU.
C. Owner Requirements Table (ORT) Uploading
(1) When the SDU is changed, the ORT needs to be uploaded before normal operation
can begin. Refer to the SYSTEM OPERATION section for the ORT upload
procedures.
D. Cable Loss Requirements
(1) The attenuation and voltage standing wave ratio (VSWR) of coaxial cable used in the
MCS system must meet the requirements specified in Table 4-1 to make sure the
system operates correctly. Figure 4-1 shows the specific cable attenuations for the
SATCOM equipment. All specified cable attenuations include connector losses, which
are assumed to be 0.1 dB each. Honeywell recommends each cable assembly be
sweep tested for loss and VSWR.
UP86308
Figure 4-1.
Cable Attenuations
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MCS-4000/7000
TEMPORARY REVISION NO. 23-1
INSERT PAGE 3 OF 6 AND PAGE 4 OF 6 FACING PAGE 4-2.
Reason:
To update the third CAUTION and the first NOTE and to delete the second NOTE before
Paragraph 3.B., and to change Figure 4-1.
The third CAUTION and the NOTES are updated and deleted, and Figure 4-1 is changed as follows:
CAUTION:
BEFORE AN LRU IS INSTALLED, PULL THE CIRCUIT BREAKERS THAT
SUPPLY POWER TO THE LRU TO REMOVE POWER.
CAUTION:
MOISTURE AND DIRT CAUSE DAMAGE TO LRUs.
CAUTION:
LRU FAILURE RATES INCREASE WITH A RISE IN OPERATIONAL
TEMPERATURE BEYOND LRU-SPECIFIED COOLING LEVELS. INSTALL THE
LRUs WITH CLEARANCE. LET THE AIR FLOW ON TOP AND BOTTOM OF LRUs
TO PREVENT OVERHEATING.
CAUTION:
MAKE SURE THAT THE LATEST ORT DATABASE SOFTWARE IS INSTALLED IN
THE SDU BEFORE PERFORMING SYSTEM OPERATIONS.
NOTE:
Honeywell/Thales recommends the MCS LRUs be installed so their installation is level
(zero degrees) to the horizontal plane of the aircraft. Compliance with RTCA/DO-160D
has been demonstrated with this orientation.
UP86308
B. Installation Dependent Considerations
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TEMPORARY REVISION NO. 23-1
UP86308
Figure 4-1.
Cable Attenuations
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MCS-4000/7000
TEMPORARY REVISION NO. 23-1
INSERT PAGE 5 OF 6 AND PAGE 6 OF 6 FACING PAGE 4-3.
Reason:
To update Table 4-1, to update the cooling requirements in Step 3.E., and to update Table 4-2.
Table 4-1, Step 3.E., and Table 4-2 are changed as follows:
Table 4-1. Cable Loss Requirements
Cable Assembly
Location
Minimum Loss
Maximum Loss
Maximum VSWR
TX Cable
Between SDU, HSU,
and HPA
1 dB
20 dB
2.0
RX Cable
Between Diplexer/LNA
and SDU
6 dB
25 dB
2.0
TX Cable
Between HPA and
Diplexer/LNA
N/A
1.4 dB 1.
1.3
RX Cable
Between Diplexer/LNA
and Antenna
N/A
0.3 dB
1.3
NOTES:
1.
2.
In installations that use a high power relay (HPR), the HPR loss must be included. The maximum Tx cable loss
between the HGA and the antenna must not exceed 2.5 dB.
N/A = Not applicable.
E. Cooling Requirements
UP86308
(1)
The cooling requirements for the MCS avionics are specified in Table 4-2 as follows:
•
Power dissipation is in Watts
•
Mass airflow is in pounds per hour
•
CF/M is cubic feet per minute at sea level and 104°F (40°C)
•
Pressure drop is in inches of water.
(2)
If the LRUs are to be operated above an altitude where the flow rates defined in Table 4-2 cannot
be met, then the units must be installed in a pressurized compartment that provides a means to
meet the Table 4-2 cooling requirements.
(3)
The temperature of the cooling air for the LRUs must not exceed 104°F (40°C).
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TEMPORARY REVISION NO. 23-1
Table 4-2. Cooling Requirements
Power Dissipation
LRU
Max.
Nom.
Mass Airflow
Max.
Min.
CF/M
Max.
Pressure Drop
Min.
Max.
Min.
SDU
150
105
96
(44 kg/hr)
73
(33 kg/hr)
23
18
0.25
(6.35 mm)
0.15
(3.81 mm)
HPA (60W)
425
250
176
(80 kg/hr)
121
(55 kg/hr)
42
29
0.25
(6.35 mm)
0.2
(5.0 mm)
HSU
100
55
63
(29 kg/hr)
49
(22 kg/hr)
15
11
0.25
(6.35 mm)
0.15
(3.81 mm)
UP86308
NOTE: The SDU draws an additional 20 W during the first 10 minutes (maximum) of operation at 25°C because of the
oven controlled crystal oscillator (OCXO). The OCXO continuously dissipates this additional 20 W at −55°C.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Table 4-1.
Cable Assembly
Cable Loss Requirements
Location
Minimum Loss
Maximum Loss
Maximum VSWR
TX Cable
Between SDU and
HPA
19 dB
25 dB 1.
TBD
RX Cable
Between
Diplexer/LNA and
SDU
6 dB
25 dB 2.
TBD
TX Cable
Between HPA and
Diplexer/LNA
1.4 dB
TBD
RF Cable
Between
Diplexer/LNA and
Antenna
0.3 dB
TBD
NOTES:
1.
In installations that use a combiner, the combiner loss must be included.
2.
In installations that use a high power relay (HPR), the HPR loss must be included. The maximum Tx cable loss
between the HGA and the antenna must not exceed 2.5 dB.
E.
Cooling Requirements
(1) The cooling requirements for the MCS avionics are specified in Table 4-2 as follows:
• Power dissipation is in Watts
• Mass airflow is in pounds per hour
• CF/M is cubic feet per minute at sea level and 40 °C (104 °F)
• Pressure drop is in inches of water.
(2) In most cases, a cooling system that meets the sea level requirements also meets
the cooling requirements at --55 °C (--67 °F) and 70,000 feet.
Table 4-2.
Power
Dissipation
Cooling Requirements
Mass Airflow
CF/M
Pressure Drop
LRU
Max.
Nom.
Max.
Min.
Max.
Min.
Max.
Min.
SDU
198
105
96 (44 kg/hr)
73 (33 kg/hr)
23
18
0.25
(6.35 mm)
0.15
(3.81 mm)
HPA
(40W)
362
300
176 (80 kg/hr) 121 (44 kg/hr)
42
29
0.25
(6.35 mm)
0.15
(3.81 mm)
HPA
(20W)
180
150
96 (44 kg/hr)
23
18
0.3
(7.62 mm)
0.2
(5.08 mm)
73 (33 kg/hr)
UP86308
NOTE: The SDU draws an additional 20 W during the first 10 minutes (maximum) of operation at 25 _C because of the
oven controlled crystal oscillator (OCXO). The OCXO continuously dissipates this additional 20 W at --55 _C.
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F.
Vendor Supplied Equipment
UP86308
(1) Installation equipment like mounting trays, connectors, and cables can be obtained
from various vendors. Refer to Appendix A for additional information about vendor
manufactured equipment. For vendor supplied avionics, refer to the vendor
documentation.
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SYSTEM DESCRIPTION, INSTALLATION,
AND MAINTENANCE MANUAL
MCS-4000/7000
TEMPORARY REVISION NO. 23-2
INSERT PAGE 3 OF 3 FACING PAGE 4-5/(4-6 BLANK).
Reason:
To change drawing data for Figure 4-2.
UP86308
Figure 4-2 is changed as follows:
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Figure 4-2.
Satellite Data Unit Outline and Installation Diagram
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UP86308
Figure 4-3.
40 Watt High Power Amplifier Outline and Installation Diagram
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UP86308
Figure 4-4 (Sheet 1).
20 Watt High Power Amplifier Outline and Installation Diagram
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UP86308
Figure 4-4 (Sheet 2).
20 Watt High Power Amplifier Outline and Installation Diagram
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UP86308
Figure 4-5 (Sheet 1).
Intermediate Gain Antenna Outline and Installation Diagram
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UP86308
Figure 4-5 (Sheet 2).
Intermediate Gain Antenna Outline and Installation Diagram
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UP86308
Figure 4-6 (Sheet 1).
D/LNA Outline and Installation Diagram
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UP86308
Figure 4-6 (Sheet 2).
D/LNA Outline and Installation Diagram
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UP86308
Figure 4-7 (Sheet 1).
RFUIA Outline and Installation Diagram
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UP86308
Figure 4-7 (Sheet 2).
RFUIA Outline and Installation Diagram
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MCS--4000/7000 Multi--Channel SATCOM System
SECTION 5
ELECTRICAL INSTALLATION
1. Overview
A. General
(1) This section supplies electrical installation procedures, power distribution, and
interconnect diagrams for each component of the MCS system.
2. Equipment and Materials
A. General
(1) None.
3. Electrical Installation Procedure
A. Connector Layout and Contact Arrangement
(1) Each front panel connector of the SDU and HPA complies with ARINC characteristic
615, and is used to interface the LRU with an ARINC 615 portable data loader for
software uploads. Pin callouts are specified in Table 5-1. See the MECHANICAL
INSTALLATION section for specifics regarding connector part numbers for the ARINC
615 connector for each LRU and the corresponding mating connector.
UP86308
(2) The rear connectors of the SDU ,HPA, and RFUIA comply with ARINC characteristic
600 as specified in Table 5-2. The ARINC 600 connector layouts and contact
arrangement for the various connector plugs for each LRU of the MCS system are
shown in Figure 5-1 thru Figure 5-10.
23--20--27
Page 5--1
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MCS--4000/7000 Multi--Channel SATCOM System
Table 5-1.
UP86308
Pin
ARINC 615 Connector Pin Callouts
SDU Signal Name
HPA Signal Name
PDL 429 A IN
PDL TO HPA 429 A
PDL 429 B IN
PDL TO HPA 429 B
SHIELD GND
CHASSIS GND
PDL 429 A OUT
HPA TO PDL 429 A
PDL 429 B OUT
HPA TO PDL 429 B
11
SPARE RX RS232
-- --
13
SPARE TX RS232
-- --
16
SHIELD GND
COMMON GND
18
PDL LINK A
PDL LINK A NO
19
GND (PDL LINK B)
GND (PDL LINK B)
20
115 VAC HOT
115 VAC HOT
21
CHASSIS GND
CHASSIS GND
22
115 VAC COLD
115 VAC GND
25
CTU RX RS232 FUTURE USE
-- --
27
CTU TX RS232 FUTURE USE
-- --
32
WH10 MIC HI
-- --
33
WH10 MIC LO
-- --
34
WH10 SPEAKER HI
-- --
35
WH10 SPEAKER LO
-- --
36
WH10 HOOKSWITCH
-- --
40
RS232 A RX--DLT
-- --
41
RS232 A TX--DLT
-- --
42
RS232 B RX--CMT
RS232 TO HPA
43
RS232 B TX--CMT
RS232 TO DEBUG
48
LOGIC COMMON
COMMON GROUND
49
LOGIC COMMON
COMMON GROUND
50
DL FUNCTION DISC 1
-- --
51
DL FUNCTION DISC 2
-- --
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 5-2.
ARINC 600 Connector Requirements
LRU
Connector Description
SDU
ARINC 600 -- Size 6
MCU No. 2 Shell
LRU Rear
Connector Part
No.
Rack Mounting
Connector Part No.
Outline Diagram
620--600--022
(Radiall)
NSXN2P201X0004
(Radiall)
Figure 4-2,
Figure 5-1,
Figure 5-2,
Table 5-3, and
Table 5-4
620--600--076
(Radiall)
NSXN2P221X0008
(Radiall)
Figure 4-3
Figure 5-3 thru
Figure 5-6
620--600--076
(Radiall)
NSXN2P221X0008
(Radiall)
Figure 4-4,
Figure 5-3,
Figure 5-7,
Figure 5-8, and
Figure 5-9
• Type 02 Top Insert
• Type 02 Middle Insert
• Type 04 Bottom Insert
• Index Pin Code 04
HPA
(40 W)
ARINC 600 -- Size 8
MCU No. 2 Shell
• Type 08 Top Insert
• Type 05 Middle Insert
• Type 04 Bottom Insert
• Index Pin Code 08
HPA
(20 W)
ARINC 600 -- Size 4
MCU No. 2 Shell
• Type 08 Top Insert
• Type 05 Middle Insert
• Type 04 Bottom Insert
• Index Pin Code 08
RFUIA
ARINC 600 -- Size 4
MCU No. 2 Shell
NSXNR221X0103 NSXNP221S0103
(Radiall)
(Radiall)
Figure 4-7 and
Figure 5-10
• Type 08 Top Insert
• Type 05 Middle Insert
• Type 04 Bottom Insert
UP86308
• Index Pin Code 03
23--20--27
Page 5--3
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MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Figure 5-1.
SDU ARINC 600 Connector Layout
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Table 5-3.
Contact Arrangements for Top Insert, SDU ARINC 600 Connector
ANALOG
CABIN
VOICE
CHANNEL 1
HOOK-SWITCH
ANALOG
CABIN
VOICE
CHANNEL 2
HOOK-SWITCH
WH10--1
STATUS
(RINGER)
WH10--1
STATUS
(RINGER)
WH10--2
STATUS
(RINGER)
WH10--2
STATUS
(RINGER)
AVIONICS
SUB-SYSTEM
SATCOM
FAIL
WARNING
(NON MCS
FAIL)
ANALOG
CABIN
VOICE
CHANNEL 1
IN--USE
SATELLITE
LINK NOT
READY
ANALOG
CABIN
VOICE
CHANNEL 2
IN--USE
ANALOG
PBX
CHANNEL 1
INPUT HI
ANALOG
PBX
CHANNEL 1
INPUT LO
ANALOG
PBX
CHANNEL 1
OUTPUT HI
ANALOG
PBX
CHANNEL 1
OUTPUT LO
ANALOG
PBX
CHANNEL 2
INPUT HI
ANALOG
PBX
CHANNEL 2
INPUT LO
ANALOG
PBX
CHANNEL 2
OUTPUT HI
ANALOG
PBX
CHANNEL 2
OUTPUT LO
COCKPIT
VOICE UN-AVAILABLE
ANALOG
CABIN
VOICE UN-AVAILABLE
PACKET
DATA UN-AVAILABLE
PACKET
DATA LOW
SPEED ONLY
AVAILABLE
SATCOM IN-OPERABLE
(MCS FAIL)
CEPT--E1
0V SHIELD
(GND)
CEPT--E1 to
BRIDGED
CTU
(CM--250) 1A
CEPT--E1 to
BRIDGED
CTU
(CM--250) 1B
CEPT--E1 to
BRIDGED
CTU
(CM--250) 2A
CEPT--E1 to
BRIDGED
CTU
(CM--250) 2B
APM PWR
OUT FUTURE
USE
APM PWR
RTN FUTURE
USE
APM CLK
OUT FUTURE
USE
APM DATA
OUT FUTURE
USE
APM DATA IN
FUTURE USE
APM WE
OUT 1
FUTURE USE
APM WE
OUT 2
FUTURE USE
APM EN1
FUTURE USE
APM EN2
FUTURE USE
CEPT--E1
0V
CTU SLOOP
CTU SLOOP
CTU SLOOP
CTU SLOOP
CTU SLOOP
CTU SLOOP
CTU SLOOP
CTU SLOOP
CTU SLOOP
CTU SLOOP
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
RESERVED
BY ARINC
741
SPARE
DISCRETE
INPUT
CONFIG
STRAP TYPE
SPARE
DISCRETE
INPUT
CONFIG
STRAP TYPE
10
AVAIL OF
429 SSR
MODE S
ADDRESS
RESERVED
FOR FMC
CONFIG
RESERVED
FOR FMC
CONFIG
CMU
BUS
SPEED
CPDF
CONFIG
RESERVED
FOR STRAP
OPTION
RESERVED
FOR STRAP
OPTION
RESERVED
FOR STRAP
OPTION
RESERVED
FOR STRAP
OPTION
CALL LIGHT
ACTIVATOR
CONFIGU-RATION
11
STRAP
PARITY
(ODD)
CCS
PRESENCE
IRS
CONFIG
IRS
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
12
CFDS/CMC
TYPE
CFDS/CMC
TYPE
CFDS/CMC
TYPE
RESERVED
A/C ID
OR CFDS/
SDU
CONFIG
SDU
CONFIG
SDU
NUMBER
CMU
NO. 1
CONFIG
CMU
NO. 2
CONFIG
MCDU/
SCDU
NO. 1
CONFIG
MCDU/
SCDU
NO. 2
CONFIG
13
PRIORITY
4 CALLS
MCDU/
SCDU
BUS SPEED
LIGHT/
CHIME
CODE
LIGHT/
CHIME
CODE
MCDU/
SCDU
NO. 3
CONFIG
SDU
CODEC 1
WIRING
SDU
CODEC 1
WIRING
SDU
CODEC 2
WIRING
SDU
CODEC 2
WIRING
COCKPIT
SIGNALING
METHOD
14
5V
POS_MON
9V
POS_MON
RESERVED
ATE
RESET-MON_N
PEIT_SEL_N
RESERVED
ATE
RESERVED
ATE
RESERVED
ATE
CEPT--E1
FROM
BRIDGED
CTU
(CM--250)1A
CEPT--E1
FROM
BRIDGED
CTU
(CM--250)1A
15
15 V
POS_MON
15 V
NEG_MON
GND (ATE
COMMON)
CEPT--E1
FROM
BRIDGED
CTU
(CM--250) 2A
CEPT--E1
FROM
BRIDGED
CTU
(CM--250) 2A
DLT_RX
(RS232
RX--SDU)
DLT_TX
(RS232
TX--SDU)
CMT_RX
(RS232
RX--SDU)
CMT_TX
(RS232
TX--SDU)
CMT_DLT_
RTN
23--20--27
Page 5--5
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MCS--4000/7000 Multi--Channel SATCOM System
Table 5-4.
Contact Arrangements for Middle Insert, SDU ARINC 600 Connector
WH10 CABIN
NO. 1
AUDIO IN HI
WH10 CABIN
No. 1
AUDIO IN LO
WH10 CABIN
No. 1
AUDIO OUT
HI
WH10 CABIN
No. 1
AUDIO OUT
LO
DATA BUS
FROM CABIN
PACKET
DATA A
DATA BUS
FROM CABIN
PACKET
DATA B
FROM CMU
NO. 1
429
FROM CMU
NO. 1
429
TO CMU
NO. 1 AND
NO. 2
429 A
TO CMU
NO. 1 AND
NO. 2
429 B
COCKPIT
AUDIO CH 1
INPUT HI
COCKPIT
AUDIO CH 1
INPUT LO
COCKPIT
AUDIO CH 1
OUTPUT HI
COCKPIT
AUDIO CH 1
OUTPUT LO
COCKPIT
AUDIO CH 2
INPUT HI
COCKPIT
AUDIO CH 2
INPUT LO
COCKPIT
AUDIO CH 2
OUTPUT HI
COCKPIT
AUDIO CH 2
OUTPUT LO
CEPT--E1
FROM CTU
INPUT A
CEPT--E1
FROM CTU
INPUT B
CEPT--E1 TO
CTU OUTPUT
CEPT--E1 TO
CTU OUTPUT
DATA FROM
SCDU
NO. 1
DATA FROM
SCDU
NO. 1
DATA FROM
SCDU
NO. 2
DATA FROM
SCDU
NO. 2
DATA FROM
CMU
NO. 2
DATA FROM
CMU
NO. 2
DATA TO
SCDU NO. 1,
NO. 2, AND
NO. 3
DATA TO
SCDU NO. 1,
NO. 2, AND
NO. 3
AES
ID
INPUT
AES
ID
INPUT
FROM
CFDS
FROM
CFDS
TO
CFDS
TO
CFDS
MULTI-CONTROL
OUTPUT
MULTI-CONTROL
OUTPUT
WH10 CABIN
NO. 2
AUDIO IN
HI
WH10 CABIN
NO. 2
AUDIO IN
LO
LGA LNA
ON/OFF
CONTROL
WH10 CABIN
NO. 2
AUDIO OUT
LO
BITE INPUT
FROM LGA
LNA
CHIME/
LIGHT
INHIBIT
DUAL
SYSTEM
SELECT
DISCRETE
I/O
DUAL
SYSTEM
SELECT
DISCRETE
INHIBIT
UP86308
WEIGHT--ON--WHEELS
INPUT
NO. 1
INPUT
NO. 2
PROGRAM
SELECT
WH10 CABIN
NO. 2
AUDIO OUT
HI
DATA FROM
PRIMARY
IRS A
DATA FROM
PRIMARY
IRS B
DATA FROM
SECONDARY
IRS A
DATA FROM
SECONDARY
IRS B
BITE INPUT
FROM
HGA/HPA A
BITE INPUT
FROM
HGA/HPA B
SPARE 429
INPUT
SPARE 429
INPUT
BITE INPUT
FROM
LGA/HPA A
BITE INPUT
FROM
LGA/HPA B
DATA BUS
FROM
AIRBORNE
LOADER
DATA BUS
FROM
AIRBORNE
LOADER
DATA BUS
TO
AIRBORNE
LOADER
DATA BUS
TO
AIRBORNE
LOADER
BSU NO. 1
AND NO. 2
STEER
INHIBIT
BSU NO. 1
AND NO. 2
STEER
INHIBIT
BITE INPUT
FROM ACU
OR
TOP--PORT
BSU A
BITE INPUT
FROM ACU
OR
TOP--PORT
BSU B
BITE INPUT
FROM STBD
BSU
BITE INPUT
FROM STBD
BSU
DATA
LOADER
LINK A
DATA
LOADER
LINK B
RESERVED
FOR DATA
BUS FROM
RMP A
RESERVED
FOR DATA
BUS FROM
RMP B
CP VOICE
CALL LGT
OUTPUT
NO. 1
CP VOICE
MIC ON
INPUT
NO. 1
CP VOICE
CALL LGT
OUTPUT
NO. 2
CP VOICE
MIC ON
INPUT
NO. 2
DATA FROM
SCDU
NO. 3
DATA FROM
SCDU
NO. 3
DATA BUS
TO SNU OR
CPDF A
DATA BUS
TO SNU OR
CPDF B
RESERVED
FOR DATA
TO RMP A
RESERVED
FOR DATA
TO RMP B
RESERVED
DATA BUS
RESERVED
DATA BUS
RESERVED
DATA BUS
RESERVED
DATA BUS
CEPT--E1
FROM 0BE1
CEPT--E1
FROM 0BE1
10
CEPT--E1 TO
0BE1 A
CEPT--E1 TO
0BE1 B
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
11
FROM
MOTION
SENSOR
NO. 1
MOTION
SENSOR
NO. 1
PROGRAM
SELECT
CALL
CANCEL
DISCRETE
INPUT
NO. 1
CALL
CANCEL
DISCRETE
INPUT
NO. 2
RESERVED
UNSPEC
PROGRAM
RESERVED
UNSPEC
PROGRAM
RESERVED
UNSPEC
PROGRAM
RESERVED
UNSPEC
PROGRAM
RESERVED
UNSPEC
PROGRAM
RESERVED
UNSPEC
PROGRAM
CROSSTALK
FROM
OTHERSDU
CROSSTALK
FROM
OTHERSDU
CROSSTALK
TO
OTHERSDU
CROSSTALK
TO
OTHERSDU
SPARE
SPARE
12
RESERVED
FOR DATA
FROM
FMC 1
RESERVED
FOR DATA
FROM
FMC 1
RESERVED
FOR DATA
FROM
FMC 2
RESERVED
FOR DATA
FROM
FMC 2
SPARE
DISCRETE
OUTPUT
28 VDC CALL
LAMP TYPE
SPARE
13
ICAO
ADDRESS
BIT NO. 1
(MSB)
ICAO
ADDRESS
BIT NO. 2
ICAO
ADDRESS
BIT NO. 3
ICAO
ADDRESS
BIT NO. 4
ICAO
ADDRESS
BIT NO. 5
ICAO
ADDRESS
BIT NO. 6
ICAO
ADDRESS
BIT NO. 7
ICAO
ADDRESS
BIT NO. 8
14
CP VOICE
GO--AHEAD
CHIME
RESET
NO. 1
CP VOICE
CHIME
CONTACT
CP VOICE
CONTACT
ICAO
ADDRESS
BIT NO. 9
ICAO
ADDRESS
BIT NO. 10
ICAO
ADDRESS
BIT NO. 11
ICAO
ADDRESS
BIT NO. 12
ICAO
ADDRESS
BIT NO. 13
ICAO
ADDRESS
BIT NO. 14
ICAO
ADDRESS
BIT NO. 15
15
ICAO
ADDRESS
BIT NO. 16
ICAO
ADDRESS
BIT NO. 17
ICAO
ADDRESS
BIT NO. 18
ICAO
ADDRESS
BIT NO. 19
ICAO
ADDRESS
BIT NO. 20
ICAO
ADDRESS
BIT NO. 21
ICAO
ADDRESS
BIT NO. 22
ICAO
ADDRESS
BIT NO. 23
ICAO
ADDRESS
BIT NO. 24
(LSB)
ICAO
ADDRESS
COMMON
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Figure 5-2.
Contact Arrangements for Bottom Insert, SDU ARINC 600 Connector
23--20--27
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UP86308
Figure 5-3.
HPA ARINC 600 Connector Layout
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Figure 5-4.
Contact Arrangements for Top Insert, HPA (40 Watt) ARINC 600 Connector
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Figure 5-5.
Contact Arrangements for Middle Insert, HPA (40 Watt) ARINC 600 Connector
23--20--27
Page 5--10
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MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Figure 5-6.
Contact Arrangements for Bottom Insert, HPA (40 Watt) ARINC 600 Connector
23--20--27
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UP86308
Figure 5-7.
Contact Arrangements for Top Insert, HPA (20 Watt) ARINC 600 Connector
23--20--27
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UP86308
Figure 5-8.
Contact Arrangements for Middle Insert, HPA (20 Watt) ARINC 600 Connector
23--20--27
Page 5--13
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MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Figure 5-9.
Contact Arrangements for Bottom Insert, HPA (20 Watt) ARINC 600 Connector
23--20--27
Page 5--14
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UP86308
Figure 5-10.
RFUIA ARINC 600 Connector Layout
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
B. Electrical Installation
(1) The information necessary to supply the electrical interconnects is shown in
Figure 5-11 thru Figure 5-26. Interconnect diagrams are as follows:
• Figure 5-11. Satellite Data Unit Interface Diagram
• Figure 5-12. WH--10 Handset Interface Diagram
• Figure 5-13. Four--to--Two Wire Interface Diagram
• Figure 5-14. Avtech Fax Interface Diagram
• Figure 5-15. HF--SAT Transfer Panel Interface Diagram
• Figure 5-16. Signal Conditioning Unit Interface Diagram
• Figure 5-17. Maintenance Panel Assembly Interface Diagram
• Figure 5-18. Intermediate Gain Antenna Interface Diagram
• Figure 5-19. CMC Top--Mount High Gain Antenna Interface Diagram
• Figure 5-20. Tecom Top--Mount High Gain Antenna Interface Diagram
• Figure 5-21. Racal Mechanically Steered High Gain Antenna Interface Diagram
• Figure 5-22. AMT--50 Mechanically Steered High Gain Antenna Interface Diagram
• Figure 5-23. Dassault Conformal High Gain Antenna Interface Diagram
• Figure 5-24. Ball Conformal High Gain Antenna Interface Diagram
• Figure 5-25. Low Gain Antenna Interface Diagram
• Figure 5-26. Toyocom Top--Mount High Gain Antenna Interface Diagram.
(2) The applicable configuration pins in the aircraft wiring must be connected to make the
MCS system functional. The SDU receives and sends 30 system configuration
discrete inputs through the configuration pins to properly match the avionics
equipment installed on the aircraft (see Figure 5-11 and Paragraph 4. to identify the
configuration pins).
UP86308
(3) The SDU receives a 24-bit ICAO address that identifies the aircraft in which the SDU
is installed (Figure 5-11). Continuity is defined as a resistance of 10 ohms or less
between a configuration pin or address pin and the common. Continuity is broken
when the resistance between a configuration pin or address pin and common
measures 100k ohms or greater.
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Figure 5-11 (Sheet 1).
Satellite Data Unit Interface Diagram
23--20--27
Page 5--17
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UP86308
Figure 5-11 (Sheet 2).
Satellite Data Unit Interface Diagram
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 5-5.
ICAO Block Strapping
Example: AES ID 53375006 (Octal)
Octal
Binary
SDU Connector Pin (MP)
C13
D13
E13
F13
G13
H13
J13
K13
D14
E14
F14
G14
H14
J14
K14
A15
B15
C15
D15
E15
F15
G15
H15
J15
Common
K15
UP86308
NOTES:
1.
53375006 (Octal) = 101011011111101000000110 (Binary).
2.
Binary 1 = Open; Binary 0 = Ground.
3.
Pins assigned a zero (0) are wired to SDU connector pin MP--K15 (common).
23--20--27
Page 5--19
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UP86308
Figure 5-12.
WH--10 Handset Interface Diagram
23--20--27
Page 5--20
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UP86308
Figure 5-13.
Four--to--Two Wire Interface Diagram
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Figure 5-14.
Avtech Fax Interface Diagram
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UP86308
Figure 5-15.
HF--SAT Transfer Panel Interface Diagram
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Figure 5-16.
Signal Conditioning Unit Interface Diagram
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Figure 5-17.
Maintenance Panel Assembly Interface Diagram
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UP86308
Figure 5-18.
Intermediate Gain Antenna Interface Diagram
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UP86308
Figure 5-19.
CMC Top--Mount High Gain Antenna Interface Diagram
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UP86308
Figure 5-20.
Tecom Top--Mount High Gain Antenna Interface Diagram
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Figure 5-21.
Racal Mechanically Steered High Gain Antenna Interface Diagram
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Figure 5-22.
AMT--50 Mechanically Steered High Gain Antenna Interface Diagram
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Figure 5-23.
Dassault Conformal High Gain Antenna Interface Diagram
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Figure 5-24.
Ball Conformal High Gain Antenna Interface Diagram
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UP86308
Figure 5-25.
Low Gain Antenna Interface Diagram
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UP86308
Figure 5-26.
Toyocom Top--Mount High Gain Antenna Interface Diagram
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4. Configuration Pins
A. General
(1) The following paragraphs supply system configuration pins definition and
interpretation information. Pins assigned to take on the binary one state in a given
code should be left as an open circuit. Pins assigned to take on the binary zero state
in the code should be wired to SDU connector pin MP15K (address common) on the
airframe side of the connection. The configuration pins are listed in Table 5-6.
Table 5-6.
Configuration Pins
UP86308
Pin
Definition
TP10A
AVAILABILITY OF ARINC 429 SSR MODE S ADDRESS (AES ID) FROM 429 PORTS
TP10B
FMC CONNECTION TO SDU
TP10C
FMC CONNECTION TO SDU
TP10D
ARINC 429 BUS SPEED TO/FROM CMU NO. 1 AND CMU NO. 2
TP10E
CPDF CONFIGURATION
TP10F
429 BUS SPEED OF AES ID INPUT
TP10G
RESERVED FOR STRAP OPTION
TP10H
RESERVED FOR STRAP OPTION
TP10J
RESERVED FOR STRAP OPTION
TP10K
CALL LIGHT ACTIVATION
TP11A
STRAP PARITY (ODD: COVERING THE OTHER 39 STRAP PINS)
TP11B
CCS PRESENCE
TP11C
IRS CONFIGURATION
TP11D
IRS CONFIGURATION
TP11E
HPR/HPA/BSU/LGA CONFIGURATION
TP11F
HPR/HPA/BSU/LGA CONFIGURATION
TP11G
HPR/HPA/BSU/LGA CONFIGURATION
TP11H
HPR/HPA/BSU/LGA CONFIGURATION
TP11J
HPR/HPA/BSU/LGA CONFIGURATION
TP11K
HPR/HPA/BSU/LGA CONFIGURATION
TP12A
CFDS TYPE
TP12B
CFDS TYPE
TP12C
CFDS TYPE
TP12D
PAD FOR CFDS/SDU CONFIGURATION
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Table 5-6.
Configuration Pins (cont)
Pin
Definition
TP12E
SDU CONFIGURATION
TP12F
SDU NUMBER
TP12G
CMU NO. 1 CONFIGURATION
TP12H
CMU NO. 2 CONFIGURATION
TP12J
MCDU/SCDU NO. 1 CONFIGURATION
TP12K
MCDU/SCDU NO. 2 CONFIGURATION
TP13A
PRIORITY 4 CALLS TO/FROM COCKPIT
TP13B
ARINC 429 BUS SPEED TO MCDU/SCDU NO. 1, NO. 2, AND NO. 3
TP13C
COCKPIT VOICE CALL LIGHT/CHIME OPTIONS
TP13D
COCKPIT VOICE CALL LIGHT/CHIME OPTIONS
TP13E
MCDU/SCDU NO. 3 CONFIGURATION
TP13F
SDU CODEC 1 WIRING
TP13G
SDU CODEC 1 WIRING
TP13H
SDU CODEC 2 WIRING
TP13J
SDU CODEC 2 WIRING
TP13K
COCKPIT HOOKSWITCH SIGNALING METHOD
B. Availability of ARINC 429 SSR MODE S (AES ID) from CMU Ports
(1) The interpretation of this configuration pin is given in Table 5-7.
Table 5-7.
UP86308
TP10 Pin A
Availability of ARINC 429 SSR MODE S (AES ID) from CMU Ports
Interpretation
SSR MODE S ADDRESS (AES ID) NOT AVAILABLE FROM CMU NO. 1 NOR
RESERVED AES ID INPUT
SSR MODE S ADDRESS (AES ID) IS AVAILABLE FROM CMU NO. 1 AND/OR CMU
NO. 2 AND/OR AES ID INPUT
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(2) When wired to the zero state, the TP10A configuration pin indicates the SSR mode S
address (AES ID) is available in the ARINC 429 label 275/276 format from one or
both of the SDU CMU input ports or the AES ID input port, and that one of those
ARINC 429 sources of the address is used with no specific preference for CMU 1,
CMU 2, CMU 3, or the AES ID input. In this state, the discrete inputs on SDU pins
MP13C thru MP13K and MP14D thru MP14J are not assumed to be wired and the
SDU does not use the discretes, even if the ARINC 429 sources fail or remain
inactive.
(3) In the zero state, the SDU monitors the CMU 1, CMU 2, and AES ID input buses until
a valid ICAO address is received. Bits 1 thru 16 of the AES ID are obtained from the
label 275 word and bits 17 thru 24 are obtained from the label 276 word. The SDU
only constructs a full 24-bit address from labels 275 and 276 words received from the
same input port (e.g., label 275 from CMU 1 can not be combined with label 276 from
CMU 2 or the AES ID input). The address is only considered valid if it does not
consist of all zeros or ones, and has been received in ARINC 429 words with their
sign--status matrix (SSM) indicating normal operation.
(4) If address words containing either all zeros or ones are received, followed by address
words with a valid address (i.e., not all zeros or ones), the SDU verifies the receipt of
both labels 275 and 276 at least twice with the same address bits content in each
respective word before declaring the address valid. This is to preclude the SDU from
inadvertently and prematurely assuming the address is valid after only one of the two
labels has yielded a valid segment of the overall address, but the most previously
received copy of the other label has not yet been updated to its intended code. The
root problem is that the 24 correlated address bits are transmitted in two separate
asynchronous words that are not inherently correlated/paired. This requirement is
intended to effectively pair the label 275 and 276 transmissions.
(5) Once a valid ICAO address is received on any bus, the SDU ignores further data
received on any of the buses until the next POST/PAST. This requirement relieves
the SDU of having to deal with the possibility that the ICAO technical address might
change while the SDU is logged-on. The AES ID (ICAO address) is determined at
startup and cannot change until the next POST/PAST. The SDU does not log-on until
it has a valid AES ID. The SDU waits indefinitely to receive a valid address from an
available ARINC 429 source rather than giving up at the end of POST/PAST, since it
cannot proceed as an AES without the address. If the configuration pin indicates the
ARINC 429 source is available, the discretes are not wired. The SDU should not
revert to the discretes at the end of POST/PAST as the CMU may not yet be
operational.
(6) If configuration pin TP10A is wired to the one state, then neither CMU input port nor
the AES ID input port is capable of supplying the AES ID in the ARINC 429 format
and the SDU reads the AES ID from the discrete inputs.
UP86308
(7) With either the ARINC 429 or discrete inputs source, an AES ID of all zeros or all
ones (binary) is invalid (typically indicative of an unprogrammed address) which
constitutes a failure. The SDU does not attempt to log-on to a GES with an invalid
AES ID.
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C. FMC Connection to SDU
(1) The interpretation of these configuration pins is given in Table 5-8.
Table 5-8.
FMC Connection to SDU
TP10 Pins
FMC NO. 1 CONNECTED, FMC NO. 2 CONNECTED
FMC NO. 1 CONNECTED, FMC NO. 2 NOT CONNECTED
FMC NO. 1 NOT CONNECTED, FMC NO. 2 CONNECTED
NEITHER FMC CONNECTED
Interpretation
NOTE: SATCOM does not support the FMC interface.
(2) When individually wired to the zero state, configuration pins TP10B and TP10C
indicate respectively that the inputs designated for FMC No. 1 and FMC No. 2 (pins
MP12G/MP12H and MP12J/MP12K, respectively) are connected to a ARINC 429
source of flight plan information (next way point, etc.). The SDU only
logs/reports/indicates bus inactivity on either bus if the respective configuration pin
indicates the bus is supposed to be connected to an ARINC source. The SDU can
assume (for functional purposes) the presence of the flight management computer
(FMC) connections from the state of these configuration pins.
D. ARINC 429 Speed to/from CMU No. 1 and CMU No. 2
(1) The interpretation of this configuration pin is given in Table 5-9.
Table 5-9.
ARINC 429 Speed to/from CMU No. 1 and CMU No. 2
TP10 Pin D
Interpretation
LOW SPEED ARINC 429 DATA BUS
HIGH SPEED ARINC 429 DATA BUS
UP86308
(2) When this configuration pin is wired to the zero state, the SDU operates its input and
output ARINC 429 buses for the CMUs No. 1 and No. 2 at high speed. When wired to
the one state, the SDU operates these buses at the low speed.
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E.
Cabin Packet Data Function (CPDF)
(1) The interpretation of this configuration pin is given in Table 5-10.
Table 5-10.
Cabin Packet Data Function (CPDF)
TP10 Pin E
Interpretation
CPDF CONNECTED
CPDF NOT CONNECTED
(2) When wired to the zero state, this configuration pin indicates the input designated for
the CPDF (MP1E and MP1F) is connected to an ARINC 429 source of data--3 packet
data and that the SDU output (pins MP9A and MP9B) is wired to the CPDF. The SDU
only logs/reports/ indicates CPDF failures and bus inactivity on the CPDF input bus if
this configuration pin indicates the bus is supposed to be connected to an ARINC
source. The SDU can assume (for functional purposes) the presence of the CPDF
connections from the state of this pin.
F.
ARINC 429 BUS Speed of AES ID Input
(1) The interpretation of these configuration pins is given in Table 5-11 and Table 5-12.
Table 5-11.
ARINC 429 Bus Speed of AES ID Input
TP10 Pin F
Interpretation
HIGH SPEED ARINC 429 BUS
LOW SPEED ARINC 429 BUS
Table 5-12.
Call Light On (Air/Ground Calls)
TP10 Pin K
Interpretation
CALL LIGHT ON AT CALL INITIATION (FOR AIR/GROUND CALLS)
CALL LIGHT ON AT CALL CONNECTION (FOR AIR/GROUND CALLS)
G. Strap Parity (ODD)
(1) The interpretation of this configuration pin is given in Table 5-13.
Table 5-13.
UP86308
TP11 Pin A
Strap Parity (ODD)
Interpretation
SUM OF ALL OTHER STRAPS SET TO 1 IS ODD
SUM OF ALL OTHER STRAPS SET TO 1 IS EVEN
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(2) The coverage of the parity pin is SDU connector pins TP10A thru TP10K and TP11B
thru TP13K (39 pins other than itself). The parity pin is programmed to a zero or one
to yield an odd number of strap bits set to the one state, including the parity pin itself.
(3) The parity pin is wired to yield odd parity over all 40 configuration pins (i.e., the parity
pin is programmed to the zero or one state to yield an odd number of configuration
pins wired to the one state, including itself. The SDU verifies the state of the parity
pin is correct when the configuration pins are read (typically once per power cycle just
after power-up). An invalid state of the parity pin is logged/reported/indicated; the
states of the other configuration pins are used as read despite the parity error.
H. Cabin Communications System (CCS)
(1) The interpretation of this configuration pin is given in Table 5-14.
Table 5-14.
Cabin Communications System (CCS)
TP11 Pin B
Interpretation
CCS INSTALLED
CCS NOT INSTALLED
(2) The state of this configuration pin is ignored. The SDU can assume (for functional
purposes) the presence of the CCS connections from the state of this pin.
UP86308
(3) Before the availability of software package C, aircraft can be fitted with interim
versions of the CCS that make use of the analog PBX interface. These installations
set the configuration pin to the zero state, but other analog PBX installations can not
so its state should be ignored in such prepackage C systems.
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I.
Inertial Reference System (IRS)
(1) The interpretation of these configuration pins is given in Table 5-15.
Table 5-15.
Inertial Reference System (IRS)
TP11 Pins
PRIMARY IRS INSTALLED, SECONDARY IRS INSTALLED
PRIMARY IRS INSTALLED, SECONDARY IRS NOT INSTALLED
PRIMARY IRS NOT INSTALLED, SECONDARY IRS INSTALLED
PRIMARY IRS NOT INSTALLED, SECONDARY IRS NOT INSTALLED
Interpretation
(2) When individually wired to the zero state, configuration pins TP11C and TP11D
indicate, respectively, that the inputs designated for the primary and secondary IRSs
(MP6A/MP6B and MP6C/MP6D, respectively) are connected to an ARINC 429
source of IRS label 310, 311, 312, 314, 324, 325, and 361 information (although label
361, Inertial Altitude, is not required for SATCOM). The actual IRS (i.e., IRS No. 1,
IRS No. 2, or IRS No. 3) driving either SDU input is determined from the source
destination identifier (SDI) bits of the received ARINC words. The SDU only
logs/reports/indicates bus inactivity on either bus if the respective configuration pin
indicates that the bus is supposed to be connected to an ARINC 429 source. The
SDU can assume (for functional purposes) the presence of the IRS connections from
the state of these pins.
J.
HPA/Antenna Subsystem Configuration
UP86308
(1) The interpretation of these configuration pins is given in Table 5-16.
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Table 5-16.
HPA/Antenna Subsystem Configuration
✱
✱
✱
✱
✱
✱
✱
TP11 Pins
L B
G S
A U
H H
P G
A A
✱
F E
O D
F O
U R
H H H U M
G P P R F
A A R E R
✱
✱
✱
✱
✱
✱
✱
✱
✱
✱
✱
✱
✱
✱
✱
✱
✱
✱
✱
Note 1.
✱
Note 1.
✱
✱
✱
✱
UP86308
NOTES:
1.
Not defined at this time.
2.
Other configurations are possible and can be added at a later date.
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(2) For functional purposes, the SDU assumes the HPA and antenna subsystem
configuration of its particular installation from states of these configuration pins.
However, configurations 100111 and 000111 are not supported. Both of the
nonsupported configurations involve the sharing of a single HPA between an LGA
and HGA, by using a high power relay (HPR). No control or BITE signal interfaces
are specified for the HPR, the MCS system does not accommodate these
configurations.
(3) The SDU commands the system, uses its resources, and logs/reports/indicates
failures in the HPAs and antenna subsystem based on the determined HPA and
antenna subsystem configuration. Inactivity on the SDU input buses from the HPA(s)
and ACU/BSU(s) and failures against the diplexer/LNA and HPR are
logged/reported/indicated if the respective LRU is specified to be connected
according to these pins. If these configuration pins are set to a nonsupported,
reserved for future, or reserved for Mfr state, the SDU logs/reports/indicates the
appropriate strap failure(s) and does not attempt any satellite communication
functions.
K. CFDS/CMC
(1) The interpretation of these configuration pins is given in Table 5-17.
Table 5-17.
CFDS/CMC
TP12 Pins
UNDEFINED
McDONNELL--DOUGLAS TYPE CFDS
AIRBUS TYPE CFDS
HONEYWELL CAIMS
BOEING TYPE CMC
UNDEFINED
UNDEFINED
CFDS NOT INSTALLED
Interpretation
UP86308
(2) For functional purposes, the SDU can assume the type of central fault/maintenance
system (if any) that is connected from the state of these configuration pins. The
CMC/CFDS interface operates according to the determined type. The appropriate
strap failure(s) is(are) logged/indicated if an undefined code is present. The SDU only
logs/reports/indicates bus inactivity for the MP4C/MP4D CFDS interface input bus if
the configuration pins indicate the CMC/CFDS is supposed to be installed.
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L.
SDU Configuration
(1) The interpretation of this configuration pin is given in Table 5-18.
Table 5-18.
SDU Configuration
TP12 Pin E
Interpretation
SECOND SDU INSTALLED
SECOND SDU NOT INSTALLED
(2) When wired to the zero state, this configuration pin indicates a second SDU is
present as part of the MCS system installation. The zero state also indicates pins
MP12C/MP12D and MP12A/MP12B (cross talk to and from the other SDU,
respectively) and MP5j/MP5K (dual system select and dual system disable discretes,
respectively) are connected to the second SDU. When this pin is in the zero state, it
also indicates these signals are used to determine dual SATCOM operation as
specified in SYSTEM OPERATION. The SDU only logs/reports/indicates inactivity on
its input cross--talk bus from the second SDU when this pin is in the zero state. The
SDU can assume (for functional purposes) the presence of a second SDU from the
state of this configuration pin. The SDU also uses the state of this pin (and for dual
SATCOM installations, the state of SDU number pin TP12F) to determine the state of
its output word SDI fields.
M. SDU Number
(1) The interpretation of this configuration pin is given in Table 5-19.
Table 5-19.
TP12 Pin F
SDU Number
Interpretation
SDU NO. 2
SDU NO. 1
NOTE: The state of this strap is Don’t Care for a single SDU configuration.
UP86308
(2) When wired to the zero state, this configuration pin indicates this SDU is No. 2 in a
dual MCS system installation. The one state indicates this SDU is No. 1 in a dual
installation. The SDU uses the state of this pin and the SDU configuration pin TP12E
to determine the state of its output word SDI fields. In a single MCS system
installation, the status of this configuration pin is ignored.
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N. CMU No. 1 and No. 2 Configuration
(1) The interpretation of these configuration pins is given in Table 5-20 and Table 5-21.
Table 5-20.
TP12 Pin G
CMU No. 1
Interpretation
CMU NO. 1 INSTALLED
CMU NO. 1 NOT INSTALLED
Table 5-21.
TP12 Pin H
CMU No. 2
Interpretation
CMU NO. 2 INSTALLED
CMU NO. 2 NOT INSTALLED
(2) When individually wired to the zero state, configuration pins TP12G and TP12H
indicate, respectively, that the inputs designated for CMU No. 1 and CMU No. 2 (pins
MP1G/MP1H and MP3G/MP3H, respectively) are connected to an ARINC 429
source of CMU information (e.g., CMU label 270 and SAL 304), and also the single
SDU output (pins MP1J/MP1K) is wired to the appropriate CMU(s). The SDU only
logs/reports/indicates bus inactivity on either CMU input bus if the respective
configuration pin indicates the bus is supposed to be connected to an ARINC source.
The SDU can assume (for functional purposes) the presence of the CMU
connections from the state of these configuration pins.
O. MCDU/SCDU No. 1 thru No. 3 Configuration
(1) The interpretation of these configuration pins is given in Table 5-22 thru Table 5-24.
Table 5-22.
MCDU/SCDU No. 1
TP12 Pin J
Interpretation
MCDU/SCDU NO. 1 INSTALLED
MCDU/SCDU NO. 1 NOT INSTALLED
Table 5-23.
MCDU/SCDU No. 2
UP86308
TP12 Pin K
Interpretation
MCDU/SCDU NO. 2 INSTALLED
MCDU/SCDU NO. 2 NOT INSTALLED
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Table 5-24.
MCDU/SCDU No. 3
TP13 Pin E
Interpretation
MCDU/SCDU NO. 3 INSTALLED
MCDU/SCDU NO. 3 NOT INSTALLED
(2) When individually wired to the zero state, configuration pins TP12J, TP12K, and
TP13E indicate, respectively, that the inputs designated for MCDU/SCDU No. 1, No.
2, and No. 3 (pins MP3C/MP3D, MP3E/MP3F, and MP8J/MP8K, respectively) are
connected to an ARINC 429 source of line select/keypad control information, and
also the single SDU output (MP3J/MP3K) is wired to all appropriate MCDU/SCDU(s).
The SDU only logs/reports/indicates bus inactivity on any of the three buses if the
respective configuration pin indicates the bus is supposed to be connected to an
ARINC source. The SDU can assume (for functional purposes) the presence of the
MCDU/SCDU connections from the state of these configuration pins.
P.
Priority 4 Calls to/from Cockpit
(1) The interpretation of this configuration pin is given in Table 5-25.
Table 5-25.
Priority 4 Calls to/from Cockpit
TP13 Pin A
Interpretation
DISALLOW PRIORITY 4 CALLS
ALLOWS PRIORITY 4 CALLS
UP86308
(2) When this configuration pin is wired to the zero state, the SDU disallows priority 4
calls from being routed to or initiated from the cockpit. This state prevents ORT item
xiii (Appendix C) from being set to allow routing of ground-to-air priority 4 calls to the
cockpit headset. When this configuration is wired to the one state, the SDU lets
priority 4 calls be initiated from the cockpit and lets ground-to-air calls be routed to
the cockpit based upon ORT item xiii.
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Q. ARINC 429 BUS Speed to SCDU No. 1 / SCDU No. 2 / SCDU No. 3
(1) The interpretation of this configuration pin is given in Table 5-26.
Table 5-26.
ARINC 429 Bus Speed to SCDU No. 1 / SCDU No. 2 / SCDU No. 3
TP13 Pin B
Interpretation
LOW SPEED ARINC 429 BUS
HIGH SPEED ARINC 429 BUS
(2) When this configuration pin is wired to the zero state, the SDU operates its ARINC
429 output bus for MCDU/SCDUs No. 1, No. 2, and No. 3 at the low speed. When
wired to the one state, the SDU operates this bus at the high speed.
R. Cockpit Voice Call Light/Chime Option
(1) The interpretation of these configuration pins is given in Table 5-27.
Table 5-27.
Cockpit Voice Call Light/Chime Option
TP13 Pins
SPARE
STEADY LIGHTS AND MULTISTROKE CHIME
FLASHING LIGHTS AND SINGLE STROKE CHIME
STEADY LIGHTS AND SINGLE STROKE CHIME
Interpretation
(2) The SDU determines the mode of cockpit call annunciation (flashing vs. steady voice
call lamp, multistroke vs single stroke chime) from the states of these configuration
pins. The functionality of the cockpit call annunciation interface (pins MP8E and
MP8G for the call lights, and MP14B and MP14C for the chime) operate according to
the configuration pin connections selected. The selected state of pins TP13C and
TP13D applies to both air- and ground-initiated calls; it only applies to the call
annunciation phase (i.e., following connection acknowledgement by receipt of the
off-hook state as specified by the state of TP13K, a multistroke chime is silenced and
the call lamp remains on steady). The appropriate strap failure(s) is logged/indicated
if an undefined code is present. The SDU defaults to the steady lights and single
stroke chime state if an undefined code is present.
UP86308
(3) The steady versus flashing light option applies to the call annunciation phase only.
The light remains on (steady) for the duration of the call after the acknowledgement
of the annunciation for either the steady or flashing light option.
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S.
SDU CODEC 1 and CODEC 2 Wiring
(1) The interpretation of these configuration pins is given in Table 5-28 and Table 5-29.
Table 5-28.
SDU Analog Interface No. 1 Wiring
TP13 Pins
AMS WIRED, CABIN AUDIO WIRED
AMS WIRED, CABIN AUDIO NOT WIRED
AMS NOT WIRED, CABIN AUDIO WIRED
AMS NOT WIRED, CABIN AUDIO NOT WIRED
Interpretation
Table 5-29.
SDU Analog Interface No. 2 Wiring
TP13 Pins
AMS WIRED, CABIN AUDIO WIRED
AMS WIRED, CABIN AUDIO NOT WIRED
AMS NOT WIRED, CABIN AUDIO WIRED
AMS NOT WIRED, CABIN AUDIO NOT WIRED
Interpretation
(2) The SDU determines the extent and nature of the analog cockpit and cabin voice
connections from the states of these configuration pins. The functionality of the
analog cockpit and cabin voice interface (pins MP1A/MP1B, MP1C/MP1D,
MP2A/MP2B, MP2C/MP2D, MP2E/MP2F, MP2G/MP2H, MP4J/MP4K, and
MP5E/MP5F) operate according to the connections selected. ORT item vi for codec
dedication (Appendix C) is related to the SDU codec configuration pins; dedication or
automatic sharing of a codec to or with a particular interface is only possible if the
SDU codec wiring straps indicate the codec is wired to that interface.
T.
Cockpit Hookswitch Signaling Method
(1) General
(a) The interpretation of this configuration pin is given in Table 5-30.
Table 5-30.
UP86308
TP13 Pin K
Cockpit Hookswitch Signaling Method
Interpretation
SWITCHED PTT AND/OR SCDU LINE SWITCH(ES)
LATCHED AUDIO CONTROL PANEL SATCOM MICROPHONE SWITCH
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(b) This configuration pin specifies the functionality of the SDU Cockpit Voice
Mic-On Input No. 1 (and No. 2) discrete inputs (referred to as the mic-on
inputs). When TP13K is wired to the one state, the SDU utilizes the switched
PTT and/or SCDU line switch(es) (referred to as switched PTT) method for
cockpit hookswitch signaling on the mic-on inputs. When TP13K is wired to the
zero state, the SDU utilizes the latched audio control panel SATCOM
microphone switch (referred to as the latched ACP) method. These two
methods are described below.
(2) Switched PTT Method
(a) With the switched PTT method, the SDU assumes the mic-on inputs are wired to
conventional microphone momentary push-to-talk switches (i.e., they are
dynamically active [on/off] throughout the duration of the call). The SDU
assumes the air- or ground-initiated call annunciation to have been
acknowledged (i.e., the call to in the off-hook state) when the appropriate mic-on
input is activated (connected to ground) for the first time after the call
annunciation for a particular channel. Successive activations of that mic-on input
for the duration of that call have no effect on the status of that call until the call
has been cleared.
(b) With the switched PTT method, the off-hook state is also entered following
activation of the Answer Call line select switch on the SCDU. The on-hook state
is entered following activation of the End Call line select switch on the SCDU
that results in call clearing.
(c) This method also allows usage of the place/end call discrete input and
associated switch to initiate calls to preselected numbers, as well as to terminate
existing calls.
(3) Latched ACP Method
(a) With the latched ACP method, the SDU assumes the mic-on inputs are wired to
SATCOM microphone select switches on the ACP that are latched on
(connected to ground) for the entire duration of a call. The SDU considers the
air- or ground-initiated call annunciation to have been acknowledged (i.e., the
call to be in the off-hook state) when the appropriate mic-on input is active
(connected to ground) for a particular channel. The call is cleared and the
channel is considered to be in the on-hook state when the mic-on input is in the
open-circuit state.
(b) With the latched ACP method, all hookswitch signaling for answering and
terminating all air- and ground-initiated calls is handled by the mic-on inputs; the
SCDU Answer Call and End Call options are blanked (the SCDU is only
necessary for specifying the called-party number and initiating the call process
for air-to-ground calls).
UP86308
(c) This method also allows usage of the mic--on discrete input and switch to initiate
calls to preselected numbers.
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UP86308
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SECTION 6
TESTING/FAULT ISOLATION
1. Overview
A. General
(1) This section defines the built-in test equipment (BITE) requirements for the MCS
system (i.e., SDU and HPA). Information supplied in this section describes how MCS
system failures are detected, recorded, and reported. See Figure 6-1 for an overview
of the BITE system communications. Refer to Appendix D for an explanation of the
fault codes obtained by any troubleshooting process.
(2) System BITE contributes to a number of maintenance functions:
• Detection of internal and external failures
• Storage of in-flight failure data
• Reporting failure status in the air and on the ground
• Ground test capability for isolating faulty LRUs, performance verification, and
system level testing.
UP86308
Figure 6-1.
System BITE Communication
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B. Definitions
(1) Degraded Operation
(a) Degraded operation is defined as the condition when the MCS system is
operating with a failure that results in diminished capability (e.g., some, but not
all channel units available, or less than nominal HPA power available).
(2) Failure
(a) A failure is defined as a fault that persists for a predetermined amount of time or
for a predetermined number of samples. The tolerance on all failure timing
criteria is ± 0.5 second.
(3) Intermittent Failure
(a) An intermittent failure is defined as a fault that had been declared a failure,
recovered to its normal valid state, and then is declared to have failed again. A
failure occurrence counter is maintained for each entry in the LRU and system
failure logs to identify intermittent failures.
(4) Fault
(a) A fault is defined as the result of a measurement or comparison that does not
satisfy the test or monitoring result requirements. The test or monitoring result
requirements can require a time element.
(5) Reversion
(a) Reversion is defined as the system response to a failure condition that results in
continued system operation in the presence of the failure, and can result in
degraded system capability.
(6) MCS LRU
(a) The following are defined as the MCS LRUs (i.e., those manufactured by
Honeywell/Racal):
• SDU
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• HPA.
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C. Failure Detection and Reporting Levels
(1) Failures are detected in the MCS system by a wide variety of tests. The immediate
result of failure detection is usually diagnosis of the failure to a specific component or
functional circuit group, on a specific SRU, in a specific LRU. However, some
detected failures may only be able to be diagnosed to a suspect SRU, or only to a
suspect LRU, or only to a pair or group of LRUs and the physical or logical
interface(s) between them. Three enumerated levels of failure diagnosis are defined
in Table 6-1.
Table 6-1.
Level
Levels of Failure
Description
Level I
Diagnosis to the LRU level or its equivalent (e.g., a specific inactive bus, error, or
warning)
Level II
Diagnosis to the SRU (module or circuit card) level
Level III
Diagnosis to the component or functional circuit group level or equivalent (e.g., a
very specific error condition)
(2) All MCS LRUs implement Level I and, where possible, Level II failure detection. Level
I diagnosis primarily supports line maintenance. Front panel displays and automatic
reports to central fault/maintenance systems are only performed to Level I resolution
because they are primarily used to support line maintenance, which is typically limited
to LRU replacement. Level II and Level III diagnosis primarily support shop and
factory maintenance. Level II and Level III failure detection information is stored in
the LRU and system failure logs, and can be displayed on the commissioning and
maintenance terminal (CMT) pages.
D. LRU Coverage
(1) The LRU coverage is defined as the sum of all component failure rates covered by
the BITE circuitry within an LRU, divided by the total of the component failure rates
within that LRU. This coverage is greater than or equal to 0.95 as defined. The LRU
probability of false detection is defined as the sum of all component failure rates of
the BITE circuitry within an LRU divided by the total of the component failure rates
within that LRU. This coverage is greater than 0.01 as defined. The LRU coverage
includes the following:
• All SDU to avionic interfaces, where possible
• All MCS inter-LRU interfaces
• All power supply voltages
• All battery voltages
• All microprocessors/microcontrollers
• All memory devices (RAM, ROM, etc).
UP86308
(2) All discrete drivers between the SDU and the avionics LRUs have over current
protection and open-circuit detection.
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E.
Monitoring and Testing Functions
(1) General
(a) The declaration of an inactive input bus takes precedence over declaration of
one or more data word failures against the LRU driving that bus (i.e., if the bus is
inactive, additional logging and reporting of low-rate failures of individual data
words on that bus are precluded). The failure and recovery criteria is set to make
sure individual data word failures are not declared when the bus is inactive. This
is typically done by setting inactive bus failure criteria (e.g., three seconds) to be
faster than word update rate failure criteria (e.g., five seconds), and inactive bus
recovery criteria (e.g., two seconds) to be longer than word update rate recovery
criteria (e.g., one second).
(b) Unless an LRU providing ARINC 429 data declares itself to have failed, a fault is
declared against that LRU when the ARINC 429 data is faulty. This is determined
by checking (as appropriate for each word) for data inconsistencies, data
out-of-range, uses of undefined or reserved values, and occurrences of the
failure warning state in the sign/status matrix (SSM) field.
(c) Two basic types of failure detection testing performed are: functional tests and
continuous monitoring (CM). The purpose of functional testing in the form of
power-on self test and person-activated self test is to exercise the equipment in a
manner as closely as possible to its normal operation. Failures detected during
functional testing are declared to be current failures until a subsequent functional
test shows the failure condition has recovered.
(d) The purpose of continuous monitoring is to test the equipment in a nondisruptive
manner while it is performing its normal operations. Such testing usually includes
monitoring the power supply voltages, temperature sensors, bias currents, input
bus activity, buffer overflow, input data failures, etc. This testing can also include
abnormal failures that cannot be tested as part of the functional testing, such as
protocol failures, processor instruction traps, data loader problems, etc.
(2) Power-On Self-Test
(a) General
UP86308
The power-on self-test (POST) is a series of functional tests for individual
LRUs; each MCS LRU performs its own internal POST upon a cold start. A
cold start is defined as the response of an LRU where no retention of any
previously stored information in any volatile memory is assumed. The power
supply provides signals to help an orderly power-down and power-up
process for the LRU during power interrupts of any length. Primary power
interrupts of less than 5 milliseconds duration have no effect on system
operation. For primary power interrupts longer than 5 milliseconds and up to
200 milliseconds duration, the LRU maintains normal operation, except the
RF transmit and receive processes do not need to be supported in any LRU
during this interval. For primary power interrupts greater than 200
milliseconds duration that causes normal operation to cease, the LRU
performs a cold start following restoration of primary power.
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The POST sequence of tests does not terminate when an out-of-tolerance
condition is encountered. Instead, the sequence continues to complete as
many tests as possible to record all available information regarding existing
failures. An individual LRU that successfully passes POST is declared to be
fully functional. POST must take into account failures detected by
continuous monitoring (i.e., if POST passes, but testing unique to
continuous monitoring has detected and logged a current failure, then the
POST result is logged as a failure).
After executing its own POST, the SDU commands a system-wide functional
test of the HPA(s) and ACU/BSU(s) (including the HGAs, HGA diplexer/LNA,
and HPR) as applicable for the installed equipment in accordance with the
system configuration pins (see MECHANICAL INSTALLATION). The SDU
then processes the results of the functional tests from these LRUs. The SDU
commands the functional test as follows through:
• SSM field of the HPA command word(s) for the HPA
• SSM field(s) for the ACU/BSU control word(s) for the ACU/BSU(s).
The BITE status from the LGA diplexer/LNA is continuously sent to the SDU,
with no functional test command necessary or possible. Test results from the
HGA(s), HGA diplexer/LNA, and HPR are reported by the ACU/BSU(s).
The SDU allows up to 30 ± 1 seconds for other system LRUs to report their
POST results following initiation of a system-wide functional test. If an LRU
fails to report its functional test results within this time period, but otherwise
meets the ARINC 429 bus communication rate requirements, the SDU
considers that LRU to have failed. If no ARINC 429 bus communication is
received on a particular bus, the SDU considers that bus to be inactive.
(b) Test Initiation
UP86308
The correct operation of much of the internal circuitry of the SDU depends
on clocks derived from the high-stability frequency reference generated by
the oven-controlled crystal oscillator (OCXO). Therefore, it is inappropriate to
perform BITE tests until this clock frequency has achieved gross stability. If
the SDU is powered on after having stabilized at a cold external temperature
(e.g., --55° C), it can take several tens of seconds for the frequency drift rate
to be low enough before the phase locked oscillators (PLO) that derive the
dependent clocks can lock onto the OCXO frequency reference.
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The SDU defers testing of sensitive equipment until a positive indication of
settling is detected, or sufficient time passes so the lack of settling itself can
be classified as a failure. Deferral of these sections of POST also result in
normal operation being deferred, including access to the user interfaces
(SCDU, CFDS, and CMT) and all automatic calibration processing.
Consequently, the SDU suspends POST until the SDU detects the first of
the following conditions:
• OCXO heater monitor indicates it has achieved operating temperature
• Power supply unit (PSU) temperature sensor indicates a reading above
25 °C
• Channel filter module transmit and receive PLO lock detectors both
indicate that lock has been achieved
• More than 4 minutes have elapsed since primary power was applied.
(c) LRU Front Panel LED and Alphanumeric Display Tests
A test of the HPA front panel LEDs is performed as a part of each POST. At
a minimum, this is made up of flashing the LEDs on and off. The LED
flashing continues until POST is completed or for 3 ± 0.5 seconds. During
the test, the SDU tests its alphanumeric display by incorporating one or
more occurrences of the word TESTING into its display sequence to make
sure all display elements are tested.
(d) RF Loop Back Tests
As part of the system-wide POST, the SDU implements a RF loop back test.
The RF loop back occurs in the radio frequency module (RFM) installed in
the SDU.
The SDU delays initiating the RF loop back test until it receives an indication
the RF loop back has been activated. If the SDU fails to receive a valid
indication within 30 seconds following the RF loop back request, then the
SDU completes its POST without executing the RF loop back test. The SDU
cancels the RF loop back request when the loop back test is completed, or if
the 30 second timer expires while waiting for verification of an active RF loop
back.
(3) Person-Activated Self-Test
(a) The person-activated self-test (PAST) performs the same functions as POST.
PAST is initiated in the HPA by pushing the PUSH-TO-TEST (PTT) switch on the
respective LRU front panel. PAST can also be initiated any time through:
• Respective CMT interface to the LRU
• SSM field of the HPA command word sent to the HPA from the SDU.
UP86308
(b) A stuck switch on the CMT or LRU front panel does not cause PAST to remain
active. Any switch activity is ignored while PAST (or POST) is executing.
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(c) The HPA inhibits PAST while the aircraft is airborne, except when PAST is
initiated through the CMT that is permitted at any time. The HPA cannot properly
function if it is not receiving valid command words from the SDU containing the
air/ground status and command information. Under these conditions, the HPA is
not usable by the SDU. PAST is only permitted while the aircraft is on the
ground, or when the airborne/on-ground status is unknown. In lieu of the
airborne/on-ground status information from the SDU, the HPA permits PAST as
though the aircraft is on the ground.
(d) A system-wide PAST is initiated in the SDU when commanded by:
• Entry through the SATCOM control and display unit (SCDU)
• Entry through the central maintenance computer (CMC)
• Entry through the central fault display system (CFDS)
• Command from the CMT
• Activating the PTT switch (SDU TEST) on the front panel.
(e) A stuck switch on the SDU front panel does not cause PAST to remain active.
Any switch activity is ignored while PAST (or POST) is executing.
(4) Continuous Monitoring
(a) Continuous monitoring (CM) of the BITE circuitry does not interfere with the
normal operation of the system. Instead any failure condition is recorded and
reported. Continuous monitoring operates as a background task at all times,
even during functional testing. Functional test failure codes that are identical to
the continuous monitoring codes (except for the MSB of the level 3 code)
indicate cases where the functional test differs in some way from the companion
CM test. Those CM failures detected during functional testing (e.g., maintenance
and status word failures) are logged as CM failures, not functional failures.
F.
Failure Recording
(1) The SDU records CFDS internal failures at all times. The SDU only records CFDS
external failures while receiving a valid All Call DC1 Command if a Douglas or Airbus
CFDS is installed. Internal failures are defined as those internal to the SATCOM
subsystem. External failures are defined as those external to the SATCOM
subsystem. If a Boeing CMC (or no CFDS) is installed or if valid DC commands are
not available, then the air/ground status is used to generate pseudo DC states of
DC0 (aircraft on-ground) and DC1 (aircraft airborne).
UP86308
(2) The HPA records internal failures at all times. The HPA only records external failures
while the aircraft is airborne, based on the status of the weight-on-wheels discrete
(on-ground vs. airborne). Internal failures are defined as those that have the same
Level I code as the LRU recording the failure (i.e., 01 for the SDU, 04 for the HGA
HPA, and 07 for the LGA HPA). External failures are defined as those failures not
having the same level 1 code as the LRU recording the failure.
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(3) The HPA stores their functional test and CM failure records in nonvolatile memory
designated as the LRU failure memory log. Each LRU failure memory log is capable
of being interrogated and cleared. The SDU contains a nonvolatile memory that
serves as a system failure memory log. Functional test results supplied by the
HPA(s), ACU/BSU(s), LGA diplexer/LNA, and the SDU itself are recorded in this
system failure memory log. The system failure memory log is capable of being
interrogated and cleared for each LRU individually. Each LRU failure memory log and
the system failure memory log is capable of recording at least 1000 failures.
(4) The HPA and other system LRUs supply failure information to the SDU for storage in
the system failure memory log. In the absence of any detected failures during a flight
leg, the SDU records the flight leg counter, flight number, ICAO address, date, and
Greenwich Mean Time (GMT) at the flight leg transition. The SDU also records the
aircraft identification for display on the SCDU and CFDS maintenance pages.
(5) Class -- The SDU declares and stores the classification (Airbus/Douglas CFDS) of
failure (one, two, three) for each entry in this field.
• Class 1 failures are indicated in flight to the crew by the CFDS because they have
operational consequences for the current or next flight(s).
• Class 2 failures are not automatically indicated in flight to the crew by the CFDS
because they have no operational consequences for the current or next flight(s),
but are indicated to the crew on the ground because they cannot be left
uncorrected until the next routine scheduled maintenance check.
• Class 3 failures are not indicated to the flight crew because they can be left
uncorrected until a routine scheduled maintenance check. An accumulation of
Class 3 failures can lead to a Class 2 or Class 1 failure.
• Aircraft Identification -- The aircraft identification (i.e., the tail number) is made up
of nine alphanumeric characters. The SDU obtains the aircraft identification from
the CMC or CFDS through ARINC labels 301, 302, and 303 (if available).
G. Failure Reporting
(1) General
(a) Active failures include those internal and external failures deemed to be currently
failing while the aircraft is on the ground or airborne. Unlike failure recording that
excludes recording external failures while on the ground, failure reporting has its
own set of criteria as specified in the following paragraphs.
(2) HPA Failure Reporting
(a) General
The HPA reports its functional test/CM failure status by lighting its front panel
LEDs, and through communication to the SDU.
(b) HPA Front Panel Indicators and Controls
UP86308
The HPA indicators and controls are given in Table 6-2.
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Table 6-2.
HPA Indicators/Controls
Indicator/Control
Description
PASS LED
Shows green after a test, if no failures are detected in the HPA
FAIL LED
Shows red after a test, if failures are detected in the HPA
PUSH--TO--TEST (PTT)
Push this button to start a test of the HPA
(c) HPA Front Panel LEDs
Functional testing effectively controls the on/off state of the front panel LEDs
during the period beginning with initiation of the functional testing
(POST/PAST), through execution of the functional test sequences (including
LED testing), and up to and including the indication of the test results on the
LEDs. Continuous monitoring exclusively controls the LEDs at all other
times.
The green LED (PASS) lights for 30 ± 5 seconds at the conclusion of the
functional test sequences if both of the following are true:
• The HPA determines there are no currently active CM failures having its
own Level I code (i.e., 04 or 07, as applicable)
• No functional test failures have been detected with its own Level I code.
There must be no known failures in order to light the green LED as the
functional test indication.
The red LED (FAIL) lights continuously during the functional test indication
phase and through the transition to the CM indication phase, if the HPA
detects at least one currently active CM failure with its own Level I code. If
the HPA detects only functional test failures (i.e., no CM failures are
currently active), the red LED lights for 30 ± 5 seconds and is then turned
off.
The red LED also lights as long as the failure persists, if the HPA detects
any CM failure that has its own Level I code while continuous monitoring is
controlling the LEDs. Otherwise, both LEDs are turned off. Continuous
monitoring itself never causes the green LED to light. The presence or
absence of functional test failures does not affect the CM indication.
(d) HPA-SDU Communication
UP86308
The HPA communicates its functional testing/CM failure status to the SDU
through the HPA maintenance and status words. The HPA only indicates a
FW SSM state in its maintenance and status words, and active discrete
failure bits in its maintenance word. Since no failures unique to functional
testing activate the SSM FW state or the discrete failure bits in the
maintenance word, no functional test failures need to be latched until the
next functional testing sequence.
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For certain failures detected during continuous monitoring, the appropriate
discrete failure bits and the SSM FW state are set within the maintenance
and status words as long as the failure persists.
(3) SDU Failure Reporting
(a) General
The SDU reports its functional testing/CM failure status and all other system
LRUs by:
• Activating its alphanumeric display
• Communicating to the SCDU, CMC, CFDS, and CMT interfaces.
The alphanumeric display indicates all applicable failure conditions with no
regard to:
• Any type of internal/external failure differentiation
• Any CFDS failure class distinctions
• Which LRU detected a failure (either the SDU itself or one of the reporting
LRUs in the SATCOM subsystem).
The SDU delays reporting the results of the functional test sequence for a
period of 5 seconds. This gives continuous monitoring the opportunity to
perform its unique tests during the delay period, and include any current CM
failures in the test report. The SDU takes a snapshot at the end of the
functional test delay period to include all currently active CM failures in
addition to all failures detected during functional testing. The functional test
delay period applies to the SDU alphanumeric display, the SCDU
maintenance pages, the CFDS pages, and the CAIMS and CMC fault
summary words, but not to the CMT.
(b) SDU Front Panel Indicators and Controls
The SDU indicators and controls are given in Table 6-3.
Table 6-3.
UP86308
Indicator/Control
SDU Indicators/Controls
Description
SDU TEST
Push this button to initiate a system--wide SATCOM test
SYSTEM STATUS DISPLAY
Shows data defining the SATCOM system configuration and the
identification of all SATCOM components that are not operating as required
MANUAL SCROLL
Push this button to scroll through the messages on the system status
display
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(c) Front Panel Alphanumeric Display and MANUAL SCROLL Button
General
The alphanumeric display makes it easy for the maintenance personnel
to identify which system LRU has failed. The alphanumeric display is
blank unless specifically activated for temporary display of failure
messages and other status information. The alphanumeric display is
also kept blank under conditions of extreme temperatures. The display
is not intended to be started when its temperature is less than --5 °C, or
greater than +30 °C. The alphanumeric display is started during the LED
test portion of the functional test sequence. After the functional test
delay period, and any time during continuous monitoring, the
alphanumeric display can be started by pushing the MANUAL SCROLL
button.
The operator can scroll the alphanumeric display through the entire
applicable message sequence by repeatedly pushing the MANUAL
SCROLL button within 30 5 seconds after the display is started. One
left-justified 20-character (or less) message is displayed each time the
MANUAL SCROLL button is pushed. When the end of the display
sequence is reached (i.e., END OF LIST), the next actuation of the
MANUAL SCROLL button returns the alphanumeric display to the top of
the display sequence, enabling the operator to scroll through the
sequence again. Message scrolling is performed according to the
following sequence:
• One of four possible system/SDU pass/fail messages
• All applicable Level I failure messages
• LRU part number messages (up to four lines)
• ORT identification message
• END OF LIST message.
SYSTEM/SDU PASS/FAIL Message
UP86308
If the MANUAL SCROLL button is inactivate for 30 ± 5 seconds at any
point during the display sequence, the alphanumeric display is blanked
and any display sequence in progress is aborted. At the same time, one
or both of the front panel LEDs (as appropriate) are turned off if they
were exclusively indicating functional test failures with no current CM
failures.
This one-line message, which summarizes the overall functional test or
CM status, takes on one of four possible states:
• SDU PASS
SYS PASS
• SDU PASS
SYS FAIL
• SDU FAIL
SYS PASS
• SDU FAIL
SYS FAIL.
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Level I Failure Messages
This section lists all the applicable Level I failure messages that can be
displayed on the alphanumeric display, along with the appropriate LRU
or control bus input. These messages are listed in failure code order in
Table 6-4. For the functional test display, the message list includes all
the active failures in the snapshot and the list is static.
For continuous monitoring, the message list includes all currently active
CM failures. The presence or absence of functional test failures does
not affect the CM message list. The failure message list for the CM
display is potentially dynamic.
During continuous monitoring, if a new CM failure becomes active
during the scroll sequence, the respective message appears at its
proper location in the sequence according to its Level I code. This
occurs either during the current scroll sequence if that Level I code has
not yet been reached, or during the next scroll sequence if the failure is
still active. If a CM failure recovers during a scroll sequence, its
message does not appear in any subsequent scroll sequence, even if it
had appeared earlier. If a CM failure recovers while its particular
message is currently being displayed, the message continues to be
displayed until the MANUAL SCROLL button is activated or until the
time-out period expires.
Table 6-4.
Level 1
Code
Level 1 Failure Messages
Failure Message
Description
UP86308
AES LRU Failures:
00
(not applicable)
Unknown Level I failure
01
SDU
SDU failed
02
OTHER SDU
Other SDU (of a dual system) failed
04
HPA--HI GAIN
High Gain Antenna HPA failed
07
HPA--LO GAIN
Low Gain Antenna HPA failed
0A
HI POWER RELAY
HPR (antenna system) failed
0D
DLNA--(TOP/L)
Top/Port Diplexer/Low Noise Amplifier failed
0F
DLNA--R
Starboard Diplexer/Low Noise Amplifier failed
10
DLNA--LO GAIN
LGA Diplexer/Low Noise Amplifier failed
13
BSU--(TOP/L)
Top/Port BSU or ACU failed
15
BSU--R
Starboard BSU failed
1A
HI GAIN ANT--(TOP/L)
Top/Port HGA failed
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Table 6-4.
Level 1
Code
Level 1 Failure Messages (cont)
Failure Message
Description
1C
HI GAIN ANTENNA--R
Starboard HGA failed
1F
LO GAIN ANTENNA
LGA failed
21
SCDU1
No. 1 SCDU failed
22
SCDU2
No. 2 SCDU failed
23
SCDU3
No. 3 SCDU failed
Non-AES LRU Failures:
33
(ACARS MU/CMU)1
No. 1 AFIS/ACARS unit failed
34
(ACARS MU/CMU)2
No. 2 AFIS/ACARS unit failed
35
IRS1
No. 1 IRS failed
36
IRS2
No. 2 IRS failed
37
IRS3
No. 3 IRS failed
38
IRS4
No. 4 IRS failed
39
(CFDIU/CMC)
CFDS/CMC failed
3D
FMC1
No. 1 FMC failed
3E
FMC2
No. 2 FMC failed
40
ARINC 429 ICAO ADDR
429 ICAO address source failed
41
(not applicable)
Discrete cockpit indicators failed
42
CTU
Cabin file server/cabin packet data function failed
43
(CFS/CPDF)
Cabin telecommunications unit failed
UP86308
Inactive BITE Bus Input to SDU from other LRU:
52
(CFS/CPDF)/SDU
Cabin file server/cabin packet data function bus
53
(ACARS MU/CMU)1/SDU
No. 1 AFIS/ACARS unit bus
54
CTU/SDU
CEPT--E1 bus from the CCS
55
SCDU1/SDU
No. 1 SCDU bus
56
SCDU2/SDU
No. 2 SCDU bus
57
(ACARS MU/CMU)2/SDU
No. 2 AFIS/ACARS unit bus
59
(CFDIU/CMC)/SDU
CFDS bus
5A
IRS--PRI/SDU
Primary IRS bus
5B
IRS--SEC/SDU
Secondary IRS bus
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Table 6-4.
Level 1
Code
Level 1 Failure Messages (cont)
Failure Message
Description
5C
HPA--HI GAIN/SDU
High Gain Antenna HPA bus
5F
HPA--LO GAIN/SDU
Low Gain Antenna HPA bus
62
BSU--(TOP/L)/SDU
Top/port BSU bus
64
BSU--R/SDU
Starboard BSU bus
65
(not applicable)
Radio Management Panel bus
66
SCDU3/SDU
No. 3 SCDU bus
67
TP1AB/SDU MP9EF
Data bus from RFU to SDU (BITE signaling)
68
TP1EF/SDU MP9JK
CEPT--E1 from RFU to CTU through SDU
6A
TP1JK/SDU MP10CD
ST--Bus data from RFU to SDU (overflow digital audio)
6C
TP3CD/SDU MP10GH
ST--Bus C2 clock from RFU to SDU (overflow digital audio)
6D
TP3EF/SDU MP10JK
ST--Bus F0 frame from RFU to SDU (overflow digital audio)
71
OTHER SDU/THIS SDU
Bus from other SDU in a dual system
73
FMC1/SDU
No. 1 FMC bus
74
FMC2/SDU
No. 2 FMC bus
Inactive Bus Inputs to other LRU:
80
SDU MP9GH/RFU TP1CD
Data bus to RFU from SDU (control)
82
CTU/SDU MP10AB
CEPT--E1 bus from CTU to RFU through SDU
88
SDU MP10EF TP3A/B
ST--Bus data from SDU to RFU (overflow digital audio)
90
SDU M--CTRL/HPA--HI
Multicontrol bus to HGA HPA from SDU
96
SDU M--CTRL/HPA--LO
Multicontrol bus to LGA HPA from SDU
98
SDU M--CTRL/BSU--(T/L)
Multicontrol bus to top/port BSU from SDU
9A
BSU--R XTALK/BSU--L
Crosstalk bus to port BSU from starboard BSU
9C
SDU M--CTRL/BSU--R
Multicontrol bus to starboard BSU from SDU
9D
BSU--L XTALK/BSU--R
Crosstalk bus to starboard BSU from port BSU
UP86308
Miscellaneous Failures:
C0
WRG:STRAPS/SDU
System configuration pins error
C1
WOW1/WOW2/SDU
Weight on wheels discrete inputs disagree
C2
SDU DUAL SEL/DISABLE
Dual system discrete inputs disagree
C3
WRG:ICAO ADDR/SDU
ICAO address straps error
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UP86308
Table 6-4.
Level 1 Failure Messages (cont)
Level 1
Code
Failure Message
C4
TX PATH VSWR--HI GAIN
Excessive VSWR load at HGA HPA output
C5
WRG:STRAPS/SDU ORT
Configuration pins and ORT settings disagree
C6
TX PATH VSWR--LO GAIN Excessive VSWR load at LGA HPA output
C7
HPA--HI GAIN
OVERTEMP
Over temperature in HGA HPA
C8
BAD GROUND STATION
Invalid GES frequency command
C9
HPA--LO GAIN
OVERTEMP
Over temperature in LGA HPA
CA
SDU/DLNA--LO GAIN
LGA LNA control driver SDU
CB
WRG:SDI/HPA--HI GAIN
(see NOTE)
HGA HPA identification strapped incorrectly
CC
WRG:SDI/HPA--LO GAIN
(see NOTE)
LGA HPA identification strapped incorrectly
CD
SDU (POC/TOTC)
SDU power-on counter or total-on-time counter has been reset
CE
RFU (POC/TOTC)
RFU power-on counter or total-on-time counter has been reset
CF
HPA--HI (POC/TOTC)
HGA HPA power-on counter or total-on-time counter has been
reset
D0
HPA--LO (POC/TOTC)
LGA HPA power-on counter or total-on-time counter has been
reset
D1
WRG:SDI/HPA--HI GAIN
(see NOTE)
HGA HPA identification strapped incorrectly
D2
WRG:SDI/HPA--LO GAIN
(see NOTE)
LGA HPA identification strapped incorrectly
D3
WRG:SDI/BSU--(T/L)
Top/Port BSU identification strapped incorrectly
D4
WRG:SDI/BSU--R
Starboard BSU identification strapped incorrectly
D5
HPA--HI GAIN COAX
HGA HPA input coax cable
D6
HPA--LO GAIN COAX
LGA HPA input coax cable
D7
SDU COAX
RFU input coax cable
D8
DLNA/(SDU)--(T/L)
Top/Port HGA LNA coax cable output to RFU or SDU
D9
DLNA/(SDU)--R
Starboard HGA LNA coax cable output to RFU or SDU
DA
DLNA/(SDU)--LO GN
LGA LNA coax cable output to RFU or SDU
DB
LO GAIN SUBSYSTEM
LGA log--on functional test failure or could not initiate test
Description
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Table 6-4.
Level 1
Code
Failure Message
Level 1 Failure Messages (cont)
Description
DC
NO ACTIVE MU/CMU
At least one (C)MU is communicating, but none have declared
themselves active
DD
SDU OWNER
REQS--SECD
Error in the secured ORT partition
DE
SDU OWNER
REQS--USER
Error in the user ORT partition
DF
HI GAIN SUBSYSTEM
Slave HGA log--on functional test failure or could not initiate test
E0
COAX/SDU
SDU input coax cable from RFU
FE
PWR SUPPLY
INTERRUPT
SDU had an in-flight primary power interrupt
Undefined:
Others
LEVEL 1 FAULT XX
XX is the Level 1 failure code (undefined)
NOTE: The front panel display messages associated with failure codes CBx and CCx (WRG:SDI/HPA HI--GAIN and
WRG:SDI/HPA LO--GAIN, respectively) are identical to the messages raised for failure codes D1x and D2x,
respectively. This use of a single front panel display message for multiple failure codes (where the CB/CCx
codes reflect detection by the HGA/LGA HPA of an invalid HPA SDI strap condition, while the D1/D2x codes are
generated by the SDU in response to a report from the HGA/LGA HPA of having detected an unexpected SDI
code) is deliberate, and results from alignment of the front panel display messages with their CFDS/CMC
counterparts. Because of this approach, it is possible (in this specific case) for an operator to receive two
consecutive front panel display messages that are the same.
LRU Identification (Part Numbers) Electronically
UP86308
Following the display of all Level I failure messages, a list of the
available LRU end-item part numbers is displayed. This list only includes
part numbers for those LRUs present in the given installation as defined
by the system configuration pins (see MECHANICAL INSTALLATION).
For an installed LRU whose end-item part number is not available,
dashes are displayed in place of the part number (e.g., HPL _ _ _ _ _ _
_ _ _ _ _). The list of part numbers are displayed in the order given in
Table 6-5.
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Table 6-5.
List of Part Numbers
LRU
Part No.
SDU
SDbbbbbbb--hhsss--nn
HGA HPA
HHbbbbbbb--hhsss--nn
IGA HPA
IHbbbbbbb--hhsss--nn
LGA HPA
LHbbbbbbb--hhsss--nn
NOTES:
1.
bbbbbbb represents the seven-digit LRU end-item base part number.
2.
hh represents the two-digit LRU end-item hardware configuration number.
3.
sss represents the three-digit LRU end-item software configuration number.
4.
nn represents the two-character LRU end-item software modification level (possibly including space, dash
characters, and alpha characters).
For Honeywell/Racal LRUs, the three-digit LRU hardware configuration
number must be entered manually through the CMT interface for valid
data to be available for display. This data is stored during LRU end-item
testing. All other numbers reside within the LRU software. All numbers
are communicated to the SDU by Honeywell/Racal HPA(s) through the
part number block transfer. For non-Honeywell/Racal interfacing HPAs,
no such data is available to the SDU, therefore, dashes are displayed
for the HPA end-item part number.
Part Number Block Format
The information contained in the part number block is required for
display on the CMC/CFDS MCDU, SCDU, CMT, and the SDU
alphanumeric display. The information must be in the specified format
(i.e., character restrictions or only digits and field length) for proper
display. The part number block transfer is made up of:
• Seven-digit end-item base part number
• Two-digit end-item hardware configuration number (the first part of
the end-item dash number, which also reflects the boot PROM
software version).
• Three-digit software configuration number (the latter part of the
end-item dash number, which only reflects the version of uploaded
software)
• Two-letter (uppercase) hardware modification level
• Two-letter (uppercase) software modification level
• Eight-digit LRU serial number
• Four-hexadecimal character LRU program store CRC code
UP86308
• Two-hexadecimal character hardware/software compatibility strap.
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ORT Identification
Following the display of the LRU end-item part numbers, the user ORT
identification is displayed as specified:
• ORT ID--XXXXXXXXXXXXX (first line)
• XXXXXXXXXXX--MODIFIED (second line, after another activation of
the MANUAL SCROLL button).
Where XXXXXXXXXXXXXXXXXXXXXXXX represents the 24-character
description contained in the user ORT description field. The user ORT
description field is used to annotate a particular set of ORT items to
identify one from another (e.g., NORTH PACIFIC ROUTE, SOUTH
ATLANTIC ROUTE, 747--400 ASIAN ROUTE, 777 ASIAN ROUTE).
Alternatively, this item could contain a software identification (e.g., a
software part number for the user ORT as a released entity).
The MODIFIED flag is only displayed if the state of the user ORT
modified flag indicates any item in the user ORT has been modified
since the user ORT was created. When any user ORT item is modified
by the SDU software, either directly or indirectly, the user ORT modified
flag is set to MODIFIED. If the state of the user ORT modified flag is
unmodified, the MODIFIED flag is not displayed. The state of the user
ORT modified flag is never set to unmodified by the SDU software.
The next two pushes of the MANUAL SCROLL button present the same
information for the Secured ORT partition.
End Of List Message
The END OF LIST message is displayed at the end of the display list
after the ORT identification.
H. Miscellaneous BITE Requirements
(1) The typical retention period for the BITE memory is at least five years at 25 °C. The
worst case retention period is at least one year at 50 °C. If batteries are used to
supply backup power for the BITE memory, the typical battery lifetime should be at
least 10 years at 25 °C. The worst case lifetime is at least two years at 50 °C.
(2) Each system LRU has a total on-time clock (TOTC) to accumulate and record the
amount of time the LRU has been powered up. The TOTC has a 10 minute
resolution, and is capable of accumulating and recording a count of at least 200,000
hours.
UP86308
(3) The TOTC value is capable of being examined, and of being reset to 0:00 through
the CMT. Any manual TOTC reset, or any automatic TOTC reset (e.g., upon
detection of corruption of its value), results in an automatic entry of the event into the
LRU failure memory log and the SDU system failure memory log. The TOTC hours
are capable of being automatically entered into the LRUs maintenance activity log.
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I.
Maintenance Activity Log
(1) A maintenance activity log is stored in each system LRU. The maintenance activity
log is made up of the six most recent maintenance activity records (MAR). Each MAR
can be entered through the CMT. Information is stored in the MAR as shown in
Table 6-6 and in the order listed.
Table 6-6.
Field
MAR Information
Size
Range
Document Number
16 ASCII Characters
a--z, A--Z, 0--9
Date (yymmdd)
6 ASCII Numerics
yy 00--99
mm 01--12
dd 01--31
Location
32 ASCII Characters
a--z, A--Z, 0--9
Phone Number
18 ASCII Numerics
0--9
Total On-Time Clock (Hours)
6 ASCII Numerics
0--200,000
(2) The fields are defined as follows:
• Document number -- The document number has up to 16 alphanumeric
characters. The intent of this field is to supply maintenance activity traceability.
• Date field -- The date field is made up of six numeric characters in the format of
yymmdd, where yy represents the year, mm represents the month, and dd
represents the day. This field is entered automatically by the SDU as determined
by its internal real-time clock (RTC); it is entered manually for the HPA. The intent
of this field is to record the date the maintenance activity was performed.
• Location field -- The location field has up to 32 alphanumeric characters. The
intent of this field is to indicate the place where the LRU maintenance service was
performed.
• Phone number field -- The phone number field is made up of 18 numeric
characters. The intent of this field is to supply a phone number of who performed
the LRU maintenance. This phone number should include the combination of
country code, area code, and local phone number.
UP86308
• Total on-time clock field -- The TOTC field is made up of six numeric characters
representing hours. This field is entered automatically by the LRU as determined
by the internal TOTC.
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2. SATCOM Control and Display Unit
A. General
(1) The SATCOM Control and Display Unit (SCDU) menu formats obey the accepted
industry standards for multifunction (multipurpose) control and display units (MCDU).
The following paragraphs describe the SCDU display layout and terminology used to
describe the display, font size conventions, scratchpad usage, format, keyboard
usage, display symbols, and update rates.
B. SCDU Display Terminology and Basic Operation
(1) General
(a) The SCDU display is made up of 14 lines of 24 characters. The top line (line 1) is
referred to as the title line and the bottom line (line 14) is referred to as the
scratchpad. Lines 2 thru 13 are arranged into six pairs having a label line and
data line. The SDU communicates to the SCDU for all data to be displayed in
green. The color displayed on the MCDU depends on how the MCDU responds
to this communication.
(b) There are six line select (LS) keys on each side of the SCDU display designated
left (L) and right (R) and numbered 1 to 6 from top to bottom. The LS keys are
associated with a pair of display lines where the upper line of a pair is the label
line and the lower line is the data line. The LS key/line pair relations are given in
Table 6-7.
(c) The SCDU can display a large and small font size. Different character fonts are
not shown in the example SCDU page figures given in this section. The use of
large font is indicated by the presence of uppercase letters in the SCDU page
figures, while the use of small fonts are demonstrated by lowercase letters. In
general, page names displayed in the title line are in large font. For pages where
p/t is specified to be displayed in the title line, the p/t is in small font. Data
entered into the scratchpad is displayed in large font. Data in the label lines is
displayed in small font, while data in the data lines is displayed in large font.
Numerical character font sizes cannot be shown in the figures, but their font
sizes follow the same conventions.
Table 6-7.
LS Key/Line Pair Relations
UP86308
LS Keys
Display Lines
1L -- 1R
2 and 3
2L -- 2R
4 and 5
3L -- 3R
6 and 7
4L -- 4R
8 and 9
5L -- 5R
10 and 11
6L -- 6R
12 and 13
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(d) Labels on the left side of the SCDU display are displayed beginning in column 2
of the label line. Data on the left side is left-justified in the data line. Labels and
data on the right side of the SCDU display is right-justified. This is the case
unless specified otherwise.
(2) Scratchpad
(a) General
The scratchpad is used for data entry and displaying SDU generated
messages. Pushing an alphanumeric key on the keypad (0 through 9, A
through Z, +/-- [plus or minus], / [slash, space]) enters that character into the
scratchpad. The scratchpad is not used for fixed format display purposes.
The mechanism used for data entry is described below.
(b) Data Entry
When the user types the appropriate characters using the SCDU keypad,
the characters are echoed on the scratchpad. After data entry, the user must
push the appropriate LS key adjacent to the data field where the data is to
be displayed. The SDU then checks the data for format and acceptability
(out-of-range, entry not permitted into the field, etc). If the data is incorrect,
the SDU leaves the previous data in the field and displays the appropriate
error message in the scratchpad. If any LS key is pushed adjacent to a
blank or nonselectable field, the scratchpad message 1 (i.e., NOT
ALLOWED) is issued. If the entry was rejected because an incorrect LS key
was pushed, the entry is accepted if the correct LS key is subsequently
pushed.
(c) Scratchpad Message
If the SDU determines a data entry does not conform to format or
acceptability requirements after an entry is attempted, the SDU issues a
scratchpad message prompting the user for the correct data. The user can
clear a scratchpad message by using the clear (CLR) key, or by entering
data into the scratchpad over the message.
(d) CLR and DEL Keys
General
CLR Key
UP86308
The CLR and delete (DEL) keys are used to clear the scratchpad and
alter the data fields. Generally, for MCDUs that have only a CLR key
(e.g., Airbus and Douglas) the scratchpad is cleared and the data fields
are altered by using this key. For MCDUs that have both CLR and DEL
keys (e.g., Boeing), the scratchpad is cleared using the CLR key, while
the data fields are altered using the DEL key.
Pushing the CLR key clears the scratchpad message. When the
scratchpad contains user-entered characters, momentary actuation of
the CLR key clears the last entered character, while continual actuation
of the CLR key clears the entire contents of the scratchpad.
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When the scratchpad is empty, pushing the CLR key causes CLR to be
displayed in the scratchpad indented five spaces. If an LS key is pushed
and the field adjacent to the LS key is specified to be either erasable
(e.g., an unprotected number) or a default maintained value (e.g.,
protected number priorities), the field is cleared or reverts back to its
default value, as applicable.
For compatibility with the Boeing 777 AIMS/CDU, the SDU clears the
entire scratchpad when the CLR command is received with the repeat
bit set.
DEL Key
The DEL key (if available) can be used to clear or revert the data fields.
Pushing the DEL key causes no response when the scratchpad is not
empty, except for either an SDU issued error message or pilot-entered
characters.
When the scratchpad is empty, pushing the DEL key causes DELETE to
be displayed in the scratchpad.
NOTE: Pushing the DEL key again does not clear DELETE from the
scratchpad. Instead, pushing the CLR key when DELETE is
displayed in the scratchpad clears DELETE.
If an LS key is pushed and the field adjacent to the LS key is specified
to be either erasable (e.g., an unprotected number) or a default
maintained value (e.g., protected number priorities), the field is cleared
or reverts back to its default value, as applicable.
When the scratchpad contains CLR indented five spaces as the result of
the CLR key being pushed with an empty scratchpad and the DEL key
is subsequently pushed, the SDU replaces CLR with DELETE in the
scratchpad.
(e) NEXT PAGE and PREV PAGE Keys
General
NEXT PAGE Key
UP86308
Pushing the NEXT PAGE and PREV PAGE (if available) function keys
on the SCDU keypad causes the SDU to display the next page, or
previous page of the display sequence where appropriate (i.e., when p/t
is displayed in the title line).
Pushing this key causes the next page in the sequence to be displayed.
If the last page in a multiple page sequence is displayed and the NEXT
PAGE key is pushed, the first page is displayed. The SDU ignores this
key if the key is pushed when p/t is not displayed, or if a p/t display is
the value 1/1.
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PREV PAGE Key
(f)
Pushing this key causes the previous page in the sequence to be
displayed. If the first page in a multiple page sequence is displayed and
the PREV PAGE key is pushed, the last page is displayed. The SDU
ignores this key if the key is pushed when p/t is not displayed, or if a p/t
display is the value 1/1.
Special Symbols
When displayed, special symbols are defined as given in Table 6-8.
Table 6-8.
Symbol
Special Symbols
Description
* (Asterik)
Pushing the LS key adjacent to this symbol (when it appears) causes an
action of some kind to occur (e.g., making a phone call, sorting a phone
list, or initiating log-off).
[ ] (Brackets)
Empty brackets prompt the user for data entry into the field. However, data
entry is not mandatory. Brackets surrounding data indicate the data is
unprotected and can be modified or deleted. Not all fields modifiable are
surrounded by brackets. When brackets are used to enclose existing data,
as opposed to prompting entry of data into an empty field, they are
intended as an indication the data is unprotected (i.e., an unprotected
phone number). Conversely, protected phone numbers do not have
brackets, indicating the phone number cannot be modified or deleted.
< , > (Carets)
A caret adjacent to an LS key indicates if the key is pushed the display
changes to a new page. The new page is either the one indicated next to
the caret or, in case of RETURN>, the higher level page.
Indicates the data in the field is currently selected (e.g., the selected GES
or antenna).
(g) Updates
UP86308
Dynamically generated display fields, whose contents have changed, are
updated by the SDU both periodically (at a rate of at least 1 Hz), and upon
completion of an LS key action that could have caused the display or the
display field to change. With multiple SCDU configurations, the SDU only
maintains one version of each page for display. The SDU responds to LS
key actuations from all SCDUs in a serial fashion and updates the display
page(s). Each SCDU scratchpad and the channel selection fields are
independent from all others, allowing each user to perform independent
actions.
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C. SCDU Page Hierarchy
(1) The SCDU page hierarchy is shown in Figure 6-2. The SATCOM MAIN MENU page
is accessed by pushing the LS key adjacent to prompt is displayed on the right adjacent to the 6R key,
as opposed to the left.
UP86308
• The SDU issues scratchpad message 1 (i.e., NOT ALLOWED) if any LS
key is pushed adjacent to a blank or display-only field.
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UP86308
Figure 6-4.
SATCOM SUBMENU Page
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Figure 6-5.
SATCOM MAINTENANCE Page
Access to SATCOM maintenance displays are as follows:
• Push LS key 1L to show the Last Leg Report page (see Figure 6-10)
• Push LS key 2L to show the Previous Leg Report page (see Figure 6-11)
• Push LS key 3Lto show the LRU Identification page (see Figure 6-12)
• Push LS key 5L to show the Trouble Shooting Data page (see
Figure 6-13)
• Push LS key 6L to show the Configuration Data page (see Figure 6-8)
• Push LS key1R to show the Last Leg Class 3 Faults page (see
Figure 6-14)
• Push LS key 2R to show the Test page (see Figure 6-6)
• Push LS key 3R to show the Data Loader Menu page (see Figure 6-9)
• Push LS key 5R to show the Ground Report page (see Figure 6-15).
(b) TEST page
UP86308
For software packages prior to D2.0, if a system-wide functional test (i.e.,
PAST) is initiated from the SCDU interface (i.e., by pushing the 2R key on
the SATCOM MAINTENANCE page), the first access of the SATCOM
subsystem from an SCDU MAIN MENU page after the POST/PAST Results
Delay period causes the TEST page to be shown with the status of the
current failures. However, the TEST page shows the TEST IN PROGRESS
60S message if this first access occurs during the POST/PAST Results
Delay period. If the SATCOM subsystem is not accessed within 5 minutes of
the completion of an SCDU-initiated PAST, the page hierarchy is reset to its
original structure as shown in Figure 6-2.
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When the 2R key is pushed on the SATCOM MAINTENANCE (i.e., SAT--N)
page, the SDU initiates a PAST and the page display temporarily goes to the
TEST page where TEST IN PROGRESS 60S is displayed. However, the
SCDU eventually times out the SATCOM subsystem and takes back control
of the display. This is due to the fact that for SCDU-accessed maintenance
pages, the SDU interfaces directly with the SCDU (as opposed to going
through the CFDIU) and is unable to maintain proper bus activity (which the
CFDIU normally does) during initial execution of the PAST.
To display the test results, the user must reselect the SATCOM system by
pushing the LS key adjacent to the beginning in column 1 when the test is active. If the log--on
state changes from Standby to any other state while the test is active,
the test is terminated. The commands on lines 4 and 5 are shown only if
the configuration straps indicate this channel is wired for headset use.
Pushing LS key 2L when the ENABLE asterisk prompt is shown causes
the voice channel selected to be activated into an analog loopback test
state. Pushing LS key 2L when the DISABLE prompt is shown causes
the voice loopback test state to be terminated.
Line 6
Line 7
This line displays *ENABLE beginning in column 1 when the test is not
active. The asterisk prompt is shown and the test allowed only if the
log--on state is Standby. This line displays *DISABLE
beginning in column 1 when the test is active. If the log--on state
changes from Standby to any other state while the test is active, the test
is terminated. The commands on lines 6 and 7 are shown only if the
configuration straps indicate this channel is wired for headset use.
Pushing LS key 3L when the ENABLE asterisk prompt is shown causes
the cockpit voice call light to be activated for a steady indication
(regardless of the state of configuration pin TP13C). Pushing LS key 3L
when the DISABLE prompt is displayed causes the cockpit voice call
light test to be terminated.
LIne 8
This line displays MP2EFGH VOICE LOOPBACK beginning in column
2. Pushing LS key 4L configures the SATCOM system to perform an
audio loopback test of flight deck channel 2.
Line 9
UP86308
This line displays MP8E CALL LIGHT TEST beginning in column 2.
Pushing LS key 3L initiates a lamp test of the flight deck channel 1 call
lamp.
This line displays ENABLE beginning in column 1 when the test is not
active. The asterisk prompt is shown and the test allowed only if the
log--on state is Standby. This line displays *DISABLE
beginning in column 1 when the test is active. If the log--on state
changes from Standby to any other state while the test is active, the test
is terminated. The commands on lines 8 and 9 are displayed only if the
configuration straps indicate this channel is wired for headset use.
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Line 10
Pushing LS key 4L when the ENABLE asterisk prompt is displayed
causes the voice channel selected to be activated into an analog
loopback test state. Pushing LS key 4L when the DISABLE prompt is
displayed causes the voice loopback test state to be terminated.
This line displays MP8G CALL LIGHT TEST beginning in column 2.
Pushing LS key 5L initiates a lamp test of the flight deck channel 2 call
lamp.
Line 11
This line displays *ENABLE beginning in column 1 when the test is not
active. The asterisk prompt is displayed and the test allowed only if the
log--on state is Standby. This line displays *DISABLE
beginning in column 1 when the test is active. If the log--on state
changes from Standby to any other state while the test is active, the test
is terminated. The commands on lines 10 and 11 are displayed only if
the configuration straps indicate this channel is wired for headset use.
Pushing LS key 5L when the ENABLE asterisk prompt is displayed
causes the cockpit voice call light to be activated for a steady indication
(regardless of the state of configuration pin TP13C). Pushing LS key 5L
when the DISABLE prompt is displayed causes the cockpit voice call
light test to be terminated.
10 Line 12
This line displays MP14BC CHIME beginning in column 2. Pushing LS
key 6L initiates the channel test.
UP86308
11 Line 13
This line displays TEST beginning in column 1. The asterisk prompt is
displayed and the test allowed only if the log--on state is Standby.
Pushing LS key 6L when the asterisk prompt is displayed causes the
cockpit voice go-ahead chime to be activated for a single stroke.
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(5) SATCOM SELF--TEST (PAST) Page
(a) General
The purpose of this page is to initiate a PAST, to enable/disable a voice
loopback on a selected (physical) channel, to enable/disable a test of the
cockpit voice call light for a selected (logical) channel, and activation of the
cockpit voice go-ahead chime test. See Figure 6-7 for example pages.
(b) Data Fields
Line 1
This line displays the title of the page, SAT--N, beginning in column 10,
where N represents 1 or 2 to indicate a single SDU (N = 1), SDU No. 1
(N = 1), or SDU No. 2 (N = 2) as determined by the settings of
configuration pins TP12E and TP12F.
If there are current failures to report after the execution of a PAST,
columns 20 thru 24 display p/t in small font, where p represents the
current displayed page, and t represents the total number of pages
needed to show the current failures. The display of the slash is always
in column 22, with p right-justified to the slash and t left-justified to the
slash.
Line 3
This line displays headers ATA beginning in column 1 and CLASS
beginning in column 20 if there are current failures to report after
execution of a PAST. This line is blank if there are no failures to report.
In addition to the above, for CFDS type none, the header ATA is not
displayed (CLASS is still displayed as specified).
Line 5
UP86308
This line displays the message TEST IN PROGRESS 60S beginning in
column 3 within one second of a PAST being initiated on the SAT--N
(i.e., SATCOM MAINTENANCE) page, and then throughout the duration
of PAST. If there are no current failures to report at the conclusion of the
PAST (including the POST/PAST results delay period), the message
TEST OK is displayed. If there are current failures to report at the
conclusion of the PAST (including the POST/PAST results delay period),
refer to paragraph 4 for line requirements.
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UP86308
Figure 6-7 (Sheet 1).
SATCOM SELF--TEST Page
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UP86308
Figure 6-7 (Sheet 2).
SATCOM SELF--TEST Page
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Other Information
The SELF--TEST page lists two failures per page if failures are detected
during the PAST(self--test). These two sets of lines (lines 5, 6, and 7
and lines 9, 10, and 11) display Level 1 diagnosed current failures.
Failures are shown in chronological order (i.e., the most recent detected
failure last) with no more than two failures displayed per page.
The number of TEST pages depends on the number of current failures
to report (up to a maximum of 99 pages). When there is an odd number
of current failures to report, the odd failure is displayed on a separate
page in lines 5, 6, and 7, and lines 9, 10, and 11 are blank. If there are
no failures to report, lines 5, 6, 7, 9, 10, and 11 are blank except as
noted in paragraph 3.
Line 5 and, if applicable, line 9 display the ATA number beginning in
column 1 and the class number beginning in column 23. The ATA
number is displayed as aaaaaa, where aaaaaa represents the ATA
reference number of the reported failure as specified in paragraph 3.E.
for each type of CFDS. For CFDS type none, no ATA number is
displayed. The class number is displayed as c, where c represents the
class (1, 2, or 3) of the failure.
Lines 6 and 7 and, if applicable, lines 10 and 11 display a text message,
as specified in paragraph 3.E. for each CFDS type, for the reported
failure beginning in column 1.
(6) CONFIGURATION DATA Pages
(a) General
Access to these pages is from the SAT--N (i.e., SATCOM MAINTENANCE)
page. The purpose of these pages is to display the status of SATCOM
configuration input parameters. See Figure 6-8 for example pages.
(b) CONFIGURATION DATA Page 1 (Figure 6-8, sheet 1):
Data Fields
Line 3
(1) This line displays the ICAO address of eight octal characters, as
determined by discrete inputs from the ICAO address straps. This
display is not derived from any ARINC 429 version of the ICAO
address.
Line 5
UP86308
(1) This line displays CONFIG as determined by the setting of the
system configuration pins, followed by (HEX). The configuration pin
settings are mapped into hexadecimal digits as shown in Table 6-9.
In the figure, digits 0 thru 9 correlate to hexadecimal digits 0 thru 9
in the table.
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MCS--4000/7000 Multi--Channel SATCOM System
Figure 6-8 (Sheet 1).
Table 6-9.
Configuration Data
System Configuration Pin Mapping
Configuration Pins
TP10
ABCD
EFGH
TP11
JK
AB CDEF
TP12
GHJK
ABCD
EFGH
TP13
JK
AB CDEF
GHJK
Hex Digits
Line 7
(1) This line displays the WOW--1 status of SDU weight-on-wheels
discrete input No. 1 as IN-AIR/NOT WIRED or ON-GROUND.
Line 8
(1) This line displays the WOW--2 status of the SDU weight-on-wheels
discrete input No. 2 as IN-AIR/NOT WIRED or ON-GROUND.
Line 10
UP86308
(1) This line displays the MIC--1 status of the SDU cockpit voice
microphone On discrete input No. 1 as ACTIVE or INACTIVE.
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MCS--4000/7000 Multi--Channel SATCOM System
Line 11
(1) This line displays the MIC--2 status of the SDU cockpit voice
microphone On discrete input No. 2 as ACTIVE or INACTIVE.
(c) CONFIGURATION DATA Page 2 (Figure 6-8, sheet 2):
Data Fields
Line 3
(1) This line displays the CHIME RESET status of the SDU cockpit
voice go-ahead chime signal reset discrete input as ACTIVE or
INACTIVE.
Line 5
(1) This line displays the DUAL SYS SELECT status of the SDU dual
system select discrete input as ACTIVE or INACT.
Line 6
(1) This line displays the DUAL SYS DISABLE status of the SDU dual
system disable discrete input as ACTIVE or INACT.
Line 8
(1) This line displays IRS SOURCE as determined by which IRS input
bus the SDU is using. A dash is displayed for the IRS source if a
429 source of IRS is not connected to the SDU.
Line 10
(1) This line displays the PLACE/END CALL 1 status of the SDU
cockpit voice place/end call 1 discrete input as ACTIVE or INACT.
Line 11
UP86308
(1) This line displays the PLACE/END CALL 2 status of the SDU
cockpit voice place/end call 2 discrete input as ACTIVE or INACT.
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Figure 6-8 (Sheet 2).
Configuration Data
(d) CONFIGURATION DATA Page 3 (Figure 6-8, sheet 3):
General
For CONFIGURATION DATA pages 3 thru 10, the strap setting value 0
or 1 in parentheses is as follows: 1= open circuit; and 0 = tied to
common.
Data Fields
Line 4
(1) This line displays A(0) ICAO ADRS AVAIL or A(1) ICAO ADRS NOT
AVAIL left-justified as determined by the state of system
configuration pin TP10A.
Line 6
(1) This line displays B(0) FMC1 CONNECTED or B(1) FMC1 NOT
CONNECTED left-justified as determined by the state of system
configuration pin TP10B.
Line 8
UP86308
(1) This line displays C(0) FMC2 CONNECTED or C(1) FMC2 NOT
CONNECTED left-justified as determined by the state of system
configuration pin TP10C.
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Line 10
(1) This line displays D(0) HS 429 TO/FROM CMUS or D(1) LS 429
TO/FROM CMUS left-justified as determined by the state of system
configuration pin TP10D.
Line 12
(1) This line displays E(0) CPDF CONNECTED or E(1) CPDF NOT
CONNECTED left-justified as determined by the state of system
configuration pin TP10E.
Figure 6-8 (Sheet 3).
Configuration Data
(e) CONFIGURATION DATA Page 4 (Figure 6-8, sheet 4):
Data Fields
Line 4
(1) This line displays F(0) HS 429 ICAO ADRS or F(1) LS 429 ICAO
ADRS left-justified as determined by the state of system
configuration pin TP10F.
Line 6
UP86308
(1) This line displays G(0) SPARE or G(1) SPARE left-justified as
determined by the state of system configuration pin TP10G.
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Line 8
(1) This line displays H(0) SPARE or H(1) SPARE left-justified as
determined by the state of system configuration pin TP10H.
Line 10
(1) This line displays J(0) SPARE or J(1) SPARE left-justified as
determined by the state of system configuration pin TP10J.
Line 12
(1) This line displays K(0) LAMP ON CALL INIT or K(1) LAMP ON
CALL CONNCT left-justified as determined by the state of system
configuration pin TP10K.
Figure 6-8 (Sheet 4).
(f)
Configuration Data
CONFIGURATION DATA Page 5 (Figure 6-8, sheet 5):
Data Fields
Line 4
UP86308
(1) This line displays A(0) PARITY: GOOD, A(1) PARITY: GOOD, A(0)
PARITY: BAD, or A(1) PARITY: BAD left-justified as determined by
the state of system configuration pin TP11A and the result of the
parity validation test.
23--20--27
Page 6--43
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Line 6
(1) This line displays B(0) CCS INSTALLED or B(1) CCS NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP11B.
Line 8
(1) This line displays C(0) PRI IRS INSTALLED or C(1) PRI IRS NOT
INSTLLD left-justified as determined by the state of system
configuration pin TP11C.
Line 10
(1) This line displays D(0) SEC IRS INSTALLED or D(1) SEC IRS NOT
INSTLLD left-justified as determined by the state of system
configuration pin TP11D.
UP86308
Figure 6-8 (Sheet 5).
Configuration Data
23--20--27
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(g) CONFIGURATION DATA Page 6 (Figure 6-8, sheet 6):
Data Fields
Lines 4 thru 9
(1) These lines display X(0)* or X(1)* left-justified as shown in the
figure, where X represents E, F, G, H, J, and K, respectively. X(0)*
or X(1)* is determined by the states of system configuration pins
TP11E, TP11F, TP11G, TP11H, TP11J, and TP11K. Asterisks are
displayed in column 5 to indicate these pins are a coded group.
(2) Beginning in column 6, textual messages are displayed (refer to
Table 6-10) in lines 4 thru 9 (as needed), where an x indicates the
message(s) to be displayed based on the state of system
configuration pins TP11E, TP11F, TP11G, TP11H, TP11J, and
TP11K.
Table 6-10.
Textual Message Display (Page 6 -- Lines 4 thru 9)
System Configuration Pin Settings
System Configuration Pin
(1 = open circuit / 0 = tied to common)
TP11E
TP11F
TP11G
TP11H
TP11J
TP11K
Textual Message
Textual Messages To Display Based On System Configuration Pin
Settings
LO GAIN ANT+DLNA
HPA--LO GAIN
HI GAIN ANT+BSU--T/L
HI GAIN ANT+BSU--R
HPA--HI GAIN
HI POWER RELAY
HPA--IGA
All Other Pin Combinations
UP86308
ERROR/UNDEFINED
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Figure 6-8 (Sheet 6).
Configuration Data
(h) CONFIGURATION DATA Page 7 (Figure 6-8, sheet 7):
Data Fields
Lines 4 thru 6
(1) These lines display X(0)* or X(1)* left-justified as shown in the
figure, where X represents A, B and C, respectively. X(0)* or X(1)*
are determined by the state of system configuration pins TP12A,
TP12B, and TP12C. Asterisks are displayed in column 5 to indicate
these pins are a coded group.
(2) CFDS/CMC TYPE = is displayed in line 4 beginning in column 6.
(3) Beginning in column 6, a textual message is displayed according to
Table 6-11, where an x indicates the message to be displayed,
based on the state of system configuration pins TP12A, TP12B and
TP12C.
Line 10
(1) This line displays D(0) RESERVED or D(1) RESERVED left-justified
as determined by the state of system configuration pin TP12D.
Line 12
UP86308
(1) This line displays E(0) OTHER SDU INSTALLED or E(1) OTHER
SDU NOT INSTD left-justified as determined by the state of system
configuration pin TP12E.
23--20--27
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Figure 6-8 (Sheet 7).
Table 6-11.
Configuration Data
Textual Message Display (Page 7 -- Lines 4, 5, an 6)
System Configuration Pin Settings
System Configuration Pin
(1 = open circuit / 0 = tied to common)
TP12A
TP12B
TP12C
Textual Message
MCDONNELL--DOUGLAS
AIRBUS
BOEING
NOT INSTALLED
All Other Pin Combinations
Textual Messages To Display Based On System Configuration Pin
Settings
UP86308
ERROR/UNDEFINED
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(i)
CONFIGURATION DATA Page 8 (Figure 6-8, sheet 8):
Data Fields
Line 4
(1) This line displays F(0) THIS IS SDU2 or F(1) THIS IS SDU1
left-justified as determined by the state of system configuration pin
TP12F.
Line 6
(1) This line displays G(0) CMU1 INSTALLED or G(1) CMU1 NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP12G.
Line 8
(1) This line displays H(0) CMU2 INSTALLED or H(1) CMU2 NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP12H.
Line 10
(1) This line displays J(0) SCDU1 INSTALLED or J(1) SCDU1 NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP12J.
Line 12
UP86308
(1) This line displays K(0) SCDU2 INSTALLED or K(1) SCDU2 NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP12K.
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Figure 6-8 (Sheet 8).
(j)
Configuration Data
CONFIGURATION DATA Page 9 (Figure 6-8, sheet 9):
Data Fields
Line 4
(1) This line displays A(0) NO HSET PRI 4 CALLS or A(1) HSET PRI 4
CALLS OK left-justified as determined by the state of system
configuration pin TP13A.
Line 6
UP86308
(1) This line displays B(0) LS 429 TO SCDUS or B(1) HS 429 TO
SCDUS left-justified as determined by the state of system
configuration pin TP13B.
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Figure 6-8 (Sheet 9).
Configuration Data
Lines 8 and 9
(1) These lines display X(0)* or X(1)* left-justified as shown in the
figure, where X represents C and D, respectively. X(0)* or X(1)* are
determined by the state of system configuration pins TP13C and
TP13D. Asterisks are displayed in column 5 to indicate these pins
are a coded group.
(2) Beginning in column 6, a textual message is shown in line 8 and
according to Table 6-12, where an x indicates the message to be
displayed, based on the state of system configuration pins TP13C
and TP13D.
Line 12
UP86308
(1) This line displays E(0) SCDU3 INSTALLED or E(1) SCDU3 NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP13E.
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MCS--4000/7000 Multi--Channel SATCOM System
Table 6-12.
Textual Message Display (Page 9 -- Lines 8 and 9)
System Configuration Pin Settings
System Configuration Pin
(1 = open circuit / 0 = tied to common)
TP13C
TP13D
Textual Message
Textual Messages to Display Based on System Configuration
Pin Settings
LIGHTS AND CHIME
UNDEFINED
(Line 8)
(Line 9)
STEADY LIGHTS AND
MULTISTROKE CHIME
(Line 8)
(Line 9)
FLASHING LIGHTS AND
SINGLE STROKE CHIME
(Line 8)
(Line 9)
STEADY LIGHTS AND
SINGLE STROKE CHIME
(Line 8)
(Line 9)
(k) CONFIGURATION DATA Page 10 (Figure 6-8, sheet 10):
Data Fields
Lines 4 and 5
(1) These lines display X(0)* or X(1)* left-justified as shown in the
figure, where X represents F and G, respectively. X(0)* or X(1)* are
determined by the state of system configuration pins TP13F and
TP13G.
(2) Beginning in column 6, a textual message is displayed in lines 4
and 5 according to Table 6-13, where an x indicates the message to
be displayed based on the state of system configuration pins
TP13F and TP13G.
Lines 8 and 9
(1) These lines display X(0)* or X(1)* left-justified, where X represents
H and J, respectively. X(0)* or X(1)* are determined by the state of
system configuration pins TP13H and TP13J. Asterisks are
displayed in column 5 to indicate these pins are a coded group.
UP86308
(2) Beginning in column 6, a textual message is displayed in lines 8
and 9 according to Table 6-14, where an x indicates the message to
be displayed based on the state of system configuration pins
TP13H and TP13J.
23--20--27
Page 6--51
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MCS--4000/7000 Multi--Channel SATCOM System
Figure 6-8 (Sheet 10).
Configuration Data
Lines 11 and 12
(1) Line 11 displays K(0) HOOK SWITCH IS left-justified and line 12
displays LATCHED ACP MIC SW beginning in column 6; or line 11
displays K(1) HOOK SWITCH IS left-justified and line 12 displays
SWITCHED PTT/SCDU beginning in column 6, as determined by
the state of system configuration pin TP13K.
Line 13 (LS Key 6L)
UP86308
(1) This line displays right-justified. Pushing LS key 6L
causes the page display to revert to the SAT--N (SATCOM
MAINTENANCE) page.
(7) DATA LOADER MENU Page
(a) General
Access to this page is from SATCOM SUBMENU page (or the SATCOM
MAINTENANCE page). The access page depends on the configuration of
the aircraft as defined in Figure 6-2. The purpose of this page is to supply a
means of commanding data loader actions. See Figure 6-9 for example
pages.
(b) Data Fields
Field 1L
This field displays DATA LOADER in the label line and the data loader
status in the data line. Possible status displays depend on the data
loader status as follows:
• NOT CONNECTED -- Displayed when the status of both data loader
is absent.
• CONNECTED -- Displayed when at least one data loader status is
CONNECTED, and the status of neither data loaders is READY,
BUSY, or ERROR.
• READY -- Displayed when a data loader status is READY.
UP86308
• BUSY -- Displayed when a data loader status is BUSY.
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READY must be displayed before data uploading or downloading can
be performed.
Asterisks are only displayed adjacent to the left LS keys when the data
loader status is READY.
UP86308
Figure 6-9 (Sheet 1).
DATA LOADER MENU
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UP86308
Figure 6-9 (Sheet 2).
DATA LOADER MENU
23--20--27
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UP86308
Figure 6-9 (Sheet 3).
DATA LOADER MENU
23--20--27
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UP86308
Figure 6-9 (Sheet 4).
DATA LOADER MENU
23--20--27
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Several messages are displayed when the status of a data loader is
ERROR . If the status becomes ERROR, an appropriate error message
is appended to ERROR, separated by a dash. Possible error messages
are displayed as follows:
• DISK FULL
• TRANSFER FAILURE
• FILE NOT FOUND
• CRC FAILURE
• BAD FILE HEADER
• BAD OWNER REQS VER
• OPEN DISK
• CLOSE DISK
• WRITE PROTECT
• COMPOSITE ORT NOT ALLOW.
The TRANSFER FAILURE error message indicates an ARINC 615
protocol transfer failure (e.g., loss of communications). The OPEN DISK
and CLOSE DISK error messages are displayed when an undefined
disk command completion code is received. COMP ORT NOT ALLOW
is indicated when a composite ORT version upload is attempted and the
setting for ORT item liv does not allow it.
Fields 2L thru 5L
These fields display prompts in the data line for commanding data
loader actions. The prompts that can be displayed for the indicated
DATA LOADER MENU page (1 or 2) are as given in Table 6-15.
Table 6-15.
UP86308
LS Key
DATA LOADER MENU Page Prompts
Display Prompt (Page 1)
Display Prompt (Page 2)
2L
UPLD OWNER REQS
DNLD MAINTENANCE
3L
DNLD OWNER REQS
DNLD FAILURES
4L
DNLD CALL EVENTS
DNLD SYS EVENTS
5L
DNLD DATA EVENTS
Refer to the description for the 5L
and 5R keys
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MCS--4000/7000 Multi--Channel SATCOM System
The display prompts given in Table 6-15 command the following actions:
•
•
•
•
•
•
•
Asterisks are only displayed beside the adjacent left LS key when the
data loader status is READY (except as stated below). When asterisks
are displayed, pushing the left LS key adjacent to the desired action
commands the data loader to initiate that action. Prior to software
package D2.0, asterisks are not displayed when the data loader status
is either NOT CONNECTED, CONNECTED, BUSY, or ERROR.
In addition, if the data loader status is READY but the log-on state is
LOGGING-ON INOP, LOGGING-ON, LOGGED-ON AUTO, or
LOGGED-ON CONSTRAINED; an asterisk is not displayed beside the
UPLD OWNER REQS prompt. Scratchpad message 1 is issued if an LS
key is pushed when no asterisks are displayed. For software packages
D2.0 and after, uploads are allowed regardless of the log-on state
(composite uploads are inhibited only by ORT item liv and not the log-on
state).
Once a left LS key is pushed, the message is displayed to the
right of the selected data loader action, right-justified. The data loader
status changes to BUSY and data transfers occur. There is only one
data loader command selected at a time. The message remains
displayed until the 6L key is pushed if the data loader status becomes
ERROR after a left LS key is pushed. When the data transfer is
completed, or after an error has been acknowledged, the
message is removed and the data loader status changes appropriately.
Fields 5L and 5R
PERIODIC DATA LOGGING is displayed on page 2 in the label line
beginning in column 2. In the data line, START is displayed adjacent to
the 5L key. No asterisk is displayed beside the 5L key when the data
loader status is either NOT CONNECTED, CONNECTED, BUSY, or
ERROR.
When the START prompt is selected by pushing the 5L key when the
data loader status is READY:
•
•
•
•
UP86308
UPLD OWNER REQS -- upload owner requirements table
DNLD OWNER REQS -- download owner requirements table
DNLD CALL EVENTS -- download call event log
DNLD DATA EVENTS -- download data event log
DNLD MAINTENANCE -- download maintenance activity log
DNLD FAILURES -- download SDU/system failure log
DNLD SYS EVENTS -- download system management event log.
Periodic data logging starts
The asterisk next to START is removed
The message is displayed beginning in column 8
STOP is displayed adjacent to the 5R key.
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Periodic data logging continues until the 5R key is pushed, at that time
the data line display reverts to its original state (i.e., only the START
prompt with or without an asterisk as appropriate).
The message remains displayed and the STOP prompt is
blanked if the data loader status changes to ERROR after periodic data
logging has started. This condition remains until the error is
acknowledged by pushing the 6L key and/or the data loader status
changes, at that time the data line display changes as appropriate.
Field 6L
6L -- This data line displays the *ACK ERROR prompt. This prompt is
displayed when the data loader status is ERROR. Pushing the 6L key
causes the SDU to remove the ERROR status and display the current
data loader status (i.e., NOT CONNECTED or CONNECTED) in the 1L
data line.
The SDU completes the upload/download data transfer by commanding
the data loader transfer complete function. The data loader responds
with a TRANSFER COMPLETE indication and enters a no loop. To
return the data loader to the READY state, the user must cause the
data loader to read the configuration file on the diskette (i.e., cycle data
loader power or remove/insert the diskette).
Field 6R
6R -- This data line displays the RETURN> prompt. Pushing the 6R key
causes the display to revert to the SATCOM SUBMENU page (or
SATCOM MAINTENANCE page) as appropriate.
(8) LAST LEG REPORT Page
(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.
The purpose of this page is to display Class 1 and 2, Level 1 diagnosed, failures
reported during the last leg. See Figure 6-10 for example pages.
UP86308
(b) The Last Leg Report lists two failures per page if a failure is present during the
last leg. These two sets of lines display Class 1 and 2, Level 1 diagnosed, last
leg failures. Failures are displayed in chronological order (i.e., the most recent
detected failure last) with no more than two failures displayed per page. The
number of LAST LEG REPORT pages depends on the number of failures to
report (up to a maximum of 99 pages). When there is an odd number of failures
to report, the odd failure is displayed on a page of its own in lines 5, 6, and 7,
and lines 9, 10, and 11 are blank. If there are no failures to report, lines 6, 7, 9,
10, and 11 are blank. Line 5 displays NO FAULT DETECTED beginning in
column 4 if there are no failures to report.
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UP86308
Figure 6-10.
LAST LEG REPORT Page
23--20--27
Page 6--67
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(c) Line 5 and, if applicable, line 9 display the universal time coordinated (UTC)
beginning in column 1, and ATA beginning in column 6, and the class number in
column 23.
(d) The UTC is displayed as hhmm, where hh represents the UTC hours from 00 to
23, and mm represents the UTC minutes from 00 to 59. The UTC is the time of
the failure reporting as stored in the SDU system failure memory log. Dashes are
displayed if no valid UTC data is available.
(e) The ATA number is displayed as aaaaaa, where aaaaaa represents the ATA
reference number of the reported failure as specified in paragraph 3.E. for each
type of CFDS. For CFDS type none, no ATA number is displayed.
(f)
The class number is displayed as c, where c represents the class (1 or 2) of the
failure.
(9) PREVIOUS LEGS REPORT Page
(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.
The purpose of this page is to display Class 1 and 2, Level 1 diagnosed, failures
reported during previous legs. See Figure 6-11 for example pages.
(b) The Previous Leg Report lists two failures per page if a failure was present
during the previous leg. These two sets of lines display Class 1 and 2, Level 1
diagnosed, last leg failures. Failures within each flight leg are displayed in
chronological order (i.e., the most recent detected failure last) with no more than
two failures displayed per page. However, the flight leg display is in reverse
chronological order (i.e., flights go back in time while failures for each individual
flight go forward in time).
(c) The number of PREVIOUS LEGS REPORT pages depends on the number of
failures to report (up to a maximum of 99 pages). If there are no failures to
report, lines 6, 7, 9, 10, and 11 are blank. Line 5 displays NO FAULT DETECTED
beginning in column 4 if there are no failures to report.
(d) Failures from different flight legs with the same aircraft identification are mixed on
the same page. When the last leg falls in lines 5, 6, and 7, failures from the
previous flight leg are displayed on the same page in lines 9, 10, and 11.
UP86308
(e) When the given flight leg has a different aircraft identification recorded than the
flight leg before it, the failure display begins in lines 5, 6, and 7 on the next page
of the multiple page sequence. When there are no failures to report for a given
flight leg, nothing is reported for that flight leg (i.e., the flight leg is skipped).
23--20--27
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UP86308
Figure 6-11 (Sheet 1).
PREVIOUS LEG REPORT Page
23--20--27
Page 6--69
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UP86308
Figure 6-11 (Sheet 2).
PREVIOUS LEG REPORT Page
23--20--27
Page 6--70
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(f)
Line 5 and line 9 (if applicable) display the flight leg number beginning in column
1, the UTC beginning in column 10, and the ATA number beginning in column
15.
(g) The flight leg is displayed as fl, where fl represents the flight leg number from 01
to either:
• The number of flight legs recorded in the SDU system failure memory log
• 63 flight legs
• From 01 to the maximum number of flight legs that can be displayed given the
PREVIOUS LEGS REPORT page limit of 99.
(h) The date is displayed as mmmdd, where mmm represents the month of the year
as JAN, FEB, MAR, APR, MAY, JUN, JUL, AUG, SEP, OCT, NOV, or DEC, and
dd represents the day of the month from 01 to 31. The date is the date of the
flight leg number as stored in the SDU system failure memory log. Dashes are
displayed if no valid UTC data is available.
(i)
The UTC time is displayed as hhmm, where hh represents the UTC hours from
00 to 23, and mm represents the UTC minutes from 00 to 59. The UTC is the
time of the failure reporting as stored in the SDU system failure memory log.
Dashes are displayed if no valid UTC data is available.
(j)
The ATA number is displayed as aaaaaa, where aaaaaa represents the ATA
reference number of the reported failure as specified in paragraph 3.E. for each
type of CFDS. For CFDS type none, no ATA number is displayed.
(k) The class number is displayed as c, where c represents the class (1 or 2) of the
failure.
(10) LRU IDENTIFICATION Page
(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.
The purpose of this page is to display a list of all installed LRUs with their
associated part numbers, modification levels, and serial numbers, and to display
ORT identification data. See Figure 6-12 for example pages.
(b) If a Honeywell/Racal HPA is installed, the associated part/serial number is
displayed; otherwise the HPA display entry is removed. The number of LRU
IDENTIFICATION pages depends on the number of LRUs to list.
UP86308
(c) For the LRUs, line 4 and, if applicable, line 9 display a three letter acronym
representing the installed LRU. The possible LRU acronyms are given in
Table 6-16.
23--20--27
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Table 6-16.
LRU Acronyms
LRU Acronym
LRU Name
SDU
Satellite Data Unit
HPH
High Power Amplifier -- High Gain Antenna
HPL
High Power Amplifier -- Low Gain Antenna
(d) For the LRUs, line 5 and, if applicable, line 10 display P/N beginning in column 1,
the LRU end-item part number beginning in column 6, and the software
modification level in columns 23 and 24.
(e) The P/N is displayed as bbbbbbb--hhsss, where bbbbbbb--hhsss represents the
LRU end-item part number consisting of a seven-digit LRU base part number
(i.e., bbbbbbb), a two-digit hardware configuration number (i.e., hh), and a
three-digit software configuration number (i.e., sss). Dashes are displayed if no
valid data is available.
(f)
The software modification level is displayed as nn, where nn represents up to a
two-character LRU software modification level.
(g) Line 6 and, if applicable, line 11 display S/N beginning in column 1 and the LRU
serial number beginning in column 5. The S/N is diplayed as ssssssss, where
ssssssss represents the LRU serial number. Dashes are displayed if no valid
data is available.
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(h) For the Honeywell/Racal MCS system, the two-digit LRU hardware and LRU
serial number must be manually entered through the CMT interface for valid data
to be available for display. This data is stored during an LRU end-item test. All
other numbers reside within the LRU software. For non-Honeywell/Racal
interfacing HPAs, no such data is available to the SDU, therefore, dashes are
displayed for the HPA part/serial numbers.
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UP86308
Figure 6-12 (Sheet 1).
LRU IDENTIFICATION Page
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UP86308
Figure 6-12 (Sheet 2).
LRU IDENTIFICATION Page
(i)
The ORT identification is displayed in either lines 4, 5, and 6, or in lines 9, 10,
and 11 depending on where the LRU list falls. Line 4 or line 9, as appropriate,
displays the header ORT IDENTIFICATION left-justified. If the ORT is a
partitioned version, the text, --USER, is added to the end of the header text. Line
5 or line 10, as appropriate, displays the ORT 24-character description as
contained in ORT item xxxiii (refer to Appendix B). Line 6 or line 11, as
appropriate, displays MODIFIED left-justified, if the state of ORT item xxxvii (refer
to Appendix C) is modified. If the state of ORT item xxxvii is unmodified, the
MODIFIED flag is not displayed.
(j)
If the ORT is loaded as separate partitions, the secured ORT identification is
displayed in either lines 4, 5, and 6, or in lines 9, 10, and 11 depending on where
the first ORT ident falls. Line 4 or line 9, as appropriate, displays the header ORT
IDENTIFICATION--SECD left-justified. Line 5 or line 10, as appropriate, displays
the ORT 24-character description as contained in ORT item liii (refer to Appendix
C) for the secured partition. Line 6 or line 11, as appropriate, displays MODIFIED
left-justified, if the state of the ORT secured partition modified flag (refer to
Appendix C) is modified. If the state of the ORT secured partition modified flag is
unmodified, the MODIFIED flag is not displayed.
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(11) TROUBLE SHOOTING DATA Page
(a) General
Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE)
page. The purpose of this page is to display Class 1 and 2, Level 1,
diagnosed failures reported during the last leg and previous legs. See
Figure 6-13 for example pages.
The Trouble Shooting Data pages display the class 1 and 2 last leg and
previous legs failure details. Failures are displayed in chronological order
(i.e., the most recent detected failure last) with one failure displayed per
page. Flight leg display order is reverse chronological (i.e., flights go back in
time while failures for each individual flight go forward in time). The number
of pages depends on the number of failures to report (up to 64 flight legs or
99 pages).
(b) Data Fields
Line 4
Line 4 displays the date beginning in column 2 and the UTC beginning
in column 8. The date and time are displayed as follows.
The month is displayed as mmm, where mmm represents the month of
the year as JAN, FEB, MAR, APR, MAY JUN, JUL, AUG, SEP, OCT,
NOV, or DEC.
The day is displayed as dd, where dd represents the day of the month
from 01 to 31.
The UTC is displayed as hh:mm, where hh represents the UTC hours
from 00 to 23 and mmm represents the UTC minutes from 00 to 59. The
UTC is the time the failure was stored in the failure memory log on this
flight leg. Dashes are displayed if no valid UTC data is available.
Line 4 displays the header, LEG, beginning in column 15 and the flight
leg count right-justified from column 23.
Line 5
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Line 5 displays beginning in column 2 the LRU abbreviated name of up
to five characters that corresponds to the level 1 failure code. The SRU
abbreviated name of up to five characters is displayed beginning in
column 8. If the SRU designation in the failure code is 0, no SRU
abbreviation is displayed. The LRU failure code is displayed as two
hexadecimal digits beginning in column 17. The SRU failure code is
displayed as one hexadecimal digit beginning in column 20. The failure
code is displayed as two hexadecimal digits beginning in column 22.
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UP86308
Figure 6-13.
TROUBLE SHOOTING DATA Page
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Line 6
Line 6 displays the time since power--on (TSPO) header beginning in
column 2, and the LRU power--on counter (POC) header beginning in
column 15. The LRU time since power-on is displayed right-justified
from column 12.
The TSPO is displayed as hhh:mm, where hhh represents the hours of
the elapsed time since the unit powered up from 0 to 999, and mm
represents the minutes portion of the elapsed time from 0 to 59.
Line 6 displays the power-on count value from 0 to 65535 right-justified
from column 23.
Line 7
Line 8
Line 9 displays the headers, CLASS, beginning in column 2, and IFC,
beginning in column 15. The failure class is displayed in column 12. The
intermittent failure count is displayed in column 23.
Line 10
Line 8 displays the headers, PHASE, beginning in column 2, and DC,
beginning in column 15. The flight phase is displayed right-justified from
column 12. If a numbered flight phase is not available, then an a or g is
shown in column 12, as appropriate. The DC state is displayed as DC0,
DC0’, DC1, DC1’, or DC2 right-justified from column 23.
Line 9
Line 7 displays the headers, TEMP, beginning in column 2, and
groundspeed (GSPD), beginning in column 15. The LRU-failed SRU (or
PSU) temperature is displayed right-justified from column 12. Dashes
are displayed if no valid temperature data is available. The GSPD is
displayed right-justified from column 23.
Line 10 displays the header FLTNO beginning in column 2. The flight
number is displayed right-justified from column 12. The aircraft tail
number is displayed right-justified from column 23. Dashes are
displayed if no valid flight number or tail number data is available.
Line 11
Line 11 displays the failure parameter as eight hexadecimal digits
beginning in column 5. The associated parameter is displayed as eight
hexadecimal digits beginning in column 16.
(12) LAST LEG CLASS 3 FAULTS Page
UP86308
(a) Access to this page is from the SAT--N (CFDS SATCOM Maintenance Menu)
page. The purpose of this page is to display Class 3, Level 1 diagnosed, failures
reported during the last leg. See Figure 6-14 for example pages.
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Figure 6-14.
LAST LEG CLASS 3 FAULTS Page
UP86308
(b) The Last Leg Class 3 Faults lists two Class 3 faults per page if Class 3 faults are
present during the last leg. These two sets of lines display Class 3, Level 1
diagnosed, last leg failures. Failures are displayed in chronological order (i.e.,
the most recent detected failure last) with no more than two failures displayed
per page.
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(c) The number of LAST LEG CLASS 3 FAULTS pages depends on the number of
failures to report (up to a maximum of 99 pages). When there is an odd number
of failures to report, the odd failure is displayed on a separate page in lines 5, 6,
and 7, and lines 9, 10, and 11 are blank. If there are no failures to report, lines 6,
7, 9, 10, and 11 are blank. Line 5 displays NO FAULT DETECTED beginning in
column 4 if there are no failures to report.
(d) Line 5 and, if applicable, line 9 display the UTC beginning in column 1 and the
ATA number beginning in column 6.
(e) The UTC number is displayed as hh:mm, where hh represents the UTC hours
from 00 to 23, and mm represents the UTC minutes from 00 to 59. The UTC is
the time of the failure reporting as stored in the SDU system failure memory log.
Dashes are displayed if no valid UTC data is available.
(f)
The ATA number is displayed as aaaaaa, where aaaaaa represents the ATA
reference number of the reported failure as specified in paragraph 3.E. for each
type of CFDS. For CFDS type none, no ATA number is displayed.
(13) GROUND REPORT Page
(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.
The purpose of this page is to display Class 1, 2, or 3, Level 1 diagnosed ground
failures that occurred during the last leg. See Figure 6-15 for example pages.
(b) The Ground Report lists two failures per page if failures are detected during the
last leg. These two sets of lines display Class 1, 2, and 3, Level 1 diagnosed,
last leg failures. Failures are displayed in chronological order (i.e., the most
recent detected failure last) with no more than two failures displayed per page.
UP86308
(c) The number of GROUND REPORT pages depends on the number of failures to
report (up to 99 pages). When there is an odd number of failures to report, the
odd failure is displayed on a separate page in lines 5, 6, and 7, and lines 9, 10,
and 11 are blank. If there are no failures to report, lines 6, 7, 9, 10, and 11 are
blank. Line 5 displays NO FAULT DETECTED beginning in column 4 if there are
no failures to report.
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UP86308
Figure 6-15.
GROUND REPORT Page
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(14) GROUND REPORT (TROUBLE SHOOTING DATA) Page
(a) General
Access to this page is from the GROUND REPORT page. The purpose of
this page is to display Class 1, 2, or 3, Level 1 diagnosed ground failures
that occurred during the last leg ground report. See Figure 6-16 for example
pages.
One failure is listed per page if a failure is present. These lines display Class
1, 2, and 3, Level 1 diagnosed, last leg ground report failure details
corresponding to the Level 1 failures from which the troubleshooting data
was initiated. Failures are displayed in chronological order (i.e., the most
recent detected failure last) with one failure displayed per page.
(b) Data Fields
Line 4
Line 4 displays the date beginning in column 2 and the UTC beginning
in column 8. The date and time are displayed as follows.
The month is displayed as mmm, where mmm represents the month of
the year as JAN, FEB, MAR, APR, MAY, JUN, JUL, AUG, SEP, OCT,
NOV, or DEC.
The day is displayed as dd, where dd represents the day of the month
from 01 to 31.
The UTC is displayed as hh:mm, where hh represents the UTC hours
from 00 to 23 and mm represents the UTC minutes from 00 to 59. The
UTC is the time the failure was stored in the failure memory log on this
flight leg. Dashes are displayed if no valid UTC data is available.
Line 5
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Line 5 displays the LRU abbreviated name of up to five characters that
corresponds to the Level 1 failure code. The SRU abbreviated name of
up to five characters is displayed beginning in column 8. If the SRU
designation in the failure code is 0, no SRU abbreviation is displayed.
The LRU failure code is displayed as two hexadecimal digits beginning
in column 17. The SRU failure code is displayed as one hexadecimal
digit beginning in column 20. The failure code is displayed as two
hexadecimal digits beginning in column 22.
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UP86308
Figure 6-16.
GROUND REPORT TROUBLE SHOOTING DATA Page
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Line 6
Line 6 displays the headers, TSPO, beginning in column 2 and, POC,
beginning in column 15. The LRU time since power-on is displayed
right-justified from column 12.
The UTC is displayed as hh:mm, where hh represents the UTC hours
from 00 to 23 and mm represents the UTC minutes from 00 to 59. The
UTC is the time the failure was stored in the failure memory log on this
flight leg. Dashes are displayed if no valid UTC data is available.
Line 6 displays the power-on count value from 0 to 65535 right-justified
from
column 23.
Line 7
Line 8
UP86308
Line 7 displays the headers, TEMP, beginning in column 2, and GSPD,
beginning in column 15. The LRU-failed SRU (or PSU) temperature is
displayed right-justified from column 12. Dashes are displayed if no valid
temperature data is available. The groundspeed is displayed
right-justified from column 23.
Line 8 displays the headers, PHASE, beginning in column 2, and DC,
beginning in column 15. The flight phase is displayed right-justified from
column 12. If a numbered flight phase is not available, then an a or g is
shown in column 12, as appropriate. The DC state is displayed as DC0,
DC0’, DC1, DC1’, or DC2 right-justified from column 23.
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3. Maintenance Computer Interface
A. General
(1) The SDU is designed to interface with the Boeing 747--400 Central Maintenance
Computer (CMC) or the Boeing 777 On--board Maintenance System (OMS), the
Airbus Central Fault Display System (CFDS), and the McDonnell Douglas CFDS in
accordance with guidelines outlined in Boeing documents D220U050 (747--400 CMC
-- release date 3 June 1991) and D243W201--1 (777 OMS -- release date 30 October
1992) and Airbus document ABD0048 issue C, all of which supersede ARINC 604 for
their respective applications.
(2) The Boeing maintenance computers (i.e., 747--400 CMC and 777 OMS) are virtually
indistinguishable to the SDU. The operations to support these two systems are very
similar and, therefore, are presented together. The operations to support the Airbus
and McDonnell Douglas maintenance computers are very similar and, therefore, are
presented together. The SDU determines the aircraft type on which the SDU is
installed, and then supports only the functionality required by that particular system.
B. Boeing 747--400 CMC/777 OMS
(1) General
(a) The CMC and SDU communicate with each other through an ARINC 429 data
bus using ARINC 429 words.
(b) When the SDU receives the standard ground test command containing its
equipment ID and source destination identifier (SDI), the SDU responds by
setting the command word (ARINC label 350) acknowledge bit to ACK for four
seconds. The SDU initiates a system-wide functional test. As soon as possible
during the execution of the functional test, the SDU sets the SSM for ARINC
label 350 to functional test.
(2) CMC to SDU Communication -- Automatic Fault Reporting
(a) The CMC and SDU communicate with each other through an ARINC 429 data
bus using ARINC 429 words.
(b) When the SDU receives the standard ground test command containing its
equipment ID and source destination identifier (SDI), the SDU responds by
setting the command word (ARINC label 350) acknowledge bit to ACK for 4
seconds. The SDU then initiates a system-wide functional test. As soon as
possible during the execution of the functional test, the SDU sets the SSM for
ARINC label 350 to functional test.
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(c) At the conclusion of the functional test, the SDU builds the fault summary words
using ARINC labels 350 thru 354 by mapping currently active failures to the
appropriate bits in the words. Once the words are built they are latched for 30
seconds, then the SDU returns to automatic fault reporting. The SDU
continuously transmits the fault summary words to the CMC at a rate of 1 to 2
Hz, with the SSM bits set to normal operation during reporting of the test results.
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(3) CMC Interactive Mode
(a) The SDU supports configuration data in CMC interactive mode for a Boeing 777
installation. If the CMC transmits a configuration data interactive mode command
addressed to the SDU on ARINC label 227, the SDU processes the command by
supplying the first page of configuration information and then resumes automatic
mode processing. The configuration data command is used to display
configuration information for the SATCOM LRUs (SDU and HPAs). The SDU
responds to the configuration data command from the automatic mode.
(b) The SDU does not support ground test and shop faults in CMC interactive mode.
If the CMC transmits a ground test or shop faults interactive mode command
addressed to the SDU on label 227, the SDU ignores the command.
(4) Configuration Data Messages
(a) General
When configuration data is commanded, the MCS configuration data
page(s) is(are) displayed. These data pages display installed LRUs as
determined by the SDU system configuration pin settings with their
associated part/serial number data. These lines also display the ORT
identification along with modification status. Figure 6-17 supplies an
example of the configuration data page.
The ORT 24-character description as contained in ORT item xxxiii is
displayed. For non-777 installations, the text is limited to 20 characters per
line.
(b) USER ORT STATUS
This displays MODIFIED if the state of the ORT user partition is modified,
otherwise no status or header is displayed.
(c) SECD ORT IDENTIFICATION
This is the 24-character description as contained in ORT item liii. For
non-777 installations, the text is limited to 20 characters per line.
(d) SECURED ORT STATUS
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This displays MODIFIED if the state of the ORT secured partition is modified,
otherwise, no status or header is displayed. For software package C3.5, the
ORT is not partitioned so only a single ORT IDENTIFICATION is supplied for
the ORT display lines.
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Figure 6-17.
Configuration Data Pages for Boeing 777 Installation
(e) LRU PART NUMBER
(f)
The part numbers for the LRUs installed are displayed as follows. The word
LRU is displayed, which is substituted with the appropriate LRU acronym.
The LRU part number is displayed as bbbbbbb-hhsss, where
bbbbbbb-hhsss represents the LRU end item part number consisting of a
seven-digit LRU base part number (bbbbbbb), a two-digit hardware
configuration number (hh), and a three-digit software configuration number
(sss). Dashes are displayed if no valid data is available.
LRU SERIAL NUMBER
The serial numbers of the LRUs installed are displayed as follows. The word
LRU is displayed, which is substituted with the appropriate LRU acronym.
The LRU serial number is displayed as ssssssss, where ssssssss represents
the LRU serial number. Dashes are displayed if no valid data is available.
(g) SDU S/W PART NUMBER
UP86308
This displays the software part number that corresponds to the software
load. The configuration data page includes the header SDU CONFIG
STRAPS and the raw strap setting for the current installation.
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(5) Standard Ground Test (Non--interactive)
(a) When a standard test on a CMC ground test menu is selected, the CMC
commands the SDU to start a standard ground test. The SDU prevents the CMC
commanded standard ground test while the aircraft is airborne. The SDU starts a
system-wide PAST after it has responded to the receipt of a standard ground test
command from the CMC.
(b) At the end of the CMC-commanded PAST, the SDU builds labels 350 thru 354
fault summary words by mapping PAST-detected SATCOM subsystem failures to
the appropriate bits. The SDU continuously transmits these fault summary words
to the CMC at a rate of 1 to 2 Hz, with the SSM set to Normal Operation, during
reporting of the test results.
C. Airbus/Douglas CFDS
(1) General
(a) The CFDS uses a centralized fault display interface unit (CFDIU) as an interface
between the SDU and the SCDU. Throughout these paragraphs the acronym
CFDIU is used to include both the A320 CFDS and the A340 CMC.
(b) When the SDU is installed on an Airbus or McDonnell Douglas aircraft with a
CFDS, it supports the normal mode and interactive mode as required by the
CFDS.
(2) CFDIU to SDU Communication
(a) The CFDIU communicates with the SDU through an ARINC 429 data bus using
ARINC 429 words.
(3) SDU to CFDIU Communication
(a) The SDU supports both the normal mode and the interactive mode, as required
by the CFDS. The SDU also transmits the LRU part number and serial number
and ORT identification data blocks to the CFDIU.
(b) The LRU/ORT identification data records make up the LRU/ORT identification
data blocks. Each LRU data record contains the LRU acronym, part number, and
serial number. Each ORT identification data record contains the ORT
IDENTIFICATION header, the ORT 24 character description, and the state of the
modified flag.
(4) Normal Mode Failure Messages
(a) As specified, the SDU transmits failure messages and LRU/ORT identification
information while operating in the normal mode. The following paragraphs
defined the contents of these reports.
UP86308
(b) Once a failure is reported in the normal mode, the failure remains in the report
for that entire flight, regardless of whether the failure is cleared. As new failures
are reported, they are added to the beginning of the report (i.e., the report is in
reverse chronological order, bearing in mind the CFDS considers the time of the
failure to be the time it is first reported on this flight leg rather than when it first
occurs).
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(c) In addition to latching the failures, the contents of the normal mode report
depend on the failure class and when it occurs in relationship to other failures
against the same LRU. Level I failures against the same LRU reported in the
normal mode are not to be transmitted more than once unless they are an upper
class and the upper class failure occurs after the lower class failure(s). Once a
report is sent to the CFDIU during the normal mode for the current flight, the
SDU does not change the content or order except to add new failure messages,
as appropriate to the beginning of the report.
(d) The McDonnell Douglas CFDIU does not decode the normal mode report until
the CFDIU detects an increase in the block word count. However, unlike the
Airbus CFDIU, the McDonnell Douglas CFDIU decodes the entire report. After
sending an All Call DC2 command for a new flight leg, the Airbus CFDIU delays
processing the normal mode report for about 30 seconds before regarding the
report as pertaining to the new flight leg.
(e) The SDU transmits the names of the installed LRUs, as determined by the
system configuration pin settings, along with their associated part/serial
numbers. At the end of this LRU transmission, the SDU transmits the ORT
identification with a modification status. The LRU names can be transmitted in
any order. Transmission of an HPA LRU part/serial number uses the same
criteria as the display of HPA data.
(5) Interactive Mode
(a) The CFDIU supplies for two-way communication between the SCDU and the
SDU, which is referred to as the interactive mode. When the SDU operates in the
interactive mode, it is responsible for all information displayed on the CFDS
maintenance pages, with exception of the scratchpad. The SDU enters the
interactive mode upon receiving an ENQ command from the CFDIU when the
aircraft is on the ground.
D. Central Aircraft Information and Maintenance System
(1) The central aircraft information and maintenance system (CAIMS) is a distributive
maintenance system where each member system performs its own built--in test (BIT)
and stores its own faults. Also, each system supplies real--time status information on
the health of each of its LRUs and their interfaces. The member systems support
CAIMS during normal operation and during on--ground maintenance.
UP86308
(2) In the normal operation mode, member systems gather and store fault data when
equipment failure occurs during normal operation. This is typically performed by
continuous BIT and power--up BIT, with identified faults stored in the member
systems non--volatile memory (NVM). The CAIMS does not store fault information for
member systems, but the fault warning processor (FWP) supplies fault event data,
such as: flight leg, date, time, fault zone, and aircraft serial number information that is
stored with the fault in the member systems NVM.
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(3) In the maintenance mode, the CAIMS is active and is called the on--board
maintenance system (CAIMS OMS). The CAIMS OMS is the ground maintenance
function and is accessible through communication link to a portable maintenance
access terminal (PMAT). With the PMAT, the aircraft maintenance crew can retrieve
stored fault data from a member system. For member systems, the CAIMS OMS
displays fault information, commands BITE test, and displays real--time data for
status displays, and commands the download of NVM fault data.
E.
Level I Failure Messages and ATA Reference Numbers
(1) The Level I failure messages and ATA reference numbers that are available for
transmittal in the CFDS normal mode, for display in the CFDS interactive mode, and
for display on SCDU accessed maintenance pages are specified in the following
paragraphs for each CFDS type installed. Level I failure messages are intended for
use by line maintenance crews. Therefore, the failure messages are designed to be
LRU-based and only supply LRU-level identification.
(2) The Level 1 failure codes are two-digit hexadecimal numbers that define the LRU,
data communication bus, or miscellaneous interface signal where a failure, bus
inactivity, or signal error has been determined to have occurred. When multiple LRUs
are suspect, the most likely LRU is listed first followed by the next most likely LRU,
separated by a slash. The ATA number listed is for the first suspect LRU. Additional
text can be supplied at the end to help clarify the failure message.
• Table 6-17 describes the Level I failure messages and ATA reference numbers to
use for display on the SCDU accessed maintenance pages when the installed
CFDS type is a Boeing CMC. Also shown is the CMC message ID which is
displayed by the CMC in response to the Level I failure messages (refer to the
OEM’s maintenance manual and fault isolation manual).
• Table 6-18 and Table 6-19 describe the Level I failure messages and ATA
reference numbers to use for transmittal in the CFDS normal mode, and the CFDS
interactive mode pages displayed when the installed CFDS type is an Airbus.
Table 6-18 is for the SDU (single configuration) or SDU No. 1 (dual configuration),
and Table 6-19 is for SDU No. 2 (dual configuration) as determined by the settings
of configuration pins TP12E and TP12F.
• Table 6-20 describes the Level I failure messages and ATA reference numbers to
use for transmittal in the CFDS normal mode, and the CFDS interactive mode
pages displayed when the installed CFDS type is a McDonnell Douglas.
• For CFDS type none, the Level I failure messages displayed on the SCDU
accessed maintenance pages are the same as those specified for Boeing (refer to
Table 6-17). However, no ATA reference numbers are displayed.
UP86308
(3) For Level I codes identified as not applicable in the tables, the SDU does not report
the failure on that particular interface (i.e., CFDS normal and interactive modes or
SCDU accessed maintenance pages as appropriate). Where TBD is used in the
Level I failure message column, it is coded as literally read. For failures that occur
that are undefined in the tables, the SDU does not report the failure on that particular
interface.
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 6-17.
UP86308
Failure
Code
Boeing Level I Failure Messages and ATA Reference Numbers
SCDU Accessed Maintenance Pages
ATA Number
CMC
Message ID
01
SDU
232500
23205
02
OTHER SDU INCOMPATIBILITY
232500
23205
03
RESERVED
04
HPA--HI GAIN
HPA--HI GAIN
232500
23207
07
HPA--LO GAIN
232500
23209
0A
HI POWER RELAY
232500
23218
0D
LNA/DIP--(TOP/PORT)
232500
23210
0F
LNA/DIP--STBD
232500
23211
10
LNA/DIP--LO GAIN
232500
23212
13
BSU--(TOP/PORT)
232500
23213
15
BSU--STBD
232500
23214
1A
IN GAIN ANTENNA--TOP
HI GAIN ANTENNA--(TOP/PORT)
232500
23215
1C
HI GAIN ANTENNA--STBD
232500
23216
1F
LO GAIN ANTENNA
232500
23225
21
MCDU1
346100
22
MCDU2
346100
23
MCDU3
346100
33
(ACARS MU/CMU)1
232700
23219
34
(ACARS MU/CMU)2
232700
23219
35
IRS--PRI
342100
34222
36
IRS--SEC
342100
34224
37
RESERVED
38
RESERVED
39
CMC
454500
23201
3D
FMC1
346100
3E
FMC2
346100
40
ARINC 429 ICAO ADDRESS
[IGA]
[HGA]
[IGA]
[HGA]
None
23--20--27
23251
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MCS--4000/7000 Multi--Channel SATCOM System
Table 6-17.
Boeing Level I Failure Messages and ATA Reference Numbers (cont)
UP86308
Failure
Code
SCDU Accessed Maintenance Pages
ATA Number
CMC
Message ID
23235
42
CTU
231900
43
(CFS/CPDF)
233200
52
(CFS/CPDF)/SDU
233200
53
(ACARS MU/CMU)1/SDU
232700
23219
54
CTU/SDU
231900
23235
55
MCDU1/SDU
346100
56
MCDU2/SDU
346100
57
(ACARS MU/CMU)2/SDU
232700
23235
59
CMC/SDU
454500
23201
5A
IRS--PRI/SDU
342100
23222
5B
IRS--SEC/SDU
342100
23224
5C
HPA--IN GAIN/SDU
HPA--HI GAIN/SDU
232500
23226
5F
HPA--LO GAIN/SDU
232500
23225
62
BSU--(TOP/PORT)/SDU
232500
23213
64
BSU--STBD/SDU
232500
23214
66
MCDU3/SDU
346100
67
RESERVED
68
RESERVED
6A
RESERVED
6C
RESERVED
6D
RESERVED
6E
RESERVED
6F
RESERVED
71
OTHER SDU/THIS SDU
232500
73
FMC1/SDU
346100
74
FMC2/SDU
346100
80
RESERVED
82
RESERVED
[IGA]
[HGA]
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 6-17.
Boeing Level I Failure Messages and ATA Reference Numbers (cont)
UP86308
Failure
Code
SCDU Accessed Maintenance Pages
ATA Number
CMC
Message ID
232500
23246
88
RESERVED
90
SDU M--CTRL/HPA--IN GAIN
SDU M--CTRL/HPA--HI GAIN
96
SDU M--CTRL/HPA--LO GAIN
232500
23248
98
SDU M--CTRL/BSU--(TOP/PORT)
232500
23249
9A
BSU--STBD XTALK/BSU--PORT
232500
23252
9C
SDU M--CTRL/BSU--STBD
232500
23250
9D
BSU--PORT XTALK/BSU--STBD
232500
23253
C0
WRG:CONFIG PIN PROG/SDU
232500
23236
C1
SDU WOW MISCOMPARE
C2
SDU/OTHER SDU SELECT--DISABLE DISCRETE
232500
C3
WRG:ICAO ADDRESS PIN PROG/SDU
232500
23251
C4
TX PATH VSWR--IN GAIN
TX PATH VSWR--HI GAIN
232500
23257
C5
WRG:CONFIG PIN PROG/SDU OWNER REQS
232500
C6
TX PATH VSWR--LO GAIN
232500
23216
C7
HPA--HI GAIN/OVER TEMPERATURE
HPA--HI GAIN/OVER TEMPERATURE
232500
23247
C8
BAD DATA FROM GROUND EARTH STATION
C9
HPA--LO GAIN/OVER TEMPERATURE
232500
23254
CA
SDU/LNA/DIP--LO GAIN
232500
23237
CB
WRG:SDI PIN PROG/HPA--IN GAIN
WRG:SDI PIN PROG/HPA--HI GAIN
CC
WRG:SDI PIN PROG/HPA--HI GAIN
CD
SDU (POC/TOTC) DATA RESET
CE
RESERVED
CF
HPA--IN GAIN (POC/TOTC) DATA RESET
HPA--HI GAIN (POC/TOTC)DATA RESET
D0
HPA--LO GAIN (POC/TOTC) DATA RESET
[IGA]
[HGA]
N/A
[IGA]
[HGA]
[IGA]
[HGA]
None
[IGA]
[HGA]
232500
232500
None
[IGA]
[HGA]
None
None
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 6-17.
Boeing Level I Failure Messages and ATA Reference Numbers (cont)
Failure
Code
SCDU Accessed Maintenance Pages
ATA Number
[IGA]
D1
WRG:SDI PIN PROG/HPA--IN GAIN
WRG:SDI PIN PROG/HPA--HI GAIN
D2
WRG:SDI PIN PROG/HPA--LO GAIN
232500
D3
WRG:SDI PIN PROG/BSU--(TOP/PORT)
232500
D4
WRG:SDI PIN PROG/BSU--STBD
232500
D5
SDU COAX/HPA--IN GAIN
SDU COAX/HPA--HI GAIN
D6
SDU COAX/HPA--LO GAIN
D7
RESERVED
D8
[HGA]
[IGA]
232500
232500
23237
232500
23237
LNA/DIP/ (SDU)--(TOP/PORT)
232500
23236
D9
LNA/DIP/ (SDU)--STBD
232500
23236
DA
LNA/DIP/ (SDU)--LO GAIN
232500
23236
DB
LO GAIN SUBSYSTEM
232500
DC
NO ACTIVE ACARS MU/CMU
232700
DD
SDU OWNER REQS -- SECURED
None
DE
SDU OWNER REQS -- USER
None
DF
IN GAIN SUBSYSTEM
HI GAIN SUBSYSTEM
E0
RESERVED
FE
POWER SUPPLY INTERRUPT
Table 6-18.
Failure
Code
01
[HGA]
[IGA]
[HGA]
232500
None
Airbus Level I (SDU No. 1) Failure Messages and ATA No.
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
SDU1(105RV1)
SDU1(5RV1)
02
SDU2(105RV2)
SDU2(5RV2) INCOMPATIBILITY
03
UP86308
CMC
Message ID
ATA Number
[IGA]
232834
[HGA]
232834
[IGA]
232834
[HGA]
232834
RESERVED
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-18.
Failure
Code
04
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
HPA1(107RV1)
HPA--HIGAIN(7RV1)
[IGA]
232835
[HGA]
232831
07
HPA--LO GAIN(9RV)
232835
0A
HI POWER RELAY(21RV)
232842
0D
DLNA1(119RV1)
[IGA]
232837
DLNA--TOP(19RV1)
[Top Mount]
232838
DLNA--L(20RV1)
[Conformal]
232837
0F
DLNA--R(20RV2)
[Conformal]
232837
10
DLNA--LO GAIN(14RV)
13
BSU(8RV1)
[Top Mount]
232846
BSU--L(15RV1)
[Conformal]
232844
15
BSU--R(15RV2)
[Conformal]
232844
1A
ANTENNA1(116RV1)
[IGA]
232813
HI GAIN ANTENNA--TOP(16RV1)
[Top Mount]
232813
HI GAIN ANTENNA--L(17RV)
[Conformal]
232812
1C
HI GAIN ANTENNA--R(18RV)
[Conformal]
232812
1F
LO GAIN ANTENNA(13RV)
232811
21
MCDU1(2CA1)
228212
22
MCDU2(2CA2)
228212
23
MCDU3(2CA3)
228212
33
ATSU1(1TX1)
ACARS MU(1RB)
ACARS MU1(1RB1)
34
ATSU2 (1TX2)
ACARS MU2
ACARS MU2(1RB2)
UP86308
ATA Number
232836
[A320/A330/A340 ATSU]
462100
[A320 ACARS]
232434
[A330/A340 ACARS]
232434
[A320/1A330/A340 ATSU]
462100
[A320 ACARS]
[A330/A340 ACARS]
N/A
232434
35
ADIRU1(1FP1)
341234
36
ADIRU2(1FP2)
341234
37
RESERVED
N/A
38
RESERVED
N/A
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-18.
Failure
Code
39
3D
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
CFDIU(1TW)
[A320]
313234
CMC1(1TM1)
[A320/A340]
451334
[A320]
228334
[A330/A340]
228334
[A320]
228334
[A330/A340]
228334
FMGC1(1CA1)
FMGEC1(1CA1)
3E
ATA Number
FMGC2(1CA2)
FMGEC2(1CA2)
40
ARINC 429 ICAO
42
CTU(303RD)
CTU(3RY)
N/A
[A320]
233534
[A330/A340]
239234
43
CPDF
N/A
52
CPDF/SDU1
N/A
53
ATSU1 (1TX1)/SDU1(105RV1)
[IGA A320/A330/A340 ATSU]
462100
[HGA A320/A330/A340 ATSU]
462100
[IGA A320 ACARS]
232434
[IGA A330/A340 ACARS]
232434
[HGA A320 ACARS]
232434
[HGA A330/A340 ACARS]
232434
[IGA A320]
233534
CTU (3RY)/SDU1(105RV1)
[IGA A330/A340]
239234
CTU (303RD)/SDU1(5RV1)
[HGA A320]
233534
[HGA A330/A340]
239234
[IGA]
228212
[HGA]
228212
[IGA]
228212
[HGA]
228212
ATSU1 (1TX1)/SDU1(5RV1)
ACARS MU (1RB)/SDU1(105RV1)
ACARS MU1 (1RB1)/SDU1(105RV1)
ACARS MU (1RB)/SDU1(5RV1)
ACARS MU1 (1RB1)/SDU1(5RV1)
54
CTU (303RD)/SDU1(105RV1)
CTU (3RY)/SDU1(5RV1)
55
MCDU1(2CA1)/SDU1(105RV1)
MCDU1(2CA1)/SDU1(5RV1)
56
MCDU2(2CA2)/SDU1(105RV1)
UP86308
MCDU2(2CA2)/SDU1(5RV1)
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-18.
Failure
Code
57
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
ATSU2 (1TX2)/SDU1(105RV1)
[IGA A320/A330/A340 ATSU]
462100
[HGA A320/A330/A340 ATSU]
462100
[IGA A320 ACARS]
232434
[IGA A330/A340 ACARS]
232434
[HGA A320 ACARS]
232434
[HGA A330/A340 ACARS]
232434
CFDIU(1TW)/SDU1(105RV1)
[IGA A320]
313243
CMC1(1TM1)/SDU1(105RV1)
[IGA A330/A340]
451334
CFDIU(1TW)/SDU1(5RV1)
[HGA A320]
313243
CMC1(1TM1)/SDU1(5RV1)
[HGA A330/A340]
451334
[IGA]
341234
[HGA]
341234
[IGA]
341234
[HGA]
341234
[IGA]
232835
[HGA]
232831
ATSU2 (1TX2)/SDU1(5RV1)
ACARS MU2/SDU1(105RV1)
ACARS MU2 (1RB2)/SDU1(105RV1)
ACARS MU2/SDU1(5RV1)
ACARS MU2 (1RB2)/SDU1(5RV1)
59
5A
ATA Number
ADIRU1(1FP1)/SDU1(105RV1)
ADIRU1(1FP1)/SDU1(5RV1)
5B
ADIRU2(1FP2)/SDU1(105RV1)
ADIRU2(1FP2)/SDU1(5RV1)
5C
HPA1 (107RV1)/SDU1(105RV1)
HPA--HI GAIN(7RV1)/SDU1(5RV1)
5F
HPA--LO GAIN(9RV)/SDU1(5RV1)
232835
62
BSU(8RV1)/SDU1(5RV1)
[Top Mount]
232846
BSU--L(15RV1)/SDU1(5RV1)
[Conformal]
232844
64
BSU--R(15RV2)/SDU1(5RV1)
[Conformal]
232844
66
MCDU3(2CA3)/SDU1(105RV1)
[IGA]
228212
[HGA]
228212
UP86308
MCDU3(2CA3)/SDU1(5RV1)
67
RESERVED
68
RESERVED
6A
RESERVED
6C
RESERVED
6D
RESERVED
6E
RESERVED
6F
RESERVED
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-18.
Failure
Code
71
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
ATA Number
SDU2(105RV2)/SDU1(105RV1)
[IGA]
232834
[HGA]
232834
[IGA A320]
228334
[IGA A330/A340]
228334
[HGA A320]
228334
[HGA A330/A340]
228334
[IGA A320]
228334
[IGA A330/A340]
228334
[HGA A320]
228334
[HGA A330/A340]
228334
[IGA]
232834
[HGA]
232834
SDU2(5RV2)/SDU1(5RV1)
73
FMGC1(1CA1)/SDU1(105RV1)
FMGEC1(1CA1)/SDU1(105RV1)
FMGC1(1CA1)/SDU1(5RV1)
FMGEC1(1CA1)/SDU1(5RV1)
74
FMGC2(1CA2)/SDU1(105RV1)
FMGEC2(1CA2)/SDU1(105RV1)
FMGC2(1CA2)/SDU1(5RV1)
FMGEC2(1CA2)/SDU1(5RV1)
80
RESERVED
82
RESERVED
88
RESERVED
90
SDU1(105RV1) BUS M--CTRL/HPA1(107RV1)
SDU1(5RV1) BUS M--CTRL/HPA--HI
GAIN(7RV1)
96
SDU1(5RV1) BUS M--CTRL/HPA--LO GAIN(9RV)
232834
98
SDU1(5RV1) BUS M--CTRL/BSU(8RV1)
[Top Mount]
232834
SDU1(5RV1) BUS M--CTRL/BSU--L(15RV1)
[Conformal]
232834
9A
BSU--R XTALK/BSU--L
[Conformal]
N/A
9C
SDU1(5RV1) BUS M--CTRL/BSU--R(15RV2)
[Conformal]
232834
9D
BSU--L XTALK/BSU--R
[Conformal]
N/A
C0
WRG:CONFIG PIN PROG/SDU1(105RV1)
C0
WRG:CONFIG PIN PROG/SDU1(5RV1)
C1
LGCIU1(5GA1)/LGCIU2(5GA2)/SDU1(105RV1)
LGCIU1(5GA1)/LGCIU2(5GA2)/SDU1(5RV1)
C2
SDU1(105RV1) SEL--DISABLE
DISCRETE/SDU2(105RV2)
UP86308
SDU1(5RV1) SEL--DISABLE
DISCRETE/SDU2(5RV2)
23--20--27
[IGA]
232834
[HGA]
232834
[IGA]
323171
[HGA]
323171
[IGA]
232834
[HGA]
232834
Page 6--97
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MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-18.
Failure
Code
C3
C4
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
WRG:ICAO ADDRESS PIN
PROG/SDU1(105RV1)
[IGA]
232834
WRG:ICAO ADDRESS PIN
PROG/SDU1(5RV1)
[HGA]
232834
[IGA]
232835
[HGA]
232831
[IGA]
232834
[HGA]
232834
HPA1 (107RV1)/VSWR
HPA--HI GAIN(7RV1)/VSWR
C5
WRG:CONFIG PIN PROG/SDU1(105RV1)
OWNER REQS DB
WRG:CONFIG PIN PROG/SDU1(5RV1)
OWNER REQS DB
C6
HPA--LO GAIN(9RV)/VSWR
C7
HPA(107RV1)/OVER TEMPERATURE
C8
232835
[IGA]
232835
HPA--HI GAIN(7RV1)/OVER TEMPERATURE
[HGA]
232831
SDU1(105RV1)/BAD DATA FROM GROUND
STATION
[IGA]
232834
[HGA]
232834
SDU1(5RV1)/BAD DATA FROM GROUND
EARTH STATION
C9
HPA--LO GAIN(9RV)/OVER TEMPERATURE
232835
CA
SDU1(5RV1)/DLNA--LO GAIN(14RV)
232834
CB
WRG:SDI PIN PROG/HPA1(107RV1)
WRG:SDI PIN PROG/HPA--HI GAIN(7RV1)
CC
WRG:SDI PIN PROG/HPA--LO GAIN(9RV)
CD
DATA:SDU1 POC/TOTC RESET
CE
RESERVED
CF
DATA:HPA1 POC/TOTC RESET
D0
DATA:HPA--LO GAIN POC/TOTC RESET
D1
WRG:SDI PIN PROG/HPA1 (107RV1)
[IGA]
232835
[HGA]
232831
232835
N/A
DATA:HPA--HI GAIN POC/TOTC RESET
[IGA]
N/A
[HGA]
N/A
N/A
WRG:SDI PIN PROG/HPA--HI GAIN(7RV1)
UP86308
ATA Number
[IGA]
232835
[HGA]
232831
D2
WRG:SDI PIN PROG/HPA--LO GAIN(9RV)
232835
D3
WRG:SDI PIN PROG/BSU(8RV1)
[Top Mount]
232846
WRG:SDI PIN PROG/BSU--L(15RV1)
[Conformal]
232844
23--20--27
Page 6--98
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-18.
Failure
Code
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
D4
WRG:SDI PIN PROG/BSU--R(15RV2)
[Conformal]
232844
D5
SDU1(105RV1) COAX/HPA1(107RV1)
[IGA]
232833
[HGA]
232833
SDU1(5RV1) COAX/HPA--HI GAIN (7RV1)
D6
SDU1 (5RV1) COAX/HPA--LO GAIN (9RV)
D7
RESERVED
D8
DLNA1(119RV1)/SDU1(105RV1)
232833
[IGA]
232838
DLNA--TOP(19RV1)/SDU1(5RV1)
[Top Mount]
232838
DLNA--L(20RV1)/SDU1(5RV1)
[Conformal]
232837
D9
DLNA--R(20RV2)/SDU1(5RV1)
[Conformal]
232837
DA
DLNA--LO GAIN(14RV)/SDU1(5RV1)
232836
DB
DLNA--LO GAIN(14RV)/LO GAIN ANTENNA(13RV)
232836
DC
ATSU1(1TX1)/NO ACTIVE ATSU
ACARS MU(1RB)/NO ACTIVE MU
ACARS MU(1RB1/2)/NO ACTIVE MU
DD
[A320/A330/A340 ATSU]
462100
[A320 ACARS]
232434
[A330/A340 ACARS]
232434
SDU1(105RV1) OWNER REQS DB SECURED
PARTITION
SDU1(5RV1) OWNER REQS DB SECURED
PARTITION
DE
SDU1(105RV1) OWNER REQS DS USER
PARTITION
SDU1(5RV1) OWNER REQS DB USER
PARTITION
DF
UP86308
ATA Number
[IGA]
N/A
[HGA]
N/A
[IGA]
N/A
[HGA]
N/A
DLNA--T(19RV1)/BSU(8RV1)/HI GAIN
ANT--TOP(16RV)
[Top Mount]
232838
HI PWR RELAY(21RV)/BSU--L(15RV1)/BSU--R
(15RV2)
[Conformal]
232842
E0
RESERVED
FE
POWER SUPPLY INTERRUPT
240000
23--20--27
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Table 6-19.
Failure
Code
01
Airbus Level I (SDU No. 2) Failure Messages and ATA No.
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
SDU2(105RV2)
SDU2(5RV2)
02
SDU1(105RV1) INCOMPATIBILITY
SDU1(5RV1) INCOMPATIBILITY
03
RESERVED
04
HPA2(107RV2)
HPA--HI GAIN(7RV1)
[IGA]
232834
[HGA]
232834
[IGA]
232834
[HGA]
232834
[IGA]
232835
[HGA]
232831
07
HPA--LO GAIN(9RV)
232835
0A
HI POWER RELAY(21RV)
232842
0D
DLNA2 (119RV2)
[IGA]
232837
DLNA--TOP(19RV1)
[Top Mount]
232838
DLNA--L(20RV1)
[Conformal]
232837
0F
DLNA--R(20RV2)
[Conformal]
232837
10
DLNA--LO GAIN(14RV)
13
BSU(8RV1)
[Top Mount]
232846
BSU--L(15RV1)
[Conformal]
232844
15
BSU--R(15RV2)
[Conformal]
232844
1A
ANTENNA2(116RV2)
[IGA]
232813
HI GAIN ANTENNA--TOP(16RV1)
[Top Mount]
232813
HI GAIN ANTENNA--L(17RV)
[Conformal]
232812
1C
HI GAIN ANTENNA--R(18RV)
[Conformal]
232812
1F
LO GAIN ANTENNA(13RV)
232811
21
MCDU1(2CA1)
228212
22
MCDU2(2CA2)
228212
23
MCDU3(2CA3)
228212
33
ATSU1(1TX1)
ACARS MU(1RB)
ACARS MU1(1RB1)
UP86308
ATA Number
232836
[A320/A330/A340 ATSU]
462100
[A320 ACARS]
232434
[A330/A340 ACARS]
232434
23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
34
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
ATSU2 (1TX2)
ACARS MU2
ACARS MU2(1RB2)
ATA Number
[A320/A330/A340 ATSU]
462100
[A320 ACARS]
232434
[A320/A340 ACARS]
232434
35
ADIRU1(1FP1)
341234
36
ADIRU2(1FP2)
341234
37
RESERVED
N/A
38
RESERVED
N/A
39
CFDIU(1TW)
[A320]
313234
CMC1(1TM1)
[A330/A340]
451334
[A320]
228334
[A330/A340]
228334
[A320]
228334
[A330/A340]
228334
3D
FMGC1(1CA1)
FMGEC1(1CA1)
3E
FMGC2(1CA2)
FMGEC2(1CA2)
40
ARINC 429 ICAO
42
CTU(303RD)
CTU(3RY)
N/A
[A320]
233534
[A330/A340]
239234
43
CPDF
N/A
52
CPDF/SDU1
N/A
53
ATSU1 (1TX1)/SDU2(105RV2)
[IGA A320/A330/A340 ATSU]
462100
[HGA A320/A330/A340 ATSU]
462100
[IGA A320 ACARS]
232434
[IGA A330/A340 ACARS]
232434
[HGA A320 ACARS]
232434
[HGA A330/A340 ACARS]
232434
[IGA A320]
233534
CTU(3RY)/SDU2(105RV2)
[IGA A330/A340]
239234
CTU(303RD)/SDU2(5RV2)
[HGA A320]
233534
[HGA A330/A340]
239234
[IGA]
228212
[HGA]
228212
ATSU1 (1TX1)/SDU2(5RV2)
ACARS MU(1RB)/SDU2(105RV2)
ACARS MU1(1RB1)/SDU2(105RV2)
ACARS MU(1RB)/SDU2(5RV2)
ACARS MU1(1RB1)/SDU2(5RV2)
54
CTU(303RD)/SDU2(105RV2)
CTU(3RY)/SDU2(5RV2)
55
MCDU1(2CA1)/SDU2(105RV2)
UP86308
MCDU1(2CA1)/SDU2(5RV2)
23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
56
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
ATA Number
MCDU2(2CA2)/SDU2(105RV2)
[IGA]
228212
[HGA]
228212
[IGA A320/A330/A340 ATSU]
462100
[HGA A320/A330/A340 ATSU]
462100
[IGA A320 ACARS]
232434
[IGA A330/A340 ACARS]
232434
[HGA A320 ACARS]
232434
[HGA A330/A340 ACARS]
232434
CFDIU(1TW)/SDU2(105RV2)
[IGA A320]
313234
CMC1(1TM1)/SDU2(105RV2)
[IGA A330/A340]
451334
CFDIU(1TW)/SDU2(5RV2)
[HGA A320]
313234
CMC1(1TM1)/SDU2(5RV2)
[HGA A330/A340]
451334
[IGA]
341234
[HGA]
341234
[IGA]
341234
[HGA]
341234
[IGA]
232835
[HGA]
232831
MCDU2(2CA2)/SDU2(5RV2)
57
ATSU2 (1TX2)/SDU2(105RV2)
ATSU2 (1TX2)/SDU2(5RV2)
ACARS MU2/SDU2(105RV2)
ACARS MU2 (1RB2)/SDU2(105RV2)
ACARS MU2/SDU2(5RV2)
ACARS MU2(1RB2)/SDU2(5RV2)
59
5A
ADIRU1(1FP1)/SDU2(105RV2)
ADIRU1(1FP1)/SDU2(5RV2)
5B
ADIRU2(1FP2)/SDU2(105RV2)
ADIRU2(1FP2)/SDU2(5RV2)
5C
HPA2(107RV2)/SDU2(105RV2)
HPA--HI GAIN(7RV1)/SDU2(5RV2)
5F
HPA--LO GAIN(9RV)/SDU2(5RV2)
232835
62
BSU(8RV1)/SDU2(5RV2)
[Top Mount]
232846
BSU--L(15RV1)/SDU2(5RV2)
[Conformal]
232844
64
BSU--R(15RV2)/SDU2(5RV2)
[Conformal]
232844
66
MCDU3(2CA3)/SDU2(105RV2)
[IGA]
228212
[HGA]
228212
UP86308
MCDU3(2CA3)/SDU2(5RV2)
67
RESERVED
68
RESERVED
6A
RESERVED
6C
RESERVED
6D
RESERVED
23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
6E
RESERVED
6F
RESERVED
71
SDU1(105RV1)/SDU2(105RV2)
ATA Number
[IGA]
232834
[HGA]
232834
[IGA A320]
228334
[IGA A330/A340]
228334
[HGA A320]
228334
[HGA A330/A340]
228334
[IGA A320]
228334
[IGA A330/A340]
228334
[HGA A320]
228334
[HGA A330/A340]
228334
[IGA]
232834
[HGA]
232834
SDU1(5RV1)/SDU2(5RV2)
73
FMGC1(1CA1)/SDU2(105RV2)
FMGEC1(1CA1)/SDU2(105RV2)
FMGC1(1CA1)/SDU2(5RV2)
FMGEC1(1CA1)/SDU2(5RV2)
74
FMGC2(1CA2)/SDU2(105RV2)
FMGEC2(1CA2)/SDU2(105RV2)
FMGC2(1CA2)/SDU2(5RV2)
FMGEC2(1CA2)/SDU2(5RV2)
80
RESERVED
82
RESERVED
88
RESERVED
90
SDU2(105RV2) BUS M--CTRL/HPA2(107RV2)
SDU2(5RV2) BUS M--CTRL/HPA--HI
GAIN(7RV1)
96
SDU2(5RV2) BUS M--CTRL/HPA--LO GAIN(9RV)
232834
98
SDU2(5RV2) BUS M--CTRL/BSU(8RV1)
[Top Mount]
232834
SDU2(5RV2) BUS M--CTRL/BSU--L(15RV1)
[Conformal]
232834
9A
BSU--R XTALK/BSU--L
[Conformal]
N/A
9C
SDU2(5RV2) BUS M--CTRL/BSU--R(15RV2)
[Conformal]
232834
9D
NBSU--L XTALK/BSU--R
[Conformal]
N/A
C0
WRG:CONFIG PIN PROG/SDU2(105RV2)
WRG:CONFIG PIN PROG/SDU2(5RV2)
C1
LGCIU1(5GA1)/LGCIU2(5GA2)/SDU2(105RV2)
UP86308
LGCIU1(5GA1)/LGCIU2(5GA2)/SDU2(5RV2)
23--20--27
[IGA]
232834
[HGA]
232834
[IGA]
323171
[HGA]
323171
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
C2
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
SDU2(105RV2) SEL--DISABLE
DISCRETE/SDU1(105RV1)
[IGA]
232834
[HGA]
232834
WRG:ICAO ADDRESS PIN PROG/
SDU2(105RV2)
[IGA]
232834
WRG:ICAO ADDRESS PIN PROG/
SDU2(5RV2)
[HGA]
232834
[IGA]
232835
[HGA]
232831
[IGA]
232834
[HGA]
232834
SDU2(5RV2) SELECT--DISABLE
DISCRETE/SDU1(5RV1)
C3
C4
HPA2(107RV2)/VSWR
HPA--HI GAIN(7RV1)/VSWR
C5
WRG:CONFIG PIN PROG/SDU2(105RV2)
OWNER REQS DB
WRG:CONFIG PIN PROG/SDU2(5RV2)
OWNER REQS DB
C6
LPA--LO GAIN(9RV)/VSWR
C7
HPA--HI GAIN(107RV2)/OVER
TEMPERATURE
C8
232835
[IGA]
232835
HPA--HI GAIN(7RV1)/OVER TEMPERATURE
[HGA]
232831
SDU2(105RV2)/BAD DATA FROM GROUND
STATION
[IGA]
232834
[HGA]
232834
SDU2(5RV2)/BAD DATA FROM GROUND
EARTH STATION
C9
HPA--LO GAIN(9RV)/OVER TEMPERATURE
232835
CA
SDU2(5RV2)/DLNA--LO GAIN(14RV)
232834
CB
WRG:SDI PIN PROG/HPA2(107RV1)
WRG:SDI PIN PROG/HPA--HI GAIN(7RV1)
CC
WRG:SDI PIN PROG/HPA--LO GAIN(9RV)
CD
DATA:SDU1 POC/TOTC RESET
CE
RESERVED
CF
DATA:HPA2 POC/TOTC RESET
D0
[IGA]
232835
[HGA]
232831
232835
N/A
DATA:HPA--HI GAIN POC/TOTC RESET
UP86308
ATA Number
DATA:HPA--LO GAIN POC/TOTC RESET
[IGA]
N/A
[HGA]
N/A
N/A
23--20--27
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
D1
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
WRG:SDI PIN PROG/HPA2(107RV2)
WRG:SDI PIN PROG/HPA--HI GAIN(7RV1)
[IGA]
232835
[HGA]
232831
D2
WRG:SDI PIN PROG/HPA--LO GAIN(9RV)
232835
D3
WRG:SDI PIN PROG/BSU(8RV1)
[Top Mount]
232846
WRG:SDI PIN PROG/BSU--L(15RV1)
[Conformal]
232844
D4
WRG:SDI PIN PROG/BSU--R(15RV2)
[Conformal]
232844
D5
SDU2(105RV2) COAX/HPA2(107RV2)
[IGA]
232833
[HGA]
232833
SDU2(105RV2) COAX/HPA--HI GAIN(7RV1)
D6
SDU2(105RV2) COAX/HPA--LO GAIN(9RV)
D7
RESERVED
D8
DLNA2(119RV2)/SDU2(105RV2)
[IGA Top Mount]
232838
DLNA--TOP(19RV1)/SDU2(5RV2)
[HGA Top Mount]
232838
DLNA--L(20RV1)/SDU2(5RV2)
[Conformal]
232837
D9
DLNA--R(20RV2)/SDU2(5RV2)
[Conformal]
232837
DA
DLNA--LO GAIN(14RV)/SDU2(5RV2)
232836
DB
DLNA--LO GAIN(14RV)/LO GAIN ANTENNA(13RV)
232836
DC
ATSU1 (1TX1)/ NO ACTIVE ATSU
ACARS MU(1RB)/ NO ACTIVE MU
ACARS MU(1RB1/2) NO ACTIVE MU
DD
232833
[A320/A330/A340 ATSU]
462100
[A320 ACARS]
232434
[A330/A340 ACARS]
232434
SDU2 (105RV2) OWNER REQS DB SECURED
PORTITION
SDU2 (5RV2) OWNER REQS DB SECURED
PORTITION
DE
SDU2 (105RV2) OWNER REQS DB USER
PORTITION
SDU2 (5RV2) OWNER REQS DB USER
PORTITION
DF
UP86308
ATA Number
[IGA]
N/A
[HGA]
N/A
[IGA]
N/A
[HGA]
N/A
DLNA--T(19RV1)/BSU(8RV1)/HI GAIN
ANT--TOP(16RV)
[Top Mount]
232838
HI PWR RELAY(21RV)/BSU--L
(15RV1)/BSU--R(15RV2)
[Conformal]
232842
23--20--27
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
E0
RESERVED
FE
POWER SUPPLY INTERRUPT
Table 6-20.
UP86308
Failure
Code
ATA Number
240000
McDonnell Douglas Level I Failures Messages and
ATA Reference Numbers
CFDS Normal and Interactive Modes
ATA Number
01
SDU
232610
02
OTHER SDU INCOMPATIBILITY
232611
03
RESERVED
04
HPA--IN GAIN
[IGA]
232600
HPA--HI GAIN
[HGA]
232613
07
HPA--LO GAIN
232614
0A
HI POWER RELAY
232615
0D
DLNA--(TOP/L)
232616
0F
DLNA--R
232618
10
DLNA--LO GAIN
232619
13
BSU--(TOP/L)
23261B
15
BSU--R
23261C
1A
IN GAIN ANTENNA--TOP
[IGA]
232600
HI GAIN ANTENNA--(TOP/L)
[HGA]
23261D
1C
HI GAIN ANTENNA--R
23261F
1F
LO GAIN ANTENNA
232620
21
MCDU1
232635
22
MCDU2
232636
23
MCDU3
232637
33
(ACARS MU/CMU)
23243C
34
(ACARS MU/CMU)2
N/A
35
(IRS/ADIRU)--PRI
23263E
36
(IRS/ADIRU)--SEC
23263F
23--20--27
Page 6--106
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Table 6-20.
UP86308
Failure
Code
McDonnell Douglas Level I Failures Messages and
ATA Reference Numbers (cont)
CFDS Normal and Interactive Modes
ATA Number
37
RESERVED
38
RESERVED
39
CFDIU
454500
3D
(FMC/VIA)1
232642
3E
(FMC/VIA)2
232643
40
ARINC 429 ICAO ADDRESS
42
CTU
43
(CFS/CPDF)
TBD
52
(CFS/CPDF)/SDU
TBD
53
(ACARS MU/CMU)/SDU
23263C
54
CTU/SDU
232644
55
MCDU1/SDU
232635
56
MCDU2/SDU
232636
57
(ACARS MU/CMU)2/SDU
59
CFDIU/SDU
232641
5A
(IRS/ADIRU)--PRI/SDU
23263E
5B
(IRS/ADIRU)--SEC/SDU
23263F
5C
HPA--IN GAIN/SDU
[IGA]
232600
HPA--HI GAIN/SDU
[HGA]
232600
N/A
232644
N/A
5F
HPA--LO GAIN/SDU
232623
62
BSU--(TOP/L)/SDU
232626
64
BSU--R/SDU
232627
66
MCDU3/SDU
232637
67
RESERVED
68
RESERVED
6A
RESERVED
6C
RESERVED
6D
RESERVED
23--20--27
Page 6--107
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Table 6-20.
UP86308
Failure
Code
McDonnell Douglas Level I Failures Messages and
ATA Reference Numbers (cont)
CFDS Normal and Interactive Modes
ATA Number
6E
RESERVED
6F
RESERVED
71
OTHER SDU/THIS SDU
232600
73
(FMC/VIA)1/SDU
232642
74
(FMC/VIA)2/SDU
232643
80
RESERVED
82
RESERVED
88
RESERVED
90
SDU M--CTRL/HPA--IN GAIN
[IGA]
232600
SDU M--CTRL/HPA--HI GAIN
[HGA]
232600
96
SDU M--CTRL/HPA--LO GAIN
23262D
98
SDU M--CTRL/BSU--(TOP/L)
232600
9A
BSU--R XTALK/BSU--L
232600
9C
SDU M--CTRL/BSU--R
232630
9D
BSU--L XTALK/BSU--R
232600
C0
WRG:CONFIG PIN PROG/SDU
232600
C1
SDU WOW MISCOMPARE
C2
SDU/OTHER SDU SELECT--DISABLE DISCRETE
232600
C3
WRG:ICAO ADDRESS PIN PROG/SDU
232631
C4
TX PATH VSWR--IN GAIN
[IGA]
232600
TX PATH VSWR--HI GAIN
[HGA]
232600
N/A
C5
WRG:CONFIG PIN PROG/SDU OWNER REQS
232600
C6
TX PATH VSWR--LO GAIN
232600
C7
HPA--IN GAIN/OVER TEMPERATURE
[IGA]
232600
HPA--HI GAIN/OVER TEMPERATURE
[HGA]
23262C
C8
BAD DATA FROM GROUND EARTH STATION
None
C9
HPA--LO GAIN/OVER TEMPERATURE
232634
CA
SDU/DLNA--LO GAIN
232619
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table 6-20.
Failure
Code
UP86308
CB
McDonnell Douglas Level I Failures Messages and
ATA Reference Numbers (cont)
CFDS Normal and Interactive Modes
ATA Number
WRG:SDI PIN PROG/HPA--IN GAIN
[IGA]
232600
WRG:SDI PIN PROG/HPA--HI GAIN
[HGA]
232600
CC
WRG:SDI PIN PROG/HPA--LO GAIN
232600
CD
SDU (POC/TOTC) DATA RESET
CE
RESERVED
CF
HPA--IN GAIN (POC/TOTC) DATA RESET
[IGA]
None
HPA--HI GAIN (POC/TOTC) DATA RESET
[HGA]
None
None
D0
HPA--LO GAIN (POC/TOTC)
None
D1
WRG:SDI PIN PROG/HPA--IN GAIN
[IGA]
232600
WRG:SDI PIN PROG/HPA--HI GAIN
[HGA]
232600
D2
WRG:SDI PIN PROG/HPA--LO GAIN
232600
D3
WRG:SDI PIN PROG/BSU--(TOP/L)
232600
D4
WRG:SDI PIN PROG/BSU--R
232600
D5
SDU COAX/HPA--IN GAIN
[IGA]
232600
SDU COAX/HPA--HI GAIN
[HGA]
232600
D6
SDU COAX/HPA--LO GAIN
D7
RESERVED
D8
DLNA/(SDU)--(TOP/L)
232600
D9
DLNA/(SDU)--R
232600
DA
DLNA/(SDU)--LO GAIN
232600
DB
LO GAIN SUBSYSTEM
232600
DC
NO ACTIVE ACARS MU/CMU
232400
DD
SDU OWNER REQS -- SECURED
None
DE
SDU OWNER REQS -- USER
None
DF
IN GAIN SUBSYSTEM
[IGA]
232600
HI GAIN SUBSYSTEM
[HGA]
232600
E0
RESERVED
FE
POWER SUPPLY INTERRUPT
232600
None
23--20--27
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4. SCDU for Dual SATCOM
A. General
(1) The SDU supports SCDU page displays for dual systems. All pages are as specified
in paragraph 2.D. (SCDU pages) with the following exceptions.
B. SATCOM Logical Channels
(1) The SATCOM channels for HEADSET calls in a dual system can be supplied by
several combinations of physical channels within both SDUs. These combinations are
determined by the configuration strap settings for cockpit wiring and ORT items
regarding the use of SDU channel resources (items vi, vii, and xlviii). The display of
channel status and selections as reported on menus MAIN, DIRECTORY, and
CATEGORY-n reflect the logical channel status.
C. SATCOM MAIN MENU (Cross-Talk Bus Failed)
(1) The SDU designated as the slave unit in a dual system must receive most of the
system status information from the master over the SDU cross-talk bus. If full
communication is not established, the slave unit cannot receive the necessary data
for the display pages. The default SATCOM MAIN MENU display page THIS UNIT
UNAVAILABLE is displayed in this case.
D. SATCOM CHANNEL STATUS
(1) The channel status page reflects the physical channels within the SDU that is
providing the display page.
E.
SATCOM MAINTENANCE Menus
(1) The maintenance menus reflect the maintenance data for the SATCOM system that
is providing the display page.
5. Maintenance Panel Assembly
A. General
(1) The maintenance panel assembly interface diagram (Figure 5-17) supplies remote
monitoring of MCS system operation. The maintenance panel assembly is made up
of two parts: the cabin telecommunications (CTM) panel and the Commissioning and
Maintenance Terminal (CMT) panel. The CTM panel is used for monitoring the cabin
telecommunications equipment. The panel contains six lamps to indicate the
availability of the telephone handsets. A keyed on/off switch arms the system when
the key is turned to the ON position.
UP86308
(2) The CMT panel is used primarily to debug, detect, isolate software and/or hardware
integration, LRU and system integration, formal testing, and system access approval,
as well as general performance analysis. The CMT data connector supplies an
access port for a commissioning and maintenance terminal that can be a personal
computer, a dumb terminal, or a modem. The SDU interface connector on the panel
supplies a remote access port for testing the SDU. The panel also contains lamps to
indicate the status of the MCS system. These lamps are defined in Table 6-21.
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Table 6-21.
UP86308
Lamp
Commissioning and Maintenance Terminal Panel Lamps
Definition
IN USE CH--1
(SDU pin TPH1) This lamp lights to show channel 1 is in use.
IN USE CH--2
(SDU pin TPK1) This lamp lights to show channel 2 is in use.
PILOT VCE NOT AVAIL
(SDU pin TP3A) This lamp lights to show no additional voice channels can be
established. This can be because no resources are available, or all available
resources being allocated to existing calls.
LOG OFF
(SDU pin TPC3) This lamp lights to show no packet mode data service
capability exists at any data rate; system not logged on.
CABIN VCE NOT AVAIL
(SDU pin TPB3) This lamp lights to show no additional channels can be
established for analog or digital cabin voice, or circuit--mode data. This can be
because no resources are available, or all available resources being allocated
to existing calls.
MCS FAIL
(SDU pin TPG1) This lamp lights to show a total loss of all SATCOM voice and
data services, and at least one cause can be attributable to the MCS system
LRUs themselves. Replacement of the appropriate LRU (SDU, HPA) is
necessary to restore partial or complete service. It is possible for this indicator
and the MCS inoperable indicator (NON-MCS FAIL) to be active
simultaneously, indicating failure in both the MCS system LRUs and nonsystem
LRUs.
NON-MCS FAIL
(SDU pin TPE3) This lamp lights to show total loss of all SATCOM voice and
data services, and at least one cause is attributable to the non-MCS system
LRUs, or interfaces to those LRUs. Replacement of the appropriate non MCS
LRU(s), or correction of the interface failure is necessary to restore partial or
complete service. It is possible for this indicator and the SATCOM fail indicator
(MCS FAIL) to be active simultaneously, indicating failure in both the MCS
system LRUs and the nonsystem LRUs or interfaces.
NO SAT LINK
(SDU pin TPJ1) This lamp lights to show no SATCOM voice or data services
are available because of the AES not being successfully logged-on, and the
cause is definitely not due to reported failures (MCS or non-MCS). If there is a
MCS or non-MCS failure, the NO SAT LINK lamp will not light.
HGA FAIL
(SDU pin TPD3) This lamp lights to show packet-mode data service capability
exists, but only at the lowest channel rates (600 and 1200 bps). This indicator
is assumed to only be present in high gain antennas installations that have a
low gain antenna backup system. The lamp indicates an HGA failure due to the
reduction from normal high speed capability.
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UP86308
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SECTION 7
MAINTENANCE PRACTICES
1. Overview
A. General
(1) This section supplies instructions for removing, reinstalling, and adjusting each LRU
of the MCS that has been installed by the aircraft manufacturer or completion center.
Where applicable, instructions for replacing lamps, knobs, and set screws are
included. Adjustment information is called out as required.
CAUTION: SHOULD ANY INSTALLATION CRITICAL CASES ARISE WITH THE
REINSTALLATION OF ANY UNIT, YOU MUST COMPLY 100 PERCENT
WITH THE INSTRUCTION.
CAUTION: TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFT POWER OFF
WHEN REMOVING OR INSTALLING LRUS.
2. Equipment and Materials
A. General
WARNING: BEFORE YOU USE A MATERIAL, KNOW THE HAZARD CODE AND GET THE
NECESSARY PROTECTION. REFER TO THE PAGE ABOUT HAZARD CODES
FOR MATERIALS IN THE FRONT OF THIS MANUAL.
(1) Maintenance materials identified with a Honeywell Material Number (HMN) are given
in Table 7-1.
(2) No additional special equipment or materials other than those commonly used in the
shop are required to install the units in existing trays and clamps, and to adjust the
system. Do not over tighten mounting screws. Where torque values are not given, it
is acceptable to finger tighten the mounting screws.
Table 7-1.
Item
Materials
Description
Source
HMN 97P5778
RTV silicone, No. 3145,
translucent, per MIL--A--46146,
Group II, Type I military
designation M4614621XTN.
Dow Corning Corp, Midland, MI
(05AJ8)
HMN 98C0978
Sealant, corrosion inhibitive
(MIL--S--81733, Type II--1/2 -- for
extrusion application in the time of
1/2 hour) — Pro--Seal 870B--1/2
Courtaulds Aerospace, Glendale,
CA (83574)
UP86308
NOTES: NOTES:
1.
Equivalent alternatives are permitted for materials in this list.
2.
The HMN codes in the list of materials identify the Honeywell Material Number (HMN) given to each material.
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3. Procedure for Antennas
A. General
(1) The following paragraphs describe general information when removing or installing
antennas.
NOTE: For all antennas not supplied by Honeywell, removal and installation should
be done according to installation instructions from the manufacturer.
B. Antenna Weather Protection
(1) Some antennas require gaskets and others have O--rings. When reinstalling
antennas, new gaskets or O--rings should be used.
(2) A weather sealant should be applied around the periphery of the antenna base to
prevent seepage of water and condensation and preclude corrosion. If a sealant or
aerodynamic smoother is used around the periphery of the antenna base, it should
be applied after the antenna has been bolted down. The sealant used should be
nonadhering so the antenna can be removed at a later time, if necessary. Chromatic
tape is recommended.
NOTE: When mounting antennas on a pressurized fuselage, a leveling and sealing
compound like Pro-Seal 870B--1/2 should be used between the entire
mounting surface of the antenna and the fuselage. Use of this compound, in
addition to the installation gasket, compensates for surface irregularities and
voids between the antenna and the fuselage. A mold releasing agent can be
used on the fuselage prior to installation to prevent the leveling compound
from adhering to the fuselage.
(3) To prevent water seepage on top mounted antennas, it can be necessary to apply
Silastic sealant (RTV--3145 or equivalent) to the mounting screw heads.
C. Antenna Hardware
(1) Clean the airframe at the antenna mounting area to remove any foreign material.
(2) Because of the insulation qualities of gaskets and leveling compounds, the mounting
screws are required to supply the electrical bonding between the antennas and the
aircraft (typically 15 milliohms or less is required). The technician doing the
reinstallation must be sure any hardware being reused is clean and free of corrosion.
If in doubt, use new hardware.
UP86308
(3) Gaskets and O--rings deform during initial installation. While it is possible to reuse
gaskets and O--rings, it is highly recommended new gaskets or O--rings be used.
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D. General Antenna Removal Instructions
NOTE: These procedures apply to all antennas. To prevent damage to the
antennas, do not apply pressure to the plastic housings or pry on plastic
housings.
(1) Pull the appropriate circuit breakers.
(2) After removing and saving the hardware, cut the bond line of any installer--applied
sealant between the antenna and the aircraft skin.
(3) Pull the antenna away from the aircraft skin far enough to disconnect the cable
connector(s).
4. Procedure for the LRUs
CAUTION: BEFORE AN LRU IS INSTALLED OR REMOVED, PULL THE CIRCUIT
BREAKERS THAT SUPPLY POWER TO THE LRU TO REMOVE POWER.
CAUTION: MOISTURE AND DIRT CAUSE DAMAGE TO LRUs.
CAUTION: LRU FAILURE RATES INCREASE WITH A RISE IN TEMPERATURE. INSTALL
THE LRUs WITH CLEARANCE; LET THE AIR FLOW ON TOP AND BOTTOM
OF LRUS TO PREVENT OVERHEATING.
A. LRU Removal
(1) Remove an LRU as follows:
(a) Disconnect the circuit breakers that supply power to the LRU.
(b) Tag the circuit breakers with DO-NOT-OPERATE identifiers.
(c) Loosen the clamp knobs and let them drop out of the way.
(d) Pull the LRU forward a minimum of 1/2 inch to clear the rear connector pins.
(e) Lift the LRU free of the cooling air-duct gasket on the mounting rack.
B. LRU Installation
(1) Install an LRU as follows:
(a) Determine the location of each LRU in the aircraft.
(b) Check the LRU to be installed and make sure all connector pins are straight and
ready for connection.
UP86308
(c) Make sure the index pin coding on the rear connector is correct for the mating
connector.
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(d) Place the LRU in the appropriate mounting rack and align the connectors. Push
the LRU back to make contact with the connector pins. Push the LRU into place
and rock the LRU sideways slightly.
CAUTION: DO NOT OVER TIGHTEN THE CLAMP. EXCESSIVE TORQUE CAN
CAUSE BRACKETS AND CONNECTORS TO WARP AND BEND.
(e) Put the hold-down clamps in place and tighten the knobs finger-tight.
5. Owner Requirements Table Uploading
A. General
UP86308
(1) When the SDU is replaced, the ORT needs to be uploaded before normal operation
can begin. Refer to SYSTEM OPERATION, for the ORT uploading procedure.
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6. Instructions for Continued Airworthiness, FAR 25.1529
A. General
(1) Maintenance requirements and instructions for continued airworthiness of the MCS
components are contained in the paragraphs that follow.
(2) Installation of the MCS on an aircraft by supplemental type certificate or Form 337
obligates the aircraft operator to include the maintenance information supplied by this
manual in the operator’s Aircraft Maintenance Manual and the operator’s Aircraft
Scheduled Maintenance Program.
(a) Maintenance information for the MCS (system description, removal, installation,
testing, etc.) is contained in this manual.
(b) LRU part numbers and other necessary part numbers contained in this manual
should be placed into the aircraft operator’s appropriate aircraft illustrated parts
catalog (IPC).
(c) Wiring diagram information contained in this manual should be placed into the
aircraft operator’s appropriate aircraft Wiring Diagram Manuals.
(d) The MCS system components are considered on--condition units and no
additional maintenance is required other than a check for security and operation
at normal inspection intervals.
(e) If a system component is inoperative, remove unit, secure cables and wiring,
collar applicable switches and circuit breakers, and placard them inoperative.
Revise equipment list and weight and balance as applicable prior to flight and
make a log book entry that unit was removed (refer to section 91.213 of the FAR
or the aircraft’s minimum equipment list (MEL).
(f)
The MCS components can be repaired at a factory authorized repair center or an
appropriately rated FAA Part 145 repair station.
(g) Once repaired, reinstall the LRU in the aircraft in accordance with the original
Form 337 approved data or instructions in this manual. Do a Return to Service
test of the system and approve it for return to service with a log book entry
required by section 43.9.
(h) Scheduled maintenance program tasks to be added to the aircraft operator’s
appropriate aircraft maintenance program are as follows:
Recommended periodic scheduled servicing tasks: None required.
Recommended periodic inspections: None required.
NOTE: The (applicable LRUs) used with this system have test and
inspections that are required by FAR 91.413 to be completed every
24 calender months.
UP86308
Recommended periodic scheduled preventative maintenance tests (Tests to
determine system condition and/or latent failures): None required.
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UP86308
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APPENDIX A
VENDOR EQUIPMENT
1. Overview
A. General
(1) Appendix A contains information on vendor-manufactured equipment that can be
installed on an aircraft configured for MCS system. Installation of this equipment
depends on the specific requirements of the operator. Therefore, information in this
section is supplied as a courtesy to the MCS equipment operators.
2. Electronic Cable Specialists
A. General
(1) This paragraph contains information on how to select installation provisions offered
by electronic cable specialists (ECS) for the Honeywell MCS--4000/7000 system.
ECS designs and manufactures the installation provisions described here and can
supply either individual components or complete installation kits. The address for
Electronic Cable Specialists is as follows:
Electronic Cable Specialists
5300 W. Franklin Drive
Franklin, WI 53132
U.S.A.
Telephone: (414) 421--5300
FAX: (414) 421--5301
B. Radio Frequency Components
(1) All RF components (cable, connectors, and attenuators) supplied to interface the
SATCOM Avionics and Antenna Subsystems have been designed to meet the strict
usage and attenuation requirements of the Honeywell MCS--4000/7000 system and
ARINC 741/761. A selected list of RF components offered by ECS for SATCOM
installations is shown in Table A--1 and Table A--2.
C. Cable Assembly Fabrication
(1) ECS fabricates cable assemblies guaranteed to meet SATCOM system requirements
and ARINC 741 specifications.
• Each cable assembly is fabricated with an individual part number, which is
permanently affixed to each end of the assembly.
UP86308
• Each set of cable assemblies is assigned a serial number, which is printed on the
part number label. Serialization makes sure each cable assembly is traceable and
repeatable.
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Table A--1.
ECS Cable Part No.
ECS Cables and Connectors
310801
310201
311501
311601
311901
3C142B*
4.7
6.9
8.7
10.7
15.5
18.4
0.45 in.
0.32 in.
0.245 in.
0.23 in.
0.195 in.
0.195 in.
15.0
8.6
5.2
5.0
4.3
5.0
Male TNC 180°
CTS022
CTS122
CTS922
CTS922
CTS722
CTS722
Male TNC 90°
CTR022
CTR122
CTR922
CTR922
CTR722
CTR722
Male N 180°
CNS022
CNS122
CNS922
CNS922
CNS722
CNS722
Male N 90°
CNR022
CNR122
CNR922
CNR922
CNR722
CNR722
Female N 180°
FNS022
FNS122
FNS922
FNS922
FNS722
FNS722
ARINC 600 Size 1
L0122
L1122
L9122
L9122
L7122
L7122
ARINC 600 Size 5
N/A
N/A
A650922
A650922
Nominal Attenuation
@ 1.6 GHz (dB/100 ft)
Overall Diameter
Pounds/100 ft
Table A--2.
225791--2 225791--2
ECS Attenuators
Attenuator (Transmit Path)
Attenuator (Receive Path)
Fixed or Variable
Fixed or Variable
D. Cable Assembly Testing
(1) Testing is done on Hewlett-Packard 8753 network analyzers to verify insertion loss
and VSWR. The results become part of a test database and are shipped with each
cable assembly. Each cable assembly is tested across the SATCOM system
frequency bandwidth (1530 MHz to 1660.5 MHz). Received path cable assemblies
are test swept from 1530 MHz to 1559 MHz. Customers have the option of having
cable assemblies tested with or without attenuators.
E.
ARINC 600 Connectors
(1) ECS supplies ARINC 600 connectors for ARINC 741 style avionic electrical
interfaces. The SATCOM rack-side connectors (Figure A--1) are described in this
paragraph. Connector part numbers are:
• HPA -- NIC66H20A00AA0
• SDU -- NIC66H21A00AA0
• SCU/BSU -- NIC66F11A00AA0.
UP86308
(2) ECS supplies ARINC 600 Size 1 coaxial connectors with the requisite termination kit
and assembly instructions (Figure A--2).
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Figure A--1.
UP86308
Figure A--2.
ARINC Connectors
ARINC Assembly
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F.
SATCOM Avionics Unit Mounting Hardware
(1) SATCOM avionics mounting hardware is made up of the HPA, SDU, and SCU and
will be mounted in ARINC 600 style tray assemblies. The HPA and SDU each require
forced air cooling during normal operation, whereas the SCU can function properly
with convection cooling alone. Refer to MECHANICAL INSTALLATION, for LRU
cooling requirements.
G. SATCOM Hardware Component Kits
(1) This paragraph contains information on how to select SATCOM hardware component
kits offered by ECS for the Honeywell MCS--4000/7000 avionic units in Table A--3
thru Table A--6. ECS supplies several options for each kit to accommodate the variety
of mounting requirements specific to each aircraft installation. ECS tray assemblies
come with and without independent cooling systems to ensure installation flexibility.
(2) The tray assemblies have been specially designed to meet Honeywell and ARINC
600 LRU cooling requirements. Tray assemblies are supplied with insertion/extraction
front hold-downs as standard, but are available with other front hold-down options.
For tray assembly dimensions refer to Figure A--3.
UP86308
(3) The hardware component kits for the HPAs, SDU, and BSU are listed in Table A--3
thru Table A--6, respectively.
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UP86308
Figure A--3.
Dimensions for ECS Tray Assemblies
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Table A--3.
Kit Part No. *
HP--600 HPA (40W) Hardware Component Kit,
Part No. 998HQS--900--1XX
Item Part Number
Quantity
998HQS--900--102
6292--101
8 MCU S/S standard tray
998HQS--900--103
6288--101
8 MCU S/S tray w/bottom
fan
998HQS--900--104
6290--101
8 MCU S/S tray w/left side
fan
998HQS--900--106
6284--101
8 MCU S/S tray w/right side
fan
998HQS--900--107
6286--101
8 MCU S/L standard tray
* Parts supplied with each kit NIC66H20A00AA0
Table A--4.
Kit Part No. *
HPA ARINC connector
22 AWG pins
20 AWG sockets
16 AWG sockets
12 AWG sockets
Size 5 coaxicons
140
HP--700 HPA (20W) Hardware Component Kit,
Part No. 998HQS--904--1XX
Item Part Number
Description
Quantity
998HQS--904--102
6280--101
4 MCU S/S standard tray
998HQS--904--103
6278--101
4 MCU S/S tray w/bottom
fan
998HQS--904--104
6279--101
4 MCU S/S tray w/left side
fan
998HQS--904--106
6302--101
4 MCU S/S tray w/right side
fan
998HQS--904--107
6277--101
4 MCU S/L standard tray
* Parts supplied with each kit NIC66H20A00AA0
UP86308
Description
HPA ARINC connector
22 AWG pins
20 AWG sockets
16 AWG sockets
12 AWG sockets
Size 5 coaxicons
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Table A--5.
SD--700 SDU Hardware Component Kit, Part No. XXXXXX--XXX--1XX
Kit Part No. *
Item Part Number
Description
Quantity
998HQS--901--102
6283--101
6 MCU S/S standard tray
998HQS--901--103
6232--101
6 MCU S/S tray w/bottom
fan
998HQS--901--104
6282--101
6 MCU S/S tray w/left side
fan
998HQS--901--106
6045--109
6 MCU S/S tray w/right side
fan
998HQS--901--107
6281--101
6 MCU S/L standard tray
* Parts supplied with each kit NIC66H21A00AA0
Table A--6.
Kit Part No. *
SDU ARINC connector
22 AWG pins
20 AWG sockets
16 AWG sockets
12 AWG sockets
Size 5 coaxicons
300
BSU Hardware Component Kit, Part No. 970HQS--903--1XX
Item Part Number
Description
Quantity
970HQS--903--101
6064--101
2 MCU S/S standard tray
970HQS--903--102
6074--101
2 MCU S/S flat bottom tray
970HQS--903--103
6051--101
2 MCU S/L standard tray
970HQS--903--104
6120--101
2 MCU S/L flat bottom tray
* Parts supplied with each kit NIC66F11A00AA0
SCU/BSU ARINC connector
22 AWG pins
16 AWG sockets
12 AWG sockets
Size 5 coaxicons
140
H. Air Filtration Assemblies
UP86308
(1) ECS can supply air filtration assemblies for the HPA, SDU, and BSU tray assemblies
described in Table A--3 thru Table A--6. These filter assemblies offer protection
against airborne contaminants, such as dust and cigarette smoke. System
mean--time--between--failures (MTBF) can be significantly increased. Appendix B
supplies installation procedures for air filtration hardware.
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MCS--4000/7000 Multi--Channel SATCOM System
I.
SATCOM Shelf Assemblies
(1) ECS supplies customized and standard turnkey plenum shelf assemblies to
accommodate either single or dual SATCOM installations. A shelf assembly can
incorporate equipment trays, racking, and additional support structures, such as
disconnect panels, cover plates, and mounting brackets. ECS can supply
components that are compatible with all types of air transport aircraft.
NOTE: Some SATCOM system installation locations render the aircraft cooling
system inadequate. ECS has designed a self-contained cooling system for
the SATCOM shelf assembly that can be used in this type of installation.
J.
Additional Avionics Installation Components
(1) ECS supplies a variety of additional components to support a SATCOM installation.
These include RF splitters, combiners, high power relays, maintenance panels,
placards, circuit breakers, and control annunciator panels.
K. Antenna System Provisions
(1) SATCOM antenna systems are available in numerous configurations. ECS supplies
installation provisions for each of these configurations.
• Some high-gain top-mounted antenna systems require a 2-MCU tray assembly
and an ARINC 600 connector (Part No. NIC66F11A00AA0) for the BSU. Others
require mounting bracketry for the BSU. ECS supplies both BSU 2-MCU tray
assembly, and connector and mounting bracketry as required.
• ECS supplies trays and ARINC connectors for various SCUs in the market place.
• ECS supplies other antenna mounting hardware, such as mounting brackets for
the diplexer/low noise amplifier (D/LNA) and high- and low-gain antenna doublers.
L.
Cabin Communications System Provisions
(1) ECS supplies ARINC 746 compliant air-to-ground communication systems installation
provisions. These provisions include mounting hardware and connectors, shelves,
racks, brackets, placards, cover plates, RF cable, connectors, cable assemblies, and
wire harness assemblies.
M. Wire Harnesses
(1) ECS can supply wire harness provisions that interface the SATCOM avionics with the
cabin communication units, the cabin communications units with the cabin phones,
and both the SATCOM avionics and cabin communication units with other aircraft
systems.
(2) ECS wire harness assemblies can be custom designed and fabricated to meet
system installation requirements.
N. Complete Integrated SATCOM Installation Kits
UP86308
(1) Complete system integration packages are available for ECS for virtually any given
installation requirements. These integration packages can include any of the
installation provisions discussed in this section, along with other customer-specified
components. ECS can also support Honeywell’s customers with systems installation
design engineering and certification design data packaging.
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MCS--4000/7000 Multi--Channel SATCOM System
3. Hollingsead International
A. General
(1) This information aids you in selecting the engineering services and installation
provisions offered by Hollingsead International for the various MCS systems.
Hollingsead International is rapidly transforming into a world-class avionics and
aircraft systems integration leader, providing the capability to perform any or all of the
following:
• Design and manufacturing of the structural mounting for the MCS and all
associated avionics.
• Design and manufacturing of all wire and cable harness assembly interface
connections between the MCS and all associated avionics.
• Development of all engineering design substantiation, documentation, and testing
in support of FAA approval.
• Complete on-site support of a full installation team for the entire MCS installation
kit.
(2) You can contact them at the following address regarding your specific MCS program
requirements:
Hollingsead International
13701 Excelsior Drive
Santa Fe Springs, CA 90670
U.S.A.
Telephone: (310) 921-3438
FAX: (310) 921-6313
Telex: 691-462
B. Engineering Services
(1) As addressed in the previous paragraph, Hollingsead International supplies any level
of engineering support from minimal consultation to full turn-key. Full turn-key support
is defined as Hollingsead International undertaking the entire systems integration
from initial design through procurement and manufacture of parts to final installation
and certification on behalf on the customer.
C. LRU Mounting Requirements
UP86308
(1) MCS avionics are made up of the HPA, SDU, and BSU, which are mounted in ARINC
600 style tray assemblies. The HPA and SDU each require forced air cooling during
normal operation. The BSU and CMU, which are mounted in an ARINC 404 tray,
function properly with convection cooling alone.
23--20--27
Page A--10
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MCS--4000/7000 Multi--Channel SATCOM System
D. Installation Kit Components
(1) General
(a) Complete system installation kits are available from Hollingsead International for
virtually any given installation requirement. These installation kits can include any
of the installation provisions discussed herein along with other
customer-specified components.
(2) Coaxial Cables
(a) All coaxial cables, connectors, and attenuators have been designed to fulfill the
MCS system and the ARINC 741 usage and attenuation requirements.
Hollingsead International supplies immediate access to several types and
manufacturers of coaxial cable, appropriate N or TNC connectors, and
attenuators to make sure the specific attenuation profiles for each aircraft
installation is achieved. These cables range in nominal attenuation from 1.27 to
16.3 dB per 100 feet at 1.6 GHz. The cable outer diameter range is from 0.206
inch to 1.55 inches. Each cable assembly is fabricated with an individual part
number and, where necessary, is assigned a serial number, which is
permanently affixed to each end. Serialization insures traceability and
reproducibility.
(b) Testing of each cable assembly is performed to verify insertion loss and VSWR.
The results become part of a test database and are shipped with each cable
assembly. Each cable assembly is tested across the MCS system frequency
bandwidth. Transmit path cable assemblies are test swept from 1626.5 MHz to
1660.5 MHz and receive path cable assemblies are test swept from 1530 MHz to
1559 MHz. Customers have the option of having cable assemblies tested with or
without attenuators.
(3) Connectors
(a) Hollingsead International supplies the appropriate ARINC connectors for ARINC
Characteristic 741 style avionics electrical interfaces. The SATCOM rack-side
connector blocks are appropriately mounted on each tray assembly. Hollingsead
International supplies ARINC 600 Size 1 coaxial connectors with the necessary
termination kit assembly instructions.
(b) The connector part numbers are as follows:
• SDU -- C--06B3--0204--0100
• HPA (40W) -- C--06B3--0708--0100
• HPA (20W) -- C--06B3--0708--0100
• BSU -- C--06B1--0101--0100
UP86308
• CMU -- DPX2MA--A106PA106P--33B--0001.
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MCS--4000/7000 Multi--Channel SATCOM System
(4) Tray Assemblies
(a) Hollingsead International manufactures several tray assemblies for the MCS
avionics. These tray assemblies come with or without independent cooling
systems to ensure installation flexibility. Where forced air cooling is required,
these tray assemblies have been specially designed to meet the cooling
requirements of each LRU using a single fan. Tray assemblies are supplied with
insertion/extraction front hold-downs as standard, but are available with other
front hold-down options. Table A--7 identifies the various tray options and
Figure A--4 identifies the dimensions for each tray assembly.
Table A--7.
UP86308
Type
Standard
Ta
Tray
Assembly
Tray Assembly Part Numbers
Assembly Fan Location
Bottom
Left Side
Right Side
Left Rear
Right Rear
N/A
N/A
8 MCU S/S
1708006--101 1708007--101 1708008--101 1708008--102
8 MCU S/L
1708006--201 1708007--201 1708008--201 1708008--202 1708009--101 1708009--102
6 MCU S/S
1706007--101 1706008--101 1706009--101 1706009--102
6 MCU S/L
1706007--201 1706008--201 1706009--201 1706009--202 1706010--101 1706010--102
4 MCU S/S
1704008--101 1704009--101 1704010--101 1704010--102
4 MCU S/L
1704008--201 1704009--201 1704010--201 1704010--202 1704011--101 1704011--102
2 MCU S/S
1702002--101 1702003--101
2 MCU S/L
1702002--201 1702003--201
N/A
N/A
N/A
23--20--27
N/A
Page A--12
30 Aug 2002
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Figure A--4.
Dimensions for Hollingsead Tray Assemblies
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(5) Plenum Shelf Assemblies
(a) Hollingsead International supplies customized and standard turnkey plenum
shelf assemblies to accommodate either single or dual MCS system installations.
A shelf assembly can incorporate equipment trays, racking, and additional
support structures such as disconnect panels, cover plates, and mounting
brackets. Hollingsead International can supply components that are compatible
with all types of air transport aircraft.
(6) Additional Components
(a) Hollingsead International supplies a variety of additional components to support
an MCS installation, including RF splitters, combiners, high power relays,
maintenance panels, placards, circuit breakers, and control enunciator panels.
(7) Antenna System Provisions
(a) The antenna subsystems for the MCS system are available in numerous
configurations. Hollingsead International supplies installation provisions for each
of these configurations. Some high-gain, top-mounted antenna systems use a
2-MCU tray assembly and ARINC 600 connector for the BSU. Others use
mounting bracket hardware for the BSU. Hollingsead International supplies both
BSU 2-MCU tray assemblies and mounting bracket hardware as necessary.
Hollingsead International supplies other antenna mounting hardware such as
mounting brackets for the diplexer/LNA and high-gain and low-gain antenna
doublers.
(8) Cabin Communications System Provisions
(a) Hollingsead International supplies ARINC 746 compliant air-to-ground
communications system installation provisions. These provisions include
mounting hardware and connectors, shelves, racks, brackets, placards, cover
plates, RF cable, connectors, cable assemblies, and wire harness assemblies.
(9) Wire Harness Assemblies
(a) Hollingsead International wire harness assemblies are custom designed and
fabricated to meet each customer’s specific system installation requirements.
Hollingsead International supplies wire harness assemblies for the following
interfaces:
• MCS avionics and cabin communication units
• MCS avionics and flight deck data and voice communication sources
• Cabin communications units and cabin telephones
UP86308
• Both the SATCOM avionics and cabin communication units with other aircraft
systems.
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MCS--4000/7000 Multi--Channel SATCOM System
4. Signal Conditioning Unit
A. General
(1) The SCU (Racal Part No. 56047--010XX) is manufactured by Racal Avionics in the
U.S.A. Contact the project manager at the following address for additional information
not supplied in this section:
Racal Avionics Incorporated
8851 Monard Drive
Silver Spring, MD 20910
U.S.A.
Telephone: (301) 495-6695
FAX: (301) 585-7578
Telex: 898316
(2) The MCS system requires ARINC 429 data for antenna pointing, antenna
stabilization, and Doppler frequency correction. These requirements are defined in
Table A--8. If the aircraft does not have an IRS that supplies this ARINC data, the
SCU can be used to supply the data.
(3) The SCU is packaged as an ARINC 600 2 MCU and weighs a maximum of 5.95
pounds (2.70 kilograms). The outer case of the SCU is constructed from two
half-shells identical in dimensions, which are made of an aluminum alloy 1.6
millimeters thick. The front and rear panels are made of the same alloy 3.3
millimeters thick. Both panels attach to the outer half-shells with corner brackets. Two
divider plates mount between the half-shells of the outer case to supply additional
rigidity and electrical shielding.
(4) The SCU translates and consolidates various input data formats into a two-wire
differential ARINC 429 high speed output for latitude and longitude position, true
heading, track angle, ground speed, and pitch and roll attitude. Program pins define
the particular type of data being received. These pins are interrogated at power on by
the software to determine the required configuration.
UP86308
(5) The SCU operates from a nominal 115 V ac, 400 Hz single phase supply and/or from
28 V dc primary power. Input pins are supplied for both power sources in the ARINC
600 connector, and both power inputs can be connected to the aircraft power.
Current consumption depends on the input voltage and temperature, but is typically
0.25 amperes at 115 V ac or 0.40 amperes at 28 V dc.
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MCS--4000/7000 Multi--Channel SATCOM System
Table A--8.
Label
ARINC 429 Data Requirements
Definition
Minimum
Rate (MS)
Maximum
Rate (ms)
310
Latitude of present position
334
67
311
Longitude of present position
334
67
312
Ground speed
125
22
313
Track angle
55
22
314
True heading
55
22
324
Pitch
40
325
Roll
40
B. Operator Functions
(1) The front panel contains six LED indicators to allow monitoring of the SCU status.
However, these indicators are intended for use during repair by maintenance
personnel rather than by the operator during normal flight operation. Discrete outputs
representing the state of each LED indicator are also supplied for remote monitoring.
The functions of these discretes are defined in Table A--9.
Table A--9.
Color
Nomenclature
SCU Discrete Functions
Function
Green
Power
Indicates SCU is on and all voltages are correct when lit.
Green
SCU Valid
Indicates correct operation of the SCU logic and processing
circuits when lit.
Red
BIT Fail
• Indicates normal operation when off.
• Indicates BIT is running repetitively when flashing slowly.
Indicates the SCU has failed BIT when steadily lit.
• Indicates the SCU has failed BIT when steadily lit.
Amber
Signal 1
Indicates selection of input channel 1 when lit.
Amber
Signal 2
Indicates selection of input channel 2 when lit.
Amber
Signal 3
Indicates selection of input channel 3 when lit.
UP86308
(2) Three amber LED indicators supply an error code that is displayed when the SCU
fails in the BIT mode. The red indicator lights and a three-bit code is continuously
displayed on the amber LEDs as indicated in Table A--10. BIT is interruptive and all
normal operation ceases during the time when the SCU is in the BIT mode.
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MCS--4000/7000 Multi--Channel SATCOM System
Table A--10.
Failure
SCU Error Code
Code
LED 1
LED 2
LED 3
ARINC 429 translator not programmed
ON
OFF
OFF
RAM read/write failed
OFF
ON
OFF
ARINC 561 translator failed
ON
ON
OFF
PROM checksum failed
OFF
OFF
ON
ARINC 561 translator not programmed
ON
OFF
ON
Discrete input failed
OFF
ON
ON
ARINC 429 translator failed
ON
ON
ON
C. Control Functions
(1) Normal operation of the SCU is fully automatic and does not require operator
intervention. Some control functions are supplied through the main ARINC 600
connector. These functions include:
• Remote SCU on/off control
• BIT initiate control
• Signal select A
• Signal select B
• Program pin A
• Program pin B
• Program pin C.
(2) The remote SCU on/off control line enables the operation of the SCU power supply.
The control line is active low and must be connected to ground to enable operation of
the SCU. An open circuit or 28 V dc on this line shuts down operation of the SCU.
(3) The BIT initiate control line is an active low input used to enable BIT in the SCU. The
BIT mode is an optional function that supplies a pre/post-flight confidence check and
is intended for use by maintenance personnel as a diagnostic tool. The SCU remains
in the BIT mode as long as the BIT initiate control line is grounded. An open circuit or
28 V dc on this control causes the SCU to return to normal operation.
UP86308
(4) Signal selection is normally an automatic function under control of the internal SCU
program and is based on the validity of the received data. The signal select control
lines supply an override of this automatic function to allow manual selection of one
input from three available sources. The signal select control lines are active low and
are internally pulled high. Manual selection is accomplished by applying a ground to
the control lines as given in Table A--11.
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MCS--4000/7000 Multi--Channel SATCOM System
Table A--11.
SCU Manual Signal Selection
Signal Select Control Lines
Automatic Selection
High
High
Select Input No. 1
Low
High
Select Input No. 2
High
Low
Select Input No. 3
Low
Low
Function
D. System Functions
(1) Initialization
(a) Operation begins with BIT when the SCU is activated by applying aircraft power
and grounding the on/off control line. Testing normally takes approximately 0.5
second and when BIT passes normal operation begins. If the SCU fails the initial
BIT check, the unit latches in the BIT mode and displays an error code with the
amber LED indicators.
(2) Automatic Input Selection Mode
(a) There are three available data input channels. Unless a channel is manually
selected, the input to be used by the SCU is selected automatically. After initially
selecting Channel 1, the SCU checks for the presence of the required valid
words in the input data stream and the status of the attitude warning discrete
from the selected synchro channel. If all validity conditions are met within 1.6
seconds from the initial channel selection, the SCU locks on to the current
channel and continues to operate from that data source. The appropriate amber
LED indicator lights to indicate the selected channel to operator. If any of the
required data is invalid, the SCU cycles to the next input channel until a channel
providing a complete frame of valid data is received.
(3) Valid Channel Condition
(a) Conditions that must exist to let the SCU accept the current input channel
include:
• At least one new data word for each of the required labels is received within
the specified time period.
• The sign/status matrix (SSM) of all words for all required labels must be valid.
UP86308
• The primary attitude warning input discrete must be in a valid state to indicate
the synchro inputs for attitude are usable.
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MCS--4000/7000 Multi--Channel SATCOM System
(4) Channel Switching Timing
(a) The SCU allows 1.6 seconds for the selected input channel to receive a valid
data frame. However, if 1.6 seconds has passed and the valid channel
conditions have not been satisfied, the input channel cycles to the next
sequential channel. If all three input channels have been checked and none are
valid, the SCU prevents further cycling of the input channel selection for 1
minute. This prevents the SCU from continuously cycling when the inertial
navigation units or other sources of navigation data have not been initialized.
After the 1-minute delay, the SCU again initiates the checking cycle.
(5) Data Input
(a) A data subset made up of present latitude and longitude, true heading, track
angle, and ground speed is received through either the ARINC 561--6 wire inputs
or the ARINC 571--2 wire inputs as defined by the program pin selections. When
used as a selector of ARINC 404 data inputs, pitch and roll labels are also
included. The words are selected from the data stream by their octal labels while
other words are ignored. Program pin selections and associated data formats
and labels are defined in Table A--12 thru Table A--16.
Table A--12.
ARINC 561 Binary Data
Program Pin
Octal Label
Coded
310
Binary
Latitude of present position
311
Binary
Longitude of present position
212
Binary
Ground speed
213
Binary
Track angle
214
Binary
True heading
Table A--13.
Definition
ARINC 561 BCD Data
UP86308
Program Pin
Octal Label
Coded
010
BCD
Latitude of present position
011
BCD
Longitude of present position
012
BCD
Ground speed
013
BCD
Track angle
014
BCD
True heading
Definition
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Table A--14.
ARINC 571 Data, ARINC 429 Format
Program Pin
Octal Label
310
Latitude of present position
311
Longitude of present position
212
Ground speed
213
Track angle
214
True heading
Table A--15.
Definition
ARINC 571 Data, ARINC 419 Format
Program Pin
Octal Label
210
Latitude of present position
211
Longitude of present position
212
Ground speed
213
Track angle
214
True heading
Table A--16.
Definition
ARINC 404 Data, ARINC 429 Format
Program Pin
Octal Label
310
Latitude of present position
311
Longitude of present position
312
Ground speed
313
Track angle
314
True heading
324
Pitch
325
Roll
Definition
UP86308
(b) The SSM of each received data word is checked. Valid words are converted to
ARINC 429 data. Invalid words are discarded.
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MCS--4000/7000 Multi--Channel SATCOM System
(c) With exception of the ARINC 404 input, the SCU also receives attitude data from
an associated attitude source. The attitude data is in the form of ARINC 407
pitch and roll synchro channels and an attitude warning flag. Attitude data is
selected from a source associated with the source selected for digital data. The
attitude inputs used are given in Table A--17.
Table A--17.
SCU Attitude Data Inputs
Data
Line Function
Roll
Synchro X
Roll
Synchro Y
Roll
Synchro Z
Pitch
Synchro X
Pitch
Synchro Y
Pitch
Synchro Z
Roll/Pitch
Reference HI
Roll/Pitch
Reference LO
Warning Flag
HI Flag (HI = Good)
(d) The pitch and roll synchro inputs are read every 20 milliseconds. The attitude
warning flag is sampled before each computation to check the validity of the
input data before the data is accepted.
(6) Data Output
(a) The SCU transmits ARINC 429 serial words at a rate of one complete
seven-word message every 20 milliseconds. The SSMs in the navigation data
words are based on those supplied by the digital input words. The SSM data for
the attitude words is derived from computations and from the primary warning
flag.
UP86308
(b) The data output is in accordance with ARINC 429 high speed data (100 kHz
clock speed). The SCU outputs ARINC 429 data on two separate ports operating
in parallel. Data from both ports is identical, but independent output buffers are
used to supply redundancy.
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E.
ARINC 600 Connector Pin Assignments
(1) The rear connector (ARINC Part No. NIC66F11A00AA0) of the SCU complies with
ARINC Characteristic 600 as specified in the following:
• ARINC 600 -- Size MCU 2 no. 2 shell
• Type 0X top insert
• Type 0X middle insert
• Type 0X bottom insert
• Index pin code 0X.
(2) The contact arrangements for the connector are specified in Table A--18. An example
pin designation of BC12 for the table is given below.
Pin Designation Example: Pin BC12
B -- C -- 12
Connector Cavity Identifier
Top Cavity = A
Middle Cavity = B
Bottom Cavity = C
Column Identifier
(A, B, C, or D)
UP86308
Row Identifier
(1 thru 15)
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MCS--4000/7000 Multi--Channel SATCOM System
Table A--18.
Contact Arrangements for SCU ARINC 600 Connector
UP86308
Pin
Function
Remarks
AC1
ARINC 561 Data No. 1 (HI)
Note 1.
AD1
ARINC 561 Data No. 1 (LO)
Note 1.
AC2
ARINC 561 Clock No. 1 (HI)
Note 1.
AD2
ARINC 561 Clock No. 1 (LO)
Note 1.
AC3
ARINC 561 Strobe No. 1 (HI) or ARINC 429/419 Data No. 1 (HI)
Note 1.
AD3
ARINC 561 Strobe No. 1 (LO) or ARINC 429/419 Data No. 1 (LO)
Note 1.
AC4
Spare
AD4
Spare
AC5
Spare
AD5
Spare
AC6
Spare
AD6
Spare
AC7
Spare
AD7
Spare
AC8
Spare
AD8
Spare
AC9
ARINC 561 Data No. 3 (HI)
Note 1.
AD9
ARINC 561 Data No. 3 (LO)
Note 1.
AC10
ARINC 561 Clock No. 3 (HI)
Note 1.
AD10
ARINC 561 Clock No. 3 (LO)
Note 1.
AC11
ARINC 561 Strobe No. 3 (HI) or ARINC 429/419 Data No. 3 (HI)
Note 1.
AD11
ARINC 561 Strobe No. 3 (LO) or ARINC 429/419 Data No. 3 (LO)
Note 1.
AC12
Spare
AD12
Spare
AC13
ARINC 407 Pitch No. 1 X
Note 2.
AD13
ARINC 407 Pitch No. 1 Y
Note 2.
AC14
ARINC 407 Pitch No. 1 Z
Note 2.
AD14
ARINC 407 Heading X
Reserved
AC15
ARINC 407 Heading Y
Reserved
AD15
ARINC 407 Heading Z
Reserved
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table A--18.
Contact Arrangements for SCU ARINC 600 Connector (cont)
UP86308
Pin
Function
Remarks
AA1
ARINC 407 Pitch No. 3 X
Note 2.
AB1
ARINC 407 Pitch No. 3 Y
Note 2.
AA2
ARINC 407 Pitch No. 3 Z
Note 2.
AB2
Attitude Warning No. 1 (From Attitude Source)
Note 2.
AA3
ARINC 407 Reference No. 1 (HI)
AB3
ARINC 407 Reference No. 1 (LO)
AA4
ARINC 407 Heading Reference (HI)
Reserved
AB4
ARINC 407 Heading Reference (LO)
Reserved
AA5
ARINC 407 Reference No. 3 (HI)
AB5
ARINC 407 Reference No. 3 (LO)
AA6
Attitude Warning No. 3 (From Attitude Source)
AB6
Spare
AA7
ARINC 407 Roll No. 1 X
Note 2.
AB7
ARINC 407 Roll No. 1 Y
Note 2.
AA8
ARINC 407 Roll No. 1 Z
Note 2.
AB8
Spare
AA9
Spare
AB9
Spare
AA10
Spare
AB10
Spare
AA11
ARINC 407 Roll No. 3 X
Note 2.
AB11
ARINC 407 Roll No. 3 Y
Note 2.
AA12
ARINC 407 Roll No. 3 Z
Note 2.
AB12
Spare
AA13
ARINC 404 Echo (HI)
Note 3.
AB13
ARINC 404 Echo (LO)
Note 3.
AA14
Spare
AB14
Spare
AA15
Spare
AB15
Spare
Note 2.
23--20--27
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Table A--18.
Contact Arrangements for SCU ARINC 600 Connector (cont)
UP86308
Pin
Function
Remarks
BC1
ARINC 407 Pitch No. 2 X
Note 2.
BD1
ARINC 407 Pitch No. 2 Y
Note 2.
BC2
ARINC 407 Pitch No. 2 Z
Note 2.
BD2
Spare
BC3
ARINC 407 Roll No. 2 X
Note 2.
BD3
ARINC 407 Roll No. 2 Y
Note 2.
BC4
Spare
BD4
ARINC 407 Roll No. 2 Z
BC5
Spare
BD5
Attitude Warning No. 2 (From Attitude Source)
BC6
ARINC 407 Reference No. 2 (HI)
BD6
ARINC 407 Reference No. 2 (LO)
BC7
Signal Source Select A (Input No. 1)
Note 4.
BD7
Signal Source Select (Input No. 2)
Note 4.
BC8
BIT initiate (Input No. 3)
Note 5.
BD8
Spare
BC9
BIT Failed (Output No. 2)
Reserved
BD9
SCU Valid
Reserved
BC10
Superflag (+28 V dc = Output Valid)
Note 6.
BD10
/Superflag (<1 V dc = Output Valid)
Note 6.
BC11
Program Pin A (Input No. 5)
Note 7.
BD11
Program Pin B (Input No. 6)
Note 7.
BC12
Program Pin C (Input No. 7)
Note 7.
BD12
Spare
BC13
Spare
BD13
Spare
BC14
Spare
BD14
Spare
BC15
ARINC 429 Out No. 1 (HI)
BD15
ARINC 429 Out No. 1 (LO)
Note 2.
Note 2.
23--20--27
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Table A--18.
Contact Arrangements for SCU ARINC 600 Connector (cont)
UP86308
Pin
Function
Remarks
BA1
Spare
BB1
Spare
BA2
ARINC 429 Out No. 2 (HI)
BB2
ARINC 429 Out No. 2 (LO)
BA3
Spare
BB3
Spare
BA4
Discrete Out No. 3 (Select No. 2 LED)
Reserved
BB4
Discrete Out No. 4 (Select No. 3 LED)
Reserved
BA5
Discrete Out No. 5 (Select No. 1 LED)
Reserved
BB5
Discrete Out No. 6
Reserved
BA6
Discrete Out No. 7
Reserved
BB6
Discrete Out No. 8
Reserved
BA7
ARINC 561 Data No. 2 (HI)
Note 1.
BB7
ARINC 561 Data No. 2 (LO)
Note 1.
BA8
ARINC 561 Clock No. 2 (HI)
Note 1.
BB8
ARINC 561 Clock No. 2 (LO)
Note 1.
BA9
ARINC 561 Strobe No. 2 (HI) or ARINC 429/419 Data No. 2 (HI)
Note 1.
BB9
ARINC 561 Strobe No. 2 (LO) or ARINC 429/419 Data No. 2 (LO)
Note 1.
BA10
+28 V dc Power
Aircraft Power (Note 8.)
BB10
+28 V dc Power
Aircraft Power (Note 8.)
BA11
0 V dc Power Return
Aircraft Power (Note 8.)
BB11
0 V dc Power Return
Aircraft Power (Note 8.)
BA12
Chassis Ground
BB12
Remote SCU On/Off Control
Note 9.
BA13
Shield return
Connected to Chassis
BB13
Shield Return
Connected to Chassis
BA14
115 V ac Power 400 Hz (HI)
Aircraft Power (Note 8.)
BB14
Chassis Ground
BA15
115 V ac Power 400 Hz (LO)
Aircraft Power (Note 8.)
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table A--18.
Contact Arrangements for SCU ARINC 600 Connector (cont)
Pin
BB15
Function
Remarks
Chassis Ground
NOTES:
1.
The 6-wire ARINC 561 or 2-wire ARINC 429/419 (ARINC 571/404) data can be routed from up to three sources.
However, if a single input is supplied, it should be connected to the No. 1 inputs as indicated. Inputs No. 2 and 3
should be left open. The type of data being used, either ARINC 561 or ARINC 571/404, must be indicated by
selecting the proper program pins as specified in NOTE 7. Also, refer to NOTE 4. for more information on selecting
a specific input as the data source.
2.
The synchro pitch and roll data can be routed from up to three sources. However, sources of attitude data must be
paired with sources of ARINC 561 or ARINC 571 data. Thus, if only one source of ARINC 561 or ARINC 571 data
is available, then only one source of attitude data can be used. An attitude warning flag for each source of attitude
that is active must be supplied. +28 V dc = valid. Ground or open = invalid.
3.
When the SCU is used as a selector/controller of multiple ARINC 404 compatible data sources, the receiving
equipment should be connected to the ARINC 404 echo outputs. In this configuration, the input as valid by the
SCU is routed back out of the unit on these pins. Since attitude data is embedded in the ARINC 404 data stream,
no attitude inputs are used.
4.
When multiple sources of data are available and routed to the SCU, it automatically searches for an input with valid
attitude data and ARINC 561/571 data. If only one source of ARINC 561/571 data and attitude data is available, the
SCU should be connected to only one input and the signal source select lines should be linked as applicable for
the selected input as given in Table A--19.
5.
Grounding the BIT initiate input forces the SCU to enter the interruptive BIT mode and repetitively do its BIT
routines until ground is removed. BIT is automatically done at each power-up cycle. This input should be an open, if
not used.
6.
The superflag output is +28 V dc whenever the SCU is operating normally and the output data is valid. If a portion
of the input data is invalid or the SCU detects an internal fault, then the superflag output is 0 V dc. The /superflag
output is the inverse of the superflag output.
7.
The data format and characteristics accepted by the SCU are programmable through pins A, B, and C. The
combinations supported by the SCU are specified in Table A--20.
8.
The SCU operates from either +28 V dc or 115 V ac, 400 Hz power. The power source not used should remain
unconnected.
9.
The remote SCU on/off control can be used to power down the SCU from a remote location. A ground activates the
unit and an open switches the unit off. If remote control is not required, this pin should be permanently grounded at
the connector.
UP86308
Table A--19.
Signal Source Select Lines
Signal Source Select
Auto
Open
Open
Input No.1
Ground
Open
Input No. 2
Open
Ground
Input No. 3
Ground
Ground
23--20--27
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MCS--4000/7000 Multi--Channel SATCOM System
Table A--20.
SCU Program Pin Combinations
Program Pins
ARINC 561 data, binary labels, synchro attitude
ARINC 561 data, BCD labels, synchro attitude
ARINC 571 data with ARINC 429 format, synchro attitude
ARINC 571 data with ARINC 419 format, synchro attitude
Input Description
UP86308
NOTE: Ground = 1; open = 0.
23--20--27
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UP86308
Blank Page
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APPENDIX B
INSTALLATION PROCEDURES FOR SATCOM AIR FILTRATION
SYSTEMS
1. Introduction
A. General
(1) Appendix B contains information on the different air filtration systems available for the
SATCOM installations. Procedures for installing these air filtration systems are also
supplied. After you have determined the proper air filtration system for your needs,
follow the appropriate procedures in paragraph 4.
(2) The SATCOM system (SDU and HPA) is designed to ARINC 600 standards including
ARINC 600 cooling requirements. ARINC 600 calls for the cooling air to contain no
contamination particles in excess of 400 microns. Several installation designs do not
supply cooling air in accordance with ARINC 600. The OEM installation design for the
B747, B767, and B777 supply unfiltered cooling air (cabin air) to the SATCOM LRUs.
As a result, contaminants in the air tend to accumulate on and inside the LRUs
sometimes blocking off the cooling air passages. This leads to units operating at a
higher temperature, which can result in decreasing the MTBF of the units.
(3) Filter assemblies have been designed that attach to the SATCOM LRUs or to the
LRU trays. These filter assemblies contain filter media that filter out contaminants
before entering the LRUs. This design is for installations where the cooling air is
drawn through the LRU top to bottom, and where there is at least 1 inch of clearance
above the LRUs to allow for the assembly itself. Thus, the air filtration units included
in this appendix are acceptable for installation on the B747 and B777 aircraft, but
because of clearance problems, are not acceptable for installation on the
OEM-provisioned B767 aircraft.
2. Continued Airworthiness
A. General
CAUTION: THE FILTER MEDIA MUST BE REPLACED (OR CLEANED) APPROXIMATELY
EVERY 4000 FLIGHT HOURS OR EVERY C CHECK, WHICHEVER COMES
FIRST, OR THE EFFECTIVENESS OF THE AIR FILTRATION ASSEMBLY CAN
BE DEGRADED.
(1) The selection of the type of filter media cartridge is based on the following:
• Effectiveness of the filter media in removing contaminants from the cooling air
before entering the SATCOM LRUs.
• Impact of the filter media on the cooling air mass flow rate through the units.
UP86308
• Time between removals.
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3. Equipment and Materials
A. General
WARNING: BEFORE YOU USE A MATERIAL, KNOW THE HAZARD CODE AND GET THE
NECESSARY PROTECTION. REFER TO THE PAGE ABOUT HAZARD CODES
FOR MATERIALS IN THE FRONT OF THIS MANUAL.
(1) Refer to Table B--1 for a list of materials.
Table B--1.
Item
Materials
Description
Source
HMN 9730178
Retaining compound
Loctite Corp, Rocky Hill, CT
(MIL--S--22473, grade A) — Grade (05972)
HMN 9731178
Primer for retaining compound,
ready--to--use, quick
(MIL--S--22473, grade T, form R)
— Locquic Grade T
NOTES: NOTES:
1.
Equivalent alternatives are permitted for equipment and materials in this list.
2.
The HMN codes in the list of materials identify the Honeywell Material Number (HMN) given to each material.
(2) The equipment listed in Table B--2, Table B--3, and Table B--4 supplies the necessary
hardware to install air filtration systems on the aircraft. Find the air filtration system
and filter that best fits your needs and contact the company that manufacturers that
particular equipment.
Table B--2.
UP86308
Equipment
Air Filtration Systems from ECS for a Top Mount Assembly
Quantity
LRU
Part No.
SATCOM System
SATCOM Filter Assembly
SDU
10919--101
6--MCU assembly
SATCOM Filter Assembly
HPA (20W)
10968--101
4--MCU assembly
SATCOM Filter Assembly
HPA (40W)
10923--101
8--MCU assembly
Filter Cartridge Assembly
SDU
10907--105
6--MCU assembly
Filter Cartridge Assembly
HPA (20W)
10907--104
4--MCU assembly
Filter Cartridge Assembly
HPA (40W)
10907--106
8--MCU assembly
23--20--27
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Table B--3.
Air Filtration Systems from ECS for a Body--Mounted Design
Equipment
Quantity
Part No.
SATCOM System
SATCOM Filter Assembly
SDU
P0329--106
6--MCU assembly
SATCOM Filter Assembly
HPA (20W)
P0329--104
4--MCU assembly
SATCOM Filter Assembly
HPA (40W)
P0329--108
8--MCU assembly
Filter Cartridge Assembly
SDU
20008--05
6--MCU assembly
Filter Cartridge Assembly
HPA (20W)
20008--04
4--MCU assembly
Filter Cartridge Assembly
HPA (40W)
20008--06
8--MCU assembly
Table B--4.
Air Filtration Systems from ECS for a Tray--Mounted Design
Equipment
UP86308
LRU
Quantity
LRU
Part No.
SATCOM System
SATCOM Filter Assembly
SDU
20005--103
6--MCU assembly
SATCOM Filter Assembly
HPA (20W)
20005--102
4--MCU assembly
SATCOM Filter Assembly
HPA (40W)
20005--104
8--MCU assembly
Filter Cartridge Assembly
SDU
20008--05
6--MCU assembly
Filter Cartridge Assembly
HPA (20W)
20008--04
4--MCU assembly
Filter Cartridge Assembly
HPA (40W)
20008--06
8--MCU assembly
23--20--27
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4. Installation Instructions
A. Top Mount Assembly
(1) The ECS top mount air filtration assembly is designed to clamp to the top of the
SATCOM LRUs so it does not come off the LRU. Once attached to the top of the
LRU, it forms a seal letting only filtered air enter the LRU. The assembly is held to the
top of the LRU by friction from the sides of the assembly and by the clamps that
supply friction to the front and rear panels of the unit. Figure B--1 shows the location
of the components for the following procedures.
(2) Install the filter assembly to an SDU or HPA using the following steps.
(a) Make sure the correct size assembly is selected for the given LRU (refer to
Table B--2).
(b) OPTIONAL — Remove the SATCOM LRU from its tray and set it on a secure
surface. (The assembly can be installed while the unit is in the rack.)
(c) Install the air filtration media inside the air filtration assembly in the rectangular
filter frame.
(d) Place the filter assembly over the top of the LRU with the clamps in the up
(thumb lever over the top of the filter assembly) position and pointing toward you.
(e) Push down on the air filtration unit until it fits over the top of the SATCOM LRU.
The sides of the air filtration assembly may need to be spread open slightly prior
to sliding over the sides of the LRU.
(f)
Once the air filtration unit is firmly seated to the top of the LRU, clamp the
assembly to the unit by pushing down on the two thumb levers until they lock into
position. The thumb levers pass through approximately 180 degrees of rotation
for the clamping process.
(g) Make sure the air filtration assembly remains seated firmly against the top of the
LRU to maintain the air seal.
(h) Make sure the air filtration assembly is held tightly to the unit by gently lifting up
on the assembly; making sure the assembly does not pull off of the LRU.
UP86308
(i)
OPTIONAL -- Install the SATCOM LRU back into its tray if removed in step
4.A.(2)(b).
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Figure B--1.
ECS Top Mount Air Filtration Assembly
(3) Replace the filter media according to the following steps.
(a) Gain access to the SATCOM LRUs.
(b) Lift up on the two thumb levers (approximately 180 degrees).
(c) Pull up on the air filtration unit until it lifts off the top of the SATCOM LRU. The
sides of the air filtration assembly may need to be spread open slightly prior to
sliding up the sides of the LRU.
(d) Remove the air filtration media from the air filtration assembly in the rectangular
filter frame.
(e) Once the assembly is removed, pull the filter assembly out of its retaining fixture
and discard the filter appropriately.
(f)
Obtain a new filter.
(g) Make sure the correct size filter assembly is selected for the given LRU (refer to
Table B--2).
UP86308
(h) Install the new filter media into the filter assembly retaining fixture.
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(i)
OPTIONAL — Remove the SATCOM LRU from its tray and set on a secure
surface. (The assembly can be installed while the unit is in the rack.)
(j)
Install the air filtration media inside the air filtration assembly in the rectangular
filter frame.
(k) Place the filter assembly over the top of the LRU with the clamps in the up
(thumb lever over the top of the filter assembly) position and pointing toward you.
(l)
Push down on the air filtration unit until it fits over the top of the SATCOM LRU.
The sides of the air filtration assembly may need to be spread open slightly prior
to sliding over the sides of the LRU.
(m) Once the air filtration unit is firmly seated to the top of the LRU, clamp the
assembly to the unit by pushing down on the two thumb levers until they lock into
position. The thumb levers will pass through approximately 180 degrees of
rotation for the clamping process.
(n) Make sure the air filtration assembly remains seated firmly against the top of the
LRU to maintain the air seal.
(o) Make sure the air filtration assembly is held tightly to the unit by gently lifting up
on the assembly to verify the assembly does not pull off the LRU.
(p) OPTIONAL -- Install the SATCOM LRU back into its tray if removed in step
4.A.(3)(i).
B. Body--Mounted Assembly
(1) The ECS body-mounted air filtration assembly is designed to strap around the body
of the SATCOM LRUs in a way that it will not come off the LRU. Once attached to the
LRU, it forms a seal allowing only filtered air to enter the LRU. The assembly is held
to the top of the LRU with a strap that fits securely around the body of the unit. The
filtration unit sits on top of the SATCOM LRU. The strap runs down the side,
underneath, and up the other side of the LRU. By way of a clamping system on top of
the LRU, the strap is pulled tight, which firmly secures the filter assembly to the top of
the unit.
(2) Install the filter assembly to an SDU or HPA according to the following steps.
(a) Make sure the correct size assembly is selected for the given LRU
(refer to Table B--3).
(b) Remove the SATCOM LRU from its tray and set it on a secure surface.
(c) Slide the filter strap around the front of the LRU so the strap is underneath and
coming up each side of the LRU.
UP86308
(d) Place the filter assembly on top of the LRU so the back lip of the assembly unit
fits over the back of the LRU.
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(e) Pull the strap around the top of the filter assembly unit so the two ends of the
strap overlap. The strap should come over the top of the filter assembly on the
front end of the assembly (dog-house end of the LRU). A channel is built into the
filter assembly for the strap.
(f)
With the strap in place, latch the strap together by inserting the lips of the strap
ends together so they latch together. With the LRU facing you, the strap on the
left-hand side should latch over the top of the strap on the right-hand side.
(g) Once the strap is latched, make sure the lip on the rear of the filter assembly is
seated firmly just over the rear of the LRU.
(h) Make sure the filter retainer mechanism is latched closed.
(3) Replace the filter media according to the following steps. Figure B--2 shows the
location of the components used.
(a) Gain access to the SATCOM LRUs.
(b) Locate the filter retaining clips located on the forward end of the filter assembly
mechanism.
(c) Slide the retainer clips (one on the left and one on the right) out to disengage the
clips from the latching pins.
(d) Lift the filter retaining tray up, (hinged on the rear side) remove the filter media
cartridge and discard the filter appropriately.
(e) Install the new filter media by placing a new filter media cartridge in the filter
retaining tray chamber.
(f)
Lower the filter retaining tray down until the locating pins protrude through the
clearance holes on the filter retaining tray.
(g) Slide the retaining clips (left and right) in until they latch around the latching pins.
C. Tray--Mounted Assembly
(1) The ECS tray-mounted air filtration assembly is designed as an integral part of the
equipment tray and does not attach to the LRU itself. The SATCOM LRU slides into
the tray, sandwiched between the tray and plenum below, and the air filtration
assembly above. Since the air filtration assembly is an integral part of the equipment
tray, in order to install this type of assembly, a modified equipment tray must be
purchased for each LRU.
(2) Replace the filter media according to the following steps. Figure B--2 shows the
location of the components used.
(a) Gain access to the SATCOM LRUs.
UP86308
(b) Locate the filter retaining clips located on the forward end of the filter assembly
mechanism.
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(c) Slide the retainer clips (one on the left and one on the right) out to disengage the
clips from the latching pins.
(d) Lift the filter retaining tray up (hinged on the rear side) and remove the filter
media cartridge. Discard the filter media cartridge appropriately.
(e) Install the new filter media by placing a new filter media cartridge in the filter
retaining tray chamber.
(f)
Make sure the filter cartridge is supported on the air plenum seals. The direction
of airflow through the filter is not important.
(g) Lower the filter retaining tray until the locating pins protrude through the
clearance holes on the filter retaining tray.
(h) Slide the retaining clips (left and right) in until they latch around the latching pins.
UP86308
Figure B--2.
Front and Side Views Showing Filter Removal
23--20--27
Page B--8
30 Aug 2002
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
APPENDIX C
OWNER REQUIREMENTS TABLE
1. Overview
A. General
(1) Appendix C contains information on the owner requirements table (ORT) and is
stored in non--volatile memory in the SDU. The ORT contains information relating to
different areas of functionality, such as log-on and telephony. The ORT does not lose
its contents because of the loss of SDU primary power or as a result of PAST. All
ORT contents are set to default values by a factory settings restart. The ORT
contains all pilot and aircraft operator entered information preserved when the SDU is
powered-down. The characteristics of the ORT are specified in Table C--1.
NOTE: Honeywell supplies Windows--based software (ORT editor) that is used to
generate the ORT files for upload. Contact your Honeywell representative for
a copy of this software.
Table C--1.
UP86308
ORT Item
Characteristic
Attributes
ORT Characteristics
Description
Log-On Policy
Secured,
common
This item defines the log-on procedure. When the SDU has
power applied, the SDU either starts the automatic log-on
procedure at the earliest opportunity (automatic), or the SDU
goes to an inert standby state, even if the SDU is entirely
failure free, where the SDU then waits for user stimulus to
start logging-on (commanded).
ii
Satellite/GES
Names
User,
common
This item defines associated names for the satellites and
GESs. Satellite names are up to five characters long. GES
names are up to 14 characters long. Names made up of
upper case letters, decimal digits, hyphens, and spaces are
allowed. A GES name can include satellite and service
identifying strings; e.g., GOON A--E SKY takes 12 characters
and identifies Goonhilly, the United Kingdom GES servicing
the Skyphone consortium and using the Atlantic ocean region
east satellite.
iii
GES Preference
Values
User,
common
This item defines the automatic log-on preference values for
GESs from 0 to 9, where 9 corresponds to the most preferred
GES. The interpretation of preference value 0 is determined
by item lvi, 0 is either the least preferred GES or it is not used
for automatic log-on. GESs with preference level 0 can still be
used for a constrained log-on. When all GESs on a particular
satellite have a preference level of 0 and this satellite
becomes the candidate for logon, the logon processing
considers all of these GESs to have a preference level of 1 to
facilitate continued SATCOM operation.
iv
Maintenance
Page Access
User,
common
This item defines whether the SCDU maintenance pages are
accessible as: a) never; b) always; or c) only when the aircraft
is on the ground.
23--20--27
Page C--1
30 Aug 2002
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Table C--1.
ORT Item
Characteristic
Cockpit
Telephone
Numbers
Attributes
User,
common
ORT Characteristics (cont)
Description
This item defines up to 100 telephone numbers as follows:
• Each made up of up to 18 numeric characters (including
optional spaces and/or trailing network ID preceded by a
slash)
• Each number having an associated priority value
(i.e., 1 thru 4), protection (i.e., protected or unprotected),
and a mnemonic of up to 14 characters
• All are located in four user-definable categories of no more
than 25 telephone numbers each.
UP86308
If configuration pin TP13A is set to the zero state, every entry
with a priority 4 is modified to a priority 3 following an ORT
upload or following a POST/PAST where priority 4 numbers
existed prior to TP13A being set to the zero state. In a dual
system, this modification takes place only if strap TP13A is in
the zero state on both SDU systems. This item includes
manually entered telephones from the SCDU CATEGORY
NUMBERS pages.
vi
Deleted
vii
Resources
Reserved for
Headset
User,
common
When enabled, this item reserves the following resources for
cockpit headset use at all times: one codec, one modem, and
sufficient HPA power to support an extra C--channel in all
prevailing circumstances. These resources are capable of
being reserved for either of the cockpit audio channels. In a
dual system, channel refers to logical channel.
viii
Response
Capability to
Log-On
Interrogation
N/A
This item is not considered part of the MCS ORT, since the
AES always supports log-on interrogation. There is always
one SDU modem dedicated to P--channel reception and
capable of R--channel and T--channel transmission.
ix
Use and Value of
Flight
Identification
N/A
This item is not considered part of the MCS ORT since the
value is dynamic and is obtained from the CFDS/CMC/OMS
or SCDU (along with item xxxiv).
Ground-to-Air
Circuit-Mode
Data
User,
common
This item defines the allowing/disallowing of analog
interconnect circuit-mode data on ground-to-air calls. It lets
the AES identify itself to the GES as being data capable and
the owner/operator anticipates receiving ground-to-air calls
that need circuit-mode data service, thereby directing the
GES to assign data capable channels to all ground-to-air
calls.
xi
Deleted
xii
Deleted
23--20--27
Page C--2
30 Aug 2002
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Table C--1.
UP86308
ORT Item
Characteristic
Attributes
ORT Characteristics (cont)
Description
xiii
Ground-to-Air
Calls
User,
common
This item defines the allowing/disallowing and routing of
ground-to-air priority 4 calls. If calls are allowed and if two or
more of the AES voice user interfaces (i.e., digital phones,
analog handset, or headset) are fitted, this item specifies
which destination (digital phone, analog handset, or headset)
incoming priority 4 calls are routed. However, routing to the
headset is only possible if configuration pin TP13A is set to
the one state. If TP13A is set to the zero state, the ORT
setting is modified to Disallowed following a factory setting
restart, an ORT upload with headset selected, or a
POST/PAST if headset was selected prior to TP13A being set
to the zero state. In a dual system, ground-to-air priority 4
calls can be routed to an interface that is installed on at least
one of the SDU systems. Routing to HEADSET is only
possible if at least one SDU system has a codec wired to
AMS with TP13A strap in the one state (on this same SDU
system).
xiv
Call Camp-On
Duration
User,
common
This item defines the camp-on duration be either indefinite, or
a specified time-out period in the range of 1 to 15 minutes, or
a time--out period of zero minutes (immediate time--out).
xv
Camp-On
Time-out Action
User,
common
This item defines whether the camp-on time-out action is to
(a) preempt (if a candidate call exists) or to cancel camp-on
(if no candidate call exists), or (b) to cancel camp-on.
xvi
Stored APHONE
(WH--10)
Telephone
Numbers
User,
duplicated
This item defines up to 10 stored telephone numbers (9
numbers plus last number redial), with each telephone
number made up of up to 18 digits, for each of the two analog
(APHONE) WH--10 channels. All such telephone numbers are
priority 4 and the priority is not modifiable. These two sets of
stored telephone numbers can be separate (distinct) or
shared as specified in ORT item xxvi.
xvii
Deleted
xviii
Noise Insertion
Level
Secured,
common
This item defines whether to enable or disable noise insertion
on ground-to-air circuit-mode telephone calls. When noise
insertion is enabled, this item also defines the level, as
selected. Noise insertion minimizes annoying noise
modulation when the GES drops the carrier in the forward
(to--aircraft) direction during speech pauses.
xix
Ground-to-Air
Preemption
User,
common
This item defines whether or not incoming calls of priority 2
and/or 3 automatically preempt (as necessary) a candidate
call as specified in SYSTEM DESCRIPTION. Priority 1
ground-to-air calls unconditionally preempt other calls of lower
priority as necessary.
xx
Preferred Cockpit User,
Call Routing
common
This item defines the routing of ground-initiated cockpit voice
calls to a particular channel when two channels are available.
This item does not affect which channel should be preempted
if both channels are not available. In a dual system, channel
refers to logical channel.
23--20--27
Page C--3
30 Aug 2002
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Table C--1.
UP86308
ORT Item
Characteristic
ORT Characteristics (cont)
Attributes
Description
xxi
Preferred
APHONE Call
Routing
User,
duplicated
When allowed by item xiii, this item defines the routing of
ground-to-air priority 4 calls, when allowed in accordance with
item xiii, to a particular channel when two APHONE channels
are available. In a dual system, this item specifies the
preferred physical channel on each SDU system, or None
when there is no channel wired to APHONE on that system.
xxii
HGA Tx Gain
Threshold
Secured,
common
This item specifies the threshold on the reported HGA Tx gain
for stimulating log-on renewal at Class 1 or automatic
handover.
xxiii
Analog telephone Secured,
(APHONE)
duplicated
System
Management
Commands
This item defines the allowing/disallowing of system
management commands from the analog phone (APHONE)
interface (WH--10 or APBX).
xxiv
Analog telephone User,
(APHONE)
duplicated
Outgoing Call
Barring Level
This item defines one of three levels for analog phone call
barring. Level 0 allows all outgoing calls and the Store Phone
Number Memory command specified in SYSTEM
DESCRIPTION, but disallows six-digit numbers between
42XXXX and 47XXXX if accompanied by credit card data.
Level 1 allows only stored phone numbers, directly dialed
short-code phone numbers, and long dialed numbers from the
APBX accompanied with credit card data to initiate outgoing
calls. Level 1 disallows manually dialed full-length phone
numbers not accompanied with credit card data, six-digit
numbers between 42XXXX and 47XXXX if accompanied by
credit card data, and the Store Phone Number Memory
command. Level 2 disallows all outgoing calls, both manual
and stored numbers, and the Store Phone Number Memory
command.
NOTE: The six-digit numbers between 42XXXX and
47XXXX have been designated air traffic control
(ATC) destinations. These numbers may be dialed
at any priority and are assigned a network ID of 1.
In order to prevent unauthorized use of these
numbers once they become publicly available, the
AES filters these numbers appropriately. The
filtering specified prohibits these numbers from
being dialed with credit card data present based on
the assumption anyone making a call to one of
these numbers using a credit card is not an
authorized user (i.e., a passenger).
xxv
Call Barring
Security Code
This item defines a four-digit password that, if entered
through the analog phone (APHONE), allows call barring
commands (SYSTEM DESCRIPTION) to be accepted.
User,
duplicated
23--20--27
Page C--4
30 Aug 2002
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
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MCS--4000/7000 Multi--Channel SATCOM System
UP86308
Table C--1.
ORT Characteristics (cont)
ORT Item
Characteristic
Attributes
Description
xxvi
Shared Analog
Telephone
(WH--10)
(APHONE)
Number Storage
User,
duplicated
This item defines whether the 10 stored numbers (9 numbers
plus the last number redial) maintained for each of the analog
phone (APHONE) channels are separate or shared (i.e.,
whether a phone number stored on a channel is accessible
by the dial stored phone number command on the other
channel).
xxvii
Deleted
xxviii
Default HPA
Backoff Limits
Secured,
duplicated
This item defines the maximum backoff values for the linear
and class C HPAs. The working (volatile) values are
automatically updated by non zero values (i.e., other than
16 dB) received in the HPA backoff range fields of valid HPA
status words. The nonvolatile entries are not modified with
the received values.
xxix
HPA Minimum
Reportable
Actual Power
Output
Secured,
duplicated
This item defines the minimum values of actual power output
capable of being reported through the HPA status words by
the linear and class C HPAs. When this value or a lower value
is reported in the HPA status word, calibration is inhibited.
xxx
Default Assumed Secured,
Global Beam
common
Initial C--Channel
EIRP
This item defines the default assumed global beam initial
C--channel EIRP. This value is used to assess the power
availability for a C--channel call in the absence of any existing
C--channels.
xxxi
SCDU Telephone Secured,
Number
common
Preselect
This item defines whether selection of a phone number on
one of the CATEGORY NUMBERS pages preselects the
phone number or initiates a call using the phone number. If
this item is enabled, the selection of a phone number on one
of the CATEGORY NUMBERS pages or manual entry of a
phone number on the DIRECTORY page retrieves the
selected number to the SATCOM MAIN MENU page
(TESTING/FAULT ISOLATION), where the number can then
be dialed by selecting the MAKE CALL prompt or by any of
the call initiation methods triggered by activation of an input
discrete.
23--20--27
Page C--5
30 Aug 2002
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
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MCS--4000/7000 Multi--Channel SATCOM System
Table C--1.
ORT Item
xxxii
Characteristic
ACP Call
Initiation
Attributes
Secured,
common
ORT Characteristics (cont)
Description
This item enables/disables ACP call initiation. This item can
only be enabled when item xxxi is enabled. If enabled, one of
the following two pairs of SDU discretes are capable of being
used for call initiation (when the associated cockpit voice call
light outputs are open), based on the state of program pin
TP13K:
• Cockpit voice mic on inputs — if the latched ACP
hookswitch signaling method is strapped.
• Place/End call discrete inputs — if the switched PTT
hookswitch signaling method is strapped.
UP86308
In either case, this item specifies whether the number dialed
should come from the ATC phone number register rather than
the SCDU MAIN menu. If the MAIN menu is selected, the
phone number displayed on the SATCOM MAIN MENU (3L
label line for channel 1, or 5L label line for channel 2) is used
for call initiation. If the ATC menu is selected, the phone
number displayed on the ATC menu is used for call initiation
on either cockpit channel. In a dual system, this item is
enabled if the straps of both SDU systems are identical.
xxxiii
User (or
Composite)
Partition ORT
Description
User,
common
This item defines the 24-character field to describe the ORT.
The ORT description is a 24-character field that annotates a
particular set of options, in order to distinguish one set from
another (e.g., NORTH PACIFIC ROUTE, SOUTH ATLANTIC
ROUTE, 747--400 ASIAN ROUTE, 777 ASIAN ROUTE).
Alternatively, this item could contain a software identification
(e.g., a software part number for the ORT as a released
entity). If the ORT version is for a composite file, the
description field is for the entire ORT and item liii is not used.
See item liii also.
xxxiv
Airline Code
User,
common
This item defines an airline code made up of up to four ISO--5
characters to be used with a four-digit BCD flight number
received from a McDonnell Douglas CFDIU (SYSTEM
DESCRIPTION) in constructing a flight identifier for log-on.
This is only used if the CFDS/CMC/OMS does not supply the
airline code.
xxxv
Headset
Outgoing Call
Barring Level
User,
common
This item defines one of two levels for headset call barring.
Level 0 allows all outgoing calls. Level 1 allows only stored
phone numbers, manually dialed short-code numbers, and
manually dialed numbers with a network ID other than 1. For
Level 1 call barring, all cockpit stored numbers are treated as
protected (i.e., they cannot be modified from the SCDU).
xxxvi
Headset Transit
Call
User,
common
This item either enables or disables transit calls from the
headset for line select key 4L.
23--20--27
Page C--6
30 Aug 2002
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Table C--1.
ORT Item
Attributes
Description
xxxvii
User ORT
User,
Partition Modified common
Flag
This item indicates whether any item in the nonvolatile copy
of the user partition of the ORT partition has been modified
since the ORT was created in a configured state by the
PC-based off-line ORT editing tool. When any user-partition
ORT item is modified in nonvolatile memory by the SDU
software, either directly or indirectly, this flag is set to
modified. This value is never set to unmodified by the SDU
software. Its value is displayed on the SCDU, on the CFDS,
on the front panel display of the SDU, and on the CMT.
xxxviii
Failure Masking
Data
Secured,
common
This item is made up of a list of up to 50 failures (Level I
code, SRU code, and failure code) whose operation is
masked or suppressed. A switch is stored with each specified
failure to indicate whether that failure should never be raised
(i.e., the failure annunciation and reversion should be
suppressed completely), or whether the failure should be
annunciated normally (i.e., recorded and reported as
specified in TESTING/FAULT ISOLATION) when declared,
but not indict the appropriate functional resource specified for
the failure (i.e., not take any other action in response to the
failure, such as reconfiguring redundant resources). Unused
entries in this table are represented by the Level I code, SRU
code, and failure code all set to zero.
xxxix
Elevation
Handover
Threshold
Secured,
common
This item, ranging in integer degrees between 0° and 90°, is
used in combination with calculated elevation of the highest
satellite to determine at what elevation to initiate a handover
from the current satellite. This item is also used to determine
when a satellite is not high enough in elevation to be
considered in view for acquisition purposes by the automatic
log-on process.
High Rate Data
User,
Transmit Support common
This item made up of two flags that specify (by being set to
enabled or disabled) whether the SDU indicates support for
10,500 bps R-- and T--channels in its log-on request of class
2, 3, and 4 (i.e., when using a high gain antenna), for the
global beam and spot beam log-on requests, respectively.
xl
UP86308
Characteristic
ORT Characteristics (cont)
23--20--27
Page C--7
30 Aug 2002
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
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MCS--4000/7000
Table C--1.
ORT Item
xli
Characteristic
Attributes
Automatic Transit Secured,
Call GES Table
common
ORT Characteristics (cont)
Description
This item indicates the transit GES ID to be specified in an
air-to-ground call setup request (SYSTEM DESCRIPTION) if
no transit GES ID has been explicitly specified through the
initiating user interface (APHONE, Headset, DPHONE). If the
GES ID in the table is 377 octal (indicating null), then the
log-on GES is used in the call setup request. For each
satellite ID of 0, 1, 2, and 3, the table stores a GES ID to be
used with the following types of calls:
• Any PSTN long number call (i.e., with network ID 1, with
between 7 and 18 digits, beginning with 00) with country
code beginning with 1 (i.e., North America)
• Any PSTN long number call with a country code beginning
with 2 (i.e., Africa)
• Any PSTN long number call with a country code beginning
with 3 (i.e., South and West Europe)
• Any PSTN long number call with a country code beginning
with a 4 (i.e., North and East Europe)
• Any PSTN long number call with a country code beginning
with a 5 (i.e., South America)
• Any PSTN long number call with a country code beginning
with a 6 (i.e., South East Asia and Australia)
• Any PSTN long number call with a country code beginning
with a 7 (i.e., Soviet Union)
• Any PSTN long number call with a country code beginning
with an 8 (i.e., Far East)
• Any PSTN long number call with a country code beginning
with a 9 (i.e., India and Middle East)
• Any PSTN short number call (i.e., network ID of 1, with
between 2 and 6 digits not beginning with 00)
The geographical region associated with each zone is
approximate; refer to Table C--1 for details of individual
country codes.
UP86308
xlii
Air-to-Ground
Chime
Secured,
common
This item defines one of three chime options. These options
only affect air-to-ground chime activation for call annunciation
and the setting of SDU-to-ACARS MU/CMU status word bits.
The first option is to always chime and always set the
appropriate bits. The second option is to chime and set the
appropriate bits only if the call was camped-on. The third
option is to never chime and never set the bits.
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page C--8
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Table C--1.
UP86308
ORT Item
Characteristic
Attributes
ORT Characteristics (cont)
Description
xliii
SCDU Call
Prompts
Secured,
common
This item defines one of three levels of SCDU call prompt
display. Level 0 causes all SCDU call prompts to be
displayed. Level 1 causes the ANSWER CALL, REJECT, and
END CALL prompts to not be displayed. Level 2 causes the
MAKE CALL prompt and the Level 1 prompts to not be
displayed. Level 2 is selectable only if ORT item xxxii is
enabled.
xliv
EIRP Overdraft
Checking Priority
Secured,
common
This item defines the call priority level where at least one call
must be in progress when considering if an EIRP overdraft is
allowed.
xlv
Analog
Telephone
(APHONE)
Called Terminal
ID Assignment
User,
duplicated
This item provides for the assignment of a three-digit called
terminal identification (CTid) code to each APHONE channel
routing ground-to-air priority 4 calls to the APHONE interface,
based on the called terminal field in the call announcement
signal unit. The CTid assigned can be any decimal value
between --1 and 999. A CTid value of --1 represents no
specific routing.
This item also specifies a CTid assignment type of exclusive
or nonexclusive for each channel. The assignment type
defaults to nonexclusive if no CTid is assigned. An
assignment type of exclusive with no CTid assigned is
undefined and is not selectable. With a CTid assigned, an
assignment type of exclusive inhibits all incoming calls from
being routed to the associated channel unless the call
announcement contains a CTid that matches the assigned
value. An assignment type of nonexclusive allows all
incoming calls to be routed to the associated channel unless
the call announcement contains a CTid that matches the
assigned value of the other channel. Regardless of the
assignment type, an incoming call with a matching CTid is
rejected if the associated channel is unavailable.
Modifications of this item through the APHONE or CMT are
checked for duplication with the other APHONE channel in
the SDU and, in a dual system, with the APHONE channels in
the other SDU.
The primary use of this ORT item is to let incoming facsimile
calls be routed to the channel connected to the facsimile
machine.
xlvi
Cockpit Audio
Level Settings
Secured,
common
This item defines the level settings for the cockpit
microphone, sidetone, and receive audio.
xlvii
HGA Retry
Period (ground
and air)
Secured,
common
This item defines the time interval for ground and airborne
cases after which SATCOM (when logged on through the
LGA) is to make attempts to logon through the HGA. A value
of 0 disables the periodic retry for each case. The time
interval is in integer minutes ranging from 0 to 255.
23--20--27
Page C--9
30 Aug 2002
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000 Multi--Channel SATCOM System
Table C--1.
ORT Item
UP86308
xlviii
Characteristic
Attributes
Cockpit Channel Secured,
Interface Type for common
Dual
ORT Characteristics (cont)
Description
This item defines the functional mapping of the one to four
potentially available physical SDU cockpit voice channels in a
dual system to the one or two logical cockpit voice channels
(as viewed from the perspective of the ACP and SCDU). It is
used in combination with ORT item vi and system
configuration pins TP13F and TP13J to determine the
number of logical channels and which physical channel(s)
is/are potentially available for each logical channel.
This item is capable of taking on the states of fixed and
shared. Fixed interfacing is interfacing each ACP/SCDU
(logical) channel to one physical channel on one SDU only.
Shared interfacing is interfacing each ACP/SCDU logical
channel to one physical channel on each of the two SDUs.
The fixed or shared interfacing declaration refers to the
functional channel mapping, and not necessarily to the
physical interwiring, e.g., the interwiring can be independent
but the interface can be effectively shared by virtue of
splitting/combining/paralleling within the AMS (as in the
Boeing 777), or the interwiring can be literally paralleled,
forcing the interface type to shared.
In the case of two logical channels, it is assumed the single
value for this item applies to both channels (i.e., both fixed or
both shared). For the case of shared (for one or two logical
channels), it is assumed each logical channel shares the
same numbered physical channel on each SDU.
The state of this item is checked for compatibility with the
state of pins TP13F and TP13J of both SDUs and the state of
ORT item vi of both SDUs.
23--20--27
Page C--10
30 Aug 2002
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
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MCS--4000/7000 Multi--Channel SATCOM System
Table C--1.
ORT Item
il
Characteristic
Mastery
Handover
Algorithm
Weighting
Attributes
User,
common
ORT Characteristics (cont)
Description
This item stores the relative weighting factors for each of the
six functional capability items that form the criteria for
determining which system should automatically become the
master in a dual system. Each of the six weighting factors is a
non-negative integer ranging from 0 to 99. Higher factors
indicate more important criteria; however, only the relative
values of the factors is significant. Zero is used to indicate a
capability factor not installed, not used, or is a don’t care. The
functional capability items are as follows:
• CoV -- Cockpit voice (for any number of channels).
• CaV -- Cabin circuit-mode voice/fax/data
(any number of channels, any cabin interface).
• CoL -- Cockpit packet-mode data
(through [C]MU) at low-rate only.
• CoH -- Cockpit packet-mode data
(through [C]MU) at (potentially) high-rate.
• CaL -- Cabin packet-mode data
(through CPDF or CTU) at low rate only.
• CaH -- Cabin packet-mode data (through CPDF or CTU) at
(potentially) high-rate.
UP86308
CoL and CoH are mutually exclusive, as are CaL and
CaH — i.e., regardless of the weighting factors assigned, no
more than one of the cockpit data (or cabin data) capabilities
can be true at a time.
The primary practical use of this ORT item is for determining
which SDU in a dual system should be the master when the
choice is down to one system which only has voice capability
vs one which only has data capability, or one with only cockpit
services capabilities vs one with only cabin services
capabilities.
Disable/Reenable Secured,
Other SATCOM
common
SCDU Prompts
This item determines if the disable other SATCOM and
re--enable other SATCOM toggling SCDU prompts are
presented or suppressed. The SCDU prompts are usually
suppressed if the optional external manual switch (that
controls the dual system select and disable discretes) is
supplied so there is only one means of performing any
function at a time and the possibility of inadvertently disabling
both systems is avoided.
li
SCDU SATCOM
Subsystem
Prompts
This item defines up to six ISO--5 characters used for the
SCDU main menu SATCOM subsystem selection LSK
prompts. The owner/operator is able to select any ISO--5
characters and any length up to six characters. Example
character strings would be SAT L and SAT R, or PROGRAM MEMORY CRC FAIL
01
87/07
PP/CM
CODA
TIMING GENERATOR FAIL
01
88
PP
CODA
DUAL PORT RAM FAIL CODEC SIDE
01
8A/0A
PP/CM
CODA
PROGRAM MEMORY W/R FAIL
01
8B
PP
CODA
DSP INTERNAL MEMORY W/R FAIL
01
8C/0C
PP/CM
CODA
DSP COMPREHENSIVE FAIL
01
0D
CM
SMPM
HEALTH COUNT UPDATE
01
8E
PP
SMPM
DUAL PORT RAM FAIL SMPM SIDE
01
90
PP
SMPM
BUS ERROR
01
91
PP
SMPM
SELF TEST MISOPERATION
01
12
CM
SMPM
COMMUNICATION PROBLEM
01
94
PP
SMPM
ST BUS AUDIO LOOPBACK FAIL
01
95
PP
SMPM
SW DOWNLOAD FAIL
CODB: SDU VOICE CODEC MODULE B
01 3 Same entries as for CODA above except substitute CODB for CODA, SRU code 3 for code 2, [CODEC_B] for [CODEC_A] and
for .
Fault codes for codecs C--F have Level 2 (SRU) codes E--H. They are listed in the appropriate section of this table for those SRU codes.
SIOM: SDU INPUT/OUTPUT MODULE (EXCLUSIVE TO SIOM)
01
81
PP
SMPM
A429 XMTR LOOP--BACK TO OTHER SDU FAIL
01
82
PP
SMPM
A429 XMTR LOOP--BACK TO CFDS FAIL
01
83
PP
SMPM
A429 XMTR LOOP--BACK TO ADL FAIL
01
84
PP
SMPM
A429 XMTR LOOP--BACK TO PDL FAIL
01
85
PP
SMPM
A429 XMTR LOOP--BACK TO (C)MUs FAIL
01
86
PP
SMPM
A429 XMTR LOOP--BACK TO SCDUs FAIL
01
87
PP
SMPM
A429 XMTR LOOP--BACK TO MULTI--CNTRL FAIL
01
89
PP
SMPM
A429 XMTR LOOP--BACK TO RMP/CAP FAIL
01
8A
PP
SMPM
A429 XMTR LOOP--BACK TO SNU/CPDF FAIL
01
8B
PP
SMPM
A429 XMTR LOOP--BACK TO HSU1 FAIL
01
8C
PP
SMPM
A429 XMTR LOOP--BACK TO HSU2 FAIL
01
8D
PP
SMPM
A429 XMTR LOOP--BACK SPARE
01
8E
PP
SMPM
A429 XMTR LOOP--BACK SPARE
01
8F
PP
SMPM
A429 XMTR LOOP--BACK SPARE
01
90
PP
SMPM
A429 XMTR LOOP--BACK SPARE
01
AB
PP
SMPM
SIOM BUS ERROR
01
2C
CM
SMPM
A429 TX TO OTHER SDU BUFFER FULL
01
2D
CM
SMPM
A429 TX TO CFDS BUFFER FULL
01
2E
CM
SMPM
A429 TX TO ADL BUFFER FULL
01
2F
CM
SMPM
A429 TX TO PDL BUFFER FULL
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page D--1
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
UP86308
LEVEL 1 SRU
FAILURE MONITORING
TESTER FAILURE DESCRIPTION
01
30
CM
SMPM
A429 TX TO (C)MUs BUFFER FULL
01
31
CM
SMPM
A429 TX TO SCDUs BUFFER FULL
01
32
CM
SMPM
A429 TX TO MULTI--CTRL BUFFER FULL
01
34
CM
SMPM
A429 TX TO RMP/CAP BUFFER FULL
01
35
CM
SMPM
A429 TX TO SNU/CPDF BUFFER FULL
01
36
CM
SMPM
A429 TX TO HSU1 BUFFER FULL
01
37
CM
SMPM
A429 TX TO HSU2 BUFFER FULL
01
38
CM
SMPM
A429 TX BUFFER FULL SPARE
01
39
CM
SMPM
A429 TX BUFFER FULL SPARE
01
3A
CM
SMPM
A429 TX BUFFER FULL SPARE
01
3B
CM
SMPM
A429 TX BUFFER FULL SPARE
01
BC
PP
SMPM
SIOM INTERRUPT FAIL
01
3D
CM
SMPM
IRS ASIC MATCHING PROBLEM
SMDM1: SDU MODEM MODULE #1
01
81
PP
SMDM1 PROCESSOR FAIL
01
84/04
PP/CM
SMDM1 PROGRAM CRC FAIL
01
0A
CM
SMDM1 MODEM TO RFM INTERFACE FAIL
01
8B
PP
SMDM1 TIMER/INTERRUPT FAIL
01
8E
PP
SMDM1 EXTERNAL MEMORY FAIL
01
91
PP
SMDM1 MODEM DPR FAIL
01
95
PP
SMPM
SMPM SIDE DPR FAIL
01
16
CM
SMPM
SW DOWNLOAD FAIL
01
17
CM
SMPM
HEALTH COUNT UPDATE FAIL
01
99
PP
SMPM
BUS ERROR
01
9A
PP
SMPM
SELF TEST MISOPERATION
01
1B
CM
SMDM1 SOFTWARE FAIL
01
1C
CM
SMPM
COMMUNICATIONS PROBLEM
01
9E
PP
SMPM
RFM SSI LOOPBACK FAIL
SMDM2: SDU MODEM MODULE #2
01 6 Same entries as for SMDM1 above except substitute SMDM2 for SMDM1, SRU code 6 for code 5, [MODEM_2] for [MODEM_1] and
for .
SMDM3: SDU MODEM MODULE #3
01 7 Same entries as for SMDM1 above except substitute SMDM3 for SMDM1, SRU code 7 for code 5, [MODEM_3] for [MODEM_1] and
for .
Fault codes for modems 4--7 have Level 2 (SRU) codes J, L, M and N. They are listed in this table in the appropriate section for those SRU
codes.
SRFM: SDU RADIO FREQUENCY MODULE
01
8E/0E
PP/CM
01
90/10
PP/CM
01
92/12
PP/CM
01
96/16
PP/CM
01
97/17
PP/CM
01
98/18
PP/CM
01
99/19
PP/CM
01
9A/1A
PP/CM
01
9B/1B
PP/CM
01
9C/1C
PP/CM
01
9D/1D
PP/CM
01
9E/1E
PP/CM
01
A0
PP
01
A1
PP
01
A2
PP
01
A3
PP
01
A4
PP
01
A5
PP
01
A6
PP
01
A7
PP
01
A8
PP
01
A9
PP
01
AA
PP
01
AB
PP
01
AC
PP
01
AD
PP
01
AE
PP
01
AF
PP
01
30
CM
01
31
CM
01
32
CM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
SMPM
RF SYNTH CHAN1 LOCK DETECT FAIL
RF SYNTH CHAN2 LOCK DETECT FAIL
RF SYNTH CHAN3 LOCK DETECT FAIL
RF SYNTH CHAN4 LOCK DETECT FAIL
RF SYNTH CHAN5 LOCK DETECT FAIL
RF SYNTH CHAN6 LOCK DETECT FAIL
RF SYNTH CHAN7 LOCK DETECT FAIL
RF SYNTH CHAN8 LOCK DETECT FAIL
RF SYNTH TX BLOCK PLO LOCK DETECT FAIL
RF SYNTH RX BLOCK PLO LOCK DETECT FAIL
RF SYNTH RX CHAN PLO LOCK DETECT FAIL
RF SYNTH TX DOPPLER PLO LOCK DETECT FAIL
RFM CHAN 1 L--BAND LOOP--BACK (TX) FAIL
RFM CHAN 1 L--BAND LOOP--BACK (RX) FAIL
RFM CHAN 2 L--BAND LOOP--BACK (TX) FAIL
RFM CHAN 2 L--BAND LOOP--BACK (RX) FAIL
RFM CHAN 3 L--BAND LOOP--BACK (TX) FAIL
RFM CHAN 3 L--BAND LOOP--BACK (RX) FAIL
RFM CHAN 4 L--BAND LOOP--BACK (TX) FAIL
RFM CHAN 4 L--BAND LOOP--BACK (RX) FAIL
RFM CHAN 5 L--BAND LOOP--BACK (TX) FAIL
RFM CHAN 5 L--BAND LOOP--BACK (RX) FAIL
RFM CHAN 6 L--BAND LOOP--BACK (TX) FAIL
RFM CHAN 6 L--BAND LOOP--BACK (RX) FAIL
RFM CHAN 7 L--BAND LOOP--BACK (TX) FAIL
RFM CHAN 7 L--BAND LOOP--BACK (RX) FAIL
RFM CHAN 8 L--BAND LOOP--BACK (TX) FAIL
RFM CHAN 8 L--BAND LOOP--BACK (RX) FAIL
RFM CHAN 1 TX CALIBRATION ERROR
RFM CHAN 2 TX CALIBRATION ERROR
RFM CHAN 3 TX CALIBRATION ERROR
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page D--2
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
UP86308
LEVEL 1 SRU
FAILURE MONITORING
TESTER FAILURE DESCRIPTION
01
33
CM
SMPM
RFM CHAN 4 TX CALIBRATION ERROR
01
34
CM
SMPM
RFM CHAN 5 TX CALIBRATION ERROR
01
35
CM
SMPM
RFM CHAN 6 TX CALIBRATION ERROR
01
36
CM
SMPM
RFM CHAN 7 TX CALIBRATION ERROR
01
37
CM
SMPM
RFM CHAN 8 TX CALIBRATION ERROR
01
38
CM
SMPM
RFM CHAN 1 RX CALIBRATION ERROR
01
39
CM
SMPM
RFM CHAN 2 RX CALIBRATION ERROR
01
3A
CM
SMPM
RFM CHAN 3 RX CALIBRATION ERROR
01
3B
CM
SMPM
RFM CHAN 4 RX CALIBRATION ERROR
01
3C
CM
SMPM
RFM CHAN 5 RX CALIBRATION ERROR
01
3D
CM
SMPM
RFM CHAN 6 RX CALIBRATION ERROR
01
3E
CM
SMPM
RFM CHAN 7 RX CALIBRATION ERROR
01
3F
CM
SMPM
RFM CHAN 8 RX CALIBRATION ERROR
01
C0/40
PP/CM
SMPM
RFM CHAN 1 AGC TELLBACK FAIL
01
C1/41
PP/CM
SMPM
RFM CHAN 2 AGC TELLBACK FAIL
01
C2/42
PP/CM
SMPM
RFM CHAN 3 AGC TELLBACK FAIL
01
C3/43
PP/CM
SMPM
RFM CHAN 4 AGC TELLBACK FAIL
01
C4/44
PP/CM
SMPM
RFM CHAN 5 AGC TELLBACK FAIL
01
C5/45
PP/CM
SMPM
RFM CHAN 6 AGC TELLBACK FAIL
01
C6/46
PP/CM
SMPM
RFM CHAN 7 AGC TELLBACK FAIL
01
C7/47
PP/CM
SMPM
RFM CHAN 8 AGC TELLBACK FAIL
01
C8/48
PP/CM
SMPM
RFM BLOCK AGC TELLBACK FAIL
01
C9
PP
SMPM
I/Q CALIBRATION FAIL
01
D0
PP
SMPM
RFM CHAN 1 AGC CALIBRATION ERROR
01
D1
PP
SMPM
RFM CHAN 2 AGC CALIBRATION ERROR
01
D2
PP
SMPM
RFM CHAN 3 AGC CALIBRATION ERROR
01
D3
PP
SMPM
RFM CHAN 4 AGC CALIBRATION ERROR
01
D4
PP
SMPM
RFM CHAN 5 AGC CALIBRATION ERROR
01
D5
PP
SMPM
RFM CHAN 6 AGC CALIBRATION ERROR
01
D6
PP
SMPM
RFM CHAN 7 AGC CALIBRATION ERROR
01
D7
PP
SMPM
RFM CHAN 8 AGC CALIBRATION ERROR
01
D8
PP
SMPM
RFM BLOCK AGC CALIBRATION ERROR
OCXO: SDU OVEN CONTROLLED CRYSTAL OSCILLATOR
01
01
CM
SMPM
OVEN READY FAIL
SMB: SDU MOTHER BOARD
01
NONE
SPSU: SDU AC OR DC POWER SUPPLY UNIT
01
01
CM
SMPM
PSU TEMP LIMITS FAIL
01
03
CM
SMPM
PSU SECONDARY VOLTAGE FAIL
SFPDM: SDU FRONT PANEL DISPLAY MODULE
01
01
CM
SMPM
TEST (PAST) SWITCH STUCK
01
02
CM
SMPM
MANUAL SCROLL SWITCH STUCK
CODC: SDU VOICE CODEC MODULE C
01 E Same entries as for CODA (01 2 xx) above except substitute CODC for CODA, SRU code E for code 2, [CODEC_C] for [CODEC_A]
and for .
CODD: SDU VOICE CODEC MODULE D
01 F Same entries as for CODA (01 2 xx) above except substitute CODD for CODA, SRU code F for code 2, [CODEC_D] for [CODEC_A]
and for .
CODE: SDU VOICE CODEC MODULE E
01 G Same entries as for CODA (01 2 xx) above except substitute CODE for CODA, SRU code G for code 2, [CODEC_E] for [CODEC_A]
and for .
CODF: SDU VOICE CODEC MODULE F
01 H Same entries as for CODA (01 2 xx) above except substitute CODF for CODA, SRU code H for code 2, [CODEC_F] for [CODEC_A]
and for .
01 I Not used.
SMDM4: SDU MODEM MODULE #4
01 J Same entries as for SMDM1 (01 5 xx) above except substitute SMDM4 for SMDM1, SRU code J for code 5, [MODEM_4] for
[MODEM_1] and for .
01 K Not used.
SMDM5: SDU MODEM MODULE #5
01 L Same entries as for SMDM1 (01 5 xx) above except substitute SMDM5 for SMDM1, SRU code L for code 5, [MODEM_5] for
[MODEM_1] and for .
SMDM6: SDU MODEM MODULE #6
01 M Same entries as for SMDM1 (01 5 xx) above except substitute SMDM6 for SMDM1, SRU code M for code 5, [MODEM_6] for
[MODEM_1] and for .
SMDM7: SDU MODEM MODULE #7
01 N Same entries as for SMDM1 (01 5 xx) above except substitute SMDM7 for SMDM1, SRU code N for code 5, [MODEM_7] for
[MODEM_1] and for .
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page D--3
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
UP86308
LEVEL 1 SRU
FAILURE MONITORING
TESTER FAILURE DESCRIPTION
VIM: VOICE INTERFACE MODULE
01
81
PP
SMPM
CABIN INTERFACE 1 AUDIO LOOPBACK FAIL
01
82
PP
SMPM
CABIN INTERFACE 2 AUDIO LOOPBACK FAIL
01
83
PP
SMPM
COCKPIT INTERFACE 1 AUDIO LOOPBACK FAIL
01
84
PP
SMPM
COCKPIT INTERFACE 2 AUDIO LOOPBACK FAIL
01
85
PP
SMPM
CTU CEPT--E1 AUDIO LOOPBACK FAIL
01
07
CM
SMPM
CABIN AUDIO DISCRETE OUTPUTS LOOPBACK FAIL
01
08
CM
SMPM
COCKPIT AUDIO DISCRETE OUTPUTS LOOPBACK FAIL
01
89
PP
SMPM
CTU CEPT--E1 HDLC LOOPBACK FAIL
01
8A
PP
SMPM
CABIN INTERFACE 1 BUS ERROR
01
8B
PP
SMPM
CABIN INTERFACE 2 BUS ERROR
01
8C
PP
SMPM
COCKPIT INTERFACE 1 BUS ERROR
01
8D
PP
SMPM
COCKPIT INTERFACE 2 BUS ERROR
01
8E
PP
SMPM
CTU CEPT--E1 BUS ERROR
“OTHER” SATCOM SYSTEM
02
01
CM
SMPM
PROTOCOL VERSION NUMBER INCOMPATIBLE
02
02
CM
SMPM
SDU/SDU MESSAGE PROTOCOL ERROR
HSU
Only applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent.
UNKNOWN HSU SRU
03
01
CM
SMPM
HSU SELF--DECLARED FAILURE
03
02
CM
SMPM
HSU WILLIAMSBURG PROTOCOL ALO/ALR FAIL
03
03
CM
SMPM
HSU WILLIAMSBURG PROTOCOL DATA XFER FAIL
03
84
PP
SMPM
HSU SELF--TEST MISOPERATION
03
05
CM
HSCP
HSU SERIAL PORT MIS--WIRING
03
86/06
PP/CM
HSCP
HSU TOTC RESET
03
87/07
PP/CM
HSCP
HSU POC RESET
03
0C
CM
SMPM
HSU CHANNEL 1 FAILURE
03
0D
CM
SMPM
HSU CHANNEL RELEASE ACKNOWLEDGE FAILURE
03
8E/0E
PP/CM
SMPM
HSU RF LOOPBACK INHIBIT FAILURE
03
0F
CM
SMPM
HSU CHANNEL 2 FAILURE
03
10
CM
SMPM
HSU CHANNEL 3 FAILURE
03
11
CM
SMPM
HSU CHANNEL 4 FAILURE
HSCC1: HSU CHANNEL CARD 1
03
01
CM
HSCP
HSU CC1 MODEM FAULT
03
02
CM
HSCP
HSU CC1 MODEM FAILURE
03
03
CM
HSCP
HSU CC1 PERIPHERAL ERROR
03
04
CM
HSCP
HSU CC1 PERIPHERAL FAILURE
03
05
CM
HSCP
HSU CC1 CP SW INCOMPATIBILITY
03
07
CM
HSCP
HSU CC1 RF FAULT
03
08
CM
HSCP
HSU CC1 RF FAILURE
03
09
CM
HSCP
HSU CC1 TAL ERROR
03
0A
CM
HSCP
HSU CC1 MODEM CALIBRATION MISSING
03
0B
CM
HSCP
HSU CC1 TEMPERATURE UNREADABLE
03
0C
CM
HSCP
HSU CC1 OVER TEMPERATURE
03
0E
CM
HSCP
HSU CC1 TURBO FAULT
03
0F
CM
HSCP
HSU CC1 TURBO FAILURE
03
11
CM
HSCP
HSU CC1 VCODEC FAULT
03
12
CM
HSCP
HSU CC1 VCODEC FAILURE
03
93
PP
HSCP
HSU CC1 APPLICATION CODE ERROR
HSCC2: HSU CHANNEL CARD 2
03
01
CM
HSCP
HSU CC2 MODEM FAULT
03
02
CM
HSCP
HSU CC2 MODEM FAILURE
03
03
CM
HSCP
HSU CC2 PERIPHERAL ERROR
03
04
CM
HSCP
HSU CC2 PERIPHERAL FAILURE
03
05
CM
HSCP
HSU CC2 CP SW INCOMPATIBILITY
03
07
CM
HSCP
HSU CC2 RF FAULT
03
08
CM
HSCP
HSU CC2 RF FAILURE
03
09
CM
HSCP
HSU CC2 TAL ERROR
03
0A
CM
HSCP
HSU CC2 MODEM CALIBRATION MISSING
03
0B
CM
HSCP
HSU CC2 TEMPERATURE UNREADABLE
03
0C
CM
HSCP
HSU CC2 OVER TEMPERATURE
03
0E
CM
HSCP
HSU CC2 TURBO FAULT
03
0F
CM
HSCP
HSU CC2 TURBO FAILURE
03
11
CM
HSCP
HSU CC2 VCODEC FAULT
03
12
CM
HSCP
HSU CC2 VCODEC FAILURE
03
93
PP
HSCP
HSU CC2 APPLICATION CODE ERROR
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page D--4
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
UP86308
MCS--4000/7000
LEVEL 1 SRU
FAILURE MONITORING
TESTER FAILURE DESCRIPTION
HSDIO: HSU DATA I/O CARD
03
02
CM
HSCP
HSU UNRECOVERABLE SW / PROTOCOL ERROR
03
03
CM
HSCP
HSU I/O CHANNEL CARD 1 UNSERVICEABLE
03
04
CM
HSCP
HSU I/O CHANNEL CARD 2 UNSERVICEABLE
03
85
PP
HSCP
HSU CONFIGURATION ERROR
03
86
PP
HSCP
HSU I/O PERIPHERAL FAILURE
03
07
CM
HSCP
HSU I/O BOTH CHANNEL CARDS UNSERVICEABLE
03
08
CM
HSCP
HSU I/O RAM FAULT
03
09
CM
HSCP
HSU I/O ROM FAULT
03
0A
CM
HSCP
HSU SW CONFIGURATION ERROR
03
0B
CM
HSCP
HSU PPPoE SESSION FAILURE
HSCP: HSU CONTROL PROCESSOR
03
87/07
PP/CM
HSCP
HSU CP CHANNEL CARD 1 UNRESPONSIVE
03
88/08
PP/CM
HSCP
HSU CP CHANNEL CARD 2 UNRESPONSIVE
03
89/09
PP/CM
HSCP
HSU CP BOTH CHANNEL CARDS UNRESPONSIVE
03
8A/0A
PP/CM
HSCP
HSU DATA I/O CARD UNRESPONSIVE
03
0B
CM
HSCP
HSU CP RAM FAULT
03
0C
CM
HSCP
HSU CP ROM FAULT
03
0D
CM
HSCP
HSU OVER TEMPERATURE
03
0E
CM
HSCP
HSU CHANNEL CARD 1 OVER TEMPERATURE
03
0F
CM
HSCP
HSU CHANNEL CARD 2 OVER TEMPERATURE
03
10
CM
HSCP
HSU BOTH CHANNEL CARDS OVER TEMPERATURE
03
91
PP
HSCP
HSU ADL BUS INTERFACE FAILURE
03
92
PP
HSCP
HSU PDL BUS INTERFACE FAILURE
03
93
PP
HSCP
HSU DATA I/O DUART FAILURE
03
94
PP
HSCP
HSU CHANNEL CARD 1 DUART FAILURE
03
95
PP
HSCP
HSU CHANNEL CARD 2 DUART FAILURE
03
96
PP
HSCP
HSU BOTH CHANNEL CARDS DUART FAILURE
03
97
PP
HSCP
HSU MAINTENANCE INTERFACE DUART FAILURE
03
98
PP
HSCP
HSU DISCRETE OUTPUT FAILURE
03
99
PP
HSCP
HSU BOARD CONFIGURATION/REVISION FAILURE
HOCXO: HSU OVEN-- CONTROLLED 10 MHZ OSCILLATOR
03
01
CM
HSCP
HSU OCXO TIMEOUT
03
02
CM
HSCP
HSU OCXO TEMPERATURE UNSTABLE
HSPSU: HSU POWER SUPPLY UNIT
03
01
CM
HSCP
HSU POWER SUPPLY FAIL
03
02
CM
HSCP
HSU PSU OVER TEMPERATURE
HSCDM: HSU CONFIGURATION DATA MODULE
03
NONE
HSFP: HSU FRONT PANEL
03
81
PP
HSCP
HSU SELF--TEST BUTTON STUCK
HSBP: HSU BACKPLANE
03
NONE
HGA/IGA HPA
This section lists failure codes inclusive of all HPA designs. Each HPA uses the SRU codes appropriate to its design.
UNKNOWN HGA/IGA HPA SRU
04
01
CM
SMPM
STATUS WORD (143) UPDATE RATE FAIL
04
02
CM
SMPM
STATUS WORD (143) DATA FAIL
04
03
CM
SMPM
MNTNC WORD (350) UPDATE RATE FAIL
04
04
CM
SMPM
MNTNC WORD (350) DATA FAIL
04
87
PP
SMPM
SELF--TEST MISOPERATION
04
08
CM
HMPM
RF OVERDRIVE ERROR
04
09
CM
HMPM
RF SUPPLY CURRENT FAIL
04
0A
CM
HMPM
OVER TEMP (COMB/DET) SHUTDOWN
04
0B
CM
SMPM
NO RESPONSE TO CARRIER COMMAND
04
0C
CM
SMPM
FAILURE WARNING W/NO DISC’S SET
04
0D
CM
SMPM
429 MNTNC WORD PSU FAIL (350)
04
0E
CM
SMPM
429 MNTNC WORD INTERNAL RAM FAIL
04
0F
CM
SMPM
429 MNTNC WORD INTERNAL ROM FAIL
04
10
CM
SMPM
CLASS C HPA MAX AVAIL PWR FAIL
04
40
CM
HMPM
SELF--TEST BUTTON STUCK
04
41
-- RESERVED (HP--720 “RF Power Input Low”)
HPSU: HPA AC OR DC POWER SUPPLY UNIT
04
01
CM
HMPM
PSU OVER TEMP SHUTDOWN
04
02
CM
HMPM PSU TEMP SENSOR FAIL
04
03
CM
HMPM PSU BIAS +5VDC FAIL
04
04
CM
HMPM
PSU +28/+25.5 VDC FAIL
04
05
CM
HMPM PSU +5 VDC FAIL
04
06
CM
HMPM
PSU +15 VDC FAIL
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page D--5
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
UP86308
LEVEL 1 SRU
FAILURE MONITORING
04
07
CM
04
08
CM
04
09
CM
04
0A
CM
04
40
CM
04
41
CM
HMPM: HPA MAIN PROCESSOR MODULE
04
81
PP
04
83/03
PP/CM
04
04
CM
04
87
PP
04
88
PP
04
89
PP
04
0A
CM
04
0B
CM
04
8C/0C
PP/CM
04
0D
CM
04
8E/0E
PP/CM
04
90
PP
04
11
CM
04
12
CM
04
93/13
PP/CM
04
94/14
PP/CM
04
95/15
PP/CM
04
96/16
PP/CM
04
17
CM
04
98
PP
04
19
CM
04
9C/1C
PP/CM
04
9D
PP
04
9E
PP
04
A0
PP
04
A2
PP
04
A5
PP
04
A6
PP
04
A7
PP
04
A8
PP
04
29
CM
04
2A
CM
04
2B
CM
04
2C
CM
04
AD/2D
PP/CM
04
2E
CM
04
2F
CM
04
30
CM
04
31
CM
04
B3/33
PP/CM
04
B4
PP
04
35
CM
04
C0
PP
04
C1/41
PP/CM
04
C2
PP
04
C3
PP
04
C4
PP
04
C5
PP
04
C6
PP
04
C7
PP
04
C8
PP
04
C9/49
PP/CM
04
CA/4A
PP/CM
04
CB
PP
04
4C
CM
04
4D
CM
DRIV: HPA RF DRIVER
04
01
CM
04
02
CM
04
03
CM
04
04
CM
TESTER
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
FAILURE DESCRIPTION
PSU --15 VDC FAIL
PSU --85 VDC FAIL
PSU +8 VDC FAIL
PSU +16 VDC FAIL
INTERNAL POWER SUPPLY FAIL
PSU OVER TEMP
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
HMPM
H/W--S/W COMPATIBILITY FAIL
BOOT FLASH MEMORY FAIL
A429 SDU XMTR LOOP--BACK FAIL
A429 MULTICNT RCVR FAIL
A429 ADL RCVR FAIL
A429 PDL--TO--HPA RCVR FAIL
MAINTENANCE MEMORY CRC FAIL
MAINTENANCE MEMORY WRITE FAIL
CALIBRATION MEMORY CRC FAIL
CALIBRATION MEMORY WRITE FAIL
PROGRAM FLASH MEMORY FAIL
RAM FAIL
CPU OVER TEMP SHUTDOWN
CPU TEMP SENSOR FAIL
CPU GND REF FAIL
FAN RELAY DRIVER FAIL
BIAS ENABLE LOOPBACK FAIL
VAR ATTN DRIVER FAIL
FRONT PANEL TEST SWITCH STUCK
WATCHDOG TIMEOUT FAIL
DRIVER GND FAIL
DRIVER TEST -- MUX
DRIVER TEST -- GREEN LED
DRIVER TEST -- RED LED
DRIVER TEST--MUTE ATTENUATOR
DRIVER TEST -- SER DATA CONCATENATE
MUTE INPUT TEST
CPU DEVICE TEST
ACTUAL POWER CALIBRATION
VALIDATION OF UPLOAD
MUTE ATTEN P OUT OF LIMITS
CODE VPP OUT OF LIMITS
MAINT LOG VPP OUT OF LIMITS
CAL MEM VPP OUT OF LIMITS
HGA HPA> ADC REF OUT OF LIMITS
PWR LO OUT OF LIMITS
PSU TEMP LO OUT OF LIMITS
AMPS LO OUT OF LIMITS
SOFTWARE FAULT
DISC OUTPUT TEST -- FAN
RS--422 INTERNAL LOOPBACK FAIL
IGA LNA/DIP ON/OFF DISC LOOP FAIL
I2C INTERFACE FAILURE
RAM FAILURE
KERNAL CODE ERROR
APPLICATION CODE ERROR
CONFIGURATION ERROR
SDU BUS I/F FAILURE
ADL BUS I/F FAILURE
PDL BUS I/F FAILURE
MAINTENANCE DUART FAILURE
DISCRETE OUTPUTS FAILURE
CP TEMP SENSOR FAILURE
BOARD CONFIG/REV FAILURE
I2C INTERFACE FAILURE
ROM FAILURE
HMPM
HMPM
HMPM
HMPM
DRIVER RF OUTPUT FAIL
DRIVER TEMP SENSOR FAIL
DRIVER OVER TEMP SHUTDOWN
DRIVER VCC FAIL
23--20--27
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page D--6
5 Feb 2008
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONAL
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4000/7000
UP86308
LEVEL 1 SRU
FAILURE MONITORING
TESTER FAILURE DESCRIPTION
PWR1: HPA RF POWER AMPLIFIER (1)
04
01
CM
HMPM
RF BALANCE FAIL
04
02
CM
HMPM
VCC FAIL
PWR2: HPA RF POWER AMPLIFIER (2)
04 6 Same as for PWR1 except sub. SRU code 6 for 5 and for .
PWR3: HPA RF POWER AMPLIFIER (3)
04 7 Same as for PWR1 except sub. SRU code 7 for 5 and for .
C/DET: HPA RF POWER COMBINER/DETECTOR
04
01
CM
HMPM
FORWARD OUTPUT POWER DET 1 FAIL
04
02
CM
HMPM
FORWARD OUTPUT POWER DET 2 FAIL
04
03
CM
HMPM
FORWARD OUTPUT PWR COMPARE FAIL
04
04
CM
HMPM REFLECTED OUTPUT PWR DET FAIL
04
05
CM
HMPM COMBINER TEMP SENSOR FAIL
FPAMP: HPA RF FINAL POWER AMPLIFIER
04
01
CM
HMPM
FINAL AMP 1 RF BALANCE FAIL
04
02
CM
HMPM
FINAL AMP 1 VCC FAIL
04
04
CM
HMPM
FINAL AMP 2 RF BALANCE FAIL
04
05
CM
HMPM
FINAL AMP 2 VCC FAIL
04
C0/40
PP/CM
HMPM PA UNRESPONSIVE
04
42
CM
HMPM
OVER CURRENT FAILURE
04
43
CM
HMPM
DRIVER AMPLIFIER DC VOLTAGE FAILURE
04
44
CM
HMPM
DRIVER AMPLIFIER CURRENT FAILURE
04
45
CM
HMPM 12 VDC FAILURE
04
46
CM
HMPM PA MUTE FAILURE
04
47
CM
HMPM
PA OVER TEMP
04
48
CM
HMPM
PA STATUS FAILURE
04
49
CM
HMPM
PA TEMP SENSOR FAILURE
HMB: HPA MOTHER BOARD
04
40
CM
HMPM
BP TEMP SENSOR FAILURE
RFAM: 20W HPA RF AMPLIFIER MODULE
04
01
CM
HMPM
OVER TEMP SHUTDOWN
04
02
CM
HMPM
RFAM VCC FAIL
04
03
CM
HMPM
AMP 1 VCC FAIL
04
04
CM
HMPM
FORWARD OUTPUT POWER DET 1 FAIL
04
05
CM
HMPM
FORWARD OUTPUT POWER DET 2 FAIL
04
06
CM
HMPM REFLECTED OUTPUT PWR DET FAIL
04
07
CM
HMPM
TEMP SENSOR FAIL
04
08
CM
HMPM
FORWARD OUTPUT POWER FAIL
04
09
CM
HMPM
AMP 2 RF BALANCE FAIL
04
0A
CM
HMPM
AMP 2 VCC FAIL
LGA HPA
07 Same entries as for HGA/IGA HPA above except substitute LRU code 7 for code 4, for , and [LGA_SUBSYS]
for [HGA_SUBSYS]. For the cases of conditional HGA subsystem indictments ([cond_HGA_SUBSYS]), the equivalent LGA HPA failures
shall UNconditionally indict [LGA_SUBSYS].
HSU #1
Only applicable prior to SDU Part Number 7516118--XX130/--xx140.
UNKNOWN SRU
08
01
CM
SMPM
SELF--DECLARED FAILURE
08
02
CM
SMPM
WILLIAMSBURG PROTOCOL ALO/ALR FAIL
08
03
CM
SMPM
WILLIAMSBURG PROTOCOL DATA XFER FAIL
08
84
PP
SMPM
SELF--TEST MISOPERATION
08
05
CM
SMPM
CHANNEL RELEASE ACKNOWLEDGE FAILURE
08
86/06
PP/CM
SMPM
RF LOOPBACK INHIBIT FAILURE
HSCPU: CPU
08
FA
PP
HSCPU ACCESS LEVEL DEVELOPMENT
08
FB
PP
HSCPU ACCESS LEVEL PRODUCTION
08
FC
PP
HSCPU ACCESS LEVEL PRODUCTION FAST STARTUP
08
FD
PP
HSCPU SW VERSIONS INCONSISTENCY
08
7F
CM
HSCPU ENVIRONMENT TEMP AT POWER--UP FAIL
08
91
PP
HSCPU TEMP SENSOR FAILURE
FDSMP: FRAME DSP (AND INTERFACES)
08
95
PP
HSCPU FRAME DSP/CPU INTERFACE FAILURE
VSDPM: VFC DSP (AND INTERFACES)
08
98
PP
HSCPU VFC DSP/CPU INTERFACE FAILURE
TFPGA: TURBO FPGA
08
86
PP
HSCPU TURBO FPGA FAIL
ISDNT: