Honeywell SD-720 Satellite Data Unit for MCS-7200 SATCOM System User Manual SDIM Multi Channel SATCOM System A15 5111 010
Honeywell International Inc. Satellite Data Unit for MCS-7200 SATCOM System SDIM Multi Channel SATCOM System A15 5111 010
Contents
- 1. SD-720 Manual Part1
- 2. SD-720 Manual Part2
- 3. SD-720 Manual Part 3
- 4. SD-720 Manual Part4
SD-720 Manual Part1
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| Document ID | 1313886 |
| Application ID | qSDcHpOrLko7i/mvw1kz+g== |
| Document Description | SD-720 Manual Part1 |
| Short Term Confidential | No |
| Permanent Confidential | No |
| Supercede | No |
| Document Type | User Manual |
| Display Format | Adobe Acrobat PDF - pdf |
| Filesize | 265.63kB (3320367 bits) |
| Date Submitted | 2010-07-19 00:00:00 |
| Date Available | 2010-07-19 00:00:00 |
| Creation Date | 2017-11-08 17:49:22 |
| Producing Software | GPL Ghostscript 9.18 |
| Document Lastmod | 2017-11-08 17:49:22 |
| Document Title | SDIM:Multi-Channel SATCOM System:A15-5111-010 |
| Document Author: | ATR |
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 TO HOLDERS OF MULTI-CHANNEL SATCOM SYSTEM, SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL WITH ILLUSTRATED PARTS LIST 23-20-35, REVISION 0, DATED 15 JUL 2006. INSERT THIS PAGE AS THE FIRST PAGE OF THE MANUAL. Temporary Revision Number 23-1 Applicable Page Number TC-9 INTRO-5 INTRO-6 INTRO-7 INTRO-8 1-1 1-3 1-4 1-5 1-6 1-7/1-8 1-9 1-10 1-11 1-12 1-13 1-14 1-15 1-17 1-18 1-21 1-22 1-23 1-24 1-25 1-45 2-1 2-3 2-8 23-20-35 Publication Number A15-5111-010 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 2-9 2-13 2-14 2-15 2-19 2-20 3-1 5-41/5-42 5-57 5-64 6-96 6-100 6-108 6-116 C-15 C-16 D-11 F-21 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 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. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2 of 53 28 Sep 2009 Honeywell International Inc. 21111 N. 19th Ave. Phoenix, AZ 85027-2708 U.S.A. (CAGE 55939) Telephone: (800) 601--3099 (U.S.A.) Telephone: (602) 365--3099 (International) System Description, Installation, and Maintenance Manual with illustrated parts list Multi--Channel SATCOM System System Designation MCS--4200 MCS--7200 Type 4--Channel 7--Channel 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. 23--20--35 Page T--1 Publication Number A15--5111--010, Revision 000 15 Jul 2006 Honeywell International Inc. Do not copy without express permission of Honeywell. SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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. Honeywell Materials License Agreement The documents and information contained herein (“the Materials”) are the proprietary data of Honeywell International Inc. and Honeywell Intellectual Properties Inc (collectively “Honeywell”). These Materials are provided for the exclusive use of Honeywell Service Centers; Honeywell--authorized repair facilities; operators of Honeywell aerospace products subject to an applicable product support agreement, their wholly owned--subsidiaries or a formally designated third party service provider thereunder; and direct recipients of Materials from Honeywell’s Aerospace Technical Publication Distribution. The terms and conditions of this License Agreement govern your use of these Materials, except to the extent that any terms and conditions of another applicable agreement with Honeywell regarding the operation, maintenance, or repair of Honeywell aerospace products conflict with the terms and conditions of this License Agreement, in which case the terms and conditions of the other agreement will govern. However, this License Agreement will govern in the event of a conflict between its terms and conditions and those of a purchase order or acknowledgement. 1. License Grant -- If you are a party to an applicable product support agreement, a Honeywell Service Center agreement, or an authorized repair facility agreement, Honeywell hereby grants you a limited, non--exclusive license to use these Materials to operate, maintain, or repair Honeywell aerospace products only in accordance with that agreement. If you are a direct recipient of these Materials from Honeywell’s Aerospace Technical Publication Distribution and are not a party to an agreement related to the operation, maintenance or repair of Honeywell aerospace products, Honeywell hereby grants you a limited, non--exclusive license to use these Materials to maintain or repair the subject Honeywell aerospace products only at the facility to which these Materials have been shipped (“the Licensed Facility”). Transfer of the Materials to another facility owned by you is permitted only if the original Licensed Facility retains no copies of the Materials and you provide prior written notice to Honeywell. 2. Rights In Materials -- Honeywell retains all rights in these Materials and in any copies thereof that are not expressly granted to you, including all rights in patents, copyrights, trademarks, and trade secrets. No license to use any Honeywell trademarks or patents is granted under this License Agreement. 3. Confidentiality -- You acknowledge that these Materials contain information that is confidential and proprietary to Honeywell. You agree to take all reasonable efforts to maintain the confidentiality of these Materials. 4. Assignment And Transfer -- This License Agreement may be assigned to a formally designated service designee to the extent allowed under an applicable product support agreement or transferred to a subsequent owner or operator of an aircraft containing the subject Honeywell aerospace products. However, the recipient of any such assignment or transfer must assume all of your obligations under this License Agreement. No assignment or transfer shall relieve any party of any obligation that such party then has hereunder. 5. Copies of Materials -- Unless you have the express written permission of Honeywell, you may not make or permit making of copies of the Materials. Notwithstanding the foregoing, you may make copies of only portions of the Material for your internal use. You agree to return the Materials and any copies thereof to Honeywell upon the request of Honeywell. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page T--2 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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 Agreement or will terminate simultaneously with the termination or expiration of your applicable product support agreement, authorized repair facility agreement, or your formal designation as a third party service provider. Upon termination of this License Agreement, you will return these Materials to Honeywell without retaining any copies and will have one of your authorized officers certify that all Materials have been returned with no copies retained. 7. Remedies -- Honeywell reserves the right to pursue all available remedies and damages resulting from a breach of this License Agreement. 8. Limitation of Liability -- Honeywell does not make any representation regarding the use, accuracy or sufficiency of the Materials. THERE ARE NO OTHER WARRANTIES, WHETHER WRITTEN OR ORAL, EXPRESS, IMPLIED OR STATUTORY, INCLUDING, BUT NOT LIMITED TO, (i) WARRANTIES ARISING FROM COURSE OF PERFORMANCE, DEALING, USAGE, OR TRADE, WHICH ARE HEREBY EXPRESSLY DISCLAIMED, OR (ii) WARRANTIES AGAINST INFRINGEMENT OF INTELLECTUAL PROPERTY RIGHTS OF THIRD PARTIES, EVEN IF HONEYWELL HAS BEEN ADVISED OF ANY SUCH INFRINGEMENT. IN NO EVENT WILL HONEYWELL BE LIABLE FOR ANY INCIDENTAL DAMAGES, CONSEQUENTIAL DAMAGES, SPECIAL DAMAGES, INDIRECT DAMAGES, LOSS OF PROFITS, LOSS OF REVENUES, OR LOSS OF USE, EVEN IF INFORMED OF THE POSSIBILITY OF SUCH DAMAGES. TO THE EXTENT PERMITTED BY APPLICABLE LAW, THESE LIMITATIONS AND EXCLUSIONS WILL APPLY REGARDLESS OF WHETHER LIABILITY ARISES FROM BREACH OF CONTRACT, WARRANTY, TORT (INCLUDING BUT NOT LIMITED TO NEGLIGENCE), BY OPERATION OF LAW, OR OTHERWISE. 9. Controlling Law -- This License shall be governed and construed in accordance with the laws of the State of New York without regard to the conflicts of laws provisions thereof. This license sets forth the entire agreement between you and Honeywell and may only be modified by a writing duly executed by the duly authorized representatives of the parties. Copyright -- Notice Copyright 2006, Honeywell International Inc. All rights reserved. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page T--3 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Blank Page 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page T--4 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System RECORD OF REVISIONS For each revision, put the changed pages in your manual and discard the replaced pages. Write the revision number and date, and the date put in the manual. Put your initials in the applicable columns on the Record of Revisions. The initial H shows that Honeywell put the changed pages in the manual. Revision Number Revision Date Date Put In Manual By Revision Number Revision Date 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Date Put In Manual By Page RR--1 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Blank Page 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page RR--2 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 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 Temporary Revision Status Date Put in Manual By * Date Removed from Manual By * * The initial H in this column shows Honeywell has done this task. ** Temporary revisions are incorporated in the manual by normal revision. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page RTR--1 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Blank Page 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page RTR--2 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System SERVICE BULLETIN LIST Service Bulletin Identified Mod Date Included in this Manual Description 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page SBL--1 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Blank Page 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page SBL--2 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System LIST OF EFFECTIVE PAGES Subeading and Page Date Title T--1 T--2 T--3 T--4 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Record of Revisions RR--1 RR--2 15 Jul 2006 15 Jul 2006 Record of Temporary Revisions RTR--1 RTR--2 15 Jul 2006 15 Jul 2006 Service Bulletin List SBL--1 SBL--2 15 Jul 2006 15 Jul 2006 List of Effective Pages LEP--1 LEP--2 LEP--3 LEP--4 LEP--5 LEP--6 LEP--7 LEP--8 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Table of Contents TC--1 TC--2 TC--3 TC--4 TC--5 TC--6 TC--7 TC--8 TC--9 TC--10 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Subeading and Page TC--11 TC--12 TC--13 TC--14 TC--15 TC--16 Date 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Introduction INTRO--1 INTRO--2 INTRO--3 INTRO--4 INTRO--5 INTRO--6 INTRO--7 INTRO--8 INTRO--9 INTRO--10 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 System Description 1--1 1--2 1--3 1--4 1--5 1--6 F 1--7/1--8 1--9 1--10 1--11 1--12 1--13 1--14 1--15 1--16 1--17 1--18 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 indicates a foldout page. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page LEP--1 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Date Subeading and Page 1--19/1--20 1--21 1--22 1--23 1--24 1--25 1--26 1--27 1--28 1--29 1--30 1--31 1--32 1--33 1--34 1--35 1--36 1--37 1--38 1--39 1--40 1--41 1--42 1--43 1--44 1--45 1--46 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 System Operation 2--1 2--2 2--3 2--4 2--5 2--6 2--7 2--8 2--9 2--10 2--11 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Subeading and Page 2--12 2--13 2--14 2--15 2--16 2--17 2--18 2--19 2--20 2--21 2--22 2--23 2--24 2--25 2--26 2--27 2--28 Date 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 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 3--12 3--13 3--14 3--15 3--16 3--17 3--18 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Mechanical Installation 4--1 4--2 15 Jul 2006 15 Jul 2006 indicates a foldout page. 23--20--35 Honeywell International Inc. 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Page LEP--2 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Subeading and Page Date 4--3 4--4 4--5/4--6 4--7/4--8 4--9/4--10 4--11/4--12 4--13/4--14 4--15/4--16 4--17/4--18 4--19/4--20 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Electrical Installation 5--1 5--2 5--3 5--4 5--5 5--6 5--7 5--8 5--9/5--10 5--11/5--12 5--13 5--14 5--15/5--16 5--17/5--18 5--19 5--20 5--21 5--22 5--23/5--24 5--25/5--26 5--27/5--28 5--29 5--30 5--31/5--32 5--33 5--34 5--35 5--36 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Subeading and Page 5--37/5--38 5--39/5--40 5--41/5--42 5--43/5--44 5--45/5--46 5--47/5--48 5--49/5--50 5--51/5--52 5--53/5--54 5--55/5--56 5--57 5--58 5--59 5--60 5--61 5--62 5--63 5--64 5--65 5--66 5--67 5--68 5--69 5--70 5--71 5--72 5--73 5--74 Date 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Testing/Fault Isolation 6--1 6--2 6--3 6--4 6--5 6--6 6--7 6--8 6--9 6--10 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 indicates a foldout page. 23--20--35 Honeywell International Inc. 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Page LEP--3 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Date Subeading and Page 6--11 6--12 6--13 6--14 6--15 6--16 6--17 6--18 6--19 6--20 6--21 6--22 6--23 6--24 6--25 6--26 F 6--27/6--28 6--29 6--30 6--31 6--32 6--33 6--34 6--35 6--36 6--37 6--38 6--39 6--40 6--41 6--42 6--43 6--44 6--45 6--46 6--47 6--48 6--49 6--50 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Subeading and Page 6--51 6--52 6--53 6--54 6--55 6--56 6--57 6--58 6--59 6--60 6--61 6--62 6--63 6--64 6--65 6--66 6--67 6--68 6--69 6--70 6--71 6--72 6--73 6--74 6--75 6--76 6--77 6--78 6--79 6--80 6--81 6--82 6--83 6--84 6--85 6--86 6--87 6--88 6--89 Date 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 indicates a foldout page. 23--20--35 Honeywell International Inc. 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Page LEP--4 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Subeading and Page Date 6--90 6--91 6--92 6--93 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 6--113 6--114 6--115 6--116 6--117 6--118 6--119 6--120 6--121 6--122 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Maintenance Practices 7--1 7--2 7--3 7--4 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Subeading and Page 7--5 7--6 Date 15 Jul 2006 15 Jul 2006 Appendix A Vendor Equipment A--1 A--2 A--3 A--4 A--5/A--6 A--7/A--8 A--9/A--10 A--11/A--12 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 A--31 A--32 A--33 A--34 A--35 A--36 A--37 A--38 A--39 A--40 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 indicates a foldout page. 23--20--35 Honeywell International Inc. 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Page LEP--5 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Date Subeading and Page Appendix B Installation Procedures For SATCOM Air Filtration B--1 B--2 B--3 B--4 F B--5/B--6 B--7 B--8 B--9 B--10 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Appendix C Owner Requirements Table C--1 C--2 C--3 C--4 C--5 C--6 C--7 C--8 C--9 C--10 C--11 C--12 C--13 C--14 C--15 C--16 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Appendix D Call Events Log (CEL) D--1 D--2 D--3 D--4 D--5 D--6 D--7 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Subeading and Page D--8 D--9 D--10 D--11 D--12 D--13 D--14 D--15 D--16 Date 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Appendix E Messaging E--1 E--2 E--3 E--4 E--6 E--7 E--8 E--9 E--10 E--11 E--12 E--13 E--14 E--15 E--16 E--17 E--18 E--19 E--20 E--21 E--22 E--23 E--24 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 indicates a foldout page. 23--20--35 Honeywell International Inc. 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Page LEP--6 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Subeading and Page Date Appendix F Failure Overview F--1 F--2 F--3 F--4 F--5 F--6 F--7 F--8 F--9 F--10 F--11 F--12 F--13 F--14 F--15 F--16 F--17 F--18 F--19 F--20 F--21 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Subeading and Page F--22 F--23 F--24 F--25 F--26 F--27 F--28 F--29 F--30 F--31 F--32 F--33 F--34 F--35 F--36 Date 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 Index INDEX--1 INDEX--2 INDEX--3 INDEX--4 INDEX--5 INDEX--6 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 15 Jul 2006 indicates a foldout page. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page LEP--7 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Blank Page 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page LEP--8 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System TABLE OF CONTENTS Subject Page INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--1 1. How to Use This Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--1 B. Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--1 C. Weights and Measurements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--2 Customer Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--2 A. Honeywell Aerospace Online Technical Publications Web Site . . . . . . . . . . . INTRO--2 B. Customer Response Center . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--2 References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--2 A. Honeywell Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--2 B. Other Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--3 Acronyms and Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--3 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--3 Maximum Permissible Exposure Level . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--9 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--9 SECTION 1 SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--1 1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--1 B. Aircraft Earth Station – General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--4 C. Space Segment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--14 D. Ground Earth Station/Land Earth Station . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--14 E. Terrestrial Data and Voice Networks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--14 System Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--16 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--16 System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--17 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--17 B. Satellite Data Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--21 C. High Speed Data Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--23 D. High Power Amplifier . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--24 E. 1--25 2. 3. 4. 5. 2. 3. Avionics Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--1 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Subject Page 4. MCS--4200/7200 Component Descriptions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--25 A. Physical Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--25 B. Satellite Data Unit (SDU) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--25 C. High Speed Data Unit (HSU) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--30 D. High--Power Amplifier (60 Watt) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--34 E. Radio Frequency Unit Interface Adapter (RFUIA) . . . . . . . . . . . . . . . . . . . . . . . 1--38 F. ARINC 429 Data Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--42 G. Nameplates (SDU, HSU, HPA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--42 H. Software and Hardware Compatibility (SDU, HSU and HPA) . . . . . . . . . . . . . 1--44 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--45 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--45 SECTION 2 SYSTEM OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--1 1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--1 AES Management . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--1 B. HSDU Installed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--3 System Log-On/Log-Off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--3 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--3 B. Automatic Log-On . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--5 C. Constrained Log-On . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--6 D. Log-On Mode Selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--6 E. Handover . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--7 F. Log-Off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--7 System Software/Database Updates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--8 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--8 B. Software Upload Process . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--8 C. Validation of the Software Upload File . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--9 Owner Requirements Table . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--10 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--10 ORT Upload/Download Process . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--11 A. 2--11 5. 2. 3. 4. 5. 6. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--2 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Subject B. Page Startup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--11 C. ORT Download . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--11 D. Control Mode ORT Upload Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--11 E. Auto Mode ORT Upload Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--13 Circuit-Mode Services . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--13 A. Circuit-Mode Voice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--13 B. Circuit-Mode Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--13 Packet-Data Services . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--15 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--15 Dual SATCOM Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--16 A. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--16 B. Dual System Control/Status Interfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--17 C. System Reversion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--18 D. Antenna Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2--19 E. Cockpit Voice Configurations and Functionality . . . . . . . . . . . . . . . . . . . . . . . . . 2--27 SECTION 3 CABIN/COCKPIT COMMUNICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--1 1. Cabin Communications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--1 B. Cabin Communications System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--1 C. Analog Audio Channels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--2 Cockpit Communications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--14 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--14 B. Headset Off-Hook Signaling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--14 C. Headset On-Hook Signaling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--15 D. Voice Codec Module Audio Switching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--15 E. Voice Codec Module Sidetone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--15 F. Voice Interface Module Stored Audio Messages . . . . . . . . . . . . . . . . . . . . . . . . 3--15 G. Voice Interface Module Dedication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3--17 SECTION 4 MECHANICAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4--1 1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4--1 A. 4--1 7. 8. 9. 2. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--3 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Subject 2. Page Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4--1 Mechanical Installation Design . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4--1 A. LRU Mechanical Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4--1 B. Installation Dependent Considerations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4--2 C. Owner Requirements Table (ORT) Uploading . . . . . . . . . . . . . . . . . . . . . . . . . . 4--2 D. Cable Loss Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4--2 E. Cooling Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4--3 F. Vendor Supplied Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4--4 SECTION 5 ELECTRICAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--1 1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--1 Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--1 Electrical Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--1 A. Connector Layout and Contact Arrangement . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--1 B. Electrical Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--21 Configuration Pins . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--57 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--57 B. Availability of ARINC 429 ICAO ADDRESS (AES ID) from 429 Ports . . . . . . 5--58 C. FMC Connection to SDU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--60 D. ARINC 429 Speed to/from CMU No. 1 and CMU No. 2 . . . . . . . . . . . . . . . . . . 5--60 E. Cabin Packet Data Function (CPDF) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--61 F. ARINC 429 BUS Speed of AES ID Input . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--61 G. HSU Presence . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--61 H. SDU Controller Type . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--62 I. Call Light On (Air/Ground Calls) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--62 J. Strap Parity (ODD) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--62 K. Cabin Communications System (CCS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--63 L. Inertial Reference System (IRS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--63 M. HPA/Antenna Subsystem Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--64 N. CFDS/CMC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--65 3. 2. 3. 4. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--4 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Subject Page O. SDU Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--66 P. SDU Number . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--66 Q. CMU No. 1 and No. 2 Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--67 R. MCDU/WSC No. 1 thru No. 3 Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--67 S. Priority 4 Calls to/from Cockpit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--68 T. ARINC 429 BUS Speed to MCDU No. 1/MCDU No. 2/MCDU No. 3 . . . . . . . 5--69 U. Cockpit Voice Call Light/Chime Option . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--69 V. SDU CODEC 1 and CODEC 2 Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--70 W. Cockpit Hookswitch Signaling Method . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--70 X. CM--250 CGU Connection Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--72 Y. Cockpit Call Discrete Signaling Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--72 Z. Strap Parity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--73 SECTION 6 TESTING/FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--1 1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--1 B. Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--2 C. Failure Detection and Reporting Levels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--3 D. LRU Coverage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--3 E. Monitoring and Testing Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--4 F. Failure Recording . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--7 G. Failure Reporting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--8 H. Miscellaneous BITE Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--20 I. Maintenance Activity Log . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--20 SATCOM Control and Display Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--21 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--21 B. SCDU Display Terminology and Basic Operation . . . . . . . . . . . . . . . . . . . . . . . 6--21 C. SCDU Page Hierarchy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--25 D. SCDU Pages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--25 Maintenance Computer Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--90 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--90 B. Boeing 747--400 CMC/777 OMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--90 C. Airbus/Douglas CFDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--93 2. 3. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--5 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Subject Page D. Central Aircraft Information and Maintenance System . . . . . . . . . . . . . . . . . . . 6--94 E. Level I Failure Messages and ATA Reference Numbers . . . . . . . . . . . . . . . . . 6--95 SCDU for Dual SATCOM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--121 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--121 B. SATCOM Logical Channels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--121 C. SATCOM (Cross-Talk Bus Failed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--121 D. SATCOM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--121 E. SATCOM Menus . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--121 Maintenance Panel Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--121 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--121 SECTION 7 MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--1 1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--1 Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--1 Procedure for Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--2 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--2 B. Antenna Weather Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--2 C. Antenna Hardware . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--2 D. General Antenna Removal Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--3 Procedure for the LRUs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--3 A. LRU Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--3 B. LRU Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--3 Owner Requirements Table Uploading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--4 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--4 Instructions for Continued Airworthiness, FAR 25.1529 . . . . . . . . . . . . . . . . . . . . . . 7--5 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--5 APPENDIX A VENDOR EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--1 1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--1 Electronic Cable Specialists . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--1 4. 5. 2. 3. 4. 5. 6. 2. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--6 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Subject Page A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--1 B. Radio Frequency Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--1 C. Cable Assembly Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--1 D. Cable Assembly Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--2 E. ARINC 600 Connectors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--2 F. SATCOM Avionics Unit Mounting Hardware . . . . . . . . . . . . . . . . . . . . . . . . . . . A--4 G. SATCOM Hardware Component Kits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--4 H. Air Filtration Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--19 I. SATCOM Shelf Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--19 J. Additional Avionics Installation Components . . . . . . . . . . . . . . . . . . . . . . . . . . . A--19 K. Antenna System Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--19 L. Cabin Communications System Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--19 M. Wire Harnesses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--19 N. Complete Integrated SATCOM Installation Kits . . . . . . . . . . . . . . . . . . . . . . . . . A--20 Hollingsead International . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--20 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--20 B. Engineering Services . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--20 C. LRU Mounting Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--21 D. Installation Kit Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--21 Signal Conditioning Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--26 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--26 B. Operator Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--27 C. Control Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--28 D. System Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--29 E. ARINC 600 Connector Pin Assignments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--33 APPENDIX B INSTALLATION PROCEDURES FOR SATCOM AIR FILTRATION SYSTEMS . . . . . B--1 1. Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B--1 Continued Airworthiness . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B--1 Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B--2 A. B--2 3. 4. 2. 3. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--7 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Subject 4. Page Installation Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B--4 A. Top Mount Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B--4 B. Body--Mounted Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B--8 C. Tray--Mounted Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B--9 APPENDIX C OWNER REQUIREMENTS TABLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C--1 1. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C--1 APPENDIX D CALL EVENTS LOG (CEL) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D--1 1. Call Events Log . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D--1 Commentary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D--4 A. Most Significant Digit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D--4 B. SLCV And Detailed Code Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D--4 C. HSD ISDN Call SLCV And Detailed Codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . D--9 APPENDIX E MESSAGING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E--1 1. PPPoE Messaging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E--1 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E--1 B. PPPoE Active Discovery Offer (PADO) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E--1 C. PPPoE Active Discovery Request (PADR) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E--3 D. PPPoE Active Discovery Session--Confirmation (PADS) . . . . . . . . . . . . . . . . . E--5 E. PPPoE Active Discovery Termination (PADT) . . . . . . . . . . . . . . . . . . . . . . . . . . E--5 APPENDIX F FAILURE OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . F--1 1. Fault Codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . F--1 INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INDEX--1 2. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--8 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 3 OF 53 FACING PAGE TC-9. Reason: To change Four-Region to Seven-Region and to change the capitalization of INMARSAT to Inmarsat for Figure 1-3 in the List of Illustrations in the Table of Contents. The List of Illustrations is changed as follows: Figure 1-3. Inmarsat Seven-Region Satellite Coverage . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . .1-13 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 3 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Illustrations Figure Figure Intro--1. Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Page INTRO--2 Figure Intro--2. Radio Frequency Energy Levels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO--10 Figure 1-1. Aviation Satellite Communications System . . . . . . . . . . . . . . . . . . . . . 1--3 Figure 1-2. Aircraft Earth Station Block Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . 1--7 Figure 1-3. INMARSAT Four-Region Satellite Coverage . . . . . . . . . . . . . . . . . . . 1--13 Figure 1-4. MCS--4200/7200 Avionics Block Diagram . . . . . . . . . . . . . . . . . . . . . . 1--19 Figure 1-5. MCS--7200 SDU Equipment Description . . . . . . . . . . . . . . . . . . . . . . . 1--21 Figure 1-6. Satellite Data Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--27 Figure 1-7. High Speed Data Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--31 Figure 1-8. High Power Amplifier . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--35 Figure 1-9. RFUIA System Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--39 Figure 1-10. Radio Frequency Unit Interface Adapter . . . . . . . . . . . . . . . . . . . . . . . 1--40 Figure 1-11. MCS--4200/7200 SDU LRU Labels . . . . . . . . . . . . . . . . . . . . . . . . . . . 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 HGAs . . . . . . . . . . . . . 2--21 Figure 2-4. HGA + LGA Configuration with Side-Mounted HGAs . . . . . . . . . . . . 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 (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--3 Figure 4-2. SD-700 and SD-720 (7516119) Outline and Installation Diagram . 4--5 Figure 4-3. HP--720 (7520006) Outline and Installation Diagram . . . . . . . . . . . . 4--7 Figure 4-4. RFUIA Outline and Installation Diagram . . . . . . . . . . . . . . . . . . . . . . . 4--13 Figure 2-11. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--9 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Illustrations (cont) Figure Page Figure 4-5. HS--720 (7520063) Outline and Installation Diagram . . . . . . . . . . . . 4--17 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 the Top Insert 60 Watt HPA ARINC 600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--9 Contact Arrangements for Middle Insert, HPA (60 Watt) ARINC 600 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--11 Contact Arrangements for Bottom Insert, HPA (60 Watt) ARINC 600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--13 Figure 5-7. HS--720 ARINC 600 Connector Layout . . . . . . . . . . . . . . . . . . . . . . . . 5--14 Figure 5-8. Contact Arrangements for Top Insert, HSU ARINC 600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--15 Contact Arrangements for the Middle Insert, HSU ARINC 600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--17 Contact Arrangements for the Bottom Insert, HSU ARINC 600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--19 Figure 5-11. RFUIA ARINC 600 Connector Layout . . . . . . . . . . . . . . . . . . . . . . . . . 5--20 Figure 5-12. Satellite Data Unit & HSU Interface Diagram . . . . . . . . . . . . . . . . . . . 5--23 Figure 5-13. CMC Top--mounted High Gain Antenna (HGA) Interface Diagram 5--31 Figure 5-14. WH--10 Handset Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--33 Figure 5-15. HF-SAT Transfer Panel Interface Diagram . . . . . . . . . . . . . . . . . . . . . 5--34 Figure 5-16. Signal Conditioning Unit Interface Diagram . . . . . . . . . . . . . . . . . . . . 5--35 Figure 5-17. Maintenance Panel Assembly Interface Diagram . . . . . . . . . . . . . . . 5--37 Figure 5-18. HS--720 Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--39 Figure 5-19. HS--720 Forward ID & Configuration Pins . . . . . . . . . . . . . . . . . . . . . . 5--41 Figure 5-20. Tecom Top--Mount High Gain Antenna Interface Diagram . . . . . . . . 5--43 Figure 5-21. Thales Mechanically Steered High Gain Antenna Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--45 EMS AMT--50 Mechanically Steered High Gain Antenna Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--47 Figure 5-23. Dassault Conformal High Gain Antenna Interface Diagram . . . . . . 5--49 Figure 5-24. Ball Conformal High Gain Antenna Interface Diagram . . . . . . . . . . . 5--51 Figure 5-25. Low Gain Antenna Interface Diagram . . . . . . . . . . . . . . . . . . . . . . . . . 5--53 Figure 5-5. Figure 5-6. Figure 5-9. Figure 5-10. Figure 5-22. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--10 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Illustrations (cont) Figure Page Figure 5-26. Toyocom Top--mounted High Gain Antenna Interface Diagram . . . 5--55 Figure 6-1. System BITE Communication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--1 Figure 6-2. SATCOM SCDU Page Hierarchy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--27 Figure 6-3. SATCOM SCDU Main Menu Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--29 Figure 6-5. SATCOM MAINTENANCE Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--34 Figure 6-6. TEST Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--36 Figure 6-7. SATCOM SELF--TEST Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--41 Figure 6-8. Configuration Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--44 Figure 6-9. DATA LOADER MENU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--67 Figure 6-10. LAST LEG REPORT Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--73 Figure 6-11. PREVIOUS LEG REPORT Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--75 Figure 6-12. LRU IDENTIFICATION Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--79 Figure 6-13. TROUBLESHOOTING DATA Page . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--82 Figure 6-14. LAST LEG CLASS 3 FAULTS Page . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--84 Figure 6-15. GROUND REPORT Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--86 Figure 6-16. GROUND REPORT TROUBLE SHOOTING DATA Page . . . . . . . . 6--88 Figure 6-17. Configuration Data Pages for Boeing 777 Installation . . . . . . . . . . . 6--92 Figure A--1. ARINC Connectors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--3 Figure A--2. ARINC Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--3 Figure A--3. Dimensions for ECS Tray Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . A--5 Figure A--4. Dimensions for Hollingsead Tray Assemblies . . . . . . . . . . . . . . . . . . . A--23 Figure B--1. ECS Top Mount Air Filtration Assembly . . . . . . . . . . . . . . . . . . . . . . . . B--5 Figure B--2. Front and Side Views Showing Filter Removal . . . . . . . . . . . . . . . . . B--10 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--11 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Tables Table Table 1-1. Classes of Installations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Page 1--11 Table 1-2. Types of Baseband RF Channels . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--12 Table 1-3. Ground Earth Stations for Aero H/H+ Services . . . . . . . . . . . . . . . . . 1--15 Table 1-4. Land Earth Stations for Aero Swift64 Services . . . . . . . . . . . . . . . . . 1--15 Table 1-5. System Components Supplied by Honeywell/Thales ........... 1--16 Table 1-6. System Components Not Supplied by Honeywell .............. 1--16 Table 1-7. SDU Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--17 Table 1-8. HSU Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--17 Table 1-9. HPA Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--17 Table 1-10. RFUIA Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--17 Table 1-11. SD--720 SDU Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--28 Table 1-12. SD--720 SDU DO--160D Environmental Categories . . . . . . . . . . . . 1--29 Table 1-13. HS--720 HSU Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--32 Table 1-14. HS--720 HSU DO--160D Environmental Categories ............ 1--33 Table 1-15. HP--720 60W HPA Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . 1--36 Table 1-16. HP--720 60W HPA Environmental Categories ................. 1--37 Table 1-17. RFUIA Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1--41 Table 1-18. RFUIA DO--160D Environmental Categories . . . . . . . . . . . . . . . . . . . 1--41 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--4 Table 5-1. ARINC 615 Connector Pin Callouts 5--2 Table 5-2. HSU Front Panel RJ--45 Pin Arrangements ................... 5--2 Table 5-3. ARINC 600 Connector Requirements . . . . . . . . . . . . . . . . . . . . . . . . . 5--3 Table 5-4. Contact Arrangements for Top Insert, SDU ARINC 600 Connector 5--5 Table 5-5. Contact Arrangements for Middle Insert, SDU ARINC 600 Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--6 .......................... 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--12 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Tables (cont) Table Page Table 5-6. ICAO Block Strapping . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--29 Table 5-7. Configuration Pins . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--57 Table 5-8. Availability of ARINC 429 ICAO ADDRESS (AES ID) from 429 Ports . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--59 Table 5-9. FMC Connection to SDU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--60 Table 5-10. ARINC 429 Speed to/from CMU No. 1 and CMU No. 2 ......... 5--60 Table 5-11. Cabin Packet Data Function (CPDF) . . . . . . . . . . . . . . . . . . . . . . . . . 5--61 Table 5-12. ARINC 429 Bus Speed of AES ID Input . . . . . . . . . . . . . . . . . . . . . . . 5--61 Table 5-13. HSU Presence ............................................ 5--61 Table 5-14. SDU Controller Type . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--62 Table 5-15. Call Light On (Air/Ground Calls) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--62 Table 5-16. Strap Parity (ODD) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--62 Table 5-17. Cabin Communications System (CCS) . . . . . . . . . . . . . . . . . . . . . . . . 5--63 Table 5-18. Inertial Reference System (IRS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--63 Table 5-19. HPA/Antenna Subsystem Configuration . . . . . . . . . . . . . . . . . . . . . . . 5--64 Table 5-20. CFDS/CMC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--65 Table 5-21. SDU Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--66 Table 5-22. SDU Number . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--66 Table 5-23. CMU No. 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--67 Table 5-24. CMU No. 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--67 Table 5-25. MCDU/WSC No. 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--67 Table 5-26. MCDU/WSC No. 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--67 Table 5-27. MCDU/WSC No. 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--68 Table 5-28. Priority 4 Calls to/from Cockpit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--68 Table 5-29. ARINC 429 Bus Speed to MCDU No. 1/MCDU No.2/MCDU No. 3 5--69 Table 5-30. Cockpit Voice Call Light/Chime Option . . . . . . . . . . . . . . . . . . . . . . . . 5--69 Table 5-31. SDU Analog Interface No. 1 Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--70 Table 5-32. SDU Analog Interface No. 2 Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--70 Table 5-33. Cockpit Hookswitch Signaling Method . . . . . . . . . . . . . . . . . . . . . . . . 5--70 Table 5-34. CM--250 CGU Connection Configuration . . . . . . . . . . . . . . . . . . . . . . 5--72 Table 5-35. Cockpit Call Discrete Signaling Mode . . . . . . . . . . . . . . . . . . . . . . . . . 5--72 Table 5-36. Call Signaling Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--72 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--13 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Tables (cont) Table Page Table 5-37. Per Channel State Definition (MP11F=0) . . . . . . . . . . . . . . . . . . . . . . 5--73 Table 5-38. Strap Parity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5--73 Table 6-1. Levels of Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--3 Table 6-2. HPA Indicators/Controls .................................... 6--9 Table 6-3. HSU Indicators/Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--10 Table 6-4. SDU Indicators/Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--12 Table 6-5. Level 1 Failure Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--13 Table 6-6. List of Part Numbers ....................................... 6--18 Table 6-7. MAR Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--20 Table 6-8. LS Key/Line Pair Relations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--22 Table 6-9. Special Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--25 Table 6-10. System Configuration Pin Mapping . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--44 Table 6-11. Textual Message Display (Page 6 -- Lines 4 thru 9) . . . . . . . . . . . . . 6--51 Table 6-12. Textual Message Display (Page 7 -- Lines 4, 5, and 6) . . . . . . . . . . 6--53 Table 6-13. Textual Message Display (Page 9 -- Lines 8 and 9) . . . . . . . . . . . . . 6--57 Table 6-14. Textual Message Display (Page 10 -- Lines 4 and 5) . . . . . . . . . . . . 6--59 Table 6-15. Textual Message Display (Page 10 -- Lines 8 and 9) . . . . . . . . . . . . 6--59 Table 6-16. DATA LOADER MENU Page Prompts . . . . . . . . . . . . . . . . . . . . . . . . 6--70 Table 6-17. LRU Acronyms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--78 Table 6-18. Boeing Level I Failure Messages and ATA Reference Numbers . . 6--96 Table 6-19. Airbus Level I (SDU No. 1) Failure Messages and ATA No. . . . . . . 6--100 Table 6-20. Airbus Level I (SDU No. 2) Failure Messages and ATA No. . . . . . . 6--108 Table 6-21. McDonnell Douglas Level I Failures Messages and ATA Reference Numbers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6--116 Table 6-22. Commissioning and Maintenance Terminal Panel Lamps . . . . . . . . 6--122 Table 7-1. Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7--1 Table A--1. ECS Cables and Connectors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--2 Table A--2. ECS Attenuators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--2 Table A--3. SD--720 (120--10141--1XX) Pressurized Hardware Kit . . . . . . . . . . A--7 Table A--4. SD--720 (120--10142--1XX) Unpressurized Hardware Kit . . . . . . . . A--9 Table A--5. HS--720 (120--10267--1XX) Pressurized Hardware Kit . . . . . . . . . . A--11 Table A--6. HS--720 (120--10268--1XX) Unpressurized Hardware Kit . . . . . . . . A--13 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--14 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Tables (cont) Table Page Table A--7. HP--720 (120--99510--1XX) Pressurized Hardware Kit . . . . . . . . . . A--15 Table A--8. HP--720 (120--99509--1XX) Unpressurized Hardware Kit . . . . . . . . A--17 Table A--9. Tray Assembly Part Numbers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--22 Table A--10. ARINC 429 Data Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--27 Table A--11. SCU Discrete Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--27 Table A--12. SCU Error Code . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--28 Table A--13. SCU Manual Signal Selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--29 Table A--14. ARINC 561 Binary Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--30 Table A--15. ARINC 561 BCD Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--30 Table A--16. ARINC 571 Data, ARINC 429 Format . . . . . . . . . . . . . . . . . . . . . . . . . A--31 Table A--17. ARINC 571 Data, ARINC 419 Format . . . . . . . . . . . . . . . . . . . . . . . . . A--31 Table A--18. ARINC 404 Data, ARINC 429 Format . . . . . . . . . . . . . . . . . . . . . . . . . A--31 Table A--19. SCU Attitude Data Inputs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--32 Table A--20. Contact Arrangements for SCU ARINC 600 Connector . . . . . . . . . A--34 Table A--21. Signal Source Select Lines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--38 Table A--22. SCU Program Pin Combinations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A--39 Table B--1. Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B--2 Table B--2. Air Filtration Systems from ECS for a Top Mount Assembly . . . . . . B--2 Table B--3. Air Filtration Systems from ECS for a Body--Mounted Design . . . . B--3 Table B--4. Air Filtration Systems from ECS for a Tray--Mounted Design . . . . . B--3 Table C--1. ORT Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C--1 Table D--1. Call Events Log . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D--1 Table D--2. SCLV and Detailed Code Descriptions . . . . . . . . . . . . . . . . . . . . . . . . D--4 Table D--3. SLCV Description for HSD ISDN Call Terminations . . . . . . . . . . . . . D--9 Table D--4. Detailed Codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D--15 Table E--1. PADO Services . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E--1 Table E--2. PADR Services . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E--3 Table E--3. Service Name Error . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E--5 Table E--4. SLCV Cause Codes and Strings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E--6 Table E--5. Q.850 Cause Codes and Strings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E--18 Table E--6. MPDS +WQ Cause Codes and Strings . . . . . . . . . . . . . . . . . . . . . . . E--20 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--15 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Blank Page 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page TC--16 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System INTRODUCTION 1. How to Use This Manual A. General (1) This manual gives general system description and installation information for the MCS--4200/7200 Multi--Channel SATCOM System. It also gives block diagram and interconnect information to permit a general understanding of the system interface. (2) The purpose of this manual is to help you install, operate, maintain, and troubleshoot the MCS--4200/7200 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. (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. WARNING: HIGH VOLTAGES MAY BE PRESENT ON SYSTEM INTERCONNECT CABLES. MAKE SURE THAT SYSTEM POWER IS OFF BEFORE YOU DISCONNECT LRU MATING CONNECTORS. WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL SAFETY DATA SHEETS FOR SAFETY INFORMATION. SOME MATERIALS CAN BE DANGEROUS. CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO MATERIALS SPECIFIED BY HONEYWELL. MATERIALS THAT ARE NOT EQUIVALENT CAN CAUSE DAMAGE TO THE EQUIPMENT AND CAN VOID THE WARRANTY. CAUTION: THE MCS--4200/7200 MULTI--CHANNEL SATCOM SYSTEM CONTAINS ITEMS THAT ARE ELECTROSTATIC DISCHARGE SENSITIVE (ESDS). IF YOU DO NOT OBEY THE NECESSARY CONTROLS, A FAILURE OR UNSATISFACTORY OPERATION OF THE UNIT CAN OCCUR FROM ELECTROSTATIC DISCHARGE. USE APPROVED INDUSTRY PRECAUTIONS TO KEEP THE RISK OF DAMAGE TO A MINIMUM WHEN YOU TOUCH, REMOVE, OR INSERT PARTS OR ASSEMBLIES. B. Symbols (1) The symbols in Figure Intro--1 identify ESDS and moisture sensitive devices in this manual, if applicable. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page INTRO--1 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Moisture Sensitive ESDS Figure Intro--1. Symbols C. Weights and Measurements (1) All weights and measurements are in U.S. and SI (metric) values. (2) The letter symbols for this units of measurement are the same as shown in ANSI/IEEE Std 260. 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 https://pubs.cas.honeywell.com/ to: • Download or see publications online • Make an order for a publication • Tell Honeywell of a possible data error in a publication. B. Customer Response Center (1) If you do not have access to the Internet, send an e--mail message or a fax, or speak to a person at the Customer Response Center: • E--mail: cas--publications--distribution@honeywell.com • Fax: 602--822--7272 • Phone: 800--601--3099 (U.S.A.) • Phone: 602--365--3900 (International). (2) Also, the Customer Response 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--26 (Pub. No. A09--5111--026), SD--700/720 Satellite Data Unit CMM 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page INTRO--2 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System • ATA No. 23--20--50 (Pub. No. A32--5111--008), HP--720 High Power Amplifier CMM • ATA No. 23--20--52 (Pub No. A32--5111--001), HS--720 High Speed Data Unit Assembly CMM • Pub. No. A09--1100--001, Handling, Storage, and Shipping Procedures for Honeywell Avionics Equipment Instruction Manual • Pub. No. A09--1100--004, Standard Repair Procedures for Honeywell Avionics Equipment Instruction Manual • Pub. No. A62--0119--001, Honeywell Material Number (HMN) Codes. B. Other Publications (1) These publications are standard references: • The United States Government Printing Office (GPO) Style Manual 2000 (available at http://www.gpoaccess.gov/stylemanual/browse.html) • 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) • H4/H8 Commercial and Government Entity (CAGE) Codes (available at http://www.dlis.dla.mil/cage_welcome.asp). 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 Term Full Term AAC aeronautical administrative communications ACARS aircraft communications addressing and reporting system ACP audio control panel ACU antenna control unit ADL airborne data loader 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page INTRO--3 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Acronyms and Abbreviations (cont) Term Full Term ADS automatic dependent surveillance AES aircraft earth station AFIS aircraft flight information system AMS audio management system AMU audio managment unit ANSI American National Standards Institute 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. ASME American Society of Mechanical Engineers ATA Air Transport Association ATC air traffic control ATN aircraft telecommunications network 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 CEL call events log CF/M cubic feet per minute CFDIU centralized fault display interface unit CFDS central fault display system CGU communications gateway unit CLR clear 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page INTRO--4 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 4 OF 53 FACING PAGE INTRO-5. Reason: To add two acronyms, GNSS and GPS to the List of Acronyms and Abbreviations and the change the definition for GES from ground earth stations to ground earth station. Add GNSS and GPS and change the definition of GES as follows: GES ground earth station GNSS global navigation satellite system GPS global positioning system 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 4 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Acronyms and Abbreviations (cont) Term Full Term CM continuous monitoring CMC central maintenance computer CMM component maintenance manual 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 DSLCV most significant digit of the detailed code DTE data terminal equipment DTMF dual tone multifrequency EAR Export Administration Regulations ECS Electronic Cable Specialists EIRP effective isotopic radiated power ESDS electrostatic discharge sensitive FID forward ID FMC flight management computer FRLP forward/return link pair FWP fault warning processor GES ground earth stations GMT Greenwich Mean Time GPO Government Printing Office GSDB GES--specific data broadcast GSPD groundspeed HDM HSU data module 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page INTRO--5 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Acronyms and Abbreviations (cont) Term Full Term HGA high gain antenna HMN Honeywell Material Number HPA high power amplifier HPR high power relay HSD high speed data HSDU high speed data unit HSU high speed data unit I/O input/output ICAO International Civil Aviation Organization ID identification IEEE Institute of Electrical and Electronics Engineers IGA intermediate gain antenna INMARSAT International Maritime Satellite Organization IOM input/output module IOR Indian Ocean Region IPC illustrated parts catalog IRS inertial reference system ISDN integrated services digital network ISN Inmarsat serial number ISO International Standards Organization ISU initial signal unit ITAR International Traffic in Arms Regulations ITU International Telecommunications Union LED light emitting diode LES land earth station LGA low gain antenna LNA low noise amplifier LRU line replaceable unit LS line select MAR maintenance activity record 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page INTRO--6 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 5 OF 53 FACING PAGE INTRO-6. Reason: To change the capitalization of INMARSAT to Inmarsat in the List of Acronyms and Abbreviations. The List of Acronyms and Abbreviations is changed as follows: Inmarsat International Maritime Satellite Organization 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 5 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 6 OF 53 FACING PAGE INTRO-7. Reason: To add four acronyms, MES, MIB, PBX, and POTS to the List of Acronyms and Abbreviations. Add MES, MIB, PBX, and POTS as follows: MES MIB mobile earth station management information base PBX private (automatic) branch exchange POTS plain-old telephone service or system 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 6 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Acronyms and Abbreviations (cont) Term Full Term MCDU multifunction control display unit MCS Multi--Channel SATCOM MEL minimum equipment list MISDN mobile integrated services digital network MPDS mobile packet--data service MPEL maximum permissible exposure level MTBF mean--time--between--failure MU management unit NVM non--volatile memory OCXO oven controlled crystal oscillator OEM Original Equipment Manufacturer OMS on--board 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 PPPoE point--to--point protocol over Ethernet PROM programmable read--only memory PSTN Public Switched Telephone Networks PSU power supply unit PTT push--to--talk RF radio frequency RFM radio frequency module RFU radio frequency unit 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page INTRO--7 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System List of Acronyms and Abbreviations (cont) Term Full Term RFUIA Radio Frequency Unit Interface Adapter RID return ID RMP Radio Management Panel RTC real--time clock RTCA radio technical commission for aeronautics SAL system address label SCDU SATCOM control and display unit SCM swift channel module SCPC single channel per carrier SCU signal conditioning unit SDI source destination identifier SDU satellite data unit SITA Satellite AIRCOM SSM sign--status matrix Std standard 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 VIM voice interface module VSWR voltage standing wave ratio WSC Williamsburg SDU controller XTB cross--talk bus 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page INTRO--8 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 7 OF 53 FACING PAGE INTRO-8. Reason: To add nine acronyms, SAS, SBB, SBS, SIM, SNMP, UE, UMTS, USIM, and UT to the List of Acronyms and Abbreviations. Add SAS, SBB, SBS, SIM, SNMP, UE, UMTS, USIM, and UT as follows: SAS SBB SBS satellite access station SwiftBroadband satellite base station SIM subscriber identity module SNMP simple network management protocol UE UMTS user equipment universal mobile telecommunications service USIM UT universal (or UMTS) SIM user terminal 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 7 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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 A 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page INTRO--9 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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. Figure Intro--2. Radio Frequency Energy Levels 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page INTRO--10 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 8 OF 53 FACING PAGE 1-1. Reason: To change the text in Paragraphs (4) and (5) to add Classic Aero, to change the capitalization of INMARSAT to Inmarsat, and to delete text, as applicable. Paragraphs (4) and (5) are changed as follows: (4) The MCS-4200/7200 system provides seven Classic Aero communication channels capable of supporting six simultaneous full-duplex circuit mode voice connections and one channel of packetmode data. In addition, the MCS-4200/7200 system provides multiple channels of Inmarsat Swift64 and SwiftBroadband functionality. This Swift capability is configurable to support four MISDN channels, four MPDS channels, or a mixture of each (when operating with Inmarsat-3 satellites); or a maximum of two SwiftBroadband channels when operating with Inmarsat-4 satellites. (5) The MCS-4200 system operates identically to the MCS-7200, except that it supports only four Classic Aero communication channels (including one packet-mode data channel) rather than the seven that are provided by the MCS-7200. The MCS system accommodates all four airborne categories of communications: • ATC • AOC • AAC • APC. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 8 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System SECTION 1 SYSTEM DESCRIPTION 1. Overview A. General (1) The MCS--4200/7200 MCS is an augmented version of the MCS--4000/7000 system currently certified and in use today by hundreds of operators. The MCS--4200/7200 is a mobile avionics communications system that supplies continuous worldwide voice and data communications services to and from the aircraft via satellite. (2) The MCS system interfaces at baseband with various avionics data equipment, as well as with crew and passenger voice equipment onboard the aircraft. It also provides narrowband connectivity to support data--intensive airborne user applications. The MCS--4200/7200 system utilizes the antenna subsystem to transmit/receive L--band RF signals to/from satellites in geostationary orbit. These satellites convey the information to and from ground stations that interface with the terrestrial telephone network. (3) The MCS system augments and/or supersedes the present HF transceiver by supplying higher quality voice service and by supplying data services at higher bit rates needed by datalink ATN applications, such as ADS and the international ACARS. Additional services include cockpit communications with administrative and operational personnel and with governmental bodies such as ATS. The system is designed to make sure that communications involving safety and regularity of flight are not delayed by the transmission and reception of other message types. (4) The MCS--4200/7200 system provides seven baseband communication channels capable of supporting six simultaneous full--duplex circuit mode voice connections and one channel of packet--mode data. In addition, the MCS--4200/7200 system provides multiple channels of INMARSAT Swift64 and SwiftBroadband functionality. This Swift capability is configurable to support four MISDN channels, four MPDS channels, or a mixture of each. By late ’07 or early ’08, this functionality will be enhanced (with a software upgrade to the HSU and perhaps the SDU, combined with a system configuration strap change) to supply a maximum of two SwiftBroadband channels as well. This is subject to the constraint that the resources necessary to support one SwiftBroadband channel are reserved at the expense of two Swift64 channels, and vice versa. (5) The MCS--4200 system operates identically to the MCS--7200, except that it supports only four baseband communication channels (including one packet--mode data channel) rather than the seven that are provided by the MCS--7200. The MCS system accommodates all four airborne categories of communications: • ATC • AOC • AAC • APC. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--1 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (6) The four airborne communication categories are recognized by the ICAO and the ITU, and are assigned priorities for communications purposes. (7) The total aviation satellite communications system, shown in Figure 1-1, is made up of the following: • Aircraft earth station (airborne avionics subsystems and antenna subsystem) • Space segment (satellite network) • Ground earth stations • Terrestrial data and voice networks. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--2 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 9 OF 53 FACING PAGE 1-3. Reason: To add aircraft earth station (for Classic Aero), mobile earth station (for Swift64), and user equipment/user terminal (for SwiftBroadband) to Figure 1-1. Replace Figure 1-1 with the revised illustration as follows: Figure 1-1. Aviation Satellite Communications System 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 9 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 1-1. Aviation Satellite Communications System 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--3 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System B. Aircraft Earth Station – General (1) General (a) The AES is fully compliant with requirements of ARINC Characteristics 741/761. Standard interfaces between the MCS--4200/7200 avionics and other aircraft avionics enables 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 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 the cockpit crew (pilot and copilot), the cabin crew 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 SATCOM avionics • Antenna subsystem • Cabin communications system • Analog connected telephones • Cockpit voice sources • Aircraft avionics. (b) MCS Avionics The MCS--4200/7200 avionics is made up of the SDU, the HSU and the HPA. The SDU supplies the digital and analog interface to all aircraft avionics, and implements all functionality associated with modulation/demodulation, error correction, channel rate/frequency selection, and RF translation for the system’s seven baseband communication channels. The SDU’s seven baseband channels support six simultaneous full--duplex circuit--mode voice connections and one packet--mode channel. The HSU incorporates the firmware necessary to support four narrowband (Swift64) channels, which provide simultaneous circuit--mode and/or packet--mode connectivity concurrently with the SDU’s baseband channels at rates of 64 kbps (per single channel) or 256 kbps (four combined [bonded ISDN] channels). Ultimately, the HSU will be augmented – by software upgrade to the HSU, and perhaps the SDU, coupled with a system configuration strap change – to support an additional two wideband channels of 432 kbps (per single channel) SwiftBroadband functionality as well. Note that when the HSU commits the resources necessary to support a single SwiftBroadband channel, it simultaneously loses the capability to provide two channels of Swift64 service (and vice versa). 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--4 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 10 OF 53 FACING PAGE 1-4. Reason: To update headings and text to include references to MES, UE, LES, SAS, and Classic Aero, as applicable, to Paragraphs B. (1) (a), B. (2) (a) 1, and B. (2) (b) 2 and 3. The headings and text are changed as follows: B. Aircraft Earth Station/Mobile Earth Station/User Equipment – General (1) General (a) The AES/MES/UE is fully compliant with requirements of ARINC Characteristics 741/761. Standard interfaces between the MCS-4200/7200 avionics and other aircraft avionics enable it 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 GES/LES/SAS. The AES/MES/UE also receives RF signals from a GES/LES/SAS through the satellite, demodulates these signals, performs the necessary decoding of the encoded messages, and outputs the data or voice message for use by the cockpit crew (pilot and copilot), the cabin crew or the passengers. (2) AES/MES/UE Components (a) General 1 A block diagram of the AES/MES/UE is shown in Figure 1-2. It is made up of the following components: • MCS avionics The SDU supplies the digital and analog interface to all aircraft avionics, and implements all functionality associated with modulation/demodulation, error correction, channel rate/frequency selection, and RF translation for the system’s seven baseband communication channels. The SDU’s seven Classic Aero channels support six simultaneous full-duplex circuit-mode voice connections and one packet-mode channel. The HSU incorporates the firmware necessary to support four narrowband (Swift64) channels, which provide simultaneous circuit-mode and/or packet-mode connectivity concurrently with the SDU’s baseband channels at rates of 64 kbps (per single channel) or 256 kbps (four combined [bonded ISDN] or two channels of up to 432 kbps (per single channel) SwiftBroadband functionality. When operating through an Inmarsat-3 satellite and its GESs/LESs, Classic Aero and Swift64 services are possible; when operating through an Inmarsat-4 satellite and its GESs/SASs, Classic Aero and SwiftBroadband services are possible; i.e., only one type of Swift service is possible at any given time, depending on the type of satellite and ground station being used at any given time. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 10 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 11 OF 53 FACING PAGE 1-5. Reason: To change the text in Paragraphs 6, 7, and 9 as applicable to the latest version of the system. Some text was deleted. Replace the text in Paragraphs 6, 7, and 9 as follows: The CMU or equivalent, route packet-data messages to and from the SDU. Cabin communications use either a CCS or an analog equivalent (cabin unit) to provide baseband voice telephone communication (including FAX and PC modem services). The HSU’s Swift64 and SwiftBroadband communication channels supporting data-intensive email, web surfing, video-conferencing transmittals, and other data, are interfaced to the user by way of a server/router, which is part of the airborne network. To permit operation of the MCS-4200/7200 system to be easily tailored around aircraftspecific and user-specific needs, the SDU incorporates an ORT. The ORT contains more than 100 configurable entries (each with a default value) that are individually designated as either a user or secure (that is, installation-specific) item, as well as either Airbus modifiable or Airbus non-modifiable. The ORT affects not only the operation of the conventional Aero channels but the HSU channel complement (that is, the four Swift64 channels or the two SwiftBroadband channels) as well. The SDU/HSU combination supplies all essential services required to accommodate effective air/ground communications by way of satellite which use the antenna and related RF components for both the cockpit and cabin environments. The 60-Watt HPA assists in supporting multiple simultaneous channel communications by supplying linear power amplification to boost the RF signals associated with each channel to the levels required for transmission to the satellite. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 11 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System The HPA implements the linear power amplification of the SDU’s and HSU’s combined RF signals needed to assure their successful transmission from the aircraft to the satellite and to the ground network. A cockpit audio system conveys cockpit voice to and from the SDU. Messages requiring cockpit action or initiation appear on the appropriate cockpit display – RMP -- for the A380 -- or MCDU for all other platforms, with the correct protocol selected by the SDU based on data present on the display buses and/or other cockpit annunciators. The CMU or equivalent, route packet--data messages to and from the SDU. Cabin communications use either a CCS or an analog equivalent (cabin unit) to provide baseband voice telephone communication (including FAX and PC modem services). The HSU’s narrowband Swift64 and SwiftBroadband communication channels supporting data--intensive e--mail, web surfing, video--conferencing transmittal, and other data, are interfaced to the user by way of a server/router, which is part of the airborne network. To permit operation of the MCS--4200/7200 system to be easily tailored around aircraft--specific and user--specific needs, the SDU incorporates an ORT. The ORT contains more than 60 configurable entries (each with a default value) that is individually designated as either a user or secure (that is, installation--specific) item. The ORT affects not only the operation of the conventional Aero channels but the HSU channel complement (that is, the four Swift64 channels initially, and the two additional SwiftBroadband channels ultimately) as well. The ORT is subject to configuration management to the extent that the ORT’s version number is incremented whenever significant changes to the database occur (for example, introduction of SwiftBroadband items). Once made, the ORT selections are preserved by the SDU across power and test cycles in non--volatile memory. In addition, the ORT is able to be downloaded from or uploaded to the SDU from an external file storage medium (such as diskettes) which serve as the file destination or file source, respectively. The SDU/HSU combination supplies all essential services required to accommodate effective air/ground communications by way of satellite which use the antenna and related RF components for both the cockpit and cabin environments. The 60--Watt HPA assists in supporting multiple simultaneous baseband and narrowband (Swift64) channel communications by supplying linear power amplification to boost the RF signals associated with each channel to the levels required for transmission to the satellite. 10 The extensive variety of functionality that is afforded by the MCS--4200/7200 system results largely from the software direction of the hardware operation. The SDU’s hardware platform uses the MCS--4000/7000 designs, which are already certified on various other aircraft, as the baseline. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--5 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 11 These proven platforms provide a solid structure on which the MCS--4200/7200 SATCOM enhancements (both hardware and software) are being built. The software that drives the MCS--4200/7200 system operation is DO--178B Level D for the SDU and HPA from their first release into production. However, the initial (that is, Swift64--only) HSU will migrate to DO--178B Level D from Level E when its capabilities are upgraded to support full SwiftBroadband functionality. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--6 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 12 OF 53 FACING PAGE 1-6. Reason: To change the text in Paragraph 11 as applicable to the latest version of the system. Some text was deleted. Replace the text in Paragraph 11 as follows: 11 These proven platforms provide a solid structure on which the MCS-4200/7200 SATCOM enhancements (both hardware and software) are built. The software that drives the MCS4200/7200 system operation is DO-178B Level D for the SDU and HPA from their first release into production. However, the HSU is DO-178B Level E. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 12 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 13 OF 53 FACING PAGE 1-7/1-8. Reason: To change Figure 1-2 to change the text of Note 1 and to add new Note 3 and Note 4. Replace Figure 1-2 with the illustration that follows: Figure 1-2. Aircraft Earth Station Block Diagram 23-20-35 Page 13 of 53 28 Sep 2009 © Honeywell International Inc. Do not copy without express permission of Honeywell. SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 1-2. Aircraft Earth Station Block Diagram 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--7/1--8 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 14 OF 53 FACING PAGE 1-9. Reason: To change INMARSAT to show initial capitalization only in Paragraph 13 and Paragraph (c) 1. To change text in Paragraphs (c) 1, 2, and 3 as applicable to add references to MES, UE, LES, SAS, ACU, Classic Aero, and additional data about SwiftBroadband operations. Paragraph 13 and Paragraphs (c) 1, 2, and 3 are changed as follows: 13 In those applications for which the Swift64/SwiftBroadband capability is not required, an additional LRU may be necessary; this is the RFUIA. The RFUIA is used in place of the RFU in a conventional ARINC 741 system, and replaces the HSU in those installations which utilize only the MCS-4200/7200 SATCOM system’s classic Inmarsat baseband features. The primary function of the antenna subsystem is to complete the communication link between the GES/LES/SAS, the space segment, and the AES/MES/UE. The D/LNA is a three-port RF device (antenna, transmit, and receive) which provides signal routing and filtering – 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 LNA establishes the noise floor of the communication system’s receiver by boosting the signals received from the antenna to the maximum level relative to the noise received with the signals, as well as the noise developed by the LNA itself. For SwiftBroadband operations, the D/LNA must be a Type F (or later type approved for SwiftBroadband operation). Also, the selected antenna must be an Inmarsat-approved type for SwiftBroadband operation. The HGA transmits L-band RF signals from the HPA to a satellite, and receives L-band RF signals from a satellite for the SDU and HSU. When installed, the LGA supplies backup communications (packet-data only) for the HGA by providing low-rate, Classic Aero (only) packet-data communication services. The BSU or ACU is used in the HGA system to convert tracking and pointing coordinates (that is, 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. 23-20-35 Publication Number A15-5111-010 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 14 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 12 The MCS--4200/7200 system LRUs (building on their legacy MCS--4000/7000 background) maintains extensive logs of information that is useful in the monitoring of normal system activity as well as identifying any failure conditions experienced during operation, whether in flight or on the ground. This is accomplished through a combination of self--test suites that are performed at POST or as the result of PAST, as well as by CM. The maintenance logs are continuously updated, and accessible for download using the ARINC 615 ADL and PDL. 13 In those applications for which the Swift64/SwiftBroadband capability is not required, an additional LRU may be necessary; this is the RFUIA. The RFUIA is used in place of the RFU in a conventional ARINC 741 system, and replaces the HSU in those installations which utilize only the MCS--4200/7200 SATCOM system’s classic INMARSAT baseband features. (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 D/LNA is a three-port RF device (antenna, transmit, and receive) which provides signal routing and filtering -- 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 LNA establishes the noise floor of the communication system’s receiver by boosting the signals received from the antenna to the maximum level relative to the noise received with the signals, as well as the noise developed by the LNA itself. The HGA transmits L--band RF signals from the HPA to a satellite, and receives L--band RF signals from a satellite for the SDU and HSU. When installed, the LGA supplies backup communications (packet--data only) for the HGA by providing low--rate, packet--data communication services. The BSU is used in the HGA system to convert tracking and pointing coordinates (that is, 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. (d) CCS The CCS, in conjunction with the MCS avionics and a worldwide network of ground stations, supplies cabin services such as baseband telephone, facsimile, and PC modem communication interfaces. The CCS is partitioned into two sections: the CTU and cabin/passenger communications equipment (digitally connected telephones). 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--9 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System The CTU performs onboard PABX telephony functions, letting the digitally connected telephones make the best use of resources supplied by the MCS avionics. The ARINC 746 CTU supplies the conversion interface between the digitally connected phones and the ARINC 741/761 SDU, and connects to the SDU by means of a high-speed serial bus pair (CEPT--E1) that accommodates up to 30 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. (e) Airborne Server (f) The airborne server provides the means by which data streams from multiple cabin (or other) users are collected and processed into formats suitable for assignment onto the HSU’s narrowband or wideband channels. The HSU interfaces with the airborne server by way of two Ethernet 10BaseT ports for MPDS/SwiftBroadband and MISDN service, and by way of two ISDN ports for MISDN service. When using the Ethernet port for either MISDN or MPDS services, PPPoE protocol is used to choose the service and to give to the HSU all the parameters needed to access the correct ground service provider for the service chosen. A configuration discrete is used to configure the Ethernet ports so that all Swift64 channels use only one Ethernet port or both Ethernet ports. Analog Connected Telephones The SDU is provisioned to support two simultaneous analog audio channels which use any four--wire analog telephone (such as, Global--Wulfsberg Flitephone WH--10 handsets) by way of the APBX. The WH--10 is a standalone handset with a 12--button keypad. The APBX has analog trunk lines and in--line DTMF signaling. (g) 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 by the way of the MCDU or RMP), and 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 combined with lit or flashing call lamps announces call connections. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--10 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 15 OF 53 FACING PAGE 1-10. Reason: To change the text in Paragraphs (e) 1, 2, and 3 and (f) 1 to add references to SwiftBroadband and to make other changes to the text as applicable. Some text was deleted. Replace the text in Paragraphs (e) 1, 2, and 3 and (f) 1 as follows: The airborne server provides the means by which data streams from multiple cabin (or other) users are collected and processed into formats suitable for assignment onto the HSU’s narrowband or wideband channels. The HSU interfaces with the airborne server by way of two Ethernet 10BaseT ports for MPDS, SwiftBroadband, and MISDN service, and by way of two ISDN ports for MISDN and SwiftBroadband service. When using the Ethernet port for either SwiftBroadband, MISDN or MPDS services, PPPoE along with an SNMP-based ARINC MIB (in accordance with ARINC 781 Attachment 5) protocol is used to choose the service and to give to the HSU all the parameters needed to access the correct ground service provider for the service chosen. A configuration discrete is used to configure the Ethernet ports so that all Swift64/SwiftBroadband channels use only one Ethernet port or both Ethernet ports. The SDU is provisioned to support two simultaneous analog audio channels which use four-wire analog telephone interfaces such as Global-Wulfsberg Flitephone WH-10 handsets or an analog PBX (APBX). The WH-10 is a standalone handset with a 12-button keypad that utilizes discretes for call signaling functions. The APBX has analog trunk lines and in-line DTMF signaling. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 15 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 16 OF 53 FACING PAGE 1-11. Reason: To change the text in Paragraphs (h) 1 (bullet 4 and bullet 7) to add a reference to GNSS and Swift64 operation, as applicable. Replace the text in Paragraphs (h) 1 (bullet 4 and bullet 7) as follows: • The IRS and GNSS (GPS), where installed, to supply the SDU with navigation coordinates for positioning the antenna platform • 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. Similar configuration pins on the HSU identify a 24-bit Forward ID for similar addressing purposes for Swift64 operation. Similar addressing and other functionality are handled for SwiftBroadband operations by the SIM cards in the HSU's HDM. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 16 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (h) Aircraft Avionics Standard interfaces between the MCS--4200/7200 avionics and the other aircraft avionics include the following: • CMU, or the MU of the ACARS, where installed • SCDU, implemented as either MCDUs or RMPs, 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 • CFDS, CMC, or OMS, where installed, for fault reporting • The 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 ADL or PDL for uploading operational software and the ORT. Connections are made through the front and back panel connectors on the MCS avionics LRUs • 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. (3) AES Classifications (a) Each AES is classified according to the configuration and dynamic capabilities of its aircraft avionics baseband communications capability and antenna subsystem. Accordingly, 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--11 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (4) GES Communication Links (a) The MCS--4200/7200 avionics supply access to ground--based networks through the GES for baseband communications. Each GES supplies system synchronization and coordination through ground--to--aircraft transmissions. Four types of RF channels supporting baseband communications are defined for use with the MCS--4200/7200 avionics as listed in Table 1-2. Table 1-2. RF Channel Types of Baseband RF Channels Description P--Channel Packet--mode 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 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 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--12 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 17 OF 53 FACING PAGE 1-12. Reason: To change the text in Paragraph (4) (a) to add a reference to Classic Aero and to delete text, as applicable. Replace the text in Paragraph (4) (a) as follows: (a) The MCS-4200/7200 avionics supply access to ground-based networks through the GES for Classic Aero communications. Each GES supplies system synchronization and coordination through ground-to-aircraft transmissions. Four types of RF channels supporting baseband communications are defined for use with the MCS-4200/7200 avionics as listed in Table 1-2. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 17 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 18 OF 53 FACING PAGE 1-13. Reason: To change the art in Figure 1-3 to show seven regions instead of four and to change INMARSAT in the figure title to show initial capitalization only. Figure 1-3 and the title of Figure 1-3 are changed as follows: Figure 1-3. Inmarsat Seven-Region Satellite Coverage 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 18 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 1-3. INMARSAT Four-Region Satellite Coverage 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--13 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System C. Space Segment (1) The space segment is made up of satellites placed in geostationary orbits that support air-to-ground/ground-to-air packet-switched data services and circuit-switched telephony communications on both baseband and narrowband channels all 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 INMARSAT, whose system provides near--worldwide coverage (that is, some problems may be encountered when the aircraft flies in Polar Regions with a latitude greater than 75 degrees). The four-region satellite system supplied by INMARSAT is shown in Figure 1-3. D. Ground Earth Station/Land Earth Station (1) Each GES (and LES for Swift64) has the necessary equipment to communicate both with terrestrial networks and through satellites with the aircraft. The ground earth stations/land 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 PSTN and avoiding multiple satellite connections whenever possible. (2) Ground earth stations/land 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 or LES through an in-view satellite depending on the service preference settings encoded in the SDU ORT. E. Terrestrial Data and Voice Networks (1) Baseband data and voice services available through satellites and ground earth stations include 9.6 and 4.8 kilobit/second (kbps) digital voice, 4.8 and 2.4 kbps FAX, 2.4 kbps PC modem data, and packet-mode data at RF channel rates ranging from 600 bit/second (bps) up to 10.5 kbps. Narrowband data services currently available through satellites and land earth stations include 64 kbps circuit-switched ISDN channels and 64 kbps packet--switched MPDS channels, either of which can be combined to afford the user higher data rate throughput (for example, up to 256 kbps). By mid to late ’07, SwiftBroadband channels are planned to be available to support wideband packet--data services at rates up to 432 kbps per channel. The present worldwide complement of ground earth stations providing support for baseband services, and land earth stations providing support for narrowband services (including location, operator, and coverage region) are summarized in Table 1-3 and Table 1-4. Aeronautical communications through the INMARSAT satellites are transmitted to and from the terrestrial phone, and data networks through these ground earth stations and land earth stations. The satellite regions that service these ground earth stations/land earth stations are shown in Figure 1--3. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--14 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 19 OF 53 FACING PAGE 1-14. Reason: To change Subhead D. and the text in Paragraphs C. (1), D. (1) and (2), and E. (1) as applicable to the latest version of the system; some text was deleted and INMARSAT was changed to show initial capitalization only. Replace Subhead D. and Paragraphs C. (1), D. (1) and (2), and E. (1) as follows: (1) The space segment is made up of satellites placed in geostationary orbits that support air-toground/ground-to-air packet-switched data services and circuit-switched telephony communications on both baseband and narrowband channels all 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 Inmarsat, whose system provides near-worldwide coverage (that is, some problems may be encountered when the aircraft flies in Polar Regions with a latitude greater than 75 degrees). The seven-region satellite system (which includes four-each Inmarsat-3 satellites and three-each Inmarsat-4 satellites) is shown in Figure 1-3. An eighth region (not shown in Figure 1-3) is the singlefunctional MTSAT satellite (which consists of two satellites, one of which is a hot spare). D. Ground Earth Station/Land Earth Station/Satellite Base Station (1) Each GES/LES/SAS has the necessary equipment to communicate both with terrestrial networks and through satellites with the aircraft. The ground 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 PSTN and avoiding multiple satellite connections whenever possible. (2) Ground stations are located strategically around the globe to supply redundancy and diversity in the terrestrial extension of communications. Aircraft are connected to one or more ground stations through an in-view satellite depending on the service preference settings encoded in the SDU ORT. (1) Classic Aero data and voice services available through satellites and ground earth stations include 9.6 and 4.8 kilobit/second (kbps) digital voice, 4.8 and 2.4 kbps FAX, 2.4 kbps PC modem data, and packet-mode data at RF channel rates ranging from 600 bit/second (bps) up to 10.5 kbps. Swift64 circuit- and packet-mode data services currently available through satellites and land earth stations include 64 kbps circuit-switched ISDN channels and 64 kbps packet-switched MPDS channels, either of which can be combined to afford the user higher data rate throughput (for example, up to 256 kbps). SwiftBroadband channels support circuit- and packet-data services at rates up to 432 kbps per channel. The present worldwide complement of ground stations are summarized in Table 1-3 and Table 1-4. Aeronautical communications through the Inmarsat satellites are transmitted to and from the terrestrial phone, and data networks through these ground earth stations and land earth stations. The satellite regions that service these ground stations are shown in Figure 1-3. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 19 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 20 OF 53 FACING PAGE 1-15. Reason: To update Table 1-3 and Table 1-4 with the latest data and to delete the Service Provider column in Table 1-3. Replace Table 1-3 and update Table 1-4, Row 3 and Row 4, the LES code for Xantic, as follows: Table 1-3. Ground Earth Stations for Aero H/H+ Services GES ID SAT ID GES Name 002 000 (I3 AOR-W) Eik 005 000 (I3 AOR-W) Aussaguel 103 000 (I3 AOR-W) Aussaguel 104 001 (I3 AOR-E) Eik 120 005 (I4 APAC) Paumalu 161 004 (MTSAT) Kobe/Hitachiota 202 002 (I3 POR) Santa Paula 205 002 (I3 POR) Perth 220 006 (I4 EMEA) Fucino 301 003 (I3 IOR) Eik 305 003 (I3 IOR) Perth 320 007 (I4 AMER) Paumalu Table 1-4. Land Earth Stations for Aero Swift64 Services LES Code 001 SAT ID 000 (AOR-W) Service Provider Telenor 002 000 Stratos 012 000 Xantic 001 001 (AOR-E) Telenor 002 001 Stratos 012 001 Xantic 001 002 (POR) Telenor 002 002 Stratos 012 002 Xantic 001 003 (IOR) Telenor 002 003 Stratos 012 003 Xantic 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 20 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 1-3. GES Name Ground Earth Stations for Aero H/H+ Services GES ID SAT ID Service Provider Goonhilly--AW 001 000 (AOR--W) Stratos Southbury--AW 002 000 Telenor Aussaguel--AW 005 000 SITA Goonhilly--AE 101 001 (AOR--E) Stratos Aussaguel--AE 103 001 SITA Eik--AE 104 001 Telenor Sentosa--P 201 002 (POR) Stratos Santa Paula--P 202 002 Telenor Yamaguchi--P 203 002 KDD Perth--P 205 002 SITA Eik--I 301 003 (IOR) Telenor Perth--I 305 003 SITA Yamaguchi--I 306 003 KDD Sentosa--I 310 003 Stratos Table 1-4. Land Earth Stations for Aero Swift64 Services LES Code SAT ID Service Provider 001 000 (AOR--W) Telenor 002 000 Stratos 012 000 Xantic 001 001 (AOR--E) Telenor 002 001 Stratos 012 001 Xantic 001 002 (POR) Telenor 002 002 Stratos 022 002 Xantic 001 003 (IOR) Telenor 002 003 Stratos 022 003 Xantic 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--15 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 2. System Components A. General (1) The MCS--4200/7200 system avionics consists of the following components: • SDU • HSU • HPA. (2) These components are compatible with ARINC Characteristics 741 and 761. Table 1-5 lists the MCS--4200/7200 system components to be supplied by Honeywell/Thales. Table 1-6 lists the MCS--4200/7200 system components not supplied by Honeywell/Thales. Table 1-7, Table 1-8, Table 1-9, and Table 1-10 list system component configuration information. Table 1-5. System Components Supplied by Honeywell/Thales Component Model No. Honeywell Part No. 1 Satellite Data Unit (SDU) SD--720 7516118--xxyyy High Speed Data Unit (HSU) HS--720 7520061--xxyyy HP--720 7520000--xxyyy RF--700 7516222--901 High Power Amplifier (60 W) (HPA) Radio Frequency Unit Interface Adapter (RFUIA) 2 NOTES: 1. The five--digit dash number 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 in place of the HSU to eliminate wiring changes in aircraft provisioned for the HSU’s presence. Table 1-6. System Components Not Supplied by Honeywell Component Comments SDU Installation Equipment (See Note) ARINC 600 6--MCU tray, cables, connectors, assemblies, mounting hardware, and kits HSU Installation Equipment (See Note) ARINC 600 4--MCU tray, cables, connectors, assemblies, mounting hardware, and kits HPA (60 W) Installation Equipment (See Note) ARINC 600 8--MCU tray, cables, connectors, assemblies, mounting hardware, and kits RFUIA Installation Equipment (See Note) ARINC 600 4--MCU tray, cables, connectors, assemblies, mounting hardware, and kits High Gain Antenna Equipment CMC Electronics - Canada,Chelton Inc - USA, Tecom - USA, Thales--UK, EMS -- Canada NOTE: Installation of this equipment is dependent on the specific requirements of the operator and will involve interaction with suppliers of this equipment (such as, ECS, EMTEQ) 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--16 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 Table 1-8A. HDM Configuration HDM Part Number 7520033-901 Description HDM (all platforms) 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 22 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 21 OF 53 THRU PAGE 22 OF 53 FACING PAGE 1-17. Reason: To update Table 1-7 to replace baseband with Classic Aero and add part numbers and descriptions applicable to the SwiftBroadband SDU. To update Table 1-8 to replace narrowband with Swift64 and add one new part number and description applicable to both Swift64 and SwiftBroadband. To add a new Table 1-8A to incorporate the HDM configuration. Table 1-7 and Table 1-8 are changed and Table 1-8A is added as follows: Table 1-7. SDU Configurations SDU Part Number Description 7516118-24130 115 V ac/320-800 Hz, or 28 V dc , 4-channel Classic Aero (3 voice, 1 data) SDU for Boeing corporate and military applications 7516118-27130 115 V ac/320-800 Hz, or 28 V dc 7-channel Classic Aero (6 voice, 1 data) SDU for Boeing corporate and military applications 7516118-24140 115 V ac/320-800 Hz, or 28 V dc 4-channel Classic Aero (3 voice, 1 data) SDU for Airbus applications 7516118-27140 115 V ac/320-800 Hz, or 28 V dc 7-channel Classic Aero (6 voice, 1 data) SDU for Airbus applications 7516118-27150 SwiftBroadband SDU for Airbus Long Range 7516118-27145 SwiftBroadband SDU for Airbus A380 7516118-24145 SwiftBroadband SDU for Airbus A380 7516118-27135 SwiftBroadband SDU for all non-Airbus, including Boeing [particularly 777] and biz jets 7516118-24135 SwiftBroadband SDU for all non-Airbus, including Boeing and biz jets Table 1-8. HSU Part Number HSU Configurations Description 7520061-34010 115 V ac/320-800 Hz, or 28 V dc 4-channel Swift64 HSU for all applications 7520061-34015 115 V ac/320-800 Hz, or 28 V dc 4-channel Swift64 and SwiftBroadband HSU for all applications 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 21 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 1-7. SDU Configurations SDU Part Number Description 7516118--24130 115 V ac/320--800 Hz, or 28 V dc , 4--channel baseband (3 voice, 1 data) SDU for Boeing corporate and military applications 7516118--27130 115 V ac/320--800 Hz, or 28 V dc 7--channel baseband (6 voice, 1 data) SDU for Boeing corporate and military applications 7516118--24140 115 V ac/320--800 Hz, or 28 V dc 4--channel baseband (3 voice, 1 data) SDU for Airbus applications 7516118--27140 115 V ac/320--800 Hz, or 28 V dc 7--channel baseband (6 voice, 1 data) SDU for Airbus applications Table 1-8. HSU Configuration Description HSU Part Number 7520061--34010 115 V ac/320--800 Hz, or 28 V dc 4--channel narrowband HSU for all applications. Table 1-9. HPA Configuration Description HPA Part Number 7520000--20140 115 V ac/320--800 Hz, or 28 V dc, 60 W HPA for all applications. Table 1-10. RFUIA Part Number 7516222--901 RFUIA Configuration Description RFU Interface Adapter for all applications. 3. System Description A. General (1) The system description gives a general overview and summary of the features and interfaces that the MCS--4200/7200 system implements. Figure 1--4 is a simplified block diagram of the MCS--4200/7200 system as well as the other airborne systems with which it interfaces. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--17 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 23 OF 53 FACING PAGE 1-18. Reason: To update the text in Paragraphs 3. A. (2) and (3) to replace baseband with Classic Aero, add a reference to MES and UE, and delete some text, as necessary. Paragraph (2) and (3) are changed as follows: 2) The core of the AES avionics subsystem is the MCS-4000/7000 avionics, supporting Classic Aero data and voice communications (inclusively) at single channel rates from 600 to 21,000 bits per second as well as Swift64 and SwiftBroadband data communications at single channel rates of up to 64 and 432 kbps, respectively. 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/MES/UE. (3) The SDU supplies all essential services required to accommodate effective air/ground communications through the satellite, using the antenna and related RF components. The SDU manages the RF link protocols on the AES side and supplies the system interface to other aircraft avionics. The HSU administers all aspects of the Swift64 and SwiftBroadband channels’ operation, from call setup through termination, in coordination with the SDU. The HPA boosts the signal to be radiated by the antenna to the power level required for transmission to the satellite. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 23 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (2) The core of the AES avionics subsystem is the MCS--4000/7000 avionics, supporting baseband data and voice communications (inclusively) at single channel rates from 600 to 21,000 bits per second as well as narrowband (Swift64 initially)/wideband (SwiftBroadband ultimately) data communications at single channel rates of 64 and 432 Kbps, respectively. 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. (3) The SDU supplies all essential services required to accommodate effective air/ground communications through the satellite, using the antenna and related RF components. The SDU manages the RF link protocols on the AES side and supplies the system interface to other aircraft avionics. The HSU administers all aspects of the narrowband and wideband channels’ operation, from call setup through termination, in coordination with the SDU. The HPA boosts the signal to be radiated by the antenna to the power level required for transmission to the satellite. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--18 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 1-4. MCS--4200/7200 Avionics Block Diagram 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--19/1--20 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 24 OF 53 FACING PAGE 1-21. Reason: To change Paragraph B. (1) (a) to replace baseband with Classic Aero. Paragraph (a) is changed as follows: (a) The SDU is the core element of the MCS–4200/7200 avionics and responsible for overall AES control and monitoring. The unit interfaces to many aircraft avionics (for example, CFDS, primary/secondary IRS, CMU 1/2, MCDU [or RMP] 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 Classic Aero voice communication, one channel of Classic Aero data 2/3 communication, and RF circuitry sufficient to operate the AES. Figure 1-5 shows the CCA listing and block diagram for the MCS-7200 SDU. Removal of one of the TTCM CCAs results in the MCS-4200 SDU. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 24 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System B. Satellite Data Unit (1) General (a) The SDU is the core element of the MCS–4200/7200 avionics and responsible for overall AES control and monitoring. The unit interfaces to many aircraft avionics (for example, CFDS, primary/secondary IRS, CMU 1/2, MCDU [or RMP] 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 baseband voice communication, one channel of baseband data 2/3 communication, and RF circuitry sufficient to operate the AES. Figure 1--5 shows the CCA listing and block diagram for the MCS--7200 SDU. Removal of one of the TTCM CCAs results in the MCS--4200 SDU. Figure 1-5. MCS--7200 SDU Equipment Description 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--21 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (b) The format for baseband voice/data encoding 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 baseband voice and data services, and the RF transmit/receive circuitry needed to convert modulated signals of either type 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. (f) 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--4200/7200 is a full--duplex system, the transmit and receive signals are processed simultaneously as in conventional terrestrial telephone equipment. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--22 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 25 OF 53 FACING PAGE 1-22. Reason: To change Paragraph (b) to replace baseband with Classic Aero and to change the capitalization of INMARSAT to Inmarsat. To add the ACU and ARINC 781 antenna to Paragraph (d). Paragraphs (b) and (d) are changed as follows: (b) The format for Classic Aero voice/data encoding 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. (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), antenna control unit (ACU), or ARINC 781 antenna to permit optimum signal transmission and reception between the high gain antenna subsystem and the satellite. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 25 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 26 OF 53 FACING PAGE 1-23. Reason: To change the text of Paragraphs C. (1) (a), (b), and (c) to include additional references to SwiftBroadband and Swift64, as well as references to POTS. Some text was deleted. Paragraphs (a), (b), and (c) are changed as follows: (a) The HSU provides four additional simultaneous full-duplex Swift64 64 kbps channels or two additional simultaneous full-duplex SwiftBroadband up-to-432 kbps channels to the MCS system when operated in conjunction with the SDU. The Swift64 channels accommodate digitized voice and data signals relayed to and from the airborne server at a maximum rate of 256 kbps when all four Swift64 channels are bonded to serve a single user or 128 kbps when two channels are bonded together. (b) The channels provided by the HSU are accessed by way of the two BRI ISDN interfaces and/or the two Ethernet interfaces and/or the two POTS interfaces. The ISDN interface provides the following services: 64 kbits/s UDI, 64 kbits/s 3.1 kHz Audio, 64 kbits/s Speech and 56 kbits/s Data. The 10 Base T Ethernet interfaces are accessed through the PPPoE using PPPoE tags for service selection. (c) A configuration discrete is provided to control the functionality of the Ethernet user interfaces, whether all channels are available on a first-come, first-served basis through either Ethernet interface, or whether half of the channels are available by way of one (and only one) of the Ethernet interfaces, and the other half of the channels are available by way of the other Ethernet interface (and only that interface). The default (open-circuit) state of this discrete is the former (first-come, first-served). The HSU supports APC calls only through its ISDN and/or Ethernet and/or POTS connections to the airborne server. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 26 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (2) 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 • HPA to antenna loss • HSDU to antenna loss. C. High Speed Data Unit (1) The HSU is partitioned into functional SRUs that are electronically interconnected by way of the motherboard. The major SRUs are: • PSU -- Power Supply Unit • CP -- Control Processor • DIO -- Data Input / Output • CC -- Channel Card (2 per unit). (a) The HSU provides four additional simultaneous full--duplex Swift64 64 kbps channels to the MCS system when operated in conjunction with the SDU. This expands (with a software upgrade to the HSU and perhaps SDU, in conjunction with a system configuration strap change) to include two more channels of simultaneous full--duplex SwiftBroadband 432 kbps channels (subject to the constraint that resources consumed by one SwiftBroadband channel preclude operation of two Swift64 channels, and vice versa). The channels provided by the HSU are not (in contrast to the SDU) capable of supporting analog voice transactions directly. Instead, these channels accommodate digitized voice and data signals relayed to and from the airborne server at a maximum rate of 256 kbps when all four Swift64 channels are bonded to serve a single user. (b) The channels provided by the HSU are accessed by way of the two BRI ISDN interfaces and/or the two Ethernet interfaces. The ISDN interface provides the following services 64 kbits/s UDI, 64 kbits/s 3.1 kHz Audio, 64 kbits/s Speech and 56 kbits/s Data. The 10 Base T Ethernet interfaces are accessed through the PPPoE using PPPoE tags for service selection. (c) A configuration discrete is provided to control the functionality of the Ethernet user interfaces, whether all channels are available on a first--come, first--served basis through either Ethernet interface, or whether half of the channels are available by way of one (and only one) of the Ethernet interfaces, and the other half of the channels are available by way of the other Ethernet interface (and only that interface). The default (open--circuit) state of this discrete is the former (first--come, first--served). The HSU supports APC calls only through its ISDN and/or Ethernet connections to the airborne server. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--23 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (2) The HSU accepts the coded voice/data signals from the airborne server and modulates them with the proper radio frequency for transmission to the HPA (for amplification) and on to the satellite. The transmission frequency is in the L--band range between 1626.5 and 1660.5 MHz, with 17.5 kHz (minimum) separating each communication channel. The HSU adjusts the transmission frequency in 1--Hertz increments to compensate for the Doppler shift caused by the speed of the aircraft. Navigation information from the SDU is required for the adjustment. (3) The HSU uses two 24--bit IDs, called a FRLP, for each Swift64 channel. Each pair consists of a FID and a RID. Each HSU contains, in an ordered tabular format, all FRLPs allocated by INMARSAT to this HSU product. The HSU is pin programmed through its rear connector for one 24--bit FID. The HSU assigns this FID and the three FIDs following it in the FRLP table, along with the associated RIDs, to the four Swift64 channels. For security reasons, the FRLP is encrypted and the table contents are not accessible to the user. (4) Honeywell uses a secure web database to store and allocate FRLPs to aircraft when HSUs are installed. Installers need to contact a Honeywell customer support person and provide an aircraft ICAO and tail number, aircraft type and HSU part number to obtain an FRLP allocation. Additionally, the aircraft customer name and contact information needs to be provided. The support person accesses the database and enters the aircraft information. The web site checks that no IDs have been assigned to any of the parameters entered and returns the four FIDs, which indicate the one that must be strapped. The customer support person conveys the FID assignment to the installer and the customer. (5) The HSU is provisioned with an HSU Data Module (HDM) that contains channel identification information required for SwiftBroadband operation. The HDM slides into and out of the HSU via the front panel. Once the SwiftBroadband channel identification information is assigned to an aircraft, the HDM must be tethered to the airframe and separated from the HSU if the HSU requires removal. Until the HSU is upgraded for SwiftBroadband operation (available late ’07 or early ’08), no channel identification information is contained in the HDM, and it need not be tethered. D. High Power Amplifier (1) The SDU sends such information as power amplifier on/off commands and amplification gain commands to the HPA. The bi--directional 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 and HSU to a power level required for transmission to the satellite. Because multiple signals are transmitted through the HPA, the HPA is a linear device (that is, operating class AB) capable of amplifying more than one signal at a time. An average of 60 Watts RF output power is developed by the HPA while passing multiple signals without generating excessive intermodulation products. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--24 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 27 OF 53 FACING PAGE 1-24. Reason: To change the text of Paragraphs C. (2) and (5) to include the latest system data and to change the capitalization of INMARSAT to Inmarsat in Paragraph (3). Paragraphs C. (2), (3), and (5) are changed as follows: (2) The HSU accepts the coded voice/data signals from the airborne server or analog voice/fax/PC modem signals from the POTS interfaces and modulates them with the proper radio frequency for transmission to the HPA (for amplification) and on to the satellite. The transmission frequency is in the L-band range between 1626.5 and 1660.5 MHz, with 17.5 kHz (minimum) separating each communication channel. The HSU adjusts the transmission frequency in 1-Hertz increments to compensate for the Doppler shift caused by the speed of the aircraft. Navigation information from the SDU is required for the adjustment. (3) The HSU uses two 24-bit IDs, called a FRLP, for each Swift64 channel. Each pair consists of a FID and a RID. Each HSU contains, in an ordered tabular format, all FRLPs allocated by Inmarsat to this HSU product. The HSU is pin programmed through its rear connector for one 24--bit FID. The HSU assigns this FID and the three FIDs following it in the FRLP table, along with the associated RIDs, to the four Swift64 channels. For security reasons, the FRLP is encrypted and the table contents are not accessible to the user. (5) The HSU is provisioned with an HSU Data Module (HDM). The HDM slides into and out of the HSU via the front panel. The HDM for the SwiftBroadband-capable HSU (PN 7520061-34015) contains channel identification information required for SwiftBroadband operation. Once the SwiftBroadband channel identification information is assigned to an aircraft, the SwiftBroadband HDM must remain with the airframe and be separated from the HSU if the HSU requires removal. Conversely, the HDM in the Swift64-capable HSU (PN 7520061-34010) has no channel identification information, and should not be retained with the aircraft. The Swift64 HDM must remain with the HSU if the HSU requires removal. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 27 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 28 OF 53 FACING PAGE 1-25. Reason: To delete references to baseband, narrowband, and wideband in Paragraph E. (2) and add references to Classic Aero. To update the component descriptions in Paragraphs 4. A. (1) and (2) and change SRU to LRU, as necessary. Some text was deleted. Paragraphs E. (2) and 4. A. (1) and (2) are changed as follows: (2) The MCS-4200/7200 system requires installation of an SDU, a 60-Watt HPA, and (optionally) an HSU. The SDU/HPA combination supports seven independent simultaneous channels for Classic Aero 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. The SDU/HSU/HPA combination allows up to four Swift64 channels or up to two SwiftBroadband channels to operate concurrently with the system’s seven Classic Aero channels. (1) The MCS-4200/7200 system LRUs perform reliably under field conditions and permit ease of maintenance when required. Each unit is an LRU, as defined by ARINC Characteristic 600, to permit easy replacement of each unit. The internal SRUs use both digital and analog solid state circuitry constructed using a mixture of SMT and DIP technology. (2) All LRUs are built to standards that qualify them for both airline and business aircraft usage. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 28 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (3) In addition to providing RF power amplification, the HPA controls output power to supply the desired EIRP from the AES. The SDU controls the gain of the HPA over a 25-dB range in 1-dB increments through the ARINC 429 interface. This permits the automatic adjustment of signal strength to 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. E. 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 MCS--4200/7200 system requires installation of an SDU, a 60--Watt HPA, and (optionally) an HSU. The SDU/HPA combination supports seven independent simultaneous channels for baseband voice and data communications. One channel is dedicated to baseband data and system management transactions. The remaining six channels are available for baseband analog or digital voice communications. The SDU/HSU/HPA combination allows up to four narrowband Swift64 channels (initially) or up to two wideband SwiftBroadband channels (ultimately) to operate concurrently with the system’s seven baseband channels. 4. MCS--4200/7200 Component Descriptions A. Physical Description (1) The MCS--4200/7200 system LRUs perform reliably under field conditions and permit ease of maintenance when required. Each LRU is a MCU, as defined by ARINC Characteristic 600, to permit easy replacement of each SRU. The SRUs use both digital and analog solid state circuitry constructed using a mixture of SMT and DIP technology. (2) All SRUs are built to standards that qualify them for both airline and business aircraft usage. (3) The MCS--4200/7200 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. B. Satellite Data Unit (SDU) (1) The SDU is packaged as an ARINC 600 6 MCU LRU suitable for mounting in the equipment bay. The mechanical chassis is constructed of lightweight aluminum alloy sheet metal. Forced air which moves through the chassis in an upward or downward direction supplies internal cooling. Two hold-down clamps enable the unit to be firmly secured in the mounting rack. The unit is carried by a fixed C-shaped handle mounted to the front panel assembly. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--25 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (2) The front panel assembly contains a 20-character alphanumeric display for displaying BITE failure messages, system LRU part numbers, AES ID (ICAO), ISN for each Swift64 channel and the ORT identification. The display remains active regardless of temperature. 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. (5) The SDU is shown in Figure 1-- 6. The SDU leading particulars are listed in Table 1-11. DO--160D environmental categories for the SDU are listed in Table 1-12. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--26 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 1-6. Satellite Data Unit 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--27 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 1-11. SD--720 SDU Leading Particulars Specification Characteristic 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) 25 lb. (11.4 kg) Power requirements: •AC Voltage at SDU terminals 100 to 122 V ac, 360 to 800 Hz (normal operation) 92 V ac, 320 Hz minimum; 134 V ac, 800 Hz maximum; > 96 V ac, 320 to 800 Hz (startup) •DC Voltage at SDU terminals 22.0 to 30.3 V dc (nominal operation) 20.5 to 32.2 V dc (maximum) AC current requirements 1: •Nominal at 115 V ac (current/power factor) 1.3 amps/0.70 @ 400 Hz •Maximum at 92 V ac (current/power factor) 2.0 amps/0.82 @ 800 Hz 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 15 amp TYPE A User replaceable parts None Operating temperature --67 °F (--55 °C) to + 158 °F (70 °C) Operating altitude to 55,000 ft (16.8 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 (OCXO at nominal current draw) •Maximum 150 W (OCXO at maximum current draw) NOTES: 1. All PF are leading. 2. Mounting trays with integral cooling fans that meet the cooling requirements are available from suitable vendors (such as, ECS, EMTEQ). 3. The SDU draws an additional 20 W during the first 10 minutes (maximum) of operation at 77 °F (25 °C) because of the OCXO. The OCXO continuously dissipates this additional 20 W at --67 °F (--55 °C). 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--28 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 1-11. SD--720 SDU Leading Particulars (cont) Characteristic Specification Mating connectors: •J1 Radiall Part No. NSXN2P201X0004 •J2 Honeywell Part No. 4004295--160, ITT Part No. KJ6F18A53P Mounting ARINC 600 6--MCU Tray Assembly NOTES: 1. All PF are leading. 2. Mounting trays with integral cooling fans that meet the cooling requirements are available from suitable vendors (such as, ECS, EMTEQ). 3. The SDU draws an additional 20 W during the first 10 minutes (maximum) of operation at 77 °F (25 °C) because of the OCXO. The OCXO continuously dissipates this additional 20 W at --67 °F (--55 °C). Table 1-12. SD--720 SDU DO--160D Environmental Categories Category Environmental Condition Temperature and altitude Category A2F21Z Temperature variation Category B Humidity Category A Shock Category B Vibration Category SB 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 Category A(WF)XBZ Voltage spike Category A Audio frequency susceptibility Category JZ Induced signal susceptibility Category Z Radio frequency susceptibility Category RR Radio frequency emissions Category M Lightning induced Category A2J33 Lightning direct Category X Icing Category X Electrostatic discharge Category A 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--29 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System C. High Speed Data Unit (HSU) (1) The HSU is packaged as an ARINC 600 4 MCU LRU suitable for mounting in the equipment bay. The mechanical chassis is constructed of lightweight aluminum alloy sheet metal. Forced air which moves through the chassis in an upward or downward direction supplies internal cooling. Two hold-down clamps enable the unit to be firmly secured 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 and a test port (Ethernet). The HDM is accessed via the front panel. (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 HSU is installed. The top insert is a type 08 arrangement, the middle insert is a type 02 arrangement, and the bottom insert is a type 04 arrangement. Index pin code 03 is used on both the HSU and the mounting rack connectors. (4) The HSU is shown in Figure 1-7. The HSU leading particulars are listed in Table 1-13. DO--160D environmental categories for the HSU are listed in Table 1-14. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--30 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 1-7. High Speed Data Unit 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--31 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 1-13. HS--720 HSU Leading Particulars Specification Characteristic Dimensions (maximum): •Height 7.624 in. (193.65 mm) •Width 5.04 in. (128.02 mm) •Length 15.07 in. (382.78 mm) Weight (maximum) 16 lb. (7.3 kg) Power requirements: •AC Voltage at HSU terminals 96 to 122 V ac, 360 to 800 Hz (normal operation) 92 V ac, 320 Hz minimum; 134 V ac, 800 Hz maximum; ≥ 96 V ac, 320 to 800 Hz (startup) •DC Voltage at HSU terminals 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) 1.2 amps/0.70 @ 400 Hz •Maximum at 92 V ac (current/power factor) 1.8 amps/0.79 @ 800 Hz DC current requirements: •Nominal at 28 V dc 2.0 amps •Maximum at 20.5 V dc 5.0 amps Circuit breaker ratings: •115 V ac circuit breaker 3 amp TYPE A •28 V dc circuit breaker 7.5 amp TYPE A User replaceable parts None Operating temperature --67 °F (--55 °C) to + 158 °F (70 °C) Operating altitude to 55,000 ft (16.8 kilometers) Cooling requirements 2: •Minimum 0.15 ± 0.05 in. (3.81 ± 1.27 mm) of water at a flow rate of 48.5 ± 2.0 lb. (22.0 ± 0.9 kg) per hour •Maximum 0.25 ± 0.05 in. (6.35 ± 1.27 mm) of water at a flow rate of 63.1 ± 2.0 lb. (28.7 ± 0.9 kg) per hour NOTES: 1. All PFs are leading. 2. Mounting trays with integral cooling fans that meet the cooling requirements are available from suitable vendors (such as, ECS, EMTEQ). 3. The HSU draws an additional 20 W during the first 10 minutes (maximum) of operation at 77 °F (25 °C) because of the OCXO. The OCXO continuously dissipates this additional 20 W at --67 °F (--55 °C). 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--32 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 1-13. HS--720 HSU Leading Particulars (cont) Characteristic Specification Power dissipation 3: •Nominal 55 W (OCXO at nominal current draw) •Maximum 100 W (OCXO at maximum current draw) Mating connectors: •J1 Radiall Part No. NSXN2P221X0003 •J2 Honeywell Part No. 4004295--160, ITT Part No. KJ6F18A53P Mounting ARINC 600 4--MCU Tray Assembly NOTES: 1. All PFs are leading. 2. Mounting trays with integral cooling fans that meet the cooling requirements are available from suitable vendors (such as, ECS, EMTEQ). 3. The HSU draws an additional 20 W during the first 10 minutes (maximum) of operation at 77 °F (25 °C) because of the OCXO. The OCXO continuously dissipates this additional 20 W at --67 °F (--55 °C). Table 1-14. HS--720 HSU DO--160D Environmental Categories Category Environmental Condition Temperature and altitude Category A2F2/Z Temperature variation Category B Humidity Category A Shock Category B Vibration Category SB 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 Category A(WF)HBZ Voltage spike Category A Audio frequency susceptibility Category JZ Induced signal susceptibility Category Z Radio frequency susceptibility Category RR Radio frequency emissions Category M 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--33 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 1-14. HS--720 HSU DO--160D Environmental Categories (cont) Environmental Condition Category Lightning induced Category A3J33 Lightning direct Category X Icing Category X Electrostatic discharge Category A D. High--Power Amplifier (60 Watt) (1) The HPA is an ARINC 600 8--MCU LRU 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 which moves through the chassis in an upward or downward direction supplies internal cooling. Two hold-down clamps hold the unit firmly secured 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. (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. (4) The 60 W HPA is shown in Figure 1--8. The leading particulars for the 60 W HPA are listed in Table 1-15. DO--160D environmental categories for the 60 W HPA are listed in Table 1-16. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--34 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 1-8. High Power Amplifier 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--35 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 1-15. HP--720 60W HPA Leading Particulars Specification Characteristic 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) 32.0 lb (14.5 kg) Power requirements: •AC voltage at HPA terminals 96 to 122 V ac, 360 to 800 Hz (normal operation) 92 V ac, 320 Hz minimum; 134 V ac, 800 Hz maximum; > 96 V ac, 320 to 800 Hz (startup) •DC voltage 22.0 to 30.3 V dc (normal operation), 20.5 V dc minimum, 32.2 V dc maximum AC current requirements1 : •Nominal at 115 V ac (current/power factor) 2.5 amps/0.89 @ 400 Hz •Maximum at 92 V ac (current/power factor) 5.1 amps/0.91 @ 800 Hz DC current requirements: •Nominal at 28 V dc 9 amps •Maximum at 20.5 V dc 21 amps RF power output: •Rated operating power 60 W (multiple carriers) •Maximum power 80 W (short duration, single carrier) Circuit breaker ratings: •15 V ac circuit breaker 7.5 amp TYPE A •28 V dc circuit breaker 30 amp TYPE A User replaceable parts None Operating temperature --67 °F (--55 °C) to + 158 °F (70 °C) Operating altitude to 55,000 ft (16.8 km) Cooling requirements 2: •Minimum 0.2 ± 0.12 in. (5.0 ± 3.0 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 Power dissipation: •Nominal 250 W for VSWR = 1.0 NOTES: 1. All PFs are leading. 2. Mounting trays with integral cooling fans that meet the cooling requirements can be obtained from suitable vendors (such as, ECS, EMTEQ). 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--36 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 1-15. HP--720 60W HPA Leading Particulars (cont) Characteristic Specification •Maximum 425 W for VSWR = 1.0 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 PFs are leading. 2. Mounting trays with integral cooling fans that meet the cooling requirements can be obtained from suitable vendors (such as, ECS, EMTEQ). Table 1-16. HP--720 60W HPA Environmental Categories Category Environmental Condition Temperature and altitude Category A2F2/Z Temperature variation Category B Humidity Category A Shock Category B Vibration Category SCLMY 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 Category A(WF)HBZ Voltage spike Category A Audio frequency susceptibility Category JZ Induced signal susceptibility Category Z Radio frequency susceptibility Category RR Radio frequency emissions Category M Lightning induced Category A3J33 Lightning direct Category X 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--37 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 1-16. HP--720 60W HPA Environmental Categories (cont) Environmental Condition Category Icing Category X Electrostatic discharge Category A E. Radio Frequency Unit Interface Adapter (RFUIA) (1) The RFUIA is an ARINC 600 4-MCU mounted 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 any active internal electronic components. No aircraft power is needed. This unit is installed in the aircraft in place of the RFU or HSU to complete the RF receive and transmit paths for the MCS-4200/7200 system. (3) The housing is constructed of lightweight aluminum alloy sheet metal. No forced-air cooling is required. Two hold-down clamps hold the unit firmly in the mounting rack. The unit is carried by a fixed C-shaped handle mounted to the front panel assembly. (4) Figure 1--9 is a block diagram that shows how the RFUIA interfaces to the other system LRUs. The RFUIA is shown in Figure 1--10. The leading particulars for the RFUIA are listed in Table 1-17. DO--160D environmental categories for the RFUIA are listed in Table 1-18. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--38 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 1-9. RFUIA System Interface Diagram 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--39 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 1-10. Radio Frequency Unit Interface Adapter 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--40 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 1-17. 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 Table 1-18. RFUIA DO--160D Environmental Categories Environmental Condition Category Temperature and altitude Category XXX Temperature variation Category X Humidity Category X Shock Category B Vibration Category SCLMY Explosion Category X 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 X Voltage spike Category X Audio frequency susceptibility -- 115 V ac Category X Induced signal susceptibility Category X Radio frequency susceptibility Category XXX Radio frequency emissions Category X Lightning induced Category XXXX Lightning direct Category X Icing Category X Electrostatic discharge Category X 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--41 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System F. ARINC 429 Data Requirements (1) The MCS--4200/7200 system requires ARINC 429 data for antenna pointing, antenna stabilization, and Doppler frequency correction. G. Nameplates (SDU, HSU, HPA) (1) General (a) Except for the RFUIA, each MCS--4200/7200 LRU has three externally--displayed, front panel--mounted nameplates which consist of: • A logo nameplate • A data matrix nameplate • An identification (ID) nameplate. (b) An example of the SD--720’s actual nameplate complement is shown in Figure 1-11. The nameplates for the HS--720 and HP--720 are similar. (2) Logo Nameplate (a) Each logo nameplate contains both company logos (Honeywell and Thales), the name of the system, the LRU equipment name, and the LRU model number (such as, SD--720, HS--720, or HP--720). (3) Data Matrix Nameplate (a) Each data matrix nameplate contains the information that follows: • • • • • • Name of the certifying and manufacturing company LRU equipment name Manufacturer’s FSCM code (MFR) LRU serial number (SER) LRU inspection marking LRU inspection date (DMF). (4) Identification (ID) Nameplate (a) Each identification (ID) nameplate contains the information that follows: • • • • • • • • • • • Name of the manufacturing company Model number (such as, SD--720, HS--720 or HP--720) LRU equipment name LRU end--item part number (including hardware and software portions) Weight Applicable DO--160D categories FCC identifier LRU hardware modification level LRU software modification level Applicable DO--178B software level Applicable DO--254 hardware level. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--42 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 1-11. MCS--4200/7200 SDU LRU Labels 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--43 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (b) The LRU 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. (c) The DO--160D categories applicable to the MCS–4200/7200 system consist of a mix of numeric and upper case alphabetic characters. See Table 1-12, Table 1-14, or Table 1-16 for a list of environmental categories applicable to the MCS--4200/7200 LRUs. (d) The FCC identifier applicable to all MCS--4200/7200 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. (e) The MCS--4200/7200 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 hardware configuration and consist of numeric values ranging from 10 to 99. The last three digits of the dash number reflect the LRU software configuration and consist of numeric values ranging from 001 to 999. (f) The hardware and software modification levels for any of the MCS--4200/7200 LRUs each 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 hardware and software changes in the given LRU. (g) The DO--178B software levels and DO--254 hardware levels applicable to each MCS--4200/7200 LRU indicate the level to which a given LRU was certified. The identification (ID) nameplate can be 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. H. Software and Hardware Compatibility (SDU, HSU and HPA) (1) Provisions are included in each MCS--4200/7200 LRU to ensure hardware and software compatibility. The settings for these provisions are manually changed each time a hardware revision is made that is not compatible with all previously released versions of software. The status of these settings 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--44 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 29 OF 53 FACING PAGE 1-45. Reason: To delete text that is not applicable, change the capitalization of INMARSAT to Inmarsat, and to add “and” to Paragraph 5. A. (1). Paragraph (1) is changed as follows: (1) The MCS-4200/7200 SATCOM system is a powerful and versatile airborne communications system. It provides the cockpit crew, cabin crew, and passengers with access to multi-channel satellite-based telephony and packet-data functionality based on the proven ARINC 741/761 specifications. In addition, it furnishes the cabin with Inmarsat Swift64 connectivity through both the circuit-switched (ISDN) and packet-switched (MPDS) versions of that service and the newer, faster generation of SwiftBroadband services (that is, 432 kbps channel rates). In all respects, the characteristics of the MCS-4200/7200 SATCOM system – size, weight, features, timeliness of development, etc. – are well-suited to meet airline satellite communication needs well into the future. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 29 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (2) The MCS--4200/7200 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 which is compatible with the software. 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, the software upload process will be allowed (otherwise, it will be inhibited). Similarly, if any of the codes in the software itself match the strap code in the LRU, normal LRU operation will be allowed. Otherwise, it will remain in a de--activated state. 5. Summary A. General (1) The MCS--4200/7200 SATCOM system is a powerful and versatile airborne communications system. It provides the cockpit crew, cabin crew, and passengers with access to multi-channel satellite-based telephony and packet-data functionality based on the proven ARINC 741/761 specifications. In addition, it furnishes the cabin with INMARSAT Swift64 connectivity through both the circuit--switched (ISDN) and packet--switched (MPDS) versions of that service in a configuration easily modified to accommodate the newer, faster generation of SwiftBroadband services (that is, 432 kbps channel rates) planned for late ’07 or ’08. In all respects, the characteristics of the MCS-4200/7200 SATCOM system – size, weight, features, timeliness of development, etc. – are well--suited to meet airline satellite communication needs well into the future. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--45 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Blank Page 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 1--46 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 30 OF 53 FACING PAGE 2-1. Reason: To add references to MES, UE, LES, SAS, and SwiftBroadband to Paragraph 1. A. (1) and to change the capitalization of INMARSAT to Inmarsat in Paragraph 2. A. (1). Paragraphs 1. A. (1) and 2. A. (1) are changed as follows: (1) The AES/MES/UE 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/LES/SAS through satellite. The AES/MES/UE also receives RF signals from the satellites, demodulates and decodes these signals, and outputs data or voice messages 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. If an HSU is installed, each of the Swift64 or SwiftBroadband channels will sequentially register with an LES/SAS. System operation terminates when the AES logs off from the GES. (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. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 30 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System SECTION 2 SYSTEM OPERATION 1. Overview A. General (1) 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 messages 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. If an HSU is installed, each of the Swift64 channels will sequentially register with an LES. 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 above 104 over an averaging period of 3 minutes • More than 10 short--term interruptions (loss of P--channel clock synchronization for less than 10 seconds) in any 3 minute period. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--1 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (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 • An unsucessful log-on renewal procedure. (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 that permits the GES to 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 data EIRP table, the satellite and GES identifying information, such as satellite Psid--channel frequencies, satellite locations and associated GES IDs, GES capabilities, 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. (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. Then a complete update of the data for that satellite happens. Satellite region blocks that have not yet been updated over the air are marked with a null revision number. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--2 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 31 OF 53 FACING PAGE 2-3. Reason: To add references to Swift64, SwiftBroadband, and SAS, as well as incorporate other minor changes, to Paragraphs B. (1) thru (4). Some text was deleted. Paragraphs B. (1) thru (4) are changed as follows: (1) If an HSDU is installed, each of its channels sequentially register for Swift64 or SwiftBroadband service when the AES achieves log-on. (2) The LES/SAS selected for registration is based on satellite and LES/SAS preference set in the ORT. (3) Two sets of preferences in the ORT define MPDS and ISDN preferences since service providers may be different between MPDS and ISDN. The respective MPDS or ISDN Swift64 service is only initiated if and when the service is initiated by a ground or airborne user. (4) The registration process starts with the preferred LES/SAS. A preference level of 9 is the highest and 1 is the lowest and 0 indicates no access. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 31 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System B. HSDU Installed (1) If an HSDU is installed, each of the four channels sequentially register for ISDN service when the AES achieves log--on. (2) The LES selected for registration is based on satellite and LES preference set in the ORT. (3) A second set of preferences in the ORT defines MPDS operation since service providers may be different between MPDS and ISDN. MPDS registration only occurs if and when an MPDS session is initiated. (4) The registration process starts with the preferred LES. A preference level of 9 is the highest and 1 is the lowest and 0 indicates no access. 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 (Psid) 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--3 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (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. (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. Upon receipt of a log--on reject, the AES will select the next most preferred GES. (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--4 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (11) The AES selects the appropriate EIRP setting for Rd--channels and T--channels from the data EIRP table. 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. (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. (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. (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--5 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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 selected 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. (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--6 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System E. Handover (1) The SDU causes the AES to initiate a handover procedure for the following reasons: • Automatic handover occurs when the AES is logged-on in the automatic or constrained mode, because of P--channel degradation. • Automatic handover occurs 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 occurs 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 is issued 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 is issued 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 is issued 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 is issued 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 (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--7 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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. (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--8 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 32 OF 53 FACING PAGE 2-8. Reason: To add references to HSU to Paragraph 4. A. (1). Paragraph 4. A. (1) is changed as follows: (1) Each MCS LRU (SDU, HSU, 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. The HSU is capable of software loading through its ADL/PDL ports and via its front-panel RJ-45 Ethernet port. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 32 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 33 OF 53 FACING PAGE 2-9. Reason: To add HSU to Paragraph (4). Paragraph (4) is changed as follows: (4) The HPA and HSU 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. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 33 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (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. • 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--9 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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 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. (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--10 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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 (that is, 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. (b) Insert an ORT diskette containing the ORT file SDU_ORT.TAB, plus the CONFIG.LDR file into the ADL/PDL. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--11 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (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 • Select the PDL to SDU option. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--12 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 34 OF 53 FACING PAGE 2-13. Reason: To change the capitalization of INMARSAT to Inmarsat in Paragraph 7. A. (1). Paragraph 7. A. (1) is changed as follows: (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 (that is, 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: 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 34 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (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 (that is, 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 (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--13 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 2-1. Satellite Audio System 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--14 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 35 OF 53 FACING PAGE 2-14. Reason: To add Classic Aero to the figure title for Figure 2-1. The title for Figure 2-1 is changed as follows: Figure 2-1. Classic Aero Satellite Audio System 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 35 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 36 OF 53 FACING PAGE 2-15. Reason: To add Classic Aero to the subhead for Paragraph 8 and to Paragraph 8. A. (1), and to change the capitalization of INMARSAT to Inmarsat. Paragraph 8 subhead and Paragraph 8. A. (1) are changed as follows: 8. Classic Aero Packet-Data Services (1) Classic Aero 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. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 36 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (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. (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--15 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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 (such as, 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 (such as, power control) and call termination are controlled by the slave SDU. (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--16 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (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, that is, 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. (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--17 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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 (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--18 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 37 OF 53 FACING PAGE 2-19. Reason: To add a new Paragraph D. (2) and (3) to incorporate references to SBB operation and to renumber the existing Paragraph D. (2) to (4). Paragraph (2) is renumbered to (4) and new Paragraphs D. (2) and (3) are added as follows: (2) For SBB operation, the selected antenna must be an Inmarsat-approved type for this service class. (3) For SBB operation, the selected D/LNA must be Type F (or later type that is approved for SBB operation). (4) The basic configurations supported by the MCS dual system design are as given in Table 2-2. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 37 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (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 — that is, 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 — that is, (HGA+LGA) + HGA. (2) The basic configurations supported by the MCS dual system design are as given in Table 2-2. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--19 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 2-2. Basic Antenna Configurations SDU No. 2 SDU No. 1 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 six 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 show the three types of the HGA + HGA configuration. This configuration is normally capable of providing 12 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. (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.) 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--20 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 38 OF 53 FACING PAGE 2-20. Reason: To add a new Paragraph (8) to incorporate SBB operation. Paragraph (8) is added as follows: (8) For SBB operation, the selected antenna must be an Inmarsat-approved type for this service class. 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 38 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 2-3. HGA + LGA Configuration with Top-Mounted HGAs Figure 2-4. HGA + LGA Configuration with Side-Mounted HGAs 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--21 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 2-5. HGA + HGA Configuration with Two Top-Mounted HGAs Figure 2-6. HGA + HGA Configuration with Two Side-Mounted HGAs 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--22 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 2-7. HGA + HGA Configuration with One Side-Mounted HGA + One Top-Mounted HGA (Dissimilar HGA) Figure 2-8. LGA + LGA Configuration 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--23 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 2-9. (HGA + LGA) + HGA Configuration with Two Side-Mounted HGAs 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--24 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 2-10. (HGA + LGA) + HGA Configuration with the LGA Paired with One Side-Mounted HGA 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--25 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 2-11. (HGA + LGA) + HGA Configuration with the LGA Paired with One Top-Mounted HGA 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--26 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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). (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 (that is, 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 — that is, 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--27 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Blank Page 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 2--28 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4200/7200 TEMPORARY REVISION NO. 23-1 INSERT PAGE 39 OF 53 FACING PAGE 3-1. Reason: To add Classic Aero to the heading of Paragraph 1. Paragraph 1 is changed as follows: 1. Classic Aero (SDU-based) Cabin Communications 23-20-35 © Honeywell International Inc. Do not copy without express permission of Honeywell. Page 39 of 53 28 Sep 2009 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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). (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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 3--1 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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 (that is, turn on the call lamps) while the voice codec associated with that analog channel is in use (off-hook) by the analog handset. (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. (e) Figure 3-1 shows Audio Interfaces. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 3--2 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Figure 3-1. Audio Interfaces 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 3--3/3--4 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 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 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 3--5 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System (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. (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 (that is, go on-hook, then off-hook) to signal the off-hook state to the SDU. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 3--6 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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. 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 3--7 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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 causes 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 message 18 (command rejected). 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. That is, the SDU responds to the commands with message 18 (command rejected). The GES preference commands are specified as follows. **60 This command sets the preference levels for all GESs to 1. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 3--8 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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# If any of the following incoming call management commands are rejected, the SDU plays message 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: that is, 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, such as, 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: 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 3--9 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System Table 3-2. 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 3--10 15 Jul 2006 SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS--4200/7200 Multi--Channel SATCOM System 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 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. 23--20--35 Honeywell International Inc. Do not copy without express permission of Honeywell. Page 3--11 15 Jul 2006
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