Honeywell SD-700A Satcom Transceiver User Manual

Honeywell International Inc. Satcom Transceiver

User Manual

  SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4000/7000  TEMPORARY REVISION NO. 23-2     23-20-27 Page 1 of 3 20 Jun 2017                                                  © Honeywell International Inc. Do not copy without express permission of Honeywell. TO HOLDERS OF MCS-4000/7000 MULTI-CHANNEL SATCOM SYSTEM SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL 23-20-27, REVISION 2, DATED 5 FEB 2008. INSERT THIS PAGE AS THE FIRST PAGE OF THE MANUAL.  Temporary Revision Number   Applicable Page Number 23-2 1-13  4-5/(4-6 BLANK)  Honeywell – Confidential THIS COPYRIGHTED WORK AND ALL INFORMATION ARE THE PROPERTY OF HONEYWELL INTERNATIONAL INC., CONTAIN TRADE SECRETS AND MAY NOT, IN WHOLE OR IN PART, BE USED, DUPLICATED, OR DISCLOSED FOR ANY PURPOSE WITHOUT PRIOR WRITTEN PERMISSION OF HONEYWELL INTERNATIONAL INC. ALL RIGHTS RESERVED.  Copyright - Notice Copyright 2017 Honeywell International Inc. All rights reserved. Honeywell is a registered trademark of Honeywell International Inc. All other marks are owned by their respective companies.    RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
  SYSTEM DESCRIPTION, INSTALLATION AND MAINTENANCE MANUAL MCS-4000/7000 TEMPORARY REVISION NO. 23-1   23-20-27  Page 1 of 630 Oct 2009Publication Number D200102000060 © Honeywell International Inc. Do not copy without express permission of Honeywell. TO HOLDERS OF MCS-4000/7000 MULTI-CHANNEL SATCOM SYSTEM SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL 23-20-27, REVISION 2, DATED 5 FEB 2008.  INSERT THIS PAGE AS THE FIRST PAGE OF THE MANUAL.  Temporary Revision Number   Applicable Page Number 23-1 4-1  4-2  4-3   Copyright - Notice Copyright 2009 Honeywell International Inc. All rights reserved. Honeywell is a registered trademark of Honeywell International Inc. All other marks are owned by their respective companies.  Honeywell – Confidential 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.    RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
Honeywell International Inc.21111 N. 19th Ave.Phoenix, AZ 85027-2708U.S.A.CAGE: 5896023--20--275 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page HL--1Telephone: (800) 601--3099 (U.S.A.)Telephone: (602) 365--3099 (International)TO HOLDERS OF SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCEMANUAL, PUB. NO. A15--5111--001, MCS 4000/7000 MULTI--CHANNELSATCOM SYSTEMREVISION NO. 002 DATED 5FEB2008This revision replaces some data in the manual. All changed pages have a new date, as identifiedin the List of Effective Pages. Revision bars identify the changed data. An “R” adjacent to theFig./Item column identifies changes in the Detailed Parts List.Put the changed pages in the manual and remove and discard all replaced pages. Write therevision number, revision date, and replacement date on the Record of Revisions page.Insert Page Description of ChangeT--1 thru T--4 Changed to show the revision date. Expanded the proprietary notice. Changed thepublication number from A15--5111--001 to D200102000060. Added the exportcontrol code.LEP--1 thru LEP--8 Changed to show the changed pages in manual.------ Removed the Business Reply Card (User Registration Card), Customer Responseform, and Report of Possible Data Error form because this data is available on theHoneywell Online Technical Publications Web site. The location of the Web site isincluded in the INTRODUCTION.TC--1 thru TC--14 Changed to include Appendix D in the TESTING/FAULT ISOLATION section.INTRO--1 thruINTRO--10 Replaced all pages of the INTRODUCTION. Revision bars are not used in theINTRODUCTION to show these changes. Removed the Proprietary Notice andExport Notice data. Added a Customer Support paragraph. Changed the sequenceof the INTRODUCTION data. Changed References, Verification Data, andAcronyms and Abbreviations data.1--12, 1--14 Corrected references to Figure 1--6 and Figure 1--7.6--1 Added statement in paragraph 1.A (1) to reference Appendix D system fault codes.C--8 Corrected reference to Table C--1.D--1 thru D--146 Added system fault codes as Appendix D.INDEX--3 Added an index entry for fault codes.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page HL--2Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
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 administrationregulations. Diversion contrary to U.S. law is prohibited.ECCN: 7E994, no license required.Honeywell International Inc.21111 N. 19th Ave.Phoenix, AZ 85027-2708U.S.A.CAGE: 58960Publication Number D200102000060, Revision 002(Formerly A15--5111--001)23--20--27Page T--1Revised 5 Feb 20081 Feb 2001©Honeywell International Inc. Do not copy without express permission of Honeywell.Telephone: (800) 601--3099 (U.S.A.)Telephone: (602) 365--3099 (International)System Description, Installation, andMaintenance ManualMCS--4000/7000Multi--Channel SATCOM SystemRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page T--2Honeywell--ConfidentialTHIS COPYRIGHTED WORK AND ALL INFORMATION ARE THE PROPERTY OF HONEYWELLINTERNATIONAL INC., CONTAIN TRADE SECRETS AND MAY NOT, IN WHOLE OR IN PART, BEUSED, DUPLICATED, OR DISCLOSED FOR ANY PURPOSE WITHOUT PRIOR WRITTENPERMISSION OF HONEYWELL INTERNATIONAL INC. ALL RIGHTS RESERVED.Honeywell Materials License AgreementThe documents and information contained herein (“the Materials”) are the proprietary data ofHoneywell 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 anapplicable product support agreement, their wholly owned--subsidiaries or a formallydesignated third party service provider; and direct recipients of Materials from Honeywell’sAerospace Technical Publication Distribution. The terms and conditions of this LicenseAgreement govern your use of these Materials, except to the extent that any terms andconditions of another applicable agreement with Honeywell regarding the operation,maintenance, or repair of Honeywell aerospace products conflict with the terms and conditionsof this License Agreement, in which case the terms and conditions of the other agreement willgovern. However, this License Agreement will govern in the event of a conflict between itsterms 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 Centeragreement, or an authorized repair facility agreement, Honeywell hereby grants you a limited, non--exclusive licenseto use these Materials to operate, maintain, or repair Honeywell aerospace products only in accordance with thatagreement.If you are a direct recipient of these Materials from Honeywell’s Aerospace Technical Publication Distribution and arenot 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 subjectHoneywell aerospace products only at the facility to which these Materials have been shipped (“the LicensedFacility”). Transfer of the Materials to another facility owned by you is permitted only if the original Licensed Facilityretains 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 notexpressly granted to you, including all rights in patents, copyrights, trademarks, and trade secrets. No license to useany Honeywell trademarks or patents is granted under this License Agreement.3. Confidentiality -- You acknowledge that these Materials contain information that is confidential and proprietary toHoneywell. 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 servicedesignee or transferred to a subsequent owner or operator of an aircraft containing the subject Honeywell aerospaceproducts. However, the recipient of any such assignment or transfer must assume all of your obligations under thisLicense Agreement. No assignment or transfer shall relieve any party of any obligation that such party then hashereunder.5. Copies of Materials -- Unless you have the express written permission of Honeywell, you may not make or permitmaking of copies of the Materials. Notwithstanding the foregoing, you may make copies of only portions of theMaterial for your internal use. You agree to return the Materials and any copies thereof to Honeywell upon therequest of Honeywell.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page T--36. Term -- This License Agreement is effective until terminated as set forth herein. This License Agreement willterminate immediately, without notice from Honeywell, if you fail to comply with any provision of this LicenseAgreement or will terminate simultaneously with the termination or expiration of your applicable product supportagreement, authorized repair facility agreement, or your formal designation as a third party service provider. Upontermination of this License Agreement, you will return these Materials to Honeywell without retaining any copies andwill 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 breachof this License Agreement.8. Limitation of Liability -- Honeywell does not make any representation regarding the use or sufficiency of theMaterials. THERE ARE NO OTHER WARRANTIES, WHETHER WRITTEN OR ORAL, EXPRESS, IMPLIED ORSTATUTORY, INCLUDING, BUT NOT LIMITED TO, (i) WARRANTIES ARISING FROM COURSE OFPERFORMANCE, DEALING, USAGE, OR TRADE, WHICH ARE HEREBY EXPRESSLY DISCLAIMED, OR (ii)WARRANTIES AGAINST INFRINGEMENT OF INTELLECTUAL PROPERTY RIGHTS OF THIRD PARTIES, EVENIF HONEYWELL HAS BEEN ADVISED OF ANY SUCH INFRINGEMENT. IN NO EVENT WILL HONEYWELL BELIABLE FOR ANY INCIDENTAL DAMAGES, CONSEQUENTIAL DAMAGES, SPECIAL DAMAGES, INDIRECTDAMAGES, LOSS OF PROFITS, LOSS OF REVENUES, OR LOSS OF USE, EVEN IF INFORMED OF THEPOSSIBILITY OF SUCH DAMAGES. TO THE EXTENT PERMITTED BY APPLICABLE LAW, THESE LIMITATIONSAND EXCLUSIONS WILL APPLY REGARDLESS OF WHETHER LIABILITY ARISES FROM BREACH OFCONTRACT, 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 NewYork without regard to the conflicts of laws provisions thereof. This license sets forth the entire agreement betweenyou and Honeywell and may only be modified by a writing duly executed by the duly authorized representatives ofthe parties.Copyright -- NoticeCopyright 2001, 2008, Honeywell International Inc. All rights reserved.Honeywell is a registered trademark of Honeywell International Inc.All other marks are owned by their respective companies.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page T--4Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 30 Aug 2002©Honeywell International Inc. Do not copy without express permission of Honeywell.Page RR--1RECORD OF REVISIONSFor each revision, put the revised pages in your manual and discard the superseded pages. Writethe revision number and date, date put in manual, and the incorporator’s initials in the applicablecolumns on the Record of Revisions. The initial H shows Honeywell is the incorporator.RevisionNumber RevisionDate Date PutIn Manual By RevisionNumber RevisionDate Date PutIn Manual By130 Aug 2002 30 Aug 2002 H25 Feb 2008 5 Feb 2008 HRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page RR--2Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page RTR--1RECORD OF TEMPORARY REVISIONSInstructions 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 temporaryrevision, put the applicable data in the record columns on this page.TemporaryRevisionNumberTemporaryRevisionDateTemporaryRevisionStatusDate Putin Manual By *DateRemovedfrom Manual By ** The initial H in this column shows Honeywell has done this task.** Temporary revisions are incorporated in the manual by normal revision.23-1               30 OCT 2017                                       30 OCT 2017          H       23-2                20 JUN 2017                                       20 JUN 2017           HRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page RTR--2Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page SBL--1SERVICE BULLETIN LISTService BulletinIdentifiedModDate Includedin this Manual DescriptionRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page SBL--2Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--275 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page LEP--1LIST OF EFFECTIVE PAGESSubheading and Page Date Subheading and Page DateTitleT--1 H5 Feb 2008T--2 H5 Feb 2008T--3 H5 Feb 2008T--4 H5 Feb 2008Record of RevisionsRR--1 30 Aug 2002RR--2 30 Aug 2002Record of Temporary RevisionsRTR--1 30 Aug 2002RTR--2 30 Aug 2002Service Bulletin ListSBL--1 30 Aug 2002SBL--2 30 Aug 2002List of Effective PagesLEP--1 H5 Feb 2008LEP--2 H5 Feb 2008LEP--3 H5 Feb 2008LEP--4 H5 Feb 2008LEP--5 H5 Feb 2008LEP--6 H5 Feb 2008LEP--7 H5 Feb 2008LEP--8 H5 Feb 2008Table of ContentsTC--1 H5 Feb 2008TC--2 H5 Feb 2008TC--3 H5 Feb 2008TC--4 H5 Feb 2008TC--5 H5 Feb 2008TC--6 H5 Feb 2008TC--7 H5 Feb 2008TC--8 H5 Feb 2008TC--9 H5 Feb 2008TC--10 H5 Feb 2008TC--11 H5 Feb 2008TC--12 H5 Feb 2008TC--13 H5 Feb 2008TC--14 H5 Feb 2008IntroductionINTRO--1 H5 Feb 2008INTRO--2 H5 Feb 2008INTRO--3 H5 Feb 2008INTRO--4 H5 Feb 2008INTRO--5 H5 Feb 2008INTRO--6 H5 Feb 2008INTRO--7 H5 Feb 2008INTRO--8 H5 Feb 2008INTRO--9 H5 Feb 2008INTRO--10 H5 Feb 2008System Description1--1 30 Aug 20021--2 30 Aug 2002F1--3/1--4 30 Aug 20021--5 30 Aug 20021--6 30 Aug 20021--7 30 Aug 20021--8 30 Aug 20021--9 30 Aug 20021--10 30 Aug 20021--11 30 Aug 20021--12 H5 Feb 20081--13 30 Aug 20021--14 H5 Feb 20081--15 30 Aug 20021--16 30 Aug 2002F1--17/1--18 30 Aug 20021--19 30 Aug 20021--20 30 Aug 20021--21 30 Aug 2002Hindicates a changed or added page.F indicates a foldout page.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page LEP--2Subheading and Page Date Subheading and Page Date1--22 30 Aug 20021--23 30 Aug 20021--24 30 Aug 20021--25 30 Aug 20021--26 30 Aug 20021--27 30 Aug 20021--28 30 Aug 20021--29 30 Aug 20021--30 30 Aug 2002F1--31/1--32 30 Aug 20021--33 30 Aug 20021--34 30 Aug 20021--35 30 Aug 20021--36 30 Aug 20021--37 30 Aug 20021--38 30 Aug 20021--39 30 Aug 20021--40 30 Aug 20021--41 30 Aug 20021--42 30 Aug 20021--43 30 Aug 20021--44 30 Aug 20021--45 30 Aug 20021--46 30 Aug 2002System Operation2--1 30 Aug 20022--2 30 Aug 20022--3 30 Aug 20022--4 30 Aug 20022--5 30 Aug 20022--6 30 Aug 20022--7 30 Aug 20022--8 30 Aug 20022--9 30 Aug 20022--10 30 Aug 20022--11 30 Aug 20022--12 30 Aug 20022--13 30 Aug 20022--14 30 Aug 20022--15 30 Aug 20022--16 30 Aug 20022--17 30 Aug 20022--18 30 Aug 20022--19 30 Aug 20022--20 30 Aug 20022--21 30 Aug 20022--22 30 Aug 20022--23 30 Aug 20022--24 30 Aug 20022--25 30 Aug 20022--26 30 Aug 20022--27 30 Aug 20022--28 30 Aug 2002Cabin/Cockpit Communications3--1 30 Aug 20023--2 30 Aug 2002F3--3/3--4 30 Aug 20023--5 30 Aug 20023--6 30 Aug 20023--7 30 Aug 20023--8 30 Aug 20023--9 30 Aug 20023--10 30 Aug 20023--11 30 Aug 20023--12 30 Aug 20023--13 30 Aug 20023--14 30 Aug 20023--15 30 Aug 20023--16 30 Aug 20023--17 30 Aug 20023--18 30 Aug 2002Mechanical Installation4--1 30 Aug 20024--2 30 Aug 20024--3 30 Aug 20024--4 30 Aug 2002F4--5/4--6 30 Aug 2002Hindicates a changed or added page.F indicates a foldout page.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page LEP--3Subheading and Page Date Subheading and Page DateF4--7/4--8 30 Aug 2002F4--9/4--10 30 Aug 2002F4--11/4--12 30 Aug 2002F4--13/4--14 30 Aug 2002F4--15/4--16 30 Aug 2002F4--17/4--18 30 Aug 2002F4--19/4--20 30 Aug 2002F4--21/4--22 30 Aug 2002F4--23/4--24 30 Aug 2002Electrical Installation5--1 30 Aug 20025--2 30 Aug 20025--3 30 Aug 20025--4 30 Aug 20025--5 30 Aug 20025--6 30 Aug 20025--7 30 Aug 20025--8 30 Aug 20025--9 30 Aug 20025--10 30 Aug 20025--11 30 Aug 20025--12 30 Aug 20025--13 30 Aug 20025--14 30 Aug 20025--15 30 Aug 20025--16 30 Aug 20025--17 30 Aug 20025--18 30 Aug 20025--19 30 Aug 20025--20 30 Aug 20025--21 30 Aug 20025--22 30 Aug 20025--23 30 Aug 20025--24 30 Aug 20025--25 30 Aug 20025--26 30 Aug 2002F5--27/5--28 30 Aug 2002F5--29/5--30 30 Aug 2002F5--31/5--32 30 Aug 20025--33 30 Aug 20025--34 30 Aug 2002F5--35/5--36 30 Aug 2002F5--37/5--38 30 Aug 2002F5--39/5--40 30 Aug 2002F5--41/5--42 30 Aug 2002F5--43/5--44 30 Aug 20025--45 30 Aug 20025--46 30 Aug 20025--47 30 Aug 20025--48 30 Aug 20025--49 30 Aug 20025--50 30 Aug 20025--51 30 Aug 20025--52 30 Aug 20025--53 30 Aug 20025--54 30 Aug 20025--55 30 Aug 20025--56 30 Aug 20025--57 30 Aug 20025--58 30 Aug 20025--59 30 Aug 20025--60 30 Aug 2002Testing/Fault Isolation6--1 H5 Feb 20086--2 30 Aug 20026--3 30 Aug 20026--4 30 Aug 20026--5 30 Aug 20026--6 30 Aug 20026--7 30 Aug 20026--8 30 Aug 20026--9 30 Aug 20026--10 30 Aug 20026--11 30 Aug 20026--12 30 Aug 20026--13 30 Aug 20026--14 30 Aug 20026--15 30 Aug 2002Hindicates a changed or added page.F indicates a foldout page.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page LEP--4Subheading and Page Date Subheading and Page Date6--16 30 Aug 20026--17 30 Aug 20026--18 30 Aug 20026--19 30 Aug 20026--20 30 Aug 20026--21 30 Aug 20026--22 30 Aug 20026--23 30 Aug 20026--24 30 Aug 20026--25 30 Aug 20026--26 30 Aug 20026--27 30 Aug 20026--28 30 Aug 20026--29 30 Aug 20026--30 30 Aug 20026--31 30 Aug 20026--32 30 Aug 20026--33 30 Aug 20026--34 30 Aug 20026--35 30 Aug 20026--36 30 Aug 20026--37 30 Aug 20026--38 30 Aug 20026--39 30 Aug 20026--40 30 Aug 20026--41 30 Aug 20026--42 30 Aug 20026--43 30 Aug 20026--44 30 Aug 20026--45 30 Aug 20026--46 30 Aug 20026--47 30 Aug 20026--48 30 Aug 20026--49 30 Aug 20026--50 30 Aug 20026--51 30 Aug 20026--52 30 Aug 20026--53 30 Aug 20026--54 30 Aug 20026--55 30 Aug 20026--56 30 Aug 20026--57 30 Aug 20026--58 30 Aug 20026--59 30 Aug 20026--60 30 Aug 20026--61 30 Aug 20026--62 30 Aug 20026--63 30 Aug 20026--64 30 Aug 20026--65 30 Aug 20026--66 30 Aug 20026--67 30 Aug 20026--68 30 Aug 20026--69 30 Aug 20026--70 30 Aug 20026--71 30 Aug 20026--72 30 Aug 20026--73 30 Aug 20026--74 30 Aug 20026--75 30 Aug 20026--76 30 Aug 20026--77 30 Aug 20026--78 30 Aug 20026--79 30 Aug 20026--80 30 Aug 20026--81 30 Aug 20026--82 30 Aug 20026--83 30 Aug 20026--84 30 Aug 20026--85 30 Aug 20026--86 30 Aug 20026--87 30 Aug 20026--88 30 Aug 20026--89 30 Aug 20026--90 30 Aug 20026--91 30 Aug 20026--92 30 Aug 20026--93 30 Aug 2002Hindicates a changed or added page.F indicates a foldout page.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page LEP--5Subheading and Page Date Subheading and Page Date6--94 30 Aug 20026--95 30 Aug 20026--96 30 Aug 20026--97 30 Aug 20026--98 30 Aug 20026--99 30 Aug 20026--100 30 Aug 20026--101 30 Aug 20026--102 30 Aug 20026--103 30 Aug 20026--104 30 Aug 20026--105 30 Aug 20026--106 30 Aug 20026--107 30 Aug 20026--108 30 Aug 20026--109 30 Aug 20026--110 30 Aug 20026--111 30 Aug 20026--112 30 Aug 2002Maintenance Practices7--1 30 Aug 20027--2 30 Aug 20027--3 30 Aug 20027--4 30 Aug 20027--5 30 Aug 20027--6 30 Aug 2002Appendix AVendor EquipmentA--1 30 Aug 2002A--2 30 Aug 2002A--3 30 Aug 2002A--4 30 Aug 2002FA--5/A--6 30 Aug 2002A--7 30 Aug 2002A--8 30 Aug 2002A--9 30 Aug 2002A--10 30 Aug 2002A--11 30 Aug 2002A--12 30 Aug 2002FA--13/A--14 30 Aug 2002A--15 30 Aug 2002A--16 30 Aug 2002A--17 30 Aug 2002A--18 30 Aug 2002A--19 30 Aug 2002A--20 30 Aug 2002A--21 30 Aug 2002A--22 30 Aug 2002A--23 30 Aug 2002A--24 30 Aug 2002A--25 30 Aug 2002A--26 30 Aug 2002A--27 30 Aug 2002A--28 30 Aug 2002A--29 30 Aug 2002A--30 30 Aug 2002Appendix BInstallation Procedures For SATCOM Air FiltrationSystemsB--1 30 Aug 2002B--2 30 Aug 2002B--3 30 Aug 2002B--4 30 Aug 2002B--5 30 Aug 2002B--6 30 Aug 2002B--7 30 Aug 2002B--8 30 Aug 2002Appendix COwner Requirements TableC--1 30 Aug 2002C--2 30 Aug 2002C--3 30 Aug 2002C--4 30 Aug 2002C--5 30 Aug 2002C--6 30 Aug 2002C--7 30 Aug 2002C--8 30 Aug 2002C--9 30 Aug 2002Hindicates a changed or added page.F indicates a foldout page.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page LEP--6Subheading and Page Date Subheading and Page DateC--10 30 Aug 2002C--11 30 Aug 2002C--12 30 Aug 2002C--13 30 Aug 2002C--14 30 Aug 2002Appendix DFault CodesD--1 H5 Feb 2008D--2 H5 Feb 2008D--3 H5 Feb 2008D--4 H5 Feb 2008D--5 H5 Feb 2008D--6 H5 Feb 2008D--7 H5 Feb 2008D--8 H5 Feb 2008D--9 H5 Feb 2008D--10 H5 Feb 2008D--11 H5 Feb 2008D--12 H5 Feb 2008D--13 H5 Feb 2008D--14 H5 Feb 2008D--15 H5 Feb 2008D--16 H5 Feb 2008D--17 H5 Feb 2008D--18 H5 Feb 2008D--19 H5 Feb 2008D--20 H5 Feb 2008D--21 H5 Feb 2008D--22 H5 Feb 2008D--23 H5 Feb 2008D--24 H5 Feb 2008D--25 H5 Feb 2008D--26 H5 Feb 2008D--27 H5 Feb 2008D--28 H5 Feb 2008D--29 H5 Feb 2008D--30 H5 Feb 2008D--31 H5 Feb 2008D--32 H5 Feb 2008D--33 H5 Feb 2008D--34 H5 Feb 2008D--35 H5 Feb 2008D--36 H5 Feb 2008D--37 H5 Feb 2008D--38 H5 Feb 2008D--39 H5 Feb 2008D--40 H5 Feb 2008D--41 H5 Feb 2008D--42 H5 Feb 2008D--43 H5 Feb 2008D--44 H5 Feb 2008D--45 H5 Feb 2008D--46 H5 Feb 2008D--47 H5 Feb 2008D--48 H5 Feb 2008D--49 H5 Feb 2008D--50 H5 Feb 2008D--51 H5 Feb 2008D--52 H5 Feb 2008D--53 H5 Feb 2008D--54 H5 Feb 2008D--55 H5 Feb 2008D--56 H5 Feb 2008D--57 H5 Feb 2008D--58 H5 Feb 2008D--59 H5 Feb 2008D--61 H5 Feb 2008D--62 H5 Feb 2008D--63 H5 Feb 2008D--64 H5 Feb 2008D--65 H5 Feb 2008D--66 H5 Feb 2008D--67 H5 Feb 2008D--68 H5 Feb 2008D--69 H5 Feb 2008D--70 H5 Feb 2008D--71 H5 Feb 2008D--72 H5 Feb 2008Hindicates a changed or added page.F indicates a foldout page.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page LEP--7Subheading and Page Date Subheading and Page DateD--73 H5 Feb 2008D--74 H5 Feb 2008D--75 H5 Feb 2008D--76 H5 Feb 2008D--77 H5 Feb 2008D--78 H5 Feb 2008D--79 H5 Feb 2008D--80 H5 Feb 2008D--81 H5 Feb 2008D--82 H5 Feb 2008D--83 H5 Feb 2008D--84 H5 Feb 2008D--85 H5 Feb 2008D--86 H5 Feb 2008D--87 H5 Feb 2008D--88 H5 Feb 2008D--89 H5 Feb 2008D--90 H5 Feb 2008D--91 H5 Feb 2008D--92 H5 Feb 2008D--93 H5 Feb 2008D--94 H5 Feb 2008D--95 H5 Feb 2008D--96 H5 Feb 2008D--97 H5 Feb 2008D--98 H5 Feb 2008D--99 H5 Feb 2008D--100 H5 Feb 2008D--101 H5 Feb 2008D--102 H5 Feb 2008D--103 H5 Feb 2008D--104 H5 Feb 2008D--105 H5 Feb 2008D--106 H5 Feb 2008D--107 H5 Feb 2008D--108 H5 Feb 2008D--109 H5 Feb 2008D--110 H5 Feb 2008D--111 H5 Feb 2008D--112 H5 Feb 2008D--113 H5 Feb 2008D--114 H5 Feb 2008D--115 H5 Feb 2008D--116 H5 Feb 2008D--117 H5 Feb 2008D--118 H5 Feb 2008D--119 H5 Feb 2008D--120 H5 Feb 2008D--121 H5 Feb 2008D--122 H5 Feb 2008D--123 H5 Feb 2008D--124 H5 Feb 2008D--125 H5 Feb 2008D--126 H5 Feb 2008D--127 H5 Feb 2008D--128 H5 Feb 2008D--129 H5 Feb 2008D--130 H5 Feb 2008D--131 H5 Feb 2008D--132 H5 Feb 2008D--133 H5 Feb 2008D--134 H5 Feb 2008D--135 H5 Feb 2008D--136 H5 Feb 2008D--137 H5 Feb 2008D--138 H5 Feb 2008D--139 H5 Feb 2008D--140 H5 Feb 2008D--141 H5 Feb 2008D--142 H5 Feb 2008D--143 H5 Feb 2008D--144 H5 Feb 2008D--145 H5 Feb 2008D--146 H5 Feb 2008Hindicates a changed or added page.F indicates a foldout page.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page LEP--8Subheading and Page Date Subheading and Page DateIndexINDEX--1 30 Aug 2002INDEX--2 30 Aug 2002INDEX--3 H5 Feb 2008INDEX--4 30 Aug 2002INDEX--5 30 Aug 2002INDEX--6 30 Aug 2002INDEX--7 30 Aug 2002INDEX--8 30 Aug 2002Hindicates a changed or added page.F indicates a foldout page.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--1TABLE OF CONTENTSSubject PageINTRODUCTION INTRO--1...........................................................1. How to Use this Manual INTRO--1.................................................A. General INTRO--1...........................................................B. Symbols INTRO--1..........................................................C. Weights and Measurements INTRO--1.........................................2. Customer Support INTRO--2......................................................A. Honeywell Aerospace Online Technical Publications Web Site INTRO--2...........B. Complete Customer Care Center INTRO--2.....................................3. References INTRO--2............................................................A. Honeywell Publications INTRO--2.............................................B. Other Publications INTRO--2..................................................4. Acronyms and Abbreviations INTRO--3............................................A. General INTRO--3...........................................................5. Maximum Permissible Exposure Level INTRO--8....................................A. General INTRO--8...........................................................SECTION 1SYSTEM DESCRIPTION 1--1...................................................1. Overview 1--1..............................................................A. General 1--1...........................................................B. Aircraft Earth Station 1--2................................................C. Space Segment 1--9....................................................D. Ground Earth Station 1--9...............................................E. Terrestrial Data and Voice Networks 1--9..................................2. System Components 1--12...................................................A. General 1--12...........................................................3. System Description 1--14.....................................................A. General 1--14...........................................................B. Satellite Data Unit 1--19..................................................C. High Power Amplifier 1--24...............................................D. Avionics Configurations 1--25.............................................4. MCS Component Descriptions 1--25...........................................A. Physical Description 1--25................................................B. Satellite Data Unit (SDU) 1--26............................................C. High--Power Amplifier (40 Watt) 1--30......................................D. High--Power Amplifier (20 Watt) 1--35......................................E. CMA--2200 Intermediate Gain Antenna 1--38...............................F. CMA--2200 Diplexer/Low Noise Amplifier 1--40..............................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--2Subject PageG. Radio Frequency Unit Interface Adapter (RFUIA) 1--43.......................H. ARINC 429 Data Requirements 1--44......................................I. Nameplates 3 (SDU and HPA) 1--44.......................................J. Software and Hardware Compatibility (SDU and HPA) 1--46..................SECTION 2SYSTEM OPERATION 2--1.....................................................1. Overview 2--1..............................................................A. General 2--1...........................................................2. AES Management 2--1......................................................A. General 2--1...........................................................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...........................................................4. 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.................................5. Owner Requirements Table 2--10..............................................A. General 2--10...........................................................6. ORT Upload/Download Process 2--11..........................................A. General 2--11...........................................................B. Startup 2--11............................................................C. ORT Download 2--11....................................................D. Control Mode ORT Upload Procedures 2--11................................E. Auto Mode ORT Upload Procedure 2--13...................................7. Circuit-Mode Services 2--13..................................................A. Circuit-Mode Voice 2--13.................................................B. Circuit-Mode Data 2--13..................................................8. Packet-Data Services 2--15...................................................A. General 2--15...........................................................9. 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.............................................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--3Subject PageE. Cockpit Voice Configurations and Functionality 2--27.........................10. ACARS/Aircraft Flight Information System (AFIS) Peripheral Function 2--28........A. General 2--28...........................................................SECTION 3CABIN/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.............................................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 4MECHANICAL INSTALLATION 4--1..............................................1. Overview 4--1..............................................................A. General 4--1...........................................................2. Equipment and Materials 4--1................................................A. General 4--1...........................................................3. 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 5ELECTRICAL INSTALLATION 5--1..............................................1. Overview 5--1..............................................................A. General 5--1...........................................................2. Equipment and Materials 5--1................................................A. General 5--1...........................................................3. Electrical Installation Procedure 5--1..........................................A. Connector Layout and Contact Arrangement 5--1...........................B. Electrical Installation 5--16................................................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--4Subject Page4. Configuration Pins 5--45......................................................A. General 5--45...........................................................B. Availability of ARINC 429 SSR MODE S (AES ID) from CMU Ports 5--46.......C. FMC Connection to SDU 5--48............................................D. ARINC 429 Speed to/from CMU No. 1 and CMU No. 2 5--48..................E. Cabin Packet Data Function (CPDF) 5--49..................................F. ARINC 429 BUS Speed of AES ID Input 5--49..............................G. Strap Parity (ODD) 5--49.................................................H. Cabin Communications System (CCS) 5--50................................I. Inertial Reference System (IRS) 5--51......................................J. HPA/Antenna Subsystem Configuration 5--51...............................K. CFDS/CMC 5--53........................................................L. SDU Configuration 5--54.................................................M. SDU Number 5--54......................................................N. CMU No. 1 and No. 2 Configuration 5--55..................................O. MCDU/SCDU No. 1 thru No. 3 Configuration 5--55...........................P. Priority 4 Calls to/from Cockpit 5--56.......................................Q. ARINC 429 BUS Speed to SCDU No. 1 / SCDU No. 2 / SCDU No. 3 5--57......R. Cockpit Voice Call Light/Chime Option 5--57................................S. SDU CODEC 1 and CODEC 2 Wiring 5--58.................................T. Cockpit Hookswitch Signaling Method 5--58................................SECTION 6TESTING/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--18...................................I. Maintenance Activity Log 6--19............................................2. SATCOM Control and Display Unit 6--20.......................................A. General 6--20...........................................................B. SCDU Display Terminology and Basic Operation 6--20.......................C. SCDU Page Hierarchy 6--24..............................................D. SCDU Pages 6--24......................................................3. Maintenance Computer Interface 6--84.........................................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--275 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--5Subject PageA. General 6--84...........................................................B. Boeing 747--400 CMC/777 OMS 6--84.....................................C. Airbus/Douglas CFDS 6--87...............................................D. Central Aircraft Information and Maintenance System 6--88...................E. Level I Failure Messages and ATA Reference Numbers 6--89.................4. SCDU for Dual SATCOM 6--110................................................A. General 6--110...........................................................B. SATCOM Logical Channels 6--110..........................................C. SATCOM MAIN MENU (Cross-Talk Bus Failed) 6--110........................D. SATCOM CHANNEL STATUS 6--110.......................................E. SATCOM MAINTENANCE Menus 6--110....................................5. Maintenance Panel Assembly 6--110............................................A. General 6--110...........................................................SECTION 7MAINTENANCE PRACTICES 7--1...............................................1. Overview 7--1..............................................................A. General 7--1...........................................................2. Equipment and Materials 7--1................................................A. General 7--1...........................................................3. 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................................4. Procedure for the LRUs 7--3.................................................A. LRU Removal 7--3......................................................B. LRU Installation 7--3....................................................5. Owner Requirements Table Uploading 7--4....................................A. General 7--4...........................................................6. Instructions for Continued Airworthiness, FAR 25.1529 7--5......................A. General 7--5...........................................................APPENDIX AVENDOR EQUIPMENT A--1.....................................................1. Overview A--1..............................................................A. General A--1...........................................................2. Electronic Cable Specialists A--1.............................................A. General A--1...........................................................B. Radio Frequency Components A--1.......................................C. Cable Assembly Fabrication A--1.........................................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--6Subject PageD. 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--8.............................................I. SATCOM Shelf Assemblies A--9..........................................J. Additional Avionics Installation Components A--9...........................K. Antenna System Provisions A--9..........................................L. Cabin Communications System Provisions A--9............................M. Wire Harnesses A--9....................................................N. Complete Integrated SATCOM Installation Kits A--9.........................3. Hollingsead International A--10................................................A. General A--10...........................................................B. Engineering Services A--10...............................................C. LRU Mounting Requirements A--10........................................D. Installation Kit Components A--11..........................................4. Signal Conditioning Unit A--16.................................................A. General A--16...........................................................B. Operator Functions A--17.................................................C. Control Functions A--18..................................................D. System Functions A--19..................................................E. ARINC 600 Connector Pin Assignments A--23...............................APPENDIX BINSTALLATION PROCEDURES FOR SATCOM AIR FILTRATION SYSTEMS B--1.....1. Introduction B--1............................................................A. General B--1...........................................................2. Continued Airworthiness B--1................................................A. General B--1...........................................................3. Equipment and Materials B--2................................................A. General B--2...........................................................4. Installation Instructions B--4..................................................A. Top Mount Assembly B--4...............................................B. Body--Mounted Assembly B--6...........................................C. Tray--Mounted Assembly B--7............................................APPENDIX COWNER REQUIREMENTS TABLE C--1...........................................1. Overview C--1..............................................................A. General C--1...........................................................APPENDIX DFAULT CODES D--1............................................................INDEX INDEX--1....................................................................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--7List of IllustrationsFigure PageFigure Intro--1. Symbols INTRO--1...................................................Figure Intro--2. Radio Frequency Energy Levels INTRO--9..............................Figure 1-1. Aviation Satellite Communications System 1--2.....................Figure 1-2. Aircraft Earth Station Block Diagram 1--3..........................Figure 1-3. INMARSAT Four-Region Satellite Coverage 1--11...................Figure 1-4. MCS Avionics Block Diagram 1--17................................Figure 1-5. MCS--4000/7000 SDU Equipment Description 1--19..................Figure 1-6. Satellite Data Unit 1--27..........................................Figure 1-7. High--Power Amplifier (40 and 20 Watt) 1--31........................Figure 1-8. RFUIA System Interface Diagram 1--43.............................Figure 2-1. Satellite Audio System 2--14......................................Figure 2-2. Dual System Wiring Diagram 2--18.................................Figure 2-3. HGA + LGA Configuration with Top-Mounted HGA 2--21..............Figure 2-4. HGA + LGA Configuration with Side-Mounted HGA 2--21.............Figure 2-5. HGA + HGA Configuration with Two Top-Mounted HGAs 2--22........Figure 2-6. HGA + HGA Configuration with Two Side-Mounted HGAs 2--22.......Figure 2-7. HGA + HGA Configuration with One Side-Mounted HGA + OneTop-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--24Figure 2-10. (HGA + LGA) + HGA Configuration with the LGA Paired withOne Side-Mounted HGA 2--25....................................Figure 2-11. (HGA + LGA) + HGA Configuration with the LGA Paired withOne Top-Mounted HGA 2--26.....................................Figure 2-12. (HGA + LGA) + HGA Configuration with Two Top-MountedHGAs 2--27.....................................................Figure 3--1. Audio Interfaces 3--3............................................Figure 4-1. Cable Attenuations 4--2.........................................Figure 4-2. Satellite Data Unit Outline and Installation Diagram 4--5.............Figure 4-3. 40 Watt High Power Amplifier Outline and Installation Diagram 4--7...Figure 4-4. 20 Watt High Power Amplifier Outline and Installation Diagram 4--9...Figure 4-5. Intermediate Gain Antenna Outline and Installation Diagram 4--13.....Figure 4-6. D/LNA Outline and Installation Diagram 4--17.......................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--8List of Illustrations (cont)Figure PageFigure 4-7. RFUIA Outline and Installation Diagram 4--21.......................Figure 5-1. SDU ARINC 600 Connector Layout 5--4...........................Figure 5-2. Contact Arrangements for Bottom Insert, SDU ARINC600 Connector 5--7.............................................Figure 5-3. HPA ARINC 600 Connector Layout 5--8...........................Figure 5-4. Contact Arrangements for Top Insert, HPA (40 Watt) ARINC600 Connector 5--9.............................................Figure 5-5. Contact Arrangements for Middle Insert, HPA (40 Watt) ARINC600 Connector 5--10.............................................Figure 5-6. Contact Arrangements for Bottom Insert, HPA (40 Watt) ARINC600 Connector 5--11.............................................Figure 5-7. Contact Arrangements for Top Insert, HPA (20 Watt) ARINC600 Connector 5--12.............................................Figure 5-8. Contact Arrangements for Middle Insert, HPA (20 Watt) ARINC600 Connector 5--13.............................................Figure 5-9. Contact Arrangements for Bottom Insert, HPA (20 Watt) ARINC600 Connector 5--14.............................................Figure 5-10. RFUIA ARINC 600 Connector Layout 5--15.........................Figure 5-11. Satellite Data Unit Interface Diagram 5--17..........................Figure 5-12. WH--10 Handset Interface Diagram 5--20...........................Figure 5-13. Four--to--Two Wire Interface Diagram 5--21.........................Figure 5-14. Avtech Fax Interface Diagram 5--22................................Figure 5-15. HF--SAT Transfer Panel Interface Diagram 5--23.....................Figure 5-16. Signal Conditioning Unit Interface Diagram 5--24....................Figure 5-17. Maintenance Panel Assembly Interface Diagram 5--25...............Figure 5-18. Intermediate Gain Antenna Interface Diagram 5--27..................Figure 5-19. CMC Top--Mount High Gain Antenna Interface Diagram 5--29.........Figure 5-20. Tecom Top--Mount High Gain Antenna Interface Diagram 5--31........Figure 5-21. Racal Mechanically Steered High Gain AntennaInterface Diagram 5--33..........................................Figure 5-22. AMT--50 Mechanically Steered High Gain AntennaInterface Diagram 5--35..........................................Figure 5-23. Dassault Conformal High Gain Antenna Interface Diagram 5--37......Figure 5-24. Ball Conformal High Gain Antenna Interface Diagram 5--39...........RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--9List of Illustrations (cont)Figure PageFigure 5-25. Low Gain Antenna Interface Diagram 5--41.........................Figure 5-26. Toyocom Top--Mount High Gain Antenna Interface Diagram 5--43......Figure 6-1. System BITE Communication 6--1................................Figure 6-2. SATCOM SCDU Page Hierarchy 6--25.............................Figure 6-3. SATCOM SCDU Main Menu Page 6--26............................Figure 6-4. SATCOM SUBMENU Page 6--28..................................Figure 6-5. SATCOM MAINTENANCE Page 6--29.............................Figure 6-6. TEST Page 6--31................................................Figure 6-7. SATCOM SELF--TEST Page 6--36.................................Figure 6-8. Configuration Data 6--39..........................................Figure 6-10. DATA LOADER MENU 6--60......................................Figure 6-11. LAST LEG REPORT Page 6--67...................................Figure 6-12. PREVIOUS LEG REPORT Page 6--69.............................Figure 6-13. LRU IDENTIFICATION Page 6--73.................................Figure 6-14. TROUBLE SHOOTING DATA Page 6--76...........................Figure 6-15. LAST LEG CLASS 3 FAULTS Page 6--78...........................Figure 6-16. GROUND REPORT Page 6--80...................................Figure 6-17. GROUND REPORT TROUBLE SHOOTING DATA Page 6--82........Figure 6-18. Configuration Data Pages for Boeing 777 Installation 6--86...........Figure A--1.1. ARINC Connectors A--3.........................................Figure A--1.2. ARINC Assembly A--3...........................................Figure A--1.3. Dimensions for ECS Tray Assemblies A--5.........................Figure A--1.4. Dimensions for Hollingsead Tray Assemblies A--13...................Figure B--1.1. ECS Top Mount Air Filtration Assembly B--5........................Figure B--1.2. Front and Side Views Showing Filter Removal B--8.................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--10List of TablesTable PageTable 1-1. Classes of Installations 1--8.....................................Table 1-2. Types of RF Channels 1--8......................................Table 1-3. Ground Earth Stations 1--10......................................Table 1-4. System Components Supplied by Honeywell 1--12..................Table 1-5. System Components Not Supplied by Honeywell 1--12..............Table 1-6. SDU Configurations 1--13........................................Table 1-7. HPA (40 Watt) Configurations 1--13...............................Table 1-8. HPA (20 Watt) Configurations 1--14...............................Table 1-9. SDU Leading Particulars 1--27....................................Table 1-10. SDU DO--160D Environmental Categories 1--29....................Table 1-11. HPA (40 Watt) Leading Particulars 1--33...........................Table 1-12. HPA (40 Watt) DO--160C Environmental Categories 1--34............Table 1-13. HPA (20 Watt) Leading Particulars 1--36...........................Table 1-14. HPA (20 Watt) DO--160D Environmental Categories 1--37............Table 1-15. CMA--2200 Intermediate Gain Antenna Features 1--38..............Table 1-16. CMA--2200 IGA Leading Particulars 1--39..........................Table 1-17. CMA--2200 IGA DO--160C Environmental Categories 1--40..........Table 1-18. CMA--2200 D/LNA Features 1--41.................................Table 1-19. CMA--2200 D/LNA Leading Particulars 1--41.......................Table 1-20. CMA--2200 D/LNA DO--160C Environmental Categories 1--42........Table 1-21. RFUIA Leading Particulars 1--44..................................Table 2-1. Data Set Upload/Download 2--8.................................Table 2-2. Basic Antenna Configurations 2--20...............................Table 3-1. SDU to WH-10 Handset Actions 3--5.............................Table 3-2. Global-Wulfsberg Flitephone WH-10 Commands 3--7...............Table 3-3. Assignment of DTMF Digits in the APBX Interface 3--13.............Table 3-4. SDU to APBX Off-Hook Actions 3--13..............................Table 3-5. Stored Audio Messages 3--16....................................Table 4-1. Cable Loss Requirements 4--3...................................Table 4-2. Cooling Requirements 4--3......................................Table 5-1. ARINC 615 Connector Pin Callouts 5--2..........................Table 5-2. ARINC 600 Connector Requirements 5--3.........................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--11List of Tables (cont)Table PageTable 5-3. Contact Arrangements for Top Insert, SDU ARINC600 Connector 5--5.............................................Table 5-4. Contact Arrangements for Middle Insert, SDU ARINC600 Connector 5--6.............................................Table 5-5. ICAO Block Strapping 5--19......................................Table 5-6. Configuration Pins 5--45.........................................Table 5-7. Availability of ARINC 429 SSR MODE S (AES ID) fromCMU Ports 5--46................................................Table 5-8. FMC Connection to SDU 5--48....................................Table 5-9. ARINC 429 Speed to/from CMU No. 1 and CMU No. 2 5--48.........Table 5-10. Cabin Packet Data Function (CPDF) 5--49.........................Table 5-11. ARINC 429 Bus Speed of AES ID Input 5--49.......................Table 5-12. Call Light On (Air/Ground Calls) 5--49..............................Table 5-13. Strap Parity (ODD) 5--49.........................................Table 5-14. Cabin Communications System (CCS) 5--50........................Table 5-15. Inertial Reference System (IRS) 5--51.............................Table 5-16. HPA/Antenna Subsystem Configuration 5--52.......................Table 5-17. CFDS/CMC 5--53...............................................Table 5-18. SDU Configuration 5--54.........................................Table 5-19. SDU Number 5--54..............................................Table 5-20. CMU No. 1 5--55................................................Table 5-21. CMU No. 2 5--55................................................Table 5-22. MCDU/SCDU No. 1 5--55........................................Table 5-23. MCDU/SCDU No. 2 5--55........................................Table 5-24. MCDU/SCDU No. 3 5--56........................................Table 5-25. Priority 4 Calls to/from Cockpit 5--56...............................Table 5-26. ARINC 429 Bus Speed to SCDU No. 1 / SCDU No. 2/SCDU No. 3 5--57...............................................Table 5-27. Cockpit Voice Call Light/Chime Option 5--57........................Table 5-28. SDU Analog Interface No. 1 Wiring 5--58...........................Table 5-29. SDU Analog Interface No. 2 Wiring 5--58...........................Table 5-30. Cockpit Hookswitch Signaling Method 5--58........................Table 6-1. Levels of Failure 6--3...........................................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--275 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--12List of Tables (cont)Table PageTable 6-2. HPA Indicators/Controls 6--9....................................Table 6-3. SDU Indicators/Controls 6--10....................................Table 6-4. Level 1 Failure Messages 6--12...................................Table 6-5. List of Part Numbers 6--17.......................................Table 6-6. MAR Information 6--19...........................................Table 6-7. LS Key/Line Pair Relations 6--20..................................Table 6-8. Special Symbols 6--23...........................................Table 6-9. System Configuration Pin Mapping 6--39...........................Table 6-10. Textual Message Display (Page 6 -- Lines 4 thru 9) 6--45.............Table 6-11. Textual Message Display (Page 7 -- Lines 4, 5, an 6) 6--47...........Table 6-12. Textual Message Display (Page 9 -- Lines 8 and 9) 6--51.............Table 6-13. Textual Message Display (Page 10 -- Lines 4 and 5) 6--53............Table 6-14. Textual Message Display (Page 10 -- Lines 8 and 9) 6--53............Table 6-15. DATA LOADER MENU Page Prompts 6--64........................Table 6-16. LRU Acronyms 6--72............................................Table 6-17. Boeing Level I Failure Messages and ATA Reference Numbers 6--90..Table 6-18. Airbus Level I (SDU No. 1) Failure Messages and ATA No. 6--93......Table 6-19. Airbus Level I (SDU No. 2) Failure Messages and ATA No. 6--100......Table 6-20. McDonnell Douglas Level I Failures Messages andATA Reference Numbers 6--106....................................Table 6-21. Commissioning and Maintenance Terminal Panel Lamps 6--111........Table 7-1. Materials 7--1..................................................Table A--1.1. ECS Cables and Connectors A--2................................Table A--1.2. ECS Attenuators A--2...........................................Table A--1.3. HP--600 HPA (40W) Hardware Component Kit,Part No. 998HQS--900--1XX A--7................................Table A--1.4. HP--700 HPA (20W) Hardware Component Kit,Part No. 998HQS--904--1XX A--7................................Table A--1.5. SD--700 SDU Hardware Component Kit,Part No. XXXXXX--XXX--1XX A--8................................Table A--1.6. BSU Hardware Component Kit, Part No. 970HQS--903--1XX A--8....Table A--1.7. Tray Assembly Part Numbers A--12................................Table A--1.8. ARINC 429 Data Requirements A--17..............................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--13List of Tables (cont)Table PageTable A--1.9. SCU Discrete Functions A--17....................................Table A--1.10. SCU Error Code A--18...........................................Table A--1.11. SCU Manual Signal Selection A--19...............................Table A--1.12. ARINC 561 Binary Data A--20.....................................Table A--1.13. ARINC 561 BCD Data A--20......................................Table A--1.14. ARINC 571 Data, ARINC 429 Format A--21.........................Table A--1.15. ARINC 571 Data, ARINC 419 Format A--21.........................Table A--1.16. ARINC 404 Data, ARINC 429 Format A--21.........................Table A--1.17. SCU Attitude Data Inputs A--22...................................Table A--1.18. Contact Arrangements for SCU ARINC 600 Connector A--24.........Table A--1.19. Signal Source Select Lines A--28..................................Table A--1.20. SCU Program Pin Combinations A--29.............................Table B--1.1. Materials B--2..................................................Table B--1.2. Air Filtration Systems from ECS for a Top Mount Assembly B--2......Table B--1.3. Air Filtration Systems from ECS for a Body--Mounted Design B--3....Table B--1.4. Air Filtration Systems from ECS for a Tray--Mounted Design B--3.....Table C--1.2. ORT Characteristics C--1........................................RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page TC--14Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page INTRO--1INTRODUCTION1. How to Use this ManualA. General(1) The purpose of this manual is to help you install, operate, maintain, and troubleshootthe MCS--4000/7000 Multi--Channel SATCOM System. Common systemmaintenance procedures are not presented in this manual. The best establishedshop and flight line practices should be used.(2) This manual gives general system description and installation information for theMCS--4000/7000 Multi--Channel SATCOM System. It also gives block diagram andinterconnect information to permit a general understanding of the system interface.(3) Warnings, cautions, and notes in this manual give the data that follows:•A WARNING gives a condition that, if you do not obey, can cause injury or death.•A CAUTION gives a condition that, if you do not obey, can cause damage to theequipment.•A NOTE gives data to make the work easier or gives direction to go to aprocedure.(4) Warnings and cautions go before the applicable paragraph or step. Notes follow theapplicable paragraph or step.(5) All personnel who operate equipment and do the specified maintenance must knowand obey the safety precautions.B. Symbols(1) The symbols in Figure Intro--1 identify ESDS and moisture sensitive devices in thismanual, if applicable.ESDS Moisture SensitiveFigure Intro--1. SymbolsC. Weights and Measurements(1) All weights and measurements are in U.S. and SI (metric) values.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page INTRO--22. Customer SupportA. Honeywell Aerospace Online Technical Publications Web Site(1) If you have access to the Internet, go to the Honeywell Online Technical Publicationsweb site at http://portal.honeywell.com/wps/portal/aero to:•Download or see publications online•Make an order for a publication•Tell Honeywell of a possible data error (report a discrepancy) in a publication.B. Complete Customer Care Center(1) If you do not have access to the Honeywell Online Technical Publications web site,send an e--mail message or a fax, or speak to a person at the Complete CustomerCare Center:•E--mail: cas--publications--distribution@honeywell.com•Fax: 602--822--7272•Phone: 800--601--3099 (U.S.A.)•Phone: 602--365--3099 (International).(2) Also, the Complete Customer Care Center is available if you need to:•Identify a change of address, telephone number, or e--mail address•Make sure that you get the next revision of this manual.3. ReferencesA. Honeywell Publications(1) The list that follows identifies Honeywell publications that are related to this manual:•ATA No. 23--20--03 (Pub. No. A32--5111--008), HP--600 High Power AmplifierComponent Maintenance Manual•ATA No. 23--20--25 (Pub No. A09--5111--025), HP--700 Watt High Power AmplifierComponent Maintenance Manual•ATA No. 23--20--26 (Pub. No. A09--5111--026), SD--700 Satellite Data UnitComponent Maintenance Manual•Pub. No. A09--1100--001, Handling, Storage, and Shipping Procedures forHoneywell Avionics Equipment Instruction ManualB. 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)RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page INTRO--3•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 onDrawings 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 forElectrical and Electronics Diagrams (available from the American NationalStandards Institute, New York, NY)•ANSI/IEEE Std 91 (1984), Graphic Symbols for Logic Functions (available fromthe American National Standards Institute, New York, NY).4. Acronyms and AbbreviationsA. General(1) Refer to the list that follows for acronyms and abbreviations in this manual.List of Acronyms and AbbreviationsTerm Full TermAAC Aeronautical Administrative CommunicationsACARS Aircraft Communications Addressing and Reporting SystemACP audio control panelACU antenna control unitADL airborne data loaderADS automatic dependent surveillanceAPC Aeronautical passenger communicationsAES aircraft earth stationAFIS aircraft flight information systemAMS audio management systemAMU audio managment unitAOC Aeronautical Operational ControlAOR--E Atlantic Ocean Region--EastAOR--W Atlantic Ocean Region--WestAPBX analog private branch exchangeAPC Aeronautical passenger communicationsAPHONE analog telephoneAPOS actual power out statusARINC Aeronautical Radio, Inc.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page INTRO--4List of Acronyms and Abbreviations (cont)Term Full TermATA Air Transport AssociationATC air traffic controlATS air traffic servicesBIT built--in testBITE built--in test equipmentBSU beam steering unitCAIMS central aircraft information and maintenance systemCCA circuit card assemblyCCS cabin communications systemCF/M cubic feet per minuteCFDIU centralized fault display interface unitCFDS central fault display systemCGU communications gateway unitCLR clearCM continuous monitoringCMC central maintenance computerCMT commissioning and maintenance terminalCMU communications management unitCPDF cabin packet data functionCRC cyclic redundancy checkCTM cabin telecommunicationsCTU cabin telecommunications unitD/LNA diplexer/low noise amplifierDEL deleteDIP dual in--line packagingDIU data interface unitDTE data terminal equipmentDTMF dual tone multifrequencyECS electronic cable specialistsEIRP effective isotopic radiated powerRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page INTRO--5List of Acronyms and Abbreviations (cont)Term Full TermFAX facsimileFMC flight management computerFWP fault warning processorGES ground earth stationGMT Greenwich Mean TimeGSDB GES--specific data broadcastGSPD groundspeedHGA high gain antennaHMN Honeywell Material NumberHPA high power amplifierHPR high power relayI/O input/outputICAO International Civil Aviation OrganizationID identificationIGA intermediate gain antennaINMARSAT International Maritime Satellite OrganizationINS inertial navigation systemIOR Indian Ocean RegionIPC illustrated parts catalogIRS inertial reference systemISO International Standards OrganizationISU initial signal unitITU International Telecommunications UnionLED light emitting diodeLGA low gain antennaLRU line replaceable unitLS line selectMAR maintenance activity recordMCDU multifunction control display unitMCS MCS--4000/7000 Multi--Channel SATCOMRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page INTRO--6List of Acronyms and Abbreviations (cont)Term Full TermMCU modular concept unitMEL minimum equipment listMTBF mean--time--between--failureMU management unitNVM non--volatile memoryOCXO oven controlled crystal oscillatorOEM Original Equipment ManufacturerOMS onboard maintenance systemORT owner requirements tablePABX private automatic branch exchangePAST person--activated self--testPDL portable data loaderPF power factorPLO phase--locked oscillatorPMAT portable maintenance access terminalPOC power--on counterPOR Pacific Ocean RegionPOST power--on self--testPROM programmable read--only memoryPSTN Public Switched Telephone NetworkPSU power supply unitPTT push--to--talkRFM radio frequency moduleRFU radio frequency unitRFUIA radio frequency unit interface adapterRTC real--time clockRTCA radio technical commission for aeronauticsSAL system address labelSCDU SATCOM control and display unitSCPC single channel per carrierRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page INTRO--7List of Acronyms and Abbreviations (cont)Term Full TermSCU signal conditioning unitSDI source destination identifierSDU satellite data unitSITA Satellite AircomSMT surface mount technologySRU shop replaceable unitSSM sign--status matrixTDM time division multiplexTDMA time division multiple accessTIF terminal interface functionTOTC total on--time clockTSPO time since power--onTTCM triple transcoder modemUTC universal time coordinatedVCM voice codec moduleVSWR voltage standing wave ratioXTB cross--talk busRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page INTRO--85. Maximum Permissible Exposure LevelA. General(1) The radio frequency energy generated by the MCS system may be hazardous topersonal health. To eliminate the potential danger, Honeywell recommends thatoperators of the MCS system implement safety procedures.(2) When the MCS system is in operation, personnel should remain at a distance fromthe antenna that is greater than the maximum permissible exposure level (MPEL)radius. Because there are many possible antenna locations, antenna gains, andsystem output powers, it is the responsibility of the operator to ascertain the MPELradius for their MCS system configuration and train their personnel in safe groundprocedures. The following warnings state Honeywell’s MPEL recommendations forboth high and low gain antennas.WARNING: TO AVOID POTENTIALLY DANGEROUS EXPOSURE TO RADIOFREQUENCY ENERGY ABOVE THE ANSI C95.1 LIMIT AND OTHERWORLD STANDARDS (SEE FIGURE INTRO--2) WHEN USING A HIGHGAIN ANTENNA (12 dB NOMINAL ANTENNA), DO NOT OPERATE THEMCS SYSTEM WHEN ANY PERSONNEL ARE WITHIN 8.5 FEET OF THEANTENNA OR WITHIN 20 FEET OF THE ANTENNA FOR PERIODS OFLONGER THAN 3 MINUTES PER HOUR.WARNING: TO AVOID POTENTIALLY DANGEROUS EXPOSURE TO RADIOFREQUENCY ENERGY ABOVE THE ANSI C95.1 LIMIT AND OTHERWORLD STANDARDS (SEE FIGURE INTRO--2) WHEN USING ANINTERMEDIATE GAIN ANTENNA (6 dB NOMINAL ANTENNA), DO NOTOPERATE THE MCS SYSTEM WHEN ANY PERSONNEL ARE WITHIN 3FEET OF THE ANTENNA OR WITHIN 6 FEET OF THE ANTENNA FORPERIODS OF LONGER THAN 3 MINUTES PER HOUR.WARNING: TO AVOID POTENTIALLY DANGEROUS EXPOSURE TO RADIOFREQUENCY ENERGY ABOVE THE ANSI C95.1 LIMIT AND OTHERWORLD STANDARDS (SEE FIGURE INTRO--2) WHEN USING A LOWGAIN ANTENNA (0 dB NOMINAL ANTENNA), DO NOT OPERATE THEMCS SYSTEM WHEN ANY PERSONNEL ARE WITHIN 1.5 FEET OF THEANTENNA OR WITHIN 3 FEET OF THE ANTENNA FOR PERIODS OFLONGER THAN 3 MINUTES PER HOUR.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page INTRO--9Figure Intro--2. Radio Frequency Energy LevelsRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page INTRO--10Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--1SECTION 1SYSTEM DESCRIPTION1. OverviewA. General(1) The MCS--4000/7000 Multi-Channel SATCOM (MCS) system is a mobile avionicscommunications system that supplies continuous worldwide voice and datacommunications services to and from the aircraft through satellite. The MCS systeminterfaces at baseband with various avionics data equipment, as well as with crewand passenger voice equipment on–board the aircraft. It interfaces with the antennasubsystem through L--band RF signals that emanate from (and are received by)satellites in geostationary orbit. These satellites then convey the information to andfrom ground stations that interface with the terrestrial telephone network.(2) The MCS system augments and/or supersedes the present high frequencytransceiver by supplying higher quality voice service and by supplying data servicesat higher bit rates needed by some future datalink (ATN) applications, such asautomatic dependent surveillance (ADS) and an international aircraft communicationsaddressing and reporting system (ACARS). Additional services include cockpitcommunications with administrative and operational personnel and withgovernmental bodies such as air traffic services (ATS). The system is designed toensure that communications for safety and regularity of flight are not delayed by thetransmission and reception of other types of messages.(3) The MCS--4000/7000 system supports seven communication channels capable ofsimultaneous full duplex voice communications and one channel of datacommunications. The MCS--4000 system operates identically to the MCS--7000except four communication channels rather than seven are supplied. Both theMCS--7000 and MCS--4000 SATCOM systems supply one channel of datacommunications. The MCS system accommodates the four categories ofcommunications:•Air traffic control (ATC)•Aeronautical operational control (AOC)•Aeronautical administrative communications (AAC)•Aeronautical passenger communications (APC).(4) The four communication categories are recognized by the International Civil AviationOrganization (ICAO) and the International Telecommunications Union (ITU), andhave been assigned priorities for communications purposes.(5) The total aviation satellite communications system, shown in Figure 1-1, is made upof the following:•Aircraft earth station (airborne avionics subsystems and antenna subsystem)•Space segment (satellite network)•Ground earth stations•Terrestrial data and voice networks.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--2Figure 1-1. Aviation Satellite Communications SystemB. Aircraft Earth Station(1) General(a) The aircraft earth station (AES) is fully compliant with requirements ofAeronautical Radio, Inc (ARINC) Characteristics 741/761. Standard interfacesbetween the MCS avionics and other aircraft avionics enable the AES to acceptdata and voice messages from various sources, encode and modulate thisinformation onto appropriate RF carrier frequencies, and transmit these carriersto the space segment for relay to a ground earth station (GES). The AES alsoreceives RF signals from a GES through the satellite, demodulates thesesignals, performs the necessary decoding of the encoded messages, andoutputs the data or voice message for use by either the pilot, copilot,or thepassengers.(2) AES Components(a) General1A block diagram of the AES is shown in Figure 1-2. The AES is made up ofthe following components:•MCS avionics•Antenna subsystem•Cabin communications services•Analog connected telephones•Cockpit voice sources•Aircraft avionics.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--3/(1--4 blank)Figure 1-2. Aircraft Earth Station Block DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--5(b) MCS Avionics1The MCS avionics are made up of the satellite data unit (SDU) and highpower amplifier (HPA). The SDU supplies the interface to all aircraft avionics,and implements all functionality associated with modulation/demodulation,error correction, channel rate/frequency selection, and RF translation forseven communication channels. The SDU supports seven communicationchannels capable of simultaneous full duplex voice and data communicationservices. The SDU manages the RF link protocols on the satellite side andsupplies the system interface with communications management avionics.The SDU interface to other aircraft avionics involves the exchange of ARINC429 and discrete data.2A cockpit audio system conveys cockpit voice to and from the SDU.Messages requiring cockpit action or initiation appear on the multifunctioncontrol display unit (MCDU) and/or other cockpit annunciators. Thecommunications management unit (CMU) or equivalent routes packet datamessages to and from the SDU. Cabin communications use either a cabincommunications system (CCS) or an analog equivalent (cabin unit) to supplyvoice telephony communication. Enhancements supply facsimile (FAX)service and secure voice and personal computer modem interfaces.3The SDU supplies all essential services required to accommodate effectiveair/ground communications through satellite using the antenna and relatedRF components. Both the 40 Watt and 20 Watt HPAs supply linear poweramplification to boost the RF signals up to the power levels required fortransmitting to the satellite. In addition, the 20 Watt HPA (used primarily forthe intermediate gain antenna) supports a beam steering function whichconverts tracking and pointing coordinates from the SDU into signalsneeded to select the desired (beam) direction towards the satellite.4Two additional LRUs may be required for some aircraft configurations:•Radio frequency unit interface adapter (RFUIA)•Signal conditioning unit (SCU).5The RFUIA is used in place of the radio frequency unit (RFU) in theMCS--7000 system.6The SCU is used in MCS installations on older generation aircraft having aninertial navigation system (INS) that does not output navigation data in anARINC 429 high speed format which is consistent with the ARINC 704characteristic.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--6(c) Antenna Subsystem1The primary function of the antenna subsystem is to complete thecommunication link between the GES, the space segment, and the AES.The diplexer is a three-port RF device (antenna, transmit, and receive),which supplies signal routing and filtering functions. Signals in the receiveband are routed from the antenna port to the receive port, and transmitsignals are routed from the transmit port to the antenna port. The low noiseamplifier establishes the noise floor of the communication system byboosting the signals and noise received from the antenna to a level muchgreater than the noise level of subsequent components in the receive path.2The high gain antenna (HGA) and intermediate gain antenna (IGA) transmitL--band RF signals from the HPA to a satellite, and receive L--band RFsignals from a satellite for the SDU. The low gain antenna (LGA) suppliesbackup communications (packet data only) for the high gain antenna orintermediate gain antenna by supplying low rate packet data communicationservices.3The beam steering unit used in the HGA system converts tracking andpointing coordinates (aircraft relative azimuth and elevation) from the SDUinto signals needed to select the antenna array elements in combinationsthat point the antenna beam in the desired direction towards the satellite. Anantenna control unit (ACU) is required for mechanically steered antennaarrays. The antenna control unit translates digitized beam position data andbeam position change commands from the SDU into a format needed toposition the antenna beam in the desired direction toward the satellite. Abeam steering function is incorporated into the 20 Watt HPA for use with theIGA.(d) Cabin Communications System (CCS)1The CCS, in conjunction with the MCS avionics and a worldwide network ofground stations, supplies cabin services such as telephone, facsimile, andother communication interfaces. The CCS is partitioned into two sections:the cabin telecommunications unit (CTU) and cabin/passengercommunications equipment (digitally connected telephones).2The CTU performs onboard private automatic branch exchange (PABX)telephony functions letting the digitally connected telephones make the bestuse of resources supplied by the MCS avionics. The CTU supplies theinterface between the digitally connected phones and the SDU. Aspecialized interface conversion function supplies compatibility between theARINC 746 CTU and the ARINC 741/761 SDU. This interface is made up ofa high-speed (CEPT--E1) serial bus pair that accommodates up to 32digitized voice channels along with status and control information.3The digitally connected phones (handsets) are primarily supplied forpassenger use and can be located throughout the aircraft. The digitalhandsets interface indirectly to the satellite communications equipment andare controlled by the CCS.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--7(e) Analog Connected Telephones1The SDU has provisions to support up to two simultaneous analog audiochannels. Each analog channel supports two interface types:Global-Wulfsberg Flitephone WH--10 and the analog private branchexchange (APBX). The WH--10 is a stand-alone handset with a 12-buttonkeypad. The APBX has analog trunk lines and in-line dual tonemultifrequency (DTMF) signaling.(f) Cockpit Voice Sources1The SDU supports headset interfaces for cockpit use only. These interfacesincorporate off-hook/on-hook signaling and dialing through the combinationof a control and display unit (either [SATCOM control and display unit] SCDUor MCDU), and push-to-talk (PTT) or similar switches. When the PTT switchis pushed, a microphone audio signal is sent to the selected voice channeland a discrete signal is sent to the SDU. An audible chime and call lampsannounce call connections.(g) Aircraft Avionics1Standard interfaces between the MCS avionics and the other aircraftavionics include the following:•Communications management unit (CMU), or the management unit (MU)of the Aircraft Communications Addressing and Reporting System(ACARS), where installed.•SATCOM control and display unit (SCDU), where installed, to supply aninterface to the MCS system for system log-on, GES selection, cockpitvoice call setup, data loading, and to access the SATCOM maintenancepages including fault messages.•Central fault display system (CFDS), central maintenance computer(CMC), or on--board maintenance system (OMS), where installed, for faultreporting.•The inertial reference system (IRS), where installed, to supply the SDUwith navigation coordinates for positioning the antenna platform.•Channels are also supplied for voice and data communication with ATCto support departure clearances by datalink, as well as ADS for non radarposition reporting in oceanic regions.•There is an ARINC 615 Airborne or portable data loader (ADL or PDL) foruploading operational software and the owner requirements table (ORT).Connections are made through front and back panel connectors on theMCS avionics LRUs.•The 24-bit ICAO address identifies the aircraft in which the SDU isinstalled. Address pins identified to take on the binary one state must beleft open. Address pins identified to take on the binary zero state must bewired to address common on the airframe side of the connector. ARINC429 interface options for the ICAO address are also supplied.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--8(3) AES Classifications(a) Each AES is classified according to the configuration and dynamic capabilities ofits aircraft avionics and antenna subsystem. An AES can be fitted with anycombination of the classes of installations given in Table 1-1.Table 1-1. Classes of InstallationsClass Description1A Class 1 AES installation uses a low gain antenna only and supplies low ratepacket-mode data services only.2A Class 2 AES installation uses a high gain antenna or intermediate gain antenna,and supplies telephony and optional circuit-mode services.3A Class 3 AES installation uses a high gain antenna or intermediate gain antenna,and supplies telephony services, packet-mode data services, and optionalcircuit-mode data services.4A Class 4 AES installation uses a high gain antenna or intermediate gain antenna,and supplies packet-mode data services only.(4) GES Communication Links(a) The MCS avionics supply access to ground-based networks through the groundearth stations. Each GES supplies system synchronization and coordinationthrough ground-to-aircraft transmissions. Four types of RF channels are definedforusewiththeMCSavionicsasgiveninTable1-2.Table 1-2. Types of RF ChannelsRF Channel DescriptionP--Channel Packet-mode time division multiplex (TDM) channel used in the forward (outbound)direction (ground-to-aircraft) to carry signaling and packet-mode data. Thetransmission 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 initialsignals of a transaction (typically request signals).T--Channel Reservation time division multiple access (TDMA) channel used in the returndirection only. The receiving GES reserves time slots for transmissions requestedby an AES according to message length. The sending AES transmits themessages in the reserved time slots.C--Channel Circuit-mode single channel per carrier (SCPC) channel used in both forward andreturn directions to carry digital voice or data/facsimile traffic. The use of thechannel is controlled by assignment and release signaling at the start and end ofeach call or FAX transmission.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--9C. Space Segment(1) The space segment is made up of satellites placed in geostationary orbits to supplyair-ground packet-switched data services and voice communications, both of whichuse worldwide standardized conventions and capabilities. The satellites function ascommunication transponders to support L--band links to and from the aircraft, andsupply links to and from ground earth stations. The space segment supplier for airlineaeronautical satellite communications is the International Maritime SatelliteOrganization (INMARSAT), whose system supplies worldwide coverage. Thefour-region satellite system supplied by INMARSAT is shown in Figure 1-3.D. Ground Earth Station(1) Each GES has the necessary equipment to communicate with terrestrial networksand communicate through satellites with the aircraft. The ground earth stations aredesigned to supply the airline customer with a diverse routing of national andinternational voice and data communications through submarine cable, satellite, andmicrowave links to all destinations. Automatic traffic management systems ensureefficient routing of communications by using optimum links into public switchedtelephone networks (PSTN) and avoiding multiple satellite connections wheneverpossible.(2) Ground earth stations are located strategically around the globe to supplyredundancy and diversity in the terrestrial extension of communications. Aircraft areconnected to a GES through an in-view satellite depending on the servicepreference settings encoded in the SDU ORT. Some problems may be encounteredwhen the aircraft flies in polar regions with a latitude greater than 75 degrees.E. Terrestrial Data and Voice Networks(1) Data and voice services available through satellites and ground earth stations include9.6 and 4.8 kilobit/second digital voice, and packet-mode data at RF channel ratesranging from 600 bit/second up to 10.5 kilobit/second. The present worldwidecomplement of ground earth stations including location, operator, and coverageregion are summarized in Table 1-3. Aeronautical communications through theINMARSAT satellites are transmitted to and from the terrestrial phone and datanetworks through these ground earth stations. The satellite regions that service theseground earth stations are shown in Figure 1-4.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--10Table 1-3. Ground Earth StationsGES Name GES ID SAT ID Service ProviderGoonhilly--AW 001 000 (AOR--W) StratosSouthbury--AW 002 000 TelenorEik--AW 004 000 TelenorAussaguel--AW 005 000 Satellite Aircom (SITA)Goonhilly--AE 101 001 (AOR--E) StratosAussaguel--AE 103 001 SITAEik--AE 104 001 TelenorSentosa--P 201 002 (POR) Sing--TelSanta Paula--P 202 002 TelenorYamaguchi--P 203 002 KDDPerth--P 205 002 SITAEik--I 301 003 (IOR) TelenorNunthaburi--I 302 003 TelenorPerth--I 305 003 SITAYamaguchi--I 306 003 KDDSentosa--I 310 003 Sing--TelRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--11Figure 1-4. INMARSAT Four-Region Satellite CoverageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page 1--122. System ComponentsA. General(1) The MCS avionics is comprised of the following components:•Satellite data unit (SDU)•High power amplifier (HPA).(2) These components are compatible with ARINC Characteristic 741. Table 1-4 givesthe MCS system components supplied by Honeywell. Table 1-5 gives the MCSsystem components not supplied by Honeywell. Table 1-6 thru Table 1-8 give systemcomponent configuration information.Table 1-4. System Components Supplied by HoneywellComponent Model No. Honeywell Part No.Satellite Data Unit SD--700 7516118--xxyyyFigure 1-6High Power Amplifier (40 W) HP--600 7516250--xxyyyFigure 1-7High Power Amplifier (20 W) HP--700 7516251--xxyyyFigure 1-7Diplexer/Low Noise Amplifier -- Aero--I -- -- 7516193--901Intermediate Gain Antenna -- -- 7516194--901Radio Frequency Unit Interface Adapter (RFUIA) 1. -- -- 7516222--901NOTES:1. The five digit dash number (xxyyy) corresponds to the hardware/software version of the unit where the first twodigits correspond to the hardware version and the last three digits correspond to the software version.2. The RFUIA is installed with the 115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data), or 28 V dc.Table 1-5. System Components Not Supplied by HoneywellComponent CommentsSDU Installation Equipment (See Note) ARINC 600 6--MCU tray, cables, connectors, assemblies,mounting hardware, and kitsHPA (40 W) Installation Equipment(See Note) ARINC 600 8--MCU tray, cables, connectors, assemblies,mounting hardware, and kitsHPA (20 W) Installation Equipment(See Note) ARINC 600 4--MCU tray, cables, connectors, assemblies,mounting hardware, and kitsSignal Conditioning Unit (SCU) RACAL Part No. 56047--010XXRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
  SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4000/7000  TEMPORARY REVISION NO. 23-2     23-20-27 Page 2 of 3 20 Jun 2017   © Honeywell International Inc. Do not copy without express permission of Honeywell.  INSERT PAGE 2 OF 3 FACING PAGE 1-13. Reason:  To add PN 7516118-77010 and PN 7516118-74010, and to change description for PNs 75166118-27020 and -24020 in Table 1-6.  Table 1-6 is changed as follows:  Table 1-6.  SDU Configurations SDU Part Number Description 7516118-27010 115 V ac/400 Hz, 7-channel SOU (6 voice, 1 data) 7516118-77010 115 V ac/400 Hz, 7-channel SDU (6 voice, 1 data), Digital RFM 7516118-57010 +28 V dc, 7- channel SOU (6 voice, 1 data) 7516118-24010 115 V ac/400 Hz, 4-channel SOU (3 voice, 1 data) 7516118-74010 115 V ac/400 Hz, 4-channel SDU (3 voice, 1 data), Digital RFM 7516118-54010 +28 V dc, 4- channel SOU (3 voice, 1 data) 7516118-27020 115 V ac/400 Hz, 7-channel SDU (6 voice, 1 data) for Airbus applications, (HW MOD J contains Digital RFM) 7516118-24020 115 V ac/400 Hz, 4-channel SDU (6 voice, 1 data) for EPIC applications, (HW MOD J contains Digital RFM) 7516118-27011 115 V ac/400 Hz, 7-channel SOU (6 voice, 1 data) for EPIC applications 7516118-57011 +28 V dc, 7-channel SOU (6 voice, 1 data) for EPIC applications 7516118-24011 115 V ac/400 Hz, 4-channel SOU (3 voice, 1 data) for EPIC applications 7516118-54011 +28 V dc, 4- channel SOU (3 voice, 1 data) for EPIC applications   RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--13Table 1-5. System Components Not Supplied by Honeywell (cont)Component CommentsHigh Gain Antenna Equipment BAE Systems -- CanadaBall Aerospace -- USADassault Electroniq -- FranceNOTE: Installation of this equipment is dependent on the specific requirements of the operator. Refer toAppendix A, Vendor Equipment, for additional information.Table 1-6. SDU ConfigurationsSDU Part Number Description7516118--27010 115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data)7516118--57010 +28 V dc, 7--channel SDU (6 voice, 1 data)7516118--24010 115 V ac/400 Hz, 4--channel SDU (3 voice, 1 data)7516118--54010 +28 V dc, 4--channel SDU (3 voice, 1 data)7516118--27020 115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data) for Airbusapplications7516118--24020 115 V ac/400 Hz, 4--channel SDU (3 voice, 1 data) for Airbusapplications7516118--27011 115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data) for EPICapplications7516118--57011 +28 V dc, 7--channel SDU (6 voice, 1 data) for EPIC applications7516118--24011 115 V ac/400 Hz, 4--channel SDU (3 voice, 1 data) for EPICapplications7516118--54011 +28 V dc, 4--channel SDU (3 voice, 1 data) for EPIC applicationsTable 1-7. HPA (40 Watt) ConfigurationsHPA Part No.SoftwarePackage Description7516250--10001 A3--channel initial release7516250--15020 B3--channel update with cabin voice7516250--18033 C0.0 6--channel cabin voice and data (1--data, 5--voice) and fax(2400/4800 bps)7516250--18036 C2.0 6--channel cabin voice and data (1--data, 5--voice) and fax(2400/4800 bps)7516250--19034 C3.0 Improves log--on capability and reversion; adds maintenancepages7516250--19037 C3.5 Adds Boeing 777 capabilityRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308SeeTR
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page 1--14Table 1-7. HPA (40 Watt) Configurations (cont)HPA Part No. DescriptionSoftwarePackage7516250--19037 C3.5 Adds Boeing 777 capability7516250--20050 D2.0 Adds several improvements to BITE, including antenna VSWRdetection reporting and compatibility with hardware Mod D(Software Mod F); Uses 115 V ac primary power.7516250--55050 D2.0 Adds several improvements to BITE, including antenna VSWRdetection reporting and compatibility with hardware Mod D(Software Mod F); Uses 115 V ac primary power.7516250--60001 A3--channel initial release7516250--60020 B3--channel update with cabin voice7516250--60033 C0.0 6--channel cabin voice and data (1--data, 5--voice) and fax(2400/4800 bps)7516250--60050 D2.0 Adds several improvements to BITE, including antenna VSWRdetection reporting and compatibility with hardware Mod D(Software Mod F); Uses 28 V dc primary power.NOTE: For the various part numbers, --1XXXX refers to an air transport LRU, while --55XXX and --6XXXXrefers to a business and commuter LRU. The functional descriptions are the same for both.Table 1-8. HPA (20 Watt) ConfigurationsHPA Part Number SoftwarePackage Description7516251--20060 E1.5 20 Watt HPA with Aero--I IGA beam steering functionality; Uses115 V ac or 28 V dc power supply.7516251--60060 E1.5 20 Watt HPA with Aero--I IGA beam steering functionality; Uses115 V ac or 28 V dc power supply.NOTE: For the various part numbers, --2XXXX refers to an air transport LRU, while --6XXXX refers to abusiness and commuter LRU. The functional descriptions are the same for both.3. System DescriptionA. General(1) The system description gives a general overview and summary of the features andinterfaces that the MCS implements. Figure 1-7 is a simplified block diagram of theMCS system.(2) The core of the AES avionics subsystem is the MCS avionics, supporting data, andvoice communications at rates from 600 to 21,000 bits per second. Interfaces tovarious aircraft systems including cockpit voice, cabin voice/data, aircraft avionics,and the antenna subsystem enable the MCS avionics to handle data and voicemessaging functions for the AES.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--15(3) The SDU supplies all essential services required to accommodate effectiveair/ground communications through satellite, using the antenna and related RFcomponents. The SDU manages the RF link protocols on the AES side and suppliesthe system interface with communications management avionics. The HPA booststhe signal to be transmitted up to the power levels required for transmission to thesatellite.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--16Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--17/(1--18 blank)Figure 1--4. MCS Avionics Block DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--19B. Satellite Data Unit(1) General(a) The SDU is the core element of the MCS avionics and is responsible for overallAES control and monitoring. The unit interfaces to many aircraft avionics (e.g.,CFDS, primary/secondary IRS, CMU 1/2, MCDU 1/2/3, ADL, etc) and hasoperational functionality, including coding and decoding all system voice anddata signals and defining system protocols. The SDU contains six channelscapable of supplying simultaneous full duplex voice communication, one channelof data 2/3 communication, and RF circuitry sufficient to operate the AES.Figure 1-5 shows the circuit card assembly (CCA) layout for the MCS--7000SDU. Removal of one of the triple transcoder modem (TTCM) CCA results in theMCS--4000 SDU.Figure 1-5. MCS--4000/7000 SDU Equipment DescriptionRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--20(b) The format for voice/data codes follows the INMARSAT system definitions forvoice and data transmission and reception. The INMARSAT system uses adigital format for voice and data. The SDU digitizes the voice or data signal andadds 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). Whensignal processing is complete, the coded voice/data signal is sent to HPA. TheSDU also controls the protocols for automatic call, setup, and clear-down.System protocols are defined so the designated GES recognizes it is beingcalled by the AES.(c) The SDU houses the voice interface modules and transcoder modems requiredfor voice and data service, and the RF transmit/receive circuitry needed toconvert modulated baseband signals to an L-band frequency (and vice versa).All AES satellite signals use digital coding and modulation, which include thevoice circuits. The voice interface modules translate baseband analog voicesignals to and from the 9600 bps or 4800 bps digital coding standard. Efficientinformation compression and coding techniques supply high voice quality at aneconomical bit rate. The modems, one for each communication channel, performall of the physical layer signal processing functions, includingmultiplexing/demultiplexing, interleaving/de--interleaving,scrambling/unscrambling, modulation/demodulation, and Doppler effectcorrection.(d) The SDU system table memory contains the location of all satellites. When aGES is selected, the SDU uses this location information and aircraft positionalinformation (through an ARINC 429 interface) from the IRS to compute theposition of the satellite relative to the aircraft. The SDU then transmits pointingand tracking coordinates (aircraft relative azimuth and elevation) to the beamsteering unit (BSU) to permit optimum signal transmission and reception betweenthe high gain antenna subsystem and the satellite.(e) The high gain antenna subsystem translates these steering commands intocontrol signals to the antenna(s). Once the beam has been steered toward thesatellite, the SDU receives the pilot tone from the satellite transponder throughits receive RF link from the antenna subsystem.(f) The SDU is now free to route communications data over the satellite link. TheSDU accomplishes this by sending commands to the MU and the CTU. Thesecommands are sent through ARINC 429 and CEPT E1 interfaces between theSDU and the MU/CTU. Data is then routed from the MU/CTU to the SDU. In theSDU, the baseband data modulates RF carriers, which are sent to the HPA foramplification, and then to the antenna subsystem for transmission to the satellite.The SDU can adjust the transmission frequency in one-Hertz increments tocompensate for the Doppler shift caused by the speed of the aircraft. Thereceive mode is handled in a similar manner. Since the MCS is a full-duplexsystem, the transmit and receive signals are processed simultaneously as inconventional terrestrial telephone equipment.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--21(2) Output Power Control(a) General1The AES output power to the satellite, specified and calculated as effectiveisotopic radiated power (EIRP) from the antenna in the direction of thesatellite, is controlled by the SDU as specified in the following paragraphs.The SDU is capable of controlling up to one HGA HPA, one LGA HPA, orone IGA HPA. These HPA(s) can be a linear or class C type in anycombination. The SDU does not establish a C-channel voice call using aclass C HGA HPA or through any LGA HPA.(b) Assumed Initial C-Channel EIRP1The SDU calculates the assumed initial C-channel EIRP as being the lowestof the currently GES-commanded EIRPs for any/all C-channels in progress.If there are no C-channels currently in progress, the SDU uses the value inORT item xxx, or the value in ORT item xxx reduced by 6 dB if the SDU iscurrently logged on through a spot-beam.(c) Current Reserved EIRP1The SDU calculates the current reserved EIRP as the summation in Watts ofthe following EIRPs:•The power reserved for the R/T-channel transmission, for the highest bitrate assigned, calculated from the EIRP assigned in the log-on confirmsignal, or the most recent data channel reassignment, if any.•The GES-assigned EIRPs of all the currently active C-channel carriers, ifany.•The cockpit reserved channel power if the reservation has been madethrough ORT option vii and is not in use. This continuously tracks theassumed initial C-channel EIRP. If it is in use, then the actualGES-assigned EIRP is used.•The power reserved for any C-channel calls in the process of being setup (i.e., after resources have been allocated but no C-channelassignment signal has been received). For each such channel, theassumed initial C-channel EIRP is used.(d) Current and Projected or Peak-To-Average Power Ratio1If the HPA is linear, the SDU calculates the current peak-to-average powerratio based on the EIRP levels for all the carriers considered in the currentreserved EIRP calculation. The current peak-to-average ratio value is sent tothe HPA periodically, alternating with the projected peak-to-average ratio(i.e., what the peak-to-average ratio would be if one additional C-channelwere established).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--222The SDU waits at least 450 milliseconds after transmitting the HPAcommand word before assuming the received HPA maximum available RMSoutput power corresponds to the most recently sent peak-to-average ratio inthe HPA command words. The current peak-to-average ratio is sent in orderto calculate the current available EIRP from the returned maximum availableRMS power. The projected peak-to-average ratio is sent in order todetermine (along with other criteria) if an additional C-channel can beestablished, if and when it is requested. If all carriers are at the same powerlevel (not true in general), the peak-to-average ratio is equal to the numberof carriers. If the HPA is class C, the SDU always sends a peak-to-averageratio equal to 1.(3) Installation Dependent Considerations(a) General1The SDU stores the following installation dependent values to enable it toset the EIRPs accurately:•SDUtoHPAloss(assumedcommonforbothLGAandHGAHPAs)•HPA to antenna loss (two values are stored, one for the HGA HPA, and aseparate value for the LGA HPA)•HPA in use is class C, the SDU stores the HPA maximum output power.(b) SDU to HPA Loss1The SDU stores the calibrated SDU to HPA loss in nonvolatile memory.When the HPA is linear, this value is calculated once whenever there is anR--or T--channel burst transmission in the absence of C--channeltransmission. This value is also calculated whenever there is a singleC--channel transmission in the absence of R-- or T--channel, unless thereported actual power output value in the HPA status word:•Matches or is less than the minimum reportable actual power value storedin ORT item xxix•Matches either the unique code 00100Bfor at/below measurable rangeor 3 dB greater than 40 W or the flag was set indicating the HPA ormodem backoff was limited.2When a single measurable carrier (R--/T--or C--channel) is present, the SDUrecalculates the SDU to HPA loss as the actual output power reported by theHPA, less the HPA nominal gain, plus the HPA backoff, or SDU calculatedRFM power. This value includes the actual cable loss, plus anyuncompensated variation from nominal in the HPA gain, and any variationfrom the calibrated RFM output power (due to temperature). This value alsolets the SDU accurately determine the common transmit gain. If thecalibration results in a value outside the range of 10 dB to 30 dB, a failure israised for the HGA HPA and LGA HPA.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--23(c) HPA to Antenna Loss1The SDU is capable of storing in nonvolatile memory the actual loss (to thenearest tenth of a dB) between the HPA and the input to the antenna for usein the power control computation. This loss is the sum of the HPA to diplexercable loss, the high power relay loss (if used), the diplexer loss, and thediplexer to antenna cable loss in an ARINC 741 system. This value isexpected to be between 0.9 and 2.5 dB, but the SDU allows the entry ofvalues in the range of 0.0 to 5.0 dB. A separate value is maintained andused for each antenna subsystem.2This loss value is necessary to enable the SDU to accurately set theantenna EIRPs, and to determine power availability for additionalC-channels. This value is not part of the ORT and is not an option. Thevalue is estimated/calibrated at the time of system installation orcommissioning, and can vary among otherwise identical installations. It isinadequate to assume a default of either end of the range, since at the lowend the AES would not necessarily make the return link in marginalconditions. At the high end, the SDU would radiate all carriers high, wastingpower and prematurely inhibiting further calls from being set up.(d) Class C HPA Maximum Output Power1When the HPA is class C, the SDU stores the calibrated HPA maximumoutput power value in nonvolatile memory. This value is calculated once perburst when there is a single measurable carrier present, unless the reportedactual power output value in the HPA status word:•Matches or is less than the minimum reportable actual power value storedin ORT item xxix•Matches either the unique code 00100Bfor at/below measurable rangeor 3 dB greater than 40 W; or the flag was set indicating the HPA ormodem backoff was limited.2This value is the actual output power reported by the HPA, plus the HPAbackoff. If the calibration results in a value outside the range of 14 dBW to21 dBW, a failure is raised for the HGA HPA and LGA HPA.(4) Antenna Subsystem Selection(a) The purpose of installing both HGA and LGA subsystems simultaneously is toincrease system availability and geographical orientation coverage. When theSDU has the choice of antenna subsystems (HGA or LGA), either as part of asingle MCS system or in its role as half of a dual system, reversion from HGA toLGA (and from LGA to HGA) is accomplished by automatic means. Automaticreversion from the HGA to the LGA occurs only upon failure of the HGAsubsystem. The SDU automatically switches from the LGA to the HGA if theHGA subsystem reverts to a normal state. In lieu of a physically separate LGA,an HGA is also usable as a steered LGA when its gain drops below the levelspecified by ORT item xxii.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--24(b) Loss of reliable communications with a GES normally occurs as a result ofchannel degradation. When channel degradation occurs, the AES considersitself logged-off and searches for another GES. If no GES is found forcommunications using the HGA subsystem, automatic switching to the LGAsubsystem does occur. Manual reversion through the SCDU is the only way theSDU switches from the HGA subsystem to the LGA subsystem.(c) The purpose of installing an IGA subsystem is to use the spot beam coverage.The satellite spot beams supply a times 8 (x8) amplification. Less power isrequired for C--channel (circuit mode) operation that equates to less cost perminute of operation.C. High Power Amplifier(1) The SDU sends such information as power amplifier on/off commands andamplification gain commands to the HPA. The bidirectional link carries status andmaintenance information to the SDU such as gain verification, standing wave ratiodata, and indication of dangerous system conditions such as temperature warningsor power supply failures.(2) The HPA supplies RF power amplification of the L-band signals generated by theSDU to a power level required for transmission to the satellite. Because multiplesignals are transmitted through the HPA, the HPA is a linear device (i.e., operatingclass AB) capable of amplifying more than one signal at a time. An average of 40Watts RF output power is developed by the HPA (up to 25 Watts RF power by the 20Watt HPA) while passing multiple signals without generating excessiveintermodulation products.(3) In addition to providing RF power amplification, the HPA must control output power tosupply the desired EIRP from the AES. The SDU controls the gain of the HoneywellHPA over a 25-dB range in 1-dB increments through the ARINC 429 interface. Thislets automatic adjustment of signal strength compensate for a wide variety ofconditions. The HPA also measures output power and available power and reports tothe SDU, which uses the information to determine if additional calls can beaccommodated.(4) Under favorable propagation conditions, the full output power capability of the HPA isnot required. The HPA automatically consumes less power and dissipates less heatwhen full power is not used.(5) The 20 Watt HPA supplies beam steering capabilities previously implemented in theantenna beam steering unit. Commands are generated to steer the antennaelements based on the SDU, IRS information, and beam map data stored in the HPA.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--25D. Avionics Configurations(1) The SDU determines the configuration installed on the aircraft, including thepresence of optional peripherals, by examining the system configuration pins. TheSDU supports interaction only with those peripherals indicated as being present bythe configuration pins.(2) The Aero H+ SATCOM system requires installation of an SDU and 40 Watt HPA, andsupports seven independent simultaneous channels for voice and datacommunications. One channel is dedicated to data and system managementtransactions. The remaining six channels are available for analog or digital voicecommunications.(3) The Aero I SATCOM system requires installation of an SDU and 20 Watt HPA, andsupports seven independent simultaneous channels for voice and datacommunications. One channel is dedicated to data and system managementtransactions. The remaining six channels are available for analog voicecommunications.4. MCS Component DescriptionsA. Physical Description(1) The LRUs are designed to perform reliably under field conditions and to supply easeof maintenance when required. Each LRU is designed as a modular concept unit(MCU), as defined by ARINC Characteristic 600, to permit easy replacement of eachshop replaceable unit (SRU). The SRUs use both digital and analog solid statecircuitry constructed using a mixture of surface mount technology (SMT) and dualin-line packaging (DIP) technology.(2) All SRUs are built to standards that qualify them for both airline and business aircraftusage. Adjustment mechanisms are accessible with the SRU installed in the LRU.These SRUs can be removed to reduce the number of functional channels withoutcompromising the functionality of the remaining channels.(3) The MCS system components meet the requirements specified in parts A and B ofthe Minimum Operational Performance Standards for Aeronautical Mobile SatelliteServices Document, Document No. RTCA/DO--210.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--26B. Satellite Data Unit (SDU)(1) The SDU is packaged as an ARINC 600 6--MCU suitable for mounting in theequipment bay. The mechanical chassis is constructed of lightweight aluminum alloysheet metal; forced air moving through the chassis in an upward or downwarddirection supplies internal cooling. Two hold-down clamps enable the unit to be firmlyclamped in the mounting rack. The unit is carried by a fixed C-shaped handlemounted to the front panel assembly.(2) The front panel assembly contains a 20-character alphanumeric display for displayingbuilt-in test equipment (BITE) failure messages, system LRU part numbers, and theORT identification. The display remains inactive when its temperature is less than-- 1 0 °C(+14°F) or greater than +50 °C(+122°F). The front panel also contains twomomentary action buttons labeled TEST and CM/SCROLL. The TEST button initiatesBITE in the SDU. The CM/SCROLL button lets the alphanumeric display scrollthrough the BITE failure messages and the software confirmation numbers.(3) The front panel also contains an ARINC 615 portable data loader connector and aprimary 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 withARINC 600) that engages a mating connector in the mounting rack when the SDU isinstalled. The top and middle inserts are type 02 arrangements and the bottom insertis a type 04 arrangement. Index pin code 04 is used on both the SDU and themounting rack connectors.(5) The SDU is shown in Figure 1-6. The SDU leading particulars are given in Table 1-9.DO--160D environmental categories for the SDU are given in Table 1-10.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--27Figure 1-6. Satellite Data UnitTable 1-9. SDU Leading ParticularsCharacteristic SpecificationDimensions (maximum):•Height ................................ 7.624 in. (193.65 mm)•Width ................................. 7.51 in. (190.75 mm)•Length ................................ 15.26 in. (337.60 mm)Weight (maximum) ....................... 21 lb (9.6 kg)Power Requirements:•ACVoltage ............................ 104 to 122 V ac, 380 to 420 Hz (normal operation)97 V ac, 360 Hz minimum; 134 V ac, 440 Hz maximum•DCVoltage ............................ 22.0 to 30.3 V dc (normal operation)20.5 V dc minimum, 32.2 V dc maximumRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--28Table 1-9. SDU Leading Particulars (cont)Characteristic SpecificationAC Current Requirements1.:•Nominal at 115 V ac (Current/Power Factor) 1.3 amps/0.70•Maximum at 104 V ac (Current/PowerFactor)................................ 2.1 amps/0.91DC Current Requirements:•Nominal at 28 V dc ..................... 3.8 amps•Maximumat20.5Vdc .................. 7.0 ampsCircuit Breaker Ratings:•115VacCircuitBreaker ................ 3 amp TYPE A•28VdcCircuitBreaker ................. 10 amp TYPE AUser Replaceable Parts ................... NoneOperatingTemperature.................... -- 5 5 _C(--67_F) to +70 _C (158 _F)OperatingAltitude ........................ to 70,000 ft (21.34 kilometers)Cooling Requirements2.:•Minimum .............................. 0.15 ±0.05 in. (3.81 ±1.27 mm) of water at a flow rate of72.8 ±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 of96.2 ±2.0 lb (43.6 ±0.9 kg) per hourPower Dissipation3.:•Nominal ............................... 105 W•Maximum ............................. 198 WMating Connectors:•J1 .................................... Radiall Part No. NSXN2P201X004•J2 .................................... Honeywell Part No. 4004295--160, ITT Part No.KJ6F18A53PMounting ................................ ARINC 600 6--MCU Tray AssemblyNOTES:1. All power factors (PF) are leading.2. Refer to Appendix A, Vendor Equipment, for mounting trays with integral cooling fans that meet the coolingrequirements.3. The SDU draws an additional 20 W during the first 10 minutes (maximum) of operation at 25_C(77_F) because ofthe OCXO. The OCXO continuously dissipates this additional 20 W at --55 _C(--67_F).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--29Table 1-10. SDU DO--160D Environmental CategoriesEnvironmental Condition CategoryTemperature and Altitude Category A2E1/Z (E1)1.Temperature Variation Category BHumidity Category AShock Category BVibration Category SB2Explosion Category EWaterproofness Category XFluids Susceptibility Category XSand and Dust Category XFungus Resistance Category XSalt Spray Category XMagnetic Effect Category ZPower Input -- 115 V ac Category EPower Input -- 28 V dc Category BZ2.Voltage Spike Category AAudio Frequency Susceptibility -- 115 V ac Category EAudio Frequency Susceptibility -- 28 V dc Category ZInduced Signal Susceptibility Category ZRadio Frequency Susceptibility Category RRRRadio Frequency Emissions Category MLightning Induced Category A3E3Lightning Direct Category XIcing Category XElectro Static Discharge Category ANOTES:1. E1 -- Operating High Temperature/High Short Time = 70 °C (158 °F).2. Z -- The power input requirements for the 28 V dc LRU are category Z except for an emergency operation, in whichcase the requirements of category B apply.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--30C. High--Power Amplifier (40 Watt)(1) The HPA is packaged as an ARINC 600 8--MCU suitable for mounting in theequipment bay or near the antenna system. The mechanical chassis is constructed oflightweight aluminum alloy sheet metal. Forced air moving through the chassis in anupward or downward direction supplies internal cooling. Two hold-down clamps letthe unit be firmly clamped in the mounting rack. The unit is carried by a fixedC-shaped handle mounted to the front panel assembly.(2) The front panel assembly contains a PTT switch to initiate BITE and a red (FAIL) andgreen (PASS) light emitting diode(LED) to indicate BITE status. The front panel alsocontains an ARINC 615 portable data loader connector and an RF monitor port.(3) The rear connector receptacle is a size No. 2 shell assembly (in accordance withARINC 600) that engages a mating connector in the mounting rack when the HPA isinstalled. The top insert is a type 08 arrangement, the middle insert is a type 05arrangement, and the bottom insert is a type 04 arrangement. Index pin code 08 isused on both the HPA and mounting rack connectors.(4) The HPA (40 Watt) is shown in Figure 1-7. The leading particulars for the HPA (40Watt) are given in Table 1-11. DO--160C environmental categories for the HPA (40Watt) are given in Table 1-12.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--31/(1--32 blank)Figure 1-7. High--Power Amplifier (40 and 20 Watt)RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--33Table 1-11. HPA (40 Watt) Leading ParticularsCharacteristic SpecificationDimensions (maximum):•Height ................................ 7.813 in. (198.45 mm)•Width ................................. 10.22 in. (259.59 mm)•Length ................................ 15.20 in. (386.08 mm)Weight (maximum) ....................... 29.15 lb (13.22 kg)Power Requirements:•ACVoltage ............................ 104 to 122 V ac, 380 to 420 Hz (normal operation)97 V ac, 360 Hz minimum; 134 V ac,440 Hz maximum•DCVoltage ............................ 22.0 to 30.3 V dc (normal operation)20.5 V dc minimum, 32.2 V dc maximumAC Current Requirements1.:•Nominal at 115 V ac (Current/Power Factor) 1.94 amps/0.95•Maximum at 104 V ac (Current/PowerFactor)................................ 2.2 amps/0.96DC Current Requirements:•Nominal at 28 V dc ..................... 7.3 amps•Maximumat20.5Vdc .................. 8.2 ampsRF Power Output:•Rated operating power .................. 40 W (multiple carriers)•Maximumpower ....................... 80 W (short duration, single carrier)Circuit Breaker Ratings:•115VacCircuitBreaker ................ 7.5 amp TYPE A•28 V dc Circuit Breaker2................. 30 amp TYPE AUser Replaceable Parts ................... NoneOperatingTemperature.................... -- 5 5 _C(--67_F) to +70 _C (158 _F)OperatingAltitude ........................ to 70,000 ft (21.34 kilometers)Cooling Requirements3.:•Minimum .............................. 0.15 ±0.05 in. (3.81 ±1.27 mm) of water at a flow rate of121.3 ±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 of176.4 ±2.0 lb (80.0 ±0.9 kg) per hourRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--34Table 1-11. HPA (40 Watt) Leading Particulars (cont)Characteristic SpecificationPower Dissipation:•Nominal ............................... 300 W•Maximum ............................. 362 WMating Connectors:•J1 .................................... Radiall Part No. NSXN2P221X0008•J2 .................................... Honeywell Part No. 4004295--160,ITT Part No. KJ6F18A53P•J3 .................................... BNC PlugMounting ................................ ARINC 600 8--MCU Tray AssemblyNOTES:1. All PF are leading.2. Wiring can not exceed 18 V dc drop at 30 amps.3. Refer to Appendix A, Vendor Equipment, for mounting trays with integral cooling fans that meet the coolingrequirements.Table 1-12. HPA (40 Watt) DO--160C Environmental CategoriesEnvironmental Condition CategoryTemperature and Altitude Category A2E1/Z (E1)1.Temperature Variation Category BHumidity Category AShock Category BVibration Category BLMYExplosion Category E1Waterproofness Category XFluids Susceptibility Category XSand and Dust Category XFungus Resistance Category XSalt Spray Category XMagnetic Effect Category ZPower Input -- 115 V ac Category EPower Input -- 28 V dc Category Z2.Voltage Spike Category ARELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--35Table 1-12. HPA (40 Watt) DO--160C Environmental Categories (cont)Environmental Condition CategoryAudio Frequency Susceptibility -- 115 V ac Category EAudio Frequency Susceptibility -- 28 V dc Category ZInduced Signal Susceptibility Category ZRadio Frequency Susceptibility Category W3.Radio Frequency Emissions Category ZLightning Induced Category KLightning Direct Category XIcing Category XNOTES:1. E1 -- Operating High Temperature/High Short Time = 70 °C (158 °F).2. Z -- The power input requirements for the 28 V dc LRU are category Z except for an emergency operation, in whichcase the requirements of category B apply.3. W -- Performance of this test is required to satisfy the HIRF requirements. The LRUs must survive a category Wevent without degradation (i.e., regain normal operation at the termination of the HIRF event), and must operatethrough (with performance degradation permitted) and after (without performance degradation) a category T event.D. High--Power Amplifier (20 Watt)(1) The HPA is packaged as an ARINC 600 4--MCU suitable for mounting in theequipment bay or near the antenna system. The mechanical chassis is constructed oflightweight aluminum alloy sheet metal. Forced air moving through the chassis in anupward or downward direction supplies internal cooling. Two hold-down clamps letthe unit be firmly clamped in the mounting rack. The unit is carried by a fixedC-shaped handle mounted to the front panel assembly.(2) The front panel assembly contains a PTT switch to initiate BITE and a red (FAIL) andgreen (PASS) LED to indicate BITE status. The front panel also contains an ARINC615 portable data loader connector.(3) The rear connector receptacle is a size No. 2 shell assembly (in accordance withARINC 600) that engages a mating connector in the mounting rack when the HPA isinstalled. The top insert is a type 08 arrangement, the middle insert is a type 05arrangement, and the bottom insert is a type 04 arrangement. Index pin code 08 isused on both the HPA and mounting rack connectors.(4) The HPA (20 Watt) is shown in Figure 1-7. The leading particulars for the HPA (20Watt) are given in Table 1-13. DO--160D environmental categories for the HPA (20Watt) are given in Table 1-14.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--36Table 1-13. HPA (20 Watt) Leading ParticularsCharacteristic SpecificationDimensions (maximum):•Height ................................ 7.64 in. (194.056 mm)•Width ................................. 4.90 in. (124.46 mm)•Length ................................ 15.26 in. (387.604 mm)Weight (maximum) ....................... 15.80 lb (7.17 kg)Power Requirements:•ACVoltage ............................ 104 to 122 V ac, 380 to 420 Hz (normal operation)97 V ac, 360 Hz minimum; 134 V ac, 440 Hz maximum•DCVoltage ............................ 22.0 to 30.3 V dc (normal operation)20.5 V dc minimum, 32.2 V dc maximumAC Current Requirements1.:•Nominal at 115 V ac (Current/Power Factor) 1.94 amps/0.96•Maximum at 104 V ac (Current/PowerFactor)................................2.2 amps/0.96DC Current Requirements:•Nominal at 28 V dc ..................... 7.3 amps•Maximumat20.5Vdc .................. 12 ampsRF Power Output:•Rated operating power .................. 25.1 W (under all conditions)•Maximumpower ....................... 25.1 W (under all conditions)Circuit Breaker Ratings:•115VacCircuitBreaker ................ 7.5 amp TYPE A•28VdcCircuitBreaker ................. 15 amp TYPE AUser Replaceable Parts ................... NoneOperatingTemperature.................... -- 1 5 _C(5_F) to +70 _C (158 _F)OperatingAltitude ........................ to 55,000 ft (16.76 kilometers)Cooling Requirements (Minimum)2.......... 0.20 ±0.12 in. (5 ±3 mm) of water at a flow rate of 72.8 ±2.0 lb (33.0 ±0.9 kg) per hourPower Dissipation:•Nominal ............................... 150 W•Maximum ............................. 219 WRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--37Table 1-13. HPA (20 Watt) Leading Particulars (cont)Characteristic SpecificationMating Connectors:•J1 .................................... Radiall Part No. NSXN2P221X0008•J2 .................................... Honeywell Part No. 4004295--160, ITT Part No.KJ6F18A53PMounting ................................ ARINC 600 4--MCU Tray AssemblyNOTES:1. All PF are leading.2. Refer to Appendix A, Vendor Equipment, for mounting trays with integral cooling fans that meet the coolingrequirements.Table 1-14. HPA (20 Watt) DO--160D Environmental CategoriesEnvironmental Condition CategoryTemperature and Altitude Category A2E1/Z (E1)1.Temperature Variation Category BHumidity Category AShock Category BVibration Category SB2Explosion Category EWaterproofness Category XFluids Susceptibility Category XSand and Dust Category XFungus Resistance Category XSalt Spray Category XMagnetic Effect Category ZPower Input -- 115 V ac Category EPower Input -- 28 V dc Category BZ2.Voltage Spike Category AAudio Frequency Susceptibility -- 115 V ac Category EAudio Frequency Susceptibility -- 28 V dc Category ZInduced Signal Susceptibility Category ZRadio Frequency Susceptibility Category RRR3.Radio Frequency Emissions Category MRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--38Table 1-14. HPA (20 Watt) DO--160D Environmental Categories (cont)Environmental Condition CategoryLightning Induced Category A3E3Lightning Direct Category XIcing Category XElectrostatic Discharge Category ANOTES:1. E1 -- Operating High Temperature/High Short Time = 70 °C (158 °F).2. BZ -- The power input requirements for the 28 V dc version of the 20 Watt HPA are category Z except for anemergency operation, in which case the requirements of category B apply.3. RRR -- Performance of this test is required to satisfy the HIRF requirements.E. CMA--2200 Intermediate Gain Antenna(1) The Intermediate Gain Antenna supplies a minimum of 6 dB antenna gain (8 dBnominal) and operates with the 20 W HPA. The IGA is manufactured by BAESystems Canada Inc. (formerly Canadian Marconi Company Aerospace) under bothBAE Systems -- Canada Part No. 100--602372--000 and Honeywell Part No.7516194--901. Features of the IGA are given in Table 1-15.Table 1-15. CMA--2200 Intermediate Gain Antenna FeaturesCharacteristic SpecificationServicecoverage.........................less than 95% of the Inmarsat hemisphere•Receive..............................1525.0 -- 1559.0 MHz•Transmit.............................1626.5 -- 1660.5 MHzPolarization ..............................Right hand circularReceive figure of merit (G/T)............--15.5 dB/K typical, --19 dB/K minimumEffective Isotropic Radiated Power (EIRP) 19.5 dBW typical, 16.5 dBW minimumPhase discontinuity.....................2.5_typical, less than 30_for 99% of all beamsteering incrementsBeam switching.........................50 µs maximumCarrier/Multipath........................15 dB typical, 10 dB minimum at 5_elevation; 20 dBtypical,12 dB minimum at 20_elevationSatellite discrimination..................16 dB typical, 7 dB minimumLatitude global Inmarsat satellitecoverage............................... ±86 degreesRequired antenna gain..................6dBRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--39Table 1-15. CMA--2200 Intermediate Gain Antenna Features (cont)Characteristic SpecificationSupport/Test equipment required........None at organizational levelDesign characteristics(RTCA/ARINC/TSO/etc.)................DO--160C, ARINC 761, MOPS, SARPS(2) Other features of the CMA--2200 IGA include:•Inmarsat Generation 3 Spot Beam coverage•Proven compatibility with ARINC 761 intermediate--gain antenna subsystems•BIT status reporting.(3) The leading particulars for the CMA--2200 IGA are given in Table 1-16. DO--160Cenvironmental categories for the CMA--2200 IGA are given in Table 1-17.Table 1-16. CMA--2200 IGA Leading ParticularsCharacteristic SpecificationDimensions (maximum):•Height ................................ 3.82 in. (97.0 mm)•Width:-- At radome ........................... 3.22 in. (81.8 mm)-- Atbase ............................. 4.25 in. (108.0 mm)•Length ................................ 29.92 in. (760.0 mm)Weight (maximum) ....................... 6lb(2.7kg)Power Requirements ..................... 15 V dc, 8 V dc and --80 V dc (7 Watts)Operating Environment:•Temperature range (operating) ........... -- 5 5 _to +70_C(--67_to +158_F)•Temperature range (non--operating) ....... -- 5 5 _to +85_C(--67_to +158_F)•Operatingaltitude ...................... to 70,000 ft (21.34 km)Mating Connectors:•J1 .................................... Circular Connector -- Part No. D38999/26FB35SN•J2 .................................... TNC JACK -- Mates with TNC plugRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--40Table 1-17. CMA--2200 IGA DO--160C Environmental CategoriesEnvironmental Condition CategoryTemperature and Altitude E1In--Flight Loss of Cooling XTemperature Variation AHumidity COperational Shock and Crash Safety -- --Vibration EExplosion Proofness XWaterproofness SFluids Susceptibility FSand and Dust DFungus Resistance FSalt Spray SMagnetic Effect XPower Input XVoltage Spike XAudio Frequency Conducted Susceptibility AInduced Signal Susceptibility ARadio Frequency Susceptibility URadio Frequency Emissions ALightning Induced XXE3Lightning Direct Effects 2AIcing CF. CMA--2200 Diplexer/Low Noise Amplifier(1) The CMA--2200 Diplexer/Low Noise Amplifier (D/LNA) supplies the RF transmit(diplexer) and RF receive (low noise amplifier) paths between the HGA, IGA, or LGAand the HPA and SDU, respectively. The D/LNA is manufactured by BAE Systems --Canada (formerly Canadian Marconi Company Aerospace) under both BAE Systems-- Canada Part No. 100--602200--001 and the Honeywell Part No. 7516193--901. Thefeatures of the D/LNA are given in Table 1-18.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--41Table 1-18. CMA--2200 D/LNA FeaturesCharacteristic SpecificationFrequency range:•Receive ...............................1525.0 -- 1559.0 MHz•Transmit.............................1626.5 -- 1660.5 MHzReceive gain...........................53 dB minimum, 60 dB maximumNoise figure............................0.8 dB maximum at 25_C.Support/Test equipment required........ None at organizational levelDesign characteristics..................(RTCA/ARINC/TSO/etc)DO--160C, ARINC 741/761, MOPS, SARPS(2) Other features of the CMA--2200:•Proven compatibility with:-- ARINC 761 intermediate--gain antenna subsystems-- ARINC 741 high--gain or low--gain antenna subsystems•Self--test function.(3) The leading particulars for the CMA--2200 D/LNA are given in Table 1-19. DO--160Cenvironmental categories for the CMA--2200 D/LNA are given in Table 1-20.Table 1-19. CMA--2200 D/LNA Leading ParticularsCharacteristic SpecificationDimensions (maximum):•Height ................................ 2.00 in. (50.8 mm)•Width ................................. 7.78 in. (197.6 mm)•Length ................................ 11.59 in. (294.4 mm)Weight (maximum) ....................... 6.5lb(3.0kg)Power Requirements ..................... 115 V ac, 400 Hz, 150 milliamps maximumOperating Environment:•Temperature range (operating) ........... -- 5 5 _to +70_C(--67_F to +158_F)•Temperature range (non--operating) ....... -- 5 5 _to +85_C(--67_F to +158_F)•Operatingaltitude ...................... to 70,000 ft (21.34 km)RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--42Table 1-20. CMA--2200 D/LNA DO--160C Environmental CategoriesEnvironmental Condition CategoryTemperature and Altitude E1In--Flight Loss of Cooling XTemperature Variation BHumidity AOperational Shock and Crash Safety -- --Vibration CExplosion Proof E2Waterproof WFluids Susceptibility XSand and Dust XFungus Resistance FSalt Spray XMagnetic Effect APower Input EVoltage Spike AAudio Frequency Conducted Susceptibility EInduced Signal Susceptibility ZRadio Frequency Susceptibility VRadio Frequency Emissions ZLightning Induced XXE3Lightning Direct Effects XIcing XRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--43G. Radio Frequency Unit Interface Adapter (RFUIA)(1) The RFUIA is packaged as an ARINC 600 4--MCU suitable for mounting in theequipment bay or near the antenna system. It consists of a housing assemblyintegrated with an ARINC 600 connector on the back of the unit.(2) The RFUIA is not an operational unit and it does not contain active internal electroniccomponents. No aircraft power is needed. This unit is installed in the aircraft in placeof the RFU to complete the RF receive and transmit paths for the MCS--7000 system.(3) The housing is constructed of lightweight aluminum alloy sheet metal. No forced aircooling is required. Two hold-down clamps let the unit be firmly clamped in themounting rack. The unit is carried by a fixed C-shaped handle mounted to the frontpanel assembly.(4) Figure 1-8 is a block diagram that shows how the RFUIA interfaces to the othersystem LRUs. The leading particulars for the CMA--2200 D/LNA are given inTable 1-21.Figure 1-8. RFUIA System Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--44Table 1-21. RFUIA Leading ParticularsCharacteristic SpecificationDimensions (maximum):•Length ................................•Width .................................•Height ................................12.76 in. (324.1 mm)4.90 in. (124.5 mm)7.64 in. (194.1 mm)Weight (maximum) 4lb(1.82kg)Power requirements NoneCooling Convection, no forced air requiredH. ARINC 429 Data Requirements(1) The MCS system requires ARINC 429 data for antenna pointing, antennastabilization, and Doppler frequency correction. If the aircraft does not have an IRSthat supplies this ARINC data, the SCU can be used to convert INS data sources.Refer to Appendix A, Vendor Equipment, for additional information about the SCUand the ARINC 429 data requirements.I. Nameplates 3 (SDU and HPA)(1) General(a) Each LRU has two externally mounted nameplates consisting of:•Front panel--mounted LRU nameplate•Second LRU nameplate that reflects the full hardware and software status ofthe LRU.(b) The details of these nameplates are specified in the following paragraphs. SeeFigure 1-6 and Figure 1-7 for the location of each nameplate.(2) Front Panel LRU Nameplate(a) Each front panel LRU nameplate contains each company’s logo (Honeywell andRacal), the name of the system, and the LRU equipment name.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--45(3) LRU Hardware and Software Nameplate(a) Each LRU hardware and software nameplate contains the following information:•Name of the company responsible for manufacturing it•Model number (e.g., SD700, HP600, or HP700)•LRU equipment name•LRU hardware part number•LRU serial number•Weight•Applicable DO--160C/DO--160D categories•FCC identifier•LRU hardware modification level•LRU end item part number•LRU software part number•Software modification level•Applicable DO--178A or DO--178B software level.(b) The model number is a five--digit alphanumeric sequence. The first two digits areupper--case alphabetic characters in the range AA to ZZ and the last three digitsare numeric characters in the range 100 to 999. The LRU equipment name isdisplayed with as many upper--case letters as are required to spell out theequipment name. The LRU serial number consists of an eight--digit numericsequence; the first two digits indicate the year of manufacture, the second twodigits indicate the month of manufacture, and the final four digits indicate howmany LRUs of this type have been manufactured. The range of the last fourdigits is 0100 to 9999.(c) The DO--160C or DO--160D categories applicable to the MCS system consist ofa mix of numeric and upper--case alphabetic characters. See Table 1-10,Table 1-12, or Table 1-14 for a list of environmental categories applicable to theMCS LRUs.(d) The FCC identifier applicable to all MCS LRUs is GB8MCS--4000 orGB8MCS--7000. The LRU hardware modification level is indicated by the set ofall marked modification level identifiers. Each modification level identifier is amaximum of two upper--case alphabetic characters that range from A to ZZ, withletters I, O, Q, and X excluded.(e) The LRU end item part number consists of a seven--digit base part number and afive--digit dash number. The first two digits of the dash number indicate the LRU’shardware configuration and consist of numeric values ranging from 10 to 99. Thelast three digits of the dash number reflect the LRU’s software configurationnumber and consist of numeric values ranging from 001 to 999.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 1--46(f) The software modification level consists of a maximum of two upper--casealphabetic characters ranging from A (or “--”) to ZZ, with letters I, O, Q, and Xexcluded. Usage of this nameplate characteristic reflects the implementation ofminor software changes.(g) The DO--178A or DO--178B software levels applicable to the MCS LRUs is thelevel an LRU was certified. This nameplate is capable of being removed andreplaced when a software change is significant enough to require the three--digitsoftware configuration number be incremented, or a hardware change issignificant enough to require that the two--digit hardware configuration numberbe incremented.J. Software and Hardware Compatibility (SDU and HPA)(1) Provisions for a set of discrete wire jumpers (straps) are included in each MCS LRUto ensure hardware and software compatibility. The code setting for these straps ismanually changed each time a hardware revision is made that is not compatible withall previously released versions of software. The status of these straps is testedevery time an LRU undergoes a cold start (power--on self--test [POST], orperson--activated self--test [PAST] ), and every time a software load is attempted froman ARINC 615 portable data loader.(2) The LRU header records in the ARINC 615 data loader software upload file and inthe operational software itself, contain a list of hardware/software compatibility strapcodes with which the software is compatible. This list of codes is compared with thewired hardware/software compatibility strap code in the LRU; if any of the codes inthe software upload file match the hardware/software compatibility strap code in theLRU, then the software upload process is allowed (otherwise it is inhibited). Similarly,if any of the codes in the software itself match the strap code in the LRU, normal LRUoperation is allowed (otherwise it remains in an inert state).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--1SECTION 2SYSTEM OPERATION1. OverviewA. GeneralThe AES accepts data and voice signals from various sources, encodes the signals,modulates the information onto the appropriate RF carrier frequencies, and transmits thesecarriers to a GES through satellite. The AES also receives RF signals from the satellites,demodulates and decodes these signals, and outputs data or voice message for passengersor flight crew members. System operation begins when the P--channel transmission from aGES in the satellite region is received. The AES then logs onto the GES to establish theuplink and exchange information. System operation terminates when the AES logs off fromthe GES.2. AES ManagementA. General(1) At any time, different satellite regions can have different satellite configurations. Allsatellites have the global beam capability to receive the continuous Psmc--channeltransmission of every GES in view. For a spot beam satellite, each spot beam isassociated with at least one GES having a continuous P--channel transmission.Selected channels from the Psmc-- and Pd--channels are designated by INMARSATfor satellite and spot beam selection.(2) An AES logs onto a GES to enter the satellite communications system and logs off toterminate its operation in the system. Log-off is initiated automatically or by a usercommand issued as part of normal operational procedures.(3) The AES also logs off before initiating handover. The AES does not log off ifhandover is initiated because of degradation or loss of the P--channel. Handover canbe initiated by the flight crew, or can be carried out automatically by the AES withouthuman intervention. A handover procedure is followed automatically when an AESneeds 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 theflight crew, to change its log-on to another GES operating in the same satelliteregion, any previously established data communication channels are maintained untilclearing before the handover is carried out. In the case of a user command initiatedsatellite-to-satellite handover, the AES ensures all communication channels are clearprior to starting the handover procedure. If any connections are in progress, the AESapplies time supervision of three minutes and then clears any remaining connections.(5) Automatic handover is initiated upon detection of Pd--channel link degradationdefined as:•Error rate rises above 104over an averaging period of 3 minutes•More than 10 short--term interruptions (loss of P--channel clock synchronization forless than 10 seconds) in any 3 minute period.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--2(6) Automatic handover is also initiated upon detection of loss of the Pd--channel definedas:•Loss of clock synchronization for more than 10 seconds•Log-on renewal procedure is unsuccessful.(7) A GES-to-GES handover is carried out by logging onto a new GES in the samesatellite region. The required P--channel frequency can be found in the system table.Each GES maintains an up-to-date status table of all AESs that have logged on.Each GES also has an inter-GES signaling capability letting the GES set up calls withany AES operating in the same satellite region as that GES, and manages the AESsduring handover.(8) If the AES attempts to renew its log-on and fails to log on to its previous GES or tothe preferred alternative GES after a log-on prompt, loss of P--channel quality, or alog-on renewal request from an application, the AES returns to the latter stages ofthe initial search procedure and scans the spot beam primary Pd--channels on itscurrent satellite to identify an alternative spot beam. The required P--channelfrequencies are found in the system table. Once an alternative spot beam isidentified, 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 anotherGES in the same satellite region, then the AES enters the search mode to select thePsmc--channel frequency of a GES operating in a new satellite region. The requiredP--channel frequency is found in the system table. Having selected a new suitablequality Psmc--channel (in another satellite region) and updating the system table forthe new satellite region (if necessary), the AES carries out a log-on procedure withthe new GES.(10) Each AES maintains a system table stored in nonvolatile memory in the SDU. Thesystem table contains the satellite and GES identifying information, such as satellitePsid--channel frequencies, satellite locations and associated GES IDs, and GESPsmc--channel frequencies. The system table does not lose its contents because ofloss of primary power.(11) The SDU also maintains a bootstrap system table containing a default set of satelliteand GES identifying information. This information includes satellite Psid--channelfrequencies, satellite location and associated GES IDs, plus satellite inclination andright ascension, spot beam support, and GES Psmc--channel frequencies that are setto zero.(12) The bootstrap system table is loaded into the SDU as an inseparable part of theupload of executable software. The SDU defaults to the bootstrap system table in theabsence of a stored system table, or upon execution of a factory settings restart. Thedefault data for a satellite is used until that satellite is first accessed, where acomplete update of the data for that satellite takes place. Satellite region blocks thathave not yet been updated over the air are marked with a null revision number.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--33. System Log-On/Log-OffA. 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 andhandover procedures occurring without external control. In the user commandedmode, the flight crew or flight control system is able to select the satellite and GES forlog-on and handover, and can initiate handovers at any time. The automatic mode isconsidered the normal mode of operation.(3) The log-on/log-off of an AES to/from the satellite communications system lets theGES manage the number of AESs that can receive a P--channel (Pd) and transmit oneach R--channel (Rd). This controls the queuing delays and burst collisionprobabilities that can be experienced. When an AES is powered up, it enters a GESselection mode if the log-on policy is set to automatic. This permits the AES to selectthe most preferred GES operating in its visible satellite region (there may be one ortwo satellites visible to the AES), and that GES is selected for log-on. If the log-onpolicy is not set to automatic, the AES waits for the GES to be selected through theuser 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--channelfrequencies of the satellite contained in the initial system table. Typically there aretwo frequencies per satellite (or group of satellites if several satellites supply serviceto essentially one region). The AES receives that Psmc--channel until one of thesystem table’s broadcast signal units is received, which permits the AES to determinewhether 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 isimplemented.(5) When the revision number is verified as correct, the AES checks for any entries in thesatellite spot beam search table. If an entry exists, the AES checks the Pd--channelfrequencies of all spot beams supported by the selected GES to identify the mostapplicable spot beam. The AES then determines which Pd--channel has the highestsignal quality. Once this task is complete, the AES is ready to log-on to the satellitecommunications system using the selected GES and the optimum spot beam, or theglobal beam if the GES does not operate a P--channel in the required spot beam.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--4(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 thecorresponding Rsmc--channels. If the log-on request signal unit cannot be acceptedby the GES, because of reasons like GES overload, invalid message, unauthorizedaccess, etc, the GES responds with a log-on reject signal unit, which includes thecause of the rejection. By returning a log-on confirm signal unit with a different AESclass value, the GES can offer log-on in a different AES class than originallyrequested. The AES can either accept log-on in the offered class by continuing thelog-on signaling procedure, or reject log-on by discontinuing the log-on signalingprocedure.(7) The AES uses the log-on request signal unit to supply the selected GES with its ownidentification (a 24-bit ICAO aircraft identification code), plus the identification of thespot beam where the AES is located. A zero value is used in the spot beamidentification 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 tohandle, the bit rate/coding algorithm in use on the voice channels, and the data bitrate capability for the R--channels, P--channels, and T--channels. Except for thenumber of C--channels and the data bit rate capability, this information is repeated inthe log-on confirm signal unit for use by other GESs.(9) An AES having circuit-mode data service capability and desiring allocation ofcircuit-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 analoginterconnect or digital interconnect. If the GES does not support circuit-mode dataservice, it ignores the information. If the GES supports the service, it registers theinformation in its log-on AES table and retransmits the information for use by otherGESs.(10) The AES supplies the GES with its flight identification number at log-on, if theowner/operator of the AES desires to use the aircraft flight identification as theaddress for ground originated calls. The use of this information in the GES dependsupon the services being offered, and therefore is at the discretion of the GESoperator.(11) The AES is given an EIRP setting for Rd--channels in the log-on confirm signal. If aT--channel is assigned, the AES determines the EIRP for the T--channel inaccordance with the assigned R--channel EIRP and the ratio of the R--channel andT--channel bit rates. The GES assigns a Pd--channel from the available channels,taking into account the loadings on the channels, the need to use a P--channel of lowpower if possible, and the need to supply some means of recovery from P--channeldegradation or failure. The ability to work with a low power P--channel is determinedby 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--channelcontrol signaling message following the log-on confirm.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--5(12) If the GES is using more than one set of R--channel frequencies and assigns newRd--channels to the aircraft, the GES transmits the new channel frequencies (up toeight) to the AES using the signaling message(s) that follow the log-on confirm. Inaddition, the GES transmits from one to four T--channel frequencies to the AES ifdata services are supplied. The GES uses the following criteria to determine thechannel and EIRP assignments for data services:•Satellite in use (its return link sensitivity)•Class of AES•Bit rate capability of the AES.(13) The GES assigns data channels at the highest agreeable bit rate supplied in both theAES and GES, and supported by the combination of the satellite in use and the classof AES. Subsequent log-on transactions for handover use Rsmc-- andPsmc--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 iscurrently 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 theSCDU, from the analog connected telephone handsets, or from the commissioningand maintenance terminal (CMT).(3) When the AES is in the automatic mode, the log-on GES/satellite/spot beam chosenis based on the GES preference (ORT item iii). A GES with a preference level of zerois not considered for automatic log-on. The SDU allows the use of tied GESpreferences. The SDU resolves tied preferences by selecting the GESs indescending order of satellite elevation. During GES selection, the set (as yet untied)of GESs with the highest preference are initially processed to exclude those GESsassociated with satellites not in view.(4) Satellites are deemed in view if they are above the elevation handover thresholdspecified in ORT item xxxix, or their elevation is higher than 1 degree less than theelevation of the highest satellite. If no IRS data is available and the currently selectedantenna is the low gain antenna, then all satellites are deemed to be in view. Theremainder of the GESs in the preference group are then sorted into a list by satelliteelevation and GES on the highest elevation satellite chosen for initial access. If morethan one GES in the preference group have the same satellite elevation, then thoseGESs are ordered by a pseudo-random choice algorithm with a uniform probabilitydensity.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--6C. Constrained Log-On(1) Constrained log-on is where the user manually selects the specific GES to be usedfor log-on. The user command can originate from either the SCDU, from theanalog-connected telephone handsets, or from the CMT. The GES preferencesspecified in ORT item iii have no effect in the constrained log-on mode, and it ispossible to execute a constrained log-on to a GES with a preference level of zero.(2) If the user has manually selected the log-on GES, and therefore also selecting thesatellite, the SDU is constrained to search for the specific GES-related satellite Psidfrequency (or frequencies), the set of spot beam Pd frequencies where the selectedGES radiates P--channels, and the selected GES Psmc frequency during the log-onsequences. If the specific GESs satellite Psid frequencies cannot be acquired, theSDU takes no action other than to reattempt the acquisition with alternate modems. Ifnone of the GES-related spot beam Pd frequencies can be acquired, the SDU startsthe GES Psmc frequency search as it would normally do after acquiring a spot beamfrequency. If the GES Psmc frequency cannot be acquired, the SDU reattempts theacquisition indefinitely. This state of unsuccessful satellite/GES Psmc frequencyacquisition is exited either by the frequency being acquired, or by a user command toselect 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 handovertakes place. The user is able to exit this constrained log-on mode by commandinglog-off, by selecting the automatic log-on mode, or by cycling SDU primary power (ifORT 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 theconstrained mode causes the SDU to abort the current log-on attempt and revert tothe automatic mode. User selection of the automatic log-on mode while the AES islogged-on in the constrained mode causes the SDU to log-off from the currentconstrained GES, and to revert to the automatic mode if there are GESs in view withhigher preference levels than the current log-on GES. User selection of the automaticmode 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 inthe constrained or automatic mode.(2) The user is able to change the selected GES if the AES is logging-on or is logged onin the constrained mode. The user can enter the constrained mode by selecting aspecified GES while the SDU is logging-on or is logged-on in the automatic mode. Inboth cases, providing the constrained GES selection is different from theautomatically chosen GES, the SDU either aborts the current log-on attempt orlogs-off from the current GES before attempting to log-on to the new GES, dependingupon the current status.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--7E. Handover(1) The SDU causes the AES to initiate a handover procedure for the following reasons:•Automatic handover when the AES is logged-on in the automatic or constrainedmode, because of P--channel degradation.•Automatic handover when the AES is logged-on in the automatic mode, becauseof the log-on satellite being below the elevation handover threshold specified inORT item xxxix, with another satellite being at least 1 degree higher than thelog-on satellite for more than 10 seconds.•Automatic handover as specified in ORT item xxii for 10 seconds because of thereported HGA Tx gain being less than the threshold value when the AES islogged-on in the automatic or constrained mode.•User command to select the constrained mode when the AES is logged-on (orawaiting log-on acknowledge) in the automatic mode if the constrained selection isdifferent from the current, automatically selected GES.•User command to select the constrained mode for a particular GES when the AESis currently logged-on (or awaiting log-on acknowledge) to a different GES, butalso in the constrained mode.•User command to select the automatic mode when the AES is logged-on (orawaiting log-on acknowledge) in the constrained mode if a GES exists with ahigher preference level than the current log-on GES.•User command to adjust the GES preference levels if the AES is logged-on (orawaiting log-on acknowledge) in the automatic mode, and the adjustment resultsin 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 forall of the above handover stimuli, except for automatic handover because ofP--channel degradation and automatic handover because of the reported HGA Txgain being less than the threshold value.(3) If any modems are being used for circuit--mode voice when a handover to a GES in adifferent satellite region occurs, then the SDU terminates the current C--channel callswith an SLCV cause of 1221x. The SDU also causes a suitable voice pacifiermessage (Sorry, your call can no longer be sustained) to be sent to each currentlyin-use digital or analog headset to inform each user of the reason for the calltermination. The SDU does not clear down any ongoing C--channel calls if thehandover 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 theanalog-connected telephone handset, or from the CMT. Log-off is also initiated by theSDU as part of the handover sequence, except for handovers implemented becauseof P--channel degradation.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--84. System Software/Database UpdatesA. General(1) Each MCS LRU (SDU and HPA) has an ARINC 615 Airborne Data Loader (ADL) andPDL port. The SDU and HPA are capable of transferring the data sets listed inTable 2-1 through these ports.Table 2-1. Data Set Upload/DownloadLRU Data Set Upload/DownloadSDU Operational Software Upload OnlyOwner Requirements Table Upload and DownloadEvent and Failure Logs Download OnlyMaintenance Activity Log Download OnlyPeriodic Data Logging (SDU system andoperational parameters)Download OnlyHPA Operational Software Upload Only(2) In Table 2-1, upload is defined as the transfer of a data set from the ARINC 615 dataloader to the appropriate LRU. A download is defined as the transfer of a data setfrom an appropriate LRU to the ARINC 615 data loader. The data set to betransferred is independent of the port used. If during a data transfer session the otherport becomes active, the session associated with the initially activated port continuesto completion before initiating any session with the other port. The software uploadfunction is resident in the bootstrap program and functions independently of anyuploadable software in the LRU.B. Software Upload Process(1) The uploading of the software is done by either connecting a PDL to the ARINC 615connector port on the LRU to be programmed, or (in the case of an ADL) by the userselecting the LRU to be programmed. With the data loader connected, the Link Aconnection is completed.(2) The diskette containing a configuration file and a file containing the software to beuploaded is inserted into the disk drive of the data loader. The configuration filecontains 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 theroot directory of the diskette with the filename CONFIG.LDR. The data loader readsthe configuration file and initializes itself according to the parameters read. The dataloader then repeatedly transmits an RTS word.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--9(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 validwhere the on-ground/airborne state is ignored).•SDU detects receiving an RTS word with a system address label (SAL) equal to307.(4) The HPA software is similarly initiated only after the requirements mentioned aresatisfied, except software uploading is also enabled when a valid air/ground statusfrom the SDU is not available to the LRU.(5) For the LRUs, the software upload is a single pass process. Upload validation checksboth the LRU and SRU header records for applicability. Each data loader block isthen transferred directly to the program store. When the software upload iscompleted, the program store CRC is checked over defined regions of the programstore. If either validation process fails, the software upload process aborts. Furtherupload 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 transfercomplete function and the LRU remains in the data load state, while the Link Aconnection remains intact. When the Link A connection is removed, the HPAperforms a POST and the SDU performs a factory settings restart. A factory settingsrestart results in Category C nonvolatile data being set to default values followed byexecution 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 forthe 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 asgiven on the LRU nameplates.•Software compatibility codes in each SRU ID PROM must appear in the list ofcompatible hardware/software codes for every SRU listed in the LRU header.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--105. Owner Requirements TableA. General(1) The ORT is stored in nonvolatile memory in the SDU. The ORT contains informationrelating to different areas of functionality like log-on and telephony. The ORT doesnot lose its contents because of the loss of SDU primary power or as a result ofPAST. All ORT contents are set to default values by a factory settings restart. TheORT contains all pilot and aircraft operator entered information preserved when theSDU 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 checksumresults in the SDU reverting to the default values specified in TESTING/FAULTISOLATION, ORT default value usage. The contents of the ORT are specified inAppendix C.(3) The ORT items are organized into two distinct partitions:•Secured•User.(4) The individual ORT items defined in Table C--1.1 are assigned to a partition by thedesignation of secured or user in the attributes column.(5) The secured partition contains those items the equipment manufacturer, aircraftmanufacturers, and certification authorities have determined to beconfiguration-dependent and crucial to the proper operation of the SATCOM system.The user partition contains all other items of the ORT. The user partition typicallyincludes items the aircraft operator is able to set or modify, enabling the efficient useof the equipment in normal operation. A composite ORT file contains all items (bothpartitions) 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 bythe 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 1and 2, the ORT items affected are duplicated withintheORT.Eachofthoseitemsiscapable of storing separate, independent entries for SDUs 1 and 2, to be used byeach particular SDU as appropriate based on the strapping of its systemconfiguration pins TP13E/F. The lone SDU in a single system uses the entry for SDU1 for duplicated items. ORT items not duplicated are said to be common,wherethesingle entry applies to SDUs 1 and 2 in dual systems as well as to the lone SDU in asingle system.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--116. ORT Upload/Download ProcessA. General(1) Each ORT download/upload diskette contains a configuration file. The configurationfile contains information for the data loader (ADL or PDL) to configure itself foroperation. All MCS ORT download/upload diskettes contain a configuration filelocated 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 anORT header record followed by the ORT data. The ORT format version in the ORTheader 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, whichreads the configuration files and initializes itself according to the parameters read.The data loader then repeatedly transmits a POLL word. The LRU detects receiving aPOLL word and initiates the ORT download/upload.(2) In the event no configuration file is present or the diskette is not formatted, the dataloader solicits a subsystem identification. The SDU does not respond to thecommand 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 insufficientspace exists to contain an ORT, the transfer operation terminates. A file nameSDU_ORT.TAB is created on the ORT diskette. This file replaces any existing file withthe same name. An ORT header is written at the head of the file. The ORT formatversion written into the header is the latest version supported by the installedsoftware build. After transferring the header record, the ORT data is written to the fileuntil the whole data table is transferred. The file is then closed and a load completefunction is commanded. When an error is detected during the ORT download (i.e.,unable to create file, ARINC 615 transfer failure, etc.) the download process abortsand 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, ora 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 theCONFIG.LDR file into the ADL/PDL.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--12(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. Removethe diskette from the ADL/PDL. Disconnect the ADL/PDL from the SDU andinitiate PAST in the SDU.(2) Upload the ORT through the CMT(a) Make sure the PDL is connected to the SDU through the appropriate connectoron the interface cable, and the MCS system is logged off.(b) Insert an ORT diskette containing the ORT file SDU_ORT.TAB, plus theCONFIG.LDR file into the PDL.(c) Access the SDU data loader menu from the CMT by performing the following keyentries 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 CMTdisplays ADL or PDL CONNECTED. The data upload is complete. Remove thediskette from the ADL/PDL. Disconnect the PDL from the SDU and initiate PASTin the SDU.(3) Upload the ORT through the CMTI (Windows)(a) Make sure the PDL is connected to the SDU through the appropriate connectoron the interface cable, and the MCS system is logged off.(b) Insert an ORT diskette containing the ORT file SDU_ORT.TAB, plus theCONFIG.LDR file into the PDL.(c) Access the SDU data loader menu from the CMT by performing the followingfrom the CMTI main menu:•Select the ORT menu•Select the ORT Transfer menu•Select the PDL to SDU option.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--13(d) Make sure the status line indicates Data Transfer in Progress.(e) When the PDL diskette activity stops, the status line should indicate TransferComplete. Remove the diskette from the ADL/PDL. Disconnect the PDL from theSDU 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 onthe 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 filecreated by the ORTool as an Auto Mode,Boeing Mode,orB777 Mode Loader FileType.(3) Make sure the status line indicates Data Transfer in Progress.(4) When the PDL diskette activity stops, the status line should indicate TransferComplete. Remove the diskette from the ADL/PDL. Disconnect the PDL from theSDU and initiate PAST in the SDU.7. Circuit-Mode ServicesA. Circuit-Mode Voice(1) The SDU supports cockpit and cabin voice services (refer to SYSTEMDESCRIPTION for a description of cabin/cockpit communications) that use theINMARSAT aeronautical satellite system. Cockpit voice services use the equipmentcurrently found on the flight deck (i.e., headsets, call lamps, chime, chime reset,push-to-talk switches, and audio control panels and audio management systems) asshown 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 4services. These SDU interfaces support analog voice with in-band DTMF dialingand 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) purposeof carrying real-time voice signals using the defined codec standard.Circuit-mode data services can be used to support a variety of communicationapplications like interactive or bulk data communication, encrypted voice/datacommunication, and facsimile transmission.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--14Figure 2-1. Satellite Audio SystemRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--15(2) Sub-Band Signaling(a) Support of circuit-mode data services is achieved through the use of sub-bandsignaling, and/or primary-band signaling. The call setup sequence for acircuit-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 canbe invoked at some point during the call. Sub-band signaling circuit-mode data isimplemented using the data interface unit (DIU) technique, which is anontransparent design that uses sub-band C--channel capacity for end-to-endsignaling. 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 asecure voice coding unit.(3) Primary-Band Signaling(a) Primary-band circuit-mode data is implemented using the terminal interfacefunction (TIF) technique, which uses primary-band C--channel capacity forend-to-end signaling. The TIF is integrated within the SDU codec. Allcircuit-mode data activation and deactivation procedures relating to circuit-modedata operation are automatically performed within the TIF. The TIFencodes/decodes circuit-mode PC modem data and facsimile data using analgorithm.8. Packet-Data ServicesA. General(1) Data services are available in the form of a standard data interface that supportsData-2 and Data-3 as defined by INMARSAT. Data-3 complies with InternationalStandards Organization (ISO) standard 8208 for open systems interconnection.Data-3 permits the operator to connect to the MCS system any data terminalequipment (DTE) compatible with this international standard. The transmission rateavailable to the operator depends on the aircraft equipment, and in particular on theantenna gain. It also depends on the capabilities of the satellite serving that particularregion 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 arehandled by two basic types of data service. Small messages (up to 128 bytes) arehandled by one self-contained message that includes the information required to setup and clear the circuit as well as the data itself. This connectionless messagetraverses the communication link autonomously and quickly.(3) Longer messages must be divided into a string of shorter messages for which aconnection-oriented circuit is set up. When the connection is established, allsubsequent data packets carry abbreviated address and control information. Thissupplies more efficiency for longer messages and inquiry/response data dialogueswith no limit set on the length of individual messages.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--169. Dual SATCOM ConfigurationA. Overview(1) General(a) Dual SATCOM configuration is one where two SDUs work together in amaster/slave relationship. This configuration also uses dual antenna systems.(b) Dual SATCOM systems can be used to supply backup redundancy forcircuit-mode and packet-mode safety communications, or for additionalcircuit-mode channel capability, or both. Each system in a dual system has thecapability to function without the other if necessary (as a sole single system whilethe other has failed or is disabled), or to work with the other system as acoordinated pair. There are three distinctions made for dual systems regardingthe SDUs:(2) No. 1 versus No. 2(a) This is a static distinction as determined by the programmed state of the SDUsystem configuration pin. (No. 1 and No. 2 can also be referred to as left andright, respectively, on Boeing aircraft.)(3) Master versus Slave(a) This is a logical and potentially dynamic distinction. Because an aircraft can haveonly one ICAO address assigned to it, dual MCS systems operate with a singlemaster SDU and the other as slave SDU. Each SDU is capable of providing itsservices with no assistance from the other SDU (e.g., when the other SDU ispowered-down). Each SDU is capable of being the master or the slave. Thereare never two masters or two slaves (except during brief switching transients andcertain failure plus manual override conditions). The master does not depend onthe 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 Tpacket-mode channels for log-on and other satellite system management,Data--2, Data--3, and GES--specific data broadcast (GSDB) packet-mode dataservices, and circuit-mode call setups. The slave (which must be equipped withan HGA in order to be a true slave from the perspective of offering additionalchannel capacity) does not perform log-on or any packet-mode data function, butis only used to supply additional C-channels for circuit-mode services undercontrol of the master. The master controls all circuit-mode call setups,preemptions, and selective releases; normal ongoing slave system callmanagement (e.g., power control) and call termination are controlled by theslave SDU.(c) In a dual system made up of an HGA and an LGA, if the LGA-equipped SDU isthe master, it cannot use the HGA-equipped system as a slave. The LGA mastermust be capable of operation through its LGA and must log-on as a Class 1AES. 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.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--17(d) A system is said to be disabled when it is inhibited from making any RFtransmissions. This disabling can be because of a failure or being manuallyinhibited through the control interfaces. Any disabled SDU indicates this in bit 12of its label 276 status word. If a system is not disabled, it is enabled. When onesystem is disabled, the other is usually selected, i.e., the selected system isessentially a single system and cannot use any potential slave resources in thedisabled system. It is possible both systems can be manually disabled for specialpurposes like when maintenance or deicing personnel are in close proximity tothe antennas. The master controls the system functional capability indicators andindicates itself as the master to the MU, cabin packet data function (CPDF), andCTU. This is true even when both SDUs are disabled (there must still be adesignated master).(4) This versus Other(a) This is a relational distinction where this refers to any and all SDUs in dualsystems, and other refers to the companion SDU interfaced to this SDU ARINC429 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 twosystems are done by using the XTB between the two SDUs (one high-speed ARINC429 bus in each direction), and by the dual system select discrete I/O and dualsystem disable discrete input discretes, which are cross-wired between the twoSDUs. Figure 2-2 shows a classic wiring diagram.(2) The select and disable discretes are normally in a high-impedance state. The selectoutput supplies a low-impedance to ground when it is asserting, and the select anddisable inputs are pulled low to be asserted. An optional external switch can also besupplied to manually select one system while disabling the other. A switch normallyleaves both discretes open-circuited, enabling fully automatic control. The optionalswitch can additionally have the enhanced capability of simultaneously disabling bothsystems while selecting neither. Manual control is also supplied through the SCDUsfor cases where the optional external switch is not supplied.(3) The disable discrete is an input only. It is automatically asserted by the other SDUselect output when attempting to perform an aggressive handover of mastery; it canalso 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. Activationof this discrete by the crew indicates this system should be the sole master and itmust not attempt to use the other as a slave. If an SDU detects the other system hasfailed, it can activate its own select output, which disables the other system andtypically becomes the sole master.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--18Figure 2-2. Dual System Wiring DiagramC. System Reversion(1) General(a) The dual MCS system can change which SDU is master automatically ormanually. Automatic system reversion of handover of mastery from the currentmaster to the current slave is done through cooperative, aggressive, and specialhandovers.(2) Automatic System Reversion(a) Cooperative handover of mastery is performed through the XTB and does notmake use of the select/disable discretes. The current master continuallyassesses the potential service capabilities of each system, including the usage ofthe other’s resources as a slave for providing additional voice services. Sincedifferent aircraft owners/operators can value the individual assessed servicecapabilities differently, weighting factors are selected in the ORT to reflect therelative importance of the various capabilities. This flexibility allows allcapabilities to be compared equally, or for any one capability to outweigh all ofthe others combined, or any combination between these extremes. When thecurrent master determines the current slave should become the new master, thecurrent master indicates it is abdicating its mastery. The slave detects theabdication of the master and takes over as master.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--19(b) Aggressive handover of mastery (used when cooperation is impossible becauseof XTB failure, manual intervention, or other reasons) makes use of theselect/disable discretes for mastery handover. An SDU asserts its select output(connected to the Disable input of the other SDU) and commands Disable OtherSATCOM 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 hasreceived a Disable Other SATCOM command through the XTB, it immediatelyasserts its My Disable Is Asserted bit in its dual control/status word on its XTBoutput, and after being so disabled for 1 second or longer, it then inhibits RFtransmissions and asserts its This SDU Is Disabled bit in its dual control/statusword.(c) If the master SDU main processor resets itself, handover of mastery occurswhen 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 disablethe other system using an external select/disable switch or through the SCDUdisable other SATCOM line select key. This permits manual system reversion forspecial cases, like undetected failures. Some external select/disable switchesmay permit both systems to be disabled simultaneously for special casesinvolving close proximity to the SATCOM antennas of maintenance or deicingpersonnel.(b) The SCDU line select key makes use of the XTB as well as the select/disablediscretes to send the appropriate command to the other SDU, thus optimizing therobustness of this function.D. Antenna Configurations(1) A number of dual system antenna configurations can be assembled to addressvarious user requirements for availability and channel capability, containing variouscombinations of LGA--, HGA-- or IGA--equipped systems — i.e., HGA(IGA) +HGA(IGA), HGA(IGA) + LGA, or LGA + LGA. The IGA equipment can be usedinterchangeably (when airplane installation supports) with the HGA equipment. AnyHGA in a dual (or single) system can function as a logically distinct steered LGAwhen its gain drops below 7 dB. Also possible is one pseudo-dual system plus oneHGA system —i.e., (HGA+LGA) + HGA.(2) The basic configurations supported by the MCS dual system design are as given inTable 2-2.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--20Table 2-2. Basic Antenna ConfigurationsSDU No. 1 SDU No. 2 NotesHGA LGA Original ARINC 741 dual system architectureHGA HGA MD--11 and 777 dual standardLGA 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. Thisconfiguration is normally capable of providing five circuit-mode channels plus one(potentially) high-rate packet-mode data channel. It supplies single-point failuretolerance for low--rate packet-mode data services. Channel unit redundancy withinthe HGA system supplies a limited but very flexible degree of failure tolerance forcircuit-mode and high-rate packet-mode services.(5) Figure 2-5, Figure 2-6, and Figure 2-7 shows the three types of the HGA + HGAconfiguration. This configuration is normally capable of providing 10 circuit-modechannels plus one (potentially) high-rate packet-mode data channel. It suppliessingle-point failure tolerance for all grades of all services. Channel unit redundancywithin each half of the dual system supplies a limited but very flexible degree offailure tolerance for all grades of all services before more serious failures force ahandover of mastery.(6) Figure 2-8 shows the LGA + LGA configuration. This configuration is capable ofproviding only one low-rate packet-mode data channel, and supplies single-pointfailure 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 andfailure-tolerance capabilities as the HGA + HGA configuration, and adds thecapability of one low-rate packet-mode data channel in instances where both HGAsare unusable because of trying to point into keyholes. (The use of dissimilar dualHGAs, like those shown in Figure 2-7, helps to minimize the need for such aconfiguration.)RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--21Figure 2-3. HGA + LGA Configuration with Top-Mounted HGAFigure 2-4. HGA + LGA Configuration with Side-Mounted HGARELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--22Figure 2-5. HGA + HGA Configuration with Two Top-Mounted HGAsFigure 2-6. HGA + HGA Configuration with Two Side-Mounted HGAsRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--23Figure 2-7. HGA + HGA Configuration with One Side-Mounted HGA + One Top-MountedHGA (Dissimilar HGA)Figure 2-8. LGA + LGA ConfigurationRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--24Figure 2-9. (HGA + LGA) + HGA Configuration with Two Side-Mounted HGAsRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--25Figure 2-10. (HGA + LGA) + HGA Configuration with the LGA Paired withOne Side-Mounted HGARELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--26Figure 2-11. (HGA + LGA) + HGA Configuration with the LGA Paired withOne Top-Mounted HGARELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--27Figure 2-12. (HGA + LGA) + HGA Configuration with Two Top-Mounted HGAsE. Cockpit Voice Configurations and Functionality(1) System configuration pins TP13F and TP13J specify the physical wiring for thecodecs of each SDU to the possible interfaces -- a codec/channel can only beavailable to the cockpit if the wiring strap is set to Cockpit or Both (and not if thewiring is to Cabin or Neither).(2) An additional issue with dual systems is how to map the potentially available fourphysical SDU cockpit voice channels with the one or two (maximum) usable logicalcockpit channels controllable through the audio control panels (ACPs) and theSCDUs (i.e., as seen by the audio management system [AMS] user). Twoconfigurations are defined, which are identified by ORT item xlviii (Cockpit ChannelInterface Type for Dual): (1) interfacing each ACP/SCDU logical channel to onephysical channel on one SDU only (fixed),and(2)interfacinganACP/SCDUlogicalchannel to one physical channel on each of the two SDUs (shared). Note theinterfacing referred to is conceptual and not necessarily physical -- i.e., for shared,the physical wiring can be literally paralleled, or it can be simple point-to-point, withsome form of signal splitting/combining or paralleling being performed within the AMSitself. The system configuration straps for codec wiring let the SDU determine thephysical channels which are candidate channels for each logical channel.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 2--2810. ACARS/Aircraft Flight Information System (AFIS) Peripheral FunctionA. General(1) The ACARS/AFIS peripheral function lets the SATCOM SDU act like any otherACARS/AFIS peripheral to receive or send blocks of data from/to ground terminalson the ARINC/SITA network, e.g., uplink ORTs, and downlink ORTs, call event logs,data event logs, system management event logs, and failure logs. This functionalityintegrates with the satellite subnetwork transfer capability. The requirements aretaken from ARINC 618 for the air-to-ground link and ARINC 620 for the data linkservice provider requirements.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--1SECTION 3CABIN/COCKPIT COMMUNICATIONS1. Cabin CommunicationsA. General(1) Cabin communications are done with both digitally connected phones and analogconnected phones (see Figure 3-1). The user interface with digitally connectedphones is handled by the cabin communications system (CCS). The SDU hasprovisions 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 groundstations, supply cabin services like telephone, facsimile, and PC data interfaces. TheCCS 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 digitallyconnected 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, calltransfer, call conferencing, and generating pacifier messages (like please hold, yourcall is being processed).(3) The CTU supplies the interface between the digitally connected phones and theSDU. The digital phones (handsets) are primarily supplied for passenger use andmay be located throughout the aircraft. The digital handsets interface indirectly to thesatellite communications equipment and they are controlled by the CCS. Each digitalhandset supplies all the normal functions of a domestic telephone. Some handsettypes are battery powered and can be used anywhere in the aircraft. When not inuse, handsets are stowed in a holster with a built-in battery charger for recharging thebatteries.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--2C. Analog Audio Channels(1) General(a) The SDU has provisions to support up to two analog channels. Each audiochannel 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 CTUor handset has analog trunk lines and in-line DTMF signaling. The SDU cansupport both analog handsets being connected simultaneously.(c) Two in-use discrete outputs are supplied for analog channels 1 and 2. Thesediscretes are asserted (i.e., turn on the call lamps) while the voice codecassociated 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 parallelaircraft-suitable handsets. The interface presented to the SDU must emulate asingle handset. The analog handsets, which can be located in the cabin orcockpit areas, supply only APC priority (priority 4) level service. This does notpreclude their use for other communications, but the SDU assigns an APCpriority to the call.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--3/(3--4 blank)Figure 3--1. Audio InterfacesRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--5(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 handsetmay be placed in parallel with the other analog phone. Buffering and sidetonearrangements are supplied by the analog connected phone, not by theSATCOM equipment.•If the voice codec is reserved by a headset user, is dedicated to a headset, oris failed, the analog phone user hears silence.•If the SDU is not logging-on, logged-on, or in the idle (standby) state, theanalog 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 SDUperforms 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 anew voice call, or the AES class is currently 1 or 4, the SDU performs action5.•Or else the SDU performs action 6 and the respective analog phone channelis deemed usable for placing a call.(b) If the system condition, as determined by the SDU, changes from usable (action6) 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 newcondition. An analog channel does not change from unusable to usable while theanalog phone is off-hook unless there is a call termination on that channel.Table 3-1. SDU to WH-10 Handset ActionsAction1Play message 10 as defined in Table 3-5 outgoing calls have been disallowed) followed byan interrupted dial tone.2Play message 1 as defined in Table 3-5 (equipment failure) followed by an interrupted dialtone.3Play message 2 as defined in Table 3-5 (attempting satellite access) followed by aninterrupted dial tone.4Play message 3 as defined in Table 3-5 (log-on disabled) followed by an interrupted dialtone.5Play message 4 as defined in Table 3-5 (channel not available) followed by an interrupteddial tone.6Play the dial tone.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--6(c) The commands given in Table 3-2 are executable from the analog WH--10handset. The inter-key push time-out is 15 seconds. After this time, a # sign isautomatically appended to the end of the keyed sequence by the SDU, and thecommand given by the user is parsed and executed. Commands shown in thetable as not being terminated by a # sign are parsed and executed as soon asthe valid key sequence has been entered. An invalid sequence only generatesvoicemessage18(Commandrejected)whena#isappended, either by the useror 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 userkeying a command start with one second of silence to allow the user enoughtime to bring the handset to their ear. During the playing of any codec-generatedmessages and pacifiers, receipt of the # key immediately mutes the codec,aborting the current message sequence. The voice codec plays the appropriatedial tone (normal or interrupted) as specified in Table 3-2.(e) An inactivity check is implemented so the SDU considers an off-hook channel tobe in the on-hook state if no call has been in progress on that channel and noDTMF digits have been received for at least 120 seconds, except whereindicated in Table 3-2. A WH--10 handset in this state must have its hookswitchcycled (i.e., go on-hook, then off-hook) to signal the off-hook state to the SDU.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--7Table 3-2. Global-Wulfsberg Flitephone WH-10 CommandsCommand Sequence Command Descriptiondddd...# 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 leadingzeros).*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 9are 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 memorylocations assigned to channel 2). However, if ORT item xxvi is set to FALSE, then modifying memorylocations 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...) tobe 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 beendisallowed) are played; otherwise, the entered data is checked. A valid commandcauses message 17 (command accepted) to be played and the number stored. Aninvalid command causes message 18 (command rejected) to be played.**2# This announce phone number memory command causes the phone numbersstored 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 isentered through the WH--10 handset, the inactivity check is disabled until the nextkey-push or until the next on-hook/off-hook transition.**2m This announce phone number memory command causes the phone number inmemory location m to be read out using message 19 (the phone number stored inmemory ...) or message 5 (phone number memory ... is empty.). If m is notbetween 1 and 9, then message 18 (command rejected) is played instead. Thedigit 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 beendisallowed/outgoing calls have been disallowed) if an attempt is made to place a call. For all the followingcall barring commands, an invalid security code (cccc) causes the command to be rejected and message18 (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 alloutgoing calls.**31cccc This command sets the call barring level (ORT item xxiv) to 1, which disallows allmanual dialing of full-length phone numbers (6 to 18 digits starting with 00). Nomemory locations can be updated using the store phone number memorycommand.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--8Table 3-2. Global-Wulfsberg Flitephone WH-10 Commands (cont)Command Sequence Command Description**32cccc This command sets the call barring level (ORT item xxiv) to 2, which disallows alloutgoing calls, both manual and stored number. No memory locations can beupdated 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 notthe same as the second four n’s, in which case message 18 (command rejected) isplayed.**4ggg# This command causes ggg to be the GES ID used in the access request signal unitfor 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 followingcommands 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 UserCommanded Log-on. If already logged-on, the SDU logs off (refer to SYSTEMOPERATION). If logging-on, the SDU terminates the logging on procedure. If thecommand is valid, message 17 (command accepted) is played immediately withoutwaiting 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 AutomaticLog-on. If the SDU is in the standby state, the SDU initiates the automatic log-onprocedure (refer to SYSTEM OPERATION). If the SDU is in the constrained log-onmode, a handover stimulus is generated to initiate automatic satellite/GESselection. If the command is valid, message 17 (command accepted) is playedimmediately without waiting for the log-on to be achieved. If the SDU is already inthe automatic mode, message 18 (command rejected) is played.**52ggg#**52gggsss#These commands set the SDU to the constrained log-on mode for selection of aspecified GES. The log-on policy (ORT item i) is set to Manual Log-on.IftheSDUis not logged-on to the GES ggg (or gggsss as appropriate), the SDU attempts alog-on to that GES alone. Any other number of digits cause message 18(command rejected) to be played. If the specified GES does exist in the systemtable, then the command is rejected. If the command is valid, message 17(command accepted) is played immediately without waiting for the log-on to beachieved. If the SDU is already constrained to GES ggg (or gggsss asappropriate), then message 18 (command rejected) is played.**59 This log-on status command causes the SDU log-on status to be announced usingmessage 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 announcedas oh.If any of the following GES preference commands are determined to be invalid, the SDU plays messages18 (command rejected); otherwise, if a specific message is not specified, then message 17 (commandaccepted) is played. If ORT item xxiii is set to disable the APHONE system management commands, thenext three commands (the preference changing commands) are rejected; i.e., the SDU responds to thecommands 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.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--9Table 3-2. Global-Wulfsberg Flitephone WH-10 Commands (cont)Command Sequence Command Description**61gggp#**61gggsssp#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 orseven digits following the **61... and preceding the # sign. Any other number ofdigits is interpreted to be an invalid command. If no GES listed in the system tablematches the one specified in the command, the command is invalid and the user isso informed through message 18 (command rejected).**62ggg#**62gggsss#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 levelset to 9. The SDU accepts either three or six digits following the 62... andpreceding the # sign. Any other number of digits is interpreted to be an invalidcommand. If no GES listed in the system table matches the one specified in thecommand, 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 asequence of message 22s (The preference level of GES ID...). If this command isentered through the WH--10 handset, the inactivity check is disabled until the nextkey-push, or until the next on-hook/off-hook transition.**69ggg#**69gggsss#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 GESID...). The SDU accepts either three or six digits following the **69... and precedingthe # sign. Any other number of digits is interpreted to be an invalid command. If noGES listed in the ORT (item iii) matches the one specified in the command, thecommand is invalid and the user is so informed through message 18 (commandrejected).If any of the following incoming call management commands are rejected, the SDU plays messages 18(command rejected); otherwise, if a specific message is not specified, then message 17 (commandaccepted) is played. If ORT item xxiii is set to disable the APHONE system management commands, thefollowing commands are rejected; i.e., the SDU responds to the commands with message 18 (commandrejected). The four DDI CTid commands allow ddd to be up to three decimal digits (including leading zeros,e.g., 02), validating the number to be within the range of 0 to 999. The incoming call managementcommands are specified as follows.**70# This command sets ORT item xlv for APHONE Channel 1 to the default value; i.e.,no CTid assigned.**70ddd# This command sets ORT item xlv for APHONE Channel 1 to ddd, Nonexclusive,unless the configuration straps indicate Channel 1 is not wired for APHONE, or dddis already assigned as the CTid for Channel 2, or (in a dual system) ddd is alreadyassigned to one of the other SDU APHONE channels, in which case, the commandis rejected. Additionally, if ORT item xiii indicates ground-to-air Priority 4 calls aredisallowed, it is adjusted to specify routing to APHONE.**71ddd# This command sets ORT item xlv for APHONE Channel 1 to ddd, Exclusive, unlessthe configuration straps indicate Channel 1 is not wired for APHONE, or ddd isalready assigned as the CTid for Channel 2, or (in a dual system) ddd is alreadyassigned to one of the other SDU APHONE channels, in which case, the commandis rejected. Additionally, if ORT item xiii indicates ground-to-air Priority 4 calls aredisallowed, it is adjusted to specify routing to APHONE.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--10Table 3-2. Global-Wulfsberg Flitephone WH-10 Commands (cont)Command Sequence 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 dddis already assigned as the CTid for Channel 1, or (in a dual system) ddd is alreadyassigned to one of the other SDU APHONE channels, in which case, the commandis rejected. Additionally, if ORT item xiii indicates ground-to-air Priority 4 calls aredisallowed, it is adjusted to specify routing to APHONE.**73ddd# This command sets ORT item xlv for APHONE Channel 2 to ddd, Exclusive, unlessthe configuration straps indicate Channel 2 is not wired for APHONE, or ddd isalready assigned as the CTid for Channel 1, or (in a dual system) ddd is alreadyassigned to one of the other SDU APHONE channels, in which case, the commandis rejected. Additionally, if ORT item xiii indicates ground-to-air Priority 4 calls aredisallowed, it is adjusted to specify routing to APHONE.**740# This command sets ORT item xiii to disallowed and causes message 33 to beplayed with the destination announced as disallowed.**741# This command sets ORT item xiii to APHONE and causes message 33 to beplayed with the destination announced as APHONE, unless no codec channel iswired for APHONE (as defined by the configuration straps), in which case, thecommand is rejected and the ORT item is set to Disallowed.**742# This command sets ORT item xiii to DPHONE and causes message 33 to beplayed with the destination announced as DPHONE, unless no codec channel iswired for CCS (as defined by the configuration straps), in which case, thecommand 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 playedwith the destination announced as headset, unless no codec channel is wired forAMS (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 andcauses message 34 to be played to announce such calls as disallowed, unlessthe 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 andcauses message 34 to be played to announce such calls as allowed, unless theSDU 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 forchannels 1 and 2 using message 31, if no ID is assigned, and message 32 if an IDis assigned, where the type of ID assignment is announced as exclusive ornonexclusive.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--11Table 3-2. Global-Wulfsberg Flitephone WH-10 Commands (cont)Command Sequence Command DescriptionLegend: cSecurity code digit (0 thru 9)dDecimal digit (0 thru 9)gGES ID octal digit, where ggg is in range (000 thru 377)mMemory location (1 thru 9)nNew security code digit (0 thru 9)pGES preference level (0 thru 9), where 1 is the least preferred and9 is the most preferred, and 0 indicates never to be selected forautomatic log-onsSatellite 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 usedby 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 bespecified, with the first two digits not 00. The 00 digits are used as thecalled–party address.•Long number manual dialing (00dddd...#). Between seven and 18 digits canbe specified including the leading 00. The 00 digits are used as thecalled–party address.•Last call redial (*0). The last phone number called by an analog phone useron a channel is used as the called–party address. If the phone number storedin memory location 0 (i.e., last number called location) is not defined (lengthfield set to zero), then message 5 (phone number memory ... is empty.) isplayed. Otherwise, the phone number is used as the called–party address.•Stored phone dialing (*m). Parameter m specifies a memory location between1 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 ... isempty.) is played. Otherwise, the phone number is used as the called–partyaddress.(4) Analog Private Branch Exchange (APBX) Interface(a) General1The APBX/SATCOM avionics interface protocol is based on the bidirectionalDTMF tones being signaled in-band. In the APBX-to-SATCOM direction, theDTMF digits are assigned to the on- and off-hook transitions as specified inTable 3-3, and are valid only from the APBX handset. All other DTMF digitsare common to both the WH--10 and APBX interfaces.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--122Taking an APBX handset off-hook results in the same decisions as specifiedfor the WH--10 handset. However, the SDU to APBX off--hook actions arespecified in Table 3-4, where the DTMF tone sequence <DTMF--C>,<DTMF--n> (n is 0, 1, 2, or 4) sent to the APBX handset indicates theSATCOM channel status:•An outgoing call cannot be supported (n = 1, 2, or 4) or•An outgoing call can be attempted (n = 0).3If the channel status indicates a call can be attempted, the SDU accepts anycommand determined to be valid from an APBX interface, including theon-hook DTMF tone. If the channel status indicates a call can not beattempted, the APBX handset is expected to send the on-hook DTMF tone.Otherwise, the SDU still accepts any command determined to be valid froman APBX interface; though the checked B-party address transfer commandis guaranteed to produce a call setup failure. Subsequent to call setupcommands sent to the SDU, call setup progress, failure, and terminationDTMF tone sequences are sent to the APBX handset.4The SDU considers an off-hook channel to be in the on-hook state if no callhas been in progress on that channel and no DTMF signals have beenreceived for at least 120 seconds. A channel in the on hook state must issueanother DTMF off-hook signal to enable the reentry into the off-hook state.(b) Checked Credit Card Data Transfer Command1The *2284*c*ddd# command, if valid, loads the transferred three-digit valueinto the SDU calling terminal ID buffer. This data is used in place of thedefault 000 in the calling terminal field of the call information service addressinitial signal unit (ISU) (S5) for any outgoing call setups on this channel untilthe next APBX on-hook is received. The command is accepted only if themodulo 10 sum of all the decimal digits in the command, including 2284, thethree-digit calling terminal ID, and the check digit c is zero.(c) Checked B-Party Address Transfer Command1The *2262*cdddd....# command, if valid, initiates a call setup request to theGES using the transferred digits dddd... as the B-party address and anytrack 2 credit card data stored since the previous on-hook transition on thischannel. The command is only accepted if the modulo 10 sum of all decimaldigits in the command, including 2262 and the check digit c is zero. A validcommand causes the SDU to send the DTMF sequence <DTMF--C>,<DTMF--8> to the APBX handset. An invalid command causes the SDU tosend the DTMF sequence <DTMF--C>, <DTMF--9> to the APBX handset.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--13Table 3-3. Assignment of DTMF Digits in the APBX InterfaceDTMF Digit Low (Hz) High (Hz) Meaning To/From SDU1697 1209 1Both2697 1336 2Both3697 1477 3Both4770 1209 4Both5770 1336 5Both6770 1477 6Both7852 1209 7Both8852 1336 8Both9852 1477 9Both0941 1336 0Both*941 1209 */STX To#941 1477 #/ETX ToA697 1633 FS/Answer BothB770 1633 Off--Hook ToC852 1633 Status FromD941 1633 On--Hook ToNOTE: STX (start sentinel), ETX (end sentinel), and FS (frame separator) are used in the transfer of ISO 7813 track 2data from the APBX to the SDU.Table 3-4. SDU to APBX Off-Hook ActionsAction Description1Play <DTMF--C>, <DTMF--2> followed by silence (idle).2Play <DTMF--C>, <DTMF--1> followed by silence (failure).3Play <DTMF--C>, <DTMF--4> followed by silence (accessing).4Play <DTMF--C>, <DTMF--2> followed by silence (idle).5Play <DTMF--C>, <DTMF--4> followed by silence (accessing).6Play <DTMF--C>, <DTMF--0> followed by silence (available).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--142. Cockpit CommunicationsA. General(1) The SDU codecs support headset interfaces for cockpit use only. These interfacesincorporate 600-ohm, 4-wire, off-hook/on-hook signaling and dialing through thecombination of a control and display unit (either SCDU or MCDU), and (at the user’soption) PTT, mic-on, or place/end call switches. If used, when the PTT button ispushed, the microphone audio signal is sent to the selected voice channel; activationof one of the discretes is signalled to the SDU. Also, an off-hook signal can be sent tothe SDU through the SCDU. An audible chime and call lamps announce aground-to-air call.(2) The cockpit headsets interface with the codecs in the SDU through an audiomanagement unit (AMU), which is also connected to other aircraft radios. The ACPassociated with the AMU can be capable of selecting either a single or dual voicechannels for the MCS system. When single-channel AMUs are installed, voicechannel 1 is wired to AMU No. 1 and voice channel 2 is wired to AMU No. 2. Thispermits operation of two independent channels. When dual-channel AMUs areinstalled, voice channels No. 1 and No. 2 are wired in parallel to each AMU, enablingtwo voice channels to be shared by the cockpit users.(3) Two functionally identical voice codec modules (VCM) are installed in the SDU anddesignated Codec A and Codec B.(4) Associated with the SATCOM channels are SCDU pages, call lamps, channelselection switches, a chime, and a chime reset. The SDU hookswitch signaling canbe supplied:•When the ACP SATCOM channel select switch is activated•When a PTT switch is activated•When signaling through the SCDU, where the SDU hookswitch signaling discreteis inactive.(5) Once off-hook, microphone audio is supplied to the selected SATCOM voice channeland the appropriate signaling is exchanged for call lamp and chime reset.Conversely, once on-hook, microphone audio is removed from the selected SATCOMvoice channel and the call lamp is turned off.B. Headset Off-Hook Signaling(1) The headset is capable of going off-hook (to connect the call and to acknowledge thecall signaling) if the cockpit voice call light output has transitioned for either theflashing or steady light activation, at which time:•If the latched ACP hookswitch signaling is strapped, the headset is consideredoff-hook whenever the cockpit voice mic-on input is activated (connected toground).•If the switched PTT hookswitch signaling is strapped, the headset is consideredoff-hook whenever the cockpit voice mic-on input is activated for the first time afterthe call light activation for an incoming call, or when the place/end call input isactivated to initiate an outgoing call.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--15(2) If ORT item xliii is enabled, the headset is capable of going off-hook when ANSWERCALL is selected on the SATCOM main menu page (TESTING/FAULT ISOLATION)after the call light activation and irrespective of hookswitch signaling.C. Headset On-Hook Signaling(1) If latched ACP hookswitch signaling is strapped, the headset is placed on-hook whenan open is present on the cockpit voice mic-on input. Regardless of the hookswitchsignaling, the cockpit voice place/end call 1 and 2 discrete inputs place the headsetinterface on-hook for cockpit audio channels 1 and 2, respectively, when a call clearevent occurs. If ORT item xliii is enabled, the selection of END CALL or REJECT onthe SATCOM main menu page (TESTING/FAULT ISOLATION) places the headsetinterface on-hook. Placing the headset on-hook results in normal call termination.D. Voice Codec Module Audio Switching(1) Headsets and analog connected phones interface to the SDU through the VCMs.Using a switch internal to the modules, each VCM can be connected to one of thecabin audio interfaces, or to one of the cockpit audio interfaces (or to both). EachVCM can be switched between either of its audio interfaces as follows:•CodecAcanbeusedinconjunctionwitheithercabinaudioNo.1(WH--10orAPBX) or cockpit audio No. 1•CodecBcanbeusedinconjunctionwitheithercabinaudioNo.2(WH--10orAPBX) or cockpit audio No. 2.E. Voice Codec Module Sidetone(1) Sidetone is supplied by each VCM. The sidetone level is adjustable for the cockpitaudio, and is set to off for cabin audio. The adjustment range for cockpit sidetone isfrom 0 dB below the receive audio to off, with the default value set to 14.1 dB belowthe receive audio level. This setting is stored in nonvolatile memory within the SDU.F. Voice Interface Module Stored Audio Messages(1) The VIMs are capable of playing standard telephony supervisory lone signals, DTMFtones, and voice messages to the headset and analog phone users. These pacifiersare only sent to the analog interfaces:•Headset•WH--10 handsets•APBX handsets.(2) Stored audio messages are summarized in Table 3-5.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--16Table 3-5. Stored Audio MessagesMessage No. Message1Sorry, equipment failure, please refer to the user guide.2Sorry, attempting satellite access, please try later.3Sorry, log-on disabled, please refer to the user guide.4Sorry, no channel available, please try later.5Phone number memory <one> is empty.6Sorry, your call can no longer be sustained, please try later.7Sorry, your call has been preempted, please try later.8Sorry, connection failure, please try later.9Sorry, dialed calls have been disallowed, please refer to the user guide.10 Sorry, outgoing calls have been disallowed, please refer to the user guide.11 Sorry, number unobtainable.12 Sorry, number busy, please try later.13 Sorry, network congestion, please try later.14 Sorry, credit card not honored at the ground station.15 Sorry, access unauthorized.16 Please wait, connecting your call.17 Command accepted.18 Command rejected.19 The phone stored in memory <one> is <oh> <oh> <one>...20 The SATCOM is in <standby> |<auto log-on| <constrained log-on> mode.21 Logged on to GES ID <one> <oh> <three>.22 The preference level of GES ID <three> <oh> <two> on satellite <oh> <oh> <three> is<six>.23 Equipment failure, equipment failure.24 No channel available, no channel available.25 Your call can no longer be sustained.26 Your call has been preempted.27 Connection failure, connection failure.28 Number unobtainable, number unobtainable.29 Number busy, number busy.30 Network congestion, network congestion.31 Channel <one> terminal ID is not assigned.32 Channel <two> terminal ID is <oh> <one> <three> <nonexclusive>.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--17Table 3-5. Stored Audio Messages (cont)Message No. Message33 Ground-to-air public calls destination set to <disallowed>.34 Ground-to-air circuit mode data calls are <allowed>.G. Voice Interface Module Dedication(1) Each voice interface module (VIM) has the property of dedication, which is differentfrom the codec wiring. This property is of value on aircraft that have both headsetand cabin (analog and digital) interface wiring, where contention for codec use canarise. Each VIM dedication is set to cabin, headset, or automatic through ORT itemvi.(2) A VIM with its dedication set to automatic can be allocated to a headset call or acabin call, and is allocated on a first-come, first-served basis. A VIM can bereallocated to a headset call of priority 1, 2, or 3 through the preemption mechanism.A VIM with its dedication set to cabin is dedicated to its cabin (WH--10 or APBX)interface.(3) A VIM with its dedication set to headset is unusable by the cabin interface. A VIM canbe reallocated to a different headset call of priority 1, 2, or 3 through the preemptionmechanism. ORT item vii (Appendix C) specifies whether a modem and HPA powershould be reserved for a VIM dedicated to headset. This lets the pilot reserve onechannel for cockpit use only.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 3--18Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
  SYSTEM DESCRIPTION, INSTALLATION AND MAINTENANCE MANUAL MCS-4000/7000 TEMPORARY REVISION NO. 23-1   23-20-27  Page 2 of 630 Oct  2009  © Honeywell International Inc. Do not copy without express permission of Honeywell. INSERT PAGE 2 OF 6 FACING PAGE 4-1. Reason:  To add cooling information and to update applicable equipment and figure references. Steps 1.A.(1), 3.A.(1), and 3.A.(2) are changed as follows:  1. Overview A. General (1)  This section contains information on how and where to mount each component of the MCS system. For new installations, plan the installation in three stages. First, determine the location of the LRUs in the aircraft. Next, determine the length of RF and electrical interconnections for selected locations and finally, determine how the LRUs are to be cooled in regards to the placement of the LRUs. 3.  Mechanical Installation Design A.  LRU Mechanical Installation (1)  The SDU and HPA are installed in mounting racks (ARINC 600) typically in the equipment bay of the aircraft. For a SATCOM installation, the primary installation dependent parameter is the RF coax cable loss requirements identified in Table 4-1 and cooling requirements identified in Section E and Table 4-2 of this document. To make sure these requirements are met, some installations require the HPA(s) be installed in close proximity to the antenna subsystem components. Refer to the aircraft installation drawings for the location of the SATCOM equipment. For new installations, refer to Table 4-1 to determine the location of the SATCOM equipment to make sure the cable loss requirements are met as well as the cooling specifications in Section E are met. (2)  Mechanical installation data for the SDU, HPA, HSDU, and RFUIA are shown in Figure 4-2 thru Figure 4-5. RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--1SECTION 4MECHANICAL INSTALLATION1. OverviewA. General(1) This section contains information on how and where to mount each component of theMCS system. For new installations, plan the installation in two stages. First,determine the location of the LRUs in the aircraft. Next, determine the length of RFand electrical interconnections for selected locations.2. Equipment and MaterialsA. General(1) Refer to SYSTEM DESCRIPTION for mounting tray and mating connectorinformation. For all other components, refer to the applicable Outline and InstallationDiagram in this section.(2) No additional special equipment or materials, other than those commonly used in theshop, are required to install the units in existing trays and clamps, and to adjust thesystem. Do not over tighten mounting screws. Where torque values are not given, itis acceptable to finger tighten the mounting screws.3. Mechanical Installation DesignA. LRU Mechanical Installation(1) The SDU and HPA are installed in mounting racks (ARINC 600) typically in theequipment bay of the aircraft. For a SATCOM installation, the primary installationdependent parameter is the RF coax cable loss requirements identified in Table 4-1.To make sure these requirements are met, some installations require the HPA(s) beinstalled in close proximity to the antenna subsystem components. Refer to theaircraft installation drawings for the location of the SATCOM equipment For newinstallations, refer to Table 4-1 to determine the location of the SATCOM equipmentto make sure the cable loss requirements are met.(2) Mechanical installation data for the SDU, HPA (40 Watt), HPA (20 Watt), IGA ,D/LNA, and RFUIA are shown in Figure 4-2 thru Figure 4-7.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308SeeTR
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--2CAUTION: BEFORE AN LRU IS INSTALLED, PULL THE CIRCUIT BREAKERS THATSUPPLY POWER TO THE LRU TO REMOVE POWER.CAUTION: MOISTURE AND DIRT CAUSE DAMAGE TO LRUs.CAUTION: LRU FAILURE RATES INCREASE WITH A RISE IN TEMPERATURE.INSTALL THE LRUsWITH CLEARANCE; LET THE AIR FLOW ON TOPAND BOTTOM OF LRUsTO PREVENT OVERHEATING.CAUTION: MAKE SURE THAT THE LATEST ORT DATABASE SOFTWARE ISINSTALLED IN THE SDU BEFORE PERFORMING SYSTEMOPERATIONS.NOTE: Honeywell/Racal recommend the MCS LRUs be installed so their installationis level (zero degrees) to the horizontal plane of the aircraft. Compliance withRTCA/DO--160C has been demonstrated with this orientation.NOTE: Ambient temperature at the LRU location must be less than 40 °C (104 °F)during operation for best reliability.B. Installation Dependent Considerations(1) Refer to the SYSTEM DESCRIPTION section for the installation dependentconsiderations for the SDU.C. Owner Requirements Table (ORT) Uploading(1) When the SDU is changed, the ORT needs to be uploaded before normal operationcan begin. Refer to the SYSTEM OPERATION section for the ORT uploadprocedures.D. Cable Loss Requirements(1) The attenuation and voltage standing wave ratio (VSWR) of coaxial cable used in theMCS system must meet the requirements specified in Table 4-1 to make sure thesystem operates correctly. Figure 4-1 shows the specific cable attenuations for theSATCOM equipment. All specified cable attenuations include connector losses, whichare assumed to be 0.1 dB each. Honeywell recommends each cable assembly besweep tested for loss and VSWR.Figure 4-1. Cable AttenuationsRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308SeeTR
  SYSTEM DESCRIPTION, INSTALLATION AND MAINTENANCE MANUAL MCS-4000/7000 TEMPORARY REVISION NO. 23-1   23-20-27  Page 3 of 630 Oct  2009  © Honeywell International Inc. Do not copy without express permission of Honeywell. INSERT PAGE 3 OF 6 AND PAGE 4 OF 6 FACING PAGE 4-2. Reason:  To update the third CAUTION and the first NOTE and to delete the second NOTE before Paragraph 3.B., and to change Figure 4-1. The third CAUTION and the NOTES are updated and deleted, and Figure 4-1 is changed as follows:  CAUTION:  BEFORE AN LRU IS INSTALLED, PULL THE CIRCUIT BREAKERS THAT SUPPLY POWER TO THE LRU TO REMOVE POWER. CAUTION:  MOISTURE AND DIRT CAUSE DAMAGE TO LRUs. CAUTION:  LRU FAILURE RATES INCREASE WITH A RISE IN OPERATIONAL TEMPERATURE BEYOND LRU-SPECIFIED COOLING LEVELS. INSTALL THE LRUs WITH CLEARANCE. LET THE AIR FLOW ON TOP AND BOTTOM OF LRUs TO PREVENT OVERHEATING. CAUTION:  MAKE SURE THAT THE LATEST ORT DATABASE SOFTWARE IS INSTALLED IN THE SDU BEFORE PERFORMING SYSTEM OPERATIONS. NOTE:  Honeywell/Thales recommends the MCS LRUs be installed so their installation is level (zero degrees) to the horizontal plane of the aircraft. Compliance with RTCA/DO-160D has been demonstrated with this orientation.  B.  Installation Dependent Considerations   RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
  SYSTEM DESCRIPTION, INSTALLATION AND MAINTENANCE MANUAL MCS-4000/7000 TEMPORARY REVISION NO. 23-1   23-20-27  Page 4 of 630 Oct  2009  © Honeywell International Inc. Do not copy without express permission of Honeywell.   Figure 4-1.  Cable Attenuations RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
  SYSTEM DESCRIPTION, INSTALLATION AND MAINTENANCE MANUAL MCS-4000/7000 TEMPORARY REVISION NO. 23-1   23-20-27  Page 5 of 630 Oct  2009  © Honeywell International Inc. Do not copy without express permission of Honeywell. INSERT PAGE 5 OF 6 AND PAGE 6 OF 6 FACING PAGE 4-3. Reason:  To update Table 4-1, to update the cooling requirements in Step 3.E., and to update Table 4-2. Table 4-1, Step 3.E., and Table 4-2 are changed as follows: Table 4-1.  Cable Loss Requirements Cable Assembly  Location  Minimum Loss  Maximum Loss  Maximum VSWR TX Cable  Between SDU, HSU, and HPA 1 dB  20 dB  2.0 RX Cable  Between Diplexer/LNA and SDU 6 dB  25 dB  2.0 TX Cable  Between HPA and Diplexer/LNA N/A 1.4 dB 1. 1.3 RX Cable  Between Diplexer/LNA and Antenna N/A 0.3 dB 1.3 NOTES: 1. In installations that use a high power relay (HPR), the HPR loss must be included. The maximum Tx cable loss between the HGA and the antenna must not exceed 2.5 dB. 2. N/A = Not applicable. E. Cooling Requirements (1)  The cooling requirements for the MCS avionics are specified in Table 4-2 as follows: •  Power dissipation is in Watts •  Mass airflow is in pounds per hour •  CF/M is cubic feet per minute at sea level and 104°F (40°C) •  Pressure drop is in inches of water. (2)  If the LRUs are to be operated above an altitude where the flow rates defined in Table 4-2 cannot be met, then the units must be installed in a pressurized compartment that provides a means to meet the Table 4-2 cooling requirements. (3)  The temperature of the cooling air for the LRUs must not exceed 104°F (40°C). RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
  SYSTEM DESCRIPTION, INSTALLATION AND MAINTENANCE MANUAL MCS-4000/7000 TEMPORARY REVISION NO. 23-1   23-20-27  Page 6 of 630 Oct  2009  © Honeywell International Inc. Do not copy without express permission of Honeywell. Table 4-2.  Cooling Requirements   Power Dissipation  Mass Airflow  CF/M  Pressure Drop LRU Max. Nom. Max. Min. Max. Min.  Max.  Min. SDU  150 105 96  (44 kg/hr) 73  (33 kg/hr) 23 18  0.25  (6.35 mm) 0.15  (3.81 mm) HPA (60W) 425 250 176  (80 kg/hr) 121  (55 kg/hr) 42 29  0.25  (6.35 mm) 0.2  (5.0 mm) HSU 100 55 63  (29 kg/hr) 49  (22 kg/hr) 15 11  0.25  (6.35 mm) 0.15  (3.81 mm) NOTE:   The SDU draws an additional 20 W during the first 10 minutes (maximum) of operation at 25°C because of the oven controlled crystal oscillator (OCXO). The OCXO continuously dissipates this additional 20 W at −55°C.  RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--3Table 4-1. Cable Loss RequirementsCable Assembly Location Minimum Loss Maximum Loss Maximum VSWRTX Cable Between SDU andHPA19 dB 25 dB1.TBDRX Cable BetweenDiplexer/LNA andSDU6dB 25 dB2.TBDTX Cable Between HPA andDiplexer/LNA1.4 dB TBDRF Cable BetweenDiplexer/LNA andAntenna0.3 dB TBDNOTES:1. In installations that use a combiner, the combiner loss must be included.2. In installations that use a high power relay (HPR), the HPR loss must be included. The maximum Tx cable lossbetween the HGA and the antenna must not exceed 2.5 dB.E. Cooling Requirements(1) The cooling requirements for the MCS avionics are specified in Table 4-2 as follows:•PowerdissipationisinWatts•Mass airflow is in pounds per hour•CF/M is cubic feet per minute at sea level and 40 °C(104°F)•Pressure drop is in inches of water.(2) In most cases, a cooling system that meets the sea level requirements also meetsthe cooling requirements at --55 °C(--67°F) and 70,000 feet.Table 4-2. Cooling RequirementsPowerDissipation Mass Airflow CF/M Pressure DropLRU Max. Nom. Max. Min. Max. Min. Max. Min.SDU 198 105 96 (44 kg/hr) 73 (33 kg/hr) 23 18 0.25(6.35 mm)0.15(3.81 mm)HPA(40W)362 300 176 (80 kg/hr) 121 (44 kg/hr) 42 29 0.25(6.35 mm)0.15(3.81 mm)HPA(20W)180 150 96 (44 kg/hr) 73 (33 kg/hr) 23 18 0.3(7.62 mm)0.2(5.08 mm)NOTE: The SDU draws an additional 20 W during the first 10 minutes (maximum) of operation at 25 _C because of theoven controlled crystal oscillator (OCXO). The OCXO continuously dissipates this additional 20 W at --55 _C.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308SeeTR
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--4F. Vendor Supplied Equipment(1) Installation equipment like mounting trays, connectors, and cables can be obtainedfrom various vendors. Refer to Appendix A for additional information about vendormanufactured equipment. For vendor supplied avionics, refer to the vendordocumentation.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
  SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL MCS-4000/7000  TEMPORARY REVISION NO. 23-2     23-20-27 Page 3 of 3 20 Jun 2017                                                  © Honeywell International Inc. Do not copy without express permission of Honeywell. INSERT PAGE 3 OF 3 FACING PAGE 4-5/(4-6 BLANK). Reason:  To change drawing data for Figure 4-2.  Figure 4-2 is changed as follows:  RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--5/(4--6 blank)Figure 4-2. Satellite Data Unit Outline and Installation DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308SeeTR
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--7/(4--8 blank)Figure 4-3. 40 Watt High Power Amplifier Outline and Installation DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--9/(4--10 blank)Figure 4-4 (Sheet 1). 20 Watt High Power Amplifier Outline and Installation DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--11/(4--12 blank)Figure 4-4 (Sheet 2). 20 Watt High Power Amplifier Outline and Installation DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--13/(4--14 blank)Figure 4-5 (Sheet 1). Intermediate Gain Antenna Outline and Installation DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--15/(4--16 blank)Figure 4-5 (Sheet 2). Intermediate Gain Antenna Outline and Installation DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--17/(4--18 blank)Figure 4-6 (Sheet 1). D/LNA Outline and Installation DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--19/(4--20 blank)Figure 4-6 (Sheet 2). D/LNA Outline and Installation DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--21/(4--22 blank)Figure 4-7 (Sheet 1). RFUIA Outline and Installation DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 4--23/(4--24 blank)Figure 4-7 (Sheet 2). RFUIA Outline and Installation DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--1SECTION 5ELECTRICAL INSTALLATION1. OverviewA. General(1) This section supplies electrical installation procedures, power distribution, andinterconnect diagrams for each component of the MCS system.2. Equipment and MaterialsA. General(1) None.3. Electrical Installation ProcedureA. Connector Layout and Contact Arrangement(1) Each front panel connector of the SDU and HPA complies with ARINC characteristic615, and is used to interface the LRU with an ARINC 615 portable data loader forsoftware uploads. Pin callouts are specified in Table 5-1. See the MECHANICALINSTALLATION section for specifics regarding connector part numbers for the ARINC615 connector for each LRU and the corresponding mating connector.(2) The rear connectors of the SDU ,HPA, and RFUIA comply with ARINC characteristic600 as specified in Table 5-2. The ARINC 600 connector layouts and contactarrangement for the various connector plugs for each LRU of the MCS system areshown in Figure 5-1 thru Figure 5-10.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--2Table 5-1. ARINC 615 Connector Pin CalloutsPin SDU Signal Name HPA Signal Name1PDL 429 A IN PDL TO HPA 429 A2PDL 429 B IN PDL TO HPA 429 B5SHIELD GND CHASSIS GND8PDL 429 A OUT HPA TO PDL 429 A9PDL 429 B OUT HPA TO PDL 429 B11 SPARE RX RS232 -- --13 SPARE TX RS232 -- --16 SHIELD GND COMMON GND18 PDL LINK A PDLLINKANO19 GND (PDL LINK B) GND (PDL LINK B)20 115 VAC HOT 115 VAC HOT21 CHASSIS GND CHASSIS GND22 115 VAC COLD 115 VAC GND25 CTU RX RS232 FUTURE USE -- --27 CTU TX RS232 FUTURE USE -- --32 WH10 MIC HI -- --33 WH10 MIC LO -- --34 WH10 SPEAKER HI -- --35 WH10 SPEAKER LO -- --36 WH10 HOOKSWITCH -- --40 RS232 A RX--DLT -- --41 RS232 A TX--DLT -- --42 RS232 B RX--CMT RS232 TO HPA43 RS232 B TX--CMT RS232 TO DEBUG48 LOGIC COMMON COMMON GROUND49 LOGIC COMMON COMMON GROUND50 DL FUNCTION DISC 1 -- --51 DL FUNCTION DISC 2 -- --RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--3Table 5-2. ARINC 600 Connector RequirementsLRU Connector DescriptionLRU RearConnector PartNo.Rack MountingConnector Part No. Outline DiagramSDU ARINC 600 -- Size 6MCU No. 2 Shell•Type 02 Top Insert•Type 02 Middle Insert•Type 04 Bottom Insert•Index Pin Code 04620--600--022(Radiall)NSXN2P201X0004(Radiall)Figure 4-2,Figure 5-1,Figure 5-2,Table 5-3, andTable 5-4HPA(40 W)ARINC 600 -- Size 8MCU No. 2 Shell•Type 08 Top Insert•Type 05 Middle Insert•Type 04 Bottom Insert•Index Pin Code 08620--600--076(Radiall)NSXN2P221X0008(Radiall)Figure 4-3Figure 5-3 thruFigure 5-6HPA(20 W)ARINC 600 -- Size 4MCU No. 2 Shell•Type 08 Top Insert•Type 05 Middle Insert•Type 04 Bottom Insert•Index Pin Code 08620--600--076(Radiall)NSXN2P221X0008(Radiall)Figure 4-4,Figure 5-3,Figure 5-7,Figure 5-8, andFigure 5-9RFUIA ARINC 600 -- Size 4MCU No. 2 Shell•Type 08 Top Insert•Type 05 Middle Insert•Type 04 Bottom Insert•Index Pin Code 03NSXNR221X0103(Radiall)NSXNP221S0103(Radiall)Figure 4-7 andFigure 5-10RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--4Figure 5-1. SDU ARINC 600 Connector LayoutRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--5Table 5-3. Contact Arrangements for Top Insert, SDU ARINC 600 ConnectorA B C D E F G H J K1ANALOGCABINVOICECHANNEL 1HOOK--SWITCHANALOGCABINVOICECHANNEL 2HOOK--SWITCHWH10--1STATUSA(RINGER)WH10--1STATUSB(RINGER)WH10--2STATUSA(RINGER)WH10--2STATUSB(RINGER)AVIONICSSUB--SYSTEMSATCOMFAILWARNING(NON MCSFAIL)ANALOGCABINVOICECHANNEL 1IN--USESATELLITELINK NOTREADYANALOGCABINVOICECHANNEL 2IN--USE2ANALOGPBXCHANNEL 1INPUT HIANALOGPBXCHANNEL 1INPUT LOANALOGPBXCHANNEL 1OUTPUT HIANALOGPBXCHANNEL 1OUTPUT LOANALOGPBXCHANNEL 2INPUT HIANALOGPBXCHANNEL 2INPUT LOANALOGPBXCHANNEL 2OUTPUT HIANALOGPBXCHANNEL 2OUTPUT LOO O3COCKPITVOICE UN--AVAILABLEANALOGCABINVOICE UN--AVAILABLEPACKETDATA UN--AVAILABLEPACKETDATA LOWSPEED ONLYAVAILABLESATCOM IN--OPERABLE(MCS FAIL)CEPT--E10V SHIELD(GND)CEPT--E1 toBRIDGEDCTU(CM--250) 1ACEPT--E1 toBRIDGEDCTU(CM--250) 1BCEPT--E1 toBRIDGEDCTU(CM--250) 2ACEPT--E1 toBRIDGEDCTU(CM--250) 2B4APM PWROUT FUTUREUSEAPM PWRRTN FUTUREUSEAPM CLKOUT FUTUREUSEAPM DATAOUT FUTUREUSEAPM DATA INFUTURE USEAPM WEOUT 1FUTURE USEAPM WEOUT 2FUTURE USEAPM EN1FUTURE USEAPM EN2FUTURE USECEPT--E10V5CTU SLOOP CTU SLOOP CTU SLOOP CTU SLOOP CTU SLOOP CTU SLOOP CTU SLOOP CTU SLOOP CTU SLOOP CTU SLOOP6RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC7417RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC741RESERVEDBY ARINC7418 O O O O O O O O O O9SPAREDISCRETEINPUTCONFIGSTRAP TYPESPAREDISCRETEINPUTCONFIGSTRAP TYPEO O O O O O O O10AVAIL OF429 SSRMODE SADDRESSRESERVEDFOR FMCCONFIGRESERVEDFOR FMCCONFIGCMUBUSSPEEDCPDFCONFIGRESERVEDFOR STRAPOPTIONRESERVEDFOR STRAPOPTIONRESERVEDFOR STRAPOPTIONRESERVEDFOR STRAPOPTIONCALL LIGHTACTIVATORCONFIGU--RATION11STRAPPARITY(ODD)CCSPRESENCEIRSCONFIGIRSCONFIGHPR/HPA/BSU/LGACONFIGHPR/HPA/BSU/LGACONFIGHPR/HPA/BSU/LGACONFIGHPR/HPA/BSU/LGACONFIGHPR/HPA/BSU/LGACONFIGHPR/HPA/BSU/LGACONFIG12 CFDS/CMCTYPECFDS/CMCTYPECFDS/CMCTYPERESERVEDA/C IDOR CFDS/SDUCONFIGSDUCONFIGSDUNUMBERCMUNO. 1CONFIGCMUNO. 2CONFIGMCDU/SCDUNO. 1CONFIGMCDU/SCDUNO. 2CONFIG13 PRIORITY4 CALLSMCDU/SCDUBUS SPEEDLIGHT/CHIMECODELIGHT/CHIMECODEMCDU/SCDUNO. 3CONFIGSDUCODEC 1WIRINGSDUCODEC 1WIRINGSDUCODEC 2WIRINGSDUCODEC 2WIRINGCOCKPITSIGNALINGMETHOD14 5VPOS_MON9VPOS_MONRESERVEDATERESET--MON_N PEIT_SEL_N RESERVEDATERESERVEDATERESERVEDATECEPT--E1FROMBRIDGEDCTU(CM--250)1ACEPT--E1FROMBRIDGEDCTU(CM--250)1A15 15 VPOS_MON15 VNEG_MONGND (ATECOMMON)CEPT--E1FROMBRIDGEDCTU(CM--250) 2ACEPT--E1FROMBRIDGEDCTU(CM--250) 2ADLT_RX(RS232RX--SDU)DLT_TX(RS232TX--SDU)CMT_RX(RS232RX--SDU)CMT_TX(RS232TX--SDU)CMT_DLT_RTNRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--6Table 5-4. Contact Arrangements for Middle Insert, SDU ARINC 600 ConnectorA B C D E F G H J K1WH10 CABINNO. 1AUDIO IN HIWH10 CABINNo. 1AUDIO IN LOWH10 CABINNo. 1AUDIO OUTHIWH10 CABINNo. 1AUDIO OUTLODATA BUSFROM CABINPACKETDATA ADATA BUSFROM CABINPACKETDATA BFROM CMUNO. 1429AFROM CMUNO. 1429BTO CMUNO. 1 ANDNO. 2429 ATO CMUNO. 1 ANDNO. 2429 B2COCKPITAUDIO CH 1INPUT HICOCKPITAUDIO CH 1INPUT LOCOCKPITAUDIO CH 1OUTPUT HICOCKPITAUDIO CH 1OUTPUT LOCOCKPITAUDIO CH 2INPUT HICOCKPITAUDIO CH 2INPUT LOCOCKPITAUDIO CH 2OUTPUT HICOCKPITAUDIO CH 2OUTPUT LOCEPT--E1FROM CTUINPUT ACEPT--E1FROM CTUINPUT B3CEPT--E1 TOCTU OUTPUTACEPT--E1 TOCTU OUTPUTBDATA FROMSCDUNO. 1ADATA FROMSCDUNO. 1BDATA FROMSCDUNO. 2ADATA FROMSCDUNO. 2BDATA FROMCMUNO. 2ADATA FROMCMUNO. 2BDATA TOSCDU NO. 1,NO.2,ANDNO. 3ADATA TOSCDU NO. 1,NO.2,ANDNO. 3B4AESIDINPUTAAESIDINPUTBFROMCFDSAFROMCFDSBTOCFDSATOCFDSBMULTI--CONTROLOUTPUTAMULTI--CONTROLOUTPUTBWH10 CABINNO. 2AUDIO INHIWH10 CABINNO. 2AUDIO INLOLGALNAW E I G H T -- O N -- W H E E L S WH10 CABINNO.2WH10 CABINNO.2BITE INPUTFROM LGACHIME/LIGHTDUALSYSTEMDUALSYSTEM5LGALNAON/OFFCONTROL INPUTNO. 1INPUTNO. 2PROGRAMSELECTNO.2AUDIO OUTHINO.2AUDIO OUTLOFROMLGALNALIGHTINHIBITSYSTEMSELECTDISCRETEI/OSYSTEMSELECTDISCRETEINHIBIT6DATA FROMPRIMARYIRS ADATA FROMPRIMARYIRS BDATA FROMSECONDARYIRS ADATA FROMSECONDARYIRS BBITE INPUTFROMHGA/HPA ABITE INPUTFROMHGA/HPA BSPARE 429INPUTASPARE 429INPUTBBITE INPUTFROMLGA/HPA ABITE INPUTFROMLGA/HPA B7DATA BUSFROMAIRBORNELOADERADATA BUSFROMAIRBORNELOADERBDATA BUSTOAIRBORNELOADERADATA BUSTOAIRBORNELOADERBBSU NO. 1AND NO. 2STEERINHIBITABSU NO. 1AND NO. 2STEERINHIBITBBITE INPUTFROM ACUORTOP--PORTBSU ABITE INPUTFROM ACUORTOP--PORTBSU BBITE INPUTFROM STBDBSUABITE INPUTFROM STBDBSUB8DATALOADERLINK ADATALOADERLINK BRESERVEDFOR DATABUS FROMRMP ARESERVEDFOR DATABUS FROMRMP BCP VOICECALL LGTOUTPUTNO. 1CP VOICEMIC ONINPUTNO. 1CP VOICECALL LGTOUTPUTNO. 2CP VOICEMIC ONINPUTNO. 2DATA FROMSCDUNO. 3ADATA FROMSCDUNO. 3B9DATA BUSTO SNU ORCPDF ADATA BUSTO SNU ORCPDF BRESERVEDFOR DATATO RMP ARESERVEDFOR DATATO RMP BRESERVEDDATA BUSRESERVEDDATA BUSRESERVEDDATA BUSRESERVEDDATA BUSCEPT--E1FROM 0BE1ACEPT--E1FROM 0BE1B10 CEPT--E1 TO0BE1 ACEPT--E1 TO0BE1 B RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED11FROMMOTIONSENSORNO. 1MOTIONSENSORNO. 1PROGRAMSELECTCALLCANCELDISCRETEINPUTNO. 1CALLCANCELDISCRETEINPUTNO. 2RESERVEDUNSPECPROGRAMRESERVEDUNSPECPROGRAMRESERVEDUNSPECPROGRAMRESERVEDUNSPECPROGRAMRESERVEDUNSPECPROGRAMRESERVEDUNSPECPROGRAM12CROSSTALKFROMOTHERSDUACROSSTALKFROMOTHERSDUBCROSSTALKTOOTHERSDUACROSSTALKTOOTHERSDUBSPAREOSPAREORESERVEDFOR DATAFROMFMC 1ARESERVEDFOR DATAFROMFMC 1BRESERVEDFOR DATAFROMFMC 2ARESERVEDFOR DATAFROMFMC 2B13SPAREDISCRETEOUTPUT28 VDC CALLLAMP TYPESPAREOICAOADDRESSBIT NO. 1(MSB)ICAOADDRESSBIT NO. 2ICAOADDRESSBIT NO. 3ICAOADDRESSBIT NO. 4ICAOADDRESSBIT NO. 5ICAOADDRESSBIT NO. 6ICAOADDRESSBIT NO. 7ICAOADDRESSBIT NO. 814CP VOICEGO--AHEADCHIMERESETNO. 1CP VOICECHIMECONTACT1CP VOICECONTACT2ICAOADDRESSBIT NO. 9ICAOADDRESSBIT NO. 10ICAOADDRESSBIT NO. 11ICAOADDRESSBIT NO. 12ICAOADDRESSBIT NO. 13ICAOADDRESSBIT NO. 14ICAOADDRESSBIT NO. 1515ICAOADDRESSBIT NO. 16ICAOADDRESSBIT NO. 17ICAOADDRESSBIT NO. 18ICAOADDRESSBIT NO. 19ICAOADDRESSBIT NO. 20ICAOADDRESSBIT NO. 21ICAOADDRESSBIT NO. 22ICAOADDRESSBIT NO. 23ICAOADDRESSBIT NO. 24(LSB)ICAOADDRESSCOMMONRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--7Figure 5-2. Contact Arrangements for Bottom Insert, SDU ARINC 600 ConnectorRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--8Figure 5-3. HPA ARINC 600 Connector LayoutRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--9Figure 5-4. Contact Arrangements for Top Insert, HPA (40 Watt) ARINC 600 ConnectorRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--10Figure 5-5. Contact Arrangements for Middle Insert, HPA (40 Watt) ARINC 600 ConnectorRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--11Figure 5-6. Contact Arrangements for Bottom Insert, HPA (40 Watt) ARINC 600 ConnectorRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--12Figure 5-7. Contact Arrangements for Top Insert, HPA (20 Watt) ARINC 600 ConnectorRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--13Figure 5-8. Contact Arrangements for Middle Insert, HPA (20 Watt) ARINC 600 ConnectorRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--14Figure 5-9. Contact Arrangements for Bottom Insert, HPA (20 Watt) ARINC 600 ConnectorRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--15Figure 5-10. RFUIA ARINC 600 Connector LayoutRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--16B. Electrical Installation(1) The information necessary to supply the electrical interconnects is shown inFigure 5-11 thru Figure 5-26. Interconnect diagrams are as follows:•Figure 5-11. Satellite Data Unit Interface Diagram•Figure 5-12. WH--10 Handset Interface Diagram•Figure 5-13. Four--to--Two Wire Interface Diagram•Figure 5-14. Avtech Fax Interface Diagram•Figure 5-15. HF--SAT Transfer Panel Interface Diagram•Figure 5-16. Signal Conditioning Unit Interface Diagram•Figure 5-17. Maintenance Panel Assembly Interface Diagram•Figure 5-18. Intermediate Gain Antenna Interface Diagram•Figure 5-19. CMC Top--Mount High Gain Antenna Interface Diagram•Figure 5-20. Tecom Top--Mount High Gain Antenna Interface Diagram•Figure 5-21. Racal Mechanically Steered High Gain Antenna Interface Diagram•Figure 5-22. AMT--50 Mechanically Steered High Gain Antenna Interface Diagram•Figure 5-23. Dassault Conformal High Gain Antenna Interface Diagram•Figure 5-24. Ball Conformal High Gain Antenna Interface Diagram•Figure 5-25. Low Gain Antenna Interface Diagram•Figure 5-26. Toyocom Top--Mount High Gain Antenna Interface Diagram.(2) The applicable configuration pins in the aircraft wiring must be connected to make theMCS system functional. The SDU receives and sends 30 system configurationdiscrete inputs through the configuration pins to properly match the avionicsequipment installed on the aircraft (see Figure 5-11 and Paragraph 4. to identify theconfiguration pins).(3) The SDU receives a 24-bit ICAO address that identifies the aircraft in which the SDUis installed (Figure 5-11). Continuity is defined as a resistance of 10 ohms or lessbetween a configuration pin or address pin and the common. Continuity is brokenwhen the resistance between a configuration pin or address pin and commonmeasures 100k ohms or greater.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--17Figure 5-11 (Sheet 1). Satellite Data Unit Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--18Figure 5-11 (Sheet 2). Satellite Data Unit Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--19Table 5-5. ICAO Block StrappingExample: AES ID 53375006 (Octal)Octal Binary SDU Connector Pin (MP)1C135 0 D131E130F133 1 G131H130J133 1 K131D141E147 1 F141G141H145 0 J141K140A150 0 B150C150D150 0 E150F151G156 1 H150J15Common K15NOTES:1. 53375006 (Octal) = 101011011111101000000110 (Binary).2. Binary 1 = Open; Binary 0 = Ground.3. Pins assigned a zero (0) are wired to SDU connector pin MP--K15 (common).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--20Figure 5-12. WH--10 Handset Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--21Figure 5-13. Four--to--Two Wire Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--22Figure 5-14. Avtech Fax Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--23Figure 5-15. HF--SAT Transfer Panel Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--24Figure 5-16. Signal Conditioning Unit Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--25Figure 5-17. Maintenance Panel Assembly Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--26Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--27/(5--28 blank)Figure 5-18. Intermediate Gain Antenna Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--29/(5--30 blank)Figure 5-19. CMC Top--Mount High Gain Antenna Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--31/(5--32 blank)Figure 5-20. Tecom Top--Mount High Gain Antenna Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--33Figure 5-21. Racal Mechanically Steered High Gain Antenna Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--34Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--35/(5--36 blank)Figure 5-22. AMT--50 Mechanically Steered High Gain Antenna Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--37/(5--38 blank)Figure 5-23. Dassault Conformal High Gain Antenna Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--39/(5--40 blank)Figure 5-24. Ball Conformal High Gain Antenna Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--41/(5--42 blank)Figure 5-25. Low Gain Antenna Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--43/(5--44 blank)Figure 5-26. Toyocom Top--Mount High Gain Antenna Interface DiagramRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--454. Configuration PinsA. General(1) The following paragraphs supply system configuration pins definition andinterpretation information. Pins assigned to take on the binary one stateinagivencode should be left as an open circuit. Pins assigned to take on the binary zero statein the code should be wired to SDU connector pin MP15K (address common) on theairframe side of the connection. The configuration pins are listed in Table 5-6.Table 5-6. Configuration PinsPin DefinitionTP10A AVAILABILITY OF ARINC 429 SSR MODE S ADDRESS (AES ID) FROM 429 PORTSTP10B FMC CONNECTION TO SDUTP10C FMC CONNECTION TO SDUTP10D ARINC 429 BUS SPEED TO/FROM CMU NO. 1 AND CMU NO. 2TP10E CPDF CONFIGURATIONTP10F 429 BUS SPEED OF AES ID INPUTTP10G RESERVED FOR STRAP OPTIONTP10H RESERVED FOR STRAP OPTIONTP10J RESERVED FOR STRAP OPTIONTP10K CALL LIGHT ACTIVATIONTP11A STRAP PARITY (ODD: COVERING THE OTHER 39 STRAP PINS)TP11B CCS PRESENCETP11C IRS CONFIGURATIONTP11D IRS CONFIGURATIONTP11E HPR/HPA/BSU/LGA CONFIGURATIONTP11F HPR/HPA/BSU/LGA CONFIGURATIONTP11G HPR/HPA/BSU/LGA CONFIGURATIONTP11H HPR/HPA/BSU/LGA CONFIGURATIONTP11J HPR/HPA/BSU/LGA CONFIGURATIONTP11K HPR/HPA/BSU/LGA CONFIGURATIONTP12A CFDS TYPETP12B CFDS TYPETP12C CFDS TYPETP12D PAD FOR CFDS/SDU CONFIGURATIONRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--46Table 5-6. Configuration Pins (cont)Pin DefinitionTP12E SDU CONFIGURATIONTP12F SDU NUMBERTP12G CMU NO. 1 CONFIGURATIONTP12H CMU NO. 2 CONFIGURATIONTP12J MCDU/SCDU NO. 1 CONFIGURATIONTP12K MCDU/SCDU NO. 2 CONFIGURATIONTP13A PRIORITY 4 CALLS TO/FROM COCKPITTP13B ARINC 429 BUS SPEED TO MCDU/SCDU NO. 1, NO. 2, AND NO. 3TP13C COCKPIT VOICE CALL LIGHT/CHIME OPTIONSTP13D COCKPIT VOICE CALL LIGHT/CHIME OPTIONSTP13E MCDU/SCDU NO. 3 CONFIGURATIONTP13F SDU CODEC 1 WIRINGTP13G SDU CODEC 1 WIRINGTP13H SDU CODEC 2 WIRINGTP13J SDU CODEC 2 WIRINGTP13K COCKPIT HOOKSWITCH SIGNALING METHODB. Availability of ARINC 429 SSR MODE S (AES ID) from CMU Ports(1) The interpretation of this configuration pin is given in Table 5-7.Table 5-7. Availability of ARINC 429 SSR MODE S (AES ID) from CMU PortsTP10 Pin A Interpretation1SSR MODE S ADDRESS (AES ID) NOT AVAILABLE FROM CMU NO. 1 NORRESERVED AES ID INPUT0SSR MODE S ADDRESS (AES ID) IS AVAILABLE FROM CMU NO. 1 AND/OR CMUNO. 2 AND/OR AES ID INPUTRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--47(2) When wired to the zero state, the TP10A configuration pin indicates the SSR mode Saddress (AES ID) is available in the ARINC 429 label 275/276 format from one orboth of the SDU CMU input ports or the AES ID input port, and that one of thoseARINC 429 sources of the address is used with no specific preference for CMU 1,CMU 2, CMU 3, or the AES ID input. In this state, the discrete inputs on SDU pinsMP13C thru MP13K and MP14D thru MP14J are not assumed to be wired and theSDU does not use the discretes, even if the ARINC 429 sources fail or remaininactive.(3) In the zero state, the SDU monitors the CMU 1, CMU 2, and AES ID input buses untila valid ICAO address is received. Bits 1 thru 16 of the AES ID are obtained from thelabel 275 word and bits 17 thru 24 are obtained from the label 276 word. The SDUonly constructs a full 24-bit address from labels 275 and 276 words received from thesame input port (e.g., label 275 from CMU 1 can not be combined with label 276 fromCMU 2 or the AES ID input). The address is only considered valid if it does notconsist of all zeros or ones, and has been received in ARINC 429 words with theirsign--status matrix (SSM) indicating normal operation.(4) If address words containing either all zeros or ones are received, followed by addresswords with a valid address (i.e., not all zeros or ones), the SDU verifies the receipt ofboth labels 275 and 276 at least twice with the same address bits content in eachrespective word before declaring the address valid. This is to preclude the SDU frominadvertently and prematurely assuming the address is valid after only one of the twolabels has yielded a valid segment of the overall address, but the most previouslyreceived copy of the other label has not yet been updated to its intended code. Theroot problem is that the 24 correlated address bits are transmitted in two separateasynchronous words that are not inherently correlated/paired. This requirement isintended to effectively pair the label 275 and 276 transmissions.(5) Once a valid ICAO address is received on any bus, the SDU ignores further datareceived on any of the buses until the next POST/PAST. This requirement relievesthe SDU of having to deal with the possibility that the ICAO technical address mightchange while the SDU is logged-on. The AES ID (ICAO address) is determined atstartup and cannot change until the next POST/PAST. The SDU does not log-on untilit has a valid AES ID. The SDU waits indefinitely to receive a valid address from anavailable ARINC 429 source rather than giving up at the end of POST/PAST, since itcannot proceed as an AES without the address. If the configuration pin indicates theARINC 429 source is available, the discretes are not wired. The SDU should notrevert to the discretes at the end of POST/PAST as the CMU may not yet beoperational.(6) If configuration pin TP10A is wired to the one state, then neither CMU input port northe AES ID input port is capable of supplying the AES ID in the ARINC 429 formatand the SDU reads the AES ID from the discrete inputs.(7) With either the ARINC 429 or discrete inputs source, an AES ID of all zeros or allones (binary) is invalid (typically indicative of an unprogrammed address) whichconstitutes a failure. The SDU does not attempt to log-on to a GES with an invalidAES ID.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--48C. FMC Connection to SDU(1) The interpretation of these configuration pins is given in Table 5-8.Table 5-8. FMC Connection to SDUTP10 PinsB C Interpretation0 0 FMC NO. 1 CONNECTED, FMC NO. 2 CONNECTED0 1 FMC NO. 1 CONNECTED, FMC NO. 2 NOT CONNECTED1 0 FMC NO. 1 NOT CONNECTED, FMC NO. 2 CONNECTED1 1 NEITHER FMC CONNECTEDNOTE: SATCOM does not support the FMC interface.(2) When individually wired to the zero state, configuration pins TP10B and TP10Cindicate respectively that the inputs designated for FMC No. 1 and FMC No. 2 (pinsMP12G/MP12H and MP12J/MP12K, respectively) are connected to a ARINC 429source of flight plan information (next way point, etc.). The SDU onlylogs/reports/indicates bus inactivity on either bus if the respective configuration pinindicates the bus is supposed to be connected to an ARINC source. The SDU canassume (for functional purposes) the presence of the flight management computer(FMC) connections from the state of these configuration pins.D. ARINC 429 Speed to/from CMU No. 1 and CMU No. 2(1) The interpretation of this configuration pin is given in Table 5-9.Table 5-9. ARINC 429 Speed to/from CMU No. 1 and CMU No. 2TP10 Pin D Interpretation1LOW SPEED ARINC 429 DATA BUS0HIGH SPEED ARINC 429 DATA BUS(2) When this configuration pin is wired to the zero state, the SDU operates its input andoutput ARINC 429 buses for the CMUs No. 1 and No. 2 at high speed. When wired tothe one state, the SDU operates these buses at the low speed.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--49E. Cabin Packet Data Function (CPDF)(1) The interpretation of this configuration pin is given in Table 5-10.Table 5-10. Cabin Packet Data Function (CPDF)TP10 Pin E Interpretation0CPDF CONNECTED1CPDF NOT CONNECTED(2) When wired to the zero state, this configuration pin indicates the input designated forthe CPDF (MP1E and MP1F) is connected to an ARINC 429 source of data--3 packetdata and that the SDU output (pins MP9A and MP9B) is wired to the CPDF. The SDUonly logs/reports/ indicates CPDF failures and bus inactivity on the CPDF input bus ifthis configuration pin indicates the bus is supposed to be connected to an ARINCsource. The SDU can assume (for functional purposes) the presence of the CPDFconnections from the state of this pin.F. ARINC 429 BUS Speed of AES ID Input(1) The interpretation of these configuration pins is given in Table 5-11 and Table 5-12.Table 5-11. ARINC 429 Bus Speed of AES ID InputTP10 Pin F Interpretation0HIGH SPEED ARINC 429 BUS1LOW SPEED ARINC 429 BUSTable 5-12. Call Light On (Air/Ground Calls)TP10 Pin K Interpretation0CALL LIGHT ON AT CALL INITIATION (FOR AIR/GROUND CALLS)1CALL LIGHT ON AT CALL CONNECTION (FOR AIR/GROUND CALLS)G. Strap Parity (ODD)(1) The interpretation of this configuration pin is given in Table 5-13.Table 5-13. Strap Parity (ODD)TP11 Pin A Interpretation0SUM OF ALL OTHER STRAPS SET TO 1 IS ODD1SUM OF ALL OTHER STRAPS SET TO 1 IS EVENRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--50(2) The coverage of the parity pin is SDU connector pins TP10A thru TP10K and TP11Bthru TP13K (39 pins other than itself). The parity pin is programmed to a zero or oneto yield an odd number of strap bits set to the one state, including the parity pin itself.(3) The parity pin is wired to yield odd parity over all 40 configuration pins (i.e., the paritypin is programmed to the zero or one state to yield an odd number of configurationpins wired to the one state, including itself. The SDU verifies the state of the paritypin is correct when the configuration pins are read (typically once per power cycle justafter power-up). An invalid state of the parity pin is logged/reported/indicated; thestates of the other configuration pins are used as read despite the parity error.H. Cabin Communications System (CCS)(1) The interpretation of this configuration pin is given in Table 5-14.Table 5-14. Cabin Communications System (CCS)TP11 Pin B Interpretation0CCS INSTALLED1CCS NOT INSTALLED(2) The state of this configuration pin is ignored. The SDU can assume (for functionalpurposes) the presence of the CCS connections from the state of this pin.(3) Before the availability of software package C, aircraft can be fitted with interimversions of the CCS that make use of the analog PBX interface. These installationsset the configuration pin to the zero state, but other analog PBX installations can notso its state should be ignored in such prepackage C systems.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--51I. Inertial Reference System (IRS)(1) The interpretation of these configuration pins is given in Table 5-15.Table 5-15. Inertial Reference System (IRS)TP11 PinsC D Interpretation0 0 PRIMARY IRS INSTALLED, SECONDARY IRS INSTALLED0 1 PRIMARY IRS INSTALLED, SECONDARY IRS NOT INSTALLED1 0 PRIMARY IRS NOT INSTALLED, SECONDARY IRS INSTALLED1 1 PRIMARY IRS NOT INSTALLED, SECONDARY IRS NOT INSTALLED(2) When individually wired to the zero state, configuration pins TP11C and TP11Dindicate, respectively, that the inputs designated for the primary and secondary IRSs(MP6A/MP6B and MP6C/MP6D, respectively) are connected to an ARINC 429source of IRS label 310, 311, 312, 314, 324, 325, and 361 information (although label361, Inertial Altitude, is not required for SATCOM). The actual IRS (i.e., IRS No. 1,IRS No. 2, or IRS No. 3) driving either SDU input is determined from the sourcedestination identifier (SDI) bits of the received ARINC words. The SDU onlylogs/reports/indicates bus inactivity on either bus if the respective configuration pinindicates that the bus is supposed to be connected to an ARINC 429 source. TheSDU can assume (for functional purposes) the presence of the IRS connections fromthe state of these pins.J. HPA/Antenna Subsystem Configuration(1) The interpretation of these configuration pins is given in Table 5-16.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--52Table 5-16. HPA/Antenna Subsystem ConfigurationTP11 PinsLGA+LNATOP/PORSTARBOARDRESERVEDFRESERVEE F G H J KA/DIPLEXERLGAHPARTBSU+HGADBSU+HGAHGAHPAHPRFORFUTUREEDFORMFRIGAHPA111111✱ ✱011111✱ ✱101111✱ ✱ ✱ ✱001111✱✱✱✱✱✱110111✱010111✱100111✱ ✱ ✱ ✱Note 1.000111✱✱✱✱ ✱Note 1.111011✱✱✱✱011010011010to✱101010000010to✱111000✱NOTES:1. Not defined at this time.2. Other configurations are possible and can be added at a later date.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--53(2) For functional purposes, the SDU assumes the HPA and antenna subsystemconfiguration of its particular installation from states of these configuration pins.However, configurations 100111 and 000111 are not supported. Both of thenonsupported configurations involve the sharing of a single HPA between an LGAand HGA, by using a high power relay (HPR). No control or BITE signal interfacesare specified for the HPR, the MCS system does not accommodate theseconfigurations.(3) The SDU commands the system, uses its resources, and logs/reports/indicatesfailures in the HPAs and antenna subsystem based on the determined HPA andantenna subsystem configuration. Inactivity on the SDU input buses from the HPA(s)and ACU/BSU(s) and failures against the diplexer/LNA and HPR arelogged/reported/indicated if the respective LRU is specified to be connectedaccording to these pins. If these configuration pins are set to a nonsupported,reserved for future, or reserved for Mfr state, the SDU logs/reports/indicates theappropriate strap failure(s) and does not attempt any satellite communicationfunctions.K. CFDS/CMC(1) The interpretation of these configuration pins is given in Table 5-17.Table 5-17. CFDS/CMCTP12 PinsABC Interpretation000UNDEFINED001McDONNELL--DOUGLAS TYPE CFDS010AIRBUS TYPE CFDS011HONEYWELL CAIMS100BOEING TYPE CMC101UNDEFINED110UNDEFINED111CFDS NOT INSTALLED(2) For functional purposes, the SDU can assume the type of central fault/maintenancesystem (if any) that is connected from the state of these configuration pins. TheCMC/CFDS interface operates according to the determined type. The appropriatestrap failure(s) is(are) logged/indicated if an undefined code is present. The SDU onlylogs/reports/indicates bus inactivity for the MP4C/MP4D CFDS interface input bus ifthe configuration pins indicate the CMC/CFDS is supposed to be installed.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--54L. SDU Configuration(1) The interpretation of this configuration pin is given in Table 5-18.Table 5-18. SDU ConfigurationTP12 Pin E Interpretation0SECOND SDU INSTALLED1SECOND SDU NOT INSTALLED(2) When wired to the zero state, this configuration pin indicates a second SDU ispresent as part of the MCS system installation. The zero state also indicates pinsMP12C/MP12D and MP12A/MP12B (cross talk to and from the other SDU,respectively) and MP5j/MP5K (dual system select and dual system disable discretes,respectively) are connected to the second SDU. When this pin is in the zero state, italso indicates these signals are used to determine dual SATCOM operation asspecified in SYSTEM OPERATION. The SDU only logs/reports/indicates inactivity onits input cross--talk bus from the second SDU when this pin is in the zero state. TheSDU can assume (for functional purposes) the presence of a second SDU from thestate of this configuration pin. The SDU also uses the state of this pin (and for dualSATCOM installations, the state of SDU number pin TP12F) to determine the state ofits output word SDI fields.M. SDU Number(1) The interpretation of this configuration pin is given in Table 5-19.Table 5-19. SDU NumberTP12 Pin F Interpretation0SDU NO. 21SDU NO. 1NOTE: The state of this strap is Don’t Care for a single SDU configuration.(2) When wired to the zero state, this configuration pin indicates this SDU is No. 2 in adual MCS system installation. The one state indicates this SDU is No. 1 in a dualinstallation. The SDU uses the state of this pin and the SDU configuration pin TP12Eto determine the state of its output word SDI fields. In a single MCS systeminstallation, the status of this configuration pin is ignored.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--55N. CMU No. 1 and No. 2 Configuration(1) The interpretation of these configuration pins is given in Table 5-20 and Table 5-21.Table 5-20. CMU No. 1TP12 Pin G Interpretation0CMU NO. 1 INSTALLED1CMU NO. 1 NOT INSTALLEDTable 5-21. CMU No. 2TP12 Pin H Interpretation0CMU NO. 2 INSTALLED1CMU NO. 2 NOT INSTALLED(2) When individually wired to the zero state, configuration pins TP12G and TP12Hindicate, respectively, that the inputs designated for CMU No. 1 and CMU No. 2 (pinsMP1G/MP1H and MP3G/MP3H, respectively) are connected to an ARINC 429source of CMU information (e.g., CMU label 270 and SAL 304), and also the singleSDU output (pins MP1J/MP1K) is wired to the appropriate CMU(s). The SDU onlylogs/reports/indicates bus inactivity on either CMU input bus if the respectiveconfiguration pin indicates the bus is supposed to be connected to an ARINC source.The SDU can assume (for functional purposes) the presence of the CMUconnections from the state of these configuration pins.O. MCDU/SCDU No. 1 thru No. 3 Configuration(1) The interpretation of these configuration pins is given in Table 5-22 thru Table 5-24.Table 5-22. MCDU/SCDU No. 1TP12 Pin J Interpretation0MCDU/SCDU NO. 1 INSTALLED1MCDU/SCDU NO. 1 NOT INSTALLEDTable 5-23. MCDU/SCDU No. 2TP12 Pin K Interpretation0MCDU/SCDU NO. 2 INSTALLED1MCDU/SCDU NO. 2 NOT INSTALLEDRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--56Table 5-24. MCDU/SCDU No. 3TP13 Pin E Interpretation0MCDU/SCDU NO. 3 INSTALLED1MCDU/SCDU NO. 3 NOT INSTALLED(2) When individually wired to the zero state, configuration pins TP12J, TP12K, andTP13E indicate, respectively, that the inputs designated for MCDU/SCDU No. 1, No.2, and No. 3 (pins MP3C/MP3D, MP3E/MP3F, and MP8J/MP8K, respectively) areconnected to an ARINC 429 source of line select/keypad control information, andalso the single SDU output (MP3J/MP3K) is wired to all appropriate MCDU/SCDU(s).The SDU only logs/reports/indicates bus inactivity on any of the three buses if therespective configuration pin indicates the bus is supposed to be connected to anARINC source. The SDU can assume (for functional purposes) the presence of theMCDU/SCDU connections from the state of these configuration pins.P. Priority 4 Calls to/from Cockpit(1) The interpretation of this configuration pin is given in Table 5-25.Table 5-25. Priority 4 Calls to/from CockpitTP13 Pin A Interpretation0DISALLOW PRIORITY 4 CALLS1ALLOWS PRIORITY 4 CALLS(2) When this configuration pin is wired to the zero state, the SDU disallows priority 4calls from being routed to or initiated from the cockpit. This state prevents ORT itemxiii (Appendix C) from being set to allow routing of ground-to-air priority 4 calls to thecockpit headset. When this configuration is wired to the one state, the SDU letspriority 4 calls be initiated from the cockpit and lets ground-to-air calls be routed tothe cockpit based upon ORT item xiii.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--57Q. ARINC 429 BUS Speed to SCDU No. 1 / SCDU No. 2 / SCDU No. 3(1) The interpretation of this configuration pin is given in Table 5-26.Table 5-26. ARINC 429 Bus Speed to SCDU No. 1 / SCDU No. 2 / SCDU No. 3TP13 Pin B Interpretation0LOW SPEED ARINC 429 BUS1HIGH SPEED ARINC 429 BUS(2) When this configuration pin is wired to the zero state, the SDU operates its ARINC429 output bus for MCDU/SCDUs No. 1, No. 2, and No. 3 at the low speed. Whenwired to the one state, the SDU operates this bus at the high speed.R. Cockpit Voice Call Light/Chime Option(1) The interpretation of these configuration pins is given in Table 5-27.Table 5-27. Cockpit Voice Call Light/Chime OptionTP13 PinsC D Interpretation0 0 SPARE0 1 STEADY LIGHTS AND MULTISTROKE CHIME1 0 FLASHING LIGHTS AND SINGLE STROKE CHIME1 1 STEADY LIGHTS AND SINGLE STROKE CHIME(2) The SDU determines the mode of cockpit call annunciation (flashing vs. steady voicecall lamp, multistroke vs single stroke chime) from the states of these configurationpins. The functionality of the cockpit call annunciation interface (pins MP8E andMP8G for the call lights, and MP14B and MP14C for the chime) operate according tothe configuration pin connections selected. The selected state of pins TP13C andTP13D applies to both air- and ground-initiated calls; it only applies to the callannunciation phase (i.e., following connection acknowledgement by receipt of theoff-hook state as specified by the state of TP13K, a multistroke chime is silenced andthe call lamp remains on steady). The appropriate strap failure(s) is logged/indicatedif an undefined code is present. The SDU defaults to the steady lights and singlestroke chime state if an undefined code is present.(3) The steady versus flashing light option applies to the call annunciation phase only.The light remains on (steady) for the duration of the call after the acknowledgementof the annunciation for either the steady or flashing light option.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--58S. SDU CODEC 1 and CODEC 2 Wiring(1) The interpretation of these configuration pins is given in Table 5-28 and Table 5-29.Table 5-28. SDU Analog Interface No. 1 WiringTP13 PinsF G Interpretation0 0 AMS WIRED, CABIN AUDIO WIRED0 1 AMS WIRED, CABIN AUDIO NOT WIRED1 0 AMS NOT WIRED, CABIN AUDIO WIRED1 1 AMS NOT WIRED, CABIN AUDIO NOT WIREDTable 5-29. SDU Analog Interface No. 2 WiringTP13 PinsH J Interpretation0 0 AMS WIRED, CABIN AUDIO WIRED0 1 AMS WIRED, CABIN AUDIO NOT WIRED1 0 AMS NOT WIRED, CABIN AUDIO WIRED1 1 AMS NOT WIRED, CABIN AUDIO NOT WIRED(2) The SDU determines the extent and nature of the analog cockpit and cabin voiceconnections from the states of these configuration pins. The functionality of theanalog cockpit and cabin voice interface (pins MP1A/MP1B, MP1C/MP1D,MP2A/MP2B, MP2C/MP2D, MP2E/MP2F, MP2G/MP2H, MP4J/MP4K, andMP5E/MP5F) operate according to the connections selected. ORT item vi for codecdedication (Appendix C) is related to the SDU codec configuration pins; dedication orautomatic sharing of a codec to or with a particular interface is only possible if theSDU codec wiring straps indicate the codec is wired to that interface.T. Cockpit Hookswitch Signaling Method(1) General(a) The interpretation of this configuration pin is given in Table 5-30.Table 5-30. Cockpit Hookswitch Signaling MethodTP13 Pin K Interpretation1SWITCHED PTT AND/OR SCDU LINE SWITCH(ES)0LATCHED AUDIO CONTROL PANEL SATCOM MICROPHONE SWITCHRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--59(b) This configuration pin specifies the functionality of the SDU Cockpit VoiceMic-On Input No. 1 (and No. 2) discrete inputs (referred to as the mic-oninputs). When TP13K is wired to the one state, the SDU utilizes the switchedPTT and/or SCDU line switch(es) (referred to as switched PTT) method forcockpit hookswitch signaling on the mic-on inputs. When TP13K is wired to thezero state, the SDU utilizes the latched audio control panel SATCOMmicrophone switch (referred to as the latched ACP) method. These twomethods are described below.(2) Switched PTT Method(a) With the switched PTT method, the SDU assumes the mic-on inputs are wired toconventional microphone momentary push-to-talk switches (i.e., they aredynamically active [on/off] throughout the duration of the call). The SDUassumes the air- or ground-initiated call annunciation to have beenacknowledged (i.e., the call to in the off-hook state) when the appropriate mic-oninput is activated (connected to ground) for the first time after the callannunciation for a particular channel. Successive activations of that mic-on inputfor the duration of that call have no effect on the status of that call until the callhas been cleared.(b) With the switched PTT method, the off-hook state is also entered followingactivation of the Answer Call line select switch on the SCDU. The on-hook stateis entered following activation of the End Call lineselectswitchontheSCDUthat results in call clearing.(c) This method also allows usage of the place/end call discrete input andassociated switch to initiate calls to preselected numbers, as well as to terminateexisting calls.(3) Latched ACP Method(a) With the latched ACP method, the SDU assumes the mic-on inputs are wired toSATCOM microphone select switches on the ACP that are latched on(connected to ground) for the entire duration of a call. The SDU considers theair- or ground-initiated call annunciation to have been acknowledged (i.e., thecall to be in the off-hook state) when the appropriate mic-on input is active(connected to ground) for a particular channel. The call is cleared and thechannel is considered to be in the on-hook state when the mic-on input is in theopen-circuit state.(b) With the latched ACP method, all hookswitch signaling for answering andterminating all air- and ground-initiated calls is handled by the mic-on inputs; theSCDU Answer Call and End Call options are blanked (the SCDU is onlynecessary for specifying the called-party number and initiating the call processfor air-to-ground calls).(c) This method also allows usage of the mic--on discrete input and switch to initiatecalls to preselected numbers.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 5--60Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page 6--1SECTION 6TESTING/FAULT ISOLATION1. OverviewA. General(1) This section defines the built-in test equipment (BITE) requirements for the MCSsystem (i.e., SDU and HPA). Information supplied in this section describes how MCSsystem failures are detected, recorded, and reported. See Figure 6-1 for an overviewof the BITE system communications. Refer to Appendix D for an explanation of thefault codes obtained by any troubleshooting process.(2) System BITE contributes to a number of maintenance functions:•Detection of internal and external failures•Storage of in-flight failure data•Reporting failure status in the air and on the ground•Ground test capability for isolating faulty LRUs, performance verification, andsystem level testing.Figure 6-1. System BITE CommunicationRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--2B. Definitions(1) Degraded Operation(a) Degraded operation is defined as the condition when the MCS system isoperating with a failure that results in diminished capability (e.g., some, but notall channel units available, or less than nominal HPA power available).(2) Failure(a) A failure is defined as a fault that persists for a predetermined amount of time orfor a predetermined number of samples. The tolerance on all failure timingcriteria is ±0.5 second.(3) Intermittent Failure(a) An intermittent failure is defined as a fault that had been declared a failure,recovered to its normal valid state, and then is declared to have failed again. Afailure occurrence counter is maintained for each entry in the LRU and systemfailure logs to identify intermittent failures.(4) Fault(a) A fault is defined as the result of a measurement or comparison that does notsatisfy the test or monitoring result requirements. The test or monitoring resultrequirements can require a time element.(5) Reversion(a) Reversion is defined as the system response to a failure condition that results incontinued system operation in the presence of the failure, and can result indegraded system capability.(6) MCS LRU(a) The following are defined as the MCS LRUs (i.e., those manufactured byHoneywell/Racal):•SDU•HPA.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--3C. Failure Detection and Reporting Levels(1) Failures are detected in the MCS system by a wide variety of tests. The immediateresult of failure detection is usually diagnosis of the failure to a specific component orfunctional circuit group, on a specific SRU, in a specific LRU. However, somedetected failures may only be able to be diagnosed to a suspect SRU, or only to asuspect LRU, or only to a pair or group of LRUs and the physical or logicalinterface(s) between them. Three enumerated levels of failure diagnosis are definedin Table 6-1.Table 6-1. Levels of FailureLevel DescriptionLevel IDiagnosis to the LRU level or its equivalent (e.g., a specific inactive bus, error, orwarning)Level IIDiagnosis to the SRU (module or circuit card) levelLevel IIIDiagnosis to the component or functional circuit group level or equivalent (e.g., avery specific error condition)(2) All MCS LRUs implement Level I and, where possible, Level II failure detection. LevelI diagnosis primarily supports line maintenance. Front panel displays and automaticreports to central fault/maintenance systems are only performed to Level I resolutionbecause they are primarily used to support line maintenance, which is typically limitedto LRU replacement. Level II and Level III diagnosis primarily support shop andfactory maintenance. Level II and Level III failure detection information is stored inthe LRU and system failure logs, and can be displayed on the commissioning andmaintenance terminal (CMT) pages.D. LRU Coverage(1) The LRU coverage is defined as the sum of all component failure rates covered bythe BITE circuitry within an LRU, divided by the total of the component failure rateswithin that LRU. This coverage is greater than or equal to 0.95 as defined. The LRUprobability of false detection is defined as the sum of all component failure rates ofthe BITE circuitry within an LRU divided by the total of the component failure rateswithin that LRU. This coverage is greater than 0.01 as defined. The LRU coverageincludes the following:•All SDU to avionic interfaces, where possible•All MCS inter-LRU interfaces•All power supply voltages•All battery voltages•All microprocessors/microcontrollers•All memory devices (RAM, ROM, etc).(2) All discrete drivers between the SDU and the avionics LRUs have over currentprotection and open-circuit detection.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--4E. Monitoring and Testing Functions(1) General(a) The declaration of an inactive input bus takes precedence over declaration ofone or more data word failures against the LRU driving that bus (i.e., if the bus isinactive, additional logging and reporting of low-rate failures of individual datawords on that bus are precluded). The failure and recovery criteria is set to makesure individual data word failures are not declared when the bus is inactive. Thisis typically done by setting inactive bus failure criteria (e.g., three seconds) to befaster than word update rate failure criteria (e.g., five seconds), and inactive busrecovery criteria (e.g., two seconds) to be longer than word update rate recoverycriteria (e.g., one second).(b) Unless an LRU providing ARINC 429 data declares itself to have failed, a fault isdeclared against that LRU when the ARINC 429 data is faulty. This is determinedby checking (as appropriate for each word) for data inconsistencies, dataout-of-range, uses of undefined or reserved values, and occurrences of thefailure warning state in the sign/status matrix (SSM) field.(c) Two basic types of failure detection testing performed are: functional tests andcontinuous monitoring (CM). The purpose of functional testing in the form ofpower-on self test and person-activated self test is to exercise the equipment in amanner as closely as possible to its normal operation. Failures detected duringfunctional testing are declared to be current failures until a subsequent functionaltest shows the failure condition has recovered.(d) The purpose of continuous monitoring is to test the equipment in a nondisruptivemanner while it is performing its normal operations. Such testing usually includesmonitoring the power supply voltages, temperature sensors, bias currents, inputbus activity, buffer overflow, input data failures, etc. This testing can also includeabnormal failures that cannot be tested as part of the functional testing, such asprotocol failures, processor instruction traps, data loader problems, etc.(2) Power-On Self-Test(a) General1The power-on self-test (POST) is a series of functional tests for individualLRUs; each MCS LRU performs its own internal POST upon a cold start. Acold start is defined as the response of an LRU where no retention of anypreviously stored information in any volatile memory is assumed. The powersupply provides signals to help an orderly power-down and power-upprocess for the LRU during power interrupts of any length. Primary powerinterrupts of less than 5 milliseconds duration have no effect on systemoperation. For primary power interrupts longer than 5 milliseconds and up to200 milliseconds duration, the LRU maintains normal operation, except theRF transmit and receive processes do not need to be supported in any LRUduring this interval. For primary power interrupts greater than 200milliseconds duration that causes normal operation to cease, the LRUperforms a cold start following restoration of primary power.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--52The POST sequence of tests does not terminate when an out-of-tolerancecondition is encountered. Instead, the sequence continues to complete asmany tests as possible to record all available information regarding existingfailures. An individual LRU that successfully passes POST is declared to befully functional. POST must take into account failures detected bycontinuous monitoring (i.e., if POST passes, but testing unique tocontinuous monitoring has detected and logged a current failure, then thePOST result is logged as a failure).3After executing its own POST, the SDU commands a system-wide functionaltest of the HPA(s) and ACU/BSU(s) (including the HGAs, HGA diplexer/LNA,and HPR) as applicable for the installed equipment in accordance with thesystem configuration pins (see MECHANICAL INSTALLATION). The SDUthen processes the results of the functional tests from these LRUs. The SDUcommands the functional test as follows through:•SSM field of the HPA command word(s) for the HPA•SSM field(s) for the ACU/BSU control word(s) for the ACU/BSU(s).4The BITE status from the LGA diplexer/LNA is continuously sent to the SDU,with no functional test command necessary or possible. Test results from theHGA(s), HGA diplexer/LNA, and HPR are reported by the ACU/BSU(s).5The SDU allows up to 30 ±1 seconds for other system LRUs to report theirPOST results following initiation of a system-wide functional test. If an LRUfails to report its functional test results within this time period, but otherwisemeets the ARINC 429 bus communication rate requirements, the SDUconsiders that LRU to have failed. If no ARINC 429 bus communication isreceived on a particular bus, the SDU considers that bus to be inactive.(b) Test Initiation1The correct operation of much of the internal circuitry of the SDU dependson clocks derived from the high-stability frequency reference generated bythe oven-controlled crystal oscillator (OCXO). Therefore, it is inappropriate toperform BITE tests until this clock frequency has achieved gross stability. Ifthe SDU is powered on after having stabilized at a cold external temperature(e.g., --55°C), it can take several tens of seconds for the frequency drift rateto be low enough before the phase locked oscillators (PLO) that derive thedependent clocks can lock onto the OCXO frequency reference.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--62The SDU defers testing of sensitive equipment until a positive indication ofsettling is detected, or sufficient time passes so the lack of settling itself canbe classified as a failure. Deferral of these sections of POST also result innormal operation being deferred, including access to the user interfaces(SCDU, CFDS, and CMT) and all automatic calibration processing.Consequently, the SDU suspends POST until the SDU detects the first ofthe following conditions:•OCXO heater monitor indicates it has achieved operating temperature•Power supply unit (PSU) temperature sensor indicates a reading above25 °C•Channel filter module transmit and receive PLO lock detectors bothindicate that lock has been achieved•More than 4 minutes have elapsed since primary power was applied.(c) LRU Front Panel LED and Alphanumeric Display Tests1A test of the HPA front panel LEDs is performed as a part of each POST. Ata minimum, this is made up of flashing the LEDs on and off. The LEDflashing continues until POST is completed or for 3 ±0.5 seconds. Duringthe test, the SDU tests its alphanumeric display by incorporating one ormore occurrences of the word TESTING into its display sequence to makesure all display elements are tested.(d) RF Loop Back Tests1As part of the system-wide POST, the SDU implements a RF loop back test.The RF loop back occurs in the radio frequency module (RFM) installed inthe SDU.2The SDU delays initiating the RF loop back test until it receives an indicationthe RF loop back has been activated. If the SDU fails to receive a validindication within 30 seconds following the RF loop back request, then theSDU completes its POST without executing the RF loop back test. The SDUcancels the RF loop back request when the loop back test is completed, or ifthe 30 second timer expires while waiting for verification of an active RF loopback.(3) Person-Activated Self-Test(a) The person-activated self-test (PAST) performs the same functions as POST.PAST is initiated in the HPA by pushing the PUSH-TO-TEST (PTT) switch on therespective LRU front panel. PAST can also be initiated any time through:•Respective CMT interface to the LRU•SSM field of the HPA command word sent to the HPA from the SDU.(b) A stuck switch on the CMT or LRU front panel does not cause PAST to remainactive. Any switch activity is ignored while PAST (or POST) is executing.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--7(c) The HPA inhibits PAST while the aircraft is airborne, except when PAST isinitiated through the CMT that is permitted at any time. The HPA cannot properlyfunction if it is not receiving valid command words from the SDU containing theair/ground status and command information. Under these conditions, the HPA isnot usable by the SDU. PAST is only permitted while the aircraft is on theground, or when the airborne/on-ground status is unknown. In lieu of theairborne/on-ground status information from the SDU, the HPA permits PAST asthough the aircraft is on the ground.(d) A system-wide PAST is initiated in the SDU when commanded by:•Entry through the SATCOM control and display unit (SCDU)•Entry through the central maintenance computer (CMC)•Entry through the central fault display system (CFDS)•Command from the CMT•Activating the PTT switch (SDU TEST) on the front panel.(e) A stuck switch on the SDU front panel does not cause PAST to remain active.Any switch activity is ignored while PAST (or POST) is executing.(4) Continuous Monitoring(a) Continuous monitoring (CM) of the BITE circuitry does not interfere with thenormal operation of the system. Instead any failure condition is recorded andreported. Continuous monitoring operates as a background task at all times,even during functional testing. Functional test failure codes that are identical tothe continuous monitoring codes (except for the MSB of the level 3 code)indicate cases where the functional test differs in some way from the companionCM test. Those CM failures detected during functional testing (e.g., maintenanceand status word failures) are logged as CM failures, not functional failures.F. Failure Recording(1) The SDU records CFDS internal failures at all times. The SDU only records CFDSexternal failures while receiving a valid All Call DC1 Command if a Douglas or AirbusCFDS is installed. Internal failures are defined as those internal to the SATCOMsubsystem. External failures are defined as those external to the SATCOMsubsystem. If a Boeing CMC (or no CFDS) is installed or if valid DC commands arenot available, then the air/ground status is used to generate pseudo DC states ofDC0 (aircraft on-ground) and DC1 (aircraft airborne).(2) The HPA records internal failures at all times. The HPA only records external failureswhile the aircraft is airborne, based on the status of the weight-on-wheels discrete(on-ground vs. airborne). Internal failures are defined as those that have the sameLevel I code as the LRU recording the failure (i.e., 01 for the SDU, 04 for the HGAHPA, and 07 for the LGA HPA). External failures are defined as those failures nothaving the same level 1 code as the LRU recording the failure.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--8(3) The HPA stores their functional test and CM failure records in nonvolatile memorydesignated as the LRU failure memory log. Each LRU failure memory log is capableof being interrogated and cleared. The SDU contains a nonvolatile memory thatserves as a system failure memory log. Functional test results supplied by theHPA(s), ACU/BSU(s), LGA diplexer/LNA, and the SDU itself are recorded in thissystem failure memory log. The system failure memory log is capable of beinginterrogated and cleared for each LRU individually. Each LRU failure memory log andthe system failure memory log is capable of recording at least 1000 failures.(4) The HPA and other system LRUs supply failure information to the SDU for storage inthe system failure memory log. In the absence of any detected failures during a flightleg, the SDU records the flight leg counter, flight number, ICAO address, date, andGreenwich Mean Time (GMT) at the flight leg transition. The SDU also records theaircraft identification for display on the SCDU and CFDS maintenance pages.(5) Class -- The SDU declares and stores the classification (Airbus/Douglas CFDS) offailure (one, two, three) for each entry in this field.•Class 1 failures are indicated in flight to the crew by the CFDS because they haveoperational consequences for the current or next flight(s).•Class 2 failures are not automatically indicated in flight to the crew by the CFDSbecause they have no operational consequences for the current or next flight(s),but are indicated to the crew on the ground because they cannot be leftuncorrected until the next routine scheduled maintenance check.•Class 3 failures are not indicated to the flight crew because they can be leftuncorrected until a routine scheduled maintenance check. An accumulation ofClass 3 failures can lead to a Class 2 or Class 1 failure.•Aircraft Identification -- The aircraft identification (i.e., the tail number) is made upof nine alphanumeric characters. The SDU obtains the aircraft identification fromthe CMC or CFDS through ARINC labels 301, 302, and 303 (if available).G. Failure Reporting(1) General(a) Active failures include those internal and external failures deemed to be currentlyfailing while the aircraft is on the ground or airborne. Unlike failure recording thatexcludes recording external failures while on the ground, failure reporting has itsown set of criteria as specified in the following paragraphs.(2) HPA Failure Reporting(a) General1The HPA reports its functional test/CM failure status by lighting its front panelLEDs, and through communication to the SDU.(b) HPA Front Panel Indicators and Controls1The HPA indicators and controls are given in Table 6-2.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--9Table 6-2. HPA Indicators/ControlsIndicator/Control DescriptionPASS LED Shows green after a test, if no failures are detected in the HPAFAIL LED Shows red after a test, if failures are detected in the HPAPUSH--TO--TEST (PTT) Push this button to start a test of the HPA(c) HPA Front Panel LEDs1Functional testing effectively controls the on/off state of the front panel LEDsduring the period beginning with initiation of the functional testing(POST/PAST), through execution of the functional test sequences (includingLED testing), and up to and including the indication of the test results on theLEDs. Continuous monitoring exclusively controls the LEDs at all othertimes.2The green LED (PASS) lights for 30 ±5 seconds at the conclusion of thefunctional test sequences if both of the following are true:•The HPA determines there are no currently active CM failures having itsown Level I code (i.e., 04 or 07, as applicable)•No functional test failures have been detected with its own Level I code.3There must be no known failures in order to light the green LED as thefunctional test indication.4The red LED (FAIL) lights continuously during the functional test indicationphase and through the transition to the CM indication phase, if the HPAdetects at least one currently active CM failure with its own Level I code. Ifthe HPA detects only functional test failures (i.e., no CM failures arecurrently active), the red LED lights for 30 ±5 seconds and is then turnedoff.5The red LED also lights as long as the failure persists, if the HPA detectsany CM failure that has its own Level I code while continuous monitoring iscontrolling the LEDs. Otherwise, both LEDs are turned off. Continuousmonitoring itself never causes the green LED to light. The presence orabsence of functional test failures does not affect the CM indication.(d) HPA-SDU Communication1The HPA communicates its functional testing/CM failure status to the SDUthrough the HPA maintenance and status words. The HPA only indicates aFW SSM state in its maintenance and status words, and active discretefailure bits in its maintenance word. Since no failures unique to functionaltesting activate the SSM FW state or the discrete failure bits in themaintenance word, no functional test failures need to be latched until thenext functional testing sequence.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--102For certain failures detected during continuous monitoring, the appropriatediscrete failure bits and the SSM FW state are set within the maintenanceand status words as long as the failure persists.(3) SDU Failure Reporting(a) General1The SDU reports its functional testing/CM failure status and all other systemLRUs by:•Activating its alphanumeric display•Communicating to the SCDU, CMC, CFDS, and CMT interfaces.2The alphanumeric display indicates all applicable failure conditions with noregard to:•Any type of internal/external failure differentiation•Any CFDS failure class distinctions•Which LRU detected a failure (either the SDU itself or one of the reportingLRUs in the SATCOM subsystem).3The SDU delays reporting the results of the functional test sequence for aperiod of 5 seconds. This gives continuous monitoring the opportunity toperform its unique tests during the delay period, and include any current CMfailures in the test report. The SDU takes a snapshot at the end of thefunctional test delay period to include all currently active CM failures inaddition to all failures detected during functional testing. The functional testdelay period applies to the SDU alphanumeric display, the SCDUmaintenance pages, the CFDS pages, and the CAIMS and CMC faultsummary words, but not to the CMT.(b) SDU Front Panel Indicators and Controls1The SDU indicators and controls are given in Table 6-3.Table 6-3. SDU Indicators/ControlsIndicator/Control DescriptionSDU TEST Push this button to initiate a system--wide SATCOM testSYSTEM STATUS DISPLAY Shows data defining the SATCOM system configuration and theidentification of all SATCOM components that are not operating as requiredMANUAL SCROLL Push this button to scroll through the messages on the system statusdisplayRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--11(c) Front Panel Alphanumeric Display and MANUAL SCROLL Button1GeneralaThe alphanumeric display makes it easy for the maintenance personnelto identify which system LRU has failed. The alphanumeric display isblank unless specifically activated for temporary display of failuremessages and other status information. The alphanumeric display isalso kept blank under conditions of extreme temperatures. The displayis not intended to be started when its temperature is less than --5 °C, orgreater than +30 °C. The alphanumeric display is started during the LEDtest portion of the functional test sequence. After the functional testdelay period, and any time during continuous monitoring, thealphanumeric display can be started by pushing the MANUAL SCROLLbutton.bThe operator can scroll the alphanumeric display through the entireapplicable message sequence by repeatedly pushing the MANUALSCROLL button within 30 5 seconds after the display is started. Oneleft-justified 20-character (or less) message is displayed each time theMANUAL SCROLL button is pushed. When the end of the displaysequence is reached (i.e., END OF LIST), the next actuation of theMANUAL SCROLL button returns the alphanumeric display to the top ofthe display sequence, enabling the operator to scroll through thesequence again. Message scrolling is performed according to thefollowing sequence:•One of four possible system/SDU pass/fail messages•All applicable Level I failure messages•LRU part number messages (up to four lines)•ORT identification message•ENDOFLISTmessage.cIftheMANUALSCROLLbuttonisinactivatefor30±5 seconds at anypoint during the display sequence, the alphanumeric display is blankedand any display sequence in progress is aborted. At the same time, oneor both of the front panel LEDs (as appropriate) are turned off if theywere exclusively indicating functional test failures with no current CMfailures.2SYSTEM/SDU PASS/FAIL MessageaThis one-line message, which summarizes the overall functional test orCM status, takes on one of four possible states:•SDU PASS SYS PASS•SDU PASS SYS FAIL•SDU FAIL SYS PASS•SDU FAIL SYS FAIL.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--123Level I Failure MessagesaThis section lists all the applicable Level I failure messages that can bedisplayed on the alphanumeric display, along with the appropriate LRUor control bus input. These messages are listed in failure code order inTable 6-4. For the functional test display, the message list includes allthe active failures in the snapshot and the list is static.bFor continuous monitoring, the message list includes all currently activeCM failures. The presence or absence of functional test failures doesnot affect the CM message list. The failure message list for the CMdisplay is potentially dynamic.cDuring continuous monitoring, if a new CM failure becomes activeduring the scroll sequence, the respective message appears at itsproper location in the sequence according to its Level I code. Thisoccurs either during the current scroll sequence if that Level I code hasnot yet been reached, or during the next scroll sequence if the failure isstill active. If a CM failure recovers during a scroll sequence, itsmessage does not appear in any subsequent scroll sequence, even if ithad appeared earlier. If a CM failure recovers while its particularmessage is currently being displayed, the message continues to bedisplayed until the MANUAL SCROLL button is activated or until thetime-out period expires.Table 6-4. Level 1 Failure MessagesLevel 1Code Failure Message DescriptionAES LRU Failures:00 (not applicable) Unknown Level I failure01 SDU SDU failed02 OTHER SDU Other SDU (of a dual system) failed04 HPA--HI GAIN High Gain Antenna HPA failed07 HPA--LO GAIN Low Gain Antenna HPA failed0A HI POWER RELAY HPR (antenna system) failed0D DLNA--(TOP/L) Top/Port Diplexer/Low Noise Amplifier failed0F DLNA--R Starboard Diplexer/Low Noise Amplifier failed10 DLNA--LO GAIN LGA Diplexer/Low Noise Amplifier failed13 BSU--(TOP/L) Top/Port BSU or ACU failed15 BSU--R Starboard BSU failed1A HI GAIN ANT--(TOP/L) Top/Port HGA failedRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--13Table 6-4. Level 1 Failure Messages (cont)Level 1Code DescriptionFailure Message1C HI GAIN ANTENNA--R Starboard HGA failed1F LO GAIN ANTENNA LGA failed21 SCDU1 No. 1 SCDU failed22 SCDU2 No. 2 SCDU failed23 SCDU3 No. 3 SCDU failedNon-AES LRU Failures:33 (ACARS MU/CMU)1 No. 1 AFIS/ACARS unit failed34 (ACARS MU/CMU)2 No. 2 AFIS/ACARS unit failed35 IRS1 No. 1 IRS failed36 IRS2 No. 2 IRS failed37 IRS3 No. 3 IRS failed38 IRS4 No. 4 IRS failed39 (CFDIU/CMC) CFDS/CMC failed3D FMC1 No. 1 FMC failed3E FMC2 No. 2 FMC failed40 ARINC 429 ICAO ADDR 429 ICAO address source failed41 (not applicable) Discrete cockpit indicators failed42 CTU Cabin file server/cabin packet data function failed43 (CFS/CPDF) Cabin telecommunications unit failedInactive BITE Bus Input to SDU from other LRU:52 (CFS/CPDF)/SDU Cabin file server/cabin packet data function bus53 (ACARS MU/CMU)1/SDU No. 1 AFIS/ACARS unit bus54 CTU/SDU CEPT--E1 bus from the CCS55 SCDU1/SDU No. 1 SCDU bus56 SCDU2/SDU No. 2 SCDU bus57 (ACARS MU/CMU)2/SDU No. 2 AFIS/ACARS unit bus59 (CFDIU/CMC)/SDU CFDS bus5A IRS--PRI/SDU Primary IRS bus5B IRS--SEC/SDU Secondary IRS busRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--14Table 6-4. Level 1 Failure Messages (cont)Level 1Code DescriptionFailure Message5C HPA--HI GAIN/SDU High Gain Antenna HPA bus5F HPA--LO GAIN/SDU Low Gain Antenna HPA bus62 BSU--(TOP/L)/SDU Top/port BSU bus64 BSU--R/SDU Starboard BSU bus65 (not applicable) Radio Management Panel bus66 SCDU3/SDU No. 3 SCDU bus67 TP1AB/SDU MP9EF Data bus from RFU to SDU (BITE signaling)68 TP1EF/SDU MP9JK CEPT--E1 from RFU to CTU through SDU6A TP1JK/SDU MP10CD ST--Bus data from RFU to SDU (overflow digital audio)6C TP3CD/SDU MP10GH ST--Bus C2clock from RFU to SDU (overflow digital audio)6D TP3EF/SDU MP10JK ST--Bus F0frame from RFU to SDU (overflow digital audio)71 OTHER SDU/THIS SDU Bus from other SDU in a dual system73 FMC1/SDU No. 1 FMC bus74 FMC2/SDU No. 2 FMC busInactive Bus Inputs to other LRU:80 SDU MP9GH/RFU TP1CD Data bus to RFU from SDU (control)82 CTU/SDU MP10AB CEPT--E1 bus from CTU to RFU through SDU88 SDU MP10EF TP3A/B ST--Bus data from SDU to RFU (overflow digital audio)90 SDU M--CTRL/HPA--HI Multicontrol bus to HGA HPA from SDU96 SDU M--CTRL/HPA--LO Multicontrol bus to LGA HPA from SDU98 SDU M--CTRL/BSU--(T/L) Multicontrol bus to top/port BSU from SDU9A BSU--R XTALK/BSU--L Crosstalk bus to port BSU from starboard BSU9C SDU M--CTRL/BSU--R Multicontrol bus to starboard BSU from SDU9D BSU--L XTALK/BSU--R Crosstalk bus to starboard BSU from port BSUMiscellaneous Failures:C0 WRG:STRAPS/SDU System configuration pins errorC1 WOW1/WOW2/SDU Weight on wheels discrete inputs disagreeC2 SDU DUAL SEL/DISABLE Dual system discrete inputs disagreeC3 WRG:ICAO ADDR/SDU ICAO address straps errorRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--15Table 6-4. Level 1 Failure Messages (cont)Level 1Code DescriptionFailure MessageC4 TX PATH VSWR--HI GAIN Excessive VSWR load at HGA HPA outputC5 WRG:STRAPS/SDU ORT Configuration pins and ORT settings disagreeC6 TX PATH VSWR--LO GAIN Excessive VSWR load at LGA HPA outputC7 HPA--HI GAINOVERTEMPOver temperature in HGA HPAC8 BAD GROUND STATION Invalid GES frequency commandC9 HPA--LO GAINOVERTEMPOver temperature in LGA HPACA SDU/DLNA--LO GAIN LGA LNA control driver SDUCB WRG:SDI/HPA--HI GAIN(see NOTE)HGA HPA identification strapped incorrectlyCC WRG:SDI/HPA--LO GAIN(see NOTE)LGA HPA identification strapped incorrectlyCD SDU (POC/TOTC) SDU power-on counter or total-on-time counter has been resetCE RFU (POC/TOTC) RFU power-on counter or total-on-time counter has been resetCF HPA--HI (POC/TOTC) HGA HPA power-on counter or total-on-time counter has beenresetD0 HPA--LO (POC/TOTC) LGA HPA power-on counter or total-on-time counter has beenresetD1 WRG:SDI/HPA--HI GAIN(see NOTE)HGA HPA identification strapped incorrectlyD2 WRG:SDI/HPA--LO GAIN(see NOTE)LGA HPA identification strapped incorrectlyD3 WRG:SDI/BSU--(T/L) Top/Port BSU identification strapped incorrectlyD4 WRG:SDI/BSU--R Starboard BSU identification strapped incorrectlyD5 HPA--HI GAIN COAX HGA HPA input coax cableD6 HPA--LO GAIN COAX LGA HPA input coax cableD7 SDU COAX RFU input coax cableD8 DLNA/(SDU)--(T/L) Top/Port HGA LNA coax cable output to RFU or SDUD9 DLNA/(SDU)--R Starboard HGA LNA coax cable output to RFU or SDUDA DLNA/(SDU)--LO GN LGA LNA coax cable output to RFU or SDUDB LO GAIN SUBSYSTEM LGA log--on functional test failure or could not initiate testRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--16Table 6-4. Level 1 Failure Messages (cont)Level 1Code DescriptionFailure MessageDC NO ACTIVE MU/CMU At least one (C)MU is communicating, but none have declaredthemselves activeDD SDU OWNERREQS--SECDError in the secured ORT partitionDE SDU OWNERREQS--USERError in the user ORT partitionDF HI GAIN SUBSYSTEM Slave HGA log--on functional test failure or could not initiate testE0 COAX/SDU SDU input coax cable from RFUFE PWR SUPPLYINTERRUPTSDU had an in-flight primary power interruptUndefined:Others LEVEL 1 FAULT XX XX is the Level 1 failure code (undefined)NOTE: The front panel display messages associated with failure codes CBx and CCx (WRG:SDI/HPA HI--GAIN andWRG:SDI/HPA LO--GAIN, respectively) are identical to the messages raised for failure codes D1x and D2x,respectively. This use of a single front panel display message for multiple failure codes (where the CB/CCxcodes reflect detection by the HGA/LGA HPA of an invalid HPA SDI strap condition, while the D1/D2x codes aregenerated by the SDU in response to a report from the HGA/LGA HPA of having detected an unexpected SDIcode) is deliberate, and results from alignment of the front panel display messages with their CFDS/CMCcounterparts. Because of this approach, it is possible (in this specific case) for an operator to receive twoconsecutive front panel display messages that are the same.4LRU Identification (Part Numbers) ElectronicallyaFollowing the display of all Level I failure messages, a list of theavailable LRU end-item part numbers is displayed. This list only includespart numbers for those LRUs present in the given installation as definedby the system configuration pins (see MECHANICAL INSTALLATION).For an installed LRU whose end-item part number is not available,dashes are displayed in place of the part number (e.g., HPL___________). The list of part numbers are displayed in the order given inTable 6-5.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--17Table6-5. ListofPartNumbersLRU Part No.SDU SDbbbbbbb--hhsss--nnHGA HPA HHbbbbbbb--hhsss--nnIGA HPA IHbbbbbbb--hhsss--nnLGA HPA LHbbbbbbb--hhsss--nnNOTES:1. bbbbbbb represents the seven-digit LRU end-item base part number.2. hh represents the two-digit LRU end-item hardware configuration number.3. sss represents the three-digit LRU end-item software configuration number.4. nn represents the two-character LRU end-item software modification level (possibly including space, dashcharacters, and alpha characters).bFor Honeywell/Racal LRUs, the three-digit LRU hardware configurationnumber must be entered manually through the CMT interface for validdata to be available for display. This data is stored during LRU end-itemtesting. All other numbers reside within the LRU software. All numbersare communicated to the SDU by Honeywell/Racal HPA(s) through thepart number block transfer. For non-Honeywell/Racal interfacing HPAs,no such data is available to the SDU, therefore, dashes are displayedfor the HPA end-item part number.5Part Number Block FormataThe information contained in the part number block is required fordisplay on the CMC/CFDS MCDU, SCDU, CMT, and the SDUalphanumeric display. The information must be in the specified format(i.e., character restrictions or only digits and field length) for properdisplay. The part number block transfer is made up of:•Seven-digit end-item base part number•Two-digit end-item hardware configuration number (the first part ofthe end-item dash number, which also reflects the boot PROMsoftware version).•Three-digit software configuration number (the latter part of theend-item dash number, which only reflects the version of uploadedsoftware)•Two-letter (uppercase) hardware modification level•Two-letter (uppercase) software modification level•Eight-digit LRU serial number•Four-hexadecimal character LRU program store CRC code•Two-hexadecimal character hardware/software compatibility strap.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--186ORT IdentificationaFollowing the display of the LRU end-item part numbers, the user ORTidentification is displayed as specified:•ORT ID--XXXXXXXXXXXXX (first line)•XXXXXXXXXXX--MODIFIED (second line, after another activation ofthe MANUAL SCROLL button).bWhere XXXXXXXXXXXXXXXXXXXXXXXX represents the 24-characterdescription contained in the user ORT description field. The user ORTdescription field is used to annotate a particular set of ORT items toidentify one from another (e.g., NORTH PACIFIC ROUTE, SOUTHATLANTIC ROUTE, 747--400 ASIAN ROUTE, 777 ASIAN ROUTE).Alternatively, this item could contain a software identification (e.g., asoftware part number for the user ORT as a released entity).cThe MODIFIED flag is only displayed if the state of the user ORTmodified flag indicates any item in the user ORT has been modifiedsince the user ORT was created. When any user ORT item is modifiedby the SDU software, either directly or indirectly, the user ORT modifiedflag is set to MODIFIED. If the state of the user ORT modified flag isunmodified, the MODIFIED flag is not displayed. The state of the userORT modified flag is never set to unmodified by the SDU software.dThe next two pushes of the MANUAL SCROLL button present the sameinformation for the Secured ORT partition.7EndOfListMessageaThe END OF LIST message is displayed at the end of the display listafter the ORT identification.H. Miscellaneous BITE Requirements(1) The typical retention period for the BITE memory is at least five years at 25 °C. Theworst case retention period is at least one year at 50 °C. If batteries are used tosupply backup power for the BITE memory, the typical battery lifetime should be atleast 10 years at 25 °C. The worst case lifetime is at least two years at 50 °C.(2) Each system LRU has a total on-time clock (TOTC) to accumulate and record theamount of time the LRU has been powered up. The TOTC has a 10 minuteresolution, and is capable of accumulating and recording a count of at least 200,000hours.(3) The TOTC value is capable of being examined, and of being reset to 0:00 throughthe CMT. Any manual TOTC reset, or any automatic TOTC reset (e.g., upondetection of corruption of its value), results in an automatic entry of the event into theLRU failure memory log and the SDU system failure memory log. The TOTC hoursare capable of being automatically entered into the LRUs maintenance activity log.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--19I. Maintenance Activity Log(1) A maintenance activity log is stored in each system LRU. The maintenance activitylog is made up of the six most recent maintenance activity records (MAR). Each MARcan be entered through the CMT. Information is stored in the MAR as shown inTable 6-6 and in the order listed.Table 6-6. MAR InformationField Size RangeDocument Number 16 ASCII Characters a--z, A--Z, 0--9Date (yymmdd) 6 ASCII Numerics yy 00--99mm 01--12dd 01--31Location 32 ASCII Characters a--z, A--Z, 0--9Phone Number 18 ASCII Numerics 0--9Total On-Time Clock (Hours) 6 ASCII Numerics 0--200,000(2) The fields are defined as follows:•Document number -- The document number has up to 16 alphanumericcharacters. The intent of this field is to supply maintenance activity traceability.•Date field -- The date field is made up of six numeric characters in the format ofyymmdd, where yy represents the year, mm represents the month, and ddrepresents the day. This field is entered automatically by the SDU as determinedby its internal real-time clock (RTC); it is entered manually for the HPA. The intentof this field is to record the date the maintenance activity was performed.•Location field -- The location field has up to 32 alphanumeric characters. Theintent of this field is to indicate the place where the LRU maintenance service wasperformed.•Phone number field -- The phone number field is made up of 18 numericcharacters. The intent of this field is to supply a phone number of who performedthe LRU maintenance. This phone number should include the combination ofcountry code, area code, and local phone number.•Total on-time clock field -- The TOTC field is made up of six numeric charactersrepresenting hours. This field is entered automatically by the LRU as determinedby the internal TOTC.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--202. SATCOM Control and Display UnitA. General(1) The SATCOM Control and Display Unit (SCDU) menu formats obey the acceptedindustry standards for multifunction (multipurpose) control and display units (MCDU).The following paragraphs describe the SCDU display layout and terminology used todescribe the display, font size conventions, scratchpad usage, format, keyboardusage, display symbols, and update rates.B. SCDU Display Terminology and Basic Operation(1) General(a) The SCDU display is made up of 14 lines of 24 characters. The top line (line 1) isreferredtoasthetitlelineandthebottomline(line14)isreferredtoasthescratchpad. Lines 2 thru 13 are arranged into six pairs having a label line anddata line. The SDU communicates to the SCDU for all data to be displayed ingreen. The color displayed on the MCDU depends on how the MCDU respondsto this communication.(b) There are six line select (LS) keys on each side of the SCDU display designatedleft (L) and right (R) and numbered 1 to 6 from top to bottom. The LS keys areassociated with a pair of display lines where the upper line of a pair is the labelline and the lower line is the data line. The LS key/line pair relations are given inTable 6-7.(c) The SCDU can display a large and small font size. Different character fonts arenot shown in the example SCDU page figures given in this section. The use oflarge font is indicated by the presence of uppercase letters in the SCDU pagefigures, while the use of small fonts are demonstrated by lowercase letters. Ingeneral, page names displayed in the title line are in large font. For pages wherep/t is specified to be displayed in the title line, the p/t is in small font. Dataentered into the scratchpad is displayed in large font. Data in the label lines isdisplayed in small font, while data in the data lines is displayed in large font.Numerical character font sizes cannot be shown in the figures, but their fontsizes follow the same conventions.Table 6-7. LS Key/Line Pair RelationsLS Keys Display Lines1L -- 1R 2 and 32L -- 2R 4 and 53L -- 3R 6 and 74L -- 4R 8 and 95L -- 5R 10 and 116L -- 6R 12 and 13RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--21(d) Labels on the left side of the SCDU display are displayed beginning in column 2of the label line. Data on the left side is left-justified in the data line. Labels anddata on the right side of the SCDU display is right-justified. This is the caseunless specified otherwise.(2) Scratchpad(a) General1The scratchpad is used for data entry and displaying SDU generatedmessages. Pushing an alphanumeric key on the keypad (0 through 9, Athrough Z, +/-- [plus or minus], / [slash, space]) enters that character into thescratchpad. The scratchpad is not used for fixed format display purposes.The mechanism used for data entry is described below.(b) Data Entry1When the user types the appropriate characters using the SCDU keypad,the characters are echoed on the scratchpad. After data entry, the user mustpush the appropriate LS key adjacent to the data field where the data is tobe displayed. The SDU then checks the data for format and acceptability(out-of-range, entry not permitted into the field, etc). If the data is incorrect,the SDU leaves the previous data in the field and displays the appropriateerror message in the scratchpad. If any LS key is pushed adjacent to ablank or nonselectable field, the scratchpad message 1 (i.e., NOTALLOWED) is issued. If the entry was rejected because an incorrect LS keywas pushed, the entry is accepted if the correct LS key is subsequentlypushed.(c) Scratchpad Message1If the SDU determines a data entry does not conform to format oracceptability requirements after an entry is attempted, the SDU issues ascratchpad message prompting the user for the correct data. The user canclear a scratchpad message by using the clear (CLR) key, or by enteringdata into the scratchpad over the message.(d) CLR and DEL Keys1GeneralaThe CLR and delete (DEL) keys are used to clear the scratchpad andalter the data fields. Generally, for MCDUs that have only a CLR key(e.g., Airbus and Douglas) the scratchpad is cleared and the data fieldsare altered by using this key. For MCDUs that have both CLR and DELkeys (e.g., Boeing), the scratchpad is cleared using the CLR key, whilethedatafieldsarealteredusingtheDELkey.2CLR KeyaPushing the CLR key clears the scratchpad message. When thescratchpad contains user-entered characters, momentary actuation ofthe CLR key clears the last entered character, while continual actuationof the CLR key clears the entire contents of the scratchpad.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--22bWhen the scratchpad is empty, pushing the CLR key causes CLR to bedisplayed in the scratchpad indented five spaces. If an LS key is pushedand the field adjacent to the LS key is specified to be either erasable(e.g., an unprotected number) or a default maintained value (e.g.,protected number priorities), the field is cleared or reverts back to itsdefault value, as applicable.cFor compatibility with the Boeing 777 AIMS/CDU, the SDU clears theentire scratchpad when the CLR command is received with the repeatbit set.3DEL KeyaTheDELkey(ifavailable)canbeusedtoclearorrevertthedatafields.Pushing the DEL key causes no response when the scratchpad is notempty, except for either an SDU issued error message or pilot-enteredcharacters.bWhen the scratchpad is empty, pushing the DEL key causes DELETE tobe displayed in the scratchpad.NOTE: Pushing the DEL key again does not clear DELETE from thescratchpad. Instead, pushing the CLR key when DELETE isdisplayed in the scratchpad clears DELETE.cIf an LS key is pushed and the field adjacent to the LS key is specifiedto be either erasable (e.g., an unprotected number) or a defaultmaintained value (e.g., protected number priorities), the field is clearedor reverts back to its default value, as applicable.dWhen the scratchpad contains CLR indented five spaces as the result ofthe CLR key being pushed with an empty scratchpad and the DEL keyis subsequently pushed, the SDU replaces CLR with DELETE in thescratchpad.(e) NEXT PAGE and PREV PAGE Keys1GeneralaPushing the NEXT PAGE and PREV PAGE (if available) function keyson the SCDU keypad causes the SDU to display the next page, orprevious page of the display sequence where appropriate (i.e., when p/tis displayed in the title line).2NEXT PAGE KeyaPushing this key causes the next page in the sequence to be displayed.If the last page in a multiple page sequence is displayed and the NEXTPAGE key is pushed, the first page is displayed. The SDU ignores thiskey if the key is pushed when p/t is not displayed, or if a p/t display isthe value 1/1.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--233PREV PAGE KeyaPushing this key causes the previous page in the sequence to bedisplayed. If the first page in a multiple page sequence is displayed andthe PREV PAGE key is pushed, the last page is displayed. The SDUignores this key if the key is pushed when p/t is not displayed, or if a p/tdisplayisthevalue1/1.(f) Special Symbols1When displayed, special symbols are defined as given in Table 6-8.Table 6-8. Special SymbolsSymbol Description* (Asterik)Pushing the LS key adjacent to this symbol (when it appears) causes anaction of some kind to occur (e.g., making a phone call, sorting a phonelist, or initiating log-off).[](Brackets)Empty brackets prompt the user for data entry into the field. However, dataentry is not mandatory. Brackets surrounding data indicate the data isunprotected and can be modified or deleted. Not all fields modifiable aresurrounded by brackets. When brackets are used to enclose existing data,as opposed to prompting entry of data into an empty field, they areintended as an indication the data is unprotected (i.e., an unprotectedphone number). Conversely, protected phone numbers do not havebrackets, indicating the phone number cannot be modified or deleted.<,>(Carets)A caret adjacent to an LS key indicates if the key is pushed the displaychanges to a new page. The new page is either the one indicated next tothe caret or, in case of RETURN>, the higher level page.<SEL>Indicates the data in the field is currently selected (e.g., the selected GESor antenna).(g) Updates1Dynamically generated display fields, whose contents have changed, areupdated by the SDU both periodically (at a rate of at least 1 Hz), and uponcompletion of an LS key action that could have caused the display or thedisplay field to change. With multiple SCDU configurations, the SDU onlymaintains one version of each page for display. The SDU responds to LSkey actuations from all SCDUs in a serial fashion and updates the displaypage(s). Each SCDU scratchpad and the channel selection fields areindependent from all others, allowing each user to perform independentactions.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--24C. SCDU Page Hierarchy(1) The SCDU page hierarchy is shown in Figure 6-2. The SATCOM MAIN MENU pageis accessed by pushing the LS key adjacent to <SAT for single SDU installations.Highlighted blocks in Figure 6-2 represent maintenance pages that are discussed indetail in paragraph D. Refer to the appropriate MCS SATCOM System Guide foradditional non highlighted SATCOM displays.D. SCDU Pages(1) SATCOM MAIN MENU Page(a) Access to this page is from the MCDU MAIN MENU page. The purpose of thispage is to display call status information, to make, answer, and terminate calls,and to supply access to lower level pages. See Figure 6-3 for example pages.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--25Figure 6-2. SATCOM SCDU Page HierarchyRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--26Figure 6-3. SATCOM SCDU Main Menu PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--27(2) SATCOM SUBMENU Page(a) Access to this page is from the SATCOM MAIN MENU page. The purpose of thispage is to display the current log-on state, to supply a way of entering anddisplaying flight identifier, and to supply access to the SATCOM LOG-ON,SATCOM CHANNEL STATUS, and SATCOM MAINTENANCE (or, if applicable,DATA LOADER MENU) pages. When in a dual system, access to the DUALSYSTEM STATUS menu page is supplied. See Figure 6-4 for example pages.(3) SATCOM MAINTENANCE Pages(a) General1An example SATCOM MAINTENANCE page for non-Airbus/Douglas CFDSequipped aircraft is shown Figure 6-5.2The SATCOM MAINTENANCE pages menu selection, subject to ORT itemiv (refer to SYSTEM OPERATION), is accessible from the SATCOMSUBMENU page only on non-Airbus/Douglas CFDS equipped aircraft. InAirbus and Douglas configurations, these pages are accessed through theCFDS.3The purpose of these pages are to display SATCOM maintenance data. In adual system, the maintenance data pertains to the system from which thedisplay pages are being supplied (SAT 1 or SAT 2).4The display format and functionality for the SATCOM maintenance pages(i.e., for the SAT--N, LAST LEG REPORT, PREVIOUS LEGS REPORT, LRUIDENTIFICATION, LAST LEG CLASS 3 FAULTS, TEST, TROUBLESHOOTDATA, GROUND TROUBLESHOOT DATA, GROUND REPORT, andCONFIGURATION DATA pages) is the same as defined for the CFDSinteractive mode maintenance pages with the exception of the following:•The RETURN> prompt is displayed on the right adjacent to the 6R key,as opposed to the left.•The SDU issues scratchpad message 1 (i.e., NOT ALLOWED) if any LSkey is pushed adjacent to a blank or display-only field.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--28Figure 6-4. SATCOM SUBMENU PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--29Figure 6-5. SATCOM MAINTENANCE Page5Access to SATCOM maintenance displays are as follows:•Push LS key 1L to show the Last Leg Report page (see Figure 6-10)•Push LS key 2L to show the Previous Leg Report page (see Figure 6-11)•Push LS key 3Lto show the LRU Identification page (see Figure 6-12)•Push LS key 5L to show the Trouble Shooting Data page (seeFigure 6-13)•Push LS key 6L to show the Configuration Data page (see Figure 6-8)•Push LS key1R to show the Last Leg Class 3 Faults page (seeFigure 6-14)•Push LS key 2R to show the Test page (see Figure 6-6)•Push LS key 3R to show the Data Loader Menu page (see Figure 6-9)•Push LS key 5R to show the Ground Report page (see Figure 6-15).(b) TEST page1For software packages prior to D2.0, if a system-wide functional test (i.e.,PAST) is initiated from the SCDU interface (i.e., by pushing the 2R key onthe SATCOM MAINTENANCE page), the first access of the SATCOMsubsystem from an SCDU MAIN MENU page after the POST/PAST ResultsDelay period causes the TEST page to be shown with the status of thecurrent failures. However, the TEST page shows the TEST IN PROGRESS60S message if this first access occurs during the POST/PAST ResultsDelay period. If the SATCOM subsystem is not accessed within 5 minutes ofthe completion of an SCDU-initiated PAST, the page hierarchy is reset to itsoriginal structure as shown in Figure 6-2.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--302When the 2R key is pushed on the SATCOM MAINTENANCE (i.e., SAT--N)page, the SDU initiates a PAST and the page display temporarily goes to theTEST page where TEST IN PROGRESS 60S is displayed. However, theSCDU eventually times out the SATCOM subsystem and takes back controlof the display. This is due to the fact that for SCDU-accessed maintenancepages, the SDU interfaces directly with the SCDU (as opposed to goingthrough the CFDIU) and is unable to maintain proper bus activity (which theCFDIU normally does) during initial execution of the PAST.3To display the test results, the user must reselect the SATCOM system bypushing the LS key adjacent to the <SAT prompt on the SCDU MAIN MENUpage, where the initial page shown is the TEST page. If the user does notreselect the SATCOM system on the SCDU MAIN MENU page after 5minutes of completion of PAST, the page hierarchy resets to its originalstructure as shown in Figure 6-2.4The TEST IN PROGRESS 60S message during the POST/PAST ResultsDelay period is required to prevent the display of premature test results, i.e.,to permit continuous monitoring sufficient time to add its contribution to thePOST/PAST results.(4) TEST Menu Page(a) General1Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE)page by pushing LS key 2R. The purpose of this page is to initiate a PAST,to enable/disable a voice loopback on a selected (physical) channel, toenable/disable a test of the cockpit voice call light for a selected (logical)channel, and activation of the cockpit voice go-ahead chime test. SeeFigure 6-6 for example pages.(b) Data Fields1Line 3aThis line displays SELF-TEST beginning in column 1. The asteriskprompt is not displayed if the aircraft is airborne.bIf the LS key 1L is pushed when the SELF-TEST asterisk prompt isshown, the system activates a PAST.2Line 4aThis line displays MP2ABCD VOICE LOOPBACK beginning in column2. Pushing LS key 2l configures the SATCOM system to perform anaudio loopback test of flight deck channel 1.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--31Figure 6-6 (Sheet 1). TEST PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--32Figure 6-6 (Sheet 2). TEST PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--333Line 5aThis line displays the message ENABLE beginning in column 1 whenthe test is not active. The asterisk prompt is displayed and the testallowed only if the log--on state is Standby. This line displays *DISABLE<ACTIVE> beginning in column 1 when the test is active. If the log--onstate changes from Standby to any other state while the test is active,thetestisterminated.Thecommandsonlines4and5areshownonlyifthe configuration straps indicate this channel is wired for headset use.bPushing LS key 2L when the ENABLE asterisk prompt is shown causesthe voice channel selected to be activated into an analog loopback teststate. Pushing LS key 2L when the DISABLE prompt is shown causesthe voice loopback test state to be terminated.4Line 6aThislinedisplaysMP8ECALLLIGHTTESTbeginningincolumn2.Pushing LS key 3L initiates a lamp test of the flight deck channel 1 calllamp.5Line 7aThis line displays *ENABLE beginning in column 1 when the test is notactive. The asterisk prompt is shown and the test allowed only if thelog--on state is Standby. This line displays *DISABLE <ACTIVE>beginning in column 1 when the test is active. If the log--on statechanges from Standby to any other state while the test is active, the testis terminated. The commands on lines 6 and 7 are shown only if theconfiguration straps indicate this channel is wired for headset use.bPushing LS key 3L when the ENABLE asterisk prompt is shown causesthe cockpit voice call light to be activated for a steady indication(regardless of the state of configuration pin TP13C). Pushing LS key 3Lwhen the DISABLE prompt is displayed causes the cockpit voice calllight test to be terminated.6LIne 8aThis line displays MP2EFGH VOICE LOOPBACK beginning in column2. Pushing LS key 4L configures the SATCOM system to perform anaudio loopback test of flight deck channel 2.7Line 9aThis line displays ENABLE beginning in column 1 when the test is notactive. The asterisk prompt is shown and the test allowed only if thelog--on state is Standby. This line displays *DISABLE <ACTIVE>beginning in column 1 when the test is active. If the log--on statechanges from Standby to any other state while the test is active, the testis terminated. The commands on lines 8 and 9 are displayed only if theconfiguration straps indicate this channel is wired for headset use.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--34bPushing LS key 4L when the ENABLE asterisk prompt is displayedcauses the voice channel selected to be activated into an analogloopback test state. Pushing LS key 4L when the DISABLE prompt isdisplayed causes the voice loopback test state to be terminated.8Line 10aThis line displays MP8G CALL LIGHT TEST beginning in column 2.Pushing LS key 5L initiates a lamp test of the flight deck channel 2 calllamp.9Line 11aThis line displays *ENABLE beginning in column 1 when the test is notactive. The asterisk prompt is displayed and the test allowed only if thelog--on state is Standby. This line displays *DISABLE <ACTIVE>beginning in column 1 when the test is active. If the log--on statechanges from Standby to any other state while the test is active, the testis terminated. The commands on lines 10 and 11 are displayed only ifthe configuration straps indicate this channel is wired for headset use.bPushing LS key 5L when the ENABLE asterisk prompt is displayedcauses the cockpit voice call light to be activated for a steady indication(regardless of the state of configuration pin TP13C). Pushing LS key 5Lwhen the DISABLE prompt is displayed causes the cockpit voice calllight test to be terminated.10 Line 12aThis line displays MP14BC CHIME beginning in column 2. Pushing LSkey 6L initiates the channel test.11 Line 13aThis line displays TEST beginning in column 1. The asterisk prompt isdisplayed and the test allowed only if the log--on state is Standby.bPushing LS key 6L when the asterisk prompt is displayed causes thecockpit voice go-ahead chime to be activated for a single stroke.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--35(5) SATCOM SELF--TEST (PAST) Page(a) General1The purpose of this page is to initiate a PAST, to enable/disable a voiceloopback on a selected (physical) channel, to enable/disable a test of thecockpit voice call light for a selected (logical) channel, and activation of thecockpit voice go-ahead chime test. See Figure 6-7 for example pages.(b) Data Fields1Line 1aThis line displays the title of the page, SAT--N, beginning in column 10,whereNrepresents1or2toindicateasingleSDU(N=1),SDUNo.1(N = 1), or SDU No. 2 (N = 2) as determined by the settings ofconfiguration pins TP12E and TP12F.bIf there are current failures to report after the execution of a PAST,columns 20 thru 24 display p/t in small font, where p represents thecurrent displayed page, and t represents the total number of pagesneeded to show the current failures. The display of the slash is alwaysin column 22, with p right-justified to the slash and t left-justified to theslash.2Line 3aThis line displays headers ATA beginning in column 1 and CLASSbeginning in column 20 if there are current failures to report afterexecution of a PAST. This line is blank if there are no failures to report.bIn addition to the above, for CFDS type none, the header ATA is notdisplayed (CLASS is still displayed as specified).3Line 5aThis line displays the message TEST IN PROGRESS 60S beginning incolumn 3 within one second of a PAST being initiated on the SAT--N(i.e., SATCOM MAINTENANCE) page, and then throughout the durationof PAST. If there are no current failures to report at the conclusion of thePAST (including the POST/PAST results delay period), the messageTEST OK is displayed. If there are current failures to report at theconclusion of the PAST (including the POST/PAST results delay period),refer to paragraph 4 for line requirements.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--36Figure 6-7 (Sheet 1). SATCOM SELF--TEST PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--37Figure 6-7 (Sheet 2). SATCOM SELF--TEST PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--384Other InformationaThe SELF--TEST page lists two failures per page if failures are detectedduring the PAST(self--test). These two sets of lines (lines 5, 6, and 7and lines 9, 10, and 11) display Level 1 diagnosed current failures.Failures are shown in chronological order (i.e., the most recent detectedfailure last) with no more than two failures displayed per page.bThe number of TEST pages depends on the number of current failuresto report (up to a maximum of 99 pages). When there is an odd numberof current failures to report, the odd failure is displayed on a separatepage in lines 5, 6, and 7, and lines 9, 10, and 11 are blank. If there areno failures to report, lines 5, 6, 7, 9, 10, and 11 are blank except asnoted in paragraph 3.cLine 5 and, if applicable, line 9 display the ATA number beginning incolumn 1 and the class number beginning in column 23. The ATAnumber is displayed as aaaaaa, where aaaaaa represents the ATAreference number of the reported failure as specified in paragraph 3.E.for each type of CFDS. For CFDS type none, no ATA number isdisplayed. The class number is displayed as c, where c represents theclass (1, 2, or 3) of the failure.dLines 6 and 7 and, if applicable, lines 10 and 11 display a text message,as specified in paragraph 3.E. for each CFDS type, for the reportedfailure beginning in column 1.(6) CONFIGURATION DATA Pages(a) General1Access to these pages is from the SAT--N (i.e., SATCOM MAINTENANCE)page. The purpose of these pages is to display the status of SATCOMconfiguration input parameters. See Figure 6-8 for example pages.(b) CONFIGURATION DATA Page 1 (Figure 6-8, sheet 1):1Data FieldsaLine 3(1) This line displays the ICAO address of eight octal characters, asdetermined by discrete inputs from the ICAO address straps. Thisdisplay is not derived from any ARINC 429 version of the ICAOaddress.bLine 5(1) This line displays CONFIG as determined by the setting of thesystem configuration pins, followed by (HEX). The configuration pinsettings are mapped into hexadecimal digits as shown in Table 6-9.In the figure, digits 0 thru 9 correlate to hexadecimal digits 0 thru 9in the table.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--39Figure 6-8 (Sheet 1). Configuration DataTable 6-9. System Configuration Pin MappingConfiguration PinsTP10 TP11 TP12 TP13ABCD EFGH JK AB CDEF GHJK ABCD EFGH JK AB CDEF GHJKHex Digits0 1 2 3 4 5 6 7 8 9cLine 7(1) This line displays the WOW--1 status of SDU weight-on-wheelsdiscrete input No. 1 as IN-AIR/NOT WIRED or ON-GROUND.dLine 8(1) This line displays the WOW--2 status of the SDU weight-on-wheelsdiscrete input No. 2 as IN-AIR/NOT WIRED or ON-GROUND.eLine 10(1) This line displays the MIC--1 status of the SDU cockpit voicemicrophone On discrete input No. 1 as ACTIVE or INACTIVE.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--40fLine 11(1) This line displays the MIC--2 status of the SDU cockpit voicemicrophone On discrete input No. 2 as ACTIVE or INACTIVE.(c) CONFIGURATION DATA Page 2 (Figure 6-8, sheet 2):1Data FieldsaLine 3(1) This line displays the CHIME RESET status of the SDU cockpitvoice go-ahead chime signal reset discrete input as ACTIVE orINACTIVE.bLine 5(1) This line displays the DUAL SYS SELECT status of the SDU dualsystem select discrete input as ACTIVE or INACT.cLine 6(1) This line displays the DUAL SYS DISABLE status of the SDU dualsystem disable discrete input as ACTIVE or INACT.dLine 8(1) This line displays IRS SOURCE as determined by which IRS inputbus the SDU is using. A dash is displayed for the IRS source if a429 source of IRS is not connected to the SDU.eLine 10(1) This line displays the PLACE/END CALL 1 status of the SDUcockpit voice place/end call 1 discrete input as ACTIVE or INACT.fLine 11(1) This line displays the PLACE/END CALL 2 status of the SDUcockpit voice place/end call 2 discrete input as ACTIVE or INACT.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--41Figure 6-8 (Sheet 2). Configuration Data(d) CONFIGURATION DATA Page 3 (Figure 6-8, sheet 3):1GeneralaFor CONFIGURATION DATA pages 3 thru 10, the strap setting value 0or 1 in parentheses is as follows: 1= open circuit; and 0 = tied tocommon.2Data FieldsaLine 4(1) This line displays A(0) ICAO ADRS AVAIL or A(1) ICAO ADRS NOTAVAIL left-justified as determined by the state of systemconfiguration pin TP10A.bLine 6(1) This line displays B(0) FMC1 CONNECTED or B(1) FMC1 NOTCONNECTED left-justified as determined by the state of systemconfiguration pin TP10B.cLine 8(1) This line displays C(0) FMC2 CONNECTED or C(1) FMC2 NOTCONNECTED left-justified as determined by the state of systemconfiguration pin TP10C.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--42dLine 10(1) This line displays D(0) HS 429 TO/FROM CMUS or D(1) LS 429TO/FROM CMUS left-justified as determined by the state of systemconfiguration pin TP10D.eLine 12(1) This line displays E(0) CPDF CONNECTED or E(1) CPDF NOTCONNECTED left-justified as determined by the state of systemconfiguration pin TP10E.Figure 6-8 (Sheet 3). Configuration Data(e) CONFIGURATION DATA Page 4 (Figure 6-8, sheet 4):1Data FieldsaLine 4(1) This line displays F(0) HS 429 ICAO ADRS or F(1) LS 429 ICAOADRS left-justified as determined by the state of systemconfiguration pin TP10F.bLine 6(1) This line displays G(0) SPARE or G(1) SPARE left-justified asdetermined by the state of system configuration pin TP10G.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--43cLine 8(1) This line displays H(0) SPARE or H(1) SPARE left-justified asdetermined by the state of system configuration pin TP10H.dLine 10(1) This line displays J(0) SPARE or J(1) SPARE left-justified asdetermined by the state of system configuration pin TP10J.eLine 12(1) This line displays K(0) LAMP ON CALL INIT or K(1) LAMP ONCALL CONNCT left-justified as determined by the state of systemconfiguration pin TP10K.Figure 6-8 (Sheet 4). Configuration Data(f) CONFIGURATION DATA Page 5 (Figure 6-8, sheet 5):1Data FieldsaLine 4(1) This line displays A(0) PARITY: GOOD, A(1) PARITY: GOOD, A(0)PARITY: BAD, or A(1) PARITY: BAD left-justified as determined bythe state of system configuration pin TP11A and the result of theparity validation test.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--44bLine 6(1) This line displays B(0) CCS INSTALLED or B(1) CCS NOTINSTALLED left-justified as determined by the state of systemconfiguration pin TP11B.cLine 8(1) This line displays C(0) PRI IRS INSTALLED or C(1) PRI IRS NOTINSTLLD left-justified as determined by the state of systemconfiguration pin TP11C.dLine 10(1) This line displays D(0) SEC IRS INSTALLED or D(1) SEC IRS NOTINSTLLD left-justified as determined by the state of systemconfiguration pin TP11D.Figure 6-8 (Sheet 5). Configuration DataRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--45(g) CONFIGURATION DATA Page 6 (Figure 6-8, sheet 6):1Data FieldsaLines 4 thru 9(1) These lines display X(0)* or X(1)* left-justified as shown in thefigure, where X represents E, F, G, H, J, and K, respectively. X(0)*or X(1)* is determined by the states of system configuration pinsTP11E, TP11F, TP11G, TP11H, TP11J, and TP11K. Asterisks aredisplayedincolumn5toindicatethesepinsareacodedgroup.(2) Beginning in column 6, textual messages are displayed (refer toTable 6-10) in lines 4 thru 9 (as needed), where an x indicates themessage(s) to be displayed based on the state of systemconfiguration pins TP11E, TP11F, TP11G, TP11H, TP11J, andTP11K.Table 6-10. Textual Message Display (Page 6 -- Lines 4 thru 9)System Configuration PinSystem Configuration Pin Settings(1 = open circuit / 0 = tied to common)TP11E 101011 All Other Pin CombinationsTP11F 110011TP11G 111111TP11H 111100TP11J 111110TP11K 111110Textual Message Textual Messages To Display Based On System Configuration PinSettingsLO GAIN ANT+DLNA X X XHPA--LO GAIN X X XHI GAIN ANT+BSU--T/L XXXXHI GAIN ANT+BSU--R X XHPA--HI GAIN XXXXHI POWER RELAY X XHPA--IGA XERROR/UNDEFINED XRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--46Figure 6-8 (Sheet 6). Configuration Data(h) CONFIGURATION DATA Page 7 (Figure 6-8, sheet 7):1Data FieldsaLines 4 thru 6(1) These lines display X(0)* or X(1)* left-justified as shown in thefigure, where X represents A, B and C, respectively. X(0)* or X(1)*are determined by the state of system configuration pins TP12A,TP12B, and TP12C. Asterisks are displayed in column 5 to indicatethese pins are a coded group.(2) CFDS/CMC TYPE = is displayed in line 4 beginning in column 6.(3) Beginning in column 6, a textual message is displayed according toTable 6-11, where an x indicates the message to be displayed,based on the state of system configuration pins TP12A, TP12B andTP12C.bLine 10(1) This line displays D(0) RESERVED or D(1) RESERVED left-justifiedas determined by the state of system configuration pin TP12D.cLine 12(1) This line displays E(0) OTHER SDU INSTALLED or E(1) OTHERSDU NOT INSTD left-justified as determined by the state of systemconfiguration pin TP12E.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--47Figure 6-8 (Sheet 7). Configuration DataTable 6-11. Textual Message Display (Page 7 -- Lines 4, 5, an 6)System Configuration PinSystem Configuration Pin Settings(1 = open circuit / 0 = tied to common)TP12A 0011 All Other Pin CombinationsTP12B 0101TP12C 1001Textual Message Textual Messages To Display Based On System Configuration PinSettingsMCDONNELL--DOUGLAS XAIRBUS XBOEING XNOT INSTALLED XERROR/UNDEFINED XRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--48(i) CONFIGURATION DATA Page 8 (Figure 6-8, sheet 8):1Data FieldsaLine 4(1) This line displays F(0) THIS IS SDU2 or F(1) THIS IS SDU1left-justified as determined by the state of system configuration pinTP12F.bLine 6(1) This line displays G(0) CMU1 INSTALLED or G(1) CMU1 NOTINSTALLED left-justified as determined by the state of systemconfiguration pin TP12G.cLine 8(1) This line displays H(0) CMU2 INSTALLED or H(1) CMU2 NOTINSTALLED left-justified as determined by the state of systemconfiguration pin TP12H.dLine 10(1) This line displays J(0) SCDU1 INSTALLED or J(1) SCDU1 NOTINSTALLED left-justified as determined by the state of systemconfiguration pin TP12J.eLine 12(1) This line displays K(0) SCDU2 INSTALLED or K(1) SCDU2 NOTINSTALLED left-justified as determined by the state of systemconfiguration pin TP12K.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--49Figure 6-8 (Sheet 8). Configuration Data(j) CONFIGURATION DATA Page 9 (Figure 6-8, sheet 9):1Data FieldsaLine 4(1) This line displays A(0) NO HSET PRI 4 CALLS or A(1) HSET PRI 4CALLS OK left-justified as determined by the state of systemconfiguration pin TP13A.bLine 6(1) This line displays B(0) LS 429 TO SCDUS or B(1) HS 429 TOSCDUS left-justified as determined by the state of systemconfiguration pin TP13B.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--50Figure 6-8 (Sheet 9). Configuration DatacLines 8 and 9(1) These lines display X(0)* or X(1)* left-justified as shown in thefigure, where X represents C and D, respectively. X(0)* or X(1)* aredetermined by the state of system configuration pins TP13C andTP13D. Asterisks are displayed in column 5 to indicate these pinsare a coded group.(2) Beginning in column 6, a textual message is shown in line 8 andaccording to Table 6-12, where an x indicates the message to bedisplayed, based on the state of system configuration pins TP13Cand TP13D.dLine 12(1) This line displays E(0) SCDU3 INSTALLED or E(1) SCDU3 NOTINSTALLED left-justified as determined by the state of systemconfiguration pin TP13E.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--51Table 6-12. Textual Message Display (Page 9 -- Lines 8 and 9)System Configuration PinSystem Configuration Pin Settings(1 = open circuit / 0 = tied to common)TP13C 0011TP13D 0101Textual Message Textual Messages to Display Based on System ConfigurationPin SettingsLIGHTS AND CHIMEUNDEFINED(Line 8)(Line 9)XSTEADY LIGHTS ANDMULTISTROKE CHIME(Line 8)(Line 9)XFLASHING LIGHTS ANDSINGLE STROKE CHIME(Line 8)(Line 9)XSTEADY LIGHTS ANDSINGLE STROKE CHIME(Line 8)(Line 9)X(k) CONFIGURATION DATA Page 10 (Figure 6-8, sheet 10):1Data FieldsaLines 4 and 5(1) These lines display X(0)* or X(1)* left-justified as shown in thefigure, where X represents F and G, respectively. X(0)* or X(1)* aredetermined by the state of system configuration pins TP13F andTP13G.(2) Beginning in column 6, a textual message is displayed in lines 4and 5 according to Table 6-13, where an x indicates the message tobe displayed based on the state of system configuration pinsTP13F and TP13G.bLines 8 and 9(1) These lines display X(0)* or X(1)* left-justified, where X representsH and J, respectively. X(0)* or X(1)* are determined by the state ofsystem configuration pins TP13H and TP13J. Asterisks aredisplayedincolumn5toindicatethesepinsareacodedgroup.(2) Beginning in column 6, a textual message is displayed in lines 8and 9 according to Table 6-14, where an x indicates the message tobe displayed based on the state of system configuration pinsTP13H and TP13J.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--52Figure 6-8 (Sheet 10). Configuration DatacLines 11 and 12(1) Line 11 displays K(0) HOOK SWITCH IS left-justified and line 12displays LATCHED ACP MIC SW beginning in column 6; or line 11displays K(1) HOOK SWITCH IS left-justified and line 12 displaysSWITCHED PTT/SCDU beginning in column 6, as determined bythe state of system configuration pin TP13K.dLine 13 (LS Key 6L)(1) This line displays <RETURN left-justified and PRINT* right-justified(if applicable). The PRINT* prompt is only displayed if bit 11 ofARINC label 155 is set to 1. Pushing the 6L key causes the pagedisplay to revert to the SAT--N (i.e., SATCOM MAINTENANCE)page.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--53Table 6-13. Textual Message Display (Page 10 -- Lines 4 and 5)System Configuration PinSystem Configuration Pin Settings(1 = open circuit / 0 = tied to common)TP13F 0011TP13G 0101Textual Message Textual Messages to Display Based on System ConfigurationPin SettingsCODEC A WIRED TO AMSAND CABIN(Line 4)(Line 5)XCODEC A WIRED TOCOCKPIT AMS ONLY(Line 4)(Line 5)XCODEC A WIRED TO CABINAUDIO ONLY(Line 4)(Line 5)XCODEC A NOT WIREDBLANK(Line 4)(Line 5)XTable 6-14. Textual Message Display (Page 10 -- Lines 8 and 9)System Configuration PinSystem Configuration Pin Settings(1 = open circuit / 0 = tied to common)TP13H 0011TP13J 0101Textual Message Textual Messages to Display Based on System ConfigurationPin SettingsCODEC B WIRED TO AMSAND CABIN(Line 8)(Line 9)XCODEC B WIRED TOCOCKPIT AMS ONLY(Line 8)(Line 9)XCODEC B WIRED TO CABINAUDIO ONLY(Line 8)(Line 9)XCODEC B NOT WIREDBLANK(Line 8)(Line 9)XRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--54(l) CONFIGURATION DATA Page 11 (Figure 6-8, Sheet 11):1GeneralaPage 11 of the CONFIGURATION DATA page is shown below.Figure 6-8 (Sheet 11). Configuration Data(m) CONFIGURATION DATA Page 12 (Figure 6-8, Sheet 12):1GeneralaPage 12 of the CONFIGURATION DATA page is shown below.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--55Figure 6-8 (Sheet 12). Configuration Data(n) CONFIGURATION DATA Page 13 (Figure 6-8, Sheet 13):1GeneralaThese configuration data pages are only available on thenon-Airbus/Douglas SCDU maintenance pages, in which case the 12pages shown in the previous paragraphs are 1/12 thru 10/12.2Data FieldsaLine 3(1) This line displays the CALL LAMP 1 status of the SDU CockpitVoice-Call Lamp Discrete Output as ACTIVE or INACT asappropriate.bLine 4(1) This line displays the CALL LAMP 2 status of the SDU CockpitVoice-Call Lamp Discrete Output as ACTIVE or INACT asappropriate.cLine 6(1) This line displays the DUAL SYS SELECT status of SDU DualSystem Select Discrete Output as ACTIVE or INACT asappropriate.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--56Figure 6-8 (Sheet 13). Configuration Data(o) CONFIGURATION DATA Page 14 (Figure 6-8, sheet 14):1Data FieldsaLine 3(1) This line displays HPA CMND/STAT beginning in column 1, HGAbeginning in column 15, and LGA beginning in column 22.bLine 4(1) This line displays BACKOFF(DB) beginning in column 1. The HGAHPA commanded backoff power level (in dB) is displayed (ifconfigured) right-justified in column 17 (as determined from theHGA HPA command word Label 143). The LGA HPA commandedbackoff power level (in dB) is displayed (if configured) right-justifiedin column 24 (as determined from the HGA HPA command wordLabel 143. The ranged allowed for display of the backoff is 0 to 31dB in increments of 1 dB.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--57Figure 6-8 (Sheet 14). Configuration DatacLine 5(1) This line displays ACTUAL(DBW) beginning in column 1. The HGAHPA reported power level (in dB Watts) is displayed (if configured)right-justified in column 16 (as determined from the HGA HPAstatus word Label 144). The state of the actual power out status(APOS) bit is indicated as either A for actual or H for held and isdisplayed in column 17. The LGA HPA commanded backoff powerlevel (in dB Watts) is displayed (if configured) right-justified incolumn 23 (as determined from the LGA HPA status word Label144). The state of the APOS status bit is displayed in column 24 aspreviously stated. The allowable range for display of the actualpower is --11.5 to 19.0 dBW in increments of 0.5 dBW. If the actualpower value is outside the measurable range, dashes are displayedfor the actual power value. If valid data is not available for the HPAstatus label, dashes are displayed to indicate the unknown data.dLine 6(1) This line displays POWER(WATTS) beginning in column 1.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--58eLine 7(1) This line displays REFLECTED beginning in column 1. The HGAHPA reflected power level (in Watts) is displayed (if configured)right-justified in column 17 (as determined from the HGA HPA ). TheLGA HPA reflected power level (in Watts) is displayed (if configured)right-justified in column 24 (as determined from the LGA HPA ). Theallowable range for the display of the reflected power value is 0.000to 25.056 Watts. If the power level is unavailable, dashes aredisplayed.fLine 8(1) This line displays FORWARD beginning in column 1. The HGA HPAreflected power level (in Watts) is displayed (if configured)right-justified in column 17 (as determined from the HGA HPA). TheLGA HPA reflected power level (in Watts) is displayed (if configured)right-justified in column 24 (as determined from the LGA HPA). Theallowable range for the display of the reflected power value is 0.000to 80.000 Watts. If the power level is unavailable, dashes aredisplayed.gLine 9(1) This line displays RATIO(R/F) beginning in column 1. The HGAHPA reflected power to forward power ratio is displayed (ifconfigured) right-justified in column 17 (as determined from theHGA HPA). The LGA HPA reflected power to forward power ratio isdisplayed (if configured) right-justified in column 24 (as determinedfrom the LGA HPA). The allowable range for the display of thereflected power to forward power ratio is 0.000 to 1.000 Watts. If thereported ratio is over-range, the text OVER is displayed. If the rationumber is unavailable, dashes are displayed.NOTE: The over-range condition occurs when the forward poweris more than 50 Watts while the reflected power is at themaximum of 25.056 Watts. The HPA indicates theover-range condition through the solo word ratio value ofFFH.hLine 10(1) This line displays CARRIER beginning in column 1.iLine 11(1) This line displays COMMANDED beginning in column 1. The HGAHPA commanded carrier state is displayed (if configured)right-justified in column 17 (as determined from the HGA HPA). TheLGA HPA commanded carrier state is displayed (if configured)right-justified in column 24 (as determined from the LGA HPA). Thecommanded carrier state is displayed as either ON or OFF.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--59jLine 12(1) This line displays ACTUAL beginning in column 1. The HGA HPAactual carrier state is displayed (if configured) right-justified incolumn 17 (as determined from the HGA HPA). The LGA HPAcommanded carrier state is displayed (if configured) right-justified incolumn 24 (as determined from the LGA HPA). The actual carrierstate is displayed as either ON or OFF.kLine 13(1) This line displays RETURN> right-justified. Pushing LS key 6Lcauses the page display to revert to the SAT--N (SATCOMMAINTENANCE) page.(7) DATA LOADER MENU Page(a) General1Access to this page is from SATCOM SUBMENU page (or the SATCOMMAINTENANCE page). The access page depends on the configuration ofthe aircraft as defined in Figure 6-2. The purpose of this page is to supply ameans of commanding data loader actions. See Figure 6-9 for examplepages.(b) Data Fields1Field 1LaThis field displays DATA LOADER in the label line and the data loaderstatus in the data line. Possible status displays depend on the dataloader status as follows:•NOT CONNECTED -- Displayed when the status of both data loaderis absent.•CONNECTED -- Displayed when at least one data loader status isCONNECTED, and the status of neither data loaders is READY,BUSY, or ERROR.•READY -- Displayed when a data loader status is READY.•BUSY -- Displayed when a data loader status is BUSY.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--60bREADY must be displayed before data uploading or downloading canbe performed.cAsterisks are only displayed adjacent to the left LS keys when the dataloader status is READY.Figure 6-9 (Sheet 1). DATA LOADER MENURELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--61Figure 6-9 (Sheet 2). DATA LOADER MENURELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--62Figure 6-9 (Sheet 3). DATA LOADER MENURELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--63Figure 6-9 (Sheet 4). DATA LOADER MENURELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--64dSeveral messages are displayed when the status of a data loader isERROR . If the status becomes ERROR, an appropriate error messageis appended to ERROR, separated by a dash. Possible error messagesare displayed as follows:•DISK FULL•TRANSFER FAILURE•FILE NOT FOUND•CRC FAILURE•BAD FILE HEADER•BAD OWNER REQS VER•OPEN DISK•CLOSE DISK•WRITE PROTECT•COMPOSITE ORT NOT ALLOW.eThe TRANSFER FAILURE error message indicates an ARINC 615protocol transfer failure (e.g., loss of communications). The OPEN DISKand CLOSE DISK error messages are displayed when an undefineddisk command completion code is received. COMP ORT NOT ALLOWis indicated when a composite ORT version upload is attempted and thesetting for ORT item liv does not allow it.2Fields 2L thru 5LaThese fields display prompts in the data line for commanding dataloader actions. The prompts that can be displayed for the indicatedDATA LOADER MENU page (1 or 2) are as given in Table 6-15.Table 6-15. DATA LOADER MENU Page PromptsLS Key Display Prompt (Page 1) Display Prompt (Page 2)2LUPLD OWNER REQS DNLD MAINTENANCE3LDNLD OWNER REQS DNLD FAILURES4LDNLD CALL EVENTS DNLD SYS EVENTS5LDNLD DATA EVENTS Refer to the description for the 5Land 5R keysRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--65bThe display prompts given in Table 6-15 command the following actions:•UPLD OWNER REQS -- upload owner requirements table•DNLD OWNER REQS -- download owner requirements table•DNLD CALL EVENTS -- download call event log•DNLD DATA EVENTS -- download data event log•DNLD MAINTENANCE -- download maintenance activity log•DNLD FAILURES -- download SDU/system failure log•DNLD SYS EVENTS -- download system management event log.cAsterisks are only displayed beside the adjacent left LS key when thedata loader status is READY (except as stated below). When asterisksare displayed, pushing the left LS key adjacent to the desired actioncommands the data loader to initiate that action. Prior to softwarepackage D2.0, asterisks are not displayed when the data loader statusis either NOT CONNECTED, CONNECTED, BUSY, or ERROR.dIn addition, if the data loader status is READY but the log-on state isLOGGING-ON INOP, LOGGING-ON, LOGGED-ON AUTO, orLOGGED-ON CONSTRAINED; an asterisk is not displayed beside theUPLD OWNER REQS prompt. Scratchpad message 1 is issued if an LSkey is pushed when no asterisks are displayed. For software packagesD2.0 and after, uploads are allowed regardless of the log-on state(composite uploads are inhibited only by ORT item liv and not the log-onstate).eOnce a left LS key is pushed, the <SEL> message is displayed to theright of the selected data loader action, right-justified. The data loaderstatus changes to BUSY and data transfers occur. There is only onedata loader command selected at a time. The <SEL> message remainsdisplayed until the 6L key is pushed if the data loader status becomesERROR after a left LS key is pushed. When the data transfer iscompleted, or after an error has been acknowledged, the <SEL>message is removed and the data loader status changes appropriately.3Fields 5L and 5RaPERIODIC DATA LOGGING is displayed on page 2 in the label linebeginning in column 2. In the data line, START is displayed adjacent tothe5Lkey.Noasteriskisdisplayedbesidethe5Lkeywhenthedataloader status is either NOT CONNECTED, CONNECTED, BUSY, orERROR.bWhen the START prompt is selected by pushing the 5L key when thedata loader status is READY:•Periodic data logging starts•TheasterisknexttoSTARTisremoved•The <SEL> message is displayed beginning in column 8•STOP is displayed adjacent to the 5R key.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--66cPeriodic data logging continues until the 5R key is pushed, at that timethe data line display reverts to its original state (i.e., only the STARTprompt with or without an asterisk as appropriate).dThe <SEL> message remains displayed and the STOP prompt isblanked if the data loader status changes to ERROR after periodic datalogging has started. This condition remains until the error isacknowledged by pushing the 6L key and/or the data loader statuschanges, at that time the data line display changes as appropriate.4Field 6La6L -- This data line displays the *ACK ERROR prompt. This prompt isdisplayed when the data loader status is ERROR. Pushing the 6L keycauses the SDU to remove the ERROR status and display the currentdata loader status (i.e., NOT CONNECTED or CONNECTED) in the 1Ldata line.bThe SDU completes the upload/download data transfer by commandingthe data loader transfer complete function. The data loader respondswith a TRANSFER COMPLETE indication and enters a no loop. Toreturn the data loader to the READY state, the user must cause thedata loader to read the configuration file on the diskette (i.e., cycle dataloader power or remove/insert the diskette).5Field 6Ra6R -- This data line displays the RETURN> prompt. Pushing the 6R keycauses the display to revert to the SATCOM SUBMENU page (orSATCOM MAINTENANCE page) as appropriate.(8) LAST LEG REPORT Page(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.The purpose of this page is to display Class 1 and 2, Level 1 diagnosed, failuresreported during the last leg. See Figure 6-10 for example pages.(b) The Last Leg Report lists two failures per page if a failure is present during thelast leg. These two sets of lines display Class 1 and 2, Level 1 diagnosed, lastleg failures. Failures are displayed in chronological order (i.e., the most recentdetected failure last) with no more than two failures displayed per page. Thenumber of LAST LEG REPORT pages depends on the number of failures toreport (up to a maximum of 99 pages). When there is an odd number of failuresto report, the odd failure is displayed on a page of its own in lines 5, 6, and 7,and lines 9, 10, and 11 are blank. If there are no failures to report, lines 6, 7, 9,10, and 11 are blank. Line 5 displays NO FAULT DETECTED beginning incolumn 4 if there are no failures to report.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--67Figure 6-10. LAST LEG REPORT PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--68(c) Line 5 and, if applicable, line 9 display the universal time coordinated (UTC)beginning in column 1, and ATA beginning in column 6, and the class number incolumn 23.(d) The UTC is displayed as hhmm, where hh represents the UTC hours from 00 to23, and mm represents the UTC minutes from 00 to 59. The UTC is the time ofthe failure reporting as stored in the SDU system failure memory log. Dashes aredisplayed if no valid UTC data is available.(e) The ATA number is displayed as aaaaaa, where aaaaaa represents the ATAreference number of the reported failure as specified in paragraph 3.E. for eachtype of CFDS. For CFDS type none, no ATA number is displayed.(f) The class number is displayed as c, where c represents the class (1 or 2) of thefailure.(9) PREVIOUS LEGS REPORT Page(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.The purpose of this page is to display Class 1 and 2, Level 1 diagnosed, failuresreported during previous legs. See Figure 6-11 for example pages.(b) The Previous Leg Report lists two failures per page if a failure was presentduring the previous leg. These two sets of lines display Class 1 and 2, Level 1diagnosed, last leg failures. Failures within each flight leg are displayed inchronological order (i.e., the most recent detected failure last) with no more thantwo failures displayed per page. However, the flight leg display is in reversechronological order (i.e., flights go back in time while failures for each individualflight go forward in time).(c) The number of PREVIOUS LEGS REPORT pages depends on the number offailures to report (up to a maximum of 99 pages). If there are no failures toreport, lines 6, 7, 9, 10, and 11 are blank. Line 5 displays NO FAULT DETECTEDbeginning in column 4 if there are no failures to report.(d) Failures from different flight legs with the same aircraft identification are mixed onthe same page. When the last leg falls in lines 5, 6, and 7, failures from theprevious flight leg are displayed on the same page in lines 9, 10, and 11.(e) When the given flight leg has a different aircraft identification recorded than theflight leg before it, the failure display begins in lines 5, 6, and 7 on the next pageof the multiple page sequence. When there are no failures to report for a givenflight leg, nothing is reported for that flight leg (i.e., the flight leg is skipped).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--69Figure 6-11 (Sheet 1). PREVIOUS LEG REPORT PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--70Figure 6-11 (Sheet 2). PREVIOUS LEG REPORT PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--71(f) Line 5 and line 9 (if applicable) display the flight leg number beginning in column1, the UTC beginning in column 10, and the ATA number beginning in column15.(g) The flight leg is displayed as fl, where fl represents the flight leg number from 01to either:•The number of flight legs recorded in the SDU system failure memory log•63 flight legs•From 01 to the maximum number of flight legs that can be displayed given thePREVIOUS LEGS REPORT page limit of 99.(h) The date is displayed as mmmdd, where mmm represents the month of the yearas JAN, FEB, MAR, APR, MAY, JUN, JUL, AUG, SEP, OCT, NOV, or DEC, anddd represents the day of the month from 01 to 31. The date is the date of theflight leg number as stored in the SDU system failure memory log. Dashes aredisplayed if no valid UTC data is available.(i) The UTC time is displayed as hhmm, where hh represents the UTC hours from00 to 23, and mm represents the UTC minutes from 00 to 59. The UTC is thetime of the failure reporting as stored in the SDU system failure memory log.Dashes are displayed if no valid UTC data is available.(j) The ATA number is displayed as aaaaaa, where aaaaaa represents the ATAreference number of the reported failure as specified in paragraph 3.E. for eachtype of CFDS. For CFDS type none, no ATA number is displayed.(k) The class number is displayed as c, where c represents the class (1 or 2) of thefailure.(10) LRU IDENTIFICATION Page(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.The purpose of this page is to display a list of all installed LRUs with theirassociated part numbers, modification levels, and serial numbers, and to displayORT identification data. See Figure 6-12 for example pages.(b) If a Honeywell/Racal HPA is installed, the associated part/serial number isdisplayed; otherwise the HPA display entry is removed. The number of LRUIDENTIFICATION pages depends on the number of LRUs to list.(c) For the LRUs, line 4 and, if applicable, line 9 display a three letter acronymrepresenting the installed LRU. The possible LRU acronyms are given inTable 6-16.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--72Table 6-16. LRU AcronymsLRU Acronym LRU NameSDUSatellite Data UnitHPHHigh Power Amplifier -- High Gain AntennaHPLHigh Power Amplifier -- Low Gain Antenna(d) For the LRUs, line 5 and, if applicable, line 10 display P/N beginning in column 1,the LRU end-item part number beginning in column 6, and the softwaremodification level in columns 23 and 24.(e) The P/N is displayed as bbbbbbb--hhsss, where bbbbbbb--hhsss represents theLRU end-item part number consisting of a seven-digit LRU base part number(i.e., bbbbbbb), a two-digit hardware configuration number (i.e., hh), and athree-digit software configuration number (i.e., sss). Dashes are displayed if novalid data is available.(f) The software modification level is displayed as nn, where nn represents up to atwo-character LRU software modification level.(g) Line 6 and, if applicable, line 11 display S/N beginning in column 1 and the LRUserial number beginning in column 5. The S/N is diplayed as ssssssss, wheressssssss represents the LRU serial number. Dashes are displayed if no validdata is available.(h) For the Honeywell/Racal MCS system, the two-digit LRU hardware and LRUserial number must be manually entered through the CMT interface for valid datato be available for display. This data is stored during an LRU end-item test. Allother numbers reside within the LRU software. For non-Honeywell/Racalinterfacing HPAs, no such data is available to the SDU, therefore, dashes aredisplayed for the HPA part/serial numbers.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--73Figure 6-12 (Sheet 1). LRU IDENTIFICATION PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--74Figure 6-12 (Sheet 2). LRU IDENTIFICATION Page(i) The ORT identification is displayed in either lines 4, 5, and 6, or in lines 9, 10,and 11 depending on where the LRU list falls. Line 4 or line 9, as appropriate,displays the header ORT IDENTIFICATION left-justified. If the ORT is apartitioned version, the text, --USER, is added to the end of the header text. Line5 or line 10, as appropriate, displays the ORT 24-character description ascontained in ORT item xxxiii (refer to Appendix B). Line 6 or line 11, asappropriate, displays MODIFIED left-justified, if the state of ORT item xxxvii (referto Appendix C) is modified. If the state of ORT item xxxvii is unmodified, theMODIFIED flag is not displayed.(j) If the ORT is loaded as separate partitions, the secured ORT identification isdisplayed in either lines 4, 5, and 6, or in lines 9, 10, and 11 depending on wherethe first ORT ident falls. Line 4 or line 9, as appropriate, displays the header ORTIDENTIFICATION--SECD left-justified. Line 5 or line 10, as appropriate, displaysthe ORT 24-character description as contained in ORT item liii (refer to AppendixC) for the secured partition. Line 6 or line 11, as appropriate, displays MODIFIEDleft-justified, if the state of the ORT secured partition modified flag (refer toAppendix C) is modified. If the state of the ORT secured partition modified flag isunmodified, the MODIFIED flag is not displayed.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--75(11) TROUBLE SHOOTING DATA Page(a) General1Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE)page. The purpose of this page is to display Class 1 and 2, Level 1,diagnosed failures reported during the last leg and previous legs. SeeFigure 6-13 for example pages.2The Trouble Shooting Data pages display the class 1 and 2 last leg andprevious legs failure details. Failures are displayed in chronological order(i.e., the most recent detected failure last) with one failure displayed perpage. Flight leg display order is reverse chronological (i.e., flights go back intime while failures for each individual flight go forward in time). The numberof pages depends on the number of failures to report (up to 64 flight legs or99 pages).(b) Data Fields1Line 4aLine 4 displays the date beginning in column 2 and the UTC beginningin column 8. The date and time are displayed as follows.bThe month is displayed as mmm, where mmm represents the month ofthe year as JAN, FEB, MAR, APR, MAY JUN, JUL, AUG, SEP, OCT,NOV, or DEC.cThe day is displayed as dd, where dd represents the day of the monthfrom 01 to 31.dThe UTC is displayed as hh:mm, where hh represents the UTC hoursfrom 00 to 23 and mmm represents the UTC minutes from 00 to 59. TheUTCisthetimethefailurewasstoredinthefailurememorylogonthisflight leg. Dashes are displayed if no valid UTC data is available.eLine 4 displays the header, LEG, beginning in column 15 and the flightleg count right-justified from column 23.2Line 5aLine 5 displays beginning in column 2 the LRU abbreviated name of upto five characters that corresponds to the level 1 failure code. The SRUabbreviated name of up to five characters is displayed beginning incolumn 8. If the SRU designation in the failure code is 0, no SRUabbreviation is displayed. The LRU failure code is displayed as twohexadecimal digits beginning in column 17. The SRU failure code isdisplayed as one hexadecimal digit beginning in column 20. The failurecode is displayed as two hexadecimal digits beginning in column 22.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--76Figure 6-13. TROUBLE SHOOTING DATA PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--773Line 6aLine 6 displays the time since power--on (TSPO) header beginning incolumn 2, and the LRU power--on counter (POC) header beginning incolumn 15. The LRU time since power-on is displayed right-justifiedfrom column 12.bThe TSPO is displayed as hhh:mm, where hhh represents the hours ofthe elapsed time since the unit powered up from 0 to 999, and mmrepresents the minutes portion of the elapsed time from 0 to 59.cLine 6 displays the power-on count value from 0 to 65535 right-justifiedfrom column 23.4Line 7aLine 7 displays the headers, TEMP, beginning in column 2, andgroundspeed (GSPD), beginning in column 15. The LRU-failed SRU (orPSU) temperature is displayed right-justified from column 12. Dashesare displayed if no valid temperature data is available. The GSPD isdisplayed right-justified from column 23.5Line 8aLine 8 displays the headers, PHASE, beginning in column 2, and DC,beginning in column 15. The flight phase is displayed right-justified fromcolumn 12. If a numbered flight phase is not available, then an aor gisshown in column 12, as appropriate. The DC state is displayed as DC0,DC0’, DC1, DC1’, or DC2 right-justified from column 23.6Line 9aLine 9 displays the headers, CLASS, beginning in column 2, and IFC,beginning in column 15. The failure class is displayed in column 12. Theintermittent failure count is displayed in column 23.7Line 10aLine 10 displays the header FLTNO beginning in column 2. The flightnumber is displayed right-justified from column 12. The aircraft tailnumber is displayed right-justified from column 23. Dashes aredisplayed if no valid flight number or tail number data is available.8Line 11aLine 11 displays the failure parameter as eight hexadecimal digitsbeginning in column 5. The associated parameter is displayed as eighthexadecimal digits beginning in column 16.(12) LAST LEG CLASS 3 FAULTS Page(a) Access to this page is from the SAT--N (CFDS SATCOM Maintenance Menu)page. The purpose of this page is to display Class 3, Level 1 diagnosed, failuresreported during the last leg. See Figure 6-14 for example pages.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--78Figure 6-14. LAST LEG CLASS 3 FAULTS Page(b) The Last Leg Class 3 Faults lists two Class 3 faults per page if Class 3 faults arepresent during the last leg. These two sets of lines display Class 3, Level 1diagnosed, last leg failures. Failures are displayed in chronological order (i.e.,the most recent detected failure last) with no more than two failures displayedper page.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--79(c) The number of LAST LEG CLASS 3 FAULTS pages depends on the number offailures to report (up to a maximum of 99 pages). When there is an odd numberof failures to report, the odd failure is displayed on a separate page in lines 5, 6,and 7, and lines 9, 10, and 11 are blank. If there are no failures to report, lines 6,7, 9, 10, and 11 are blank. Line 5 displays NO FAULT DETECTED beginning incolumn 4 if there are no failures to report.(d) Line 5 and, if applicable, line 9 display the UTC beginning in column 1 and theATA number beginning in column 6.(e) The UTC number is displayed as hh:mm, where hh represents the UTC hoursfrom 00 to 23, and mm represents the UTC minutes from 00 to 59. The UTC isthe time of the failure reporting as stored in the SDU system failure memory log.Dashes are displayed if no valid UTC data is available.(f) The ATA number is displayed as aaaaaa, where aaaaaa represents the ATAreference number of the reported failure as specified in paragraph 3.E. for eachtype of CFDS. For CFDS type none, no ATA number is displayed.(13) GROUND REPORT Page(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.The purpose of this page is to display Class 1, 2, or 3, Level 1 diagnosed groundfailures that occurred during the last leg. See Figure 6-15 for example pages.(b) The Ground Report lists two failures per page if failures are detected during thelast leg. These two sets of lines display Class 1, 2, and 3, Level 1 diagnosed,last leg failures. Failures are displayed in chronological order (i.e., the mostrecent detected failure last) with no more than two failures displayed per page.(c) The number of GROUND REPORT pages depends on the number of failures toreport (up to 99 pages). When there is an odd number of failures to report, theodd failure is displayed on a separate page in lines 5, 6, and 7, and lines 9, 10,and 11 are blank. If there are no failures to report, lines 6, 7, 9, 10, and 11 areblank. Line 5 displays NO FAULT DETECTED beginning in column 4 if there areno failures to report.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--80Figure 6-15. GROUND REPORT PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--81(14) GROUND REPORT (TROUBLE SHOOTING DATA) Page(a) General1Access to this page is from the GROUND REPORT page. The purpose ofthis page is to display Class 1, 2, or 3, Level 1 diagnosed ground failuresthat occurred during the last leg ground report. See Figure 6-16 for examplepages.2One failure is listed per page if a failure is present. These lines display Class1, 2, and 3, Level 1 diagnosed, last leg ground report failure detailscorresponding to the Level 1 failures from which the troubleshooting datawas initiated. Failures are displayed in chronological order (i.e., the mostrecent detected failure last) with one failure displayed per page.(b) Data Fields1Line 4aLine 4 displays the date beginning in column 2 and the UTC beginningin column 8. The date and time are displayed as follows.bThe month is displayed as mmm, where mmm represents the month ofthe year as JAN, FEB, MAR, APR, MAY, JUN, JUL, AUG, SEP, OCT,NOV, or DEC.cThe day is displayed as dd, where dd represents the day of the monthfrom 01 to 31.dThe UTC is displayed as hh:mm, where hh represents the UTC hoursfrom 00 to 23 and mm represents the UTC minutes from 00 to 59. TheUTCisthetimethefailurewasstoredinthefailurememorylogonthisflight leg. Dashes are displayed if no valid UTC data is available.2Line 5aLine 5 displays the LRU abbreviated name of up to five characters thatcorresponds to the Level 1 failure code. The SRU abbreviated name ofup to five characters is displayed beginning in column 8. If the SRUdesignation in the failure code is 0, no SRU abbreviation is displayed.The LRU failure code is displayed as two hexadecimal digits beginningin column 17. The SRU failure code is displayed as one hexadecimaldigit beginning in column 20. The failure code is displayed as twohexadecimal digits beginning in column 22.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--82Figure 6-16. GROUND REPORT TROUBLE SHOOTING DATA PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--833Line 6aLine 6 displays the headers, TSPO, beginning in column 2 and, POC,beginning in column 15. The LRU time since power-on is displayedright-justified from column 12.bThe UTC is displayed as hh:mm, where hh represents the UTC hoursfrom 00 to 23 and mm represents the UTC minutes from 00 to 59. TheUTCisthetimethefailurewasstoredinthefailurememorylogonthisflight leg. Dashes are displayed if no valid UTC data is available.cLine 6 displays the power-on count value from 0 to 65535 right-justifiedfromcolumn 23.4Line 7aLine 7 displays the headers, TEMP, beginning in column 2, and GSPD,beginning in column 15. The LRU-failed SRU (or PSU) temperature isdisplayed right-justified from column 12. Dashes are displayed if no validtemperature data is available. The groundspeed is displayedright-justified from column 23.5Line 8aLine 8 displays the headers, PHASE, beginning in column 2, and DC,beginning in column 15. The flight phase is displayed right-justified fromcolumn 12. If a numbered flight phase is not available, then an aor gisshown in column 12, as appropriate. The DC state is displayed as DC0,DC0’, DC1, DC1’, or DC2 right-justified from column 23.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--843. Maintenance Computer InterfaceA. General(1) The SDU is designed to interface with the Boeing 747--400 Central MaintenanceComputer (CMC) or the Boeing 777 On--board Maintenance System (OMS), theAirbus Central Fault Display System (CFDS), and the McDonnell Douglas CFDS inaccordance with guidelines outlined in Boeing documents D220U050 (747--400 CMC-- release date 3 June 1991) and D243W201--1 (777 OMS -- release date 30 October1992) and Airbus document ABD0048 issue C, all of which supersede ARINC 604 fortheir respective applications.(2) The Boeing maintenance computers (i.e., 747--400 CMC and 777 OMS) are virtuallyindistinguishable to the SDU. The operations to support these two systems are verysimilar and, therefore, are presented together. The operations to support the Airbusand McDonnell Douglas maintenance computers are very similar and, therefore, arepresented together. The SDU determines the aircraft type on which the SDU isinstalled, and then supports only the functionality required by that particular system.B. Boeing 747--400 CMC/777 OMS(1) General(a) The CMC and SDU communicate with each other through an ARINC 429 databus using ARINC 429 words.(b) When the SDU receives the standard ground test command containing itsequipment ID and source destination identifier (SDI), the SDU responds bysetting the command word (ARINC label 350) acknowledge bit to ACK for fourseconds. The SDU initiates a system-wide functional test. As soon as possibleduring the execution of the functional test, the SDU sets the SSM for ARINClabel 350 to functional test.(2) CMC to SDU Communication -- Automatic Fault Reporting(a) The CMC and SDU communicate with each other through an ARINC 429 databus using ARINC 429 words.(b) When the SDU receives the standard ground test command containing itsequipment ID and source destination identifier (SDI), the SDU responds bysetting the command word (ARINC label 350) acknowledge bit to ACK for 4seconds. The SDU then initiates a system-wide functional test. As soon aspossible during the execution of the functional test, the SDU sets the SSM forARINC label 350 to functional test.(c) At the conclusion of the functional test, the SDU builds the fault summary wordsusing ARINC labels 350 thru 354 by mapping currently active failures to theappropriate bits in the words. Once the words are built they are latched for 30seconds, then the SDU returns to automatic fault reporting. The SDUcontinuously transmits the fault summary words to the CMC at a rate of 1 to 2Hz, with the SSM bits set to normal operation during reporting of the test results.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--85(3) CMC Interactive Mode(a) The SDU supports configuration data in CMC interactive mode for a Boeing 777installation. If the CMC transmits a configuration data interactive mode commandaddressed to the SDU on ARINC label 227, the SDU processes the command bysupplying the first page of configuration information and then resumes automaticmode processing. The configuration data command is used to displayconfiguration information for the SATCOM LRUs (SDU and HPAs). The SDUresponds to the configuration data command from the automatic mode.(b) The SDU does not support ground test and shop faults in CMC interactive mode.If the CMC transmits a ground test or shop faults interactive mode commandaddressed to the SDU on label 227, the SDU ignores the command.(4) Configuration Data Messages(a) General1When configuration data is commanded, the MCS configuration datapage(s) is(are) displayed. These data pages display installed LRUs asdetermined by the SDU system configuration pin settings with theirassociated part/serial number data. These lines also display the ORTidentification along with modification status. Figure 6-17 supplies anexample of the configuration data page.2The ORT 24-character description as contained in ORT item xxxiii isdisplayed. For non-777 installations, the text is limited to 20 characters perline.(b) USER ORT STATUS1This displays MODIFIED if the state of the ORT user partition is modified,otherwise no status or header is displayed.(c) SECD ORT IDENTIFICATION1This is the 24-character description as contained in ORT item liii. Fornon-777 installations, the text is limited to 20 characters per line.(d) SECURED ORT STATUS1This displays MODIFIED if the state of the ORT secured partition is modified,otherwise, no status or header is displayed. For software package C3.5, theORT is not partitioned so only a single ORT IDENTIFICATION is supplied forthe ORT display lines.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--86Figure 6-17. Configuration Data Pages for Boeing 777 Installation(e) LRU PART NUMBER1The part numbers for the LRUs installed are displayed as follows. The wordLRU is displayed, which is substituted with the appropriate LRU acronym.The LRU part number is displayed as bbbbbbb-hhsss, wherebbbbbbb-hhsss represents the LRU end item part number consisting of aseven-digit LRU base part number (bbbbbbb), a two-digit hardwareconfiguration number (hh), and a three-digit software configuration number(sss). Dashes are displayed if no valid data is available.(f) LRU SERIAL NUMBER1The serial numbers of the LRUs installed are displayed as follows. The wordLRU is displayed, which is substituted with the appropriate LRU acronym.The LRU serial number is displayed as ssssssss, where ssssssss representsthe LRU serial number. Dashes are displayed if no valid data is available.(g) SDU S/W PART NUMBER1This displays the software part number that corresponds to the softwareload. The configuration data page includes the header SDU CONFIGSTRAPS and the raw strap setting for the current installation.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--87(5) Standard Ground Test (Non--interactive)(a) When a standard test on a CMC ground test menu is selected, the CMCcommands the SDU to start a standard ground test. The SDU prevents the CMCcommanded standard ground test while the aircraft is airborne. The SDU starts asystem-wide PAST after it has responded to the receipt of a standard ground testcommand from the CMC.(b) At the end of the CMC-commanded PAST, the SDU builds labels 350 thru 354fault summary words by mapping PAST-detected SATCOM subsystem failures tothe appropriate bits. The SDU continuously transmits these fault summary wordstotheCMCatarateof1to2Hz,withtheSSMsettoNormalOperation,duringreporting of the test results.C. Airbus/Douglas CFDS(1) General(a) The CFDS uses a centralized fault display interface unit (CFDIU) as an interfacebetween the SDU and the SCDU. Throughout these paragraphs the acronymCFDIU is used to include both the A320 CFDS and the A340 CMC.(b) When the SDU is installed on an Airbus or McDonnell Douglas aircraft with aCFDS, it supports the normal mode and interactive mode as required by theCFDS.(2) CFDIU to SDU Communication(a) The CFDIU communicates with the SDU through an ARINC 429 data bus usingARINC 429 words.(3) SDU to CFDIU Communication(a) The SDU supports both the normal mode and the interactive mode, as requiredby the CFDS. The SDU also transmits the LRU part number and serial numberand ORT identification data blocks to the CFDIU.(b) The LRU/ORT identification data records make up the LRU/ORT identificationdata blocks. Each LRU data record contains the LRU acronym, part number, andserial number. Each ORT identification data record contains the ORTIDENTIFICATION header, the ORT 24 character description, and the state of themodified flag.(4) Normal Mode Failure Messages(a) As specified, the SDU transmits failure messages and LRU/ORT identificationinformation while operating in the normal mode. The following paragraphsdefined the contents of these reports.(b) Once a failure is reported in the normal mode, the failure remains in the reportfor that entire flight, regardless of whether the failure is cleared. As new failuresare reported, they are added to the beginning of the report (i.e., the report is inreverse chronological order, bearing in mind the CFDS considers the time of thefailure to be the time it is first reported on this flight leg rather than when it firstoccurs).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--88(c) In addition to latching the failures, the contents of the normal mode reportdepend on the failure class and when it occurs in relationship to other failuresagainst the same LRU. Level I failures against the same LRU reported in thenormal mode are not to be transmitted more than once unless they are an upperclass and the upper class failure occurs after the lower class failure(s). Once areport is sent to the CFDIU during the normal mode for the current flight, theSDU does not change the content or order except to add new failure messages,as appropriate to the beginning of the report.(d) The McDonnell Douglas CFDIU does not decode the normal mode report untilthe CFDIU detects an increase in the block word count. However, unlike theAirbus CFDIU, the McDonnell Douglas CFDIU decodes the entire report. Aftersending an All Call DC2 command for a new flight leg, the Airbus CFDIU delaysprocessing the normal mode report for about 30 seconds before regarding thereport as pertaining to the new flight leg.(e) The SDU transmits the names of the installed LRUs, as determined by thesystem configuration pin settings, along with their associated part/serialnumbers. At the end of this LRU transmission, the SDU transmits the ORTidentification with a modification status. The LRU names can be transmitted inany order. Transmission of an HPA LRU part/serial number uses the samecriteria as the display of HPA data.(5) Interactive Mode(a) The CFDIU supplies for two-way communication between the SCDU and theSDU, which is referred to as the interactive mode. When the SDU operates in theinteractive mode, it is responsible for all information displayed on the CFDSmaintenance pages, with exception of the scratchpad. The SDU enters theinteractive mode upon receiving an ENQ command from the CFDIU when theaircraft is on the ground.D. Central Aircraft Information and Maintenance System(1) The central aircraft information and maintenance system (CAIMS) is a distributivemaintenance system where each member system performs its own built--in test (BIT)and stores its own faults. Also, each system supplies real--time status information onthe health of each of its LRUs and their interfaces. The member systems supportCAIMS during normal operation and during on--ground maintenance.(2) In the normal operation mode, member systems gather and store fault data whenequipment failure occurs during normal operation. This is typically performed bycontinuous BIT and power--up BIT, with identified faults stored in the membersystems non--volatile memory (NVM). The CAIMS does not store fault information formember systems, but the fault warning processor (FWP) supplies fault event data,such as: flight leg, date, time, fault zone, and aircraft serial number information that isstored with the fault in the member systems NVM.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--89(3) In the maintenance mode, the CAIMS is active and is called the on--boardmaintenance system (CAIMS OMS). The CAIMS OMS is the ground maintenancefunction and is accessible through communication link to a portable maintenanceaccess terminal (PMAT). With the PMAT, the aircraft maintenance crew can retrievestored fault data from a member system. For member systems, the CAIMS OMSdisplays fault information, commands BITE test, and displays real--time data forstatus displays, and commands the download of NVM fault data.E. Level I Failure Messages and ATA Reference Numbers(1) The Level I failure messages and ATA reference numbers that are available fortransmittal in the CFDS normal mode, for display in the CFDS interactive mode, andfor display on SCDU accessed maintenance pages are specified in the followingparagraphs for each CFDS type installed. Level I failure messages are intended foruse by line maintenance crews. Therefore, the failure messages are designed to beLRU-based and only supply LRU-level identification.(2) The Level 1 failure codes are two-digit hexadecimal numbers that define the LRU,data communication bus, or miscellaneous interface signal where a failure, businactivity, or signal error has been determined to have occurred. When multiple LRUsare suspect, the most likely LRU is listed first followed by the next most likely LRU,separated by a slash. The ATA number listed is for the first suspect LRU. Additionaltext can be supplied at the end to help clarify the failure message.•Table 6-17 describes the Level I failure messages and ATA reference numbers touse for display on the SCDU accessed maintenance pages when the installedCFDS type is a Boeing CMC. Also shown is the CMC message ID which isdisplayed by the CMC in response to the Level I failure messages (refer to theOEM’s maintenance manual and fault isolation manual).•Table 6-18 and Table 6-19 describe the Level I failure messages and ATAreference numbers to use for transmittal in the CFDS normal mode, and the CFDSinteractivemodepagesdisplayedwhentheinstalledCFDStypeisanAirbus.Table 6-18 is for the SDU (single configuration) or SDU No. 1 (dual configuration),and Table 6-19 is for SDU No. 2 (dual configuration) as determined by the settingsof configuration pins TP12E and TP12F.•Table 6-20 describes the Level I failure messages and ATA reference numbers touse for transmittal in the CFDS normal mode, and the CFDS interactive modepages displayed when the installed CFDS type is a McDonnell Douglas.•For CFDS type none, the Level I failure messages displayed on the SCDUaccessed maintenance pages are the same as those specified for Boeing (refer toTable 6-17). However, no ATA reference numbers are displayed.(3) For Level I codes identified as not applicable in the tables, the SDU does not reportthe failure on that particular interface (i.e., CFDS normal and interactive modes orSCDU accessed maintenance pages as appropriate). Where TBD is used in theLevel I failure message column, it is coded as literally read. For failures that occurthat are undefined in the tables, the SDU does not report the failure on that particularinterface.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--90Table 6-17. Boeing Level I Failure Messages and ATA Reference NumbersFailureCode SCDU Accessed Maintenance Pages ATA NumberCMCMessage ID01 SDU 232500 2320502 OTHER SDU INCOMPATIBILITY 232500 2320503 RESERVED04 HPA--HI GAINHPA--HI GAIN[IGA][HGA] 232500 2320707 HPA--LO GAIN 232500 232090A HI POWER RELAY 232500 232180D LNA/DIP--(TOP/PORT) 232500 232100F LNA/DIP--STBD 232500 2321110 LNA/DIP--LO GAIN 232500 2321213 BSU--(TOP/PORT) 232500 2321315 BSU--STBD 232500 232141A IN GAIN ANTENNA--TOPHI GAIN ANTENNA--(TOP/PORT)[IGA][HGA] 232500 232151C HI GAIN ANTENNA--STBD 232500 232161F LO GAIN ANTENNA 232500 2322521 MCDU1 34610022 MCDU2 34610023 MCDU3 34610033 (ACARS MU/CMU)1 232700 2321934 (ACARS MU/CMU)2 232700 2321935 IRS--PRI 342100 3422236 IRS--SEC 342100 3422437 RESERVED38 RESERVED39 CMC 454500 232013D FMC1 3461003E FMC2 34610040 ARINC 429 ICAO ADDRESS None 23251RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--91Table 6-17. Boeing Level I Failure Messages and ATA Reference Numbers (cont)FailureCodeCMCMessage IDATA NumberSCDU Accessed Maintenance Pages42 CTU 231900 2323543 (CFS/CPDF) 23320052 (CFS/CPDF)/SDU 23320053 (ACARS MU/CMU)1/SDU 232700 2321954 CTU/SDU 231900 2323555 MCDU1/SDU 34610056 MCDU2/SDU 34610057 (ACARS MU/CMU)2/SDU 232700 2323559 CMC/SDU 454500 232015A IRS--PRI/SDU 342100 232225B IRS--SEC/SDU 342100 232245C HPA--IN GAIN/SDUHPA--HI GAIN/SDU[IGA][HGA] 232500 232265F HPA--LO GAIN/SDU 232500 2322562 BSU--(TOP/PORT)/SDU 232500 2321364 BSU--STBD/SDU 232500 2321466 MCDU3/SDU 34610067 RESERVED68 RESERVED6A RESERVED6C RESERVED6D RESERVED6E RESERVED6F RESERVED71 OTHER SDU/THIS SDU 23250073 FMC1/SDU 34610074 FMC2/SDU 34610080 RESERVED82 RESERVEDRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--92Table 6-17. Boeing Level I Failure Messages and ATA Reference Numbers (cont)FailureCodeCMCMessage IDATA NumberSCDU Accessed Maintenance Pages88 RESERVED90 SDU M--CTRL/HPA--IN GAINSDU M--CTRL/HPA--HI GAIN[IGA][HGA] 232500 2324696 SDU M--CTRL/HPA--LO GAIN 232500 2324898 SDU M--CTRL/BSU--(TOP/PORT) 232500 232499A BSU--STBD XTALK/BSU--PORT 232500 232529C SDU M--CTRL/BSU--STBD 232500 232509D BSU--PORT XTALK/BSU--STBD 232500 23253C0 WRG:CONFIG PIN PROG/SDU 232500 23236C1 SDU WOW MISCOMPARE N/AC2 SDU/OTHER SDU SELECT--DISABLE DISCRETE 232500C3 WRG:ICAO ADDRESS PIN PROG/SDU 232500 23251C4 TX PATH VSWR--IN GAINTX PATH VSWR--HI GAIN[IGA][HGA] 232500 23257C5 WRG:CONFIG PIN PROG/SDU OWNER REQS 232500C6 TX PATH VSWR--LO GAIN 232500 23216C7 HPA--HI GAIN/OVER TEMPERATUREHPA--HI GAIN/OVER TEMPERATURE[IGA][HGA] 232500 23247C8 BAD DATA FROM GROUND EARTH STATION NoneC9 HPA--LO GAIN/OVER TEMPERATURE 232500 23254CA SDU/LNA/DIP--LO GAIN 232500 23237CB WRG:SDI PIN PROG/HPA--IN GAINWRG:SDI PIN PROG/HPA--HI GAIN[IGA][HGA] 232500CC WRG:SDI PIN PROG/HPA--HI GAIN 232500CD SDU (POC/TOTC) DATA RESET NoneCE RESERVEDCF HPA--IN GAIN (POC/TOTC) DATA RESETHPA--HI GAIN (POC/TOTC)DATA RESET[IGA][HGA] NoneD0 HPA--LO GAIN (POC/TOTC) DATA RESET NoneRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--93Table 6-17. Boeing Level I Failure Messages and ATA Reference Numbers (cont)FailureCodeCMCMessage IDATA NumberSCDU Accessed Maintenance PagesD1 WRG:SDI PIN PROG/HPA--IN GAINWRG:SDI PIN PROG/HPA--HI GAIN[IGA][HGA] 232500D2 WRG:SDI PIN PROG/HPA--LO GAIN 232500D3 WRG:SDI PIN PROG/BSU--(TOP/PORT) 232500D4 WRG:SDI PIN PROG/BSU--STBD 232500D5 SDU COAX/HPA--IN GAINSDU COAX/HPA--HI GAIN[IGA][HGA] 232500 23237D6 SDU COAX/HPA--LO GAIN 232500 23237D7 RESERVEDD8 LNA/DIP/ (SDU)--(TOP/PORT) 232500 23236D9 LNA/DIP/ (SDU)--STBD 232500 23236DA LNA/DIP/ (SDU)--LO GAIN 232500 23236DB LO GAIN SUBSYSTEM 232500DC NO ACTIVE ACARS MU/CMU 232700DD SDU OWNER REQS -- SECURED NoneDE SDU OWNER REQS -- USER NoneDF IN GAIN SUBSYSTEMHI GAIN SUBSYSTEM[IGA][HGA] 232500E0 RESERVEDFE POWER SUPPLY INTERRUPT NoneTable 6-18. Airbus Level I (SDU No. 1) Failure Messages and ATA No.FailureCode SDU/SDU No. 1 -- CFDS Normal and Interactive Modes ATA Number01 SDU1(105RV1)SDU1(5RV1)[IGA][HGA]23283423283402 SDU2(105RV2)SDU2(5RV2) INCOMPATIBILITY[IGA][HGA]23283423283403 RESERVEDRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--94Table 6-18. Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 1 -- CFDS Normal and Interactive Modes04 HPA1(107RV1)HPA--HIGAIN(7RV1)[IGA][HGA]23283523283107 HPA--LO GAIN(9RV) 2328350A HI POWER RELAY(21RV) 2328420D DLNA1(119RV1)DLNA--TOP(19RV1)DLNA--L(20RV1)[IGA][Top Mount][Conformal]2328372328382328370F DLNA--R(20RV2) [Conformal] 23283710 DLNA--LO GAIN(14RV) 23283613 BSU(8RV1)BSU--L(15RV1)[Top Mount][Conformal]23284623284415 BSU--R(15RV2) [Conformal] 2328441A ANTENNA1(116RV1)HI GAIN ANTENNA--TOP(16RV1)HI GAIN ANTENNA--L(17RV)[IGA][Top Mount][Conformal]2328132328132328121C HI GAIN ANTENNA--R(18RV) [Conformal] 2328121F LO GAIN ANTENNA(13RV) 23281121 MCDU1(2CA1) 22821222 MCDU2(2CA2) 22821223 MCDU3(2CA3) 22821233 ATSU1(1TX1) [A320/A330/A340 ATSU] 462100ACARS MU(1RB) [A320 ACARS] 232434ACARS MU1(1RB1) [A330/A340 ACARS] 23243434 ATSU2 (1TX2) [A320/1A330/A340 ATSU] 462100ACARS MU2 [A320 ACARS] N/AACARS MU2(1RB2) [A330/A340 ACARS] 23243435 ADIRU1(1FP1) 34123436 ADIRU2(1FP2) 34123437 RESERVED N/A38 RESERVED N/ARELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--95Table 6-18. Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 1 -- CFDS Normal and Interactive Modes39 CFDIU(1TW)CMC1(1TM1)[A320][A320/A340]3132344513343D FMGC1(1CA1)FMGEC1(1CA1)[A320][A330/A340]2283342283343E FMGC2(1CA2)FMGEC2(1CA2)[A320][A330/A340]22833422833440 ARINC 429 ICAO N/A42 CTU(303RD)CTU(3RY)[A320][A330/A340]23353423923443 CPDF N/A52 CPDF/SDU1 N/A53 ATSU1 (1TX1)/SDU1(105RV1) [IGA A320/A330/A340 ATSU] 462100ATSU1 (1TX1)/SDU1(5RV1) [HGA A320/A330/A340 ATSU] 462100ACARS MU (1RB)/SDU1(105RV1) [IGA A320 ACARS] 232434ACARS MU1 (1RB1)/SDU1(105RV1) [IGA A330/A340 ACARS] 232434ACARS MU (1RB)/SDU1(5RV1) [HGA A320 ACARS] 232434ACARS MU1 (1RB1)/SDU1(5RV1) [HGA A330/A340 ACARS] 23243454 CTU (303RD)/SDU1(105RV1) [IGA A320] 233534CTU (3RY)/SDU1(105RV1) [IGA A330/A340] 239234CTU (303RD)/SDU1(5RV1) [HGA A320] 233534CTU (3RY)/SDU1(5RV1) [HGA A330/A340] 23923455 MCDU1(2CA1)/SDU1(105RV1)MCDU1(2CA1)/SDU1(5RV1)[IGA][HGA]22821222821256 MCDU2(2CA2)/SDU1(105RV1)MCDU2(2CA2)/SDU1(5RV1)[IGA][HGA]228212228212RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--96Table 6-18. Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 1 -- CFDS Normal and Interactive Modes57 ATSU2 (1TX2)/SDU1(105RV1) [IGA A320/A330/A340 ATSU] 462100ATSU2 (1TX2)/SDU1(5RV1) [HGA A320/A330/A340 ATSU] 462100ACARS MU2/SDU1(105RV1) [IGA A320 ACARS] 232434ACARS MU2 (1RB2)/SDU1(105RV1) [IGA A330/A340 ACARS] 232434ACARS MU2/SDU1(5RV1) [HGA A320 ACARS] 232434ACARS MU2 (1RB2)/SDU1(5RV1) [HGA A330/A340 ACARS] 23243459 CFDIU(1TW)/SDU1(105RV1) [IGA A320] 313243CMC1(1TM1)/SDU1(105RV1) [IGA A330/A340] 451334CFDIU(1TW)/SDU1(5RV1) [HGA A320] 313243CMC1(1TM1)/SDU1(5RV1) [HGA A330/A340] 4513345A ADIRU1(1FP1)/SDU1(105RV1)ADIRU1(1FP1)/SDU1(5RV1)[IGA][HGA]3412343412345B ADIRU2(1FP2)/SDU1(105RV1)ADIRU2(1FP2)/SDU1(5RV1)[IGA][HGA]3412343412345C HPA1 (107RV1)/SDU1(105RV1)HPA--HI GAIN(7RV1)/SDU1(5RV1)[IGA][HGA]2328352328315F HPA--LO GAIN(9RV)/SDU1(5RV1) 23283562 BSU(8RV1)/SDU1(5RV1)BSU--L(15RV1)/SDU1(5RV1)[Top Mount][Conformal]23284623284464 BSU--R(15RV2)/SDU1(5RV1) [Conformal] 23284466 MCDU3(2CA3)/SDU1(105RV1)MCDU3(2CA3)/SDU1(5RV1)[IGA][HGA]22821222821267 RESERVED68 RESERVED6A RESERVED6C RESERVED6D RESERVED6E RESERVED6F RESERVEDRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--97Table 6-18. Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 1 -- CFDS Normal and Interactive Modes71SDU2(105RV2)/SDU1(105RV1)SDU2(5RV2)/SDU1(5RV1)[IGA][HGA]23283423283473 FMGC1(1CA1)/SDU1(105RV1) [IGA A320] 228334FMGEC1(1CA1)/SDU1(105RV1) [IGA A330/A340] 228334FMGC1(1CA1)/SDU1(5RV1) [HGA A320] 228334FMGEC1(1CA1)/SDU1(5RV1) [HGA A330/A340] 22833474 FMGC2(1CA2)/SDU1(105RV1) [IGA A320] 228334FMGEC2(1CA2)/SDU1(105RV1) [IGA A330/A340] 228334FMGC2(1CA2)/SDU1(5RV1) [HGA A320] 228334FMGEC2(1CA2)/SDU1(5RV1) [HGA A330/A340] 22833480 RESERVED82 RESERVED88 RESERVED90 SDU1(105RV1) BUS M--CTRL/HPA1(107RV1) [IGA] 232834SDU1(5RV1) BUS M--CTRL/HPA--HIGAIN(7RV1)[HGA]23283496 SDU1(5RV1) BUS M--CTRL/HPA--LO GAIN(9RV) 23283498 SDU1(5RV1) BUS M--CTRL/BSU(8RV1)SDU1(5RV1) BUS M--CTRL/BSU--L(15RV1)[Top Mount][Conformal]2328342328349A BSU--R XTALK/BSU--L [Conformal] N/A9C SDU1(5RV1) BUS M--CTRL/BSU--R(15RV2) [Conformal] 2328349D BSU--L XTALK/BSU--R [Conformal] N/AC0 WRG:CONFIG PIN PROG/SDU1(105RV1) [IGA] 232834C0 WRG:CONFIG PIN PROG/SDU1(5RV1) [HGA] 232834C1 LGCIU1(5GA1)/LGCIU2(5GA2)/SDU1(105RV1) [IGA] 323171LGCIU1(5GA1)/LGCIU2(5GA2)/SDU1(5RV1) [HGA] 323171C2 SDU1(105RV1) SEL--DISABLEDISCRETE/SDU2(105RV2)[IGA] 232834SDU1(5RV1) SEL--DISABLEDISCRETE/SDU2(5RV2)[HGA] 232834RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--98Table 6-18. Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 1 -- CFDS Normal and Interactive ModesC3 WRG:ICAO ADDRESS PINPROG/SDU1(105RV1)[IGA] 232834WRG:ICAO ADDRESS PINPROG/SDU1(5RV1)[HGA] 232834C4 HPA1 (107RV1)/VSWR [IGA] 232835HPA--HI GAIN(7RV1)/VSWR [HGA] 232831C5 WRG:CONFIG PIN PROG/SDU1(105RV1)OWNER REQS DB[IGA] 232834WRG:CONFIG PIN PROG/SDU1(5RV1)OWNER REQS DB[HGA] 232834C6 HPA--LO GAIN(9RV)/VSWR 232835C7 HPA(107RV1)/OVER TEMPERATURE [IGA] 232835HPA--HI GAIN(7RV1)/OVER TEMPERATURE [HGA] 232831C8 SDU1(105RV1)/BAD DATA FROM GROUNDSTATION[IGA] 232834SDU1(5RV1)/BAD DATA FROM GROUNDEARTH STATION[HGA] 232834C9 HPA--LO GAIN(9RV)/OVER TEMPERATURE 232835CA SDU1(5RV1)/DLNA--LO GAIN(14RV) 232834CB WRG:SDI PIN PROG/HPA1(107RV1) [IGA] 232835WRG:SDI PIN PROG/HPA--HI GAIN(7RV1) [HGA] 232831CC WRG:SDI PIN PROG/HPA--LO GAIN(9RV) 232835CD DATA:SDU1 POC/TOTC RESET N/ACE RESERVEDCF DATA:HPA1 POC/TOTC RESET [IGA] N/ADATA:HPA--HI GAIN POC/TOTC RESET [HGA] N/AD0 DATA:HPA--LO GAIN POC/TOTC RESET N/AD1 WRG:SDI PIN PROG/HPA1 (107RV1) [IGA] 232835WRG:SDI PIN PROG/HPA--HI GAIN(7RV1) [HGA] 232831D2 WRG:SDI PIN PROG/HPA--LO GAIN(9RV) 232835D3 WRG:SDI PIN PROG/BSU(8RV1)WRG:SDI PIN PROG/BSU--L(15RV1)[Top Mount][Conformal]232846232844RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--99Table 6-18. Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 1 -- CFDS Normal and Interactive ModesD4 WRG:SDI PIN PROG/BSU--R(15RV2) [Conformal] 232844D5 SDU1(105RV1) COAX/HPA1(107RV1) [IGA] 232833SDU1(5RV1) COAX/HPA--HI GAIN (7RV1) [HGA] 232833D6 SDU1 (5RV1) COAX/HPA--LO GAIN (9RV) 232833D7 RESERVEDD8 DLNA1(119RV1)/SDU1(105RV1)DLNA--TOP(19RV1)/SDU1(5RV1)DLNA--L(20RV1)/SDU1(5RV1)[IGA][Top Mount][Conformal]232838232838232837D9 DLNA--R(20RV2)/SDU1(5RV1) [Conformal] 232837DA DLNA--LO GAIN(14RV)/SDU1(5RV1) 232836DB DLNA--LO GAIN(14RV)/LO GAIN ANTENNA(13RV) 232836DC ATSU1(1TX1)/NO ACTIVE ATSU [A320/A330/A340 ATSU] 462100ACARS MU(1RB)/NO ACTIVE MU [A320 ACARS] 232434ACARS MU(1RB1/2)/NO ACTIVE MU [A330/A340 ACARS] 232434DD SDU1(105RV1) OWNER REQS DB SECUREDPARTITION[IGA] N/ASDU1(5RV1) OWNER REQS DB SECUREDPARTITION[HGA] N/ADE SDU1(105RV1) OWNER REQS DS USERPARTITION[IGA] N/ASDU1(5RV1) OWNER REQS DB USERPARTITION[HGA] N/ADF DLNA--T(19RV1)/BSU(8RV1)/HI GAINANT--TOP(16RV)[Top Mount] 232838HI PWR RELAY(21RV)/BSU--L(15RV1)/BSU--R(15RV2)[Conformal] 232842E0 RESERVEDFE POWER SUPPLY INTERRUPT 240000RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--100Table 6-19. Airbus Level I (SDU No. 2) Failure Messages and ATA No.FailureCode SDU/SDU No. 2 -- CFDS Normal and Interactive Modes ATA Number01 SDU2(105RV2)SDU2(5RV2)[IGA][HGA]23283423283402 SDU1(105RV1) INCOMPATIBILITYSDU1(5RV1) INCOMPATIBILITY[IGA][HGA]23283423283403 RESERVED04 HPA2(107RV2)HPA--HI GAIN(7RV1)[IGA][HGA]23283523283107 HPA--LO GAIN(9RV) 2328350A HI POWER RELAY(21RV) 2328420D DLNA2 (119RV2)DLNA--TOP(19RV1)DLNA--L(20RV1)[IGA][Top Mount][Conformal]2328372328382328370F DLNA--R(20RV2) [Conformal] 23283710 DLNA--LO GAIN(14RV) 23283613 BSU(8RV1)BSU--L(15RV1)[Top Mount][Conformal]23284623284415 BSU--R(15RV2) [Conformal] 2328441A ANTENNA2(116RV2)HI GAIN ANTENNA--TOP(16RV1)HI GAIN ANTENNA--L(17RV)[IGA][Top Mount][Conformal]2328132328132328121C HI GAIN ANTENNA--R(18RV) [Conformal] 2328121F LO GAIN ANTENNA(13RV) 23281121 MCDU1(2CA1) 22821222 MCDU2(2CA2) 22821223 MCDU3(2CA3) 22821233 ATSU1(1TX1) [A320/A330/A340 ATSU] 462100ACARS MU(1RB) [A320 ACARS] 232434ACARS MU1(1RB1) [A330/A340 ACARS] 232434RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--101Table 6-19. Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 2 -- CFDS Normal and Interactive Modes34 ATSU2 (1TX2) [A320/A330/A340 ATSU] 462100ACARS MU2 [A320 ACARS] 232434ACARS MU2(1RB2) [A320/A340 ACARS] 23243435 ADIRU1(1FP1) 34123436 ADIRU2(1FP2) 34123437 RESERVED N/A38 RESERVED N/A39 CFDIU(1TW)CMC1(1TM1)[A320][A330/A340]3132344513343D FMGC1(1CA1)FMGEC1(1CA1)[A320][A330/A340]2283342283343E FMGC2(1CA2)FMGEC2(1CA2)[A320][A330/A340]22833422833440 ARINC 429 ICAO N/A42 CTU(303RD)CTU(3RY)[A320][A330/A340]23353423923443 CPDF N/A52 CPDF/SDU1 N/A53 ATSU1 (1TX1)/SDU2(105RV2) [IGA A320/A330/A340 ATSU] 462100ATSU1 (1TX1)/SDU2(5RV2) [HGA A320/A330/A340 ATSU] 462100ACARS MU(1RB)/SDU2(105RV2) [IGA A320 ACARS] 232434ACARS MU1(1RB1)/SDU2(105RV2) [IGA A330/A340 ACARS] 232434ACARS MU(1RB)/SDU2(5RV2) [HGA A320 ACARS] 232434ACARS MU1(1RB1)/SDU2(5RV2) [HGA A330/A340 ACARS] 23243454 CTU(303RD)/SDU2(105RV2) [IGA A320] 233534CTU(3RY)/SDU2(105RV2) [IGA A330/A340] 239234CTU(303RD)/SDU2(5RV2) [HGA A320] 233534CTU(3RY)/SDU2(5RV2) [HGA A330/A340] 23923455 MCDU1(2CA1)/SDU2(105RV2)MCDU1(2CA1)/SDU2(5RV2)[IGA][HGA]228212228212RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--102Table 6-19. Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 2 -- CFDS Normal and Interactive Modes56 MCDU2(2CA2)/SDU2(105RV2)MCDU2(2CA2)/SDU2(5RV2)[IGA][HGA]22821222821257 ATSU2 (1TX2)/SDU2(105RV2) [IGA A320/A330/A340 ATSU] 462100ATSU2 (1TX2)/SDU2(5RV2) [HGA A320/A330/A340 ATSU] 462100ACARS MU2/SDU2(105RV2) [IGA A320 ACARS] 232434ACARS MU2 (1RB2)/SDU2(105RV2) [IGA A330/A340 ACARS] 232434ACARS MU2/SDU2(5RV2) [HGA A320 ACARS] 232434ACARS MU2(1RB2)/SDU2(5RV2) [HGA A330/A340 ACARS] 23243459 CFDIU(1TW)/SDU2(105RV2) [IGA A320] 313234CMC1(1TM1)/SDU2(105RV2) [IGA A330/A340] 451334CFDIU(1TW)/SDU2(5RV2) [HGA A320] 313234CMC1(1TM1)/SDU2(5RV2) [HGA A330/A340] 4513345A ADIRU1(1FP1)/SDU2(105RV2) [IGA] 341234ADIRU1(1FP1)/SDU2(5RV2) [HGA] 3412345B ADIRU2(1FP2)/SDU2(105RV2) [IGA] 341234ADIRU2(1FP2)/SDU2(5RV2) [HGA] 3412345C HPA2(107RV2)/SDU2(105RV2) [IGA] 232835HPA--HI GAIN(7RV1)/SDU2(5RV2) [HGA] 2328315F HPA--LO GAIN(9RV)/SDU2(5RV2) 23283562 BSU(8RV1)/SDU2(5RV2)BSU--L(15RV1)/SDU2(5RV2)[Top Mount][Conformal]23284623284464 BSU--R(15RV2)/SDU2(5RV2) [Conformal] 23284466 MCDU3(2CA3)/SDU2(105RV2)MCDU3(2CA3)/SDU2(5RV2)[IGA][HGA]22821222821267 RESERVED68 RESERVED6A RESERVED6C RESERVED6D RESERVEDRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--103Table 6-19. Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 2 -- CFDS Normal and Interactive Modes6E RESERVED6F RESERVED71 SDU1(105RV1)/SDU2(105RV2)SDU1(5RV1)/SDU2(5RV2)[IGA][HGA]23283423283473 FMGC1(1CA1)/SDU2(105RV2) [IGA A320] 228334FMGEC1(1CA1)/SDU2(105RV2) [IGA A330/A340] 228334FMGC1(1CA1)/SDU2(5RV2) [HGA A320] 228334FMGEC1(1CA1)/SDU2(5RV2) [HGA A330/A340] 22833474 FMGC2(1CA2)/SDU2(105RV2) [IGA A320] 228334FMGEC2(1CA2)/SDU2(105RV2) [IGA A330/A340] 228334FMGC2(1CA2)/SDU2(5RV2) [HGA A320] 228334FMGEC2(1CA2)/SDU2(5RV2) [HGA A330/A340] 22833480 RESERVED82 RESERVED88 RESERVED90 SDU2(105RV2) BUS M--CTRL/HPA2(107RV2) [IGA] 232834SDU2(5RV2) BUS M--CTRL/HPA--HIGAIN(7RV1)[HGA] 23283496 SDU2(5RV2) BUS M--CTRL/HPA--LO GAIN(9RV) 23283498 SDU2(5RV2) BUS M--CTRL/BSU(8RV1) [Top Mount] 232834SDU2(5RV2) BUS M--CTRL/BSU--L(15RV1) [Conformal] 2328349A BSU--R XTALK/BSU--L [Conformal] N/A9C SDU2(5RV2) BUS M--CTRL/BSU--R(15RV2) [Conformal] 2328349D NBSU--L XTALK/BSU--R [Conformal] N/AC0 WRG:CONFIG PIN PROG/SDU2(105RV2)WRG:CONFIG PIN PROG/SDU2(5RV2)[IGA][HGA]232834232834C1 LGCIU1(5GA1)/LGCIU2(5GA2)/SDU2(105RV2) [IGA] 323171LGCIU1(5GA1)/LGCIU2(5GA2)/SDU2(5RV2) [HGA] 323171RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--104Table 6-19. Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 2 -- CFDS Normal and Interactive ModesC2 SDU2(105RV2) SEL--DISABLEDISCRETE/SDU1(105RV1)[IGA] 232834SDU2(5RV2) SELECT--DISABLEDISCRETE/SDU1(5RV1)[HGA] 232834C3 WRG:ICAO ADDRESS PIN PROG/SDU2(105RV2)[IGA] 232834WRG:ICAO ADDRESS PIN PROG/SDU2(5RV2)[HGA] 232834C4 HPA2(107RV2)/VSWR [IGA] 232835HPA--HI GAIN(7RV1)/VSWR [HGA] 232831C5 WRG:CONFIG PIN PROG/SDU2(105RV2)OWNER REQS DB[IGA] 232834WRG:CONFIG PIN PROG/SDU2(5RV2)OWNER REQS DB[HGA] 232834C6 LPA--LO GAIN(9RV)/VSWR 232835C7 HPA--HI GAIN(107RV2)/OVERTEMPERATURE[IGA] 232835HPA--HI GAIN(7RV1)/OVER TEMPERATURE [HGA] 232831C8 SDU2(105RV2)/BAD DATA FROM GROUNDSTATION[IGA] 232834SDU2(5RV2)/BAD DATA FROM GROUNDEARTH STATION[HGA] 232834C9 HPA--LO GAIN(9RV)/OVER TEMPERATURE 232835CA SDU2(5RV2)/DLNA--LO GAIN(14RV) 232834CB WRG:SDI PIN PROG/HPA2(107RV1) [IGA] 232835WRG:SDI PIN PROG/HPA--HI GAIN(7RV1) [HGA] 232831CC WRG:SDI PIN PROG/HPA--LO GAIN(9RV) 232835CD DATA:SDU1 POC/TOTC RESET N/ACE RESERVEDCF DATA:HPA2 POC/TOTC RESET [IGA] N/ADATA:HPA--HI GAIN POC/TOTC RESET [HGA] N/AD0 DATA:HPA--LO GAIN POC/TOTC RESET N/ARELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--105Table 6-19. Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 2 -- CFDS Normal and Interactive ModesD1 WRG:SDI PIN PROG/HPA2(107RV2) [IGA] 232835WRG:SDI PIN PROG/HPA--HI GAIN(7RV1) [HGA] 232831D2 WRG:SDI PIN PROG/HPA--LO GAIN(9RV) 232835D3 WRG:SDI PIN PROG/BSU(8RV1)WRG:SDI PIN PROG/BSU--L(15RV1)[Top Mount][Conformal]232846232844D4 WRG:SDI PIN PROG/BSU--R(15RV2) [Conformal] 232844D5 SDU2(105RV2) COAX/HPA2(107RV2) [IGA] 232833SDU2(105RV2) COAX/HPA--HI GAIN(7RV1) [HGA] 232833D6 SDU2(105RV2) COAX/HPA--LO GAIN(9RV) 232833D7 RESERVEDD8 DLNA2(119RV2)/SDU2(105RV2) [IGA Top Mount] 232838DLNA--TOP(19RV1)/SDU2(5RV2) [HGA Top Mount] 232838DLNA--L(20RV1)/SDU2(5RV2) [Conformal] 232837D9 DLNA--R(20RV2)/SDU2(5RV2) [Conformal] 232837DA DLNA--LO GAIN(14RV)/SDU2(5RV2) 232836DB DLNA--LO GAIN(14RV)/LO GAIN ANTENNA(13RV) 232836DC ATSU1 (1TX1)/ NO ACTIVE ATSU [A320/A330/A340 ATSU] 462100ACARS MU(1RB)/ NO ACTIVE MU [A320 ACARS] 232434ACARS MU(1RB1/2) NO ACTIVE MU [A330/A340 ACARS] 232434DD SDU2 (105RV2) OWNER REQS DB SECUREDPORTITION[IGA] N/ASDU2 (5RV2) OWNER REQS DB SECUREDPORTITION[HGA] N/ADE SDU2 (105RV2) OWNER REQS DB USERPORTITION[IGA] N/ASDU2 (5RV2) OWNER REQS DB USERPORTITION[HGA] N/ADF DLNA--T(19RV1)/BSU(8RV1)/HI GAINANT--TOP(16RV)[Top Mount] 232838HI PWR RELAY(21RV)/BSU--L(15RV1)/BSU--R(15RV2)[Conformal] 232842RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--106Table 6-19. Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)FailureCode ATA NumberSDU/SDU No. 2 -- CFDS Normal and Interactive ModesE0 RESERVEDFE POWER SUPPLY INTERRUPT 240000Table 6-20. McDonnell Douglas Level I Failures Messages andATA Reference NumbersFailureCode CFDS Normal and Interactive Modes ATA Number01 SDU 23261002 OTHER SDU INCOMPATIBILITY 23261103 RESERVED04 HPA--IN GAIN [IGA] 232600HPA--HI GAIN [HGA] 23261307 HPA--LO GAIN 2326140A HI POWER RELAY 2326150D DLNA--(TOP/L) 2326160F DLNA--R 23261810 DLNA--LO GAIN 23261913 BSU--(TOP/L) 23261B15 BSU--R 23261C1A IN GAIN ANTENNA--TOP [IGA] 232600HI GAIN ANTENNA--(TOP/L) [HGA] 23261D1C HI GAIN ANTENNA--R 23261F1F LO GAIN ANTENNA 23262021 MCDU1 23263522 MCDU2 23263623 MCDU3 23263733 (ACARS MU/CMU) 23243C34 (ACARS MU/CMU)2 N/A35 (IRS/ADIRU)--PRI 23263E36 (IRS/ADIRU)--SEC 23263FRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--107Table 6-20. McDonnell Douglas Level I Failures Messages andATA Reference Numbers (cont)FailureCode ATA NumberCFDS Normal and Interactive Modes37 RESERVED38 RESERVED39 CFDIU 4545003D (FMC/VIA)1 2326423E (FMC/VIA)2 23264340 ARINC 429 ICAO ADDRESS N/A42 CTU 23264443 (CFS/CPDF) TBD52 (CFS/CPDF)/SDU TBD53 (ACARS MU/CMU)/SDU 23263C54 CTU/SDU 23264455 MCDU1/SDU 23263556 MCDU2/SDU 23263657 (ACARS MU/CMU)2/SDU N/A59 CFDIU/SDU 2326415A (IRS/ADIRU)--PRI/SDU 23263E5B (IRS/ADIRU)--SEC/SDU 23263F5C HPA--IN GAIN/SDU [IGA] 232600HPA--HI GAIN/SDU [HGA] 2326005F HPA--LO GAIN/SDU 23262362 BSU--(TOP/L)/SDU 23262664 BSU--R/SDU 23262766 MCDU3/SDU 23263767 RESERVED68 RESERVED6A RESERVED6C RESERVED6D RESERVEDRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--108Table 6-20. McDonnell Douglas Level I Failures Messages andATA Reference Numbers (cont)FailureCode ATA NumberCFDS Normal and Interactive Modes6E RESERVED6F RESERVED71 OTHER SDU/THIS SDU 23260073 (FMC/VIA)1/SDU 23264274 (FMC/VIA)2/SDU 23264380 RESERVED82 RESERVED88 RESERVED90 SDU M--CTRL/HPA--IN GAINSDU M--CTRL/HPA--HI GAIN[IGA][HGA]23260023260096 SDU M--CTRL/HPA--LO GAIN 23262D98 SDU M--CTRL/BSU--(TOP/L) 2326009A BSU--R XTALK/BSU--L 2326009C SDU M--CTRL/BSU--R 2326309D BSU--L XTALK/BSU--R 232600C0 WRG:CONFIG PIN PROG/SDU 232600C1 SDU WOW MISCOMPARE N/AC2 SDU/OTHER SDU SELECT--DISABLE DISCRETE 232600C3 WRG:ICAO ADDRESS PIN PROG/SDU 232631C4 TX PATH VSWR--IN GAINTX PATH VSWR--HI GAIN[IGA][HGA]232600232600C5 WRG:CONFIG PIN PROG/SDU OWNER REQS 232600C6 TX PATH VSWR--LO GAIN 232600C7 HPA--IN GAIN/OVER TEMPERATUREHPA--HI GAIN/OVER TEMPERATURE[IGA][HGA]23260023262CC8 BAD DATA FROM GROUND EARTH STATION NoneC9 HPA--LO GAIN/OVER TEMPERATURE 232634CA SDU/DLNA--LO GAIN 232619RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--109Table 6-20. McDonnell Douglas Level I Failures Messages andATA Reference Numbers (cont)FailureCode ATA NumberCFDS Normal and Interactive ModesCB WRG:SDI PIN PROG/HPA--IN GAINWRG:SDI PIN PROG/HPA--HI GAIN[IGA][HGA]232600232600CC WRG:SDI PIN PROG/HPA--LO GAIN 232600CD SDU (POC/TOTC) DATA RESET NoneCE RESERVEDCF HPA--IN GAIN (POC/TOTC) DATA RESETHPA--HI GAIN (POC/TOTC) DATA RESET[IGA][HGA]NoneNoneD0 HPA--LO GAIN (POC/TOTC) NoneD1 WRG:SDI PIN PROG/HPA--IN GAINWRG:SDI PIN PROG/HPA--HI GAIN[IGA][HGA]232600232600D2 WRG:SDI PIN PROG/HPA--LO GAIN 232600D3 WRG:SDI PIN PROG/BSU--(TOP/L) 232600D4 WRG:SDI PIN PROG/BSU--R 232600D5 SDU COAX/HPA--IN GAINSDU COAX/HPA--HI GAIN[IGA][HGA]232600232600D6 SDU COAX/HPA--LO GAIN 232600D7 RESERVEDD8 DLNA/(SDU)--(TOP/L) 232600D9 DLNA/(SDU)--R 232600DA DLNA/(SDU)--LO GAIN 232600DB LO GAIN SUBSYSTEM 232600DC NO ACTIVE ACARS MU/CMU 232400DD SDU OWNER REQS -- SECURED NoneDE SDU OWNER REQS -- USER NoneDF IN GAIN SUBSYSTEMHI GAIN SUBSYSTEM[IGA][HGA]232600232600E0 RESERVEDFE POWER SUPPLY INTERRUPT NoneRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--1104. SCDU for Dual SATCOMA. General(1) The SDU supports SCDU page displays for dual systems. All pages are as specifiedin paragraph 2.D. (SCDU pages) with the following exceptions.B. SATCOM Logical Channels(1) The SATCOM channels for HEADSET calls in a dual system can be supplied byseveral combinations of physical channels within both SDUs. These combinations aredetermined by the configuration strap settings for cockpit wiring and ORT itemsregarding the use of SDU channel resources (items vi, vii, and xlviii). The display ofchannel status and selections as reported on menus MAIN, DIRECTORY, andCATEGORY-n reflect the logical channel status.C. SATCOM MAIN MENU (Cross-Talk Bus Failed)(1) The SDU designated as the slave unit in a dual system must receive most of thesystem status information from the master over the SDU cross-talk bus. If fullcommunication is not established, the slave unit cannot receive the necessary datafor the display pages. The default SATCOM MAIN MENU display page THIS UNITUNAVAILABLE is displayed in this case.D. SATCOM CHANNEL STATUS(1) The channel status page reflects the physical channels within the SDU that isproviding the display page.E. SATCOM MAINTENANCE Menus(1) The maintenance menus reflect the maintenance data for the SATCOM system thatis providing the display page.5. Maintenance Panel AssemblyA. General(1) The maintenance panel assembly interface diagram (Figure 5-17) supplies remotemonitoring of MCS system operation. The maintenance panel assembly is made upof two parts: the cabin telecommunications (CTM) panel and the Commissioning andMaintenance Terminal (CMT) panel. The CTM panel is used for monitoring the cabintelecommunications equipment. The panel contains six lamps to indicate theavailability of the telephone handsets. A keyed on/off switch arms the system whenthe key is turned to the ON position.(2) The CMT panel is used primarily to debug, detect, isolate software and/or hardwareintegration, LRU and system integration, formal testing, and system access approval,as well as general performance analysis. The CMT data connector supplies anaccess port for a commissioning and maintenance terminal that can be a personalcomputer, a dumb terminal, or a modem. The SDU interface connector on the panelsupplies a remote access port for testing the SDU. The panel also contains lamps toindicate the status of the MCS system. These lamps are defined in Table 6-21.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--111Table 6-21. Commissioning and Maintenance Terminal Panel LampsLamp DefinitionIN USE CH--1 (SDU pin TPH1) This lamp lights to show channel 1 is in use.IN USE CH--2 (SDU pin TPK1) This lamp lights to show channel 2 is in use.PILOT VCE NOT AVAIL (SDU pin TP3A) This lamp lights to show no additional voice channels can beestablished. This can be because no resources are available, or all availableresources being allocated to existing calls.LOG OFF (SDU pin TPC3) This lamp lights to show no packet mode data servicecapability exists at any data rate; system not logged on.CABIN VCE NOT AVAIL (SDU pin TPB3) This lamp lights to show no additional channels can beestablished for analog or digital cabin voice, or circuit--mode data. This can bebecause no resources are available, or all available resources being allocatedto existing calls.MCS FAIL (SDU pin TPG1) This lamp lights to show a total loss of all SATCOM voice anddata services, and at least one cause can be attributable to the MCS systemLRUs themselves. Replacement of the appropriate LRU (SDU, HPA) isnecessary to restore partial or complete service. It is possible for this indicatorand the MCS inoperable indicator (NON-MCS FAIL) to be activesimultaneously, indicating failure in both the MCS system LRUs and nonsystemLRUs.NON-MCS FAIL (SDU pin TPE3) This lamp lights to show total loss of all SATCOM voice anddata services, and at least one cause is attributable to the non-MCS systemLRUs, or interfaces to those LRUs. Replacement of the appropriate non MCSLRU(s), or correction of the interface failure is necessary to restore partial orcomplete service. It is possible for this indicator and the SATCOM fail indicator(MCS FAIL) to be active simultaneously, indicating failure in both the MCSsystem LRUs and the nonsystem LRUs or interfaces.NO SAT LINK (SDU pin TPJ1) This lamp lights to show no SATCOM voice or data servicesare available because of the AES not being successfully logged-on, and thecause is definitely not due to reported failures (MCS or non-MCS). If there is aMCS or non-MCS failure, the NO SAT LINK lamp will not light.HGA FAIL (SDU pin TPD3) This lamp lights to show packet-mode data service capabilityexists, but only at the lowest channel rates (600 and 1200 bps). This indicatoris assumed to only be present in high gain antennas installations that have alow gain antenna backup system. The lamp indicates an HGA failure due to thereduction from normal high speed capability.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 6--112Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 7--1SECTION 7MAINTENANCE PRACTICES1. OverviewA. General(1) This section supplies instructions for removing, reinstalling, and adjusting each LRUof the MCS that has been installed by the aircraft manufacturer or completion center.Where applicable, instructions for replacing lamps, knobs, and set screws areincluded. Adjustment information is called out as required.CAUTION: SHOULD ANY INSTALLATION CRITICAL CASES ARISE WITH THEREINSTALLATION OF ANY UNIT, YOU MUST COMPLY 100 PERCENTWITH THE INSTRUCTION.CAUTION: TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFT POWER OFFWHEN REMOVING OR INSTALLING LRUS.2. Equipment and MaterialsA. GeneralWARNING: BEFORE YOU USE A MATERIAL, KNOW THE HAZARD CODE AND GET THENECESSARY PROTECTION. REFER TO THE PAGE ABOUT HAZARD CODESFOR MATERIALS IN THE FRONT OF THIS MANUAL.(1) Maintenance materials identified with a Honeywell Material Number (HMN) are givenin Table 7-1.(2) No additional special equipment or materials other than those commonly used in theshop are required to install the units in existing trays and clamps, and to adjust thesystem. Do not over tighten mounting screws. Where torque values are not given, itis acceptable to finger tighten the mounting screws.Table 7-1. MaterialsItem Description SourceHMN 97P5778 RTV silicone, No. 3145,translucent, per MIL--A--46146,Group II, Type I militarydesignation M4614621XTN.Dow Corning Corp, Midland, MI(05AJ8)HMN 98C0978 Sealant, corrosion inhibitive(MIL--S--81733, Type II--1/2 -- forextrusion application in the time of1/2 hour) — Pro--Seal 870B--1/2Courtaulds Aerospace, Glendale,CA (83574)NOTES: NOTES:1. Equivalent alternatives are permitted for materials in this list.2. The HMN codes in the list of materials identify the Honeywell Material Number (HMN) given to each material.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 7--23. Procedure for AntennasA. General(1) The following paragraphs describe general information when removing or installingantennas.NOTE: For all antennas not supplied by Honeywell, removal and installation shouldbe done according to installation instructions from the manufacturer.B. Antenna Weather Protection(1) Some antennas require gaskets and others have O--rings. When reinstallingantennas, new gaskets or O--rings should be used.(2) A weather sealant should be applied around the periphery of the antenna base toprevent seepage of water and condensation and preclude corrosion. If a sealant oraerodynamic smoother is used around the periphery of the antenna base, it shouldbe applied after the antenna has been bolted down. The sealant used should benonadhering so the antenna can be removed at a later time, if necessary. Chromatictape is recommended.NOTE: When mounting antennas on a pressurized fuselage, a leveling and sealingcompound like Pro-Seal 870B--1/2 should be used between the entiremounting surface of the antenna and the fuselage. Use of this compound, inaddition to the installation gasket, compensates for surface irregularities andvoids between the antenna and the fuselage. A mold releasing agent can beused on the fuselage prior to installation to prevent the leveling compoundfrom adhering to the fuselage.(3) To prevent water seepage on top mounted antennas, it can be necessary to applySilastic sealant (RTV--3145 or equivalent) to the mounting screw heads.C. Antenna Hardware(1) Clean the airframe at the antenna mounting area to remove any foreign material.(2) Because of the insulation qualities of gaskets and leveling compounds, the mountingscrews are required to supply the electrical bonding between the antennas and theaircraft (typically 15 milliohms or less is required). The technician doing thereinstallation must be sure any hardware being reused is clean and free of corrosion.If in doubt, use new hardware.(3) Gaskets and O--rings deform during initial installation. While it is possible to reusegaskets and O--rings, it is highly recommended new gaskets or O--rings be used.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 7--3D. General Antenna Removal InstructionsNOTE: These procedures apply to all antennas. To prevent damage to theantennas, do not apply pressure to the plastic housings or pry on plastichousings.(1) Pull the appropriate circuit breakers.(2) After removing and saving the hardware, cut the bond line of any installer--appliedsealant between the antenna and the aircraft skin.(3) Pull the antenna away from the aircraft skin far enough to disconnect the cableconnector(s).4. Procedure for the LRUsCAUTION: BEFORE AN LRU IS INSTALLED OR REMOVED, PULL THE CIRCUITBREAKERS THAT SUPPLY POWER TO THE LRU TO REMOVE POWER.CAUTION: MOISTURE AND DIRT CAUSE DAMAGE TO LRUs.CAUTION: LRU FAILURE RATES INCREASE WITH A RISE IN TEMPERATURE. INSTALLTHE LRUs WITH CLEARANCE; LET THE AIR FLOW ON TOP AND BOTTOMOF LRUS TO PREVENT OVERHEATING.A. LRU Removal(1) Remove an LRU as follows:(a) Disconnect the circuit breakers that supply power to the LRU.(b) Tag the circuit breakers with DO-NOT-OPERATE identifiers.(c) Loosen the clamp knobs and let them drop out of the way.(d) Pull the LRU forward a minimum of 1/2 inch to clear the rear connector pins.(e) Lift the LRU free of the cooling air-duct gasket on the mounting rack.B. LRU Installation(1) Install an LRU as follows:(a) Determine the location of each LRU in the aircraft.(b) Check the LRU to be installed and make sure all connector pins are straight andready for connection.(c) Make sure the index pin coding on the rear connector is correct for the matingconnector.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 7--4(d) Place the LRU in the appropriate mounting rack and align the connectors. Pushthe LRU back to make contact with the connector pins. Push the LRU into placeand rock the LRU sideways slightly.CAUTION: DO NOT OVER TIGHTEN THE CLAMP. EXCESSIVE TORQUE CANCAUSE BRACKETS AND CONNECTORS TO WARP AND BEND.(e) Put the hold-down clamps in place and tighten the knobs finger-tight.5. Owner Requirements Table UploadingA. General(1) When the SDU is replaced, the ORT needs to be uploaded before normal operationcan begin. Refer to SYSTEM OPERATION, for the ORT uploading procedure.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 7--56. Instructions for Continued Airworthiness, FAR 25.1529A. General(1) Maintenance requirements and instructions for continued airworthiness of the MCScomponents are contained in the paragraphs that follow.(2) Installation of the MCS on an aircraft by supplemental type certificate or Form 337obligates the aircraft operator to include the maintenance information supplied by thismanual in the operator’s Aircraft Maintenance Manual and the operator’s AircraftScheduled Maintenance Program.(a) Maintenance information for the MCS (system description, removal, installation,testing, etc.) is contained in this manual.(b) LRU part numbers and other necessary part numbers contained in this manualshould be placed into the aircraft operator’s appropriate aircraft illustrated partscatalog (IPC).(c) Wiring diagram information contained in this manual should be placed into theaircraft operator’s appropriate aircraft Wiring Diagram Manuals.(d) The MCS system components are considered on--condition units and noadditional maintenance is required other than a check for security and operationat normal inspection intervals.(e) If a system component is inoperative, remove unit, secure cables and wiring,collar applicable switches and circuit breakers, and placard them inoperative.Revise equipment list and weight and balance as applicable prior to flight andmake a log book entry that unit was removed (refer to section 91.213 of the FARor the aircraft’s minimum equipment list (MEL).(f) The MCS components can be repaired at a factory authorized repair center or anappropriately rated FAA Part 145 repair station.(g) Once repaired, reinstall the LRU in the aircraft in accordance with the originalForm 337 approved data or instructions in this manual. Do a Return to Servicetest of the system and approve it for return to service with a log book entryrequired by section 43.9.(h) Scheduled maintenance program tasks to be added to the aircraft operator’sappropriate aircraft maintenance program are as follows:1Recommended periodic scheduled servicing tasks: None required.2Recommended periodic inspections: None required.NOTE: The (applicable LRUs) used with this system have test andinspections that are required by FAR 91.413 to be completed every24 calender months.3Recommended periodic scheduled preventative maintenance tests (Tests todetermine system condition and/or latent failures): None required.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page 7--6Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--1APPENDIX AVENDOR EQUIPMENT1. OverviewA. General(1) Appendix A contains information on vendor-manufactured equipment that can beinstalled on an aircraft configured for MCS system. Installation of this equipmentdepends on the specific requirements of the operator. Therefore, information in thissection is supplied as a courtesy to the MCS equipment operators.2. Electronic Cable SpecialistsA. General(1) This paragraph contains information on how to select installation provisions offeredby electronic cable specialists (ECS) for the Honeywell MCS--4000/7000 system.ECS designs and manufactures the installation provisions described here and cansupply either individual components or complete installation kits. The address forElectronic Cable Specialists is as follows:Electronic Cable Specialists5300 W. Franklin DriveFranklin, WI 53132U.S.A.Telephone: (414) 421--5300FAX: (414) 421--5301B. Radio Frequency Components(1) All RF components (cable, connectors, and attenuators) supplied to interface theSATCOM Avionics and Antenna Subsystems have been designed to meet the strictusage and attenuation requirements of the Honeywell MCS--4000/7000 system andARINC 741/761. A selected list of RF components offered by ECS for SATCOMinstallations is shown in Table A--1 and Table A--2.C. Cable Assembly Fabrication(1) ECS fabricates cable assemblies guaranteed to meet SATCOM system requirementsand ARINC 741 specifications.•Each cable assembly is fabricated with an individual part number, which ispermanently affixed to each end of the assembly.•Each set of cable assemblies is assigned a serial number, which is printed on thepart number label. Serialization makes sure each cable assembly is traceable andrepeatable.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--2Table A--1. ECS Cables and ConnectorsECS Cable Part No. 310801 310201 311501 311601 311901 3C142B*Nominal Attenuation@ 1.6 GHz (dB/100 ft)4.7 6.9 8.7 10.7 15.5 18.4Overall Diameter 0.45 in. 0.32 in. 0.245 in. 0.23 in. 0.195 in. 0.195 in.Pounds/100 ft 15.0 8.6 5.2 5.0 4.3 5.0Male TNC 180°CTS022 CTS122 CTS922 CTS922 CTS722 CTS722Male TNC 90°CTR022 CTR122 CTR922 CTR922 CTR722 CTR722Male N 180°CNS022 CNS122 CNS922 CNS922 CNS722 CNS722Male N 90°CNR022 CNR122 CNR922 CNR922 CNR722 CNR722Female N 180°FNS022 FNS122 FNS922 FNS922 FNS722 FNS722ARINC 600 Size 1 L0122 L1122 L9122 L9122 L7122 L7122ARINC 600 Size 5 N/A N/A A650922 A650922 225791--2 225791--2Table A--2. ECS AttenuatorsAttenuator (Transmit Path) Attenuator (Receive Path)Fixed or Variable Fixed or VariableD. Cable Assembly Testing(1) Testing is done on Hewlett-Packard 8753 network analyzers to verify insertion lossand VSWR. The results become part of a test database and are shipped with eachcable assembly. Each cable assembly is tested across the SATCOM systemfrequency bandwidth (1530 MHz to 1660.5 MHz). Received path cable assembliesare test swept from 1530 MHz to 1559 MHz. Customers have the option of havingcable assemblies tested with or without attenuators.E. ARINC 600 Connectors(1) ECS supplies ARINC 600 connectors for ARINC 741 style avionic electricalinterfaces. The SATCOM rack-side connectors (Figure A--1) are described in thisparagraph. Connector part numbers are:•HPA -- NIC66H20A00AA0•SDU -- NIC66H21A00AA0•SCU/BSU -- NIC66F11A00AA0.(2) ECS supplies ARINC 600 Size 1 coaxial connectors with the requisite termination kitand assembly instructions (Figure A--2).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--3Figure A--1. ARINC ConnectorsFigure A--2. ARINC AssemblyRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--4F. SATCOM Avionics Unit Mounting Hardware(1) SATCOM avionics mounting hardware is made up of the HPA, SDU, and SCU andwill be mounted in ARINC 600 style tray assemblies. The HPA and SDU each requireforced air cooling during normal operation, whereas the SCU can function properlywith convection cooling alone. Refer to MECHANICAL INSTALLATION, for LRUcooling requirements.G. SATCOM Hardware Component Kits(1) This paragraph contains information on how to select SATCOM hardware componentkits offered by ECS for the Honeywell MCS--4000/7000 avionic units in Table A--3thru Table A--6. ECS supplies several options for each kit to accommodate the varietyof mounting requirements specific to each aircraft installation. ECS tray assembliescome with and without independent cooling systems to ensure installation flexibility.(2) The tray assemblies have been specially designed to meet Honeywell and ARINC600 LRU cooling requirements. Tray assemblies are supplied with insertion/extractionfront hold-downs as standard, but are available with other front hold-down options.For tray assembly dimensions refer to Figure A--3.(3) The hardware component kits for the HPAs, SDU, and BSU are listed in Table A--3thru Table A--6, respectively.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--5/(A--6 blank)Figure A--3. Dimensions for ECS Tray AssembliesRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--7Table A--3. HP--600 HPA (40W) Hardware Component Kit,Part No. 998HQS--900--1XXKit Part No. * Item Part Number Description Quantity998HQS--900--102 6292--101 8 MCU S/S standard tray 1998HQS--900--103 6288--101 8 MCU S/S tray w/bottomfan1998HQS--900--104 6290--101 8 MCU S/S tray w/left sidefan1998HQS--900--106 6284--101 8 MCU S/S tray w/right sidefan1998HQS--900--107 6286--101 8 MCU S/L standard tray 1* Parts supplied with each kit NIC66H20A00AA0 HPA ARINC connector22 AWG pins20 AWG sockets16 AWG sockets12 AWG socketsSize 5 coaxicons11404342Table A--4. HP--700 HPA (20W) Hardware Component Kit,Part No. 998HQS--904--1XXKit Part No. * Item Part Number Description Quantity998HQS--904--102 6280--101 4 MCU S/S standard tray 1998HQS--904--103 6278--101 4 MCU S/S tray w/bottomfan1998HQS--904--104 6279--101 4 MCU S/S tray w/left sidefan1998HQS--904--106 6302--101 4 MCU S/S tray w/right sidefan1998HQS--904--107 6277--101 4 MCU S/L standard tray 1* Parts supplied with each kit NIC66H20A00AA0 HPA ARINC connector22 AWG pins20 AWG sockets16 AWG sockets12 AWG socketsSize 5 coaxicons11404342RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--8Table A--5. SD--700 SDU Hardware Component Kit, Part No. XXXXXX--XXX--1XXKit Part No. * Item Part Number Description Quantity998HQS--901--102 6283--101 6 MCU S/S standard tray 1998HQS--901--103 6232--101 6 MCU S/S tray w/bottomfan1998HQS--901--104 6282--101 6 MCU S/S tray w/left sidefan1998HQS--901--106 6045--109 6 MCU S/S tray w/right sidefan1998HQS--901--107 6281--101 6 MCU S/L standard tray 1* Parts supplied with each kit NIC66H21A00AA0 SDU ARINC connector22 AWG pins20 AWG sockets16 AWG sockets12 AWG socketsSize 5 coaxicons13004342Table A--6. BSU Hardware Component Kit, Part No. 970HQS--903--1XXKit Part No. * Item Part Number Description Quantity970HQS--903--101 6064--101 2 MCU S/S standard tray 1970HQS--903--102 6074--101 2 MCU S/S flat bottom tray 1970HQS--903--103 6051--101 2 MCU S/L standard tray 1970HQS--903--104 6120--101 2 MCU S/L flat bottom tray 1* Parts supplied with each kit NIC66F11A00AA0 SCU/BSU ARINC connector22 AWG pins16 AWG sockets12 AWG socketsSize 5 coaxicons1140212H. Air Filtration Assemblies(1) ECS can supply air filtration assemblies for the HPA, SDU, and BSU tray assembliesdescribed in Table A--3 thru Table A--6. These filter assemblies offer protectionagainst airborne contaminants, such as dust and cigarette smoke. Systemmean--time--between--failures (MTBF) can be significantly increased. Appendix Bsupplies installation procedures for air filtration hardware.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--9I. SATCOM Shelf Assemblies(1) ECS supplies customized and standard turnkey plenum shelf assemblies toaccommodate either single or dual SATCOM installations. A shelf assembly canincorporate equipment trays, racking, and additional support structures, such asdisconnect panels, cover plates, and mounting brackets. ECS can supplycomponents that are compatible with all types of air transport aircraft.NOTE: Some SATCOM system installation locations render the aircraft coolingsystem inadequate. ECS has designed a self-contained cooling system fortheSATCOMshelfassemblythatcanbeusedinthistypeofinstallation.J. Additional Avionics Installation Components(1) ECS supplies a variety of additional components to support a SATCOM installation.These include RF splitters, combiners, high power relays, maintenance panels,placards, circuit breakers, and control annunciator panels.K. Antenna System Provisions(1) SATCOM antenna systems are available in numerous configurations. ECS suppliesinstallation provisions for each of these configurations.•Some high-gain top-mounted antenna systems require a 2-MCU tray assemblyand an ARINC 600 connector (Part No. NIC66F11A00AA0) for the BSU. Othersrequire mounting bracketry for the BSU. ECS supplies both BSU 2-MCU trayassembly, and connector and mounting bracketry as required.•ECS supplies trays and ARINC connectors for various SCUs in the market place.•ECS supplies other antenna mounting hardware, such as mounting brackets forthe diplexer/low noise amplifier (D/LNA) and high- and low-gain antenna doublers.L. Cabin Communications System Provisions(1) ECS supplies ARINC 746 compliant air-to-ground communication systems installationprovisions. These provisions include mounting hardware and connectors, shelves,racks, brackets, placards, cover plates, RF cable, connectors, cable assemblies, andwire harness assemblies.M. Wire Harnesses(1) ECS can supply wire harness provisions that interface the SATCOM avionics with thecabin communication units, the cabin communications units with the cabin phones,and both the SATCOM avionics and cabin communication units with other aircraftsystems.(2) ECS wire harness assemblies can be custom designed and fabricated to meetsystem installation requirements.N. Complete Integrated SATCOM Installation Kits(1) Complete system integration packages are available for ECS for virtually any giveninstallation requirements. These integration packages can include any of theinstallation provisions discussed in this section, along with other customer-specifiedcomponents. ECS can also support Honeywell’s customers with systems installationdesign engineering and certification design data packaging.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--103. Hollingsead InternationalA. General(1) This information aids you in selecting the engineering services and installationprovisions offered by Hollingsead International for the various MCS systems.Hollingsead International is rapidly transforming into a world-class avionics andaircraft systems integration leader, providing the capability to perform any or all of thefollowing:•Design and manufacturing of the structural mounting for the MCS and allassociated avionics.•Design and manufacturing of all wire and cable harness assembly interfaceconnections between the MCS and all associated avionics.•Development of all engineering design substantiation, documentation, and testingin support of FAA approval.•Complete on-site support of a full installation team for the entire MCS installationkit.(2) You can contact them at the following address regarding your specific MCS programrequirements:Hollingsead International13701 Excelsior DriveSanta Fe Springs, CA 90670U.S.A.Telephone: (310) 921-3438FAX: (310) 921-6313Telex: 691-462B. Engineering Services(1) As addressed in the previous paragraph, Hollingsead International supplies any levelof engineering support from minimal consultation to full turn-key. Full turn-key supportis defined as Hollingsead International undertaking the entire systems integrationfrom initial design through procurement and manufacture of parts to final installationand certification on behalf on the customer.C. LRU Mounting Requirements(1) MCS avionics are made up of the HPA, SDU, and BSU, which are mounted in ARINC600 style tray assemblies. The HPA and SDU each require forced air cooling duringnormal operation. The BSU and CMU, which are mounted in an ARINC 404 tray,function properly with convection cooling alone.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--11D. Installation Kit Components(1) General(a) Complete system installation kits are available from Hollingsead International forvirtually any given installation requirement. These installation kits can include anyof the installation provisions discussed herein along with othercustomer-specified components.(2) Coaxial Cables(a) All coaxial cables, connectors, and attenuators have been designed to fulfill theMCS system and the ARINC 741 usage and attenuation requirements.Hollingsead International supplies immediate access to several types andmanufacturers of coaxial cable, appropriate N or TNC connectors, andattenuators to make sure the specific attenuation profiles for each aircraftinstallation is achieved. These cables range in nominal attenuation from 1.27 to16.3 dB per 100 feet at 1.6 GHz. The cable outer diameter range is from 0.206inch to 1.55 inches. Each cable assembly is fabricated with an individual partnumber and, where necessary, is assigned a serial number, which ispermanently affixed to each end. Serialization insures traceability andreproducibility.(b) Testing of each cable assembly is performed to verify insertion loss and VSWR.The results become part of a test database and are shipped with each cableassembly. Each cable assembly is tested across the MCS system frequencybandwidth. Transmit path cable assemblies are test swept from 1626.5 MHz to1660.5 MHz and receive path cable assemblies are test swept from 1530 MHz to1559 MHz. Customers have the option of having cable assemblies tested with orwithout attenuators.(3) Connectors(a) Hollingsead International supplies the appropriate ARINC connectors for ARINCCharacteristic 741 style avionics electrical interfaces. The SATCOM rack-sideconnector blocks are appropriately mounted on each tray assembly. HollingseadInternational supplies ARINC 600 Size 1 coaxial connectors with the necessarytermination kit assembly instructions.(b) The connector part numbers are as follows:•SDU -- C--06B3--0204--0100•HPA (40W) -- C--06B3--0708--0100•HPA (20W) -- C--06B3--0708--0100•BSU -- C--06B1--0101--0100•CMU -- DPX2MA--A106PA106P--33B--0001.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--12(4) Tray Assemblies(a) Hollingsead International manufactures several tray assemblies for the MCSavionics. These tray assemblies come with or without independent coolingsystems to ensure installation flexibility. Where forced air cooling is required,these tray assemblies have been specially designed to meet the coolingrequirements of each LRU using a single fan. Tray assemblies are supplied withinsertion/extraction front hold-downs as standard, but are available with otherfront hold-down options. Table A--7 identifies the various tray options andFigure A--4 identifies the dimensions for each tray assembly.Table A -- 7.Tray Assembly Part NumbersStandardTaAssembly Fan LocationTypeTrayAssembly Bottom Left Side Right Side Left Rear Right Rear8MCUS/S 1708006--101 1708007--101 1708008--101 1708008--102 N/A N/A8MCUS/L 1708006--201 1708007--201 1708008--201 1708008--202 1708009--101 1708009--1026MCUS/S 1706007--101 1706008--101 1706009--101 1706009--102 N/A N/A6MCUS/L 1706007--201 1706008--201 1706009--201 1706009--202 1706010--101 1706010--1024MCUS/S 1704008--101 1704009--101 1704010--101 1704010--102 N/A N/A4MCUS/L 1704008--201 1704009--201 1704010--201 1704010--202 1704011--101 1704011--1022MCUS/S 1702002--101 1702003--1012MCUS/L 1702002--201 1702003--201RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--13/(A--14 blank)Figure A--4. Dimensions for Hollingsead Tray AssembliesRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--15(5) Plenum Shelf Assemblies(a) Hollingsead International supplies customized and standard turnkey plenumshelf assemblies to accommodate either single or dual MCS system installations.A shelf assembly can incorporate equipment trays, racking, and additionalsupport structures such as disconnect panels, cover plates, and mountingbrackets. Hollingsead International can supply components that are compatiblewith all types of air transport aircraft.(6) Additional Components(a) Hollingsead International supplies a variety of additional components to supportan MCS installation, including RF splitters, combiners, high power relays,maintenance panels, placards, circuit breakers, and control enunciator panels.(7) Antenna System Provisions(a) The antenna subsystems for the MCS system are available in numerousconfigurations. Hollingsead International supplies installation provisions for eachof these configurations. Some high-gain, top-mounted antenna systems use a2-MCU tray assembly and ARINC 600 connector for the BSU. Others usemounting bracket hardware for the BSU. Hollingsead International supplies bothBSU 2-MCU tray assemblies and mounting bracket hardware as necessary.Hollingsead International supplies other antenna mounting hardware such asmounting brackets for the diplexer/LNA and high-gain and low-gain antennadoublers.(8) Cabin Communications System Provisions(a) Hollingsead International supplies ARINC 746 compliant air-to-groundcommunications system installation provisions. These provisions includemounting hardware and connectors, shelves, racks, brackets, placards, coverplates, RF cable, connectors, cable assemblies, and wire harness assemblies.(9) Wire Harness Assemblies(a) Hollingsead International wire harness assemblies are custom designed andfabricated to meet each customer’s specific system installation requirements.Hollingsead International supplies wire harness assemblies for the followinginterfaces:•MCS avionics and cabin communication units•MCS avionics and flight deck data and voice communication sources•Cabin communications units and cabin telephones•Both the SATCOM avionics and cabin communication units with other aircraftsystems.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--164. Signal Conditioning UnitA. General(1) The SCU (Racal Part No. 56047--010XX) is manufactured by Racal Avionics in theU.S.A. Contact the project manager at the following address for additional informationnot supplied in this section:Racal Avionics Incorporated8851 Monard DriveSilver Spring, MD 20910U.S.A.Telephone: (301) 495-6695FAX: (301) 585-7578Telex: 898316(2) The MCS system requires ARINC 429 data for antenna pointing, antennastabilization, and Doppler frequency correction. These requirements are defined inTable A--8. If the aircraft does not have an IRS that supplies this ARINC data, theSCU can be used to supply the data.(3) The SCU is packaged as an ARINC 600 2 MCU and weighs a maximum of 5.95pounds (2.70 kilograms). The outer case of the SCU is constructed from twohalf-shells identical in dimensions, which are made of an aluminum alloy 1.6millimeters thick. The front and rear panels are made of the same alloy 3.3millimeters thick. Both panels attach to the outer half-shells with corner brackets. Twodivider plates mount between the half-shells of the outer case to supply additionalrigidity and electrical shielding.(4) The SCU translates and consolidates various input data formats into a two-wiredifferential ARINC 429 high speed output for latitude and longitude position, trueheading, track angle, ground speed, and pitch and roll attitude. Program pins definethe particular type of data being received. These pins are interrogated at power on bythe software to determine the required configuration.(5) The SCU operates from a nominal 115 V ac, 400 Hz single phase supply and/or from28 V dc primary power. Input pins are supplied for both power sources in the ARINC600 connector, and both power inputs can be connected to the aircraft power.Current consumption depends on the input voltage and temperature, but is typically0.25 amperes at 115 V ac or 0.40 amperes at 28 V dc.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--17Table A--8. ARINC 429 Data RequirementsLabel DefinitionMinimumRate (MS)MaximumRate (ms)310 Latitude of present position 334 67311 Longitude of present position 334 67312 Ground speed 125 22313 Track angle 55 22314 True heading 55 22324 Pitch 40 8325 Roll 40 8B. Operator Functions(1) The front panel contains six LED indicators to allow monitoring of the SCU status.However, these indicators are intended for use during repair by maintenancepersonnel rather than by the operator during normal flight operation. Discrete outputsrepresenting the state of each LED indicator are also supplied for remote monitoring.The functions of these discretes are defined in Table A--9.Table A--9. SCU Discrete FunctionsColor Nomenclature FunctionGreen Power Indicates SCU is on and all voltages are correct when lit.Green SCU Valid Indicates correct operation of the SCU logic and processingcircuits when lit.Red BIT Fail •Indicates normal operation when off.•Indicates BIT is running repetitively when flashing slowly.Indicates the SCU has failed BIT when steadily lit.•Indicates the SCU has failed BIT when steadily lit.Amber Signal 1 Indicates selection of input channel 1 when lit.Amber Signal 2 Indicates selection of input channel 2 when lit.Amber Signal 3 Indicates selection of input channel 3 when lit.(2) Three amber LED indicators supply an error code that is displayed when the SCUfails in the BIT mode. The red indicator lights and a three-bit code is continuouslydisplayed on the amber LEDs as indicated in Table A--10. BIT is interruptive and allnormal operation ceases during the time when the SCU is in the BIT mode.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--18Table A--10. SCU Error CodeFailure Code LED 1 LED 2 LED 3ARINC 429 translator not programmed 1ON OFF OFFRAM read/write failed 2OFF ON OFFARINC 561 translator failed 3ON ON OFFPROM checksum failed 4OFF OFF ONARINC 561 translator not programmed 5ON OFF ONDiscrete input failed 6OFF ON ONARINC 429 translator failed 7ON ON ONC. Control Functions(1) Normal operation of the SCU is fully automatic and does not require operatorintervention. Some control functions are supplied through the main ARINC 600connector. These functions include:•Remote SCU on/off control•BIT initiate control•Signal select A•Signal select B•Program pin A•Program pin B•Program pin C.(2) The remote SCU on/off control line enables the operation of the SCU power supply.Thecontrollineisactivelowandmustbeconnectedtogroundtoenableoperationofthe SCU. An open circuit or 28 V dc on this line shuts down operation of the SCU.(3) The BIT initiate control line is an active low input used to enable BIT in the SCU. TheBIT mode is an optional function that supplies a pre/post-flight confidence check andis intended for use by maintenance personnel as a diagnostic tool. The SCU remainsin the BIT mode as long as the BIT initiate control line is grounded. An open circuit or28 V dc on this control causes the SCU to return to normal operation.(4) Signal selection is normally an automatic function under control of the internal SCUprogram and is based on the validity of the received data. The signal select controllines supply an override of this automatic function to allow manual selection of oneinput from three available sources. The signal select control lines are active low andare internally pulled high. Manual selection is accomplished by applying a ground tothe control lines as given in Table A--11.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--19Table A--11. SCU Manual Signal SelectionSignal Select Control LinesFunction A BAutomatic Selection High HighSelect Input No. 1 Low HighSelect Input No. 2 High LowSelect Input No. 3 Low LowD. System Functions(1) Initialization(a) Operation begins with BIT when the SCU is activated by applying aircraft powerand grounding the on/off control line. Testing normally takes approximately 0.5second and when BIT passes normal operation begins. If the SCU fails the initialBIT check, the unit latches in the BIT mode and displays an error code with theamber LED indicators.(2) Automatic Input Selection Mode(a) There are three available data input channels. Unless a channel is manuallyselected, the input to be used by the SCU is selected automatically. After initiallyselecting Channel 1, the SCU checks for the presence of the required validwords in the input data stream and the status of the attitude warning discretefrom the selected synchro channel. If all validity conditions are met within 1.6seconds from the initial channel selection, the SCU locks on to the currentchannel and continues to operate from that data source. The appropriate amberLED indicator lights to indicate the selected channel to operator. If any of therequired data is invalid, the SCU cycles to the next input channel until a channelproviding a complete frame of valid data is received.(3) Valid Channel Condition(a) Conditions that must exist to let the SCU accept the current input channelinclude:•At least one new data word for each of the required labels is received withinthe specified time period.•The sign/status matrix (SSM) of all words for all required labels must be valid.•The primary attitude warning input discrete must be in a valid state to indicatethe synchro inputs for attitude are usable.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--20(4) Channel Switching Timing(a) The SCU allows 1.6 seconds for the selected input channel to receive a validdata frame. However, if 1.6 seconds has passed and the valid channelconditions have not been satisfied, the input channel cycles to the nextsequential channel. If all three input channels have been checked and none arevalid, the SCU prevents further cycling of the input channel selection for 1minute. This prevents the SCU from continuously cycling when the inertialnavigation units or other sources of navigation data have not been initialized.After the 1-minute delay, the SCU again initiates the checking cycle.(5) Data Input(a) A data subset made up of present latitude and longitude, true heading, trackangle, and ground speed is received through either the ARINC 561--6 wire inputsor the ARINC 571--2 wire inputs as defined by the program pin selections. Whenused as a selector of ARINC 404 data inputs, pitch and roll labels are alsoincluded. The words are selected from the data stream by their octal labels whileother words are ignored. Program pin selections and associated data formatsand labels are defined in Table A--12 thru Table A--16.Table A--12. ARINC 561 Binary DataProgram PinOctal Label Coded ABC Definition310 Binary 000Latitude of present position311 Binary 000Longitude of present position212 Binary 000Ground speed213 Binary 000Track angle214 Binary 000True headingTable A--13. ARINC 561 BCD DataProgram PinOctal Label Coded ABC Definition010 BCD 100Latitude of present position011 BCD 100Longitude of present position012 BCD 100Ground speed013 BCD 100Track angle014 BCD 100True headingRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--21Table A--14. ARINC 571 Data, ARINC 429 FormatProgram PinOctal Label ABC Definition310 010Latitude of present position311 010Longitude of present position212 010Ground speed213 010Track angle214 010True headingTable A--15. ARINC 571 Data, ARINC 419 FormatProgram PinOctal Label ABC Definition210 110Latitude of present position211 110Longitude of present position212 110Ground speed213 110Track angle214 110True headingTable A--16. ARINC 404 Data, ARINC 429 FormatProgram PinOctal Label ABC Definition310 001Latitude of present position311 001Longitude of present position312 001Ground speed313 001Track angle314 001True heading324 001Pitch325 001Roll(b) The SSM of each received data word is checked. Valid words are converted toARINC 429 data. Invalid words are discarded.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--22(c) With exception of the ARINC 404 input, the SCU also receives attitude data froman associated attitude source. The attitude data is in the form of ARINC 407pitch and roll synchro channels and an attitude warning flag. Attitude data isselected from a source associated with the source selected for digital data. Theattitude inputs used are given in Table A--17.Table A--17. SCU Attitude Data InputsData Line FunctionRoll Synchro XRoll Synchro YRoll Synchro ZPitch Synchro XPitch Synchro YPitch Synchro ZRoll/Pitch Reference HIRoll/Pitch Reference LOWarning Flag HI Flag (HI = Good)(d) The pitch and roll synchro inputs are read every 20 milliseconds. The attitudewarning flag is sampled before each computation to check the validity of theinput data before the data is accepted.(6) Data Output(a) The SCU transmits ARINC 429 serial words at a rate of one completeseven-word message every 20 milliseconds. The SSMs in the navigation datawords are based on those supplied by the digital input words. The SSM data forthe attitude words is derived from computations and from the primary warningflag.(b) The data output is in accordance with ARINC 429 high speed data (100 kHzclock speed). The SCU outputs ARINC 429 data on two separate ports operatingin parallel. Data from both ports is identical, but independent output buffers areused to supply redundancy.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--23E. ARINC 600 Connector Pin Assignments(1) The rear connector (ARINC Part No. NIC66F11A00AA0) of the SCU complies withARINC Characteristic 600 as specified in the following:•ARINC 600 -- Size MCU 2 no. 2 shell•Type 0X top insert•Type 0X middle insert•Type 0X bottom insert•Index pin code 0X.(2) The contact arrangements for the connector are specified in Table A--18. An examplepin designation of BC12 for the table is given below.Pin Designation Example: Pin BC12Connector Cavity IdentifierTop Cavity = AMiddle Cavity = BBottom Cavity = CColumn Identifier(A,B,C,orD)Row Identifier(1 thru 15)B--C --12RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--24Table A--18. Contact Arrangements for SCU ARINC 600 ConnectorPin Function RemarksAC1 ARINC 561 Data No. 1 (HI) Note 1.AD1 ARINC 561 Data No. 1 (LO) Note 1.AC2 ARINC 561 Clock No. 1 (HI) Note 1.AD2 ARINC 561 Clock No. 1 (LO) Note 1.AC3 ARINC 561 Strobe No. 1 (HI) or ARINC 429/419 Data No. 1 (HI) Note 1.AD3 ARINC 561 Strobe No. 1 (LO) or ARINC 429/419 Data No. 1 (LO) Note 1.AC4 SpareAD4 SpareAC5 SpareAD5 SpareAC6 SpareAD6 SpareAC7 SpareAD7 SpareAC8 SpareAD8 SpareAC9 ARINC 561 Data No. 3 (HI) Note 1.AD9 ARINC 561 Data No. 3 (LO) Note 1.AC10 ARINC 561 Clock No. 3 (HI) Note 1.AD10 ARINC 561 Clock No. 3 (LO) Note 1.AC11 ARINC 561 Strobe No. 3 (HI) or ARINC 429/419 Data No. 3 (HI) Note 1.AD11 ARINC 561 Strobe No. 3 (LO) or ARINC 429/419 Data No. 3 (LO) Note 1.AC12 SpareAD12 SpareAC13 ARINC 407 Pitch No. 1 X Note 2.AD13 ARINC 407 Pitch No. 1 Y Note 2.AC14 ARINC 407 Pitch No. 1 Z Note 2.AD14 ARINC 407 Heading X ReservedAC15 ARINC 407 Heading Y ReservedAD15 ARINC 407 Heading Z ReservedRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--25Table A--18. Contact Arrangements for SCU ARINC 600 Connector (cont)Pin RemarksFunctionAA1 ARINC 407 Pitch No. 3 X Note 2.AB1 ARINC 407 Pitch No. 3 Y Note 2.AA2 ARINC 407 Pitch No. 3 Z Note 2.AB2 Attitude Warning No. 1 (From Attitude Source) Note 2.AA3 ARINC 407 Reference No. 1 (HI)AB3 ARINC 407 Reference No. 1 (LO)AA4 ARINC 407 Heading Reference (HI) ReservedAB4 ARINC 407 Heading Reference (LO) ReservedAA5 ARINC 407 Reference No. 3 (HI)AB5 ARINC 407 Reference No. 3 (LO)AA6 Attitude Warning No. 3 (From Attitude Source) Note 2.AB6 SpareAA7 ARINC 407 Roll No. 1 X Note 2.AB7 ARINC 407 Roll No. 1 Y Note 2.AA8 ARINC 407 Roll No. 1 Z Note 2.AB8 SpareAA9 SpareAB9 SpareAA10 SpareAB10 SpareAA11 ARINC 407 Roll No. 3 X Note 2.AB11 ARINC 407 Roll No. 3 Y Note 2.AA12 ARINC 407 Roll No. 3 Z Note 2.AB12 SpareAA13 ARINC 404 Echo (HI) Note 3.AB13 ARINC 404 Echo (LO) Note 3.AA14 SpareAB14 SpareAA15 SpareAB15 SpareRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--26Table A--18. Contact Arrangements for SCU ARINC 600 Connector (cont)Pin RemarksFunctionBC1 ARINC 407 Pitch No. 2 X Note 2.BD1 ARINC 407 Pitch No. 2 Y Note 2.BC2 ARINC 407 Pitch No. 2 Z Note 2.BD2 SpareBC3 ARINC 407 Roll No. 2 X Note 2.BD3 ARINC 407 Roll No. 2 Y Note 2.BC4 SpareBD4 ARINC 407 Roll No. 2 Z Note 2.BC5 SpareBD5 Attitude Warning No. 2 (From Attitude Source) Note 2.BC6 ARINC 407 Reference No. 2 (HI)BD6 ARINC 407 Reference No. 2 (LO)BC7 Signal Source Select A (Input No. 1) Note 4.BD7 Signal Source Select (Input No. 2) Note 4.BC8 BIT initiate (Input No. 3) Note 5.BD8 SpareBC9 BIT Failed (Output No. 2) ReservedBD9 SCU Valid ReservedBC10 Superflag (+28 V dc = Output Valid) Note 6.BD10 /Superflag (<1 V dc = Output Valid) Note 6.BC11 Program Pin A (Input No. 5) Note 7.BD11 Program Pin B (Input No. 6) Note 7.BC12 Program Pin C (Input No. 7) Note 7.BD12 SpareBC13 SpareBD13 SpareBC14 SpareBD14 SpareBC15 ARINC 429 Out No. 1 (HI)BD15 ARINC 429 Out No. 1 (LO)RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--27Table A--18. Contact Arrangements for SCU ARINC 600 Connector (cont)Pin RemarksFunctionBA1 SpareBB1 SpareBA2 ARINC 429 Out No. 2 (HI)BB2 ARINC 429 Out No. 2 (LO)BA3 SpareBB3 SpareBA4 Discrete Out No. 3 (Select No. 2 LED) ReservedBB4 Discrete Out No. 4 (Select No. 3 LED) ReservedBA5 Discrete Out No. 5 (Select No. 1 LED) ReservedBB5 Discrete Out No. 6 ReservedBA6 Discrete Out No. 7 ReservedBB6 Discrete Out No. 8 ReservedBA7 ARINC 561 Data No. 2 (HI) Note 1.BB7 ARINC 561 Data No. 2 (LO) Note 1.BA8 ARINC 561 Clock No. 2 (HI) Note 1.BB8 ARINC 561 Clock No. 2 (LO) Note 1.BA9 ARINC 561 Strobe No. 2 (HI) or ARINC 429/419 Data No. 2 (HI) Note 1.BB9 ARINC 561 Strobe No. 2 (LO) or ARINC 429/419 Data No. 2 (LO) Note 1.BA10 +28 V dc Power Aircraft Power (Note 8.)BB10 +28 V dc Power Aircraft Power (Note 8.)BA11 0 V dc Power Return Aircraft Power (Note 8.)BB11 0 V dc Power Return Aircraft Power (Note 8.)BA12 Chassis GroundBB12 Remote SCU On/Off Control Note 9.BA13 Shield return Connected to ChassisBB13 Shield Return Connected to ChassisBA14 115 V ac Power 400 Hz (HI) Aircraft Power (Note 8.)BB14 Chassis GroundBA15 115 V ac Power 400 Hz (LO) Aircraft Power (Note 8.)RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--28Table A--18. Contact Arrangements for SCU ARINC 600 Connector (cont)Pin RemarksFunctionBB15 Chassis GroundNOTES:1. The 6-wire ARINC 561 or 2-wire ARINC 429/419 (ARINC 571/404) data can be routed from up to three sources.However, if a single input is supplied, it should be connected to the No. 1 inputs as indicated. Inputs No. 2 and 3should be left open. The type of data being used, either ARINC 561 or ARINC 571/404, must be indicated byselecting the proper program pins as specified in NOTE 7. Also, refer to NOTE 4. for more information on selectinga specific input as the data source.2. The synchro pitch and roll data can be routed from up to three sources. However, sources of attitude data must bepaired with sources of ARINC 561 or ARINC 571 data. Thus, if only one source of ARINC 561 or ARINC 571 datais available, then only one source of attitude data can be used. An attitude warning flag for each source of attitudethat is active must be supplied. +28 V dc = valid. Ground or open = invalid.3. When the SCU is used as a selector/controller of multiple ARINC 404 compatible data sources, the receivingequipment should be connected to the ARINC 404 echo outputs. In this configuration, the input as valid by theSCU is routed back out of the unit on these pins. Since attitude data is embedded in the ARINC 404 data stream,no attitude inputs are used.4. When multiple sources of data are available and routed to the SCU, it automatically searches for an input with validattitude data and ARINC 561/571 data. If only one source of ARINC 561/571 data and attitude data is available, theSCU should be connected to only one input and the signal source select lines should be linked as applicable forthe selected input as given in Table A--19.5. Grounding the BIT initiate input forces the SCU to enter the interruptive BIT mode and repetitively do its BITroutines until ground is removed. BIT is automatically done at each power-up cycle. This input should be an open, ifnot used.6. The superflag output is +28 V dc whenever the SCU is operating normally and the output data is valid. If a portionof the input data is invalid or the SCU detects an internal fault, then the superflag output is 0 V dc. The /superflagoutput is the inverse of the superflag output.7. The data format and characteristics accepted by the SCU are programmable through pins A, B, and C. Thecombinations supported by the SCU are specified in Table A--20.8. The SCU operates from either +28 V dc or 115 V ac, 400 Hz power. The power source not used should remainunconnected.9. The remote SCU on/off control can be used to power down the SCU from a remote location. A ground activates theunit and an open switches the unit off. If remote control is not required, this pin should be permanently grounded atthe connector.Table A--19. Signal Source Select LinesSignal Source Select A BAuto Open OpenInput No.1 Ground OpenInput No. 2 Open GroundInput No. 3 Ground GroundRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--29Table A--20. SCU Program Pin CombinationsProgram PinsABC Input Description000ARINC 561 data, binary labels, synchro attitude100ARINC 561 data, BCD labels, synchro attitude010ARINC 571 data with ARINC 429 format, synchro attitude110ARINC 571 data with ARINC 419 format, synchro attitudeNOTE: Ground = 1; open = 0.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page A--30Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page B--1APPENDIX BINSTALLATION PROCEDURES FOR SATCOM AIR FILTRATIONSYSTEMS1. IntroductionA. General(1) Appendix B contains information on the different air filtration systems available for theSATCOM installations. Procedures for installing these air filtration systems are alsosupplied. After you have determined the proper air filtration system for your needs,follow the appropriate procedures in paragraph 4.(2) The SATCOM system (SDU and HPA) is designed to ARINC 600 standards includingARINC 600 cooling requirements. ARINC 600 calls for the cooling air to contain nocontamination particles in excess of 400 microns. Several installation designs do notsupply cooling air in accordance with ARINC 600. The OEM installation design for theB747, B767, and B777 supply unfiltered cooling air (cabin air) to the SATCOM LRUs.As a result, contaminants in the air tend to accumulate on and inside the LRUssometimes blocking off the cooling air passages. This leads to units operating at ahigher temperature, which can result in decreasing the MTBF of the units.(3) Filter assemblies have been designed that attach to the SATCOM LRUs or to theLRU trays. These filter assemblies contain filter media that filter out contaminantsbefore entering the LRUs. This design is for installations where the cooling air isdrawn through the LRU top to bottom, and where there is at least 1 inch of clearanceabove the LRUs to allow for the assembly itself. Thus, the air filtration units includedin this appendix are acceptable for installation on the B747 and B777 aircraft, butbecause of clearance problems, are not acceptable for installation on theOEM-provisioned B767 aircraft.2. Continued AirworthinessA. GeneralCAUTION: THE FILTER MEDIA MUST BE REPLACED (OR CLEANED) APPROXIMATELYEVERY 4000 FLIGHT HOURS OR EVERY C CHECK, WHICHEVER COMESFIRST, OR THE EFFECTIVENESS OF THE AIR FILTRATION ASSEMBLY CANBE DEGRADED.(1) The selection of the type of filter media cartridge is based on the following:•Effectiveness of the filter media in removing contaminants from the cooling airbefore entering the SATCOM LRUs.•Impact of the filter media on the cooling air mass flow rate through the units.•Time between removals.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page B--23. Equipment and MaterialsA. GeneralWARNING: BEFORE YOU USE A MATERIAL, KNOW THE HAZARD CODE AND GET THENECESSARY PROTECTION. REFER TO THE PAGE ABOUT HAZARD CODESFOR MATERIALS IN THE FRONT OF THIS MANUAL.(1) Refer to Table B--1 for a list of materials.Table B -- 1. MaterialsItem Description SourceHMN 9730178 Retaining compound(MIL--S--22473, grade A) — GradeALoctite Corp, Rocky Hill, CT(05972)HMN 9731178 Primer for retaining compound,ready--to--use, quick(MIL--S--22473, grade T, form R)— Locquic Grade TNOTES: NOTES:1. Equivalent alternatives are permitted for equipment and materials in this list.2. The HMN codes in the list of materials identify the Honeywell Material Number (HMN) given to each material.(2) The equipment listed in Table B--2, Table B--3, and Table B--4 supplies the necessaryhardware to install air filtration systems on the aircraft. Find the air filtration systemand filter that best fits your needs and contact the company that manufacturers thatparticular equipment.Table B--2. Air Filtration Systems from ECS for a Top Mount AssemblyEquipment Quantity LRU Part No. SATCOM SystemSATCOM Filter Assembly 1SDU 10919--101 6--MCU assemblySATCOM Filter Assembly 1HPA (20W) 10968--101 4--MCU assemblySATCOM Filter Assembly 1HPA (40W) 10923--101 8--MCU assemblyFilter Cartridge Assembly 1SDU 10907--105 6--MCU assemblyFilter Cartridge Assembly 1HPA (20W) 10907--104 4--MCU assemblyFilter Cartridge Assembly 1HPA (40W) 10907--106 8--MCU assemblyRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page B--3Table B--3. Air Filtration Systems from ECS for a Body--Mounted DesignEquipment Quantity LRU Part No. SATCOM SystemSATCOM Filter Assembly 1SDU P0329--106 6--MCU assemblySATCOM Filter Assembly 1HPA (20W) P0329--104 4--MCU assemblySATCOM Filter Assembly 1HPA (40W) P0329--108 8--MCU assemblyFilter Cartridge Assembly 1SDU 20008--05 6--MCU assemblyFilter Cartridge Assembly 1HPA (20W) 20008--04 4--MCU assemblyFilter Cartridge Assembly 1HPA (40W) 20008--06 8--MCU assemblyTable B--4. Air Filtration Systems from ECS for a Tray--Mounted DesignEquipment Quantity LRU Part No. SATCOM SystemSATCOM Filter Assembly 1SDU 20005--103 6--MCU assemblySATCOM Filter Assembly 1HPA (20W) 20005--102 4--MCU assemblySATCOM Filter Assembly 1HPA (40W) 20005--104 8--MCU assemblyFilter Cartridge Assembly 1SDU 20008--05 6--MCU assemblyFilter Cartridge Assembly 1HPA (20W) 20008--04 4--MCU assemblyFilter Cartridge Assembly 1HPA (40W) 20008--06 8--MCU assemblyRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page B--44. Installation InstructionsA. Top Mount Assembly(1) The ECS top mount air filtration assembly is designed to clamp to the top of theSATCOM LRUs so it does not come off the LRU. Once attached to the top of theLRU, it forms a seal letting only filtered air enter the LRU. The assembly is held to thetop of the LRU by friction from the sides of the assembly and by the clamps thatsupply friction to the front and rear panels of the unit. Figure B--1 shows the locationof the components for the following procedures.(2) Install the filter assembly to an SDU or HPA using the following steps.(a) Make sure the correct size assembly is selected for the given LRU (refer toTable B--2).(b) OPTIONAL — Remove the SATCOM LRU from its tray and set it on a securesurface. (The assembly can be installed while the unit is in the rack.)(c) Install the air filtration media inside the air filtration assembly in the rectangularfilter frame.(d) Place the filter assembly over the top of the LRU with the clamps in the up(thumb lever over the top of the filter assembly) position and pointing toward you.(e) Push down on the air filtration unit until it fits over the top of the SATCOM LRU.The sides of the air filtration assembly may need to be spread open slightly priorto sliding over the sides of the LRU.(f) Once the air filtration unit is firmly seated to the top of the LRU, clamp theassembly to the unit by pushing down on the two thumb levers until they lock intoposition. The thumb levers pass through approximately 180 degrees of rotationfor the clamping process.(g) Make sure the air filtration assembly remains seated firmly against the top of theLRU to maintain the air seal.(h) Make sure the air filtration assembly is held tightly to the unit by gently lifting upon the assembly; making sure the assembly does not pull off of the LRU.(i) OPTIONAL -- Install the SATCOM LRU back into its tray if removed in step4.A.(2)(b).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page B--5Figure B--1. ECS Top Mount Air Filtration Assembly(3) Replace the filter media according to the following steps.(a) Gain access to the SATCOM LRUs.(b) Lift up on the two thumb levers (approximately 180 degrees).(c) Pull up on the air filtration unit until it lifts off the top of the SATCOM LRU. Thesides of the air filtration assembly may need to be spread open slightly prior tosliding up the sides of the LRU.(d) Remove the air filtration media from the air filtration assembly in the rectangularfilter frame.(e) Once the assembly is removed, pull the filter assembly out of its retaining fixtureand discard the filter appropriately.(f) Obtain a new filter.(g) Make sure the correct size filter assembly is selected for the given LRU (refer toTable B--2).(h) Install the new filter media into the filter assembly retaining fixture.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page B--6(i) OPTIONAL — Remove the SATCOM LRU from its tray and set on a securesurface. (The assembly can be installed while the unit is in the rack.)(j) Install the air filtration media inside the air filtration assembly in the rectangularfilter frame.(k) Place the filter assembly over the top of the LRU with the clamps in the up(thumb lever over the top of the filter assembly) position and pointing toward you.(l) Push down on the air filtration unit until it fits over the top of the SATCOM LRU.The sides of the air filtration assembly may need to be spread open slightly priorto sliding over the sides of the LRU.(m) Once the air filtration unit is firmly seated to the top of the LRU, clamp theassembly to the unit by pushing down on the two thumb levers until they lock intoposition. The thumb levers will pass through approximately 180 degrees ofrotation for the clamping process.(n) Make sure the air filtration assembly remains seated firmly against the top of theLRU to maintain the air seal.(o) Make sure the air filtration assembly is held tightly to the unit by gently lifting upon the assembly to verify the assembly does not pull off the LRU.(p) OPTIONAL -- Install the SATCOM LRU back into its tray if removed in step4.A.(3)(i).B. Body--Mounted Assembly(1) The ECS body-mounted air filtration assembly is designed to strap around the bodyof the SATCOM LRUs in a way that it will not come off the LRU. Once attached to theLRU, it forms a seal allowing only filtered air to enter the LRU. The assembly is heldto the top of the LRU with a strap that fits securely around the body of the unit. Thefiltration unit sits on top of the SATCOM LRU. The strap runs down the side,underneath, and up the other side of the LRU. By way of a clamping system on top ofthe LRU, the strap is pulled tight, which firmly secures the filter assembly to the top ofthe unit.(2) Install the filter assembly to an SDU or HPA according to the following steps.(a) Make sure the correct size assembly is selected for the given LRU(refer to Table B--3).(b) Remove the SATCOM LRU from its tray and set it on a secure surface.(c) Slide the filter strap around the front of the LRU so the strap is underneath andcoming up each side of the LRU.(d) Place the filter assembly on top of the LRU so the back lip of the assembly unitfits over the back of the LRU.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page B--7(e) Pull the strap around the top of the filter assembly unit so the two ends of thestrap overlap. The strap should come over the top of the filter assembly on thefront end of the assembly (dog-house end of the LRU). A channel is built into thefilter assembly for the strap.(f) With the strap in place, latch the strap together by inserting the lips of the strapends together so they latch together. With the LRU facing you, the strap on theleft-hand side should latch over the top of the strap on the right-hand side.(g) Once the strap is latched, make sure the lip on the rear of the filter assembly isseated firmly just over the rear of the LRU.(h) Make sure the filter retainer mechanism is latched closed.(3) Replace the filter media according to the following steps. Figure B--2 shows thelocation of the components used.(a) Gain access to the SATCOM LRUs.(b) Locate the filter retaining clips located on the forward end of the filter assemblymechanism.(c) Slide the retainer clips (one on the left and one on the right) out to disengage theclips from the latching pins.(d) Lift the filter retaining tray up, (hinged on the rear side) remove the filter mediacartridge and discard the filter appropriately.(e) Install the new filter media by placing a new filter media cartridge in the filterretaining tray chamber.(f) Lower the filter retaining tray down until the locating pins protrude through theclearance holes on the filter retaining tray.(g) Slide the retaining clips (left and right) in until they latch around the latching pins.C. Tray--Mounted Assembly(1) The ECS tray-mounted air filtration assembly is designed as an integral part of theequipment tray and does not attach to the LRU itself. The SATCOM LRU slides intothe tray, sandwiched between the tray and plenum below, and the air filtrationassembly above. Since the air filtration assembly is an integral part of the equipmenttray, in order to install this type of assembly, a modified equipment tray must bepurchased for each LRU.(2) Replace the filter media according to the following steps. Figure B--2 shows thelocation of the components used.(a) Gain access to the SATCOM LRUs.(b) Locate the filter retaining clips located on the forward end of the filter assemblymechanism.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page B--8(c) Slide the retainer clips (one on the left and one on the right) out to disengage theclips from the latching pins.(d) Lift the filter retaining tray up (hinged on the rear side) and remove the filtermedia cartridge. Discard the filter media cartridge appropriately.(e) Install the new filter media by placing a new filter media cartridge in the filterretaining tray chamber.(f) Make sure the filter cartridge is supported on the air plenum seals. The directionof airflow through the filter is not important.(g) Lower the filter retaining tray until the locating pins protrude through theclearance holes on the filter retaining tray.(h) Slide the retaining clips (left and right) in until they latch around the latching pins.Figure B--2. Front and Side Views Showing Filter RemovalRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--1APPENDIX COWNER REQUIREMENTS TABLE1. OverviewA. General(1) Appendix C contains information on the owner requirements table (ORT) and isstored in non--volatile memory in the SDU. The ORT contains information relating todifferent areas of functionality, such as log-on and telephony. The ORT does not loseits contents because of the loss of SDU primary power or as a result of PAST. AllORT contents are set to default values by a factory settings restart. The ORTcontains all pilot and aircraft operator entered information preserved when the SDU ispowered-down. The characteristics of the ORT are specified in Table C--1.NOTE: Honeywell supplies Windows--based software (ORT editor) that is used togenerate the ORT files for upload. Contact your Honeywell representative fora copy of this software.Table C--1. ORT CharacteristicsORT Item Characteristic Attributes DescriptioniLog-On Policy Secured,commonThis item defines the log-on procedure. When the SDU haspower applied, the SDU either starts the automatic log-onprocedure at the earliest opportunity (automatic), or the SDUgoes to an inert standby state, even if the SDU is entirelyfailure free, where the SDU then waits for user stimulus tostart logging-on (commanded).ii Satellite/GESNamesUser,commonThis item defines associated names for the satellites andGESs. Satellite names are up to five characters long. GESnames are up to 14 characters long. Names made up ofupper case letters, decimal digits, hyphens, and spaces areallowed. A GES name can include satellite and serviceidentifying strings; e.g., GOON A--E SKY takes 12 charactersand identifies Goonhilly, the United Kingdom GES servicingthe Skyphone consortium and using the Atlantic ocean regioneast satellite.iii GES PreferenceValuesUser,commonThis item defines the automatic log-on preference values forGESs from 0 to 9, where 9 corresponds to the most preferredGES. The interpretation of preference value 0 is determinedby item lvi, 0 is either the least preferred GES or it is not usedfor automatic log-on. GESs with preference level 0 can still beused for a constrained log-on. When all GESs on a particularsatellite have a preference level of 0 and this satellitebecomes the candidate for logon, the logon processingconsiders all of these GESs to have a preference level of 1 tofacilitate continued SATCOM operation.iv MaintenancePage AccessUser,commonThis item defines whether the SCDU maintenance pages areaccessible as: a) never; b) always; or c) only when the aircraftis on the ground.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--2Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristicvCockpitTelephoneNumbersUser,commonThis item defines up to 100 telephone numbers as follows:•Each made up of up to 18 numeric characters (includingoptional spaces and/or trailing network ID preceded by aslash)•Each number having an associated priority value(i.e., 1 thru 4), protection (i.e., protected or unprotected),and a mnemonic of up to 14 characters•All are located in four user-definable categories of no morethan 25 telephone numbers each.If configuration pin TP13A is set to the zero state, every entrywith a priority 4 is modified to a priority 3 following an ORTupload or following a POST/PAST where priority 4 numbersexisted prior to TP13A being set to the zero state. In a dualsystem, this modification takes place only if strap TP13A is inthe zero state on both SDU systems. This item includesmanually entered telephones from the SCDU CATEGORYNUMBERS pages.vi Deletedvii ResourcesReserved forHeadsetUser,commonWhen enabled, this item reserves the following resources forcockpit headset use at all times: one codec, one modem, andsufficient HPA power to support an extra C--channel in allprevailing circumstances. These resources are capable ofbeing reserved for either of the cockpit audio channels. In adual system, channel refers to logical channel.viii ResponseCapability toLog-OnInterrogationN/A This item is not considered part of the MCS ORT, since theAES always supports log-on interrogation. There is alwaysone SDU modem dedicated to P--channel reception andcapable of R--channel and T--channel transmission.ix Use and Value ofFlightIdentificationN/A This item is not considered part of the MCS ORT since thevalue is dynamic and is obtained from the CFDS/CMC/OMSor SCDU (along with item xxxiv).xGround-to-AirCircuit-ModeDataUser,commonThis item defines the allowing/disallowing of analoginterconnect circuit-mode data on ground-to-air calls. It letsthe AES identify itself to the GES as being data capable andthe owner/operator anticipates receiving ground-to-air callsthat need circuit-mode data service, thereby directing theGES to assign data capable channels to all ground-to-aircalls.xi Deletedxii DeletedRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--3Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristicxiii Ground-to-AirCallsUser,commonThis item defines the allowing/disallowing and routing ofground-to-air priority 4 calls. If calls are allowed and if two ormore of the AES voice user interfaces (i.e., digital phones,analog handset, or headset) are fitted, this item specifieswhich destination (digital phone, analog handset, or headset)incoming priority 4 calls are routed. However, routing to theheadset is only possible if configuration pin TP13A is set tothe one state. If TP13A is set to the zero state, the ORTsetting is modified to Disallowed following a factory settingrestart, an ORT upload with headset selected, or aPOST/PAST if headset was selected prior to TP13A being setto the zero state. In a dual system, ground-to-air priority 4calls can be routed to an interface that is installed on at leastone of the SDU systems. Routing to HEADSET is onlypossible if at least one SDU system has a codec wired toAMS with TP13A strap in the one state (on this same SDUsystem).xiv Call Camp-OnDurationUser,commonThis item defines the camp-on duration be either indefinite, ora specified time-out period in the range of 1 to 15 minutes, ora time--out period of zero minutes (immediate time--out).xv Camp-OnTime-out ActionUser,commonThis item defines whether the camp-on time-out action is to(a) preempt (if a candidate call exists) or to cancel camp-on(if no candidate call exists), or (b) to cancel camp-on.xvi Stored APHONE(WH--10)TelephoneNumbersUser,duplicatedThis item defines up to 10 stored telephone numbers (9numbers plus last number redial), with each telephonenumber made up of up to 18 digits, for each of the two analog(APHONE) WH--10 channels. All such telephone numbers arepriority 4 and the priority is not modifiable. These two sets ofstored telephone numbers can be separate (distinct) orshared as specified in ORT item xxvi.xvii Deletedxviii Noise InsertionLevelSecured,commonThis item defines whether to enable or disable noise insertionon ground-to-air circuit-mode telephone calls. When noiseinsertion is enabled, this item also defines the level, asselected. Noise insertion minimizes annoying noisemodulation when the GES drops the carrier in the forward(to--aircraft) direction during speech pauses.xix Ground-to-AirPreemptionUser,commonThis item defines whether or not incoming calls of priority 2and/or 3 automatically preempt (as necessary) a candidatecall as specified in SYSTEM DESCRIPTION. Priority 1ground-to-air calls unconditionally preempt other calls of lowerpriority as necessary.xx Preferred CockpitCall RoutingUser,commonThis item defines the routing of ground-initiated cockpit voicecalls to a particular channel when two channels are available.This item does not affect which channel should be preemptedif both channels are not available. In a dual system, channelrefers to logical channel.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--4Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristicxxi PreferredAPHONE CallRoutingUser,duplicatedWhen allowed by item xiii, this item defines the routing ofground-to-air priority 4 calls, when allowed in accordance withitem xiii, to a particular channel when two APHONE channelsare available. In a dual system, this item specifies thepreferred physical channel on each SDU system, or Nonewhen there is no channel wired to APHONE on that system.xxii HGATxGainThresholdSecured,commonThis item specifies the threshold on the reported HGA Tx gainfor stimulating log-on renewal at Class 1 or automatichandover.xxiii Analog telephone(APHONE)SystemManagementCommandsSecured,duplicatedThis item defines the allowing/disallowing of systemmanagement commands from the analog phone (APHONE)interface (WH--10 or APBX).xxiv Analog telephone(APHONE)Outgoing CallBarring LevelUser,duplicatedThis item defines one of three levels for analog phone callbarring. Level 0 allows all outgoing calls and the Store PhoneNumber Memory command specified in SYSTEMDESCRIPTION, but disallows six-digit numbers between42XXXX and 47XXXX if accompanied by credit card data.Level 1 allows only stored phone numbers, directly dialedshort-code phone numbers, and long dialed numbers from theAPBX accompanied with credit card data to initiate outgoingcalls. Level 1 disallows manually dialed full-length phonenumbers not accompanied with credit card data, six-digitnumbers between 42XXXX and 47XXXX if accompanied bycredit card data, and the Store Phone Number Memorycommand. Level 2 disallows all outgoing calls, both manualand stored numbers, and the Store Phone Number Memorycommand.NOTE: The six-digit numbers between 42XXXX and47XXXX have been designated air traffic control(ATC) destinations. These numbers may be dialedat any priority and are assigned a network ID of 1.In order to prevent unauthorized use of thesenumbers once they become publicly available, theAES filters these numbers appropriately. Thefiltering specified prohibits these numbers frombeing dialed with credit card data present based onthe assumption anyone making a call to one ofthese numbers using a credit card is not anauthorized user (i.e., a passenger).xxv Call BarringSecurity CodeUser,duplicatedThis item defines a four-digit password that, if enteredthrough the analog phone (APHONE), allows call barringcommands (SYSTEM DESCRIPTION) to be accepted.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--5Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristicxxvi Shared AnalogTelephone(WH--10)(APHONE)Number StorageUser,duplicatedThis item defines whether the 10 stored numbers (9 numbersplus the last number redial) maintained for each of the analogphone (APHONE) channels are separate or shared (i.e.,whether a phone number stored on a channel is accessibleby the dial stored phone number command on the otherchannel).xxvii Deletedxxviii Default HPABackoff LimitsSecured,duplicatedThis item defines the maximum backoff values for the linearand class C HPAs. The working (volatile) values areautomatically updated by non zero values (i.e., other than16 dB) received in the HPA backoff range fields of valid HPAstatus words. The nonvolatile entries are not modified withthe received values.xxix HPA MinimumReportableActual PowerOutputSecured,duplicatedThis item defines the minimum values of actual power outputcapable of being reported through the HPA status words bythe linear and class C HPAs. When this value or a lower valueis reported in the HPA status word, calibration is inhibited.xxx Default AssumedGlobal BeamInitial C--ChannelEIRPSecured,commonThis item defines the default assumed global beam initialC--channel EIRP. This value is used to assess the poweravailability for a C--channel call in the absence of any existingC--channels.xxxi SCDU TelephoneNumberPreselectSecured,commonThis item defines whether selection of a phone number onone of the CATEGORY NUMBERS pages preselects thephone number or initiates a call using the phone number. Ifthis item is enabled, the selection of a phone number on oneof the CATEGORY NUMBERS pages or manual entry of aphone number on the DIRECTORY page retrieves theselected number to the SATCOM MAIN MENU page(TESTING/FAULT ISOLATION), where the number can thenbe dialed by selecting the MAKE CALL prompt or by any ofthe call initiation methods triggered by activation of an inputdiscrete.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--6Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristicxxxii ACP CallInitiationSecured,commonThis item enables/disables ACP call initiation. This item canonly be enabled when item xxxi is enabled. If enabled, one ofthe following two pairs of SDU discretes are capable of beingused for call initiation (when the associated cockpit voice calllight outputs are open), based on the state of program pinTP13K:•Cockpit voice mic on inputs — if the latched ACPhookswitch signaling method is strapped.•Place/End call discrete inputs — if the switched PTThookswitch signaling method is strapped.In either case, this item specifies whether the number dialedshould come from the ATC phone number register rather thanthe SCDU MAIN menu. If the MAIN menu is selected, thephone number displayed on the SATCOM MAIN MENU (3Llabel line for channel 1, or 5L label line for channel 2) is usedfor call initiation. If the ATC menu is selected, the phonenumber displayed on the ATC menu is used for call initiationon either cockpit channel. In a dual system, this item isenabled if the straps of both SDU systems are identical.xxxiii User (orComposite)Partition ORTDescriptionUser,commonThis item defines the 24-character field to describe the ORT.The ORT description is a 24-character field that annotates aparticular set of options, in order to distinguish one set fromanother (e.g., NORTH PACIFIC ROUTE, SOUTH ATLANTICROUTE, 747--400 ASIAN ROUTE, 777 ASIAN ROUTE).Alternatively, this item could contain a software identification(e.g., a software part number for the ORT as a releasedentity). If the ORT version is for a composite file, thedescription field is for the entire ORT and item liii is not used.See item liii also.xxxiv Airline Code User,commonThis item defines an airline code made up of up to four ISO--5characters to be used with a four-digit BCD flight numberreceived from a McDonnell Douglas CFDIU (SYSTEMDESCRIPTION) in constructing a flight identifier for log-on.This is only used if the CFDS/CMC/OMS does not supply theairline code.xxxv HeadsetOutgoing CallBarring LevelUser,commonThis item defines one of two levels for headset call barring.Level 0 allows all outgoing calls. Level 1 allows only storedphone numbers, manually dialed short-code numbers, andmanually dialed numbers with a network ID other than 1. ForLevel 1 call barring, all cockpit stored numbers are treated asprotected (i.e., they cannot be modified from the SCDU).xxxvi Headset TransitCallUser,commonThis item either enables or disables transit calls from theheadset for line select key 4L.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--7Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristicxxxvii User ORTPartition ModifiedFlagUser,commonThis item indicates whether any item in the nonvolatile copyof the user partition of the ORT partition has been modifiedsince the ORT was created in a configured state by thePC-based off-line ORT editing tool. When any user-partitionORT item is modified in nonvolatile memory by the SDUsoftware, either directly or indirectly, this flag is set tomodified. This value is never set to unmodified by the SDUsoftware. Its value is displayed on the SCDU, on the CFDS,on the front panel display of the SDU, and on the CMT.xxxviii Failure MaskingDataSecured,commonThis item is made up of a list of up to 50 failures (Level Icode, SRU code, and failure code) whose operation ismasked or suppressed. A switch is stored with each specifiedfailure to indicate whether that failure should never be raised(i.e., the failure annunciation and reversion should besuppressed completely), or whether the failure should beannunciated normally (i.e., recorded and reported asspecified in TESTING/FAULT ISOLATION) when declared,but not indict the appropriate functional resource specified forthe failure (i.e., not take any other action in response to thefailure, such as reconfiguring redundant resources). Unusedentries in this table are represented by the Level I code, SRUcode, and failure code all set to zero.xxxix ElevationHandoverThresholdSecured,commonThis item, ranging in integer degrees between 0°and 90°,isused in combination with calculated elevation of the highestsatellite to determine at what elevation to initiate a handoverfrom the current satellite. This item is also used to determinewhen a satellite is not high enough in elevation to beconsidered in view for acquisition purposes by the automaticlog-on process.xl High Rate DataTransmit SupportUser,commonThis item made up of two flags that specify (by being set toenabled or disabled) whether the SDU indicates support for10,500 bps R-- and T--channels in its log-on request of class2, 3, and 4 (i.e., when using a high gain antenna), for theglobal beam and spot beam log-on requests, respectively.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--275 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page C--8Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristicxli Automatic TransitCall GES Table Secured,common This item indicates the transit GES ID to be specified in anair-to-ground call setup request (SYSTEM DESCRIPTION) ifno transit GES ID has been explicitly specified through theinitiating user interface (APHONE, Headset, DPHONE). If theGES ID in the table is 377 octal (indicating null), then thelog-on GES is used in the call setup request. For eachsatellite ID of 0, 1, 2, and 3, the table stores a GES ID to beused with the following types of calls:•Any PSTN long number call (i.e., with network ID 1, withbetween 7 and 18 digits, beginning with 00) with countrycode beginning with 1 (i.e., North America)•Any PSTN long number call with a country code beginningwith 2 (i.e., Africa)•Any PSTN long number call with a country code beginningwith 3 (i.e., South and West Europe)•Any PSTN long number call with a country code beginningwitha4(i.e.,NorthandEastEurope)•Any PSTN long number call with a country code beginningwitha5(i.e.,SouthAmerica)•Any PSTN long number call with a country code beginningwitha6(i.e.,SouthEastAsiaandAustralia)•Any PSTN long number call with a country code beginningwitha7(i.e.,SovietUnion)•Any PSTN long number call with a country code beginningwith an 8 (i.e., Far East)•Any PSTN long number call with a country code beginningwitha9(i.e.,India and Middle East)•Any PSTN short number call (i.e., network ID of 1, withbetween 2 and 6 digits not beginning with 00)The geographical region associated with each zone isapproximate; refer to Table C--1 for details of individualcountry codes.xlii Air-to-GroundChime Secured,common This item defines one of three chime options. These optionsonly affect air-to-ground chime activation for call annunciationand the setting of SDU-to-ACARS MU/CMU status word bits.The first option is to always chime and always set theappropriate bits. The second option is to chime and set theappropriate bits only if the call was camped-on. The thirdoption is to never chime and never set the bits.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--9Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristicxliii SCDU CallPromptsSecured,commonThis item defines one of three levels of SCDU call promptdisplay. Level 0 causes all SCDU call prompts to bedisplayed. Level 1 causes the ANSWER CALL, REJECT, andEND CALL prompts to not be displayed. Level 2 causes theMAKE CALL prompt and the Level 1 prompts to not bedisplayed. Level 2 is selectable only if ORT item xxxii isenabled.xliv EIRP OverdraftChecking PrioritySecured,commonThis item defines the call priority level where at least one callmust be in progress when considering if an EIRP overdraft isallowed.xlv AnalogTelephone(APHONE)Called TerminalID AssignmentUser,duplicatedThis item provides for the assignment of a three-digit calledterminal identification (CTid) code to each APHONE channelrouting ground-to-air priority 4 calls to the APHONE interface,based on the called terminal field in the call announcementsignal unit. The CTid assigned can be any decimal valuebetween --1 and 999. A CTid value of --1 represents nospecific routing.This item also specifies a CTid assignment type of exclusiveor nonexclusive for each channel. The assignment typedefaults to nonexclusive if no CTid is assigned. Anassignment type of exclusive with no CTid assigned isundefined and is not selectable. With a CTid assigned, anassignment type of exclusive inhibits all incoming calls frombeing routed to the associated channel unless the callannouncement contains a CTid that matches the assignedvalue. An assignment type of nonexclusive allows allincoming calls to be routed to the associated channel unlessthe call announcement contains a CTid that matches theassigned value of the other channel. Regardless of theassignment type, an incoming call with a matching CTid isrejected if the associated channel is unavailable.Modifications of this item through the APHONE or CMT arechecked for duplication with the other APHONE channel inthe SDU and, in a dual system, with the APHONE channels inthe other SDU.The primary use of this ORT item is to let incoming facsimilecalls be routed to the channel connected to the facsimilemachine.xlvi Cockpit AudioLevel SettingsSecured,commonThis item defines the level settings for the cockpitmicrophone, sidetone, and receive audio.xlvii HGA RetryPeriod (groundand air)Secured,commonThis item defines the time interval for ground and airbornecases after which SATCOM (when logged on through theLGA) is to make attempts to logon through the HGA. A valueof 0 disables the periodic retry for each case. The timeinterval is in integer minutes ranging from 0 to 255.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--10Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristicxlviii Cockpit ChannelInterface Type forDualSecured,commonThis item defines the functional mapping of the one to fourpotentially available physical SDU cockpit voice channels in adual system to the one or two logical cockpit voice channels(as viewed from the perspective of the ACP and SCDU). It isused in combination with ORT item vi and systemconfiguration pins TP13F and TP13J to determine thenumber of logical channels and which physical channel(s)is/are potentially available for each logical channel.This item is capable of taking on the states of fixed andshared. Fixed interfacing is interfacing each ACP/SCDU(logical) channel to one physical channel on one SDU only.Shared interfacing is interfacing each ACP/SCDU logicalchannel to one physical channel on each of the two SDUs.The fixed or shared interfacing declaration refers to thefunctional channel mapping, and not necessarily to thephysical interwiring, e.g., the interwiring can be independentbut the interface can be effectively shared by virtue ofsplitting/combining/paralleling within the AMS (as in theBoeing 777), or the interwiring can be literally paralleled,forcing the interface type to shared.In the case of two logical channels, it is assumed the singlevalue for this item applies to both channels (i.e., both fixed orboth shared). For the case of shared (for one or two logicalchannels), it is assumed each logical channel shares thesame numbered physical channel on each SDU.The state of this item is checked for compatibility with thestate of pins TP13F and TP13J of both SDUs and the state ofORTitemviofbothSDUs.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--11Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristicil MasteryHandoverAlgorithmWeightingUser,commonThis item stores the relative weighting factors for each of thesix functional capability items that form the criteria fordetermining which system should automatically become themaster in a dual system. Each of the six weighting factors is anon-negative integer ranging from 0 to 99. Higher factorsindicate more important criteria; however, only the relativevalues of the factors is significant. Zero is used to indicate acapability factor not installed, not used, or is a don’t care. Thefunctional capability items are as follows:•CoV -- Cockpit voice (for any number of channels).•CaV -- Cabin circuit-mode voice/fax/data(any number of channels, any cabin interface).•CoL -- Cockpit packet-mode data(through [C]MU) at low-rate only.•CoH -- Cockpit packet-mode data(through [C]MU) at (potentially) high-rate.•CaL -- Cabin packet-mode data(through CPDF or CTU) at low rate only.•CaH -- Cabin packet-mode data (through CPDF or CTU) at(potentially) high-rate.CoL and CoH are mutually exclusive, as are CaL andCaH — i.e., regardless of the weighting factors assigned, nomore than one of the cockpit data (or cabin data) capabilitiescanbetrueatatime.The primary practical use of this ORT item is for determiningwhich SDU in a dual system should be the master when thechoice is down to one system which only has voice capabilityvs one which only has data capability, or one with only cockpitservices capabilities vs one with only cabin servicescapabilities.lDisable/ReenableOther SATCOMSCDU PromptsSecured,commonThis item determines if the disable other SATCOM andre--enable other SATCOM toggling SCDU prompts arepresented or suppressed. The SCDU prompts are usuallysuppressed if the optional external manual switch (thatcontrols the dual system select and disable discretes) issupplied so there is only one means of performing anyfunction at a time and the possibility of inadvertently disablingboth systems is avoided.li SCDU SATCOMSubsystemPromptsSecured,duplicatedThis item defines up to six ISO--5 characters used for theSCDU main menu SATCOM subsystem selection LSKprompts. The owner/operator is able to select any ISO--5characters and any length up to six characters. Examplecharacter strings would be SAT L and SAT R, or <SDU--1 and<SDU--2.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--12Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristiclii SCDU ChannelLabel SuffixesSecured,commonThis item defines the one-character suffix for each cockpitvoice channel label on the SCDU displays. The choices are 1and 2, or L and R for channels 1 and 2, respectively. Thesesuffixes are used for the channel identifiers on the SATCOMMain Menu, Directory, and Category Numbers pages.liii Secured ORTDescriptionSecured,commonThis items defines a 24-character (ISO--5) field to describethe secured ORT partition. The description field is used towrite a particular set of secured ORT items to distinguish onefrom another (e.g., B777 DUAL 950901, B747--400 DUAL951001, B747--300 STC 951225). Alternatively, this item cancontain a software identification (e.g., a software part numberfor the ORT as a released entity). If the ORT version is for acomposite file, description field xxxiii is for the entire ORT, soitem liii is not used in that case.liv Composite ORTFile UploadCapabilitySecured,commonThis item defines whether or not the uploading of a compositeORT file version is to be allowed. This option is required toprevent the unintentional overwriting of the secured partitionwith a composite ORT file that contains both user andsecured ORT items.lv Secured ORTModified FlagSecured,commonThis item indicates whether any item in the nonvolatile copyof the secured ORT partition has been modified since theORT was created in a configured state by the PC-basedoff-line ORT editing tool. When any secured ORT item ismodified in nonvolatile memory by the SDU software, directlyor indirectly, this flag is set to Modified. This value is never setto Unmodified by SDU software. Its value is displayed on theSCDU, the CFDS, the front panel display, and the CMT.lvi Access toZero-PreferenceGESsSecured,commonThis item defines whether automatic log-on is allowed ordisallowed to GESs with preference values set to zero byORT item iii. This is intended to be set to allowed in Essentialcertified systems so at least two GESs are selectable forautomatic log-on on each satellite. It can be set to disallowedin nonessential certified systems to intentionally precludeautomatic log-on to particular GESs, e.g., those with the AESowner/operator have no contractual arrangements. See ORTitem iii for additional information.lvii L--BandReference OffsetCalibrationThresholdsSecured,commonThis item defines (in Hz) the thresholds of the L--Bandreference offset calibration for both the with IRS and withoutIRS cases. These thresholds are used to determine whetherto adjust the L--Band reference offsets. These values aredisplayed on the CMT.lviii Suppress AESPositionReportingUser,commonThis item enables or disables the AES position reporting sentacross each active C--channel.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--13Table C--1. ORT Characteristics (cont)ORT Item DescriptionAttributesCharacteristiclix APHONE AudioLevel SettingSecured,commonThis item defines the output level setting for the receiveaudio.lx AERO H OnlyOperationSecured,commonThis item defines the service mode when an HGA is installed.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page C--14Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--1APPENDIX DFAULT CODESLEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTIONFailure OverviewSDUUNKNOWN SDU SRU01 0 02 CM HMPM HPA CMD WORD (143) UPDATE RATE FAIL01 0 03 CM HMPM HPA CMD WORD (143) DATA FAIL01 0 07 CM SMPM HSU1--SDU W’BURG DATA TX FAIL01 0 08 CM SMPM HSU1--SDU W’BURG SOLO WORD ACK FAIL01 0 0B CM SMPM HSU2--SDU W’BURG DATA TX FAIL01 0 0C CM SMPM HSU2--SDU W’BURG SOLO WORD ACK FAIL01 0 10 CM SMPM HGA HPA COMMAND WORD (NCD)01 0 12 CM SMPM LGA HPA COMMAND WORD (NCD)01 0 96 PP SMPM INCOMPLETE ID PROM RESPONSESSMPM: SDU MAIN PROCESSOR MODULE01 1 81 PP SMPM SDU H/W--S/W COMPATIBILITY FAIL01 1 82 PP SMPM BATTERY VOLTAGE LOW01 1 83 PP SMPM WATCHDOG TIMEOUT FAIL01 1 84 PP SMPM MICRO BOOT ROM FAIL01 1 85/05 PP/CM SMPM EEPROM FAIL01 1 86/06 PP/CM SMPM FLASH FAIL01 1 87/07 PP/CM SMPM SRAM FAIL]01 1 88/08 PP/CM SMPM REAL TIME CLOCK FAIL01 1 89 PP SMPM QUART FAIL01 1 0A CM SMPM SOFTWARE ERROR (SYSFAIL)01 1 0B CM SMPM FLASH--PSRAM MISCOMPARE01 1 0C CM SMPM FLASH--PSRAM MISCOMPARE EXTENSION01 1 0D CM SMPM FLASH--PSRAM MISCOMPARE EXTENSIONCODA: SDU VOICE CODEC MODULE A01 2 81/01 PP/CM CODA <CODEC--A> PROGRAM MEMORY CRC FAIL01 2 87/07 PP/CM CODA <CODEC--A> TIMING GENERATOR FAIL01 2 88 PP CODA <CODEC--A> DUAL PORT RAM FAIL CODEC SIDE01 2 8A/0A PP/CM CODA <CODEC--A> PROGRAM MEMORY W/R FAIL01 2 8B PP CODA <CODEC--A> DSP INTERNAL MEMORY W/R FAIL01 2 8C/0C PP/CM CODA <CODEC--A> DSP COMPREHENSIVE FAIL01 2 0D CM SMPM <CODEC--A> HEALTH COUNT UPDATE01 2 8E PP SMPM <CODEC--A> DUAL PORT RAM FAIL SMPM SIDE01 2 90 PP SMPM <CODEC--A> BUS ERROR01 2 91 PP SMPM <CODEC--A> SELF TEST MISOPERATION01 2 12 CM SMPM <CODEC--A> COMMUNICATION PROBLEM01 2 94 PP SMPM <CODEC--A> ST BUS AUDIO LOOPBACK FAIL01 2 95 PP SMPM <CODEC--A> SW DOWNLOAD FAILCODB: SDU VOICE CODEC MODULE B01 3 Same entries as for CODA above except substitute CODB for CODA, SRU code 3 for code 2, [CODEC_B] for [CODEC_A] and<CODEC--B> for <CODEC--A>.Fault codes for codecs C--F have Level 2 (SRU) codes E--H. They are listed in the appropriate section of this table for those SRU codes.SIOM: SDU INPUT/OUTPUT MODULE (EXCLUSIVE TO SIOM)01 4 81 PP SMPM A429 XMTR LOOP--BACK TO OTHER SDU FAIL01 4 82 PP SMPM A429 XMTR LOOP--BACK TO CFDS FAIL01 4 83 PP SMPM A429 XMTR LOOP--BACK TO ADL FAIL01 4 84 PP SMPM A429 XMTR LOOP--BACK TO PDL FAIL01 4 85 PP SMPM A429 XMTR LOOP--BACK TO (C)MUs FAIL01 4 86 PP SMPM A429 XMTR LOOP--BACK TO SCDUs FAIL01 4 87 PP SMPM A429 XMTR LOOP--BACK TO MULTI--CNTRL FAIL01 4 89 PP SMPM A429 XMTR LOOP--BACK TO RMP/CAP FAIL01 4 8A PP SMPM A429 XMTR LOOP--BACK TO SNU/CPDF FAIL01 4 8B PP SMPM A429 XMTR LOOP--BACK TO HSU1 FAIL01 4 8C PP SMPM A429 XMTR LOOP--BACK TO HSU2 FAIL01 4 8D PP SMPM A429 XMTR LOOP--BACK SPARE01 4 8E PP SMPM A429 XMTR LOOP--BACK SPARE01 4 8F PP SMPM A429 XMTR LOOP--BACK SPARE01 4 90 PP SMPM A429 XMTR LOOP--BACK SPARE01 4 AB PP SMPM SIOM BUS ERROR01 4 2C CM SMPM A429 TX TO OTHER SDU BUFFER FULL01 4 2D CM SMPM A429 TX TO CFDS BUFFER FULL01 4 2E CM SMPM A429 TX TO ADL BUFFER FULL01 4 2F CM SMPM A429 TX TO PDL BUFFER FULLRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--2LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTION01 4 30 CM SMPM A429 TX TO (C)MUs BUFFER FULL01 4 31 CM SMPM A429 TX TO SCDUs BUFFER FULL01 4 32 CM SMPM A429 TX TO MULTI--CTRL BUFFER FULL01 4 34 CM SMPM A429 TX TO RMP/CAP BUFFER FULL01 4 35 CM SMPM A429 TX TO SNU/CPDF BUFFER FULL01 4 36 CM SMPM A429 TX TO HSU1 BUFFER FULL01 4 37 CM SMPM A429 TX TO HSU2 BUFFER FULL01 4 38 CM SMPM A429 TX BUFFER FULL SPARE01 4 39 CM SMPM A429 TX BUFFER FULL SPARE01 4 3A CM SMPM A429 TX BUFFER FULL SPARE01 4 3B CM SMPM A429 TX BUFFER FULL SPARE01 4 BC PP SMPM SIOM INTERRUPT FAIL01 4 3D CM SMPM IRS ASIC MATCHING PROBLEMSMDM1: SDU MODEM MODULE #101 5 81 PP SMDM1 <MODEM--1> PROCESSOR FAIL01 5 84/04 PP/CM SMDM1 <MODEM--1> PROGRAM CRC FAIL01 5 0A CM SMDM1 <MODEM--1>MODEM TO RFM INTERFACE FAIL01 5 8B PP SMDM1 <MODEM--1> TIMER/INTERRUPT FAIL01 5 8E PP SMDM1 <MODEM--1> EXTERNAL MEMORY FAIL01 5 91 PP SMDM1 <MODEM--1> MODEM DPR FAIL01 5 95 PP SMPM <MODEM--1> SMPM SIDE DPR FAIL01 5 16 CM SMPM <MODEM--1> SW DOWNLOAD FAIL01 5 17 CM SMPM <MODEM--1> HEALTH COUNT UPDATE FAIL01 5 99 PP SMPM <MODEM--1> BUS ERROR01 5 9A PP SMPM <MODEM--1> SELF TEST MISOPERATION01 5 1B CM SMDM1 <MODEM--1> SOFTWARE FAIL01 5 1C CM SMPM <MODEM--1> COMMUNICATIONS PROBLEM01 5 9E PP SMPM <MODEM--1> RFM SSI LOOPBACK FAILSMDM2: SDU MODEM MODULE #201 6 Same entries as for SMDM1 above except substitute SMDM2 for SMDM1, SRU code 6 for code 5, [MODEM_2] for [MODEM_1] and<MODEM--2> for <MODEM--1>.SMDM3: SDU MODEM MODULE #301 7 Same entries as for SMDM1 above except substitute SMDM3 for SMDM1, SRU code 7 for code 5, [MODEM_3] for [MODEM_1] and<MODEM--3> for <MODEM--1>.Fault codes for modems 4--7 have Level 2 (SRU) codes J, L, M and N. They are listed in this table in the appropriate section for those SRUcodes.SRFM: SDU RADIO FREQUENCY MODULE01 8 8E/0E PP/CM SMPM RF SYNTH CHAN1 LOCK DETECT FAIL01 8 90/10 PP/CM SMPM RF SYNTH CHAN2 LOCK DETECT FAIL01 8 92/12 PP/CM SMPM RF SYNTH CHAN3 LOCK DETECT FAIL01 8 96/16 PP/CM SMPM RF SYNTH CHAN4 LOCK DETECT FAIL01 8 97/17 PP/CM SMPM RF SYNTH CHAN5 LOCK DETECT FAIL01 8 98/18 PP/CM SMPM RF SYNTH CHAN6 LOCK DETECT FAIL01 8 99/19 PP/CM SMPM RF SYNTH CHAN7 LOCK DETECT FAIL01 8 9A/1A PP/CM SMPM RF SYNTH CHAN8 LOCK DETECT FAIL01 8 9B/1B PP/CM SMPM RF SYNTH TX BLOCK PLO LOCK DETECT FAIL01 8 9C/1C PP/CM SMPM RF SYNTH RX BLOCK PLO LOCK DETECT FAIL01 8 9D/1D PP/CM SMPM RF SYNTH RX CHAN PLO LOCK DETECT FAIL01 8 9E/1E PP/CM SMPM RF SYNTH TX DOPPLER PLO LOCK DETECT FAIL01 8 A0 PP SMPM RFM CHAN 1 L--BAND LOOP--BACK (TX) FAIL01 8 A1 PP SMPM RFM CHAN 1 L--BAND LOOP--BACK (RX) FAIL01 8 A2 PP SMPM RFM CHAN 2 L--BAND LOOP--BACK (TX) FAIL01 8 A3 PP SMPM RFM CHAN 2 L--BAND LOOP--BACK (RX) FAIL01 8 A4 PP SMPM RFM CHAN 3 L--BAND LOOP--BACK (TX) FAIL01 8 A5 PP SMPM RFM CHAN 3 L--BAND LOOP--BACK (RX) FAIL01 8 A6 PP SMPM RFM CHAN 4 L--BAND LOOP--BACK (TX) FAIL01 8 A7 PP SMPM RFM CHAN 4 L--BAND LOOP--BACK (RX) FAIL01 8 A8 PP SMPM RFM CHAN 5 L--BAND LOOP--BACK (TX) FAIL01 8 A9 PP SMPM RFM CHAN 5 L--BAND LOOP--BACK (RX) FAIL01 8 AA PP SMPM RFM CHAN 6 L--BAND LOOP--BACK (TX) FAIL01 8 AB PP SMPM RFM CHAN 6 L--BAND LOOP--BACK (RX) FAIL01 8 AC PP SMPM RFM CHAN 7 L--BAND LOOP--BACK (TX) FAIL01 8 AD PP SMPM RFM CHAN 7 L--BAND LOOP--BACK (RX) FAIL01 8 AE PP SMPM RFM CHAN 8 L--BAND LOOP--BACK (TX) FAIL01 8 AF PP SMPM RFM CHAN 8 L--BAND LOOP--BACK (RX) FAIL01 8 30 CM SMPM RFM CHAN 1 TX CALIBRATION ERROR01 8 31 CM SMPM RFM CHAN 2 TX CALIBRATION ERROR01 8 32 CM SMPM RFM CHAN 3 TX CALIBRATION ERRORRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--3LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTION01 8 33 CM SMPM RFM CHAN 4 TX CALIBRATION ERROR01 8 34 CM SMPM RFM CHAN 5 TX CALIBRATION ERROR01 8 35 CM SMPM RFM CHAN 6 TX CALIBRATION ERROR01 8 36 CM SMPM RFM CHAN 7 TX CALIBRATION ERROR01 8 37 CM SMPM RFM CHAN 8 TX CALIBRATION ERROR01 8 38 CM SMPM RFM CHAN 1 RX CALIBRATION ERROR01 8 39 CM SMPM RFM CHAN 2 RX CALIBRATION ERROR01 8 3A CM SMPM RFM CHAN 3 RX CALIBRATION ERROR01 8 3B CM SMPM RFM CHAN 4 RX CALIBRATION ERROR01 8 3C CM SMPM RFM CHAN 5 RX CALIBRATION ERROR01 8 3D CM SMPM RFM CHAN 6 RX CALIBRATION ERROR01 8 3E CM SMPM RFM CHAN 7 RX CALIBRATION ERROR01 8 3F CM SMPM RFM CHAN 8 RX CALIBRATION ERROR01 8 C0/40 PP/CM SMPM RFM CHAN 1 AGC TELLBACK FAIL01 8 C1/41 PP/CM SMPM RFM CHAN 2 AGC TELLBACK FAIL01 8 C2/42 PP/CM SMPM RFM CHAN 3 AGC TELLBACK FAIL01 8 C3/43 PP/CM SMPM RFM CHAN 4 AGC TELLBACK FAIL01 8 C4/44 PP/CM SMPM RFM CHAN 5 AGC TELLBACK FAIL01 8 C5/45 PP/CM SMPM RFM CHAN 6 AGC TELLBACK FAIL01 8 C6/46 PP/CM SMPM RFM CHAN 7 AGC TELLBACK FAIL01 8 C7/47 PP/CM SMPM RFM CHAN 8 AGC TELLBACK FAIL01 8 C8/48 PP/CM SMPM RFM BLOCK AGC TELLBACK FAIL01 8 C9 PP SMPM I/Q CALIBRATION FAIL01 8 D0 PP SMPM RFM CHAN 1 AGC CALIBRATION ERROR01 8 D1 PP SMPM RFM CHAN 2 AGC CALIBRATION ERROR01 8 D2 PP SMPM RFM CHAN 3 AGC CALIBRATION ERROR01 8 D3 PP SMPM RFM CHAN 4 AGC CALIBRATION ERROR01 8 D4 PP SMPM RFM CHAN 5 AGC CALIBRATION ERROR01 8 D5 PP SMPM RFM CHAN 6 AGC CALIBRATION ERROR01 8 D6 PP SMPM RFM CHAN 7 AGC CALIBRATION ERROR01 8 D7 PP SMPM RFM CHAN 8 AGC CALIBRATION ERROR01 8 D8 PP SMPM RFM BLOCK AGC CALIBRATION ERROROCXO: SDU OVEN CONTROLLED CRYSTAL OSCILLATOR01 A 01 CM SMPM OVEN READY FAILSMB: SDU MOTHER BOARD01 B NONESPSU: SDU AC OR DC POWER SUPPLY UNIT01 C 01 CM SMPM PSU TEMP LIMITS FAIL01 C 03 CM SMPM PSU SECONDARY VOLTAGE FAILSFPDM: SDU FRONT PANEL DISPLAY MODULE01 D 01 CM SMPM TEST (PAST) SWITCH STUCK01 D 02 CM SMPM MANUAL SCROLL SWITCH STUCKCODC: SDU VOICE CODEC MODULE C01 E Same entries as for CODA (01 2 xx) above except substitute CODC for CODA, SRU code E for code 2, [CODEC_C] for [CODEC_A]and <CODEC--C> for <CODEC--A>.CODD: SDU VOICE CODEC MODULE D01 F Same entries as for CODA (01 2 xx) above except substitute CODD for CODA, SRU code F for code 2, [CODEC_D] for [CODEC_A]and <CODEC--D> for <CODEC--A>.CODE: SDU VOICE CODEC MODULE E01 G Same entries as for CODA (01 2 xx) above except substitute CODE for CODA, SRU code G for code 2, [CODEC_E] for [CODEC_A]and <CODEC--E> for <CODEC--A>.CODF: SDU VOICE CODEC MODULE F01 H Same entries as for CODA (01 2 xx) above except substitute CODF for CODA, SRU code H for code 2, [CODEC_F] for [CODEC_A]and <CODEC--F> for <CODEC--A>.01 I Not used.SMDM4: SDU MODEM MODULE #401 J Same entries as for SMDM1 (01 5 xx) above except substitute SMDM4 for SMDM1, SRU code J for code 5, [MODEM_4] for[MODEM_1] and <MODEM--4> for <MODEM--1>.01 K Not used.SMDM5: SDU MODEM MODULE #501 L Same entries as for SMDM1 (01 5 xx) above except substitute SMDM5 for SMDM1, SRU code L for code 5, [MODEM_5] for[MODEM_1] and <MODEM--5> for <MODEM--1>.SMDM6: SDU MODEM MODULE #601 M Same entries as for SMDM1 (01 5 xx) above except substitute SMDM6 for SMDM1, SRU code M for code 5, [MODEM_6] for[MODEM_1] and <MODEM--6> for <MODEM--1>.SMDM7: SDU MODEM MODULE #701 N Same entries as for SMDM1 (01 5 xx) above except substitute SMDM7 for SMDM1, SRU code N for code 5, [MODEM_7] for[MODEM_1] and <MODEM--7> for <MODEM--1>.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--4LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTIONVIM: VOICE INTERFACE MODULE01 P 81 PP SMPM CABIN INTERFACE 1 AUDIO LOOPBACK FAIL01 P 82 PP SMPM CABIN INTERFACE 2 AUDIO LOOPBACK FAIL01 P 83 PP SMPM COCKPIT INTERFACE 1 AUDIO LOOPBACK FAIL01 P 84 PP SMPM COCKPIT INTERFACE 2 AUDIO LOOPBACK FAIL01 P 85 PP SMPM CTU CEPT--E1 AUDIO LOOPBACK FAIL01 P 07 CM SMPM CABIN AUDIO DISCRETE OUTPUTS LOOPBACK FAIL01 P 08 CM SMPM COCKPIT AUDIO DISCRETE OUTPUTS LOOPBACK FAIL01 P 89 PP SMPM CTU CEPT--E1 HDLC LOOPBACK FAIL01 P 8A PP SMPM CABIN INTERFACE 1 BUS ERROR01 P 8B PP SMPM CABIN INTERFACE 2 BUS ERROR01 P 8C PP SMPM COCKPIT INTERFACE 1 BUS ERROR01 P 8D PP SMPM COCKPIT INTERFACE 2 BUS ERROR01 P 8E PP SMPM CTU CEPT--E1 BUS ERROR“OTHER” SATCOM SYSTEM02 0 01 CM SMPM PROTOCOL VERSION NUMBER INCOMPATIBLE02 0 02 CM SMPM SDU/SDU MESSAGE PROTOCOL ERRORHSUOnly applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent.UNKNOWN HSU SRU03 0 01 CM SMPM HSU SELF--DECLARED FAILURE03 0 02 CM SMPM HSU WILLIAMSBURG PROTOCOL ALO/ALR FAIL03 0 03 CM SMPM HSU WILLIAMSBURG PROTOCOL DATA XFER FAIL03 0 84 PP SMPM HSU SELF--TEST MISOPERATION03 0 05 CM HSCP HSU SERIAL PORT MIS--WIRING03 0 86/06 PP/CM HSCP HSU TOTC RESET03 0 87/07 PP/CM HSCP HSU POC RESET03 0 0C CM SMPM HSU CHANNEL 1 FAILURE03 0 0D CM SMPM HSU CHANNEL RELEASE ACKNOWLEDGE FAILURE03 0 8E/0E PP/CM SMPM HSU RF LOOPBACK INHIBIT FAILURE03 0 0F CM SMPM HSU CHANNEL 2 FAILURE03 0 10 CM SMPM HSU CHANNEL 3 FAILURE03 0 11 CM SMPM HSU CHANNEL 4 FAILUREHSCC1: HSU CHANNEL CARD 103 1 01 CM HSCP HSU CC1 MODEM FAULT03 1 02 CM HSCP HSU CC1 MODEM FAILURE03 1 03 CM HSCP HSU CC1 PERIPHERAL ERROR03 1 04 CM HSCP HSU CC1 PERIPHERAL FAILURE03 1 05 CM HSCP HSU CC1 CP SW INCOMPATIBILITY03 1 07 CM HSCP HSU CC1 RF FAULT03 1 08 CM HSCP HSU CC1 RF FAILURE03 1 09 CM HSCP HSU CC1 TAL ERROR03 1 0A CM HSCP HSU CC1 MODEM CALIBRATION MISSING03 1 0B CM HSCP HSU CC1 TEMPERATURE UNREADABLE03 1 0C CM HSCP HSU CC1 OVER TEMPERATURE03 1 0E CM HSCP HSU CC1 TURBO FAULT03 1 0F CM HSCP HSU CC1 TURBO FAILURE03 1 11 CM HSCP HSU CC1 VCODEC FAULT03 1 12 CM HSCP HSU CC1 VCODEC FAILURE03 1 93 PP HSCP HSU CC1 APPLICATION CODE ERRORHSCC2: HSU CHANNEL CARD 203 2 01 CM HSCP HSU CC2 MODEM FAULT03 2 02 CM HSCP HSU CC2 MODEM FAILURE03 2 03 CM HSCP HSU CC2 PERIPHERAL ERROR03 2 04 CM HSCP HSU CC2 PERIPHERAL FAILURE03 2 05 CM HSCP HSU CC2 CP SW INCOMPATIBILITY03 2 07 CM HSCP HSU CC2 RF FAULT03 2 08 CM HSCP HSU CC2 RF FAILURE03 2 09 CM HSCP HSU CC2 TAL ERROR03 2 0A CM HSCP HSU CC2 MODEM CALIBRATION MISSING03 2 0B CM HSCP HSU CC2 TEMPERATURE UNREADABLE03 2 0C CM HSCP HSU CC2 OVER TEMPERATURE03 2 0E CM HSCP HSU CC2 TURBO FAULT03 2 0F CM HSCP HSU CC2 TURBO FAILURE03 2 11 CM HSCP HSU CC2 VCODEC FAULT03 2 12 CM HSCP HSU CC2 VCODEC FAILURE03 2 93 PP HSCP HSU CC2 APPLICATION CODE ERRORRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--5LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTIONHSDIO: HSU DATA I/O CARD03 3 02 CM HSCP HSU UNRECOVERABLE SW / PROTOCOL ERROR03 3 03 CM HSCP HSU I/O CHANNEL CARD 1 UNSERVICEABLE03 3 04 CM HSCP HSU I/O CHANNEL CARD 2 UNSERVICEABLE03 3 85 PP HSCP HSU CONFIGURATION ERROR03 3 86 PP HSCP HSU I/O PERIPHERAL FAILURE03 3 07 CM HSCP HSU I/O BOTH CHANNEL CARDS UNSERVICEABLE03 3 08 CM HSCP HSU I/O RAM FAULT03 3 09 CM HSCP HSU I/O ROM FAULT03 3 0A CM HSCP HSU SW CONFIGURATION ERROR03 3 0B CM HSCP HSU PPPoE SESSION FAILUREHSCP: HSU CONTROL PROCESSOR03 4 87/07 PP/CM HSCP HSU CP CHANNEL CARD 1 UNRESPONSIVE03 4 88/08 PP/CM HSCP HSU CP CHANNEL CARD 2 UNRESPONSIVE03 4 89/09 PP/CM HSCP HSU CP BOTH CHANNEL CARDS UNRESPONSIVE03 4 8A/0A PP/CM HSCP HSU DATA I/O CARD UNRESPONSIVE03 4 0B CM HSCP HSU CP RAM FAULT03 4 0C CM HSCP HSU CP ROM FAULT03 4 0D CM HSCP HSU OVER TEMPERATURE03 4 0E CM HSCP HSU CHANNEL CARD 1 OVER TEMPERATURE03 4 0F CM HSCP HSU CHANNEL CARD 2 OVER TEMPERATURE03 4 10 CM HSCP HSU BOTH CHANNEL CARDS OVER TEMPERATURE03 4 91 PP HSCP HSU ADL BUS INTERFACE FAILURE03 4 92 PP HSCP HSU PDL BUS INTERFACE FAILURE03 4 93 PP HSCP HSU DATA I/O DUART FAILURE03 4 94 PP HSCP HSU CHANNEL CARD 1 DUART FAILURE03 4 95 PP HSCP HSU CHANNEL CARD 2 DUART FAILURE03 4 96 PP HSCP HSU BOTH CHANNEL CARDS DUART FAILURE03 4 97 PP HSCP HSU MAINTENANCE INTERFACE DUART FAILURE03 4 98 PP HSCP HSU DISCRETE OUTPUT FAILURE03 4 99 PP HSCP HSU BOARD CONFIGURATION/REVISION FAILUREHOCXO: HSU OVEN--CONTROLLED 10 MHZ OSCILLATOR03 5 01 CM HSCP HSU OCXO TIMEOUT03 5 02 CM HSCP HSU OCXO TEMPERATURE UNSTABLEHSPSU: HSU POWER SUPPLY UNIT03 6 01 CM HSCP HSU POWER SUPPLY FAIL03 6 02 CM HSCP HSU PSU OVER TEMPERATUREHSCDM: HSU CONFIGURATION DATA MODULE03 7 NONEHSFP: HSU FRONT PANEL03 8 81 PP HSCP HSU SELF--TEST BUTTON STUCKHSBP: HSU BACKPLANE03 9 NONEHGA/IGA HPAThis section lists failure codes inclusive of all HPA designs. Each HPA uses the SRU codes appropriate to its design.UNKNOWN HGA/IGA HPA SRU04 0 01 CM SMPM <HGA HPA> STATUS WORD (143) UPDATE RATE FAIL04 0 02 CM SMPM <HGA HPA> STATUS WORD (143) DATA FAIL04 0 03 CM SMPM <HGA HPA> MNTNC WORD (350) UPDATE RATE FAIL04 0 04 CM SMPM <HGA HPA> MNTNC WORD (350) DATA FAIL04 0 87 PP SMPM <HGA HPA> SELF--TEST MISOPERATION04 0 08 CM HMPM <HGA HPA> RF OVERDRIVE ERROR04 0 09 CM HMPM <HGA HPA> RF SUPPLY CURRENT FAIL04 0 0A CM HMPM <HGA HPA> OVER TEMP (COMB/DET) SHUTDOWN04 0 0B CM SMPM <HGA HPA> NO RESPONSE TO CARRIER COMMAND04 0 0C CM SMPM <HGA HPA> FAILURE WARNING W/NO DISC’S SET04 0 0D CM SMPM <HGA HPA> 429 MNTNC WORD PSU FAIL (350)04 0 0E CM SMPM <HGA HPA> 429 MNTNC WORD INTERNAL RAM FAIL04 0 0F CM SMPM <HGA HPA> 429 MNTNC WORD INTERNAL ROM FAIL04 0 10 CM SMPM <HGA HPA> CLASS C HPA MAX AVAIL PWR FAIL04 0 40 CM HMPM <HGA HPA> SELF--TEST BUTTON STUCK04 0 41 -- -- <HGA HPA> RESERVED (HP--720 “RF Power Input Low”)HPSU: HPA AC OR DC POWER SUPPLY UNIT04 1 01 CM HMPM <HGA HPA> PSU OVER TEMP SHUTDOWN04 1 02 CM HMPM <HGA HPA> PSU TEMP SENSOR FAIL04 1 03 CM HMPM <HGA HPA> PSU BIAS +5VDC FAIL04 1 04 CM HMPM <HGA HPA> PSU +28/+25.5 VDC FAIL04 1 05 CM HMPM <HGA HPA> PSU +5 VDC FAIL04 1 06 CM HMPM <HGA HPA> PSU +15 VDC FAILRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--6LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTION04 1 07 CM HMPM <HGA HPA> PSU --15 VDC FAIL04 1 08 CM HMPM <HGA HPA> PSU --85 VDC FAIL04 1 09 CM HMPM <HGA HPA> PSU +8 VDC FAIL04 1 0A CM HMPM <HGA HPA> PSU +16 VDC FAIL04 1 40 CM HMPM <HGA HPA> INTERNAL POWER SUPPLY FAIL04 1 41 CM HMPM <HGA HPA> PSU OVER TEMPHMPM: HPA MAIN PROCESSOR MODULE04 2 81 PP HMPM <HGA HPA> H/W--S/W COMPATIBILITY FAIL04 2 83/03 PP/CM HMPM <HGA HPA> BOOT FLASH MEMORY FAIL04 2 04 CM HMPM <HGA HPA> A429 SDU XMTR LOOP--BACK FAIL04 2 87 PP HMPM <HGA HPA> A429 MULTICNT RCVR FAIL04 2 88 PP HMPM <HGA HPA> A429 ADL RCVR FAIL04 2 89 PP HMPM <HGA HPA> A429 PDL--TO--HPA RCVR FAIL04 2 0A CM HMPM <HGA HPA> MAINTENANCE MEMORY CRC FAIL04 2 0B CM HMPM <HGA HPA> MAINTENANCE MEMORY WRITE FAIL04 2 8C/0C PP/CM HMPM <HGA HPA> CALIBRATION MEMORY CRC FAIL04 2 0D CM HMPM <HGA HPA> CALIBRATION MEMORY WRITE FAIL04 2 8E/0E PP/CM HMPM <HGA HPA> PROGRAM FLASH MEMORY FAIL04 2 90 PP HMPM <HGA HPA> RAM FAIL04 2 11 CM HMPM <HGA HPA> CPU OVER TEMP SHUTDOWN04 2 12 CM HMPM <HGA HPA> CPU TEMP SENSOR FAIL04 2 93/13 PP/CM HMPM <HGA HPA> CPU GND REF FAIL04 2 94/14 PP/CM HMPM <HGA HPA> FAN RELAY DRIVER FAIL04 2 95/15 PP/CM HMPM <HGA HPA> BIAS ENABLE LOOPBACK FAIL04 2 96/16 PP/CM HMPM <HGA HPA> VAR ATTN DRIVER FAIL04 2 17 CM HMPM <HGA HPA> FRONT PANEL TEST SWITCH STUCK04 2 98 PP HMPM <HGA HPA> WATCHDOG TIMEOUT FAIL04 2 19 CM HMPM <HGA HPA> DRIVER GND FAIL04 2 9C/1C PP/CM HMPM <HGA HPA> DRIVER TEST -- MUX04 2 9D PP HMPM <HGA HPA> DRIVER TEST -- GREEN LED04 2 9E PP HMPM <HGA HPA> DRIVER TEST -- RED LED04 2 A0 PP HMPM <HGA HPA> DRIVER TEST--MUTE ATTENUATOR04 2 A2 PP HMPM <HGA HPA> DRIVER TEST -- SER DATA CONCATENATE04 2 A5 PP HMPM <HGA HPA> MUTE INPUT TEST04 2 A6 PP HMPM <HGA HPA> CPU DEVICE TEST04 2 A7 PP HMPM <HGA HPA> ACTUAL POWER CALIBRATION04 2 A8 PP HMPM <HGA HPA> VALIDATION OF UPLOAD04 2 29 CM HMPM <HGA HPA> MUTE ATTEN P OUT OF LIMITS04 2 2A CM HMPM <HGA HPA> CODE VPP OUT OF LIMITS04 2 2B CM HMPM <HGA HPA> MAINT LOG VPP OUT OF LIMITS04 2 2C CM HMPM <HGA HPA> CAL MEM VPP OUT OF LIMITS04 2 AD/2D PP/CM HMPM HGA HPA> ADC REF OUT OF LIMITS04 2 2E CM HMPM <HGA HPA> PWR LO OUT OF LIMITS04 2 2F CM HMPM <HGA HPA> PSU TEMP LO OUT OF LIMITS04 2 30 CM HMPM <HGA HPA> AMPS LO OUT OF LIMITS04 2 31 CM HMPM <HGAHPA>SOFTWAREFAULT04 2 B3/33 PP/CM HMPM <HGA HPA> DISC OUTPUT TEST -- FAN04 2 B4 PP HMPM <HGA HPA> RS--422 INTERNAL LOOPBACK FAIL04 2 35 CM HMPM <HGA HPA> IGA LNA/DIP ON/OFF DISC LOOP FAIL04 2 C0 PP HMPM <HGA HPA> I2C INTERFACE FAILURE04 2 C1/41 PP/CM HMPM <HGA HPA> RAM FAILURE04 2 C2 PP HMPM <HGA HPA> KERNAL CODE ERROR04 2 C3 PP HMPM <HGA HPA> APPLICATION CODE ERROR04 2 C4 PP HMPM <HGA HPA> CONFIGURATION ERROR04 2 C5 PP HMPM <HGA HPA> SDU BUS I/F FAILURE04 2 C6 PP HMPM <HGA HPA> ADL BUS I/F FAILURE04 2 C7 PP HMPM <HGA HPA> PDL BUS I/F FAILURE04 2 C8 PP HMPM <HGA HPA> MAINTENANCE DUART FAILURE04 2 C9/49 PP/CM HMPM <HGA HPA> DISCRETE OUTPUTS FAILURE04 2 CA/4A PP/CM HMPM <HGA HPA> CP TEMP SENSOR FAILURE04 2 CB PP HMPM <HGA HPA> BOARD CONFIG/REV FAILURE04 2 4C CM HMPM <HGA HPA> I2C INTERFACE FAILURE04 2 4D CM HMPM <HGA HPA> ROM FAILUREDRIV: HPA RF DRIVER04 3 01 CM HMPM <HGA HPA> DRIVER RF OUTPUT FAIL04 3 02 CM HMPM <HGA HPA> DRIVER TEMP SENSOR FAIL04 3 03 CM HMPM <HGA HPA> DRIVER OVER TEMP SHUTDOWN04 3 04 CM HMPM <HGA HPA> DRIVER VCC FAILRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--7LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTIONPWR1: HPA RF POWER AMPLIFIER (1)04 5 01 CM HMPM <HGA HPA> <AMP 1> RF BALANCE FAIL04 5 02 CM HMPM <HGAHPA><AMP1>VCCFAILPWR2: HPA RF POWER AMPLIFIER (2)04 6 Same as for PWR1 except sub. SRU code 6 for 5 and <AMP--2> for <AMP--1>.PWR3: HPA RF POWER AMPLIFIER (3)04 7 Same as for PWR1 except sub. SRU code 7 for 5 and <AMP--3> for <AMP--1>.C/DET: HPA RF POWER COMBINER/DETECTOR04 8 01 CM HMPM <HGA HPA> FORWARD OUTPUT POWER DET 1 FAIL04 8 02 CM HMPM <HGA HPA> FORWARD OUTPUT POWER DET 2 FAIL04 8 03 CM HMPM <HGA HPA> FORWARD OUTPUT PWR COMPARE FAIL04 8 04 CM HMPM <HGA HPA> REFLECTED OUTPUT PWR DET FAIL04 8 05 CM HMPM <HGA HPA> COMBINER TEMP SENSOR FAILFPAMP: HPA RF FINAL POWER AMPLIFIER04 9 01 CM HMPM <HGA HPA> FINAL AMP 1 RF BALANCE FAIL04 9 02 CM HMPM <HGA HPA> FINAL AMP 1 VCC FAIL04 9 04 CM HMPM <HGA HPA> FINAL AMP 2 RF BALANCE FAIL04 9 05 CM HMPM <HGA HPA> FINAL AMP 2 VCC FAIL04 9 C0/40 PP/CM HMPM <HGA HPA> PA UNRESPONSIVE04 9 42 CM HMPM <HGA HPA> OVER CURRENT FAILURE04 9 43 CM HMPM <HGA HPA> DRIVER AMPLIFIER DC VOLTAGE FAILURE04 9 44 CM HMPM <HGA HPA> DRIVER AMPLIFIER CURRENT FAILURE04 9 45 CM HMPM <HGA HPA> 12 VDC FAILURE04 9 46 CM HMPM <HGA HPA> PA MUTE FAILURE04 9 47 CM HMPM <HGAHPA>PAOVERTEMP04 9 48 CM HMPM <HGAHPA>PASTATUSFAILURE04 9 49 CM HMPM <HGA HPA> PA TEMP SENSOR FAILUREHMB: HPA MOTHER BOARD04 A 40 CM HMPM <HGA HPA> BP TEMP SENSOR FAILURERFAM: 20W HPA RF AMPLIFIER MODULE04 B 01 CM HMPM <HGA HPA> OVER TEMP SHUTDOWN04 B 02 CM HMPM <HGA HPA> RFAM VCC FAIL04 B 03 CM HMPM <HGA HPA> AMP 1 VCC FAIL04 B 04 CM HMPM <HGA HPA> FORWARD OUTPUT POWER DET 1 FAIL04 B 05 CM HMPM <HGA HPA> FORWARD OUTPUT POWER DET 2 FAIL04 B 06 CM HMPM <HGA HPA> REFLECTED OUTPUT PWR DET FAIL04 B 07 CM HMPM <HGA HPA> TEMP SENSOR FAIL04 B 08 CM HMPM <HGA HPA> FORWARD OUTPUT POWER FAIL04 B 09 CM HMPM <HGA HPA> AMP 2 RF BALANCE FAIL04 B 0A CM HMPM <HGA HPA> AMP 2 VCC FAILLGA HPA07 Same entries as for HGA/IGA HPA above except substitute LRU code 7 for code 4, <LGA HPA> for <HGA HPA>, and [LGA_SUBSYS]for [HGA_SUBSYS]. For the cases of conditional HGA subsystem indictments ([cond_HGA_SUBSYS]), the equivalent LGA HPA failuresshall UNconditionally indict [LGA_SUBSYS].HSU #1Only applicable prior to SDU Part Number 7516118--XX130/--xx140.UNKNOWN <HSU1> SRU08 0 01 CM SMPM <HSU1> SELF--DECLARED FAILURE08 0 02 CM SMPM <HSU1> WILLIAMSBURG PROTOCOL ALO/ALR FAIL08 0 03 CM SMPM <HSU1> WILLIAMSBURG PROTOCOL DATA XFER FAIL08 0 84 PP SMPM <HSU1> SELF--TEST MISOPERATION08 0 05 CM SMPM <HSU1> CHANNEL RELEASE ACKNOWLEDGE FAILURE08 0 86/06 PP/CM SMPM <HSU1> RF LOOPBACK INHIBIT FAILUREHSCPU: <HSU1> CPU08 1 FA PP HSCPU <HSU1> ACCESS LEVEL DEVELOPMENT08 1 FB PP HSCPU <HSU1> ACCESS LEVEL PRODUCTION08 1 FC PP HSCPU <HSU1> ACCESS LEVEL PRODUCTION FAST STARTUP08 1 FD PP HSCPU <HSU1> SW VERSIONS INCONSISTENCY08 1 7F CM HSCPU <HSU1> ENVIRONMENT TEMP AT POWER--UP FAIL08 1 91 PP HSCPU <HSU1> TEMP SENSOR FAILUREFDSMP: <HSU1> FRAME DSP (AND INTERFACES)08 2 95 PP HSCPU <HSU1> FRAME DSP/CPU INTERFACE FAILUREVSDPM: <HSU1> VFC DSP (AND INTERFACES)08 3 98 PP HSCPU <HSU1> VFC DSP/CPU INTERFACE FAILURETFPGA: <HSU1> TURBO FPGA08 4 86 PP HSCPU <HSU1> TURBO FPGA FAILISDNT: <HSU1> ISDN TRANSCEIVER08 5 87 PP HSCPU <HSU1> ISDN TRANSCEIVER FAILURERELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--8LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTIONAFPGA: <HSU1> ARINC 429 FPGA08 6 NONECPURM: <HSU1> CPU RAM08 7 84 PP HSCPU <HSU1> CPU RAM FAILURECEM: <HSU1> CONVERTER EEPROM08 8 81 PP HSCPU <HSU1> EEPROM FAILUREFLASH: <HSU1> FLASH08 9 82 PP HSCPU <HSU1> PARAMETER BLOCK CHECKSUM FAILURE08 9 83 PP HSCPU <HSU1> CPU BIOS/APPLICATION CRC FAILURE08 9 87 PP HSCPU <HSU1> MISSING FILE IN FLASH08 9 88 PP HSCPU <HSU1> CORRUPTED FILE IN FLASH/INCORRECT CRCQUART: <HSU1> QUAD UART08 A 91 PP HSCPU <HSU1> EXTERNAL UART FAILUREETHER: <HSU1> ETHERNET08 B NONEPSPCB: <HSU1> POWER SUPPLY PCB08 C 0B CM HSCPU <HSU1> POWER FAILUREHCDMI: <HSU1>/CDM INTERFACE08 G F2 PP HSCPU <HSU1> CDM INTERFACE FAILURE08 G FE PP HSCPU <HSU1> CDM NOT FITTEDTDRAM: <HSU1> TURBO DECODER RAM08 J 8A PP HSCPU <HSU1> TURBO DECODER RAM FAILUREBATTM: <HSU1> BATTERY08 K 85 PP HSCPU <HSU1> BATTERY CHECK FAILURESTAM: <HSU1> STEP ATTENUATOR08 M B5 PP HSCPU <HSU1> STEP ATTENUATOR FAILUREHRFM: <HSU1> RF08 N 81 PP HSCPU <HSU1> 1.LO LOCK DETECTOR FAILURE08 N 82 PP HSCPU <HSU1> 2.LO LOCK DETECTOR FAILURE08 N 83 PP HSCPU <HSU1> 3.LO LOCK DETECTOR FAILURE08 N 91 PP HSCPU <HSU1> 1.LO MIN FREQUENCY TEST FAILURE08 N 92 PP HSCPU <HSU1> 2.LO MIN FREQUENCY TEST FAILURE08 N 93 PP HSCPU <HSU1> 3.LO MIN FREQUENCY TEST FAILURE08 N A1 PP HSCPU <HSU1> 1.LO MAX FREQUENCY TEST FAILURE08 N A2 PP HSCPU <HSU1> 2.LO MAX FREQUENCY TEST FAILURE08 N A3 PP HSCPU <HSU1> 3.LO MAX FREQUENCY TEST FAILURE08 N B0 PP HSCPU <HSU1> ALC -- CARRIER OFF FAILURE08 N B1 PP HSCPU <HSU1> ALC -- CARRIER ON FAILURE08 N B2 PP HSCPU <HSU1> RF LOOPBACK FAILURE08 N B3 PP HSCPU <HSU1> AVERAGE AMPLITUDE FAILURE08 N B4 PP HSCPU <HSU1> 16QAM SCPC FRAME SYNC FAILURE08 N BA PP HSCPU <HSU1> INTERNAL RX COAX CABLE FAILURE08 N BB PP HSCPU <HSU1> TX/RX CHANNEL FREQUENCY ERROR08 N BC PP HSCPU <HSU1> CARRIER_ON OFF CONTROL FAILURE08 N BD PP HSCPU <HSU1> RF LOOP_BACK OFF CONTROL FAILURE08 N BE PP HSCPU <HSU1> TX_ON/OFF CONTROL FAILURE08 N 41 CM HSCPU <HSU1> AGC LEVEL OUTSIDE LIMITS WARNING08 N C3 PP HSCPU <HSU1> LINEARITY OUTSIDE LIMITS WARNING08 N 51 CM HSCPU <HSU1> 1.LO LOCK FAILURE08 N 52 CM HSCPU <HSU1> 2.LO LOCK FAILURE08 N 53 CM HSCPU <HSU1> 3.LO LOCK FAILUREREOSM: <HSU1> REFERENCE OSCILLATOR08 O 42 CM HSCPU <HSU1> REF OSC WARNING: SEND HSU TO CAL08 O 63 CM HSCPU <HSU1> REF OSC FAILURE/VOLTAGE TOO LOW08 O 64 CM HSCPU <HSU1> REF OSC FAILURE/VOLTAGE TOO HIGHBMONM: <HSU1> BURST DURATION MONITOR08 P 81 PP HSCPU <HSU1> BURST DURATION MONITOR CIRCUIT08 P 04 CM HSCPU <HSU1> TDM BURST DURATION FAILURE08 P 85 PP HSCPU <HSU1> CARRIER ON SIGNALSDCOMM: <HSU1> DOPPLER COMPENSATION08 Q 39 CM HSCPU <HSU1> REF OSC COMPENSATION ERRORFVFCI: <HSU1> FRAME DSP/VFC DSP INTERFACE08 R 17 CM HSCPU <HSU1> FRAME DSP/VFC DSP FAILUREFDTFI: <HSU1> FRAME DSP/TURBO FPGA INTERFACE08 S 96 PP HSCPU <HSU1> FRAME TURBO FPGA INTERFACE FAILUREPSIPI: <HSU1> POWER SUPPLY PCB/ISDN PHONE INTERFACE08 W 88 PP HSCPU <HSU1> ISDN SUPPLY VOLTAGE FAILURERELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--9LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTIONCDM: <HSU1> CONFIGURATION DATA MODULE08 X F1 PP HSCPU <HSU1> INVALID SERIAL NUMBER08 X F3 PP HSCPU <HSU1> CDM ESSENTIAL DATA FAILURE08 X F4 PP HSCPU <HSU1> CDM DATA ACCESS ERROR08 X F5 PP HSCPU <HSU1> CDM MISSING WRITE PROTECTION08 X F6 PP HSCPU <HSU1> CDM INCORRECT VERSIONITPSI: <HSU1> ISDN TRANSCEIVER/POWER SUPPLY PCB INTERFACE08 Z 89 PP HSCPU <HSU1> ISDN RX VOLTAGEHSU #209 Same entries as for HSU #1 above except substitute LRU code 09 for code 08, <HSU2> for <HSU1>, and [HSU2] for [HSU1]. Onlyapplicable prior to SDU Part Number 7516118--XX130/--xx140.HIGH POWER RELAYUNKNOWN HPR SRU0A 0 01 CM SMPM (PORT) MNTNC WORD HPR FAIL0A 0 02 CM SMPM (STBD) MNTNC WORD HPR FAILTOP/PORT LNA/DIPLEXERUNKNOWN TOP/PORT LNA/DIPLEXER SRU0D 0 01 CM SMPM <T/P LNA/DIP> MNTNC WORD FAILSTARBOARD LNA/DIPLEXER0F Same entries as for TOP/PORT LNA/Diplexer above except substitute STBD BSU for T/P BSU, LRU code 0F for code 0D and <STBDLNA/DIP> for <T/P LNA/DIP>.LGA LNA/DIPLEXERUNKNOWN LGA LNA/DIPLEXER SRU10 0 01 CM SMPM LGA LNA/DIP FAILTOP/PORT BSU OR ACUUNKNOWN TOP/PORT BSU OR ACU SRU13 0 01 CM SMPM <T/P B/A> MNTNC WORD (350) UPDATE RATE FAIL13 0 02 CM SMPM <T/P B/A> MNTNC WORD (350) DATA FAIL13 0 03 CM SMPM <T/P B/A> STATUS WORD (144) UPDATE RATE FAIL13 0 04 CM SMPM <T/P B/A> STATUS WORD (144) DATA FAIL13 0 05 CM SMPM <T/P B/A> MNTNC WORD RAM FAIL13 0 06 CM SMPM <T/P B/A> MNTNC WORD ROM FAIL13 0 07 CM SMPM <T/P B/A> MNTNC WORD PSU FAIL13 0 08 CM SMPM <T/P B/A> MNTNC WORD PARAMETER FAIL13 0 09 CM SMPM <T/P B/A> MNTNC WORD TEMP FAIL13 0 8A PP SMPM <T/P B/A> SELF--TEST MISOPERATIONSTARBOARD BSU15 Same entries as for TOP/PORT BSU or ACU above except substitute LRU code 15 for code 13 and <STBD BSU> for <T/P B/A>.TOP/PORT HGA/IGAUNKNOWN TOP/PORT HGA/IGA SRU1A 0 01 CM SMPM <T/P HGA/IGA> MNTNC WORD FAIL1A 0 02 CM HMPM IGA FAILURE1A 0 03 CM HMPM IGA RS--422 INPUT BUS LINK FAULT1A 0 04 CM HMPM IGA HPA RS--422 INPUT BUS ERROR/INACTIVESTARBOARD HGA1C Same entries as for TOP/PORT HGA above except substitute LRU code 1C for code 1A, <STBD BSU> for <T/P B/A>, and <STBDHGA> for <T/P HGA>.LGAUNKNOWN LGA SRUSCDU/WSC #1UNKNOWN SCDU/WSC #1 SRU21 0 01 CM SMPM <SCDU--1> PROTOCOL ERROR21 0 02 CM SMPM <WSC--1> STATUS (270) BAD SSM21 0 03 CM SMPM <WSC--1> MASTER PROTOCOL ERROR21 0 04 CM SMPM <WSC--1> DATA TRANSMISSION FAILURE21 0 07 CM SMPM <WSC--1> MASTER TEST LOOP FAILURESCDU/WSC #222 Same entries as for SCDU/WSC #1 above except substitute LRU code 22 for code 21, <WSC--2> for <WSC--1>, and <SCDU--2> for<SCDU--1>.SCDU/WSC #323 Same entries as for SCDU/WSC #1 above except substitute LRU code 23 for code 21, <WSC--3> for <WSC--1>, and <SCDU--3> for<SCDU--1>.(C)MU #1UNKNOWN (C)MU #1 SRU33 0 02 CM SMPM <(C)MU--1> STATUS (270) BAD SSM33 0 03 CM SMPM <(C)MU--1> MASTER PROTOCOL ERROR33 0 04 CM SMPM <(C)MU--1> DATA TRANSMISSION FAILURE33 0 05 CM SMPM <(C)MU--1> SLAVE PROTOCOL ERROR33 0 06 CM SMPM <(C)MU--1> SELF--DECLARED FAILURERELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--10LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTION33 0 07 CM SMPM <(C)MU--1> MASTER TEST LOOP FAILURE33 0 08 CM SMPM <(C)MU--1> SLAVE TEST LOOP FAILURE(C)MU #234 Same entries as for CMU #1 above except substitute LRU code 34 for code 33 and <(C)MU--2> for <(C)MU--1>.IRS--PRIUNKNOWN IRS--PRI SRU35 0 02 CM SMPM <IRS--PRI> LAT DATA (310) FAIL35 0 04 CM SMPM <IRS--PRI> LON DATA (311) FAIL35 0 06 CM SMPM <IRS--PRI> GND SPD DATA (312) FAIL35 0 08 CM SMPM <IRS--PRI> TRK DATA (313) FAIL35 0 0A CM SMPM <IRS--PRI> TRUE HDG DATA (314) FAIL35 0 0C CM SMPM <IRS--PRI> PITCH DATA (324) FAIL35 0 0E CM SMPM <IRS--PRI> ROLL DATA (325) FAILIRS--SEC36 Same entries as for IRS--PRI above except substitute LRU code 36 for code 35 and <IRS--SEC> for <IRS--PRI>.CFDS/CMCUNKNOWN CFDS/CMC SRU39 0 01 CM SMPM INVALID OMS PARAMETER(S)429 ICAO ADDRESS SOURCEUNKNOWN 429 ICAO ADDRESS SOURCE SRU40 0 01 CM SMPM 429 ICAO ADDRESS FAIL40 0 02 CM SMPM DUAL SYSTEM DIFFERENT 429 AES IDCABIN TELECOMMUNICATIONS UNITUNKNOWN CABIN TELECOMMUNICATIONS UNIT SRU42 0 01 CM SMPM CCS ECL NOT ESTABLISHED42 0 02 CM SMPM CCS CCL NOT ESTABLISHED42 0 03 CM SMPM CCS CTU NOT AVAILABLE42 0 04 CM SMPM CCS PDL NOT ESTABLISHEDCPDF43 Same entries as for CMU #1 above except substitute LRU code 43 for code 33, <CPDF> for <(C)MU--1> and make the class of all CPDFfailure 2.SDU INPUT BUSES AND RELATED50 0 01 CM SMPM SDU HSU1 BUS INACTIVE50 0 02 CM SMPM HSU1 SELF--TEST MISOPERATION50 0 03 CM SMPM HSU1 PERIODIC DATA RATE FAIL50 0 04 CM SMPM HSU1 SOLO WORD DATA RATE FAIL50 0 05 CM SMPM HSU1 W’BURG DATA RATE FAIL51 0 01 CM SMPM SDU HSU2 BUS INACTIVE51 0 02 CM SMPM HSU2 SELF--TEST MISOPERATION51 0 03 CM SMPM HSU2 PERIODIC DATA RATE FAIL51 0 04 CM SMPM HSU2 SOLO WORD DATA RATE FAIL51 0 05 CM SMPM HSU2 W’BURG DATA RATE FAIL52 0 01 CM SMPM SDU CPDF BUS INACTIVE53 0 01 CM SMPM SDU CMU--1 BUS INACTIVE54 0 01 CM SMPM SDU CTU CEPT--E1 BUS INACTIVE55 0 01 CM SMPM SDU SCDU/WSC--1 BUS INACTIVE56 0 01 CM SMPM SDU SCDU/WSC--2 BUS INACTIVE57 0 01 CM SMPM SDU CMU--2 BUS INACTIVE59 0 01 CM SMPM SDU CFDS BUS INACTIVE59 0 02 CM SMPM INVALID OMS PARAMETER(S)5A 0 01 CM SMPM SDU PRI IRS BUS INACTIVE5B 0 01 CM SMPM SDU SEC IRS BUS INACTIVE5C 0 01 CM SMPM SDU HGA/IGA HPA BITE BUS INACTIVE5C 0 02 CM SMPM HGA/IGA HPA SELF--TEST MISOPERATION5F 0 01 CM SMPM SDU LGA HPA BITE BUS INACTIVE5F 0 02 CM SMPM LGA HPA SELF--TEST MISOPERATION62 0 01 CM SMPM SDU TOP/PORT BSU/ACU BITE BUS INACTIVE62 0 02 CM SMPM TOP/PORT BSU/ACU SELF--TEST MISOPERATION64 0 01 CM SMPM SDU STBD BSU BITE BUS INACTIVE64 0 02 CM SMPM STBD BSU/ACU SELF--TEST MISOPERATION65 0 01 CM SMPM SDU RMP BUS INACTIVE66 0 01 CM SMPM SDU SCDU/WSC--3 BUS INACTIVE71 0 01 CM SMPM SDU CROSS--TALK BUS INACTIVE73 0 01 CM SMPM SDU FMC--1 BUS INACTIVE74 0 01 CM SMPM SDU FMC--2 BUS INACTIVEHGA/IGA HPA INPUT BUSES90 0 01 CM SMPM HGA/IGA HPA 429 MNTNC WORD CTL BUS INACTIVE90 0 02 CM HMPM HGA/IGA HPA MULTICONTROL BUS INACTIVERELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--11LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTIONLGA HPA INPUT BUSES96 0 01 CM SMPM LGA HPA 429 MNTNC WORD CONTROL BUS INACTIVE96 0 02 CM HMPM LGA HPA MULTICONTROL BUS INACTIVETOP/PORT BSU/ACU INPUT BUSES98 0 01 CM SMPM MNTNC WORD T/P BSU/ACU MULTICTL BUS INACTIVEPORT BSU INPUT BUSES9A 0 01 CM SMPM MNTNC WORD PORT BSU CROSSTALK BUS INACTIVESTARBOARD BSU INPUT BUSES9C 0 01 CM SMPM MNTNC WORD STBD BSU MULTICTL BUS INACTIVE9D 0 01 CM SMPM MNTNC WORD STBD BSU CROSSTALK BUS INACTIVEHSU #1 INPUT BUS9E 0 01 CM SMPM <HSU1> 429 CONTROL BUS INACTIVE9E 0 02 CM SMPM <HSU1> ICAO ADDRESS INVALID9E 0 03 CM SMPM <HSU1> POSITION UNAVAILABLE9E 0 04 CM SMPM <HSU1> VELOCITY UNAVAILABLEHSU #2 INPUT BUS9F Same as entries for HSU #1 above except substitute Level 1 code 9F for code 9E and <HSU2> for <HSU1>. Only applicable prior toSDU Part Number 7516118--XX130/--xx140.WSC INPUT BUSESA1 0 01 CM SMPM WSC1 429 CNTRL BUS FROM THIS SDU INACTIVEA2 0 01 CM SMPM WSC2 429 CNTRL BUS FROM THIS SDU INACTIVEA3 0 01 CM SMPM WSC3 429 CNTRL BUS FROM THIS SDU INACTIVEHSU USER INTERFACESA6 0 01 CM HSCP HSU ETHERNET PORT 1 BUS INACTIVEA7 0 01 CM HSCP HSU ETHERNET PORT 2 BUS INACTIVEA8 0 01 CM HSCP HSU ISDN PORT 1 BUS INACTIVEA9 0 01 CM HSCP HSU ISDN PORT 2 BUS INACTIVEMISCELLANEOUS ERRORS, FAILURES AND WARNINGSSDU SYSTEM CONFIGURATION STRAP ERRORSC0 0 81 PP SMPM SDU STRAPS PARITY ERRORC0 0 82 PP SMPM SDU ANT CONFIG STRAPS ERRORC0 0 83 PP SMPM SDU CFDS CONFIG STRAPS ERRORC0 0 84 PP SMPM SDU STRAPS INCONSISTENCYC0 0 05 CM SMPM DUAL SYSTEM CONFIG STRAPS ERRORC0 0 06 CM SMPM DUAL REMOTE COCKPIT STRAPS INCOMPATIBLEC0 0 87 PP SMPM MANUFACTURER--SPECIFIC STRAPS PARITY ERRORMISCC1 0 81/01 PP/CM SMPM SDU WOW MISCOMPARE ERRORC2 0 81 PP SMPM SDU DUAL SYSTEM SELECT/DISABLE TEST ERRORC2 0 82 PP SMPM SDU DUAL SYSTEM SEL/DIS TEST NOT INITIATEDC3 0 81 PP SMPM SDU (ICAO) ADDRESS BITS (STRAPS) ERRORC3 0 02 CM SMPM DUAL SYSTEM DIFFERENT STRAPS AES IDC4 0 01 CM SMPM HGA/IGA HPA 429 MNTNC WORD OUTPUT VSWR BADC4 0 02 CM HMPM HGA/IGA HPA REFLECTED OUTPUT POWER ERRORC5 0 81/01 PP/CM SMPM ORT/LOCAL CONFIG STRAPS INCOMPATIBILITYC5 0 02 CM SMPM DUAL ORT/COMBINED CONFIG STRAPS INCOMPC6 0 01 CM SMPM LGA HPA 429 MNTNC WORD OUTPUT VSWR BADC6 0 02 CM HMPM LGA HPA REFLECTED OUTPUT POWER ERRORHGA/IGA HPA OVER TEMP WARNINGSC7 0 01 CM SMPM HGA HPA MNTNC WORD LRU OVER TEMPC7 1 01 CM HMPM HGA HPA PSU OVER TEMP WARNINGC7 2 01 CM HMPM HGA HPA CPU OVER TEMP WARNINGC7 2 02 CM HMPM HGA HPA OVER TEMP WARNINGC7 3 01 CM HMPM HGA HPA DRIVER OVER TEMP WARNINGC7 8 01 CM HMPM HGA HPA OVER TEMP (COMBINER) WARNINGC7 B 01 CM HMPM HGA HPA RFAM OVER TEMP WARNINGMISCC8 0 01 CM SMPM INVALID FREQ CMD FROM GESC8 0 02 CM SMPM GNSS INTERFERENCE RISK FROM GESLGA HPA OVER TEMP WARNINGSC9 0 01 CM SMPM LGA HPA MNTNC WORD LRU OVER TEMPC9 1 01 CM HMPM LGA HPA PSU OVER TEMP WARNINGC9 2 01 CM HMPM LGA HPA CPU OVER TEMP WARNINGC9 2 02 CM HMPM LGA HPA OVER TEMP WARNINGC9 3 01 CM HMPM LGA HPA DRIVER OVER TEMP WARNINGC9 8 01 CM HMPM LGA HPA OVER TEMP (COMBINER) WARNINGC9 B 01 CM HMPM LGA HPA RFAM OVER TEMP WARNINGRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--12LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTIONMISCCA 0 01 CM SMPM LGA LNA CONTROL DRIVER FAILCB 0 01 PP HMPM HGA/IGA HPA INVALID SDI STRAPPINGCC 0 01 PP HMPM LGA HPA INVALID SDI STRAPPINGTOTC/POC RESETSCD 0 81/01 PP/CM SMPM SDU TOTC AUTO/MANUAL RESETCD 0 82/02 PP/CM SMPM SDU POC AUTO/MANUAL RESETCF 0 81/01 PP/CM HMPM HGA/IGA HPA TOTC AUTO/MANUAL RESETCF 0 82/02 PP/CM HMPM HGA/IGA HPA POC AUTO/MANUAL RESETD0 0 81/01 PP/CM HMPM LGA HPA TOTC AUTO/MANUAL RESETD0 0 82/02 PP/CM HMPM LGA HPA POC AUTO/MANUAL RESETWRONG SDI CODESD1 0 01 CM SMPM HGA/IGA HPA WRONG A429 SDI CODED2 0 01 CM SMPM LGA HPA WRONG A429 SDI CODED3 0 01 CM SMPM TOP/PORT BSU/ACU WRONG A429 SDI CODED4 0 01 CM SMPM STARBOARD BSU WRONG A429 SDI CODERF INTER--LRU FAILURESD5 0 01 CM SMPM SDU TO HGA/IGA HPA CALIBRATION ERRORD5 0 02 CM SMPM SDU TO LINEAR HGA/IGA HPA RF CONTIN. FAILD5 0 03 CM SMPM SDU TO CLASS C HGA/IGA HPA RF CONTIN. FAILD5 0 04 CM SMPM SDU TO HGA/IGA HPA ATTEN. CALIBRATION ERRORD5 0 05 CM SMPM SDU TO LINEAR HGA/IGA HPA ATTEN. RF CONTIN. FAILD6 0 01 CM SMPM SDU TO LGA HPA CALIBRATION ERRORD6 0 02 CM SMPM SDU TO LINEAR LGA HPA RF CONTINUITY FAILD6 0 03 CM SMPM SDU TO CLASS C LGA HPA RF CONTINUITY FAILD6 0 04 CM SMPM SDU TO LGA HPA ATTEN. CALIBRATION ERRORD6 0 05 CM SMPM SDU TO LINEAR LGA HPA ATTEN. RF CONTIN. FAILD8 0 81 PP SMPM T/P HGA LNA TO SDU RF CONTINUITY FAILD9 0 81 PP SMPM STBD HGA LNA TO SDU RF CONTINUITY FAILDA 0 81 PP SMPM LGA LNA TO SDU RF CONTINUITY FAILMISCDB 0 01 CM SMPM LGA LOG--ON TEST FAILUREDB 0 02 CM SMPM SLAVE LGA LOG--ON TEST NOT INITIATEDDC 0 01 CM SMPM NO DECLARED ACTIVE (C)MUSDU ORT ERRORSSDU SECURED ORT ERRORSDD 0 01 CM SMPM (I) STARTUP LOG--ON POLICYDD 0 03 CM SMPM (VIII) RESPONSE CAPABILITY TO LOG--ON INTRRGTNDD 0 04 CM SMPM (XVIII) NOISE INSERTION LEVELDD 0 05 CM SMPM (XXII) TX GAIN THRESHOLDDD 0 06 CM SMPM (XXIII) APHONE SYSTEM MANAGEMENT COMMANDSDD 0 08 CM SMPM (XXVIII) HPA BACKOFF LIMITSDD 0 09 CM SMPM (XXIX) HPA MIN REPORTABLE ACTUAL PWR OUTDD 0 0A CM SMPM (XXX) DEFAULT ASSUMED GLOBAL INITIAL C--CH EIRPDD 0 0B CM SMPM (XXXI) SCDU TELEPHONE NUMBER PRESELECTDD 0 0C CM SMPM (XXXII) ACP CALL INITIATIONDD 0 0D CM SMPM (XXXVIII) FAILURE MASKING DATADD 0 0E CM SMPM (XXXIX) ELEVATION HANDOVER THRESHOLDDD 0 0F CM SMPM (XLI) AUTOMATIC TRANSIT CALL GES TABLEDD 0 10 CM SMPM (XLII) AIR--TO--GROUND CHIMEDD 0 11 CM SMPM (XLIII) SCDU CALL PROMPTSDD 0 12 CM SMPM (XLIV) EIRP OVERDRAFT CHECKING PRIORITYDD 0 13 CM SMPM (XLVI) COCKPIT AUDIO LEVEL SETTINGSDD 0 14 CM SMPM (XLVII) HGA RETRY PERIODDD 0 15 CM SMPM (XLVIII) COCKPIT CHAN INTERFACE TYPE FOR DUALDD 0 16 CM SMPM (L) “DIS/REENABLE OTHER SATCOM” SCDU PROMPTSDD 0 17 CM SMPM (LI) SCDU SATCOM SUBSYSTEM PROMPTSDD 0 18 CM SMPM (LII) SCDU CHANNEL LABEL SUFFIXESDD 0 19 CM SMPM (LIII) SECURED ORT DESCRIPTIONDD 0 1A CM SMPM (LIV) COMPOSITE ORT FILE UPLOAD ALLOWEDDD 0 1B CM SMPM SECURED ORT MISMATCH WITH OTHER SDUDD 0 1C CM SMPM (LVI) ACCESS TO ZERO--PREFERENCE GESSDD 0 1D CM SMPM (LV) SECURED ORT MODIFIED FLAGDD 0 1E CM SMPM (LVII) L--BAND REFERENCE OFFSET CAL THRESHOLDSDD 0 1F CM SMPM (LIX) APHONE AUDIO LEVEL SETTINGDD 0 20 CM SMPM (LX) AERO--H ONLY OPERATIONSDU USER ORT ERRORSDE 0 01 CM SMPM (II) SATELLITE/GES NAMESDE 0 02 CM SMPM (III) GES PREFERENCE VALUESRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--13LEVEL 1 SRU FAILURE MONITORING TESTER FAILURE DESCRIPTIONDE 0 03 CM SMPM (IV) MAINTENANCE PAGE ACCESSDE 0 04 CM SMPM (V) COCKPIT TELEPHONE NUMBERSDE 0 05 CM SMPM (VII) RESOURCES RESERVED FOR HEADSETDE 0 07 CM SMPM (X) GROUND--TO--AIR CIRCUIT--MODE DATADE 0 08 CM SMPM (XIII) GROUND--TO--AIR CALLSDE 0 09 CM SMPM (XIV) CALL CAMP--ON DURATIONDE 0 0A CM SMPM (XV) CAMP--ON TIMEOUT ACTIONDE 0 0B CM SMPM (XVI) STORE APHONE TELEPHONE NUMBERSDE 0 0C CM SMPM (XIX) GROUND--TO--AIR CALL PREEMPTIONDE 0 0D CM SMPM (XX) PREFERRED COCKPIT CALL ROUTINGDE 0 0E CM SMPM (XXI) PREFERRED APHONE CALL ROUTINGDE 0 0F CM SMPM (XXIV) APHONE OUTGOING CALL BARRING LEVELDE 0 10 CM SMPM (XXV) CALL BARRING SECURITY CODEDE 0 11 CM SMPM (XXVI) SHARED APHONE PHONE NUMBER STORAGEDE 0 12 CM SMPM (XXXIII) ORT DESCRIPTIONDE 0 13 CM SMPM (XXXIV) AIRLINE CODEDE 0 14 CM SMPM (XXXV) HEADSET OUTGOING CALL BARRING LEVELDE 0 15 CM SMPM (XXXVI) HEADSET TRANSIT CALLDE 0 16 CM SMPM (XL) HIGH RATE DATA TRANSMIT SUPPORTDE 0 17 CM SMPM (XLV) APHONE CALLED TERMINAL ID ASSIGNMENTDE 0 18 CM SMPM (IL) MASTERY HANDOVER ALGORITHM WEIGHTINGDE 0 19 CM SMPM (LVIII) AES POSITION REPORTINGDE 0 1A CM SMPM (LXI) HSD PREEMPTION FOR PRIORITY 4 CALLSDE 0 1B CM SMPM (LXII) ONGOING HSD CALL EIRPDE 0 1C CM SMPM (XXXVII) ORT MODIFIED FLAGDE 0 1D CM SMPM (LXIII) WSC MANUAL DIALINGDE 0 1E CM SMPM (LXIV) MINIMUM HSD CALL EIRPDE 0 1F CM SMPM (LXV) HSD REGISTRATION PREFERENCEDE 0 20 CM SMPM (LXVI) SWIFT64 M--ISDN LES PREFERENCE VALUESDE 0 21 CM SMPM (LXVII) SWIFT64 MPDS LES PREFERENCE VALUESDE 0 22 CM SMPM (LXVIII) ETHERNET MAC ADDRESS ASSIGNMENTDE 0 23 CM SMPM (LXIX) PPPoE ACCESS--CONCENTRATOR NAMEDE 0 24 CM SMPM (LXX) TELNET SERVER ACCESSDE 0 25 CM SMPM (LXXI) DHCP SERVER ACCESSDE 0 26 CM SMPM (LXXII) TELNET IP ADDRESS ASSIGNMENTDE 0 27 CM SMPM (LXXIII) TELNET SUBNET MASK ASSIGNMENTDE 0 28 CM SMPM (LXXIV) TELNET DEFAULT GATEWAY ASSIGNMENTDE 0 29 CM SMPM (LXXV) DHCP IP ADDRESS ASSIGNMENTDE 0 2A CM SMPM (LXXVI) DHCP IP ADDRESS POOL ALLOCATIONDE 0 2B CM SMPM (LXXVII) BGAN PDP SESSION PARAMETERSDE 0 2C CM SMPM (LXXVIII) PSID SUPPLEMENTARY FREQUENCIESMISCDF 0 01 CM SMPM SLAVE HGA/IGA LOG--ON TEST FAILUREDF 0 02 CM SMPM SLAVE HGA/IGA LOG--ON TEST NOT INITIATEDE1 0 01 CM SMPM HSU1 SYSTEM DISABLE DISCRETE FAILUREE1 0 01 CM SMPM HSU SYSTEM DISABLE DISCRETE FAILUREE2 0 01 CM SMPM HSU2 SYSTEM DISABLE DISCRETE FAILUREE3 0 01 CM SMPM UNSUPPORTED HSU1 CONFIGURATIONE3 0 02 CM SMPM UNSUPPORTED HSU2 CONFIGURATIONE4 0 81 PP SMPM HSU1/SDU INTERFACE VERSION INCOMPATIBILITYE5 0 81 PP SMPM HSU2/SDU INTERFACE VERSION INCOMPATIBILITYE6 0 81/01 PP/CM SMPM HSU1/HPA TX RF SIGNAL PATH FAILUREE6 0 02 CM SMPM HSU1 to HGA/IGA HPA CALIBRATION ERRORE6 0 03 CM SMPM HSU2 to HGA/IGA HPA CALIBRATION ERRORE6 0 04 CM SMPM HSU3 to HGA/IGA HPA CALIBRATION ERRORE6 0 05 CM SMPM HSU4 to HGA/IGA HPA CALIBRATION ERRORE7 0 01 CM SMPM HSU2/HPA TX RF SIGNAL PATH FAILUREE8 0 81 PP SMPM DLNA/HSU1 RX RF SIGNAL PATH FAILUREE9 0 81 PP SMPM DLNA/HSU2 RX RF SIGNAL PATH FAILUREEA 0 01 CM SMPM DUAL HSU--700 CONFIG WARNINGEB 0 01 CM SMPM NO DECLARED ACTIVE WSCEC 0 81 PP HSCP HSU CONFIGURATION STRAPS PARITY ERROREC 0 82 PP HSCP HSU CONFIGURATION STRAPS ERRORED 0 01 CM HSCP SDU ORT/HSU CONFIG STRAPS INCOMPATIBILITYEE 0 81 PP HSCP HSU FORWARD ID ADDRESS BITS (STRAPS) ERROREE 0 82 PP HSCP ILLEGAL HSU FORWARD ID ADDRESSFD 0 01--16 N/A SMPM EXTERNAL PILOT EVENT MARKER TO SDUFE 0 01 POST SMPM EXTERNAL POWER SUPPLY INTERRUPT TO SDURELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--14COMMENTARYThe following information is applicable prior to SDU Part Number 7516118--XX130/--xx140, and translates theHSU failure codes to their “original” codes (for correlation with non--SYP documentation).HSU FAILURES ORIGINAL CODE08001--08002--08003--08084--081FAUH7A081FBUH7B081FCUH7C081FDUH7D0817FUHB008191UHB108295UH9508398UH9808486UHA608587UHA708784UH8408881UHEU08982UH8208983UH8308987UH8708988UH8808 A 91 UH9108 C 0B UHAB08 G F2 UH7208 G FE UH7E08 J 8A UHAA08 K 85 UH8508 M B5 UH3508 N 81 UH0108 N 82 UH0208 N 83 UH0308 N 91 UH1108 N 92 UH1208 N 93 UH1308 N A1 UH2108 N A2 UH2208 N A3 UH2308 N B0 UH3008 N B1 UH3108 N B2 UH3208 N B3 UH3308 N B4 UH3408 N BA UE0108 N BB UH3B08NBCUH3C08NBDUH3D08 N BE UH3E08 N 40 UHW008 N 41 UHW108 N C3 UHW308 N 51 UH5108 N 52 UH5208 N 53 UH53RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--1508 O 42 UHW208 O 63 UH6308 O 64 UH6408 P 81 UHA108 P 04 UHA408 P 85 UHA508 Q 39 UH3908 R 17 UH9708 S 96 UH9608 W 88 UHA808 X F1 UH7108 X F3 UH7308 X F4 UH7408 X F5 UH7508 X F6 UH7608 Z 89 UHA99E002UH779E003UH789E004UH79COMMENTARYThe following information is applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent, andtranslates the remapped HSU failure codes back to their “original” codes (as reported by the HSU viaWilliamsburg messages).HSU FAILURES ORIGINAL CODEA6001001A7001002A8001003A9001004EC08108CEC082982ED00100FEE081981EE082090NOTES:1. This note not used for MCS7000.2. Not implemented.3. To preclude the possibility of ongoing failure indications in case the “OK” flag block transfer (which clears afailure when it is no longer currently active) is not received for any reason, failure codes 04/07 1 40, 04/07 241/4D, 90/96 0 02, C4/C6 0 02 are implemented only in the HPA (i.e., they are ignored by the SDU and arenot copied into the system failure log) since they are redundant to failures raised by the SDU in response tocertain HPA Maintenance Word DISCRETES bits being set.4. This note not applicable for MCS7000.5. This failure is declared “Internal,” even though it is believed to be caused by the GES, in order to permit itto be logged if it occurs while the aircraft is on the ground (since the defined response is to reset the SDU,whereupon the failure is lost while on the ground due to external failure logging being inhibited at that time).6. Failure CB 0 01 is used by either the SDU in the system failure log (”HGA HPA INVALID ...”) or genericallyby either HPA in its LRU failure log (”HPA INVALID ...”), hence the bracketed “[HGA]” in the failure descriptionentry (because the “HGA” part only applies to the SDU usage). Failure CC 0 01 is used exclusively by theSDU, hence “LGA” is not bracketed. Contrary to the usual convention, the CM failure code 01 is used (ratherthan the POST/PAST code 81) even though the failures are only detected during POST/PAST.7. This note not applicable to MCS7000.8. This note not applicable to MCS7000.9. If the 40W HGA (or LGA) HPA’s hardware/software compatibility strap setting is 00h (indicating thepresence of the original 40W HPA hardware configuration), then regardless of the software package residentin the HPA, failure codes 04 (or 07)/4/xx (for the splitter SRU [A4]), 04 (or 07)/6/xx (for the power amplifier #2SRU [A6]), and 04 (or 07)/7/xx (for the power amplifier #3 SRU [A7]) is reported to the SDU as well as storedRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--16in the HPA when the respective failures occur. If the HPA’s HW/SW compatibility strap setting is 02h orbeyond (indicating the inclusion of Hardware Mod D, in which the functions of the former A4, A6, and A7SRUs, as well as the combiner portion of the former A8 SRU, are integrated into a single new final poweramplifier SRU [A9]), and if the resident HPA software package is any one prior to D2.0, then the HPA shalltransmit 04 (or 07)/7/xx (the code for SRU A7 [power amplifier #3]) to the SDU whenever 04 (or 07)/9/xx (thecode for SRU A9 [final power amplifier]) is recorded in the HPA’s internal failure log; under these conditions,the other codes (for A4 and A6) are never transmitted to the SDU.10. Failure codes 04 (or 07)/9/xx is reported to the SDU as well as stored in the HPA when the HPA’s residentsoftware package is D2.0 or beyond and the HPA has a hardware/software compatibility strap setting of 02hor beyond.11. All other HPA block--transfer failures that are redundant to those covered by the HPA Maintenance Wordare not implemented in the SDU (per Note 3 above). The overtemp warnings and shutdowns covered by thisnote, however, (04/07 0 0A/42, 04/07 1 01/41, 04/07 2 11, 04/07 3 03, 04/07 9 47, 04/07 B 01, C7/C91/2/3/8/B 01, C7/C9 2 02), which do map to HPA Maintenance Word bit #13 (which is covered by failureC7/C9 0 01), are nonetheless still implemented by the SDU.12. Code 35 is designated IRS--PRI, code 36 is designated IRS--SEC.13. This note not applicable to MCS7000.14. This is a pseudo--failure.15. This failure is only generated by the Honeywell 20W HPA.16. This failure is only generated by the Honeywell 40W HPA.17. The PSU +25.5 VDC failure is only applicable to the Honeywell 20W HPA and the +28 VDC failure is onlyapplicable to the Honeywell 40W HPA.18. Not used.19. These BSU Maintenance Word--related failures can also be raised due to Solo Word #8 transmitted froma Honeywell 20W HPA that is steering an IGA.20. This fault, if it does not transition to a failure, will cause the modem software to be reloaded.21. This note not applicable to MCS7000.22. This note not applicable to MCS7000.23. This note not applicable to MCS7000.24. This note not applicable to MCS7000.25. This failure is only applicable to Modems 2 and 5.26. Code not used in MCS7000, reserved due to use in MCS 3000/6000.27. The indicted functional resource is conditional ---- [hga_subsys] if another antenna subsystem is installed(including the case of a dual system), and NONE if the HGA is the only antenna subsystem installed.28. These failures shall not apply to aircraft strapped for “Airbus” CFDS type.29. These failures shall only apply to aircraft strapped for “Airbus” CFDS type.30. Resource indictment prior to package 2.0 is (unconditional) [hga_subsys].31. HSU failures reported by the HSU via Williamsburg message type code 4Dx do not directly indict the[hsu1] or [hsu2] functional resources (hence the “NONE” entries in this table for these failures). HSUfunctional resource indictment for these failures is handled indirectly, as necessary, via the SSM = FailureWarning state of the HSU’s label 270 status word, as follows:Within the HSU, errors (failures) are classified as either fatal, essential or non--essential, depending on theiroperational impact. (”Fatal” means that one or more HSD services are unavailable and that the HSU is notallowed to continue to operate in normal mode, else it may be harmful to itself or other LRUs; “essential”means that one or more services are unavailable, but the HSU can run in normal mode without any risk ofharm to itself or other LRUs; “non--essential” means that there is no definite service unavailability, but thatthere is some kind of service degradation, and that the HSU can run in normal mode without any risk of harmto itself or other LRUs). The HSU sets its label 270 status word SSM to Failure Warning [and also asserts itsHSU Failure discrete output, and also sets its Category field to 1 (indicting) in its code 4Dx failure messages]for all current fatal errors. Depending on the HSU user data interface configuration as specified by the HSU’sCDM programming (MPDS {Ethernet or 232}, or M--ISDN, or both), the HSU may set its label 270 statusword SSM to Failure Warning for current essential errors (it will if all configured user data interfaces {one orthe other or both sets} are rendered unavailable by the essential error(s)). [The HSU also sets the HSUFailure discrete output if its label 270 status word SSM is set to Failure Warning, and sets its Category field to1 (indicting) in its code 4Dx failure messages, for all current essential errors.] The HSU does not set its labelRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--17270 status word SSM to Failure Warning [nor does it set its HSU Failure discrete output, nor does it set itsCategory field to 1 (indicting) in its code 4Dx failure messages] for any current non--essential errors.When the SDU receives HSU label 270 status words with the SSM = Failure Warning, the SDU raises theHSU Self--Declared Failure (08/0/01 or 09/0/01), and indicts the respective HSU functional resource ([hsu1]or [hsu2]).Through this indirect process, the SDU thus indicts the HSU functional resources as required for the HSU’sself--reported failures.In this table, an asterisk following the note “31” entry indicates the failures which may (depending on theHSU’s user data interface configuration) or definitely do result in HSU functional resource indictment via thisindirect process.32. These failures is not implemented in software packages 3.0 and subsequent. These failure codes is notused for any other purpose in packages 3.0 and subsequent in order to maintain compatibility with theirpre--package 3.0 usage.33. Although no functional resource is indicted for this condition, there is grave operational impact34. These failures are applicable prior to SDU Part Number 7516118--XX130/--xx140.35. These failures are applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent.36. HSU failures reported by the HSU (via Williamsburg message type code 6Dx) shall never directly indictthe [hsu] functional resource. If an HSU failure requires indictment, the SSM field will be set to FailureWarning in the label 270 status word sent from the HSU (see Commentary below for details). The SDU shallthen raise the HSU Self--Declared Failure (03/0/01), and indict the HSU functional resource. Failures whichcan cause HSU functional resource indictment via this indirect process are indicated in the table by anasterisk * next to “36” in the NOTES column.The HS--720 (supported from SDU Part Number 7516118--XX130/--xx140) provides Channel Failureinformation in the label 270 status word, in addition to the SSM Failure Warning indication. When an HSUfailure results in the loss of one or more individual HSD channels, the HSU will set the associated ChannelFailure bit(s) in the status word. The SDU shall then raise the appropriate non--indicting HSU ChannelFailure(s) (03/0/0C, 03/0/OF, 03/0/10, 03/0/11), as specified in COMMENTARYFor failures with major operational impact, the HSU will set the Category field to 1 (indicting) in thecorresponding Williamsburg failure message, will set SSM to Failure Warning in the label 270 status word,and will assert the HSU Failure discrete output. For failures with no/limited operational impact, the HSU willset the Category field to 0 (non--indicting) in the corresponding Williamsburg failure message, but will not setthe SSM to Failure Warning in the label 270 status word, and will not assert the HSU Failure discrete output.37. This failure is only generated by the Honeywell 60W HPA.38. The HP--720 60W HPA has several failures that do not map to the DISCRETES bits in the HPAMaintenance word but which do cause SSM=FW in Maintenance and the Status words. When the HP--720raises such failures, the SDU will raise this failure (04 0 0C), resulting in both failures appearing in the failurelogs.39. HP--720 failure codes 04/07 2 C0/C1/C2/C3/C4/C will never be transferred to the SDU via the HPA blocktransfer for various reasons, which are detailed in the Remarks block for the respective failure.40. Prior to SDU Part Number 7516118--XX130/--xx140, these failures shall indict the [hsu1] functionalresource, whereas for SDU Part Number 7516118--XX130/--xx140 and subsequent, these failures shall indictthe [hsu] functional resource.41. The POST/PAST failure is applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent only.42. These failures are not currently implemented in the HS--720.43. Prior to SDU Part Number 7516118--XX130/--xx140, these failures shall indict the [hsu1] functionalresource, whereas for SDU Part Number 7516118--XX130/--xx140 and subsequent, these failures is nonindicting.44. This failure code (04 0 41) is used by the HP--720 to indicate when the RF power at the HPA input is lessthan --32 dBm. In addition to transferring this failure with the label 171 manufacturer--specific status word, theHP--720 also sets DISCRETES bit 14 in the label 350 maintenance word. Since the SDU completely ignoresthis failure code and the state of bit 14, this failure code is not defined, but is reserved so that it not be usedfor anything else.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--18Failure DetailsThis section provides a further level of detail to the failure. Each failure has the following associatedinformation:DESCRIPTION : A thorough description of the fault condition. Whether stated explicitly in the followingsubsections or not, an implicit requirement for every failure is that it shall only be declared if the associatedLevel 1 equipment has been installed, as defined by the systemconfiguration straps; LRU failures and inactive buses is not declared if the associated LRU is not installed.PARAMETERS : The data parameter(s) that are required to be saved as part of the failure information. Thisdata will provide the exact nature of the error, e.g., a voltage value for a power fault.FAIL CRITERIA : The time limit or other criteria for which the fault condition must exist before it is declared afailure. The tolerance on all failure timing criteria is + 0.5 second.RECOVERY CRIT. : The time or other criteria for which a normal condition must exist before a failurecondition will be considered to have been “healed” and the current failure status removed. The tolerance onall failure timing criteria is + 0.5 second.REMARK : Any information that is important in understanding the fault condition or affect on other faultconditions that may seem important to remember.With the exception of the Level 1 code 01, the hex equivalent of the Level 1, SRU and Failure codes areadded to each title for ease of comparison.COMMENTARYFailures that are described as not being explicitly cleared, may be cleared at the next cold or factory settingsstart. Not explicitly clearing means that during the power cycle when the failure occurred, no tests on thefailed component will be carried out and thus the failure will not be cleared from the current failures list.SDU (Level 1 Code 01h)SMPM: SDU Main Processor Module (SRU Code 1)SDU H/W--S/W Compatibility Fail (01 1 81)DESCRIPTION : During POST/PAST the SMP Hardware/Software Compatibility Codes as read from the IDPROMs of each physical SRU is compared against the list of ardware/Software Compatibility Codes for eachSRU contained in the SDU LRU Header record (stored as part of the SDU software image). If a conflict isfound then a ’H/W--S/W COMPATIBILITY FAIL’ is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a fail immediatelyRECOVERY CRIT. : This failure is never explicitly cleared.REMARK :Battery Voltage Low (01 1 82)DESCRIPTION : During POST/PAST the voltage of the battery is read. If the battery voltage is below thethreshold required to maintain the contents of battery backed RAM then the test is repeated. If the secondtest also fails, then a ’BATTERY VOLTAGE LOW’ fault is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a fail immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :Watchdog Timeout Fail (01 1 83)DESCRIPTION : During POST the watchdog is interrogated to determine if the reason for the Cold Start wasthe watchdog timer not being strobed. If there is a watchdog timer reset and no other failure or PAST requestis declared then a ’WATCHDOG TIMEOUT FAIL’ fault shallbe declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into a failure immediatelyRECOVERY CRIT. : This failure is cleared immediately.REMARK : All failures and PAST requests will result in transition to the POST/PAST state via awatchdog timeout failure, however the battery backed RAM will contain an indication of thefailure cause/PAST request. Watchdog timeout fail will only be regarded as a fault when itoccurs in isolation from any other failure or PAST request.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--19Micro Boot ROM Fail (01 1 84)DESCRIPTION : During POST/PAST the validity of the Micro Boot Image in Flash is determined bycomparing a value calculated from the contents of the Micro Boot, with the stored value calculated at the timethe Micro Boot image was built. If the values differ during the firstcomparison then the calculation and the comparison is repeated. If the values still differ after the secondcomparison then a failure is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into a failure immediatelyRECOVERY CRIT. : This failure is never explicitly cleared.REMARK :EEPROM Fail (01 1 85/05)DESCRIPTION : If CM detects a corruption of EEPROM, then a Cold Start is initiated indicatingUnrecoverable Failure -- EEPROM Fail. During the resulting POST/PAST the EEPROMis non--destructively tested. If the test passes, only the CM fault is declared. If the POST/PAST test fails, it isrepeated. If both the first and second tests fail, the POST/PAST fault is declared.PARAMETERS : If this is a CM fault, an identifier indicating which section of EEPROM has failed is stored.FAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : This failure is not explicitly cleared.REMARK : After detection of EEPROM Fail, a Factory Settings start is initiated.FLASH Fail (01 1 86/06)DESCRIPTION : During POST/PAST the validity of the FLASH contents is determined by comparing achecksum value calculated from the contents of the FLASH, with the stored checksum value calculated at thetime the FLASH image was built. If no match is found during the first comparison then the comparison isrepeated. If the values differ during both the first and second comparisons then a ’FLASH FAIL’ fault isdeclared.During CM the validity of the FLASH contents is determined by periodically comparing a CRC valuecalculated from the contents of the FLASH with the stored CRC value calculated at the time the FLASHimage was built. If the values differ, a CM ’FLASH FAIL’ fault is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into a failure immediatelyRECOVERY CRIT. : This failure is never explicitly cleared.REMARK :SRAM Fail (01 1 87/07)DESCRIPTION : During POST/PAST the SRAM is tested by a method capable of detecting addressingfaults. If the test fails the first attempt, it is repeated. If both the first and second test results indicate a failurethen a ’SRAM FAIL’ is raised.During CM each location of category A and B data is tested at least once every thirtyminutes by saving the current contents, writing/reading a binary pattern, checking that the value read equalsthe value written and then restoring the original value. Should there be any variation between the two valuesthen a CM ’SRAM FAIL’ fault is declared.PARAMETERS : For the CM failure, the SRAM address where the fault occurred.FAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly cleared.REMARK :Real Time Clock Fail (01 1 88/08)DESCRIPTION : During POST/PAST tests is conducted on the Real Time Clock as appropriate to the deviceselected. Once the Real Time Clock is operating, a comparison between Real Time Clock elapsed time andthe micro processor operating speed is conducted. If any of these tests fail, they is repeated. If any of thesetests fail both the first and second attempts then a ’REAL TIME CLOCK FAIL’ fault is declared.During CM the Real Time Clock (RTC) is tested once per second to ensure it is still ticking. While in the faultstate the RTC is tested once per second, to see if the fault has cleared.PARAMETERS : For the POST/PAST case, an indication of which of the above RTC tests it was that failed isstored. For the CM tests the value shall indicate the time that it failed.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--20FAIL CRITERIA : The POST/PAST fault transitions to a failure immediately. The CM fault transitions intofailure if it persists for ten seconds or more. For the case of the gross update check, since it is not explicitlycleared, the failure will be logged ten seconds after the offendingupdate.RECOVERY CRIT. : For the POST/PAST or gross CM check the failure is not explicitly cleared. In the caseof the CM 1 second update test, this failure is cleared if the cleared condition persists for more than 10seconds.REMARK : If the POST/PAST RTC versus micro processor operating speed fault condition is found the faultmay be in either device.QUART Fail (01 1 89)DESCRIPTION : During POST/PAST the QUART is tested for asynchronous transmit and receive on allchannels, and its timer is tested against the microprocesser operating speed. If any test fails it is repeated. Asecond failure of any of the transmit/receive tests shallresult in a ’QUART FAIL’ being declared. If the timer test fails the second test the Boot software shall nothand over to the Application software, but shall initiate a Cold Start indicating Unrecoverable Failure --QUART Fail. If on a subsequent attempt the test does not fail, then on the successful Application startup aQUART Fail fault is declared.PARAMETERS : An indication of which of the above tests it was that failed is stored.FAIL CRITERIA : This fault transitions into a failure immediatelyRECOVERY CRIT. : The timer failure is cleared immediately. The transmit and receive failure is not explicitlycleared.REMARK : Note that the QUART timer failure is only logged after the problem has recovered;therefore, the information logged with the failure (e.g., date, time, power--on count, etc.) Isnot necessarily accurate.Software Error (SYSFAIL) (01 1 0A)DESCRIPTION : Any unexpected interrupt, trap or exception (other than Bus Error while accessing SIOM,Codec, or Modem during POST/PAST), or any internal software inconsistency being detected shall result in a’S/W SYS FAIL’ fault being declared (SRU Bus Error duringPOST/PAST has a separate fault for each SRU).PARAMETERS : The address of a string which gives an indication of the cause of S/W SYS FAIL (e.g.,unexpected interrupt) and a data item which helps diagnose the problem (e.g., theexception which caused the S/W SYS FAIL, or the failed address for a Bus Error trap).FAIL CRITERIA : This fault transitions into a failure immediatelyRECOVERY CRIT. : This failure transitions to normal immediatelyREMARK : A software SYS FAIL results in a Cold start. The fault will be logged after the reset. Inorder to prevent erroneous display of this event, the failure condition is immediatelyremoved from the current failures list after it has been logged. This prevents the failurecondition from appearing in multiple flight leg reports until a subsequent system reset.Flash--PSRAM Miscompare (01 1 0B)DESCRIPTION : CM shall periodically compare the copy of the SMP Application Program in SRAM (i.e.PSRAM) with the contents of Flash memory. If no match is found during the firstcomparison then the comparison is repeated. If discrepancies are found on both thefirst and second comparisons, then a Cold Start is initiated indicating UnrecoverableFailure -- Flash--PSRAM Miscompare. If the resulting POST/PAST does not result in a differentUnrecoverable Failure restart occuring (e.g. due to an SRAM Fail or a Flash Fail) then a Flash--PSRAMMiscompare fault is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : This failure is cleared immediately.REMARK : See failures (01/1/0C) and (01/1/0D) for storage of additional diagnostic information for thisfailure.Flash--PSRAM Miscompare Extension 1 (01 1 0C)DESCRIPTION : This failure is raised with the Flash--PSRAM Miscompare failure (01/1/0B) as a vehicle tostore additional diagnostic information in its parameters.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--21PARAMETERS : The first parameter holds the address in SRAM of the 32--bit longword in which the firstFlash--PSRAM Miscompare was detected. The second parameter holds the length (inbytes) of the first contiguous block of corruption.FAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : This failure is explicitly cleared immediately.REMARK :Flash--PSRAM Miscompare Extension 2 (01 1 0D)DESCRIPTION : This failure is raised with the Flash--PSRAM Miscompare failure (01/1/0B) as a vehicle tostore additional diagnostic information in its parameters.PARAMETERS : The first parameter holds the contents of the first 32--bit longword of SRAM in whichcorruption was detected. The second parameter holds the second 32--bit longword ofSRAM in which corruption was detected, unless only 4 bytes or less of corruption weredetected.FAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : This failure is cleared immediately.REMARK :<CODEC--A> SRU (SRU Code 2)Program Memory CRC Fail (01 2 81/01)DESCRIPTION : During POST/PAST and CM, a CRC is calculated on Program memory and comparedagainst the stored CRC in the memory being tested.PARAMETERS : None for POST/PAST.Event code (001) for CM.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK :Timing Generator Fail (01 2 87/07)DESCRIPTION : During POST/PAST and CM, a timing generator (serial input/output) test is performed. Thisfault is declared if the codec detects loss of timing generatorsynchronization.PARAMETERS : None for POST/PAST.Event code (006) for CM.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : The codec declares a timing generator failure when the audio samples are not clocked into andout of the DSP’s serial port.Dual Port RAM Fail Codec Side (01 2 88)DESCRIPTION : During POST/PAST, a Dual Port RAM test is performed. The test is a nondestructive RAMtest.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK :Program Memory W/R Fail (01 2 8A/0A)DESCRIPTION : During POST/PAST and CM, a Program Memory (RAM) test is performed. This test is anon--destructive RAM test.PARAMETERS : None for POST/PAST.For CM the following code applies:(00B) = Program Memory W/R failure.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--22DSP Internal Memory W/R Fail (01 2 8B)DESCRIPTION : During POST/PAST, a DSP Internal Memory (RAM) test is performed. This test is anon--destructive RAM test.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK :DSP Comprehensive Fail (01 2 8C/0C)DESCRIPTION : During POST/PAST and CM, a DSP comprehensive/instruction test is performed. Arepresentative sample of the DSP instructions is tested. These tests isperformed such that they do not interfere with other operations.During CM, a DSP Internal Memory (RAM) test is performed. This test is anon--invasive RAM test.PARAMETERS : None for POST/PAST.For CM the following codes apply:(00C) = DSP Internal Memory W/R failure,(00D) = DSP Instruction failure.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK :Health Count Update (01 2 0D)DESCRIPTION : During CM <CODEC--A> is supplied with a value (Codec Health Count) once per secondand must echo it back within the next second. Should the Codec fail to echo thevalue within the time limit or echo an incorrect value then a ’<CODEC--A> Health CountUpdate’ fault is declared. Once faulted, the test is not continued.PARAMETERS : Codec Health Count Echo, Codec Health CountFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : Should this failure occur, the Codec will be held in reset until the next power cycle.Dual Port RAM Fail SMPM Side (01 2 8E)DESCRIPTION : During POST/PAST the Dual Port RAM of <CODEC--A> is tested for read and write accesswhile the codec is held in reset. If any value read from the DPR differs from thevalue written, then the test is repeated. A ’<CODEC--A> Dual Port RAM SMPM SideFail’ fault is declared if, during the second test, any value read from the DPR differsfrom the value written, and if ID Prom information relating to this SRU has successfullybeen received.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : Should this failure occur, the Codec will be held in reset until the next power cycle.BusError(01290)DESCRIPTION : If a bus error occurs during POST/PAST while accessing <CODEC--A> then this test isrepeated. If a bus error occurs during the second test, and ID Prom information relating to this SRU hassuccessfully been received, then a ’<CODEC--A> Bus Error’ fault isdeclared.PARAMETERS : The address where the bus error occured.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : Should this failure occur, the Codec will be held in reset. If a Bus Error occurs duringnormal operation, a S/W SYSFAIL failure is raised whatever the failed address.Self Test Misoperation (01 2 91)DESCRIPTION : During POST/PAST <CODEC--A> is commanded to perform a self--test. Should the Codecfail to return a bit response within 2 seconds then a ’<CODEC--A> Self TestRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--23Misoperation’ fault is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : This failure occuring, might indicate software download to the Codec had beenunsuccessful. Codec Self test is a part of the Codec booting up activity, ie it will be doneimmediately after code download and before any other commands are sent to the Codec.Communication Problem (01 2 12)DESCRIPTION : This fault is declared if the Communication across the Dual Port Ram interface to the Codecbecomes inconsistent.PARAMETERS : An enumeration of the possible cause is stored.FAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : An example would be the command buffer to the Codec filling up, indicating the Codec was notservicing the buffer.ST Bus Audio Loopback Fail (01 2 94)DESCRIPTION : During POST/PAST, the codec is tested.PARAMETERS : Param 1 : Actual DTMF digit received, or zero for no DTMF digit receivedParam 2 : Expected DTMF digitFAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK :SW Download Fail (01 2 95)DESCRIPTION : This fault is declared if the codec does not behave as expected at any point during thedownloading of its code.PARAMETERS : Parameter 1Bits 31--28 Failure Type1 Not used.2 Timeout waiting for codec to clear buffer full flag.3 Response from codec is unexpected.4 The codec has not sent a codec ready event at startup.When the failure type is set to 3 then the following additional bits of parameter 1 togetherwith parameter 2 are also given.Bits 27--24 Identity of the code segment read from the codec.Bits 23--20 Last block flag read from the codec.Bits 15--0 Block number read from the codec.Parameter 2Bits 27--24 Identity of the code segment passed to the codec.Bits 23--20 Last block flag passed to the codec.Bits 15--0 Block number passed to the codec.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : If at startup the SMP is not able to load the codec code into the codec this failure is raised withparameters indicating at what point during the download the problem occured.Codec B SRU (SRU Code 3)As for Codec A above except substitute SRU code 3 for code 2 and <CODEC--B> for <CODEC--A>SIOM: SDU Input/Output Module (Exclusive To SIOM) (SRU Code 4)A429 XMTR Loop--Back To Other SDU Fail (01 4 81)DESCRIPTION : During POST/PAST the A429 XMTR transmitter is tested by using the BITE ARINC loopback receiver. An ’A429 XMTR Loop--Back To Other SDU Fail’ fault is declared if, after two consecutiveattempts, no messages are received via the loop back input. This fault shall only be raised after theconfiguration straps have been read and the pertinentRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--24interface has been found to be wired.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :A429 XMTR Loop--Back To CFDS Fail (01 4 82)DESCRIPTION : During POST/PAST the A429 XMTR transmitter is tested by using the BITE ARINC loopback receiver. An ’A429 XMTR Loop--Back To CFDS Fail’ fault is declared if, after two consecutive attempts,no messages are received via the loop back input. This fault shall only be raised after the configuration strapshave been read and the pertinentinterface has been found to be wired.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :A429 XMTR Loop--Back To ADL Fail (01 4 83)DESCRIPTION : During POST/PAST the A429 XMTR transmitter is tested by using the BITE ARINC loopback receiver. An ’A429 XMTR Loop--Back To ADL Fail’ fault is declared if, after two consecutive attempts, nomessages are received via the loop back input.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :A429 XMTR Loop--Back To PDL Fail (01 4 84)DESCRIPTION : During POST/PAST the A429 XMTR transmitter is tested by using the BITE ARINC loopback receiver. An ’A429 XMTR Loop--Back To PDL Fail’ fault is declared if, after two consecutive attempts, nomessages are received via the loop back input.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :A429 XMTR Loop--Back To (C)MUs Fail (01 4 85)DESCRIPTION : During POST/PAST the A429 XMTR transmitter is tested by using the BITE ARINC loopback receiver. An ’A429 XMTR Loop--Back To (C)MUs Fail’ fault is declared if, after two attempts, nomessages are received via the loop back input. This fault shall only be raised after the configuration strapshave been read and at least one CMU has beenfound to be wired.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :A429 XMTR Loop--Back To SCDUs Fail (01 4 86)DESCRIPTION : During POST/PAST the A429 XMTR transmitter is tested by using the BITE ARINC loopback receiver. An ’A429 XMTR Loop--Back To SCDUs Fail’ fault is declared if, after two consecutive attempts,no messages are received via the loop back input. This fault shall only be raised after the configuration strapshave been read and at least oneSCDU has been found to be wired, as specified in section 3.2.4.19.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--25A429 XMTR Loop--Back To Multi--Cntrl Fail (01 4 87)DESCRIPTION : During POST/PAST the A429 XMTR transmitter is tested by using the BITE ARINC loopback receiver. An ’A429 XMTR Loop--Back To Multi--Cntrl Fail’ fault is declared if, after two consecutiveattempts, no messages are received via the loop back input.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :A429 XMTR Loop--Back To RMP/CAP Fail (01 4 89)DESCRIPTION : This failure is not implemented since Boeing and Airbus have not implemented CAP/RMP. Ifimplemented, then during POST/PAST the A429 XMTR transmitter is tested by using the BITE ARINC loopback receiver. If implemented, an ’A429 XMTRLoop--Back To RMP/CAP Fail’ fault is declared if, after two consecutive attempts, nomessages are received via the loop back input.PARAMETERS : NoneFAIL CRITERIA : If implemented, this fault transitions into failure immediatelyRECOVERY CRIT. : If implemented, this failure is never explicitly clearedREMARK : This failure is only pertinent if software is in place to communicate operational information to theRMP or CAP on this output; if no such software exists (e.g., in early builds), thisfailure should be ignored.A429 XMTR Loop--Back SNU/CPDF (01 4 8A)DESCRIPTION : During POST/PAST the A429 XMTR transmitter is tested by using the BITE ARINC loopback receiver. An ’A429 XMTR Loop--Back To SNU/CPDF Fail’ fault is declared if, after two consecutiveattempts, no messages are received via the loop back input.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly clearedREMARK : This failure is only pertinent if an SNU/CPDF is fitted; if an SNU/CPDF is not fitted, this failureshould be ignored.A429 XMTR Loop--Back HSU1 (01 4 8B)DESCRIPTION : During POST/PAST the A429 XMTR transmitter is tested by using the BITE ARINC loopback receiver. An ’A429 XMTR Loop--Back To HSU Fail’ fault is declared if, after two consecutive attempts,no messages are received via the loop back input.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly clearedREMARK : This failure is only pertinent if HSU1 is fitted; if HSU1 is not fitted, this failure should be ignored.A429 XMTR Loop--Back HSU2 (01 4 8C)Same as for 01 4 8B except substitute “HSU2” for “HSU1”. Only applicable prior to SDU Part Number7516118--XX130/--xx140.SIOM Bus Error (01 4 AB)DESCRIPTION : During POST/PAST all SIOM devices is tested for read write access. An ’SIOM Bus Error’is declared if any of the tests result in a bus error.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : If a Bus Error occurs during normal operation, a S/W SYSFAIL failure is raised whatever the failedaddress.A429 Tx To Other SDU Buffer Full (01 4 2C)DESCRIPTION : The ARINC 429 Hardware is not accepting data for transmission, and the Tx buffer hasbecome full.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--26PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : This would indicate that a specific ASIC had failed.A429 Tx To CFDS Buffer Full (01 4 2D)DESCRIPTION : The ARINC 429 Hardware is not accepting data for transmission, and the Tx buffer hasbecome full.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : This would indicate that a specific ASIC had failed.A429 Tx To ADL Buffer Full (01 4 2E)DESCRIPTION : The ARINC 429 Hardware is not accepting data for transmission, and the Tx buffer hasbecome full.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : This would indicate that a specific ASIC had failed.A429 Tx To PDL Buffer Full (01 4 2F)DESCRIPTION : The ARINC 429 Hardware is not accepting data for transmission, and the Tx buffer hasbecome full.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : This would indicate that a specific ASIC had failed.A429 Tx To (C)MUs Buffer Full (01 4 30)DESCRIPTION : The ARINC 429 Hardware is not accepting data for transmission, and the Tx buffer hasbecome full.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : This would indicate that a specific ASIC had failed.A429 Tx To SCDUs Buffer Full (01 4 31)DESCRIPTION : The ARINC 429 Hardware is not accepting data for transmission, and the Tx buffer hasbecome full.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : This would indicate that a specific ASIC had failed.A429 Tx To MULTI_CTRL Buffer Full (01 4 32)DESCRIPTION : The ARINC 429 Hardware is not accepting data for transmission, and the Tx buffer hasbecome full.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : This would indicate that a specific ASIC had failed.A429 Tx To RMP/CAP Buffer Full (01 4 34)DESCRIPTION : The ARINC 429 Hardware is not accepting data for transmission, and the Tx buffer hasbecome full.PARAMETERS : NoneRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--27FAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : This would indicate that a specific ASIC had failed.A429 Tx To SNU/CPDF Buffer Full (01 4 35)DESCRIPTION : The ARINC 429 Hardware is not accepting data for transmission, and the Tx buffer hasbecome full.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : This would indicate that a specific ASIC had failed.A429 Tx To HSU1 Buffer Full (01 4 36)DESCRIPTION : The ARINC 429 Hardware is not accepting data for transmission, and the Tx buffer hasbecome full.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : This would indicate that a specific ASIC had failed.A429 Tx To HSU2 Buffer Full (01 4 37)Same as for 01 4 36 except substitute “HSU2” for “HSU1”. Only applicable prior to SDU Part Number7516118--XX130/--xx140.SIOM Interrupt Fail (01 4 BC)DESCRIPTION : The SIOM is forced to interrupt the SMPM; if this does not occur within the expected time,then the attempt to interrupt the SMPM is repeated. If this does not occur within the expected time during thesecond attempt then a fault is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : Without this interrupt, no ARINC communication can take place.IRS ASIC Matching Problem (01 4 3D)DESCRIPTION : This fault is declared if any unexpected data is received whilst the label matching algorithmis enabled.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is not explicitly cleared in the unexpected label match caseREMARK :SMDM1: SDU Modem Module #1 (SRU Code 05)<MODEM--1> Processor Fail (01 5 81)DESCRIPTION : A subset of the DSP56300 processor instruction set is tested, along with associatedcondition flags. Following the instruction set test, the processor internal memory is tested. If either of thesetests fail, the Processor fail condition is reported to the SMP. If this test orany other Modem Start--up Built--in Test (SBIT) fails during POST/PAST, SBIT is requested a second time. Ifthis test fails on the second attempt, a failure is raised.PARAMETERS : Parameter 1 bit 1 -- Set when Internal Memory test Failed bit 0 -- Set when Instruction Settest FailedFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : It is noteworthy that not all of the DSP56300 instructions are tested, as this would take aninordinate time to complete. The subset of instructions chosen are deemed to test all addressing modes ofthe processor, and all of the condition flags, thus exercising theRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--28processor in the most time efficient manner.<MODEM--1> Program CRC Fail (01 5 84/04)DESCRIPTION : A Cyclic Redundancy Check is performed on the external program memory segments, tocheck for program corruption. The CRC algorithm used is that described in the CCITT Redbookrecommendation X.25, Section 3.2.1.2.7. The Continuous Monitoring fault is raised only if the CRC checkfails twice within a 10 second period. This fault shall only transition into failure if it satisfies the conditionsspecified in section 4.3.6.7. If this test or any other Modem Start--up Built--in Test (SBIT) fails duringPOST/PAST, SBIT is requested a second time. If this test fails on the second attempt, a failure is raised.PARAMETERS : Parameter 1 #bit 28 -- 31 Corrupted Segment Numberbit 24 -- 27 Unused*bit 0 -- 23 Start Address of Corrupt DataParameter 2 *bit 24 -- 31 Number of Corrupt Words (FFx if >= FFx)*bit 0 -- 23 Contents of First Corrupt Address’*’ -- These diagnostics shall only provided if there is enough available memory in themodem to store a ’shadow’ copy of the program segments to check against.’#’ -- This information shall only be provided by a POST/PAST test failure, as the CM testhas no knowledge of the segment which it is currently checking.FAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : The program segment CRC values against which the modem checks will have beencalculated by the code build tools, and inserted into the program segment memory as the last entry. If enoughfree memory exists in the modem, a ’shadow’ copy of the program segments is stored, enabling a word byword comparison to be made, and further diagnostics provided to the main processor for inclusion in FailureParameter words.<MODEM--1> Modem To RFM Interface Fail (01 5 0A)DESCRIPTION : The Modem/RFM Interface is continuously monitored to ensure that the I and Q samplesare transmitted under interrupt. If no samples are transmitted for 100ms whilst the TxChannel is active, the modem reports a failure to the SMP via the DPR interface. This fault shall onlytransition into failure if it satisfies the conditions specified in section 4.3.6.7.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :<MODEM--1> Timer Interrupt Fail (01 5 8B)DESCRIPTION : The internal timers 0 and 1 (both 128Hz) and the IRQB input are tested on the Modemprocessor. The TIO0 external input (10.08MHz) is implicitly tested by testing the internaltimers 0 and 1. IRQB is a general purpose 1KHz timer signal generated by external hardware logic. Thepurpose of this test is twofold, as follows;1. To verify that the internal timers 0 and 1 are present.2. To verify that the frequency of the external IRQB input signal is accurate to 1000 partsper million.If this test or any other Modem Start--up Built--in Test (SBIT) fails during POST/PAST, SBITis requested a second time. If this test fails on the second attempt, a failure israised.PARAMETERS : Parameter 1 bit 2 IRQB Failurebit 1 Timer 1 Failurebit 0 Timer 0 FailureFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : The full details on this test are available in section 3.4.6 of the MDM DDD. The following is a briefoutline of the test method. Depending on which timer is under test, interrupts should be generated at a knownfrequency. The processor performs a count in background,following the first detected interrupt. The count is checked following the next interrupt, andshould be within a known range. The count is reset for the next count sequence. If theRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--29count value is out of range a failure is reported to the SMP in the DPR interface.<MODEM--1> External Memory Fail (01 5 8E)DESCRIPTION : The Modem Processor’s external Y--RAM is tested. External X--RAM is the DPR and istested elsewhere. The external P--RAM is tested by the CRC test. The test is performed bywriting words with alternating bit patterns (AAAAAAx, 555555x), and also with incrementing bit patterns to allY--RAM locations, reading the values back and checking for errors. If this test or any other Modem Start--upBuilt--in Test (SBIT) fails during POST/PAST, SBIT is requested a second time. If this test fails on the secondattempt, a failure is raised.PARAMETERS : Parameter 1 bit 28 -- 31 Test Type (’1’ -- Incrementing, ’A’ or ’5’ -- Alternating)bit 24 -- 27 Unusedbit 0 -- 23 Address of First Location which failed testFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :<MODEM--1> Modem DPR Fail (01 5 91)DESCRIPTION : The DPR is decoded as X--RAM space in the modem address space. The ModemProcessor tests each location by writing alternating bit patterns (AAAAx, 5555x), and alsowith incrementing bit patterns, reading them back and checking for errors. If this test or any other ModemStart--up Built--in Test (SBIT) fails during POST/PAST, SBIT is requested a second time. If this test fails onthe second attempt, a failure is raised.PARAMETERS : Parameter 1 bit 28 -- 31 Test Type (’1’ -- Incrementing, ’A’ or ’5’ -- Alternating)bit 24 -- 27 Unusedbit 0 -- 23 Address of First Location which failed testFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : As the DPR is the mechanism for communications between the Modem Processor and the SMP,and the DPR test is destructive, the SMP is not allowed access to the DPR until theend of DPR testing. The modem indicates to the SMP that the test is finished by interrupting the SMP.<MODEM--1> SMPM Side DPR Fail (01 5 95)DESCRIPTION : During POST/PAST the Dual Port RAM of <MODEM--1> is tested by the SMP for read andwrite access. The modem is held in reset during the test. If any value read from the DPR differs from thevalue written, the test is repeated. If the test fails on the second attempt, and Id Prom information from theassociated physical SRU has been received successfully, a ’<MODEM--1> SMPM Side DPR Fail’ fault isdeclared.PARAMETERS : The address in the DPR where the error occured.FAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :<MODEM--1> SW Download Fail (01 5 16)DESCRIPTION : During POST/PAST the modem code is downloaded to <MODEM--1>. A ’<MODEM--1> SWDownload Fail’ fault is declared if any errors occur during the downloadprocess.PARAMETERS : Parameter 1 bit 28 -- 31 Segment Idbit 24 -- 27 Destination Memorybit 20 -- 23 SRU Identitybit 4 -- 19 Sent Block Numberbit 3 Last Block of Segment Flagbit 2 Last Segment Flagbit 1 SMPM to Modem Buffer Full Flagbit 0 if set, indicates a timeout errorParameter 2 bit 28 -- 31 Response Block Numberbit 27 Set if last Block of Segmentbit 26 Set if last SegmentRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--30bit 25 Buffer Full Flag (Set if block processed okay)bit 1 -- 24 Unusedbit0SetiffailureoccuredFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : Refer to Section 3.2 of the SMP DDD for further details of diagnostic parameters.<MODEM--1> Health Count Update Fail (01 5 17)DESCRIPTION : During CM <MODEM--1> is supplied with three values (Modem Health Counts) onceper second. Each Modem virtual processor must echo its Health Count back within the nextsecond. Should a Modem virtual processor fail to echo the value within the time limit orecho an incorrect value then a ’<MODEM--1> Health Count Update’ fault is declared.This fault shall only transition into failure if it satisfies the conditions specified in section4.3.6.7.Once faulted, the test is not continued for the failed Modem virtual Processor.PARAMETERS : Parameter 1 bit 2 Modem Decoder Process Failbit 1 Modem Receiver Process Failbit 0 Modem Controller Process FailFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :<MODEM--1> Bus Error (01 5 99)DESCRIPTION : During POST/PAST if a bus error occurs during the Dual Port RAM test on <MODEM--1>,the test is repeated. If the test fails on the second attempt. and Id Prom information relating to this physicalSRU has been received successfully, then a ’<MODEM--1> Bus Error’ fault is declared.PARAMETERS : The address where the bus error occuredFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : If a Bus Error occurs during normal operation, a S/W SYSFAIL failure is raised whatever the failedaddress.<MODEM--1> Self Test Misoperation (01 5 9A)DESCRIPTION : During POST/PAST <MODEM--1> is commanded to perform a self--test. Should the modemfail to return a bit response within 1 second or any Modem Start--up Built--in Test (SBIT) fails duringPOST/PAST, SBIT is requested a second time. Should the modemfail to return a bit response within 1 second on the second attempt, a ’<MODEM--1> Self Test Misoperation’fault is declared.During a Factory Setting Start, and once every 24 hours, <MODEM--1> is commanded to perform the I/Qcalibration of the selected RFM channels. Should the modem fail to return a response to the I/Q calibrationrequest within 30 seconds or any initial calibration fails, <MODEM--1> is commanded to repeat thecalibration. Should the modem fail to return a response to the repeated I/Q calibration request within 30seconds, a ’<MODEM--1> Self Test Misoperation’ fault is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :<MODEM--1> Software Fail (01 5 1B)DESCRIPTION : If the modem detects a fatal internal software problem during normal operation, this fault isdeclared.PARAMETERS :FAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :<MODEM--1> Communication Problem (01 5 1C)RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--31DESCRIPTION : If the SMP detects a problem with communication to the Modem through the DPR (such asit filling up with commands from the SMP, receiving an unknown Modem Event orResponse, or receiving a ’Last SMP Command Invalid’ Event), then this fault is declared.PARAMETERS : Parameter 1 bit 31 SMP to Modem DPR Fullbit 30 Unknown/Invalid Modem Event receivedbit 29 Last SMP (to Modem) Command Invalidbit 0 -- 23 Offending Command/Event ValueFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :<Modem--1> RFM SSI Loopback Fail (01 5 9E)DESCRIPTION : During POST/PAST, the modem and its connection to the RFM is tested.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :SMDM2:SDU Modem Module #2 (SRU Code 6)As for SMDM1 except substitute SRU code 6 for code 5 and <MODEM--2> for <MODEM--1>.SMDM3:SDU Modem Module #3 (SRU Code 7)As for SMDM1 except substitute SRU code 7 for code 5 and <MODEM--3> for <MODEM--1>.SRFM: SDU Radio Frequency Module (SRU Code 8)<SRFM> RF Synth Chan 1 Lock Detect Fail (01 8 8E/0E)DESCRIPTION : During POST/PAST the RFM Synth Chan 1 lock is tested. A ’RF Synth Chan 1 Lock DetectFail’ fault is declared if the synthesizer lock discrete indicates a loss of lock after 2 succesive tests.During CM the RFM Synth Chan 1 lock is tested at least once every second, and after each time it is tuned.An ’RF Synth Chan 1 Lock Detect Fail’ fault is declared if the synthesizer lock discrete indicates a loss oflock.While in the fault state the RFM Synth Chan 1 lock is tested at least once every second. The ’RF Synth Chan1 Lock Detect Fail’ fault is cleared if the synthesizer lock discrete indicates lock has been regained.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure if it persists for 3 seconds or more.RECOVERY CRIT. : This failure is cleared immediatelyREMARK :<SRFM> RF Synth Chan 2 Lock Detect Fail (01 8 90/10)As RF Synth Chan 1 Lock Detect Fail except substitute ’Chan 2’ for ’Chan 1’.<SRFM> RF Synth Chan 3 Lock Detect Fail (01 8 92/12)As RF Synth Chan 1 Lock Detect Fail except substitute Chan 3 for ’Chan 1’.<SRFM> RF Synth Chan 4 Lock Detect Fail (01 8 96/16)As RF Synth Chan 1 Lock Detect Fail except substitute ’Chan 4’ for ’Chan 1’.<SRFM> RF Synth Chan 5 Lock Detect Fail (01 8 97/17)As RF Synth Chan 1 Lock Detect Fail except substitute ’Chan 5’ for ’Chan 1’.<SRFM> RF Synth Chan 6 Lock Detect Fail (01 8 98/18)As RF Synth Chan 1 Lock Detect Fail except substitute ’Chan 6’ for ’Chan 1’.<SRFM> RF Synth Chan 7 Lock Detect Fail (01 8 99/19)As RF Synth Chan 1 Lock Detect Fail except substitute ’Chan 7’ for ’Chan 1’.<SRFM> RF Synth Chan 8 Lock Detect Fail (01 8 9A/1A)RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--32As RF Synth Chan 1 Lock Detect Fail except substitute ’Chan 8’ for ’Chan 1’.<SRFM> RF Synth TX Block PLO Lock Detect Fail (01 8 9B/1B)As RF Synth Chan 1 Lock Detect Fail except substitute ’TX Block PLO’ for ’Chan 1’.<SRFM> RF Synth RX Block PLO Lock Detect Fail (01 8 9C/1C)As RF Synth Chan 1 Lock Detect Fail except substitute ’RX Block PLO’ for ’Chan 1’.<SRFM> RF Synth RX Channel PLO Lock Detect Fail (01 8 9D/1D)As RF Synth Chan 1 Lock Detect Fail except substitute ’RX Channel PLO’ for ’Chan 1’.<SRFM> RF Synth TX Doppler PLO Lock Detect Fail (01 8 9E/1E)DESCRIPTION : During POST/PAST the RF Synth TX Doppler PLO lock is tested. A ’RF Synth TX DopplerPLO Lock Detect Fail’ fault is declared if the synthesizer lock discreteindicates a loss of lock after 2 succesive tests.During CM the RF Synth TX Doppler PLO lock is tested at least once every second, and after each time it istuned. An ’RF Synth TX Doppler PLO Lock Detect Fail’ fault is declared if the synthesizer lock discreteindicates a loss of lock.While in the fault state the RF Synth TX Doppler PLO lock is tested at least once every second. The ’RFSynth TX Doppler PLO Lock Detect Fail’ fault is cleared if the synthesizer lock discrete indicates lock hasbeen regained.PARAMETERS : bit 0: Failure Reference Lockbit 1: Failure Main LockFAIL CRITERIA : This fault transitions into failure if it persists for 3 seconds or more.RECOVERY CRIT. : This failure is cleared immediatelyREMARK :<SRFM> RFM Chan 1 L--Band Loop--back (TX) Fail (01 8 A0)DESCRIPTION : During POST/PAST, the RFM channel is tested. This fault is raised if the LNA Continuitytests (D8--DA 0 81) for all installed LNAs have passed.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :<SRFM> RFM Chan 1 L--Band Loop--back (RX) Fail (01 8 A1)DESCRIPTION : During POST/PAST, the RFM channel is tested. This fault is raised if the LNA Continuitytests (D8--DA 0 81) for all installed LNAs have passed.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :<SRFM> RFM Chan 2 L--Band Loop--back (TX) Fail (01 8 A2)As RFM Chan 1 L--Band Loop--back (TX) Fail except substitute ’Chan 2’ for ’Chan 1’.<SRFM> RFM Chan 2 L--Band Loop--back (RX) Fail (01 8 A3)As RFM Chan 1 L--Band Loop--back (RX) Fail except substitute ’Chan 2’ for ’Chan 1’.<SRFM> RFM Chan 3 L--Band Loop--back (TX) Fail (01 8 A4)As RFM Chan 1 L--Band Loop--back (TX) Fail except substitute ’Chan 3’ for ’Chan 1’.<SRFM> RFM Chan 3 L--Band Loop--back (RX) Fail (01 8 A5)As RFM Chan 1 L--Band Loop--back (RX) Fail except substitute ’Chan 3’ for ’Chan 1’.<SRFM> RFM Chan 4 L--Band Loop--back (TX) Fail (01 8 A6)As RFM Chan 1 L--Band Loop--back (TX) Fail except substitute ’Chan 4’ for ’Chan 1’.<SRFM> RFM Chan 4 L--Band Loop--back (RX) Fail (01 8 A7)RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--33As RFM Chan 1 L--Band Loop--back (RX) Fail except substitute ’Chan 4’ for ’Chan 1’.<SRFM> RFM Chan 5 L--Band Loop--back (TX) Fail (01 8 A8)As RFM Chan 1 L--Band Loop--back (TX) Fail except substitute ’Chan 5’ for ’Chan 1’.<SRFM> RFM Chan 5 L--Band Loop--back (RX) Fail (01 8 A9)As RFM Chan 1 L--Band Loop--back (RX) Fail except substitute ’Chan 5’ for ’Chan 1’.<SRFM> RFM Chan 6 L--Band Loop--back (TX) Fail (01 8 AA)As RFM Chan 1 L--Band Loop--back (TX) Fail except substitute ’Chan 6’ for ’Chan 1’.<SRFM> RFM Chan 6 L--Band Loop--back (RX) Fail (01 8 AB)As RFM Chan 1 L--Band Loop--back (RX) Fail except substitute ’Chan 6’ for ’Chan 1’.<SRFM> RFM Chan 7 L--Band Loop--back (TX) Fail (01 8 AC)As RFM Chan 1 L--Band Loop--back (TX) Fail except substitute ’Chan 7’ for ’Chan 1’.<SRFM> RFM Chan 7 L--Band Loop--back (RX) Fail (01 8 AD)As RFM Chan 1 L--Band Loop--back (RX) Fail except substitute ’Chan 7’ for ’Chan 1’.<SRFM> RFM Chan 8 L--Band Loop--back (TX) Fail (01 8 AE)As RFM Chan 1 L--Band Loop--back (TX) Fail except substitute ’Chan 8’ for ’Chan 1’.<SRFM> RFM Chan 8 L--Band Loop--back (RX) Fail (01 8 AF)As RFM Chan 1 L--Band Loop--back (RX) Fail except substitute ’Chan 8’ for ’Chan 1’.RFM Chan 1 TX Calibration Error (01 8 30)DESCRIPTION : During a Factory Setting Start, and once every 24 hours, RFM channel 1 is calibrated in TXfor power variation over the frequency range. This fault is declared if the RFM channel cannot achieve thecommanded frequency or power setting.PARAMETERS : Param 1 : Bit 0 1 = Lock error during RFM Synth tuningBit 16 1 = Back off error during power settingParam 2 : (used only if there was an error during power setting)0 = Low power setting not achieved1 = High power setting not achieved.FAIL CRITERIA : This fault transitions to failure immediatelyRECOVERY CRIT. : This failure is not explicitly clearedREMARK :RFM Chan 2 TX Calibration Error (01 8 31)Same as RFM Chan 1 TX Calibration ErrorRFM Chan 3 TX Calibration Error (01 8 32)Same as RFM Chan 1 TX Calibration ErrorRFM Chan 4 TX Calibration Error (01 8 33)Same as RFM Chan 1 TX Calibration Error except substitute chan 4 for chan 1RFM Chan 5 TX Calibration Error (01 8 34)Same as RFM Chan 1 TX Calibration Error except substitute chan 5 for chan 1RFM Chan 6 TX Calibration Error (01 8 35)Same as RFM Chan 1 TX Calibration Error except substitute chan 6 for chan 1RFM Chan 7 TX Calibration Error (01 8 36)Same as RFM Chan 1 TX Calibration Error except substitute chan 7 for chan 1RFM Chan 8 TX Calibration Error (01 8 37)Same as RFM Chan 1 TX Calibration Error except substitute chan 8 for chan 1RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--34RFM Chan 1 RX Calibration Error (01 8 38)DESCRIPTION : During a Factory Setting Start, and once every 24 hours, RFM channel 1 is calibrated in RXfor power variation over the frequency range. This fault is declared if the RFM channel cannot achieve thecommanded frequency or if the incoming power is out of range.PARAMETERS : Param 1 : Bit 0 1 = Lock error during RFM Synth tuningBit 16 1 = Incoming ADC power out of rangeParam 2 : (used only if power was out of range)Measured incoming power (16 bits, tenths of dB with respect to Full Scale (dBFS))FAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :RFM Chan 2 RX Calibration Error (01 8 39)Same as RFM Chan 1 RX Calibration Error except substitute chan 2 for chan 1RFM Chan 3 RX Calibration Error (01 8 3A)Same as RFM Chan 1 RX Calibration Error except substitute chan 3 for chan 1RFM Chan 4 RX Calibration Error (01 8 3B)Same as RFM Chan 1 RX Calibration Error except substitute chan 4 for chan 1RFM Chan 5 RX Calibration Error (01 8 3C)Same as RFM Chan 1 RX Calibration Error except substitute chan 5 for chan 1RFM Chan 6 RX Calibration Error (01 8 3D)Same as RFM Chan 1 RX Calibration Error except substitute chan 6 for chan 1RFM Chan 7 RX Calibration Error (01 8 3E)Same as RFM Chan 1 RX Calibration Error except substitute chan 7 for chan 1RFM Chan 8 RX Calibration Error (01 8 3F)Same as RFM Chan 1 RX Calibration Error except substitute chan 8 for chan 1RFM Chan 1 AGC Tellback Fail (01 8 C0/40)DESCRIPTION : This failure (and failures 01 8 C1/41 through 01 8 C8/48, which reference this section) isonly implemented in software packages prior to 3.0. During POST/PAST following programming and duringCM at a rate of 1 Hz the RFM channel 1 AGC value is checked to ensure that it lies within 5 dB of theprogrammed value. The fault is declared if, after two attempts, the programmed value has not been achieved.The POST/PAST fault is not raised if a factory setting restart has been performed.COMMENTARYA wide tolerance range has been chosen as the tellback is intended as a grossindication that the command has been received at the RFM rather than an accuratemeasure of the gain value.The POST/PAST fault is not raised following a factory setting restart as the channelAGC calibration will not have been performed.PARAMETERS : Param 1 : Expected AGC value in units of 1/10 dB.Param 2 : Actual AGC value in units of 1/10 dB.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK :RFM Chan 2 AGC Tellback Fail (01 8 C1/41)Same as RFM Chan 1 AGC Fail except substitute chan 2 for chan 1.RFM Chan 3 AGC Tellback Fail (01 8 C2/42)Same as RFM Chan 1 AGC Fail except substitute chan 3 for chan 1.RFM Chan 4 AGC Tellback Fail (01 8 C3/43)Same as RFM Chan 1 AGC Fail except substitute chan 4 for chan 1.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--35RFM Chan 5 AGC Tellback Fail (01 8 C4/44)Same as RFM Chan 1 AGC Fail except substitute chan 5 for chan 1.RFM Chan 6 AGC Tellback Fail (01 8 C5/45)Same as RFM Chan 1 AGC Fail except substitute chan 6 for chan 1.RFM Chan 7 AGC Tellback Fail (01 8 C6/46)Same as RFM Chan 1 AGC Fail except substitute chan 7 for chan 1.RFM Chan 8 AGC Tellback Fail (01 8 C7/47)Same as RFM Chan 1 AGC Fail except substitute chan 8 for chan 1.RFM Block AGC Tellback Fail (01 8 C8/48)As RFM Chan1 AGC Fail except substitute ’Block’ for ’Channel 1’.I/Q Calibration Fail (01 8 C9)DESCRIPTION : During a Factory Setting Start, and once every 24 hours, I/Q calibration is performed on allRFM transmit and receive channels to compensate for errors introduced by the quadrature sections of thehardware. If the modem controlling the calibration of a transmit/receive channel pair reports a failure tocalibrate or fails to respond to the SMP within 30 seconds, then it is commanded to repeat the calibration.Should the Modem report a failure to the repeated calibration request, an ’I/Q Calibration Fail’ fault isdeclared.PARAMETERS : Param 1 : 1 = Power level insufficient for I/Q Calibration2 = RFM channels have failed to converge on a resultParam 2 : Bit 0--15 RFM Transmit Channel IdBit 16--31 RFM Receive Channel IdFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :RFM Chan 1 AGC Calibration Error (01 8 D0)DESCRIPTION : During a Factory Setting Start, and once every 24 hours, RFM channel 1 AGC is calibratedfor DAC and ADC values over a variable gain range (the default being a rangeof 5 to 35 dB). Prior to calibrating the channel AGC, the block AGC is adjusted from an initial 0 dB gain suchthat the power level as measured at the modem ADC is less than --10 dB relative to full scale, with thechannel AGC at 35 dB gain. This fault is declared if the block AGC cannot be adjusted sufficiently to achievethe required ADC power level threshold, or if the initial value of the measured ADC power with the channelAGC at 35 dB gain and the block AGC at 0 dB gain is below --30 dB relative to full scale.PARAMETERS : Param 1 : Final modem ADC power level in units of 1/10 dB relative to full scaleParam 2 : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :RFM Chan 2 AGC Calibration Error (01 8 D1)Same as RFM Chan 1 AGC Calibration Error except substitute chan 2 for chan 1RFM Chan 3 AGC Calibration Error (01 8 D2)Same as RFM Chan 1 AGC Calibration Error except substitute chan 3 for chan 1RFM Chan 4 AGC Calibration Error (01 8 D3)Same as RFM Chan 1 AGC Calibration Error except substitute chan 4 for chan 1RFM Chan 5 AGC Calibration Error (01 8 D4)Same as RFM Chan 1 AGC Calibration Error except substitute chan 5 for chan 1RFM Chan 6 AGC Calibration Error (01 8 D5)Same as RFM Chan 1 AGC Calibration Error except substitute chan 6 for chan 1RFM Chan 7 AGC Calibration Error (01 8 D6)Same as RFM Chan 1 AGC Calibration Error except substitute chan 7 for chan 1RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--36RFM Chan 8 AGC Calibration Error (01 8 D7)Same as RFM Chan 1 AGC Calibration Error except substitute chan 8 for chan 1RFM Block AGC Calibration Error (01 8 D8)DESCRIPTION : During a Factory Setting Start, and once every 24 hours, the RFM block AGC is calibratedfor DAC and ADC values over a 0 to --28 dB gain range. Prior to calibrating theblock AGC, the channel AGC is adjusted such that the power level as measured at the modem ADC is in therange --10 to --15 dB relative to full scale, with the block AGC at 0 dB gain. This fault is declared if therequired range cannot be achieved following adjustment of the channel AGC.PARAMETERS : Param 1 : Final modem ADC power level in units of 1/10 dB relative to full scaleParam 2 : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :SCFM SRU (SRU Code 9)OCXO SRU (SRU Code A)Oven Ready Fail (01 A 01)DESCRIPTION : During CM no tests is carried out on the OCXO Oven Ready discrete during the first 12minutes after power on to allow the device time to reach operating temperature.After the 12 minute delay the OCXO Oven Ready discrete is tested once per second. Should the discreteindicate that the oven has not maintained temperature then an ’OVENREADY FAIL’ fault is declared. While in the fault state the OCXO Oven Ready discrete is tested once persecond. The ’OVEN READY FAIL’ fault is cleared if the discrete indicates that the oven temperature isachieved again.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure if it persists for ten seconds or more.RECOVERY CRIT. : This failure is cleared, on receipt of an ’OVEN READY FAIL’ fault cleared report, if nofurther ’OVEN READY FAIL’ faults are reported for ten seconds or more.REMARK :SPSU SRU (SRU Code C)PSU Temp Limits Fail (01 C 01)DESCRIPTION : During CM the PSU temperature sensor is read once per second. A ’PSU Temp Limits Fail’fault is declared if the temperature sensor has a reading below --55 deg. C or above +125 deg.C.While in the fault state the PSU temperature sensor is read once per second. The ’PSU Temp Limits Fail’fault is cleared if the PSU temperature sensor has a reading equal to or above --55 deg. C and less than orequal to +125 deg C.PARAMETERS : The PSU temperature sensor readingFAIL CRITERIA : This fault transitions into failure if it persists for ten seconds or moreRECOVERY CRIT. : This failure is cleared, on receipt of a ’PSU Temp Limits Fail’ fault cleared report, if nofurther ’PSU Temp Limits Fail’ faults are reported for ten seconds or moreREMARK :PSU Secondary Voltage Fail (01 C 03)DESCRIPTION : The PSU secondary voltage supply discrete is tested every second. A ’PSU SecondaryVoltage Fail’ fault is declared if the discrete indicates the secondary voltage supply is not operational.While in the fault state the PSU secondary voltage discrete is not tested and the faultis not explicitly cleared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : Should this fault occur, but the 5 Volt rail still remain up, then this failure can be logged becausethe SMPM will be active, but it is unlikely to be able to be communicated outside of the SDU as the othervoltage rails typically provide the power for the I/O device drivers.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--37SFPDM SRU (SRU Code D)Test (PAST) Switch Stuck (01 D 01)DESCRIPTION : Should the Test (PAST) switch become stuck on, i.e. have become activated and remainedactivated for a period greater than 10 seconds without going inactive, then this fault is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure after 80 seconds.RECOVERY CRIT. : Cleared if it goes good for greater than 10 seconds.REMARK : The 10 second delay required for the fault to be declared, combined with the 80 second delayrequired to transition to failure, result in a total period of 90 seconds the test switchmust be on before a failure is declared.Manual Scroll Switch Fail (01 D 02)DESCRIPTION : Should the Manual Scroll switch become stuck on, i.e. have become activated andremained activated for a period greater than 90 seconds without going inactive, then this fault is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is cleared when the switch returns to the inactive state.REMARK :CODEC C SRU (SRU Code E)As for Codec A above except substitute SRU code E for code 2 and <CODEC--C> for <CODEC--A>.CODEC D SRU (SRU Code F)As for Codec A above except substitute SRU code F for code 2 and <CODEC--D> for <CODEC--A>.CODECESRU(SRUCodeG)As for Codec A above except substitute SRU code G for code 2 and <CODEC--E> for <CODEC--A>.CODECFSRU(SRUCodeH)As for Codec A above except substitute SRU code H for code 2 and <CODEC--F> for <CODEC--A>.SMDM4:SDU Modem Module #4 (SRU Code J)As for SMDM1 above except substitute SRU code J for code 5 and <MODEM--4> for <MODEM--1>.SMDM5:SDU Modem Module #5 (SRU Code L)As for SMDM1 above except substitute SRU code L for code 5 and <MODEM--5> for <MODEM--1>.SMDM6:SDU Modem Module #6 (SRU Code M)As for SMDM1 above except substitute SRU code M for code 5 and <MODEM--6> for <MODEM--1>.SMDM7:SDU Modem Module #7 (SRU Code N)As for SMDM1 above except substitute SRU code N for code 5 and <MODEM--7> for <MODEM--1>.VIM SRU (SRU Code P)Cabin Interface 1 Audio Loopback Fail (01 P 81)DESCRIPTION : During POST/PAST, Cabin Analogue Audio Interface 1 and its connection to the Codecs istested.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :Cabin Interface 2 Audio Loopback Fail (01 P 82)As for Cabin Interface 1 Audio Loopback Fail but substitute ’Interface 2’ for ’Interface 1’.Cockpit Interface 1 Audio Loopback Fail (01 P 83)DESCRIPTION : During POST/PAST, Cockpit Analogue Audio Interface 1 and its connection to the Codecs istested.PARAMETERS : NoneRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--38FAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :Cockpit Interface 2 Audio Loopback Fail (01 P 84)As for Cockpit Interface 1 Audio Loopback Fail but substitute ’Interface 2’ for ’Interface 1’.CTU CEPT--E1 Audio Loopback Fail (01 P 85)DESCRIPTION : During POST/PAST, the CTU CEPT--E1 Interface and its connection to the Codecs istested.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK :Cabin Audio Discrete Outputs Loopback Fail (01 P 07)DESCRIPTION : During CM, a test of each of the four WH--10 Status discrete outputs is performed 10 timesa second (Status A and B discrete outputs on each of Cabin Audio Interfaces #1 and #2). If a discrete outputis being driven to the active state it is verified to be at theactive state.PARAMETERS : The following codes apply:(001) = WH--10 Status A #1 output failure,(002) = WH--10 Status A #2 output failure,(003) = WH--10 Status B #1 output failure,(004) = WH--10 Status B #2 output failure,FAIL CRITERIA : The CM fault transitions to a failure if the fault persists for 1 second.RECOVERY CRIT. : This failure is cleared immediately.REMARK : The fault to failure timer is included to prevent the annunciation of spurious failuresdetected as the various SDU PSU buses decay on loss of primary power.Cockpit Audio Discrete Outputs Loopback Fail (01 P 08)During CM, a test of each of the Cockpit Call Lamp discrete outputs (on Cockpit Audio Interfaces #1 and #2)and the Cockpit Chime discrete output is performed 10 times a second. If the Cockpit Chime discrete outputis being driven to the active state it is verified to be at the active state. If the Cockpit Call Lamp discreteoutput is being driven to the active state it is verified to be at the active state.PARAMETERS : The following codes apply:(001) = Cockpit Call Lamp #1 output failure,(002) = Cockpit Call Lamp #2 output failure,(003) = Cockpit Chime output failure.FAIL CRITERIA : The CM fault transitions to a failure if the fault persists for 1 second.RECOVERY CRIT. : This failure shall recover immediately.REMARK : The fault to failure timer is included to prevent the annunciation of spurious failuresdetected as the various SDU PSU busses decay on loss of primary power.When MP11F=0, the discretes associated with this failure map to the CD1/2 discretes.CTU CEPT--E1 HDLC Loopback Fail (01 P 89)DESCRIPTION : During POST/PAST, the HDLC controller within CEPT--E1 framer chip is tested by loopingback the transmitter to the receiver on the chip. This fault is declared if the received frame does not matchthe transmitted frame after two successive tests.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK :Cabin Interface 1 Bus Error (01 P 8A)DESCRIPTION : During POST/PAST all VIM devices is tested for read write access. A ’VIM Bus Error’ isdeclared if any of the tests result in a bus error.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--39RECOVERY CRIT. : This failure is never explicitly clearedREMARK : If a Bus Error occurs during normal operation, a S/W SYSFAIL failure is raised whatever the failedaddress. Faults (01 P 8A)--(01 P 8E) are identical, and have been split out due to the desire to indict allapplicable resources.Cabin Interface 2 Bus Error (01 P 8B)DESCRIPTION : During POST/PAST all VIM devices is tested for read write access. A ’VIM Bus Error’ isdeclared if any of the tests result in a bus error.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : If a Bus Error occurs during normal operation, a S/W SYSFAIL failure is raised whatever the failedaddress. Faults (01 P 8A)--(01 P 8E) are identical, and have been split out due to the desire to indict allapplicable resources.Cockpit Interface 1 Bus Error (01 P 8C)DESCRIPTION : During POST/PAST all VIM devices is tested for read write access. A ’VIM Bus Error’ isdeclared if any of the tests result in a bus error.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : If a Bus Error occurs during normal operation, a S/W SYSFAIL failure is raised whatever the failedaddress. Faults (01 P 8A)--(01 P 8E) are identical, and have been split out due to the desire to indict allapplicable resources.Cockpit Interface 2 Bus Error (01 P 8D)DESCRIPTION : During POST/PAST all VIM devices is tested for read write access. A ’VIM Bus Error’ isdeclared if any of the tests result in a bus error.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : If a Bus Error occurs during normal operation, a S/W SYSFAIL failure is raised whatever the failedaddress. Faults (01 P 8A)--(01 P 8E) are identical, and have been split out due to the desire to indict allapplicable resources.CTU CEPT--E1 Bus Error (01 P 8E)DESCRIPTION : During POST/PAST all VIM devices is tested for read write access. A ’VIM Bus Error’ isdeclared if any of the tests result in a bus error.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure immediatelyRECOVERY CRIT. : This failure is never explicitly clearedREMARK : If a Bus Error occurs during normal operation, a S/W SYSFAIL failure is raised whatever the failedaddress. Faults (01 P 8A)--(01 P 8E) are identical, and have been split out due to the desire to indict allapplicable resources.HPA Command Word (143) Update Rate Fail (01 0 02)DESCRIPTION : The number of HPA Command Words with no parity error received by the HPA in the lastsecond is less than 1 after completion of POST/PAST, and the associated bus is notinactive.PARAMETERS : Number of HPA Command Words received with no parity error during the 1st second of thefault. None for 60W HPA.FAIL CRITERIA : This fault transitions to a failure if the fault persists for at least five seconds but other wordsare being received on the Multi--Control bus (i.e., the bus is not inactive).RECOVERY CRIT. : The fault is cleared if the word is received in the range specified for at least one second.REMARK : This fault can only be reported with a Honeywell HPA, as the fault report is made using themanufacturer specific protocol. “No Computed Data” will be indicated in the HPA Status words. The 60W HPAwill set bit 15 in its Maintenance words. The SDU will raise failure (90 0 01), section 4.4.5.144.1 while bit 15 isset.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--40HPA Command Word (143) Data Fail (01 0 03)DESCRIPTION : The last HPA Command Word with no parity error received by the HPA contains a field setto an unauthorised or undetermined value.PARAMETERS : HPA Command Word in error.FAIL CRITERIA : This fault transitions to a failure if the fault persists for at least five seconds.RECOVERY CRIT. : The fault is cleared if the valid word is received for at least five seconds.REMARK : Only the first error seen on one of the HPA Command Words received will be reported;subsequent errors, possibly affecting other data fields in the word, will not be reportedunless the first error disappears. This fault can only be reported with a Honeywell HPA, as the fault report ismade using the manufacturer specific protocol.HSU1--SDU Williamsburg Data TX Fail (01 0 07)DESCRIPTION : The SDU shall raise this fault when bit 15 of the HSU’s label 270 status word is set, i.e., theSDU has failed to transfer data to the HSU or any of the Williamsburg timers/retrieshave been exceeded, unless the HSU input bus inactive failure is currently active (reference 9E 0 01, Section4.4.5.158).PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure if bit 15 is set in at least 5 consecutive words.RECOVERY CRIT. : This fault is cleared when the SDU’s input bus from the HSU transitions from an inactiveto an active state, with the SSM field of the label 270 HSU Status word indicating Functional Test.REMARK:HSU1--SDU Williamsburg Solo Word Ack Fail (01 0 08)DESCRIPTION : The SDU shall raise this fault when bit 16 of the HSU’s label 270 status word is set, i.e., theHSU has not received an acknowledgment back from the SDU within 25 ms aftersending a solo word transmission.PARAMETERS : NoneFAIL CRITERIA : This fault transitions into failure if bit 16 is set in at least 5 consecutive status words.RECOVERY CRIT. : This fault is cleared when the SDU’s input bus from the HSU transitions from an inactiveto an active state, with the SSM field of the label 270 HSU Status word indicating Functional Test.REMARK :HSU2--SDU Williamsburg Data TX Fail (01 0 0B)Same as 01 0 07 except substitute “HSU2” for “HSU1”. Only applicable prior to SDU Part Number7516118--XX130/--xx140.HSU2--SDU Williamsburg Solo Word Ack Fail (01 0 0C)Same as 01 0 08 except substitute “HSU2” for “HSU1”. Only applicable prior to SDU Part Number7516118--XX130/--xx140.<HGA HPA> Command Word (NCD) (01 0 10)DESCRIPTION : This fault is declared if the SSM of Status words from the HGA HPA show No ComputedData (due to not receiving valid Command words for at least one second), but the Multi--Control bus is notinactive.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure if the fault persists for at least three seconds.RECOVERY CRIT. : Cleared as soon as the first status word is received without SSM = NCD or the controlbus is declared inactive.REMARK :<LGA HPA> Command Word (NCD) (01 0 12)Same as <HGA HPA> Command Word (NCD).Incomplete ID Prom Responses (01 0 96)DESCRIPTION : During Power Up or Factory Setting Start, the Id Prom on each physical SRU is interrogatedas specified in Section 3.2.1.2.3.5.1. The response is held in category B storage. On each subsequent PASTor system reset, the preserved response is checked to verify that, for each mandatory SRU and each optionalSRU determined to be present, the Id Prom responds correctly. This fault is raised if any Id Prom fails to givea response.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--41PARAMETERS : The SRUs which failed to respond is identified as follows:Bit SRU0MPMM1 SIOM2VIM3RFM4MBD5FPD6IFM7 TTCM in slot #18 TTCM in slot #2FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : Also reference Section 3.2.1.3.1.5.4, which defines the cases of depopulation, faulty (butpopulated) SRUs, and unprogrammed Id Proms. Section 3.2.1.2.3.5.1 requires that if an IdProm is found to have not been programmed, software upload processes are allowed to proceed, assuming(hoping for) hardware/software compatibility; and it also requires that this failure be raised under suchconditions. For any logic in the SDU main processor that is dependent upon Id Prom information (e.g., thefront panel display type), default values are assumed when the relevant data is unavailable.“Other” SATCOM System (Level 1 Code 02h)”Other” SATCOM System, Unknown SRU (SRU Code 0h)Protocol Version Number Incompatible (02 0 01)DESCRIPTION : This fault is declared in a dual system if the Protocol Version Number (PVN) received fromthe other SDU is lower than this SDU’s PVN, and this SDU is not capable of operating with the lower PVN.PARAMETERS : 1st parameter: Last 8 decimal digits of this SDU’s PVN (presented as BCD) 2nd parameter:Last 8 decimal digits of the other SDU’s PVN (presented as BCD)FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared if a compatible PVN is received from the other SDU.REMARK : This failure is only declared in the SDU disabling the other one.SDU/SDU Message Protocol Error (02 0 02)DESCRIPTION : This fault is declared if an SDU/SDU Message Transfer protocol error is detected by thisSDU. This fault is not declared if the cross--talk bus is inactive.PARAMETERS : Error discriminator:1: Transmission Buffer Overflow in this SDU2: Retransmission Retry Limit exceeded (from this SDU)3: Invalid Message Received by this SDUFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared after one second.REMARK : When this failure is detected, the XTB falls back to initial communications status.HSU (Level 1 Code 03h)This section, and all its subsections, are only applicable to SDU Part Number 7516118--XX130/--xx140 andsubsequent, for the HS--720. Although not documented for individual failures in the subsections that follow,any and all current failures for the HSU (i.e., failures having the HSU level 1 failure code) is considered tohave “recovered” when the SDU’s input bus from the HSU transitions from an inactive to an active state, withthe SSM field of the label 270 status word indicating Functional Test.In the subsections below, the statement “HSU is declared unserviceable” indicates that the following actionsare taken by the HSU: in the HSU Status Word (Label 270), all four Channel Failure bits are set to 1 andSSM is set to Failure Warning; all four HSD Service Available discretes are set to 0; the HSU Failure discreteis set to 1.HSCC1: HSU Channel Card 1 (SRU Code 1h)COMMENTARYError reporting for the HS--720 channel cards is performed by the TAL (Terminal Adaption Layer) ----thecommon interface to access the top layer of the different protocol stacks (i.e. Swift64 CircuitRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--42Switched, Swift64 MPDS or BGAN). There are two instances of the TAL in each channel card (one permodem). When a TAL error is reported, the HS--720 translates the hexadecimal TAL error code into theappropriate HSU failure, which is then reported to the SDU via a Williamsburg Failure Report message in theusual manner.Certain channel card faults, mainly software and communication errors, are transitory and normaloperation may resume if the TAL is commanded to the ’Idle’ state. Other faults are more likely toreoccur. For such errors, the TAL will first be commanded to ’Idle’. If the fault reoccurs, then a reboot of theentire channel card will be performed. For faults that are considered more likely to be hardware related,recovery from a transition to ’Idle’ is unlikely and therefore a reboot of thechannel card will be performed immediately.HSU Channel Card 1 Modem Fault (03 1 01)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B090h (modemburst overflow), B091h (modem data overflow) or B093h (modem burst sent too late).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure if the fault reoccurs within one minute of the associatedTAL being commanded to the ’Idle’ state following the initial TAL report.RECOVERY CRIT. : This failure is cleared if there is no reoccurrence within one minute of the reboot of thechannel card (refer to Remark below).REMARK : When this failure is declared, the HSU control processor will reboot channel card 1.HSU Channel Card 1 Modem Failure (03 1 02)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B0B3h--B0B6h(DSP not responding), B493h (DSP failed to boot), B49Ah (modem not sending messages), B090h (modemburst overflow), B091h (modem data overflow) or B093h (modem burst sent too late).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure if the fault reoccurs following a reboot of the associatedchannel card.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the appropriate Channel Failure bit (1 or 2) to 1 in theHSU Status Word (Label 270), and the appropriate HSD Service Available discrete (1 or 2) to 0.HSU Channel Card 1 Peripheral Error (03 1 03)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B922h (invalidperipheral request), B923h (peripheral acknowledgement lost), B940h (peripheral data overflow), B941h(peripheral not in correct mode) or B942h (peripheral parameter error).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared if there is no reoccurrence within one minute of the associatedTAL being commanded to the ’Idle’ state (refer to Remark below).REMARK : When this failure is declared, the HSU control processor will command the TAL reporting the errorto the ’Idle’ state.HSU Channel Card 1 Peripheral Failure (03 1 04)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B924h (peripheralnot responding).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure if the fault reoccurs following a reboot of the associatedchannel card.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the appropriate Channel Failure bit (1 or 2) to 1 in theHSU Status Word (Label 270), and the appropriate HSD Service Available discrete (1or 2) to 0.HSU Channel Card 1 Control Processor SW Incompatibility (03 1 05)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B590h (unknownprocessor parameter), B591h (processor function not implemented) or B592h (incorrectprocessor parameter).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--43PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : None.HSU Channel Card 1 RF Fault (03 1 07)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports one of 24 specific errorsrelating to RF (B660h, B661h, B662h, B663h, B664h, B666h, B667h, B668h, B669h, B66Bh, B66Fh, B670h,B672h, B673h, B674h, B675h, B676h, B677h, B678h, B679h,B67Ah, B67Bh, B67Ch, B67Dh).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure if the fault reoccurs within one minute of the associatedTAL being commanded to the ’Idle’ state following the initial TAL report.RECOVERY CRIT. : This failure is cleared if there is no reoccurrence within one minute of the reboot of thechannel card (refer to Remark below).REMARK : When this failure is declared, the HSU control processor will reboot channel card 1.HSU Channel Card 1 RF Failure (03 1 08)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B492h (RF failedto boot), B494h (RF failed to calibrate), B49Bh (RF not sending messages), or one of the 24 errors relating toRF.PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure if the fault reoccurs following a reboot of the associatedchannel card.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the appropriate Channel Failure bit (1 or 2) to 1 in theHSU Status Word (Label 270), and the appropriate HSD Service Available discrete (1or 2) to 0.HSU Channel Card 1 TAL Error (03 1 09)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B490h (TALsmartcard not responding) or B491h (TAL PPD late).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared if there is no reoccurrence within one minute of the associatedTAL being commanded to the ’Idle’ state (refer to Remark below).REMARK : When this failure is declared, the HSU control processor will command the TAL reporting the errorto the ’Idle’ state.HSU Channel Card 1 Modem Calibration Missing (03 1 0A)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B49Ch (calibrationmodem values missing).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure if the fault reoccurs following a reboot of the associatedchannel card.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the appropriate Channel Failure bit (1 or 2) to 1 in theHSU Status Word (Label 270), and the appropriate HSD Service Available discrete (1 or 2) to 0.HSU Channel Card 1 Temperature Unreadable (03 1 0B)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B49Dh(temperature sensor not reading).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure if the fault reoccurs following a reboot of the associatedchannel card.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the appropriate Channel Failure bit (1 or 2) to 1 in theHSU Status Word (Label 270), and the appropriate HSD Service Available discrete (1 or 2) to 0.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--44HSU Channel Card 1 Over Temperature (03 1 0C)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B400h(temperature over limit).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : None.HSU Channel Card 1 TURBO Fault (03 1 0E)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B800h (TURBObusy, cannot accept message) or B801h (bad TURBO parameters).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure if the fault reoccurs within one minute of the associatedTAL being commanded to the ’Idle’ state.RECOVERY CRIT. : This failure is cleared if there is no reoccurrence within one minute of the reboot of thechannel card (refer to Remark below).REMARK : When this failure is declared, the HSU control processor will reboot channel card 1.HSU Channel Card 1 TURBO Failure (03 1 0F)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B800h (TURBObusy, cannot accept message) or B801h (bad TURBO parameters).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure if the fault reoccurs following a reboot of the associatedchannel card.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the appropriate Channel Failure bit (1 or 2) to 1 in theHSU Status Word (Label 270), and the appropriate HSD Service Available discrete (1 or 2) to 0.HSU Channel Card 1 VCODEC Fault (03 1 11)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B880h (VCODECbusy, cannot accept message) or B881h (bad VCODEC parameters).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure if the fault reoccurs within one minute of the associatedTAL being commanded to the ’Idle’ state following the initial report.RECOVERY CRIT. : This failure is cleared if there is no reoccurrence within one minute of the reboot of thechannel card (refer to Remark below).REMARK : When this failure is declared, the HSU control processor will reboot Channel Card 1.HSU Channel Card 1 VCODEC Failure (03 1 12)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B880h (VCODECbusy, cannot accept message) or B881h (bad VCODEC parameters).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure if the fault reoccurs following a reboot of the associatedchannel card.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the appropriate Channel Failure bit (1 or 2) to 1 in theHSU Status Word (Label 270), and the appropriate HSD Service Available discrete (1 or 2) to 0.HSU Channel Card 1 Application Code Error (03 1 93)DESCRIPTION : This fault is declared by the HSU when channel card 1 TAL reports error B593h (PROMcorrupted).PARAMETERS : TAL error code in failure parameter; TAL ID in associated failure parameter.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the Channel 1 Failure and Channel 2 Failure bits to 1in the HSU Status Word (Label 270), and the HSD 1 Service Available and HSD 2 Service Available discretesto 0. Thus, the HSU declares channel card 1 unserviceable.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--45HSCC2: HSU Channel Card 2 (SRU Code 2h)Same as for HSCC1, but make the following substitutions:SRU Code 2 instead of SRU Code 1,Channel card 2 instead of channel card 1,Channel 3/4 Failure instead of Channel 1/2 Failure,HSD 3/4 Service Available instead of HSD 1/2 Service Available.HSDIO: HSU Data I/O Card (SRU Code 3h)HSU Unrecoverable SW / Protocol Error (03 3 02)DESCRIPTION : This fault is declared by the HSU when an unrecoverable software or protocol error occursin the Data I/O Card.PARAMETERS : Data I/O Card error code in failure parameter; associated Data I/O error code in associatedfailure parameter.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared immediately.REMARK : When this failure is declared, the Data I/O card automatically reboots.HSU Channel Card 1 Unresponsive / Unserviceable (03 3 03)DESCRIPTION : This fault is declared by the HSU when channel card 1 is observed to be unresponsive orunserviceable via an associated interface (identified by the failure parameter).PARAMETERS : The failure parameter contains one of the following values:01: ISDN interface02: Serial interface03: Ethernet interfaceFAIL CRITERIA : This fault transitions to a failure if the fault persists through one retry of the affectedinterface.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the Channel 1 Failure and Channel 2 Failure bits to 1in the HSU Status Word (Label 270), and the HSD 1 Service Available and HSD 2 Service Available discretesto 0. Thus, the HSU declares channel card 1 unserviceable.HSU Channel Card 2 Unresponsive / Unserviceable (03 3 04)DESCRIPTION : This fault is declared by the HSU when channel card 2 is observed to be unresponsive orunserviceable via an associated interface (identified by the failure parameter).PARAMETERS : The failure parameter contains one of the following values:01: ISDN interface02: Serial interface03: Ethernet interfaceFAIL CRITERIA : This fault transitions to a failure if the fault persists through one retry of the affectedinterface.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the Channel 3 Failure and Channel 4 Failure bits to 1in the HSU Status Word (Label 270), and the HSD 3 Service Available and HSD 4 Service Available discretesto 0. Thus, the HSU declares channel card 2 unserviceable.HSU Configuration Error (03 3 85)DESCRIPTION : This fault is declared by the HSU when the Boot or Application fails a software/hardwarecompatibility check.PARAMETERS : The failure parameter contains one of the following values:00: Boot / hardware incompatibility01: Application / hardware incompatibilityFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is detected, the HSU is declared unserviceable.HSU Peripheral Failure (03 3 86)DESCRIPTION : This fault is declared by the HSU when at least one of the peripherals fails an integritycheck.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--46PARAMETERS : The failure parameter contains one of the following values:00: MPC 862 (Serial Communication Controllers for Ethernet 1 and 2, MPDS, Control Processor interface(RS--232), debug port (RS--232) and TDM bus for E1 and POTS.01: ST16C654 (Quad. UART for communications with the channel card MPDS ports)02: PSB21150 #1 (ISDN transceiver)03: PSB21150 #2 (ISDN transceiver)04: DS21354LN (E1 transceiver)The associated failure parameter contains the number of loopback test faults for the failedperipheral.FAIL CRITERIA : This fault transitions to a failure if two out of three consecutive loopback tests for a specificperipheral fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is detected, the HSU is declared unserviceable.HSU Both Channel Cards Unresponsive / Unserviceable (03 3 07)DESCRIPTION : This fault is declared by the HSU when both channel card 1 and channel card 2 areunresponsive or unserviceable.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is detected, the HSU is declared unserviceable.HSU RAM Fault (03 3 08)DESCRIPTION : This fault is declared by the HSU when a CRC check of the Data I/O Application image inRAM fails.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure when the fault is reported more than twice since the HSUpowered up.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is detected, the HSU is declared unserviceable and the Data I/O cardautomatically reboots.HSU ROM Fault (03 3 09)DESCRIPTION : This fault is declared by the HSU when a CRC check of the configuration information storedin EEPROM or Flash fails.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure when the fault is reported more than twice since the HSUpowered up.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is detected, the HSU is declared unserviceable and the Data I/O cardautomatically resets the configuration information to factory defaults.HSU SW Configuration Error (03 3 0A)DESCRIPTION : This fault is declared by the HSU when an illegal configuration parameter value is receivedfrom the SDU.PARAMETERS : The failure parameter contains the relevant parameter number if the parameter is containedin the HSU Configuration Data Part 1 message sent from the SDU. The associated parameter contains therelevant parameter number if the parameter is contained in the HSU Configuration Data Part 2 message sentfrom the SDU.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared when all Data I/O configuration parameters received from the SDUare valid.REMARK : None.HSU PPPoE Session Failure (03 3 0B)DESCRIPTION : This fault is declared by the HSU when the PPPoE client has been unresponsive.PARAMETERS : None.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--47FAIL CRITERIA : This fault transitions to a failure if the PPPoE client has been unresponsive for at least fiveseconds.RECOVERY CRIT. : This failure is cleared immediately.REMARK : When this failure is declared, the HSU will clear the PPPoE session.HSU Channel Card 1 Unresponsive (03 4 87/07)DESCRIPTION : This fault is declared by the HSU when channel card 1 is observed to be unresponsive (orunserviceable).PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if the fault persists through a reboot of the channel card.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the Channel 1 Failure and Channel 2 Failure bits to 1in the HSU Status Word (Label 270), and the HSD 1 Service Available and HSD 2 Service Available discretesto 0. Thus, the HSU declares channel card 1 unserviceable.HSU Channel Card 2 Unresponsive (03 4 88/08)DESCRIPTION : This fault is declared by the HSU when channel card 2 is observed to be unresponsive (orunserviceable).PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if the fault persists through a reboot of the channel card.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the Channel 3 Failure and Channel 4 Failure bits to 1in the HSU Status Word (Label 270), and the HSD 3 Service Available and HSD 4 Service Available discretesto 0. Thus, the HSU declares channel card 2 unserviceable.HSU Both Channel Cards Unresponsive (03 4 89/09)DESCRIPTION : This fault is declared by the HSU when both channel card 1 and channel card 2 areobserved to be unresponsive (or unserviceable or both channel cards are reporting unrecoverable errors onall TALs.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately .RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is detected, the HSU is declared unserviceable.HSU Data I/O Card Unresponsive (03 4 8A/0A)DESCRIPTION : This fault is declared by the HSU when the Data I/O Card is observed to be unresponsive.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if the fault persists through a reboot of the Data I/O card.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is detected, the HSU is declared unserviceable.HSU Control Processor RAM Fault (03 4 0B)DESCRIPTION : This fault is declared by the HSU when a CRC check of the control processor Applicationimage in RAM fails.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure after a retry of the CRC check also fails.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is detected, the HSU is declared.HSU Control Processor ROM Fault (03 4 0C)DESCRIPTION : This fault is declared by the HSU when a CRC check of the configuration information storedin EEPROM or Flash fails.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure after a retry of the CRC check also fails.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is detected, the HSU is declared.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--48HSU Control Processor Over Temperature (03 4 0D)DESCRIPTION : This fault is declared by the HSU when the control processor on--board temperature sensorreaches 85°C.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared when the control processor on--board temperature sensor drops tobelow 60°C.REMARK : When this failure is detected, the HSU is declared.HSU Channel Card 1 Over Temperature (03 4 0E)DESCRIPTION : This fault is declared by the HSU when the control processor detects channel card 1reporting a temperature that exceeds the over--temperature threshold (indicating atemperature of at least 85°C).PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure when channel card 1 reports a temperature that exceedsthe over--temperature threshold for at least five seconds.RECOVERY CRIT. : This failure is cleared if channel card 1 reports a temperature below the overtemperature threshold for at least five seconds following the repowering of the channel card (refer to Remarkbelow).REMARK : When this failure is declared, channel card 1 is powered--down and then powered--up again afterfive minutes. The HSU also sets the Channel 1 Failure and Channel 2 Failure bits to 1in the HSU Status Word (Label 270), and the HSD 1 Service Available and HSD 2 Service Available discretesto 0. Thus, the HSU declares Channel Card 1 unserviceable.HSU Channel Card 2 Over Temperature (03 4 0F)DESCRIPTION : This fault is declared by the HSU when the control processor detects channel card 2reporting a temperature that exceeds the over--temperature threshold (indicating a temperature of at least85°C).PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure when channel card 2 reports a temperature that exceedsthe over--temperature threshold for at least five seconds.RECOVERY CRIT. : This failure is cleared if channel card 2 reports a temperature below the overtemperature threshold for at least five seconds following the repowering of the channel card (refer to Remarkbelow).REMARK : When this failure is declared, channel card 2 is powered--down and then powered--up again afterfive minutes. The HSU also sets the Channel 3 Failure and Channel 4 Failure bits to 1in the HSU Status Word (Label 270), and the HSD 3 Service Available and HSD 3 Service Available discretesto 0. Thus, the HSU declares Channel Card 2 unserviceable.HSU Both Channel Cards Over Temperature (03 4 10)DESCRIPTION : This fault is declared by the HSU when the control processor detects both channel cardsreporting a temperature exceeding the over--temperature threshold.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared if both channel cards report a temperature below the overtemperature threshold for at least five seconds following the repowering of the channel cards (refer to Remarkbelow).REMARK : When this failure is declared, both channel cards are powered--down and then powered--up againafter five minutes. The HSU is also declared unserviceable.HSU ADL Bus Interface Failure (03 4 91)DESCRIPTION : This fault is declared by the HSU during PP when the loopback test of the ARINC 429transceiver used for the ADL fails.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if two out of three consecutive loopback tests fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : None.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--49HSU PDL Bus Interface Failure (03 4 92)DESCRIPTION : This fault is declared by the HSU during PP when the loopback test of the ARINC 429transceiver used for the PDL fails.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if two out of three consecutive loopback tests fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : None.HSU Data I/O DUART Failure (03 4 93)DESCRIPTION : This fault is declared by the HSU during PP when the loopback test for channel 1 of DUART1 fails. This channel is used for communications with the Data I/O card.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if two out of three consecutive loopback tests fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is detected, the HSU is declared unserviceable.HSU Channel Card 1 DUART Failure (03 4 94)DESCRIPTION : This fault is declared by the HSU during PP when the loopback test for channel 1 of DUART2 fails. This channel is used for communications with channel card 1.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if two out of three consecutive loopback tests fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the Channel 1 Failure and Channel 2 Failure bits to 1in the HSU Status Word (Label 270), and the HSD 1 Service Available and HSD 2 Service Available discretesto 0. Thus, the HSU declares Channel Card 1 unserviceable.HSU Channel Card 2 DUART Failure (03 4 95)DESCRIPTION : This fault is declared by the HSU during PP when the loopback test for channel 2 of DUART2 fails. This channel is used for communications with channel card 2.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if two out of three consecutive loopback tests fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is declared, the HSU sets the Channel 3 Failure and Channel 4 Failure bits to 1in the HSU Status Word (Label 270), and the HSD 3 Service Available and HSD 4 Service Available discretesto 0. Thus, the HSU declares Channel Card 2 unserviceable.HSU Both Channel Cards DUART Failure (03 4 96)DESCRIPTION : This fault is declared by the HSU during PP when the loopback tests for channels 1 and 2 ofDUART 2 fail.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure is detected, the HSU is declared unserviceable.HSU Maintenance Interface DUART Failure (03 4 97)DESCRIPTION : This fault is declared by the HSU during PP when the loopback test for DUART 3 fails. Thisdevice is used for communications with the maintenance interface.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if two out of three consecutive loopback tests fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : None.HSU Discrete Output Failure (03 4 98)DESCRIPTION : This fault is declared by the HSU during PP when there is no response from the DiscreteOutputs device.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if there is no response from the Discrete Outputs hardwarefor two out of three consecutive tests.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--50RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : None.HSU Board Configuration/Revision Failure (03 4 99)DESCRIPTION : This fault is declared by the HSU during PP when there is no response from the BoardConfiguration/Revision device.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if there is no response from the BoardConfiguration/Revision hardware for two out of three consecutive tests.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : None.HOCXO: HSU Oven--Controlled 10 MHz Oscillator (SRU Code 5h)HSU OCXO Timeout (03 5 01)DESCRIPTION : This fault is declared by the HSU when the “OCXO Ready” discrete signal remains deasserted.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if the “OCXO Ready” signal remains de--asserted for atleast 15 minutes after powering--up the HSU.RECOVERY CRIT. : This failure is cleared if the “OCXO Ready” signal is asserted for five seconds.REMARK : When this failure is detected, the HSU is declared unserviceable.HSU OCXO Temperature Unstable (03 5 02)DESCRIPTION : This fault is declared by the HSU when the “OCXO Ready” signal transitions from theasserted to de--asserted state.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if the “OCXO Ready” signal remains de--asserted for atleast five seconds.RECOVERY CRIT. : This failure is cleared if the “OCXO Ready” signal is asserted for five seconds.REMARK : None.HSPSU: HSU Power Supply Unit (SRU Code 6h)HSU Power Supply Fail (03 6 01)DESCRIPTION : This fault is declared by the HSU when the PSU “Power Good” signal is de--asserted.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if the “Power Good” signal remains de--asserted for at least250 ms.RECOVERY CRIT. : This failure is cleared if the “Power Good” signal is asserted for five seconds.REMARK : None.HSU PSU Over Temperature (03 6 02)DESCRIPTION : This fault is declared by the HSU when PSU “Over Temperature” signal is asserted.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if the PSU “Over Temperature” signal is asserted for atleast 5 ms.RECOVERY CRIT. : This failure is cleared if the PSU “Over Temperature” signal is de--asserted for at leastfive seconds.REMARK : When this failure is detected, both channel cards are powered--down and the HSU isdeclared unserviceable.HSFP: HSU Front Panel (SRU Code 8h)HSU Self--Test Button Stuck (03 8 81)DESCRIPTION : This fault is declared by the HSU when the self--test button becomes stuck on, i.e. hasbecome activated and remained activated for an abnormally long period of time withoutgoing inactive.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if the self--test button remains active for at least 10seconds.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--51RECOVERY CRIT. : This failure is cleared if the self--test button becomes de--activated for at least onesecond.REMARK : None.HSU Self--Declared Failure (03 0 01)DESCRIPTION : This fault is declared by the SDU if the SSM field of the Label 270 status word receivedfrom the HSU is set to Failure Warning.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if it is continually active in at least 5 consecutive statuswords.RECOVERY CRIT. : This failure is cleared as soon as a status word is received with the SSM set to NormalOperation.REMARK: One second of filtering is applied by the SDU (assuming the nominal transfer rate of 5 Hz) to coverthe possibility that the HSU does not apply any filtering to its activation of SSM = Failure Warning.HSU Williamsburg Protocol ALO/ALR Fail (03 0 02)DESCRIPTION : This fault is declared by the SDU if, after 3 transmissions of an ALO word to the HSU, theSDU has not received a responding ALR word.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared as soon as communication is re--established with the HSU.REMARK : None.HSU Williamsburg Protocol Data Transfer Fail (03 0 03)DESCRIPTION : This fault is declared by the SDU if the maximum number of RTS words have been sent tothe HSU without receiving a valid CTS word, or if the maximum number of attempts have been made fortransmitting an LDU to the HSU without receiving a valid ACK word when HSU is the active DTE.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared as soon as a successful transmission of an LDU has been madeto the HSU.REMARK : A transmission failure indicates a break in the bus connecting the SDU output and the HSU input.HSU Self Test Misoperation (03 0 84)DESCRIPTION : This fault is declared by the SDU, and covers all possible SDU--initiated POST/PASTmisbehavior related to HSU Functional Test. If no ARINC words are being received from the HSU, thePOST/PAST fault is not declared. Also, if the HSU is declaring the control bus input inactive, the POST/PASTno response fault is not declared.PARAMETERS : For SDU--initiated POST/PAST:01: The HSU has not responded to functional test commanded for 15 seconds by theSDU (POST/PAST).02: The HSU has started functional test, but the SDU has not received an HSU self--testcomplete response within the 60 seconds accorded to external LRUs duringsystem--wide POST/PAST.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : Functional Test response checking is determined on the HSU Status Word. The CMversion of this fault is (50 0 02).HSU Serial Port Mis--wiring (03 0 05)DESCRIPTION : This fault is declared by the HSU when inconsistent behaviour of RTS, CTS, DTR and Tx isdetected in communications from the User.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure when the behaviour persists for at least five seconds.RECOVERY CRIT. : This failure is cleared when a PPPoE session is successfully established on the serialport.REMARK : None.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--52HSU TOTC Reset (03 0 86/06)DESCRIPTION : This fault is declared by the HSU when the TOTC has been reset (either with or withoutuser intervention).PARAMETERS : The failure parameter contains the value of TOTC prior to being reset.The associated failure parameter contains one of the following values:0: Auto Reset ---- TOTC has been reset without user intervention (rollover, orautomatic clearing of EEPROM due to corruption).1: Manual Reset ---- TOTC has been reset through user intervention.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure occurs during PP (ie. 03 0 86), the associated failure parameter willalways contain the value 0 (Auto Reset).HSU POC Reset (03 0 87/07)DESCRIPTION : This fault is declared by the HSU when the POC has been reset (either with or without userintervention).PARAMETERS : The failure parameter contains the value of POC prior to being reset.The associated failure parameter contains one of the following values:0: Auto Reset ---- POC has been reset without user intervention (rollover, orautomatic clearing of EEPROM due to corruption).1: Manual Reset ---- POC has been reset through user intervention.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : When this failure occurs during PP (ie. 03 0 87), the associated failure parameter willalways contain the value 0 (Auto Reset).HSU Channel 1 Failure (03 0 0C)DESCRIPTION : This fault is declared by the SDU if bit 17 of the HSU’s label 270 status word is set, i.e. theHSU has detected one or more “fatal” or “essential” errors that prevent the use of channel 1.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if bit 17 is set in at least 5 consecutive status words.RECOVERY CRIT. : This failure is cleared as soon as a status word is received with bit 17 cleared.REMARK : None.HSU Channel Release Acknowledge Failure (03 0 0D)DESCRIPTION : This fault is declared by the SDU if the HSU fails to acknowledge a cooperative channelrelease request from the SDU within 20 seconds.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : The SDU shall assert the HSU System Disable discrete for 10 seconds. This failure iscleared when, following the associated HSU reset, the SDU bus from the HSU transitions from an inactive toan active state, with the SSM field of the Label 270 status word indicating Functional Test.REMARK : None.HSU RF Loopback Inhibit Failure (03 0 8E/0E)DESCRIPTION : This fault is declared by the SDU if the HSU fails to acknowledge the termination of RFloopback testing by indicating “Normal Operation” in bits 12 and 13 of the HSU status word. The failure codeshall reflect CM(0E) or PP(8E) depending on the CM/PP state ofthe SDU at the time the failure was declared.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if bits 12 and 13 of the HSU status word do not indicate“Normal Operation” within two seconds of inhibit command from the SDU.RECOVERY CRIT. : The SDU shall assert the HSU System Disable discrete for 10 seconds. This failure iscleared when, following the associated HSU reset, the SDUbus from the HSU transitions from an inactive toan active state, with the SSM field of the Label 270 status word indicating Functional Test.REMARK : None.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--53HSU Channel 2 Failure (03 0 0F)DESCRIPTION : This fault is declared by the SDU if bit 18 of the HSU’s label 270 status word is set, i.e. theHSU has detected one or more “fatal” or “essential” errors that prevent the use of channel 2.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if bit 18 is set in at least 5 consecutive status words.RECOVERY CRIT. : This failure is cleared as soon as a status word is received with bit 18 cleared.REMARK : None.HSU Channel 3 Failure (03 0 10)DESCRIPTION : This fault is declared by the SDU if bit 19 of the HSU’s label 270 status word is set, i.e. theHSU has detected one or more “fatal” or “essential” errors that prevent the use of channel 3.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if bit 19 is set in at least 5 consecutive status words.RECOVERY CRIT. : This failure is cleared as soon as a status word is received with bit 19 cleared.REMARK : None.HSU Channel 4 Failure (03 0 11)DESCRIPTION : This fault is declared by the SDU if bit 20 of the HSU’s label 270 status word is set, i.e. theHSU has detected one or more “fatal” or “essential” errors that prevent the use of channel 4.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if bit 20 is set in at least 5 consecutive status words.RECOVERY CRIT. : This failure is cleared as soon as a status word is received with bit 20 cleared.REMARK : None.HGA/IGA HPA (Level 1 Code 04h)Failures listed in this section apply to both the HGA (40W/60W) and IGA (20W) Honeywell/Thales HPAs, asnoted in the description for each failure.HPSU: HPA (AC Or DC) Power Supply Unit (SRU Code 1h)<HGA HPA> PSU Over Temp Shutdown (04 1 01)DESCRIPTION : During CM (for all software packages prior to as well as including D2.0), the 40W HPA’sPSU temperature is tested four times per second and a fault is declared if it equals or exceeds +130 degreesCelsius; for all 40W HPA software packages subsequentto D2.0, and for all software versions of the 20W HPA, the maximum value threshold shallbe increased from +130 to +133 degrees Celsius. This failure code shall only be applicable to the 20W and40W HPAs.PARAMETERS : PSU temperature sensor scaled analog output, shutdown temperature limit.FAIL CRITERIA : A failure is declared if the PSU temperature sensor scaled analog output is greater than orequal to the specified fault threshold for four consecutive readings.RECOVERY CRIT. : The failure is cleared (by all software packages prior to as well as including D2.0) if afterfour consecutive readings the 40W HPA’s PSU temperature sensor scaled analog output is less than +130degrees Celsius; for all 40W HPA software packages subsequentto D2.0, and for all software versions of the 20W HPA, the temperature threshold isdecreased from +130 to +125 degrees Celsius.REMARK : The HPA shall set bit 13 and indicate Failure Warning in its Maintenance words while this failure isactive (reference also Section 4.3.5.1). The HPA Carriers is set to OFF, theHPA Bias voltage is set to OFF, and the Variable Attenuator is set to maximum while this failure is active.<HGA HPA> PSU Temp Sensor Fail (04 1 02)DESCRIPTION : This fault is declared if (during CM) the reported PSU temperature is either less than --90degrees Celsius or greater than +210 degrees Celsius. This failure code shall only be applicable to the 20Wand 40W HPAs.PARAMETERS : PSU temperature sensor scaled analog output.FAIL CRITERIA : PSU temperature sensor scaled analog output either less than --90 degrees Celsius orgreater than +210 degrees Celsius for four consecutive reads.RECOVERY CRIT. : PSU temperature sensor scaled analog output greater than or equal to --90 degreesCelsius and less than or equal to +210 degrees Celsius for four consecutive reads.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--54REMARK : It is assumed that the PSU temperature sensor is faulty if the reported PSUtemperature is either less than --90 degrees Celsius or exceeds +210 degrees Celsius. TheHPA Carriers, the HPA Bias, and the Variable Attenuator is restored to normal operation, and a temperatureof +25 degrees Celsius reported while this fault is active.<HGA HPA> PSU +5VDC Bias Fail (04 1 03)DESCRIPTION : The PSU +5VDC Bias voltage fault limits is dependent upon the logic state of the Biasdiscrete. A failure is registered if the PSU +5VDC Bias voltage is outside of those limits for four consecutivereadings. This failure code shall only be applicable to the20W and 40W HPAs.PARAMETERS : PSU +5VDC Bias scaled analog voltageFAIL CRITERIA : Bias discrete OFF--state limits:PSU +5VDC Bias voltage of less than --1.0 VDC or greater than 1.0 VDC.Bias discrete ON--state limits:PSU +5VDC Bias voltage of less than 3.0 VDC or greater than 7.0 VDC.RECOVERY CRIT. : When the PSU +5VDC Bias voltage returns to within normal limits (dependent upon theBias discrete state) for four consecutive reads.REMARK : The 20W HPA power supply hardware can independently disable the +5VDC bias voltage as aprotective measure, e.g., when a short--circuit condition is detected on a secondary output voltage. This willresult in failure 04 1 03 being raised.<HGA HPA> PSU +28/+25.5 VDC Fail (04 1 04)DESCRIPTION : For the 40W Honeywell HPA, during CM, the PSU +28 VDC scaled analog value is faulted ifit exceeds its limits. For the 20W Honeywell HPA, during CM, the PSU +25.5 VDC scaled analog value isfaulted if it exceeds its limits. This fault is neitherrecorded nor annunciated by either HPA if it is detected while the respective LRU’s Power Fail Warning signal(PFW) is asserted; note that this requirement shall only be implemented in software packages subsequent toD2.0 where the 40W HPA is concerned; and subsequent to E1.0 for the 20W HPA. This failure code shallonly be applicable to the 20Wand 40W HPAs.PARAMETERS : In the 40W HPA the PSU +28 VDC scaled analog voltage is the parameter. In the 20W HPAthe PSU +25.5 VDC scaled analog voltage is the parameter.FAIL CRITERIA : For all software packages prior to as well as including D2.0, the 40W HPA shall declare afailure if the PSU +28 VDC scaled analog value is less than +20.0 VDC or greater than+30.0 VDC for four consecutive reads; in all software packages subsequent to D2.0, the upper threshold isincreased from +30.0 to +35.0 VDC. The 20W HPA shall declare a failure if the PSU +25.5 VDC scaledanalog value is not within +20% of 25.5 VDC for four consecutive reads.RECOVERY CRIT. : The 40W HPA PSU +28 VDC transitions to not failed if the scaled analog value is withinits specified limits for four consecutive reads. The 20W HPA PSU +25.5 VDC transitions to not failed if thescaled analog value is within its specified limits for fourconsecutive reads.REMARK : None<HGA HPA> PSU +5 VDC Fail (04 1 05)DESCRIPTION : During CM, the PSU +5 VDC scaled analog value is faulted if it exceeds its limits. Thisfailure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : PSU +5 VDC scaled analog voltage.FAIL CRITERIA : The 40W HPA shall (for all software packages prior to as well as including D2.0) declare afailure if the PSU +5 VDC scaled analog value is less than +4.0 VDC or greater than +7.0 VDC for fourconsecutive reads. For all software packages subsequent to D2.0 in the 40W HPA, and for all softwareversions of the 20W HPA, the upper threshold is decreasedfrom +7.0 to +6.0 VDC.RECOVERY CRIT. : The PSU +5 VDC transitions to not failed if the scaled analog value is within its specifiedlimits for four consecutive reads.<HGA HPA> PSU +15 VDC Fail (04 1 06)DESCRIPTION : During CM, the PSU +15 VDC scaled analog value is faulted if it exceeds its limits. Thisfailure code shall only be applicable to the 20W and 40W HPAs.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--55PARAMETERS : PSU +15 VDC scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the PSU +15 VDC scaled analog value is less than +10.0VDC or greater than +20.0 VDC for four consecutive readings.RECOVERY CRIT. : The PSU +15 VDC transitions to not failed if the scaled analog value is within itsspecified limits for four consecutive readings.<HGA HPA> PSU --15 VDC Fail (04 1 07)DESCRIPTION : During CM, the PSU --15 VDC scaled analog value is faulted if it exceeds its limits. Thisfailure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : PSU --15 VDC scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the PSU --15 VDC scaled analog value is less than --20VDC or greater than --10.0 VDC for four consecutive readings.RECOVERY CRIT. : The PSU --15 VDC transitions to not failed if the scaled analog value is within itsspecified limits for four consecutive readings.<HGA HPA> PSU --85 VDC Fail (04 1 08)DESCRIPTION : During CM, the 20W HPA PSU --85 VDC scaled analog value is faulted if it exceeds itslimits. This fault is neither recorded nor annunciated by the 20W HPA if it is detected while the Power FailWarning signal (PFW) is asserted. This failure code shall only be applicable to the 20W HPA.PARAMETERS : 20W HPA PSU --85 VDC scaled analog voltage.FAIL CRITERIA : The 20W HPA shall declare a failure if the PSU --85 VDC scaled analog value is less than--100 VDC or greater than --70 VDC for four consecutive readings.RECOVERY CRIT. : The 20W HPA PSU --85 VDC transitions to not failed if the scaled analog value is withinits specified limits for 4 consecutive readings.REMARKS : If the 25.5V power supply fails and is = 22.95 VDC, then a failure in the final RF Power amp(failure code 04 9 XX) may be the root cause.If any one of the +8V, +16V or the --85V power supply failures is currently active in a “low voltage” state, theroot cause may be a short circuit in the external cabling to the IGA or in the IGA itself. The definition of “lowvoltage” is as follows: = 1VDC for the +8V and +16V power supplies, and = --4VDC for the --85V powersupply.Also see failure D5 0 02.<HGA HPA> PSU +8 VDC Fail (04 1 09)DESCRIPTION : During CM, the 20W HPA PSU +8 VDC scaled analog value is faulted if it exceeds its limits.This fault is neither recorded nor annunciated by the 20W HPA if it is detected while the Power Fail Warningsignal (PFW) is asserted. This failure code shall only be applicable to the 20W HPA.PARAMETERS : 20W HPA PSU +8 VDC scaled analog voltage.FAIL CRITERIA : The 20W HPA shall declare a failure if the PSU +8 VDC scaled analog value is less than+6.5 VDC or greater than +9.5 VDC for four consecutive readings.RECOVERY CRIT. : The 20W HPA PSU +8 VDC transitions to not failed if the scaled analog value is withinits specified limits for 4 consecutive readings.REMARKS : See remarks for Failure (04 1 08).<HGA HPA> PSU +16 VDC Fail (04 1 0A)DESCRIPTION : During CM, the 20W HPA PSU +16 VDC scaled analog value is faulted if it exceeds itslimits. This fault is neither recorded nor annunciated by the 20W HPA if it is detected while the Power FailWarning signal (PFW) is asserted. This failure code shall only be applicable to the 20W HPA.PARAMETERS : 20W HPA PSU +16 VDC scaled analog voltage.FAIL CRITERIA : The 20W HPA shall declare a failure if the PSU +16 VDC scaled analog value is less than+12.0 VDC or greater than +20.0 VDC for four consecutive readings.RECOVERY CRIT. : The 20W HPA PSU +16 VDC transitions to not failed if the scaled analog value is withinits specified limits for 4 consecutive readings.REMARKS : See remarks for Failure (04 1 08).<HGA HPA> Internal Power Supply Fail (04 1 40)DESCRIPTION : During CM, the PSU “Power Good” signal is de--asserted. This fault is applicable to the60W HPA only.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--56PARAMETERS : None.FAIL CRITERIA : Two consecutive readings with “Power Good” signal de--asserted, followed by 5 secondsmore with Maximum Available Power reduced by 3 dB.RECOVERY CRIT. : The “Power Good” is asserted for 5 seconds.REMARKS : The 60W HPA will set bit 11 in its Maintenance words, indicate Failure Warning in its Status andMaintenance words, illuminate its red (fail) LED and command PA “carriers off” while this failure is active.The SDU will raise failure (04 0 0D) while bit 11 is set.<HGA HPA> PSU Over Temp (04 1 41)DESCRIPTION : During CM, the PSU temperature detector measures a value over the threshold of 89 to 94degrees celsius. This fault is applicable to the 60W HPA only.PARAMETERS : None.FAIL CRITERIA : The PSU temperature exceeds the threshold for at least 5 ms.RECOVERY CRIT. : The PSU temperature drops below the threshold for at least 5 seconds.REMARKS : The 60W HPA will set bit 13 in its Maintenance words, indicate Failure Warning in its Status andMaintenance words, report Actual Power Out = “At/Below Measurable Range” in its Status words andilluminate its red (fail) LED while this failure is active. The HPA control processor will also command carriersoff to the PA while this failure is active.HMPM: HPA Main Processor Module (SRU Code 2h)<HGA HPA> H/W--S/W Compatibility Fail (04 2 81)DESCRIPTION : A variable in the LRU header contains the Hardware/Software Compatibility bits from theUpload file stored in HPA flash memory. This variable is compared to the H/W--S/W Compatibility straps onceduring POST/PAST, and if different, a fault shall exist. The parity of the HW/SW straps shall also be checked.This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : Parameter is none. Associated parameter: H/W--S/W Compatibility straps parity=1, LRUHeader H/W--S/W Compatibility mismatch=0.FAIL CRITERIA : A failure is declared if the H/W--S/W Compatibility bits and the LRU Header H/W--S/WCompatibility value do not match.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : This failure shall cause the HPA to transition to standby mode only when tested during POST.<HGA HPA> Boot Flash Memory Fail (04 2 83/03)DESCRIPTION : During POST only, the validity of the Flash contents is determined by comparing thechecksum value calculated from the contents of the Boot Flash, with the stored checksum calculated at thetime the Flash image was built. If the values differ, then the Boot software shall not hand over to the Programsoftware, but instead transitions to standby mode where the failed test is continuously repeated. The resultsfrom POST testing ismade available for future PAST testing.Once every sixty seconds during CM, the validity of the Flash contents is determined by comparing a CRCvalue calculated from the contents of the Flash with the stored CRC value calculated at the time the Flashimage was built. The HPA shall use the 32--bit IEEE 802.3 CRC to calculate the Boot Memory CRC. If thevalues differ, a CM Boot Flash Memory fault is declared. This failure code shall only be applicable to the 20Wand 40W HPAs.PARAMETERS : During CM: Calculated CRC, stored CRC.During PP: Value of the calculated checksum for the boot code.FAIL CRITERIA : POST: This fault transitions into a failure immediately.CM: This fault transitions into a failure after four consecutive compare faults.RECOVERY CRIT. : POST: This failure is not explicitly cleared.CM: This failure shall clear after one valid CRC compare.REMARK : None<HGA HPA> A429 HPA--to--SDU Xmtr Loop--Back Fail (04 2 04)DESCRIPTION : The A429 HPA--to--SDU Xmtr is tested using the ARINC 429 loop--back receiver. An A429HPA--to--SDU Xmtr Loop--Back fault is declared if no messages are received via the loop back input. Thisfailure code shall only be applicable to the 20W and 40W HPAs.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--57PARAMETERS : Test word transmitted, test word received.FAIL CRITERIA : This fault transitions into failure after four consecutive faults are declared.RECOVERY CRIT. : This failure is not explicitly cleared.<HGA HPA> A429 SDU--to--HPA Multicnt Rcvr Fail (04 2 87)DESCRIPTION : During POST/PAST, the A429 SDU--to--HPA Multicontrol Receiver is tested using theARINC 429 loop--back transmitter. An A429 SDU--to--HPA Multicnt Rcvr fault is declared if the received worddoes not equal the test word. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure after four consecutive faults are declared.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : None<HGA HPA> A429 ADL--to--HPA Rcvr Fail (04 2 88)DESCRIPTION : During POST/PAST, the A429 ADL--to--HPA Receiver is tested using the ARINC 429loop--back transmitter and a test word. An A429 ADL--to--HPA Rcvr fault is declared if the received word doesnot equal the test word. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure after four consecutive faults are declared.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : None<HGA HPA> A429 PDL--to--HPA Rcvr Fail (04 2 89)DESCRIPTION : During POST/PAST, the A429 PDL--to--HPA Receiver is tested using the ARINC 429loop--back transmitter and a test word. An A429 PDL--to--HPA Rcvr fault is declared if the received word doesnot equal the test word. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure after four consecutive faults are declared.RECOVERY CRIT. : This failure is not explicitly cleared.<HGA HPA> Maintenance Memory CRC Fail (04 2 0A)DESCRIPTION : During POST/PAST, each maintenance memory record is checked to verify its CRC iscorrect. The HPA shall use the 32--bit IEEE 802.3 CRC to calculate the Maintenance Memory CRC. A fault isdeclared if the calculated CRC does not match the CRC stored with each record. This failure code shall onlybe applicable to the 20W and 40W HPAs.PARAMETERS : The failed Flash device (HI or LO).FAIL CRITERIA : This fault transitions into a failure after four consecutive faults are declared.RECOVERY CRIT. : There is no explicit clearing of this failure.<HGA HPA> Maintenance Memory Write Fail (04 2 0B)DESCRIPTION : A Maintenance Memory Write fault shall exist if the programming or erase operations fail.This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : None.FAIL CRITERIA : This fault transitions into a failure after four consecutive faults are declared.RECOVERY CRIT. : This failure is not explicitly cleared.<HGA HPA> Calibration Memory CRC Fail (04 2 8C/0C)DESCRIPTION : At the time of calibration, a CRC is computed over the range of calibration memory used.The resulting CRC is stored in an adjacent area of calibration memory. During POST/PAST and once every60 seconds, the CRC of the calibration memory iscomputed and compared to the stored value. The HPA shall use the 32--bit IEEE 802.3 CRC to calculate theCalibration Memory CRC. A fault is declared if the two CRCs are different. This failure code shall only beapplicable to the 20W and 40W HPAs.PARAMETERS : None.FAIL CRITERIA : This fault transitions into a failure after one miscomparison.RECOVERY CRIT. : This failure is cleared after one successful comparison.<HGA HPA> Calibration Memory Write Fail (04 2 0D)DESCRIPTION : A calibration memory write fault shall exist if the calibration Flash programming or eraseoperations fail. This failure code shall only be applicable to the 20W and 40W HPAs.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--58PARAMETERS : None.FAIL CRITERIA : This fault transitions into a failure after four consecutive faults are declared.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : None<HGA HPA> Program Flash Memory Fail (04 2 8E/0E)DESCRIPTION : During POST only, the validity of the Program Flash contents is determined by comparing achecksum value calculated from the contents of the Flash, with the stored checksum value calculated at thetime the Flash image was built. If the values differ, thenthe Boot software shall not hand over to the Program software, but instead transitions to standby mode wherethe failed test is continuously repeated. The results from POST testing is made available for future PASTtesting.Once every 60 seconds during CM, the validity of the Flash contents is determined by comparing a CRCvalue calculated from the contents of the Flash with the stored CRC value calculated at the time the Flashimage was built. The HPA shall use the 32--bit IEEE 802.3 CRC to calculate the Program Memory CRC. If thevalues differ, a CM Program Flash Memory fault is declared. This failure code shall only be applicable to the20W and 40W HPAs.PARAMETERS : During CM: Calculated CRC, stored CRC.During PP: Value of the calculated checksum for the program code.FAIL CRITERIA : POST: This fault transitions into a failure immediately.CM: This fault transitions into a failure after four consecutive compare faults.RECOVERY CRIT. : POST: This failure is not explicitly cleared.CM: This failure shall clear after one valid CRC compare.<HGA HPA> RAM Fail (04 2 90)DESCRIPTION : It is required that all volatile memory be tested to determine that every byte of RAM isaddressable and can correctly store data. Testing shall include all address combinationsand exercise each bit by storing both high (Logic ’1’) and low (Logic ’0’). Each location is shown to retain itscontent while all other locations are written to. The protected area at the end of RAM is not tested in order topreserve data passed between Boot software and Program software. Since the RAM test is destructive, thetest is performed only during POST testing, and transitions to standby mode where the failed test iscontinuously repeated. The results from POST testing is made available for future PAST testing. This failurecode shall only be applicable to the 20W and 40W HPAs.PARAMETERS : None.FAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.<HGA HPA> CPU Over Temp Shutdown (04 2 11)DESCRIPTION : During CM (for all software packages prior to as well as including D2.0), the 40W HPA’sCPU temperature is tested four times per second, and a fault is declared if it equals or exceeds +130 degreesCelsius; for all 40W HPA software packages subsequentto D2.0, and for all software versions of the 20W HPA, the maximum value threshold is increased from +130to +133 degrees Celsius. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : CPU temperature sensor scaled analog output value, shutdown temperature limit.FAIL CRITERIA : A failure is declared if the CPU temperature sensors’s scaled analog output value is greaterthan or equal to the specified fault threshold for four consecutive readings.RECOVERY CRIT. : The failure is cleared (by all software packages prior to as well as including D2.0) if afterfour consecutive readings, the 40W HPA’s CPU temperature sensor scaled analog output value is less than+130 degrees Celsius; for all 40W HPA software packages subsequent to D2.0, and for all software versionsof the 20W HPA, the temperature threshold is decreased from +130 to +125 degrees Celsius.REMARK : The HPA shall set bit 13 and indicate Failure Warning in its Maintenance words while this failure isactive. The HPA Carriers is set to OFF, the HPA Bias voltage is setto OFF, and the Variable Attenuator is set to maximum while this failure is active.<HGA HPA> CPU Temp Sensor Fail (04 2 12)DESCRIPTION : This fault is declared if (during CM) the reported CPU temperature is either less than --90degrees Celsius or greater than +210 degrees Celsius. This failure code shall only be applicable to the 20Wand 40W HPAs.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--59PARAMETERS : CPU temperature sensor scaled analog output value.FAIL CRITERIA : CPU temperature sensor scaled analog output value is either less than --90 degreesCelsius or greater than +210 degrees Celsius for four consecutive readings.RECOVERY CRIT. : CPU temperature sensor scaled analog output value is greater than or equal to --90degrees Celsius and less than or equal to +210 degrees Celsius for four consecutivereadings.REMARK : It is assumed that the CPU temperature sensor is faulty if the reported CPU temperature is eitherless than --90 degrees Celsius or exceeds +210 degrees Celsius. The HPA Carriers, the HPA Bias voltage,and the Variable Attenuator voltage is restored to normal operation, and a temperature of +25 degreesCelsius reported while this failure is active.<HGA HPA> CPU Gnd Ref Fail (04 2 93/13)DESCRIPTION : During CM, CPU Gnd Ref scaled analog value is faulted if it exceeds its limits. This failurecode shall only be applicable to the 20W and 40W HPAs.PARAMETERS : CPU Gnd Ref scaled analog value.FAIL CRITERIA : The HPA shall declare a failure if the CPU Gnd Ref scaled analog value is less than --0.3VDC or greater than +0.3 VDC for four consecutive readings.RECOVERY CRIT. : The CPU Gnd Ref transitions to not failed if the scaled analog value is within itsspecified limits for four consecutive readings.REMARK : None<HGA HPA> Fan Relay Driver Fail (04 2 94/14)DESCRIPTION : The Fan Relay Driver voltage fault limits is dependent upon the logic state of the Fandiscrete. A failure is registered if the Fan Relay Driver voltage is outside of those limits for four consecutivereadings. This failure code shall only be applicable to the 40W HPA.PARAMETERS : HMPM Fan discrete, Fan Relay Driver scaled analog voltage.FAIL CRITERIA : Fan discrete OFF state limit:Fan Relay Driver voltage of less than 8.0 VDC.Fan discrete ON state limit:Fan Relay Driver voltage greater than 12.0 VDC.RECOVERY CRIT. : When the Fan Relay Driver voltage returns to within normal limits dependent upon theBias discrete state for four consecutive reads.REMARK : None<HGA HPA> Bias Enable Loop--back Fail (04 2 95/15)DESCRIPTION : The Bias Enable discrete is measured at the loop--back discrete input, and a fault isdeclared if the loop--back discrete value does not match the last Bias Enable value set. This failure code shallonly be applicable to the 20W and 40W HPAs.PARAMETERS : During CM: Carriers off: parameter=0; assoc. parameter=1.Carriers on: parameter=1; assoc. parameter=0.Parameter during PP: Concatenated HPACPU and Arinc429 discrete input words. Upper 16 bits contain thearinc port discrete input word. Lower 16 bits contain the hw/sw port discrete input word.Assoc. parameter during PP: Mux port discrete input word.FAIL CRITERIA : POST/PAST:The Bias Enable discrete is set to 1. The discrete loop--back is read, and a failure is declared if the BiasEnable discrete value does not equal the loop--back value.CM: As the Bias Enable is set, the loop--back discrete value is compared to theBias Enable. A failure is declared if the Bias Enable value does not equal the discrete loop--back value.RECOVERY CRIT. : POST/PAST:This failure is not explicitly cleared.CM: This failure transitions to not failed after four successful comparisons.REMARK : None<HGA HPA> Var Atten Driver Fail (04 2 96/16)DESCRIPTION : During POST/PAST, the Bias voltage is set to off and the DAC output set to 0fffh (for +10.0VDC out), 0800h (for +5.0 VDC out), and 007h (for +17 mVDC out). A fault is declared if the Var Atten Drivervoltage is not the voltage specified (plus or minus 10 mVDC).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--60During CM, a fault is declared if the Variable Attenuator Driver voltage, as measured at the analog loop--backinput, is not within the range of the voltage specified plus or minus 10 mVDC.A fault is declared if the Variable Attenuator Driver analog value exceeds the absolute limits of less than --0.7mVDC or greater than +18.0 VDC.This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : Parameter: Variable Attenuator Driver scaled analog output value.Associated parameter: 2 possible values 0x00050000 = DAC output was set to +5.0 VDC out0x000A0000 = DAC output was set to +10.0 VDC out.FAIL CRITERIA : POST: This fault transitions into a failure immediately.CM: A failure is declared if the Variable Attenuator Driver scaled analog value exceeds its limits for fourconsecutive readings.RECOVERY CRIT. : POST: This failure is not explicitly cleared.CM: The Variable Attenuator Driver transitions to not failed if the scaled analog value is within its specifiedlimits for four consecutive readings.<HGA HPA> Front Panel Test Switch Stuck (04 2 17)DESCRIPTION : A fault is declared if the Front Panel Test Switch is stuck in the depressed state. The switchis considered stuck if it is detected as depressed for the entire duration of PAST, including the 30 seconddisplay of the PAST results. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : None.FAIL CRITERIA : A failure is declared if (after the 30 second display of PAST results) the Front Panel TestSwitch is closed for 5 consecutive readings of the discrete.RECOVERY CRIT. : The failure transitions to not failed if the Front Panel Test switch is in the open positionfor 5 consecutive readings of the discrete.<HGA HPA> Watchdog Timeout Fail (04 2 98)DESCRIPTION : When the HPA receives a hardware reset, the discrete input WDO (WatchDog Output) istested. If the WDO discrete is TRUE, a Watchdog timeout fault is recorded. This failure code shall only beapplicable to the 20W and 40W HPAs.PARAMETERS : None.FAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : For Packages prior to E1.0, this failure is not explicitly cleared. For Package E1.0 andlater software, this failure is cleared immediately.<HGA HPA> Driver Gnd Fail (04 2 19)DESCRIPTION : During CM, Driver Gnd scaled analog value is faulted if it exceeds its limits. This failurecode shall only be applicable to the 20W and 40W HPAs.PARAMETERS : Driver Gnd scaled analog value.FAIL CRITERIA : The HPA shall declare a failure if the Driver Gnd scaled analog value is less than --1.0 VDCor greater than +1.0 VDC for four consecutive readings.RECOVERY CRIT. : The Driver Gnd transitions to not failed if the scaled analog value is within its specifiedlimits for four consecutive readings.REMARK : This fault is raised after the ensuing processor reset.<HGA HPA> Driver Test -- Mux (04 2 9C/1C)DESCRIPTION : The Analog Multiplexer Status is a partially decoded version of the Analog MultiplexerChannel Latch output. During POST/PAST, the Analog Multiplexer Latch address bits are sequentiallytoggled. A fault is recorded if the Analog Multiplexer Status’ bits do not match the Analog Multiplexer Latchbits. This failure code shall only be applicable to the 20W and 40W HPAs.During CM, the Analog Multiplexer Status bits shall match those of the most recent Analog MultiplexerChannel Latch.PARAMETERS : Parameter during CM: Analog Multiplexer Status bits, Analog Multiplexer bits.Parameter during PP: Concatenated HPACPU and Arinc429 discrete input words. Upper 16 bits contain thearinc port discrete input word. Lower 16 bits contain the hw/sw port discrete input word.Assoc. parameter during PP: Mux port discrete input word.FAIL CRITERIA : POST/PAST:This fault transitions into a failure immediately.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--61CM:This fault transitions into a failure after four consecutive mismatches.RECOVERY CRIT. : POST/PAST:This failure is not explicitly cleared.CM:This failure shall clear after four consecutive correct matches.<HGA HPA> Driver Test -- Green LED (04 2 9D)DESCRIPTION : During POST/PAST the Green LED is turned on and off with a 2.0 +/-- 1 Hz frequency, withthe ratio of on--time to off--time equal to .5 +/-- .25. In the 40W HPA (for all software packages prior to as wellas including D2.0), the discrete loop--back is read, and afailure is declared if the Green LED Driver discrete value does not equal the loopback value. For all softwarepackages subsequent to D2.0 in the 40W HPA, and for all software versions of the 20W HPA, this test is notimplemented. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : Parameter: Concatenated HPACPU and Arinc429 discrete input words. Upper 16 bitscontain the arinc port discrete input w=rd. =ower 16 bits contain the hw/sw port discrete input word.Assoc. parameter: Mux port discrete input word.FAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : The Green LED indicator on the front of the HPA is tested by turning on and off. No results arerecorded by the HPA, therefore operator observation is required to detect an indicatorfailure.<HGA HPA> Driver Test -- Red LED (04 2 9E)DESCRIPTION : During POST/PAST, the Red LED is turned on and off with a 2.0 +/-- 1 Hz frequency, withthe ratio of on--time to off--time equal to .5 +/-- .25. In the 40W HPA (for all softwarepackages prior to as well as including D2.0), the discrete loop--back is read, and a failure is declared if theRed LED Driver discrete value does not equal the loop--back value.For all software packages subsequent to D2.0 in the 40W HPA, and for all software versions of the 20W HPA,this test is not implemented. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : Parameter: Concatenated HPACPU and Arinc429 discrete input words. Upper 16 bitscontain the arinc port discrete input word. Lower 16 bits contain the hw/sw port discreteinput word.Assoc. parameter: Mux port discrete input word.FAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : The Red LED indicator on the front of the HPA is tested by turning on and off. No results arerecorded by the HPA, therefore operator observation is required to detect an indicatorfailure.<HGA HPA> Driver Test -- Mute Atten (04 2 A0)DESCRIPTION : During POST/PAST, the discrete loop--back is read, and a failure is declared if the MuteAttenuator Driver discrete value does not equal the loop--back value. This failure code shall only be applicableto the 20W and 40W HPAs.PARAMETERS : Failure Parameter: Two types of inputs:1) Concatenated Top Mute Discrete Input Word and the Starboard Mute Discrete Input Word. Upper 16 bitscontain the Starboard Mute Discrete Input word. Lower 16 bits contain the top Mute Discrete Input Word.2) Concatenated HPACPU and Arinc429 discrete input words. Upper 16 bits contain the arinc port discreteinput word. Lower 16 bits contain the hw/sw port discrete input word.Associated failure parameter: Two types of inputs:1) Values used to distinguish types of mute test. Possible values are 0--3, 5--7. Mute test 4can be ignored.2) Mux port discrete input word.FAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : NoneRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--62<HGA HPA> Driver Test -- Ser Data Concatenate (04 2 A2)DESCRIPTION : During POST/PAST, the discrete loop--back is read, and a failure is declared if the SerialData Concatenate discrete value does not equal the loop--back value. This failure code shall only beapplicable to the 20W and 40W HPAs.PARAMETERS : Parameter: Concatenated HPACPU and Arinc429 discrete input words. Upper 16 bitscontain the arinc port discrete input word. Lower 16 bits contain the hw/sw port discrete input word.Assoc. parameter: Mux port discrete input word.FAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : None<HGA HPA> Mute Input Test (04 2 A5)DESCRIPTION : During POST/PAST, the BSU Mute Buffers is tested by writing the INPUTS and verifying theOUTPUTS. During these tests the Variable Attenuator is set to maximum attenuation. The software shall setthe inputs (”Mute test data bit 1” and “Mute test data bit 2”) low while the buffers are not being tested so thatthe buffers will receive BSU mute data. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS :FAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : None<HGA HPA> CPU Device Test (04 2 A6)DESCRIPTION : The CPU is tested by executing selected instruction sets, which shall exercise the internalpathways of the INTEL 80C186 device. The outputs is compared to predefined results, and if in error, a faultshall exist. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : None.FAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : None<HGA HPA> Actual Power Calibration (04 2 A7)DESCRIPTION : The criteria for valid calibration data is as follows:1. The CRC for the calibration data must be valid.2. Actual Power 1 and Actual Power 2 tables must have at least 3 entries in eachtable.3. The entries for Forward Power--volts and Forward Power--watts in the Actual Power 1 and Actual Power 2tables shall increase monotonically, whereby each table data point is larger than the previous one.4. Attenuator Cal table shall have at least 20 entries.5. Attenuator Cal table shall increase monotonically.If upon hardware reset the Actual Power calibration tables are found to be invalid, the default calibrationtables is used and a fault declared. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : Parameter: 3 possible values.1 -- Fault related to Power Table 12 -- Fault related to Power Table 23 -- Fault related to Attenuator TableAssociated Parameters: 3 possible values0 -- Used in conjunction with failure parameter of 1 (calibrated with different software, version failure).-- used in conjunction with failure parameter of 3 (There has to be > 20 entries in the attenuator table).11 -- Used in conjunction with failure parameter of 1 (Values are not monotonically increasing in PowerTable 1).-- used in conjunction with Failure parameter of 2 (Values are not monotonically increasing in PowerTable 2).12 -- Used in conjunction with failure parameter of 1 (there has to be >= 3 entries in Power Table 1).-- Used in conjunction with Failure parameter of 2 (there has to be >= 3 entries in power Table 2).FAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : NoneRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--63<HGA HPA> Validation Of Upload (04 2 A8)DESCRIPTION : The following items is validated when new application software is loaded:1. The first two bytes of each LRU/SRU header record shall indicate a valid record type for the record positionin the data sequence.2. The company name in the LRU header record is HONEYWELL/RACAL.3. The LRU name and base part number shall match the current LRU specification.4. The LRU Hardware/Software Compatibility strap, as read by the processor, shall match one of theHardware/Software Compatibility straps contained in the list in the LRU Header record of the software uploadfile.5. The SRU name is valid for the named LRU.6. The start address within an LRU/SRU Record shall represent a valid target storage address of theProgram Store.A fault is declared, and the HPA transitioned into Standby mode, if the Upload does not validate. This failurecode shall only be applicable to the 20W and 40W HPAs.PARAMETERS : None.FAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : The Validation of Upload test occurs only at the time of an upload of application software.The invalid code is rejected and the HPA transitioned into standby mode. When theADL/PDL link is cleared, the HPA will attempt to run the application software residing inflash memory if application code is present.<HGA HPA> Mute Atten P Out Of Limits (04 2 29)DESCRIPTION : The Mute Attenuator voltage fault limits is dependent upon whether or not muting isselected. A failure is registered if the Mute Attenuator voltage is outside of those limits for four consecutivereadings. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : Mute Atten P scaled analog voltage.FAIL CRITERIA : Muted state limit:Mute Atten P voltage of >= 5.0 VDC.Not muted state limit:Mute Atten P voltage <= --5.0 VDC.RECOVERY CRIT. : When Mute Atten P voltage returns to within normal limits dependent upon the Mutediscrete state for four consecutive reads.REMARK : None<HGA HPA> Code VPP Out Of Limits (04 2 2A)DESCRIPTION : The Code VPP voltage fault limits is dependent upon the state of the ADL/PDL Link. Afailure is registered if the Code VPP voltage is outside of those limits for four consecutive readings. Thisfailure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : Code VPP scaled analog voltageFAIL CRITERIA : Active state limit:Code VPP voltage of less than 11.5 VDC or greater than 12.7 VDC.Inactive state limit:Code VPP voltage of less than --2.0 VDC or greater than 9.0 VDC.RECOVERY CRIT. : When Code VPP voltage returns to within normal limits (dependent upon the ADL/PDLLink state) for four consecutive reads.REMARK : None<HGA HPA> Maint Log VPP Out Of Limits (04 2 2B)DESCRIPTION : A failure is registered if the Maint Log VPP voltage is outside of its limits for fourconsecutive readings. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : Maint Log VPP scaled analog voltage.FAIL CRITERIA : Maint Log VPP voltage of less than 11.5 VDC or greater than 12.7 VDC.RECOVERY CRIT. : When Maint Log VPP voltage returns to within normal limits for four consecutive reads.REMARK : NoneRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--64<HGA HPA> Cal Mem VPP Out Of Limits (04 2 2C)DESCRIPTION : A fault is registered if the Cal Mem VPP voltage is outside its specified limits. This failurecode shall only be applicable to the 20W and 40W HPAs.PARAMETERS : Cal Mem VPP scaled analog voltage.FAIL CRITERIA : A failure is declared if the Cal Mem VPP voltage of less than --2.0 VDC or greater than+12.7 VDC for four consecutive readings.RECOVERY CRIT. : When Cal Mem VPP voltage returns to within normal limits (dependent upon the CalMem Enable discrete) state for four consecutive reads.REMARK : None<HGA HPA> ADC Ref Out Of Limits (04 2 AD/2D)DESCRIPTION : ADC Ref scaled analog value is faulted if it exceeds its limits. This failure code shall only beapplicable to the 20W and 40W HPAs.PARAMETERS : ADC Ref scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the ADC Ref scaled analog value is less than +4.5 VDCor greater than +5.5 VDC for four consecutive readings.RECOVERY CRIT. : The ADC Ref transitions to not failed if the scaled analog value is within its specifiedlimits for four consecutive readings.REMARK : None<HGA HPA> Power LO Out Of Limits (04 2 2E)DESCRIPTION : During CM, Power LO scaled analog value is faulted if it exceeds its limits. This failure codeshall only be applicable to the 20W and 40W HPAs.PARAMETERS : Power LO scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Power LO scaled analog value is less than --1.0 VDCor greater than +1.0 VDC for four consecutive readings.RECOVERY CRIT. : The Power LO transitions to not failed if the scaled analog value is within its specifiedlimits for four consecutive readings.REMARK : None<HGA HPA> PSU Temp LO Out Of Limits (04 2 2F)DESCRIPTION : During CM, PSU Temp LO scaled analog value is faulted if it exceeds its limits. This failurecode shall only be applicable to the 20W and 40W HPAs.PARAMETERS : PSU Temp LO scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the PSU Temp LO scaled analog value is less than --1.0VDC or greater than +1.0 VDC for four consecutive readings.RECOVERY CRIT. : The PSU Temp LO transitions to not failed if the scaled analog value is within itsspecified limits for four consecutive readings.REMARK : None<HGA HPA> Amps LO Out Of Limits (04 2 30)DESCRIPTION : During CM, Amps LO scaled analog value is faulted if it exceeds its limits. This failure codeshall only be applicable to the 20W and 40W HPAs.PARAMETERS : Amps LO scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Amps LO scaled analog value is less than --1.0 VDCor greater than +1.0 VDC for four consecutive readings.RECOVERY CRIT. : The Amps LO transitions to not failed if the scaled analog value is within its specifiedlimits for four consecutive readings.REMARK : None<HGA HPA> Software Fault (04 2 31)DESCRIPTION : A software fault is activated when a divide--by--zero or overflow error occurs in the floatingpoint operations. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : FFFFFFFFh for overflow error; 0 for divide by zero error.FAIL CRITERIA : This fault transitions into a failure immediately.RECOVERY CRIT. : For Packages prior to D2.1, this failure is not explicitly cleared. For Packages D2.1andlater, this failure is cleared immediately.REMARK : This fault is raised after the ensuing processor reset.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--65<HGA HPA> Discrete Output Test -- Fan (04 2 B3/33)DESCRIPTION : During POST/PAST, the discrete loop--back is read, and a failure is declared if the Fandiscrete value does not equal the loop--back value.During CM, the discrete loop--back is read, and a failure is declared if the Fandiscrete value does not equal the loop--back value.This failure code shall only be applicable to the 40W HPA.PARAMETERS : None.FAIL CRITERIA : POST/PAST:This fault transitions into a failure immediately.CM:This fault transitions into a failure after four consecutive mismatches.RECOVERY CRIT. : POST/PAST:This failure is not explicitly cleared.CM:This failure shall clear after four consecutive correct matches.REMARK : None<HGA HPA> RS--422 Internal Loopback Fail (04 2 B4)DESCRIPTION : This fault shall only be applicable to the 20W HPA (with IGA beam steering capabilities).During POST/PAST, the 82510 asynchronous serial controller is placed into internal loopback mode. A singlecharacter is transmitted and subsequently looped back tothe receive port, and the received and transmitted characters is compared; this is done four times. All fourtests must fail for this fault to be declared.PARAMETERS : Parameter: Transmitted Loopback character.Associated parameter: Received Loopback character.FAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : This failure is not explicitly cleared.REMARK : Declaration of this failure means that the 20W Honeywell HPA is not able to control anHPA--beam--steered IGA; however, this is only significant if such an IGA is installed. Ratherthan requiring the class and functional resource indictment of this failure to beconfiguration--dependent, the class is fixed at 3, no resource is indicted, and failure 1A 0 01(Top/Port HGA/IGA Maintenance Word Fail, which will subsequently trigger as well, and which isconfiguration dependent and is Class 1 and does indict [hga_subsys] if another antenna subsystem isinstalled) is depended upon to bring this condition to a class 1 level of awareness and to cause functionalresource--dependent reconfiguration to take place as necessary. If thisoccurs, the existence of failure 04 2 B4 will point to the HPA as a (if not the) cause of the Maintenance WordFail condition.<HGA HPA> IGA LNA/DIP On/Off Discrete Loopback Fail (04 2 35)DESCRIPTION : This fault shall only be applicable to the 20W HPA (with IGA beam steering capabilities).During CM, the loopback of the LNA/DIP on/off discrete output is compared with the commanded value. Afault is declared if the loopback logic state does not match the commanded state.PARAMETERS : LNA/DIP command wrap around discrete; commanded value.FAIL CRITERIA : For Packages prior to and not including D2.1, this fault transitions to a failure after fourconsecutive mismatches. For Package D2.1 and later software, This fault transitions to a failure after twelveconsecutive mismatches.RECOVERY CRIT. : For Packages prior to and not including D2.1, this failure shall clear after fourconsecutive matches. For Package D2.1 and later software, This failure shall clear immediately after onematch.REMARK : This test does not need to be performed during POST/PAST because of the system--widefunctional test, which toggles the LNA/DIP control in order to check whether the receivenoise floor rises when the LNA is turned on.<HGA HPA> I2C Interface Failure (04 2 C0)DESCRIPTION : During PP, the control processor fails to communicate with the backplane unit configurationor control processor discrete input devices on the I2C bus. This failure code shall only be applicable to the60W HPA.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--66PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly clearedREMARKS : The 60W HPA cannot transmit any words but does illuminate its red (fail) LED while this failureis active. This failure cannot be transferred to the SDU, although the Kernel maintenance and data loaderinterfaces are activated. This failure is also not recorded in the HPA failure log and can only be observed viathe Kernel maintenance interface.The SDU will raise a bus inactive failure (5C 0 01).<HGA HPA> RAM Failure (04 2 C1/41)DESCRIPTION : The CRC check of the application image in RAM fails. This failure code shall only beapplicable to the 60W HPA.PARAMETERS : Failure parameter:CM: None.PP: Address of faulty memory word.Associated parameter:CM: None.PP: Number of failed attempts.FAIL CRITERIA : This fault transitions to a failure after a retry of the CRC check also fails.RECOVERY CRIT. : This failure is never explicitly cleared.REMARKS : The 60W HPA will set bit 16 in its Maintenance words, indicate Failure Warning in its Status andMaintenance words and illuminate its red (fail) LED while this failure is active.For the PP case only, this failure cannot be transferred to the SDU, although the Kernel maintenance anddata loader interfaces are activated.The SDU will raise failure (04 0 0E) while bit 16 is set.<HGA HPA> Kernel Code Error (04 2 C2)DESCRIPTION : During PP, the CRC check of the Kernel code fails. This failure code shall only be applicableto the 60W HPA.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARKS : The 60W HPA will set bit 17 in its Maintenance words, indicate Failure Warning in its Status andMaintenance words and illuminate its red (fail) LED while this failure is active. This failure cannot betransferred to the SDU, although the Kernel maintenance and data loader interfaces are activated.The SDU will raise failure (04 0 0F) while bit 17 is set.<HGA HPA> Application Code Error (04 2 C3)DESCRIPTION : During PP, the CRC check of the Application code fails. This failure code shall only beapplicable to the 60W HPA.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARKS : The 60W HPA will set bit 17 in its Maintenance words, indicate Failure Warning in its Status andMaintenance words and illuminate its red (fail) LED while this failure is active. This failure cannot betransferred to the SDU, although the Kernel maintenance and data loader interfaces are activated.The SDU will raise failure (04 0 0F) while bit 17 is set.<HGA HPA> Configuration Error (04 2 C4)DESCRIPTION : During PP, the hardware/software compatibility check of the Kernel or Application code fails.This failure code shall only be applicable to the 60W HPA.PARAMETERS : 0 = Kernel / hardware incompatibility1 = Application / hardware incompatibilityFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--67REMARKS : The 60W HPA will set bit 17 in its Maintenance words, indicate Failure Warning in its Status andMaintenance words and illuminate its red (fail) LED while this failure is active. This failure cannot betransferred to the SDU, although the Kernel maintenance and data loader interfaces are activated. The SDUwill raise failure (04 0 0F) while bit 17 is set.<HGA HPA> SDU Bus Interface Failure (04 2 C5)DESCRIPTION : During PP, the loopback test of the SDU input/output fails. This failure code shall only beapplicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after 2 out of 3 loopback tests fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARKS : The 60W HPA cannot transmit any words, therefore, this failure cannot be transferred to theSDU, but its red (fail) LED is illuminated and the Kernel maintenance and data loader interfaces are activated.The SDU will raise a bus inactive failure (5C 0 01).<HGA HPA> ADL Bus Interface Failure (04 2 C6)DESCRIPTION : During PP, the loopback test of the ADL input/output fails. This failure code shall only beapplicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after 2 out of 3 loopback tests fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARKS : None<HGA HPA> PDL Bus Interface Failure (04 2 C7)DESCRIPTION : During PP, the loopback test of the PDL input/output fails. This failure code shall only beapplicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after 2 out of 3 loopback tests fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARKS : None<HGA HPA> Maintenance DUART Failure (04 2 C8)DESCRIPTION : During PP, the loopback test of the maintenance port fails. This failure code shall only beapplicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after 2 out of 3 loopback tests fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARKS : The 60W HPA maintenance interface will not be functional.<HGA HPA> Discrete Output Failure (04 2 C9/49)DESCRIPTION : The control processor receives no response from the discrete outputs device. This failurecode shall only be applicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after 2 out of 3 communication attempts fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARKS : None<HGA HPA> Control Processor Temp Sensor Failure (04 2 CA/4A)DESCRIPTION : The control processor receives no response from the control processor board temperaturesensor. This failure code shall only be applicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after 2 out of 3 communication attempts fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARKS : If both the CP and BP temp sensors are non--responsive, the 60W HPA will indicate FailureWarning in its Status and Maintenance words and illuminate its red (fail) LED while this failure is active. TheKernel maintenance and data loader interfaces are activated otherwise the application software is inactive.The SDU will raise failure (04 0 0C) while SSM=FW and no DISCRETES bits set. If only the CP temp sensoris non--responsive, the BP temp sensor is used for temp monitoring.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--68<HGA HPA> Board Config/Rev Failure (04 2 CB)DESCRIPTION : During PP, the control processor receives no response from the board config/rev device.This failure code shall only be applicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after 2 out of 3 communication attempts fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARKS : If the software is sensitive to board config/rev, the 60W HPA will indicate Failure Warning in itsStatus and Maintenance words and illuminate its red (fail) LED while this failure is active. The Kernelmaintenance and data loader interfaces are activated, otherwise the application software is inactive. TheSDU will raise failure (04 0 0C) while SSM=FW and no DISCRETES bits set.<HGA HPA> I2C Interface Failure (04 2 4C)DESCRIPTION : During CM, the control processor fails to communicate with the power amplifier (PA),discrete output devices and temperature sensors on the I2C bus. This failure code shall only be applicable tothe 60W HPA.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure after two attempts to reset the I2C bus.RECOVERY CRIT. : This failure is never explicitly clearedREMARKS : The 60W HPA will indicate Failure Warning in its Status and Maintenance words and illuminateits red (fail) LED while this failure is active. The application software effectively becomes inactive since theCP cannot control the PA. The SDU will raise failure (04 0 0C) while SSM=FW and no DISCRETES bits set.<HGA HPA> ROM Failure (04 2 4D)DESCRIPTION : During CM, the CRC check of the configuration information stored in EEPROM or Flashfails. This failure code shall only be applicable to the 60W HPA.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure after a retry of the CRC check also fails.RECOVERY CRIT. : This failure is never explicitly clearedREMARKS : The 60W HPA will set bit 17 in its Maintenance words, indicate Failure Warning in its Status andMaintenance words and illuminate its red (fail) LED while this failure is active. The SDU will raise failure (04 00F, while bit 17 is set.DRIV: HPA RF Driver (SRU Code 3h)<HGA HPA> Driver RF Output Fail (04 3 01)DESCRIPTION : During CM, Driver Pwr HI scaled analog value is faulted if it exceeds its limits. This failurecode shall only be applicable to the 40W HPA.PARAMETERS : Driver Pwr HI scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Driver Pwr HI scaled analog value is less than --1.0VDC or greater than +6.0 VDC for four consecutive readings.RECOVERY CRIT. : The Driver Pwr HI transitions to not failed if the scaled analog value is within its specifiedlimits for four consecutive readings.REMARK : None<HGA HPA> Driver Temp Sensor Fail (04 3 02)DESCRIPTION : This fault is declared if (during CM) the reported Driver temperature is either less than --90degrees Celsius or greater than +210 degrees Celsius. This failure code shallonly be applicable to the 40W HPA.PARAMETERS : Driver temperature sensor scaled analog voltage.FAIL CRITERIA : Driver temperature sensor scaled analog output value is either less than --90 degreesCelsius or greater than +210 degrees Celsius for four consecutive readings.RECOVERY CRIT. : Driver temperature sensor scaled analog output value is greater than or equal to --90degrees Celsius and less than or equal to +210 degrees Celsius for four consecutive readings.REMARK : It is assumed that the Driver temperature sensor is faulty if the reported Drivertemperature is either less than --90 degrees Celsius or exceeds +210 degrees Celsius. The HPA Carriers, theHPA Bias, and the Variable Attenuator is restored to normal operation, and a temperature of +25 degreesCelsius reported while this fault is active.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--69<HGA HPA> Driver Over Temp Shutdown (04 3 03)DESCRIPTION : During CM (for all software packages prior to as well as including D2.0), the Drivertemperature is tested four times per second, and fault is declared if it equals orexceeds the maximum value of +130 degrees Celsius; for all software packages subsequent to D2.0, themaximum value threshold is increased from +130 to +133 degrees Celsius. This failure code shall only beapplicable to the 40W HPA.PARAMETERS : Driver temperature sensor scaled analog voltage, shutdown temperature limit.FAIL CRITERIA : A failure is declared if the Driver temperature sensor output scaled analog value is greaterthan or equal to the specified fault threshold for four consecutive readings.RECOVERY CRIT. : The failure is cleared (by all software packages prior to as well as including D2.0) if afterfour consecutive readings the Driver temperature sensor scaled analog output is less than +130 degreesCelsius; for all software packages subsequent to D2.0, the temperature threshold is decreased from +130 to+125 degrees Celsius.REMARK : The HPA shall set bit 13 and indicate Failure Warning in its Maintenance words while this failure isactive. The HPA Carriers is set to OFF, the HPA Bias voltage is setto OFF, and the Variable Attenuator is set to maximum while this failure is active.<HGA HPA> Driver VCC Fail (04 3 04)DESCRIPTION : During CM, Driver VCC scaled analog value is faulted if it exceeds its limits. This failurecode shall only be applicable to the 40W HPA.PARAMETERS : Driver VCC scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Driver VCC scaled analog value is less than 50percent of the PSU +15 VDC scaled analog value for four consecutive readings.RECOVERY CRIT. : The Driver VCC transitions to not failed if the scaled analog value is within its specifiedlimits for four consecutive readings.REMARK : NonePWR1: HPA RF Power Amplifier (1) (SRU Code 5h)<HGA HPA> Amp 1 RF Balance Fail (04 5 01)DESCRIPTION : During CM, the Amp1 RF Balance Error scaled analog value is faulted if it exceeds its limits.This failure shall only be raised when a single RF carrier is operating. Thisfailure code shall only be applicable to the 40W HPA.PARAMETERS : Amp1 RF Balance Error scaled analog value.FAIL CRITERIA : The HPA shall declare a failure if the Amp1 RF Balance Error scaled analog value isgreater than +3.0 VDC for four consecutive readings.RECOVERY CRIT. : The Amp1 RF Balance Error transitions to not failed if the scaled analog value is withinits specified limits for four consecutive readings.REMARK : The applicability of this failure is limited to single--carrier operation since this failure has nodefinitive meaning in the multi--carrier case. The determination as to whether the system isoperating in single--carrier or multi--carrier mode is made by examining the Peak--to--Average Power Ratiocontained in the three most recent HPA Control Words. When the lowest reading of the three is equal to one,the RF Balance is checked for the error condition; for all other readings, the RF Balance is not examined.<HGA HPA> Amp 1 VCC Fail (04 5 02)DESCRIPTION : During CM, Amp1 VCC Error scaled analog value is faulted if it exceeds its limits. Thisfailure code shall only be applicable to the 40W HPA.PARAMETERS : Amp1 VCC Error scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Amp1 VCC Error scaled analog value is less than 75percent of the PSU +28 VDC scaled analog value for four consecutive readings.RECOVERY CRIT. : The Amp1 VCC Error transitions to not failed if the scaled analog value is within itsspecified limits for four consecutive readings.REMARK : None<HGA HPA> Spare (04 5 03)PWR2: HPA RF Power Amplifier (2) (SRU Code 6h)Same as for PWR1, except substitute Amp2 for Amp1. This failure code is only reported for HPAs with ahardware/software strap setting of 00h.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--70PWR3: HPA RF Power Amplifier (3) (SRU Code 7h)Same as for PWR1, except substitute Amp3 for Amp1. This failure code is only reported for HPAs with ahardware/software strap setting of 00h; it is reported to the SDU in lieu of failure code 04 (or 07)/9/xx forHPAs having a hardware/software strap setting of 02h or greater, although the HPA will record internally thecorrect failure code for the hardware present.HPA RF Power Combiner/Detector (SRU Code 8h)<HGA HPA> Forward Output Power Det 1 Fail (04 8 01)DESCRIPTION : During CM, Range 1 Forward Power detector scaled analog value is faulted if it exceeds itslimits. This failure code shall only be applicable to the 40W HPA.PARAMETERS : Range 1 Forward Power detector scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Range 1 Forward Power detector scaled analog valueis less than --2.0 VDC for four consecutive readings.RECOVERY CRIT. : The Range 1 Forward detector transitions to not failed if the scaled analog value isgreater than or equal to --2.0 VDC for four consecutive readings.REMARK : None<HGA HPA> Forward Output Power Det 2 Fail (04 8 02)DESCRIPTION : During CM, Range 2 Forward Power detector scaled analog value is faulted if it exceeds itslimits. This failure code shall only be applicable to the 40W HPA.PARAMETERS : Range 2 Forward Power detector scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Range 2 Forward Power detector scaled analog valueis less than --2.0 VDC for four consecutive readings.RECOVERY CRIT. : The Range 2 Forward detector transitions to not failed if the scaled analog value isgreater than or equal to --2.0 VDC for four consecutive readings.REMARK : None<HGA HPA> Forward Output Power Compare Fail (04 8 03)DESCRIPTION : During CM, a fault is declared if the forward powers detected by the two sensors do notagree to within 10 dB. This failure code shall only be applicable to the 40W HPA.PARAMETERS : None.FAIL CRITERIA : This fault transitions into a failure after four consecutive miscompares of the two forwardpower sensors.RECOVERY CRIT. : This failure transitions to not failed if the two forward power sensors comparesuccessfully for four consecutive readings.REMARK : These two sensors are used to independently measure two different output power ranges, andare not compared in any other way than for this detection of a gross failure of onesensor.<HGA HPA> Reflected Output Power Det Fail (04 8 04)DESCRIPTION : During CM, Reflected Output Power detector scaled analog value is faulted if it exceeds itslimits. This failure code shall only be applicable to the 40W HPA.PARAMETERS : Reflected Output Power detector scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Reflected Output Power detector scaled analog valueis less than --2.0 VDC for four consecutive readings.RECOVERY CRIT. : The Reflected Output Power detector transitions to not failed if the scaled analog valueis greater than or equal to --2.0 VDC for four consecutive readings.REMARK : None<HGA HPA> Combiner Temp Sensor Fail (04 8 05)DESCRIPTION : This fault is declared if (during CM) the reported Combiner temperature is either less than--90 degrees Celsius or greater than +210 degrees Celsius. This failure code shallonly be applicable to the 40W HPA.PARAMETERS : Combiner temperature sensor scaled analog voltage.FAIL CRITERIA : Combiner temperature sensor scaled analog output value is either less than --90 degreesCelsius or greater than +210 degrees Celsius for four consecutive readings.RECOVERY CRIT. : Combiner temperature sensor scaled analog output value is greater than or equal to --90degrees Celsius and less than or equal to +210 degrees Celsius for four consecutive readings.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--71REMARK : It is assumed that the Combiner temperature sensor is faulty if the reported Driver temperature iseither less than --90 degrees Celsius or exceeds +210 degrees Celsius. TheHPA Carriers, the HPA Bias, and the Variable Attenuator is restored to normal operation, and a temperatureof +25 degrees Celsius reported while this fault is active.HPA Final RF Power Amplifier (SRU Code 9h)<HGA HPA> Final Amp 1 RF Balance Fail (04 9 01)DESCRIPTION : During CM, the Final Amp1 RF Balance Error scaled analog value is faulted if it exceeds itslimits while only a single RF carrier is in use; this fault is not raised ifmultiple RF carriers are operating. This failure code shall only be applicable to the 40W HPA.PARAMETERS : Final Amp1 RF Balance Error scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Final Amp1 RF Balance Error scaled analog value isgreater than +3.0 VDC for four consecutive readings.RECOVERY CRIT. : The Final Amp1 RF Balance Error transitions to not failed if the scaled analog value iswithin its specified limits for four consecutive readings.REMARK : This failure will occur only in HPAs using Package D2.0 software (or beyond) in conjunction with ahardware/software compatibility strap setting of 02h (or greater). In HPAs having a hardware/softwarecompatibility strap setting of 02h or greater for which the residentsoftware package is any one prior to D2.0, the HPA shall report failure code 04 7 01 to the SDU (althoughfailure code 04 9 01 is recorded by the HPA in its internal failure log). The failure applicability is limited to thesingle--RF carrier case since it has no definitive meaning in the multi--carrier case. The determination as towhether the system is operating in single--carrier or multi--carrier mode is made by examining thePeak--to--Average Power Ratio contained in the three most recent HPA Control Words. When the lowestreading of the three is equal to one, the RF Balance is checked for the error condition; for all other readings,the RF Balance is not examined.<HGA HPA> Final Amp 1 VCC Fail (04 9 02)DESCRIPTION : During CM, the Final Amp1 VCC Error scaled analog value is faulted if it exceeds its limits.This failure code shall only be applicable to the 40W HPA.PARAMETERS : Final Amp1 VCC Error scaled analog value.FAIL CRITERIA : The HPA shall declare a failure if the Final Amp1 VCC Error scaled analog value is lessthan 75 percent of the PSU +28 VDC scaled analog value for four consecutive readings.RECOVERY CRIT. : The Final Amp1 VCC Error transitions to not failed if the scaled analog value is within itsspecified limits for four consecutive readings.REMARK : This failure will occur only in HPAs using Package D2.0 software (or beyond) in conjunction with ahardware/software compatibility strap setting of 02h (or greater). In HPAs having a hardware/softwarecompatibility strap setting of 02h or greater for which the residentsoftware package is any one prior to D2.0, the HPA shall report failure code 04 7 02 to the SDU (althoughfailure code 04 9 02 is recorded by the HPA in its internal failure log).<HGA HPA> Final Amp 2 RF Balance Fail (04 9 04)DESCRIPTION : During CM, the Final Amp2 RF Balance Error scaled analog value is faulted if it exceeds itslimits while only a single RF carrier is in use; this fault is not raised ifmultiple RF carriers are operating. This failure code shall only be applicable to the 40W HPA.PARAMETERS : Final Amp2 RF Balance Error scaled analog value.FAIL CRITERIA : The HPA shall declare a failure if the Final Amp2 RF Balance Error scaled analog value isgreater than +3.0 VDC for four consecutive readings.RECOVERY CRIT. : The Final Amp2 RF Balance Error transitions to not failed if the scaled analog value iswithin its specified limits for four consecutive readings.REMARK : This failure will occur only in HPAs using Package D2.0 software (or beyond) in conjunction with ahardware/software compatibility strap setting of 02h (or greater). In HPAs having a hardware/softwarecompatibility strap setting of 02h or greater for which the residentsoftware package is any one prior to D2.0, the HPA shall report failure code 04 7 01 to the SDU (althoughfailure code 04 9 04 is recorded by the HPA in its internal failure log). The failure applicability is limited to thesingle RF carrier case since it has no definitive meaning in the multi--carrier case. The determination as towhether the system is operating in single--carrier or multi--carrier mode is made by examining thePeak--to--Average Power Ratio contained in the three most recent HPA Control Words. When the lowestRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--72reading of the three is equal to one, the RF Balance is checked for the error condition; for all other readings,the RF Balance is not examined.<HGA HPA> Final Amp 2 VCC Fail (04 9 05)DESCRIPTION : During CM, the Final Amp2 VCC Error scaled analog value is faulted if it exceeds it limits.This failure code shall only be applicable to the 40W HPA.PARAMETERS : Final Amp2 VCC Error scaled analog value.FAIL CRITERIA : The HPA shall declare a failure if the Final Amp2 VCC Error scaled analog value is lessthan 75 percent of the PSU +28 VDC scaled analog value for four consecutive readings.RECOVERY CRIT. : The Final Amp2 VCC Error transitions to not failed if the scaled analog value is within itsspecified limits for four consecutive readings.REMARK : This failure will occur only in HPAs using Package D2.0 software (or beyond) in conjunction with ahardware/software compatibility strap setting of 02h (or greater). In HPAs having a hardware/softwarecompatibility strap setting of 02h or greater for which the residentsoftware package is any one prior to D2.0, the HPA shall report failure code 04 7 02 to the SDU (althoughfailure code 04 9 05 is recorded by the HPA in its internal failure log).<HGA HPA> PA Unresponsive (04 9 C0/40)DESCRIPTION : The control processor receives no response from the power amplifier (PA) module. Thisfailure code shall only be applicable to the 60W HPA.PARAMETERS : Number of failed attempts.FAIL CRITERIA : This fault transitions to a failure after 2 out of 3 communication attempts fail.RECOVERY CRIT. : This failure is cleared when all devices on the I2C bus are responsive.REMARKS : The 60W HPA will indicate Failure Warning in its Status and Maintenance words and illuminateits red (fail) LED while this failure is active. The Kernel maintenance and data loader interfaces are activatedand the PA is reset.The SDU will raise failure (04 0 0C) per section 4.4.5.4.20.12 while SSM=FW and no DISCRETES bits set.<HGA HPA> Over Current Failure (04 9 42)DESCRIPTION : The control processor receives an over current failure indication from the power amplifier(PA). This failure code shall only be applicable to the 60W HPA.PARAMETERS : PA status word.FAIL CRITERIA : This fault transitions to a failure after two consecutive PA status readings reporting overcurrent failure.RECOVERY CRIT. : This failure is cleared if the PA failure indication clears for at least 5 seconds.REMARKS : The 60W HPA will indicate Failure Warning in its Status and Maintenance words and illuminateits red (fail) LED while this failure is active. The PA is reset.The SDU will raise failure (04 0 0C) per section 4.4.5.4.20.12 while SSM=FW and no DISCRETES bits set.<HGA HPA> Driver Amplifier DC Voltage Failure (04 9 43)DESCRIPTION : The control processor receives a driver amplifier DC voltage failure indication from thepower amplifier (PA). This failure code shall only be applicable to the 60W HPA.PARAMETERS : PA status word.FAIL CRITERIA : This fault transitions to a failure after two consecutive PA status readings reporting DriverAmplifier DC Voltage failure.RECOVERY CRIT. : This failure is cleared if the PA failure indication clears for at least 5 seconds.REMARKS : The 60W HPA will indicate Failure Warning in its Status and Maintenance words and illuminateits red (fail) LED while this failure is active. The PA is resetThe SDU will raise failure (04 0 0C) per section 4.4.5.4.20.12 while SSM=FW and no DISCRETES bits set.<HGA HPA> Driver Amplifier Current Failure (04 9 44)DESCRIPTION : The control processor receives a driver amplifier current failure indication from the poweramplifier (PA). This failure code shall only be applicable to the 60W HPA.PARAMETERS : PA status word.FAIL CRITERIA : This fault transitions to a failure after two consectuive PA status readings reporting DriverAmplifier Current failure.RECOVERY CRIT. : This failure is cleared if the PA failure indication clears for at least 5 seconds.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--73REMARKS : The 60W HPA will indicate Failure Warning in its Status and Maintenance words and illuminateits red (fail) LED while this failure is active. The PA is reset.The SDU will raise failure (04 0 0C) per section 4.4.5.4.20.12 while SSM=FW and no DISCRETES bits set.<HGA HPA> 12 VDC Failure (04 9 45)DESCRIPTION : The control processor receives a 12 VDC failure indication from the power amplifier (PA).This failure code shall only be applicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after two consecutive PA BITE discrete readings reporting12 Vdc failure.RECOVERY CRIT. : This failure is cleared if the PA failure indication clears for at least 5 seconds.REMARKS : The 60W HPA will indicate Failure Warning in its Status and Maintenance words and illuminateits red (fail) LED while this failure is active. The PA is reset.The SDU will raise failure (04 0 0C) per section 4.4.5.4.20.12 while SSM=FW and no DISCRETES bits set.<HGA HPA> PA Mute Failure (04 9 46)DESCRIPTION : The output power detector measures power greater than +24 dBm when the PA mute isasserted. This failure code shall only be applicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure if fault persists for 3 ms.RECOVERY CRIT. : This failure is cleared when output power is less than or equal to +24 dBm while the PAmute is asserted for at least 8 ms.REMARKS : The 60W HPA will indicate Failure Warning in its Status and Maintenance words and illuminateits red (fail) LED while this failure is active.The SDU will raise failure (04 0 0C) per section 4.4.5.4.20.12 while SSM=FW and no DISCRETES bits set.<HGA HPA> Over Temp Failure (04 9 47)DESCRIPTION : The control processor receives an over temperature indication from the power amplifier(PA). This failure code shall only be applicable to the 60W HPA.PARAMETERS : PA status word.FAIL CRITERIA : This fault transitions to a failure if fault persists for two consecutive PA status reports.RECOVERY CRIT. : This failure is cleared if the PA failure indication clears for at least two consecutive PAstatus reports.REMARKS : The 60W HPA will set bit 13 in its Maintenance words, indicate Failure Warning in its Status andMaintenance words, report Maximum Available RMS Power = “8 dB less than 40W” in its Status words andilluminate its red (fail) LED while this failure is active. The PA is shut down.<HGA HPA> PA Status Failure (04 9 48)DESCRIPTION : The control processor receives no response from the I2C PA Status device. This failurecode shall only be applicable to the 60W HPA.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure after no response from PA status device in two out of threetests.RECOVERY CRIT. : This failure is cleared if the PA status device responds to tests for at least 5 seconds.REMARKS : The 60W HPA will indicate Failure Warning in its Status and Maintenance words and illuminateits red (fail) LED while this failure is active. The PA is reset.<HGA HPA> PA Temp Sensor Failure (04 9 49)DESCRIPTION : The control processor receives no response from the I2C PA temperature sensor device.This failure code shall only be applicable to the 60W HPA.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure after no response from PA temperature sensor device intwo out of three tests.RECOVERY CRIT. : This failure is cleared if the PA temperature sensor device responds to tests for at least5 seconds.REMARKS : The PA is reset.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--74HPA Mother Board (SRU Code Ah)<HGA HPA> Backplane Temp Sensor Failure (04 A 40)DESCRIPTION : The control processor receives no response from the backplane (BP) temperature sensor.This failure code shall only be applicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after 2 out of 3 communication attempts fail.RECOVERY CRIT. : This failure is never explicitly cleared.REMARKS : If both the CP and BP temp sensors are non--responsive, the 60W HPA will indicate FailureWarning in its Status and Maintenance words and illuminate its red (fail) LED while this failure is active. TheKernel maintenance and data loader interfaces are activated otherwise the application software is inactive.The SDU will raise failure (04 0 0C) while SSM=FW and no DISCRETES bits set.If only the BP temp sensor is non--responsive, the CP temp sensor is used for temp monitoring.<HGA HPA> RFAM: 20W HPA RF Amplifier Module (SRU Code Bh)Over Temp Shutdown (04 B 01)DESCRIPTION : During CM, the RFAM temperature is tested four times per second, and a fault is declared ifit equals or exceeds the maximum value of +133 degrees Celsius. Thisfailure code shall only be applicable to the 20W HPA.PARAMETERS : RFAM temperature sensor scaled analog voltage.FAIL CRITERIA : A failure is declared if the RFAM temperature sensor output scaled analog value is greaterthan or equal to +133 degrees Celsius for four consecutive readings.RECOVERY CRIT. : The failure is cleared if after four consecutive readings the RFAM temperature sensorscaled analog output is less than +125 degrees Celsius.REMARK : The HPA shall set bit 13 and indicate Failure Warning in its Maintenance words while this failure isactive. The HPA Carriers is set to OFF, the HPA Bias voltage is setto OFF, and the Variable Attenuator is set to maximum while this failure is active.RFAM VCC Fail (04 B 02)DESCRIPTION : During CM, RFAM VCC scaled analog value is faulted if it exceeds its limits. This failurecode shall only be applicable to the 20W HPA.PARAMETERS : RFAM VCC scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the RFAM VCC scaled analog value is less than 50percent of the PSU +15 VDC scaled analog value for four consecutive readings.RECOVERY CRIT. : The RFAM VCC failure transitions to not failed if the scaled analog value is within itsspecified limits for four consecutive readings.REMARK : NoneAmp 1 VCC Fail (04 B 03)DESCRIPTION : During CM, Amp1 VCC Error scaled analog value is faulted if it exceeds its limits. Thisfailure code shall only be applicable to the 20W HPA.PARAMETERS : Amp1 VCC Error scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Amp1 VCC Error scaled analog value is less than 75percent of the PSU +28 VDC scaled analog value for four consecutive readings.RECOVERY CRIT. : The Amp1 VCC Error transitions to not failed if the scaled analog value is within itsspecified limits for four consecutive readings.REMARK : NoneForward Output Power Det 1 Fail (04 B 04)DESCRIPTION : During CM, Range 1 Forward Power detector scaled analog value is faulted if it exceeds itslimits. This failure code shall only be applicable to the 20W HPA.PARAMETERS : Range 1 Forward Power detector scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Range 1 Forward Power detector scaled analog valueis less than --2.0 VDC for four consecutive readings.RECOVERY CRIT. : The Range 1 Forward detector transitions to not failed if the scaled analog value isgreater than or equal to --2.0 VDC for four consecutive readings.REMARK : NoneRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--75Forward Output Power Det 2 Fail (04 B 05)DESCRIPTION : During CM, Range 2 Forward Power detector scaled analog value is faulted if it exceeds itslimits. This failure code shall only be applicable to the 20W HPA.PARAMETERS : Range 2 Forward Power detector scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Range 2 Forward Power detector scaled analog valueis less than --2.0 VDC for four consecutive readings.RECOVERY CRIT. : The Range 2 Forward detector transitions to not failed if the scaled analog value isgreater than or equal to --2.0 VDC for four consecutive readings.REMARK : NoneReflected Output Pwr Det Fail (04 B 06)DESCRIPTION : During CM, Reflected Output Power detector scaled analog value is faulted if it exceeds itslimits. This failure code shall only be applicable to the 20W HPA.PARAMETERS : Reflected Output Power detector scaled analog voltage.FAIL CRITERIA : The HPA shall declare a failure if the Reflected Output Power detector scaled analog valueis less than --2.0 VDC for four consecutive readings.RECOVERY CRIT. : The Reflected Output Power detector transitions to not failed if the scaled analog valueis greater than or equal to --2.0 VDC for four consecutive readings.REMARK : NoneTemp Sensor Fail (04 B 07)DESCRIPTION : This fault is declared if (during CM) the reported RFAM temperature is either less than --90degrees Celsius or greater than +210 degrees Celsius. This failure code shallonly be applicable to the 20W HPA.PARAMETERS : RFAM temperature sensor scaled analog voltage.FAIL CRITERIA : The RFAM temperature sensor scaled analog output value is either less than --90 degreesCelsius or greater than +210 degrees Celsius for four consecutive readings.RECOVERY CRIT. : The RFAM temperature sensor scaled analog output value is greater than or equal to--90 degrees Celsius and less than or equal to +210 degrees Celsius for four consecutive readings.REMARK : This sensor is located in the Driver portion of the RFAM; therefore, it is assumed that the RFAMtemperature sensor is faulty if the reported Driver temperature is either less than --90 degrees Celsius orexceeds +210 degrees Celsius. The HPA Carriers, the HPA Bias, and the Variable Attenuator is restored tonormal operation, and a temperature of+25 degrees Celsius reported while this fault is active.<HGA HPA> Forward Output Power Compare Fail (04 B 08)DESCRIPTION : During CM, a fault is declared if the forward powers detected by the two sensors do notagree to within 10 dB. This failure code shall only be applicable to the 20W HPA.PARAMETERS : Forward power voltage 1; forward power voltage 2.FAIL CRITERIA : This fault transitions into a failure after four consecutive miscompares of the two forwardpower sensors.RECOVERY CRIT. : This failure transitions to not failed if the two forward power sensors comparesuccessfully for four consecutive readings.REMARK : These two sensors are used to independently measure two different output power ranges, andare not compared in any other way than for this detection of a gross failure of onesensor.Amp 2 RF Balance Fail (04 B 09)DESCRIPTION : During CM, the Final Amp2 RF Balance Error scaled analog value is faulted if it exceeds itslimits while only a single RF carrier is in use; this fault is not raised ifmultiple RF carriers are operating. This failure code shall only be applicable to the 20WHPA.PARAMETERS : Final Amp2 RF Balance Error scaled analog value.FAIL CRITERIA : The HPA shall declare a failure if the Final Amp2 RF Balance Error scaled analog value isgreater than +3.0 VDC for four consecutive readings.RECOVERY CRIT. : The Final Amp2 RF Balance Error transitions to not failed if the scaled analog value iswithin its specified limits for four consecutive readings.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--76REMARK : This failure will occur only in HPAs using Package E1.0 software or beyond. The failureapplicability is limited to the single RF carrier case since it has no definitive meaning in themulti--carrier case. The determination as to whether the system is operating in single--carrier or multi--carriermode is made by examining the Peak--to--Average Power Ratio contained in the three most recent HPAControl Words. When the lowest reading of the three is equal to one, the RF Balance is checked for the errorcondition; for all other readings, the RF Balance is not examined.Amp 2 VCC Fail (04 B 0A)DESCRIPTION : During CM, the Final Amp2 VCC Error scaled analog value is faulted if it exceeds it limits.This failure code shall only be applicable to the 20W HPA.PARAMETERS : Final Amp2 VCC Error scaled analog value.FAIL CRITERIA : The HPA shall declare a failure if the Final Amp2 VCC Error scaled analog value is lessthan 75 percent of the PSU +28 VDC scaled analog value for four consecutive readings.RECOVERY CRIT. : The Final Amp2 VCC Error transitions to not failed if the scaled analog value is within itsspecified limits for four consecutive readings.REMARK : This failure will occur only in HPAs using Package E1.0 software or beyond.HGA HPA, Unknown SRU (SRU Code 0h)<HGA HPA> Status Word (143) Update Rate Fail (04 0 01)DESCRIPTION : This fault is declared when the number of HPA Status Words with no parity error receivedby the SDU in the last second is less than 1 or exceeds 15 for that HPA aftercompletion of system--wide POST/PAST, and the associated bus is not inactive.PARAMETERS : Number of HPA Status Words received with no parity error during the first second of thefault.FAIL CRITERIA : If the fault is active for five seconds.RECOVERY CRIT.: Immediately upon receipt of a fault cleared report (i.e. the correct number of words in asecond), or the occurrence of an HGA HPA input bus fault.REMARK : None<HGA HPA> Status Word (143) Data Fail (04 0 02)DESCRIPTION : This fault is declared when the last HPA Status Word with no parity error received by theSDU contains a field set to an unauthorized or undetermined value.PARAMETERS : The offending status word.FAIL CRITERIA : If the fault is active for five seconds.RECOVERY CRIT. : As soon as an HPA Status Word is received with no error.REMARK : Only the first error seen on one of the HPA Status Words received will be reported, subsequenterrors, possibly affecting other data fields in the word, will not be reported unless at least one HPA StatusWord was declared “correct.”<HGA HPA> Maintenance Word (350) Update Rate Fail (04 0 03)DESCRIPTION : This fault is declared when the number of HPA Maintenance Words with no parity errorreceived by the SDU in the last second is less than 1 or exceeds 15 for that HPAafter completion of system--wide POST/PAST, and the associated bus is not inactive.PARAMETERS : Number of HPA Maintenance Words received with no parity error during the first second ofthe fault.FAIL CRITERIA : If the fault is active for five seconds.RECOVERY CRIT. : As soon as the HPA Maintenance Word is received with no parity errors in the correctrate range for one second, or upon the occurrence of an HGA HPA input bus fault.REMARK : None<HGA HPA> Maintenance Word (350) Data Fail (04 0 04)DESCRIPTION : This fault is declared when the last HPA Maintenance Word with no parity error received bythe SDU contains a field set to an unauthorized or undetermined value.PARAMETERS : The offending maintenance word.FAIL CRITERIA : If the fault is active for five seconds.RECOVERY CRIT. : As soon as an HPA Maintenance Word is received with no error.REMARK : The only error possibly detected in the HPA Maintenance Word is the SSM field set to NOCOMPUTED DATA (according to ARINC 741 Note 30 : “should not be used”).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--77<HGA HPA> Self Test Misoperation (143) (04 0 87)DESCRIPTION : This fault covers all possible POST/PAST misbehaviour related to HPA Functional Test.The POST/PAST fault is not declared if no ARINC words are being received from the HPA.Also, the POST/PAST no response fault is not declared if the HPA is declaring the controlbus input inactive.PARAMETERS : For SDU--initiated POST/PAST:01 : the HPA has not responded to functional test commanded for 30 seconds by theSDU (POST/PAST).02 : the HPA has started functional test, but the SDU has not received an HPA self-- testcomplete response within the 30 seconds accorded to external LRUs during system wide POST/PAST.03 : HPA functional tests exceeded 15 seconds.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is not explicitly clearedREMARK : Functional Test response checking is determined on the HPA Status Word’s SSM field. The CMversion of this fault is (5C 0 02).<HGA HPA> RF Overdrive Error (04 0 08)DESCRIPTION : Tested continuously at a rate of 4 times per second, a fault is declared if the 40W HPAoutput power “greater than 80 watt” limiting function is activated. This same fault is declared if the 20W HPAoutput power “greater than 40 watt” limiting function is activated. This failure code shall only be applicable tothe 20W and 40W HPAs.PARAMETERS : Actual Power Out value.FAIL CRITERIA : This fault transitions into a failure if it is not cleared after one second.RECOVERY CRIT. : For the 40W HPA, this failure transitions to not failed if the power output is less than 80watts for more than one second. For the 20W HPA, this failure transitions to not failed if the power output isless than 40 watts for more than one second.REMARK : None<HGA HPA> RF Supply Current Fail (04 0 09)DESCRIPTION : This fault is based on a measure of the LRU primary (i.e., 115 VAC or +28 VDC) inputpower consumption for the 40W HPA; it is based on a measure of the current drawn by theRF Amplifier Module from the +25.5 VDC supply in the 20W HPA. For both HPAs, during CM, a fault isdeclared if the Amps HI scaled analog value exceeds its limits, where the limits are dependent on theoperational status of the HPA. This fault is neither recorded nor annunciated by either HPA if it is detectedwhile the respective LRU’s PSU Power Fail Warning (PFW) signal is asserted. This failure code shall only beapplicable to the 20W and 40W HPAs.PARAMETERS : Amps HI scaled analog voltage, RF carrier--on bit.FAIL CRITERIA : This fault transitions into a failure if the Amps HI scaled analog value exceeds its limits forfour consecutive readings. Those limits are as follows:Operational: 40W HPA: Less than --15 Watts or greater than +500 Watts.20W HPA: Greater than 8.0 Amps DC.Idle: 40W HPA: Less than --20 Watts or greater than +190 Watts.20W HPA: Not applicable.Standby: 40W HPA: Less than --100 Watts or greater than 70 Watts.20W HPA: Greater than +0.7 Amps DC.RECOVERY CRIT. : This failure transitions to not failed if the Amps HI scaled analog value is within specifiedlimits for four consecutive readings.REMARK : An offset of 100 is used by the 40W HPA software in scaling the LRU primary input power value,which accounts for the negative power limits specified above. An offset of 0.5 isused by the 20W HPA software in scaling the current drawn by the RFAM.Operational is defined as carriers--on and RF output power greater than 1 Watt (for bothHPAs). Idle is defined as carriers--on and RF output power less than or equal to 1 Watt (40W HPAonly). Standby is defined as carriers--off (for both HPAs).<HGA HPA> Over Temperature (Combiner/Detector) Shutdown (04 0 0A)DESCRIPTION : During CM (for all software packages prior to as well as including D2.0), theCombiner/Detector temperature is tested four times per second, and shall declare a fault if it equals orRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--78exceeds +130 degrees Celsius; for all software packages subsequent to D2.0, the maximum value thresholdis increased from +130 to +133 degrees Celsius.This failure code shall only be applicable to the 40W HPA.PARAMETERS : Combiner/Detector temperature sensor output scaled analog voltage.FAIL CRITERIA : A failure is declared if the Combiner/Detector temperature sensor output scaled analogvalue is greater than or equal to the specified fault threshold for four consecutivereadings.RECOVERY CRIT. : The failure is cleared (by all software packages prior to as well as including D2.0) if afterfour consecutive readings the Combiner/Detector temperature sensor scaled analog output is less than +130degrees Celsius; for all software packages subsequent to D2.0, the temperature threshold is decreased from+130 to +125 degrees Celsius.REMARK : The HPA shall set bit 13 and indicate Failure Warning in its Maintenance words while this failure isactive. The HPA Carriers is set to OFF, the HPA Bias voltage is setto OFF, and the Variable Attenuator is set to maximum while this failure is active. Prior to hardwaremodification D to the 40W HPA, the sensor for this fault resided on the Combiner module. Withimplementation of hardware modification D, this sensor was relocated to the 40W HPA’s Detector module.Since the sensor’s function remains the same regardless of location, this fault was renamed (in conjunctionwith introduction of hardware modification D to the 40W HPA) so as to cover its arising from either site.<HGA HPA> No Response To Carrier Command (143) (04 0 0B)DESCRIPTION : This fault is declared when the SDU has commanded the HPA to a new carrier on/off state(via the HPA command word) for at least one second, but the HPA has not yet indicated its response to thenew commanded state in the HPA status word.PARAMETERS : 01 : no response to carrier ON.02 : no response to carrier OFF.FAIL CRITERIA : This fault transitions into failure if it is not cleared after one second.RECOVERY CRIT. : As soon as an HPA Status Word is received with the correct carrier state.REMARK : None<HGA HPA> Failure Warning With No Discretes Set (350) (04 0 0C)DESCRIPTION : The last HPA Maintenance Word received indicates a Failure Warning, but none of discretes#11, #12, #13, #15 #16 or #17 are set.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure after the receipt of four consecutive maintenance wordsindicating Failure Warning but with none of discretes #11, #12, #13, #15 #16 nor #17 set.RECOVERY CRIT. : As soon as an HPA Maintenance Word is received with either no Failure Warning or oneof the above discretes is set.REMARK : None<HGA HPA> 429 Maintenance Word PSU Fail (350) (04 0 0D)DESCRIPTION : This fault is declared when the last HPA Maintenance Word received had bit #11 set.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure after the receipt of four consecutive maintenance wordswith bit 11 set.RECOVERY CRIT. : As soon as an HPA Maintenance Word is received with the above discrete cleared.REMARK : None<HGA HPA> 429 Maintenance Word Internal RAM Fail (350) (04 0 0E)DESCRIPTION : This fault is declared when the last HPA Maintenance Word received had bit #16 set.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure after the receipt of four consecutive maintenance wordswith bit 16 set.RECOVERY CRIT. : As soon as an HPA Maintenance Word is received with the above discrete cleared.REMARK : NoneRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--79<HGA HPA> 429 Maintenance Word Internal ROM Fail (350) (04 0 0F)DESCRIPTION : This fault is declared when the last HPA Maintenance Word received had bit #17 set.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure after the receipt of four consecutive maintenance wordswith bit 17 set.RECOVERY CRIT. : As soon as an HPA Maintenance Word is received with the above discrete cleared.REMARK : None<HGA HPA> Class C HPA Maximum Available Power Fail (04 0 10)DESCRIPTION : This fault is declared when calibration of the HGA Class C HPA (i.e., projected maximumoutput power capability as specified in Section 3.3.1.3.2.8.4, in terms of theActual Power Output reported by the HPA plus a factor corresponding to the current HPA backoff) hasdetermined that the maximum output power capability projected for the Class C HGA HPA (i.e., at 0 dBbackoff) is outside of the range of 14 dBW to 21 dBW (approximately 25 to 126 watts).PARAMETERS : Failure Param: A 1 shall indicate that the calibrated output power was calculated to begreater than the maximum value.A 0 shall indicate that the calibrated output power was less than the minimum value.Assoc Param: The projected maximum output power capability, in tenths of dBW.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : As soon as a calibration yields a maximum output power capability within the range of 14to 21 dBW.REMARK : None.<HGA HPA> Self--Test Button Stuck (04 0 40)DESCRIPTION : The self--test button is detected as being depressed for more than 10 seconds. This failurecode shall only be applicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after 10 seconds of button press indication.RECOVERY CRIT. : This failure is cleared if the button is released for at least 1 second.REMARKS : NoneLGA HPA (Level 1 Code 07h)Same as for the <HGA HPA>HSU #1 (Level 1 Code 08h)This section, and all its subsections, are only applicable prior to SDU Part Number 7516118--XX130/--xx140.Although not documented for individual failures in the subsections that follow, any and all current failures forthe HSU (i.e., failures having the HSU level 1 failure code) is considered to have recovered” when the SDU’sinput bus from the HSU transitions from an inactive to an active state, with the SSM field of the label 270status word indicating Functional Test.Note: unlike other subsections of Section 4.4.5, the 6th level of the subsection numbers in the subsectionsthat follow do not correlate directly to their Level 3 failure codes.<HSU1> CPU (SRU Code 1h)<HSU1> Access Level Development (08 1 FA)DESCRIPTION :PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Access Level Production (08 1 FB)DESCRIPTION :PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--80<HSU1> Access Level Production Fast Startup (08 1 FC)DESCRIPTION :PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> SW Versions Inconsistency (08 1 FD)DESCRIPTION : This fault is raised when one or more software items in the HSU have a different versionnumber other than the expected one in the main application.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Environment Temperature At Power--Up Failure (08 1 7F)DESCRIPTION : This fault is raised when the temperature in the HSU is less than --30 Celsius, and alsowhen the temperature is greater than 95 Celsius.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Temperature Sensor Failure (08 1 91)DESCRIPTION : This fault is raised if the sensor does not send valid data to the CPU within 500 ms.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Frame DSP (SRU Code 2h)<HSU1> Frame DSP/CPU Interface Failure (08 2 95)DESCRIPTION : This fault is raised when the HSU fails to write or read a block of the DSP memory throughthe IDMA interface.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> VFC DSP (SRU Code 3h)<HSU1> VFC DSP/CPU Interface Failure (08 3 98)DESCRIPTION : This fault is raised when the HSU fails to write or read a block of the DSP memory throughthe IDMA interface.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Turbo FPGA (SRU Code 4h)<HSU1> Turbo FPGA Fail (08 4 86)DESCRIPTION : This fault is raised when the HSU fails to load the Turbo FPGA at the end of its self--test.PARAMETERS : 01: The Turbo FPGA code does not exist in the Flash.02: The Turbo FPGA code is defective. The code’s CRC does not match the stored CRC.03: The interface between the CPU and the Turbo FPGA is defective.04: The Turbo FPGA is defective.FAIL CRITERIA :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--81RECOVERY CRIT. :REMARK :<HSU1> ISDN Transceiver (SRU Code 5h)<HSU1> ISDN Transceiver Failure (08 5 87)DESCRIPTION : This fault is raised when the HSU ISDN S/T interface transceiver Byte Register 5 fails theinternal loop back.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> CPU RAM (SRU Code 7h)<HSU1> CPU RAM Failure (08 7 84)DESCRIPTION : This fault is raised when the HSU fails its RAM data/address line test.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Converter EEPROM (SRU Code 8h)<HSU1> EEPROM Failure (08 8 81)DESCRIPTION : This fault is raised when the HSU reports that the CRC check of its EEPROM has failed.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Flash (SRU Code 9h)<HSU1> Parameter Block Checksum Failure (08 9 82)DESCRIPTION : This fault is raised when the HSU reports that the arithmetic checksum of its ParameterBlock has failed.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> CPU BIOS/Application CRC Failure (08 9 83)DESCRIPTION : This fault is raised when the HSU reports that the CRC check of its BIOS/Application hasfailed.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Missing File In Flash (08 9 87)DESCRIPTION : This fault is raised when the HSU reports that the list of files in Flash does not match the listof files in the main application.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Corrupted File In Flash/Incorrect CRC (08 9 88)DESCRIPTION : This fault is raised when the HSU reports that the CRC in a file in the flash list does notmatch the stored CRC in the file header.PARAMETERS :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--82FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Quad UART (SRU Code A)<HSU1> External UART Failure (08 A 91)DESCRIPTION : This fault is raised when a loopback test of the external UART in the HSU fail.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :PSPCB: <HSU1> Power Supply PCB (SRU Code C)<HSU1> Power Failure (08 C 0B)DESCRIPTION : This fault is raised when the HSU detects a loss of external power for more than 10seconds.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1>/CDM Interface (SRU Code G)<HSU1> CDM Interface Failure (08 G F2)DESCRIPTION : This fault is raised when an error occurs on the interface between the HSU and the CDM,and the HSU CPU is unable to read valid data.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> CDM Not Fitted (08 G FE)DESCRIPTION : This fault is raised when the CDM is either not fitted or incorrectly inserted in the HSU.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Turbo Decoder RAM (SRU Code J)<HSU1> Turbo Decoder RAM Failure (08 J 8A)DESCRIPTION : This fault is raised when the interface between the turbo decoder FPGA and the RAM hasfailed, or when the contents of the RAM are corrupt.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Battery (SRU Code K)<HSU1> Battery Check Failure (08 K 85)DESCRIPTION : This fault is raised if the HSU battery voltage drops below 2.0 V.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Step Attenuator (SRU Code M)<HSU1> Step Attenuator Failure (08 M B5)DESCRIPTION : This fault is raised when the accuracy of the Rx attenuator and the two Tx attenuators isworse than the limit of ±2 dB of their commanded settings during RF loopback, or when AestAvgHi is > itslow threshold and when AestAvgHi is < its high threshold.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--83PARAMETERS : 01: Rx attenuator = 16 dB, Tx attenuator1 = 0 dB, Tx attenuator2 = 0 dB02: Rx attenuator = 8 dB, Tx attenuator1 = 4 dB, Tx attenuator2 = 4 dB03: Rx attenuator = 4 dB, Tx attenuator1 = 10 dB, Tx attenuator2 = 2 dB04: Rx attenuator = 0 dB, Tx attenuator1 = 8 dB, Tx attenuator2 = 8 dB05: Rx attenuator = 12 dB, Tx attenuator1 = 1 dB, Tx attenuator2 = 3 dB06: Rx attenuator = 12 dB, Tx attenuator1 = 0.5 dB, Tx attenuator2 = 3.5 dBFAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> RF (SRU Code N)<HSU1> 1.LO Lock Detector Failure (08 N 81)DESCRIPTION : This fault is raised when PLL 1 indicates lock detected when it has been forced not to lock.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> 2.LO Lock Detector Failure (08 N 82)DESCRIPTION : This fault is raised when PLL 2 indicates lock detected when it has been forced not to lock.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> 3.LO Lock Detector Failure (08 N 83)DESCRIPTION : This fault is raised when PLL 3 indicates lock detected when it has been forced not to lock.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> 1.LO Min Frequency Test Failure (08 N 91)DESCRIPTION : This fault is raised when PLL 1 does not lock at its minimum frequency specification.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> 2.LO Min Frequency Test Failure (08 N 92)DESCRIPTION : This fault is raised when PLL 2 does not lock at its minimum frequency specification.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> 3.LO Min Frequency Test Failure (08 N 93)DESCRIPTION : This fault is raised when PLL 3 does not lock at its minimum frequency specification.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> 1.LO Max Frequency Test Failure (08 N A1)DESCRIPTION : This fault is raised when PLL 1 does not lock at its maximum frequency specification.PARAMETERS :FAIL CRITERIA :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--84RECOVERY CRIT. :REMARK :<HSU1> 2.LO Max Frequency Test Failure (08 N A2)DESCRIPTION : This fault is raised when PLL 2 does not lock at its maximum frequency specification.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> 3.LO Max Frequency Test Failure (08 N A3)DESCRIPTION : This fault is raised when PLL 3 does not lock at its maximum frequency specification.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> ALC -- Carrier Off Failure (08 N B0)DESCRIPTION : This fault is raised when ALC_Level exceeds its BITE threshold, or when Power_Detectedis HIGH.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> ALC -- Carrier ON Failure (08 N B1)DESCRIPTION : This fault is raised when ALC_Level < its low threshold, or when ALC_Level > its highthreshold, and when Power_Detected* is HIGH.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> RF Loopback Failure (08 N B2)DESCRIPTION : This fault is raised when the measured BER in a period of one second is = 10.2 %.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Average Amplitude Failure (08 N B3)DESCRIPTION : This fault is raised when the average AGC_value = AGC0--100, and when AGC_value =AGC0+100 during RF loopback.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> 16QAM SCPC Frame Sync Failure (08 N B4)DESCRIPTION : This fault is raised when the Rx channel is not able to acquire frame sync during RFloopbackPARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--85<HSU1> Internal RX Coax Cable Failure (08 N BA)DESCRIPTION : This fault is raised when Rx_BITE is HIGH during RF loopback.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Tx/Rx Channel Frequency Error (08 N BB)DESCRIPTION : This fault is raised when the frequency error is = 20 Hz during RF loopback.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Carrier_ON/OFF Control Failure (08 N BC)DESCRIPTION : This fault is raised when the time between the frame reports (Tfr) is < its threshold, and alsowhen the ALC_Level is > than its threshold, and also when Pwr_Detected* = 0 when the Frm_Carrier_ONsignal is in its “off” state during RF loopback.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK : The HSU performs a set of three related tests of which this is one (see also 08 N BD and 08 NBE), to verify that no transmit power is measured when none is expected.<HSU1> RF Loopback OFF Control Failure (08 N BD)DESCRIPTION : This fault is raised when time between the frame reports (Tfr) is < its threshold, and alsowhen the ALC_Level is > than its threshold, and also when Pwr_Detected* = 0 when the RF_Loopback signalis in its “off” state.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK : The HSU performs a set of three related tests of which this is one (see also 08 N BC and 08 NBE), to verify that no transmit power is measured when none is expected.<HSU1> TX_ON/OFF Control Failure (08 N BE)DESCRIPTION : The fault is raised time between the frame reports (Tfr) is < its threshold when Frm_TX_ONsignal is in its “off” state during RF loopback.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK : The HSU performs a set of three related tests of which this is one (see also 08 N BC and 08 NBD), to verify that no transmit power is measured when none is expected.<HSU1> AGC Level Outside Limits Warning (08 N 41)DESCRIPTION : This fault, as a warning, is raised when AGC0 -- 100 < AGC_Value < AGC0 -- 50, or whenAGC0 + 50 < AGC_Value < AGC0 + 100.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Linearity Outside Limits Warning (08 N C3)DESCRIPTION : This fault is raised as a warning during RF loopback if the magnitude between twomodulation constellation test symbols, one at maximum amplitude (e.g., 1111) and theother at minimum amplitude (e.g., 1010), is different from the expected 3.00 by more than 0.11 (i.e. < 2.89 or>3.11).PARAMETERS :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--86FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> 1.LO Lock Failure (08 N 51)DESCRIPTION : This fault is raised when the #1 local oscillator fails to indicate lock detection during CM,including within 10 ms after a Tx or Rx channel change.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> 2.LO Lock Failure (08 N 52)DESCRIPTION : This fault is raised when the #2 local oscillator fails to indicate lock detection during CM,including within 10 ms after a Tx or Rx channel change.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> 3.LO Lock Failure (08 N 53)DESCRIPTION : This fault is raised when the #3 local oscillator fails to indicate lock detection during CM,including within 20 ms after a Tx or Rx channel change. The #3 LO is monitored only if “In Use”.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Reference Oscillator (SRU Code O)<HSU1> Ref Osc Warning: Send HSU To Cal (08 O 42)DESCRIPTION : This fault is raised when the reference oscillator tune voltage is within either its lower orupper warning range (but not within either of its failure ranges).PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK : See fault 08 O 63<HSU1> Ref Osc Failure/Voltage Too Low (08 O 63)DESCRIPTION : This fault is raised when the reference oscillator tune voltage is within its lower failure range.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK : See fault 08 O 42<HSU1> Ref Osc Failure/Voltage Too High (08 O 64)DESCRIPTION : This fault is raised when the reference oscillator tune voltage is within its upper failurerange.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK : See 08 O 42<HSU1> Burst Duration Monitor (SRU Code P)<HSU1> Burst Duration Monitor Circuit (08 P 81)DESCRIPTION : This fault is raised when a TDM burst of a specific duration is detected to be outside therange of the Burst Duration Monitor, i.e., a burst duration error occurs if the Burst Duration Monitor is set to60 ms and TDM burst is > 60 ms.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--87PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> TDM Burst Duration Failure (08 P 04)DESCRIPTION : This fault is raised when a TDM channel signaling burst more than 160 ms in length triggersthe burst duration monitor.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Carrier On Signals (08 P 85)DESCRIPTION : This fault is raised when a continuous TDM burst is transmitted and no carrier on signal ispresent.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK : The CPU can read the Carrier_On and Tx_On signals from the burst duration monitor.<HSU1> Doppler Compensation (SRU Code Q)<HSU1> Reference Oscillator Compensation Error (08 Q 39)DESCRIPTION : This fault is raised if, 20 seconds after the Rx channel is present (i.e., the Rx channel hasacquired satellite frequency tracking), the frequency error is greater than 290 Hz.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Frame DSP/VFC DSP Interface (SRU Code R)<HSU1> Frame DSP/VFC DSP Interface Failure (08 R 17 )DESCRIPTION : This fault is raised when an error occurs in the serial link between the Frame DSP and theVFC DSP.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Frame DSP/Turbo FPGA Interface (SRU Code S)<HSU1> Frame DSP/Turbo FPGA Interface Failure (08 S 96)DESCRIPTION : This fault is raised when a write/read error occurs in a block of the RAM attached to theTurbo FPGA through its parallel interface with the Frame DSP.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> Power Supply PCB/ISDN Phone Interface (SRU Code W)<HSU1> ISDN Supply Voltage Failure (08 W 88)DESCRIPTION : This fault is raised when the 38V ISDN line voltage is out of range, i.e., less than 33V orgreater than 43V.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--88<HSU1> Configuration Data Module (SRU Code X)<HSU1> Invalid Serial Number (08 X F1)DESCRIPTION : This fault is raised when the HSU detects that the LRU serial number, HW revision number,PCB number, CDM internal serial number, CDM internal revision number, or CDM internal part number arenot valid.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> CDM Essential Data Failure (08 X F3)DESCRIPTION : This fault is raised when the HSU detects that essential data in the CDM is not available.PARAMETERS : 01: Inconsistent Major or Minor version on an essential structure02: Both backup and main structure for an essential structure are corrupted or unavailable03: The CDM platform type is incompatibleFAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> CDM Data Access Error (08 X F4)DESCRIPTION : This fault is raised when the HSU detects that non--essential data in the CDM is corrupted.PARAMETERS : 01: Either backup or (exclusive or) main structure for an essential structure are corrupted orunavailable02: Either backup or main structure for a non--essential structure are corrupted orunavailableFAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> CDM Missing Write Protection Failure (08 X F5)DESCRIPTION : This fault is raised by the HSU when any status register in the CDM EEPROMs has thewrong status or is able to update a test variable in the write--protected area.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> CDM Incorrect Version (08 X F6)DESCRIPTION : This fault is raised by the HSU when the version of the data in the CDM is not correct, andalso when the version on an essential and non--essential structure is inconsistent.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1> ISDN Transceiver/Power Supply PCB Interface (SRU Code Z)<HSU1> ISDN Rx Voltage (08 Z 89)DESCRIPTION : This fault is raised when the HSU detects that the ISDN voltage supplied to the S--bus isoutside its range, i.e., less than 33V or greater than 43V.PARAMETERS :FAIL CRITERIA :RECOVERY CRIT. :REMARK :<HSU1>, Unknown SRU (SRU Code 0)<HSU1> Self--Declared Fail (08 0 01)DESCRIPTION : This fault is raised if the SSM field of the Label 270 status word received by the SDU fromthe HSU is set to Failure Warning.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--89PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure if it is continually active in at least 5 consecutive statuswords.RECOVERY CRIT. : As soon as a status word is received with the SSM cleared to Normal Operation.REMARK : One second of filtering is applied by the SDU (assuming the nominal transfer rate of 5 Hz) tocover the possibility that the HSU does not apply any filtering to its activation of SSM = Failure Warning.<HSU1> Williamsburg Protocol ALO/ALR Fail (08 0 02)DESCRIPTION : This fault is declared by the SDU If the HSU does not respond with an ALR word after 3transmissions of the ALO word to it.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : As soon as communication is re--established with the HSU.REMARK : None<HSU1> Williamsburg Protocol Data Transfer Fail (08 0 03)DESCRIPTION : If the maximum number of RTS words have been sent to the HSU without receiving a validCTS word or if the maximum number of attempts have been made for transmitting an LDU to the HSUwithout receiving a valid ACK word when HSU is the active DTE, this fault is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : As soon as a successful transmission of an LDU has been made to the HSU.REMARK : A transmission failure indicates a break in the bus connecting the SDU output and the HSU input.<HSU1> Self Test Misoperation (08 0 84)DESCRIPTION : This fault covers all possible SDU--initiated POST/PAST misbehavior related to HSUFunctional Test. The POST/PAST fault is not declared if no ARINC words are beingreceived from the HSU. Also, the POST/PAST no response fault is not declared if the HSU is declaring thecontrol bus input inactive.PARAMETERS : For SDU--initiated POST/PAST:01 : the HSU has not responded to functional test commanded for 15 seconds bythe SDU (POST/PAST).02 : the HSU has started functional test, but the SDU has not received an HSU self--test complete responsewithin the 40 seconds accorded to external LRUs during system wide POST/PAST.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : Functional Test response checking is determined on the HSU Status Word’s SSM field. The CMversion of this fault is (50 0 02).<HSU1> Channel Release Acknowledge Failure (08 0 05)DESCRIPTION : This fault is declared by the SDU If the HSU fails to acknowledge a cooperative channelrelease request from the SDU within 10 seconds.PARAMETERS :FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : The SDU shall assert the HSU System Disable discrete for 10 seconds. This failure iscleared when, following the associated HSU reset, the SDU’s input bus from the HSU transitions from aninactive to an active state, with the SSM field of the Label 270 status word indicating Functional Test.REMARK :<HSU1> RF Loopback Inhibit Failure (08 0 86/06)DESCRIPTION : This fault is declared by the SDU if the HSU fails to acknowledge the termination of RFloopback testing by indicating “Normal Operation” in bits 12 and 13 of the HSU status word. The failure codeshall reflect CM(06) or PP(86) depending on the CM/PP state of theSDU at the time (not the HSU).PARAMETERS :FAIL CRITERIA : This fault transitions into a failure if bits 12 and 13 of the HSU status word do not indicate“Normal Operation” within two seconds of inhibit command from the SDU.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--90RECOVERY CRIT. : The SDU shall assert the HSU System Disable discrete for 10 seconds. This failure iscleared when, following the associated HSU reset, the SDU’s input bus from the HSU transitions from aninactive to an active state, with the SSM field of the Label 270 status word indicating Functional Test.REMARK :HSU #2 (Level 1 Code 09h)Same as for HSU #1, Level 1 code 08, except substitute <HSU2> for <HSU1>. Only applicable prior to SDUPart Number 7516118--XX130/--xx140.High Power Relay (Level 1 Code 0Ah)High Power Relay, Unknown SRU (SRU Code 0h)(PORT) MNTNC WORD HPR Fail (0A 0 01)DESCRIPTION : The HPR status is determined to be failed from discrete bit #17 in the Maintenance Wordfrom the Port BSUPARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after the receipt of four consecutive maintenance wordswith bit 17 set.RECOVERY CRIT. : As soon as a fault cleared report is madeREMARK : The LNA/DIP control discrete from the BSU is also used to control the HPR(STBD) MNTNC WORD HPR Fail (0A 0 02)DESCRIPTION : The HPR status is determined to be failed from discrete bit #17 in the Maintenance Wordfrom the Starboard BSUPARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after the receipt of four consecutive maintenance wordswith bit 17 set.RECOVERY CRIT. : As soon as a Starboard BSU/ACU Maintenance Word is received with bit #17 clearREMARK : The LNA/DIP control discrete from the BSU is also used to control the HPR.Top/Port LNA/Diplexer (Level 1 Code 0Dh)Top/Port LNA/Diplexer, Unknown SRU (SRU Code 0h))<T/P LNA/DIP> Maintenance Word Fail (0D 0 01)DESCRIPTION : This fault is raised when the LNA/DIP BITE discrete bit #20 in the BSU Maintenance Wordis set, indicating failure of the Top/Port LNA/DIP, or (for software package E1.0 and later) when bit #25 of soloword #08 from the 20W HPA is set, indicating failure of the IGA LNA/DIP.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after the receipt of four consecutive maintenance or solowords with the respective bit set.RECOVERY CRIT. : As soon as a maintenance or solo word is received with the respective bit cleared.REMARK : Solo word #08 is only generated by a Honeywell 20W HPA using the internal beamsteering functionality to control an IGA system.Spare LRU (Level 1 Code 0Eh)Starboard LNA/Diplexer (Level 1 Code 0Fh)Same as for the Top/Port LNA/Diplexer (Section 4.4.5.13), except substitute Starboard for both Top/Port andPort/Top, <STBD LNA/DIP> for <T/P LNA/DIP>, and failure code (0F 0 01) for (0D 0 01).LGA LNA/Diplexer (Level 1 Code 10h)Unknown LGA LNA/Diplexer (SRU Code 0h)LGA LNA Dip Fail (10 0 01)DESCRIPTION : This fault is raised if the LGA LNA BITE discrete input is not Ok when the LGA LNA hasbeen commanded to the “On” state, more than 1/7th second after the command isapplied.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure if it is not cleared after one second.RECOVERY CRIT. : Immediately after the LGA LNA BITE discrete input is as expected.REMARK : No functional resource indictment is performed because there is no possible reversion action; theSDU will continue to attempt to utilize the LGA, even though BITE has indicated this failure.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--91Top/Port BSU Or ACU (Level 1 Code 13h)Top/Port BSU Or ACU, Unknown SRU (SRU Code 0h)<T/P B/A> Mntnc Word (350) Update Rate Fail (13 0 01)DESCRIPTION : The number of Top/Port BSU Maintenance Words (label 350) with no parity error receivedby the SDU in the last second is less than 1 or greater than 15 for that BSU aftercompletion of system--wide POST/PAST, and the associated bus is not inactive.PARAMETERS : Number of BSU Maintenance Words received with no parity error during the first second ofthe faultFAIL CRITERIA : If the fault is active for more than 5 seconds.RECOVERY CRIT. : As soon as a fault cleared report is made (ie the correct number of words have beenreceived in a second), or a Top/Port BSU input bus fault is declared.REMARK :<T/P B/A> Mntnc Word (350) Data Fail (13 0 02)DESCRIPTION : The last Top/Port BSU Maintenance Word (label 350) with no parity error received by theSDU contains a field set to an unauthorised or indeterminate valuePARAMETERS : BSU Maintenance Word in errorFAIL CRITERIA : If the fault is active for five seconds.RECOVERY CRIT. : As soon as a Top/Port BSU Maintenance Word is received with no errorREMARK : This is not implemented since there are no fields worth checking.<T/P B/A> Status Word (144) Update Rate Fail (13 0 03)DESCRIPTION : The number of Top/Port BSU Status Words (label 144) with no parity error received by theSDU in the last second is less than 1 or greater than 15 after completion of system--widePOST/PAST, and the associated bus is not inactive.PARAMETERS : The number of Status Words received in the first secondFAIL CRITERIA : If the fault is active for 5 secondsRECOVERY CRIT. : As soon as a fault cleared report is made (ie the correct number of words have beenreceived in a second), or a Top/Port BSU input bus fault is declared.REMARK :<T/P B/A> Status Word (144) Data Fail (13 0 04)DESCRIPTION : The last Top/Port BSU Status Word (label 144) with no parity error received by the SDUcontains a field set to an unauthorised or indeterminate valuePARAMETERS : BSU Status Word in errorFAIL CRITERIA : If the fault is active for five secondsRECOVERY CRIT. : As soon as a Top/Port BSU Status Word is received with no errorREMARK : Only the first error seen will be reported. Subsequent errors, even those affecting different fields,will not be reported unless separated by one or more ’correct’ BSU Status Words.The only field checked will be the closed loop tracking bit which should only be open loop.<T/P B/A> Maintenance Word RAM Fail (13 0 05)DESCRIPTION : Top/Port BSU Maintenance Word (label 350) discrete bit #14 set indicating internal RAMfailedPARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after the receipt of four consecutive maintenance wordswith bit 14 set.RECOVERY CRIT. : Immediately after a Top/Port BSU Maintenance Word is received with bit #14 clear.REMARK :<T/P B/A> Maintenance Word ROM Fail (13 0 06)DESCRIPTION : Top/Port BSU Maintenance Word (label 350) discrete bit #15 set indicating internal ROMfailedPARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after the receipt of four consecutive maintenance wordswith bit 15 set.RECOVERY CRIT. : Immediately after a Top/Port BSU Maintenance Word is received with bit #15 clear.REMARK :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--92<T/P B/A> Maintenance Word PSU Fail (13 0 07)DESCRIPTION : Top/Port BSU Maintenance Word (label 350) discrete bit #16 set indicating internal PSUfailedPARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after the receipt of four consecutive maintenance wordswith bit 16 set.RECOVERY CRIT. : Immediately after a Top/Port BSU Maintenance Word is received with bit #16 clearREMARK :<T/P B/A> Maintenance Word Parameter Fail (13 0 08)DESCRIPTION : Top/Port BSU Maintenance Word (350) discrete bit #18 is set indicating internal ParameterfailurePARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after the receipt of four consecutive maintenance wordswith bit 18 set.RECOVERY CRIT. : Immediately after a Top/Port BSU Maintenance Word is received with bit #18 clearREMARK :<T/P B/A> Maintenance Word Temp Fail (13 0 09)DESCRIPTION : Top/Port BSU Maintenance Word (350) discrete bit #22 is set indicating BSUOver temperaturePARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure after the receipt of four consecutive maintenance wordswith bit 22 set.RECOVERY CRIT. : Immediately after a Top/Port BSU Maintenance Word is received with bit #22 clearREMARK : None<T/P B/A> Self--Test Misoperation (13 0 8A)DESCRIPTION : This fault covers all possible POST/PAST misbehaviour related to BSU Functional Test.This fault is not declared if no ARINC words are being received from the BSU.PARAMETERS : 01 : the BSU has not responded to functional test commanded for 30 seconds by the SDU(POST/PAST)02 : the BSU has started functional test, but the SDU has not received a BSU self test response completewithin the 30 seconds accorded to external LRUs during system wide POST/PAST03 : BSU functional tests exceeded 15 secondsFAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared for cases 1,2 and 3REMARK : Functional Test response checking is determined on the BSU Maintenance word’s SSM field. TheCM version of this failure is (62 0 02).<T/P B/A> Spare (13 0 0B)Spare LRU (Level 1 Code 14h)Starboard BSU (Level 1 Code 15h)Same as for the Top/Port BSU or ACU (Section 4.4.5.19)Top/Port HGA/IGA (Level 1 Code 1A)Unknown Top/Port HGA/IGA (SRU Code 0h)Top/Port HGA/IGA Maintenance Word Fail (1A 0 01)DESCRIPTION : This fault is raised when the Top/Port BSU Maintenance Word (label 350) discrete bit #11 isset indicating HGA Failed, or in an IGA system when bit #24 of solo word #08 from the 20W HPA is set,indicating failure of the IGA or the interface between the HPA and theIGA.PARAMETERS : None. However, for the case of this failure being triggered by the 20W IGA HPA setting soloword #8 bit #24, the HPA will be declaring one or more of failures 1A/0/02, 1A/0/03 or1A/0/04, which do contain parameter information relevant to this failure.FAIL CRITERIA : This fault transitions to a failure after the receipt of four consecutive maintenance or solowords with the respective bit set.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--93RECOVERY CRIT. : Immediately after a maintenance or solo word is received with the respective bit cleared.REMARK : Solo word #08 is only generated by a Honeywell 20W HPA using its internal beam steeringfunctionality to control an IGA system.Also note that, contrary to the norm, Level 1 failure code 1A is used for failures of the power and signalinterfaces between the IGA and the 20W HPA, as well as for the IGA itself.IGA Failure (1A 0 02)DESCRIPTION : This fault is raised by the 20W HPA whenever the BITE Data Word received from the IGAindicates Power Supply Fault [whose root cause could be in the IGA, or in the power feed from the HPA,including the HPA itself], and also when the IGA’s re--transmitted echo (also in the BITE Data Word from theIGA) of the HPA’s commanded Beam Steering Word byte #1 bit #0 does not match the commanded bit,indicating failure of the IGA or the interface between the HPA and the IGA. While this failure is currentlyactive, the HPA shall also set bit #24 of its solo word #8.PARAMETERS : For the failure parameter, the following codes apply:0=Reserved1 = CMC antenna2 = CAL antennaThe associated parameter is defined as follows:BIT Meaning0 Reserved1 Reserved21=CMCSteeringDataMismatch,0=OK3 1 = CMC Power Supply fault (--85V), 0 = OK4 Reserved5 ReservedFAIL CRITERIA : After four successive fault conditions are declared (any one or more of the conditionsspecified in the associated parameter value).RECOVERY CRIT. : Immediately after none of the conditions specified in the associated parameter value isdetected by the HPA nor indicated by the IGA.REMARK : The parameters stored with this failure will be pertinent to the 1A/0/01 failure stored by the SDU inresponse to the HPA’s solo word.IGA RS--422 Input Bus Link Fault (1A 0 03)DESCRIPTION : This fault is raised by the 20W HPA whenever the BITE Data Word received from the IGAhas its Link Fault bit set, indicating failure of the IGA or the RS--422 bus from the HPA to the IGA (whose rootcause could be in the IGA, or in the RS--422 interface from the HPA to the IGA, or in the HPA). While thisfailure is currently active, the HPA shall also set bit #24 of its solo word #8.PARAMETERS : None.FAIL CRITERIA : After four successive fault conditions are declared.RECOVERY CRIT. : Immediately after the IGA’s BITE Data Word is received with the Link Fault bit cleared.REMARK :IGA HPA RS--422 Input Bus Error/Inactive (1A 0 04)DESCRIPTION : This fault is raised by the 20W HPA if the IGA fails to respond to a steering command wordtransmitted from the HPA after 0.5 second, and also when the HPA detects interface errors on the associatedserial input port, indicating failure of the IGA or the RS--422 bus from the IGA to the HPA (whose root causecould be in the IGA, or in the RS--422 bus from the IGA to the HPA, or in the HPA). While this failure iscurrently active, the HPA shall also set bit #24 of its solo word #8.PARAMETERS : The associated parameter value is set to the last received character. The failure parameteris set as follows (with bits 0 through 7 obtained from the associated UART status register [and those specifiedas “Always 0” being masked out by the HPA software] ):Bit0:Always0.Bit 1: 1 = Receive data character framing error, 0 = OK.Bit 2: 1 = Break flag (twisted pair wiring probably reversed), 0 = OK.Bit3:Always0.Bit 4: 1 = Receive data character parity error, 0 = OK.Bit 5: 1 = Receive data noisy, 0 = OK.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--94Bit6:Always0.Bit7:Always0.Bit 8: Bus inactive (response data timeout fault).FAIL CRITERIA : For bus inactive: after 10 expected responses are missed. (The wordtransmission/response rate is not fixed, but varies with the rate of change of commanded beam steering data;this criteria equates to approximately 0.5 to 5 seconds, depending on the actual command word transmissionrate.) For all other indicated fault causes: after four consecutive indications of any one or more of the causeslisted for the failure parameter.RECOVERY CRIT. : As soon as valid data is received.REMARK :Starboard HGA (Level 1 Code 1C)Same as for the Top/Port HGASCDU/WSC--1 (Level 1 Code 21h)The SDU may be wired to ARINC 739 SCDUs/MCDUs or to ARINC 741 Williamsburg SDU controllers(WSCs) for similar functionality on the same physical SDU ARINC 429 interfaces (but with only one controllertype at a time). Due to this similarity, the same Level 1 failure codes are used for both controller types.Different Level 3 failures shall apply as appropriate to the controller type. The failures defined below for theWSC are patterned after those for the (C)MU (Level 1 code 33).SCDU/WSC--1, Unknown SRU (SRU Code 0h)<SCDU--1> Protocol Error (21 0 01)DESCRIPTION : The SDU shall declare this failure in response to specifically defined errors occuring in thecommunication protocol between the SDU and the SCDU. For expedience, the specific errors are definedbelow along with their respective stored parameter codes.PARAMETERS : Each detected protocol error shall result in its respective parameter value bit being set tothe one state (with unused and inactive bits cleared to zero). The bits (decimal weighted) and their errordefinitions is as follows:1 CTS Timeout: After transmitting an RTS word, if a CTS word is not received within 200 ms, the SDUrepeats the RTS/Wait--For--CTS cycle up to 10 times if necessary. If no CTS word is received within 200 msafter the 10th repeat, this error is declared.4 Transmit ACK Timeout: After transmission of a message transfer block, the SDU waits for an ACK or NAKfor up to 1.5 seconds; if none is received, the SDU repeats the Transmit/Wait--For--ACK--or--NAK cycle up tonine times if necessary, repeating the sequence of sending RTS and awaiting CTS after every threetransmissions. If no ACK or NAK is received within 1.5 seconds of the ninth transmission, this error isdeclared.8 Transmit NAK: During or after a message transfer block, a SYN or NAK word may be received from theSCDU, at which time the SDU discontinues transmission of the block and repeats the transmission sequence(beginning with the RTS word), up to two times if necessary. If a SYN or NAK word is received again on thesecond repeat, this error is declared.16 Discrete Timeout: The SDU transmits SCDU Discrete word updates to the SCDU; if no ACK is receivedwithin one second, the SDU repeats the Transmit/Wait--For--ACK cycle up to 3 times if necessary. If no ACKis received within one second after the 3rd repeat, this error is declared.FAIL CRITERIA : This fault transitions to a failure if it persists for between three to six seconds (ensuring thatthe cause is not an inactive input bus).RECOVERY CRIT. : Successful receipt of an ENQ word from the SCDU.REMARK :<WSC--1> Status (270) Bad SSM (21 0 02)DESCRIPTION : This fault is raised if a label 270 WSC--1 Status word is received with “Failure Warning”(11b) indicated in the SSM field.PARAMETERS : NoneFAIL CRITERIA : If the fault persists for three seconds.RECOVERY CRIT. : As soon as a WSC--1 Status word is received with “Normal Operation” (00b) in its SSMfield or when an SDU WSC--1 Bus Inactive fault is raised.REMARK :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--95<WSC--1> Master Protocol Error (21 0 03)DESCRIPTION : If WSC--1 is the first WSC to declare itself “active” after system initialization, and then itsubsequently does not respond with an ALR word after 3 transmissions of the ALO word toit, then this fault is raised if the SDU is configured as a single SDU or is the Master in a dual system.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure only if it persists for at least ten seconds.RECOVERY CRIT. : As soon as communication is re--established with WSC--1, or an SDU WSC--1 BusInactive fault is raised.REMARK :<WSC--1> Data Transmission Failure (21 0 04)DESCRIPTION : If the maximum number of RTS words have been sent to WSC--1 without receiving a validCTS word or the maximum number of attempts have been made for transmitting an LDU to WSC--1 withoutreceiving a valid ACK word when WSC--1 is the “active” WSC, this fault is raised.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : As soon as a successful transmission of an LDU has been made to WSC--1, or WSC--1responds to a SOLO TEST word, or when an SDU WSC--1 Bus Inactive failure is declared.REMARK : Whenever the SDU has a data file ready to transmit to WSC--1, it follows the transferprocedure.<WSC--1> Master TEST/LOOP Failure (21 0 07)DESCRIPTION : If WSC--1 fails to respond to two consecutive SOLO TEST words with the correct LOOPword, then this fault is raised if the SDU is either the sole SDU in a single system orthe Master in a dual system.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : As soon as WSC--1 responds to a SOLO TEST word with the correct LOOP word, anSDU WSC--1 Bus Inactive fault is raised.REMARK :SCDU/WSC--2 (Level 1 Code 22h)Same as for SCDU/WSC--1 (Section 4.4.5.33), except substitute SCDU--2 for SCDU--1 and WSC--2 forWSC--1.SCDU/WSC--3 (Level 1 Code 23h)Same as for SCDU/WSC--1 (Section 4.4.5.33), except substitute SCDU--3 for SCDU--1 and WSC--3 forWSC--1.(C)MU--1 (Level 1 Code 33h)(C)MU--1, Unknown SRU (SRU Code 0h)COMMENTARYThe failure of a (C)MU to respond to ALO, SOLO TEST words or data transmissions is indicative of a brokenSDU to CMU bus. These faults will indict the [cmu] level--2 resource. This does not affect bit 11 of the SDUlabel 270 status word, but may initiate a handover of mastery in a dual system.(C)MU--1 Status (270) Bad SSM (33 0 02)DESCRIPTION : For Airbus, this fault is raised if a Label 270 Status word is received with the SSM field setto “Failure Warning” (11b). For other aircraft, this fault is raised if a Statusword is received with anything other than “Normal Operation” (00b) in the SSM field.PARAMETERS : NoneFAIL CRITERIA : For Airbus, if the fault is active for three seconds; for other aircraft, if the fault is active forfive seconds.RECOVERY CRIT. : For Airbus, this failure shall clear as soon as a Status word is received with its SSM fieldset to any state other than Failure Warning or when a CMU--1 Bus Inactive fault is declared. For otheraircraft, this failure shall clear as soon as a Status word is received with “Normal Operation” in its SSM fieldor when a CMU--1 Bus Inactive fault is declared.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--96REMARK : The failure criteria for this fault was changed to three seconds for Airbus in response to AirbusEPR 109, in order that such a fault would be reported on the Airbus CFDS Testpage upon completion of the Test (PAST) function.(C)MU--1 Master Protocol Error (33 0 03)DESCRIPTION : If this CMU is the first CMU to declare itself active after system init, and then itsubsequently does not respond with an ALR word after 3 transmissions of the ALO word to it, then this faultis declared if the SDU is configured as a single SDU or is the Master in a dual system.PARAMETERS : NoneFAIL CRITERIA : Prior to Package 2.0, this fault transitions to a failure immediately. For Package 2.0 andsubsequent, this fault transitions to a failure only if it persists for at least tenseconds.RECOVERY CRIT. : As soon as communication is re--established with this CMU, a CMU--1 Bus Inactive faultis declared, or a CMU--1 Slave Protocol Error is declared.REMARK :(C)MU--1 Data Transmission Failure (33 0 04)DESCRIPTION : If the maximum number of RTS words have been sent to the CMU without receiving a validCTS word or if the maximum number of attempts have been made for transmitting an LDU to the CMUwithout receiving a valid ACK word when CMU 1 is the active DTE, this fault is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : As soon as a successful transmission of an LDU has been made to the CMU, or theCMU responds to a SOLO TEST word, or when a CMU--1 Bus Inactive failure is declared.COMMENTARYA transmission failure indicates a break in the bus connecting the SDU output and the CMU input. It shouldindict the [cmu] resource because several back--to--back LDU transfers could prevent this being detected by aSOLO TEST/LOOP test. To make this failure recoverable it should be cleared once a SOLO TEST/LOOPtest succeeds (these are still carried out regardless of [cmu] indictment).REMARK : Whenever the SDU has a data file ready to transmit to the CMU, it follows the transferprocedure.(C)MU--1 Slave Protocol Error (33 0 05)DESCRIPTION : If this CMU is the first CMU to declare itself active after system init, and then itsubsequently does not respond with an ALR word after 3 transmissions of the ALO word to it, then this faultis declared if the SDU is the Slave in a dual system.PARAMETERS : None.FAIL CRITERIA : Prior to Package 2.0, this fault transitions to a failure immediately. For Package 2.0 andsubsequent, this fault transitions to a failure only if it persists for at least tenseconds.RECOVERY CRIT. : As soon as communication is re--established with this CMU, a CMU--1 Bus Inactive faultis declared, or a CMU--1 Master Protocol Error is declared.REMARK : See failure 33 0 03.(C)MU--1 Self--Declared Failure (33 0 06)DESCRIPTION : This fault is declared if the Fail bit (bit 16) of the Label 270 Status word received by the SDUfrom the (C)MU is set.PARAMETERS : None.FAIL CRITERIA : This fault transitions to the failure state if it is continuously active for at least three seconds.RECOVERY CRIT. : As soon as a Status word is received with bit 16 cleared or a CMU--1 Bus Inactive faultis declared.REMARK : The three seconds of filtering is applied by the SDU to cover the possibility that the (C)MU doesnot apply any time filtering to its activation of bit 16.(C)MU--1 Master TEST/LOOP Failure (33 0 07)DESCRIPTION : If this CMU fails to respond to two consecutive SOLO TEST words with the correct LOOPword, then this fault is declared if the SDU is either the sole SDU in a single system or the Master in a dualsystem.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--97PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : As soon as the CMU responds to a SOLO TEST word with the correct LOOP word, aCMU--1 Bus Inactive fault is declared, or a CMU--1 Slave Protocol Error is declared.REMARK : A nuisance case of this failure may occur on Airbus aircraft when the CFDS is not powered on oris otherwise not functioning properly, due to the fact that the CFDS is used to inform the ATSU of the SDU’spresence or absence. If the CFDS does not inform the ATSU thatthe SDU is installed, then the ATSU will ignore the SDU’s TEST words, resulting in this failure being raised.Such nuisance failure should not occur if the CFDS is powered on and is operating normally.(C)MU--1 Slave TEST/LOOP Failure (33 0 08)DESCRIPTION : If this CMU fails to respond to two consecutive SOLO TEST words with the correct LOOPword, then this fault is declared if the SDU is the Slave in a dual system.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : As soon as the CMU responds to a SOLO TEST word with the correct LOOP word, aCMU--1 Bus Inactive fault is declared, or a CMU--1 Master Protocol Error is declared.REMARK : See the Remark in Section 4.4.5.51.20.7 regarding failure 33 0 07.(C)MU--2 (Level 1 Code 34h)Same as for (C)MU--1, except (C)MU--2 for (C)MU--1.IRS--PRI (Level 1 Code 35h)IRS--PRI, Unknown SRU (SRU Code 0h)COMMENTARYIf the SDU is strapped for both IRSs being installed (Primary and Secondary), the SDU softwareuses the IRS inputs as follows:The Primary IRS is initially selected to be the active IRS data source. The Secondary IRS is monitored for itshealth status, such that the SDU can revert to the Secondary IRS if the Secondary is healthy and the Primaryfails. Such reversions can thereafter occur in either direction if the currently selected IRS fails and the otherIRS is healthy.The ARINC 429 receiver used for the IRS interface is programmed to constantly detect the seven 429 labelsused by the SDU software on seven of its input channels (one label per channel) from the currently selectedIRS interface. A single channel of an ARINC 429 receiver is used to monitor the IRS input that is NOTcurrently selected, by dynamically programming the label--matching register to input one different label (of theseven labels used) every second ---- i.e., on the monitored bus, each label is examined for validity andpresence every seven seconds.<IRS--PRI> Spare (35 0 01)<IRS--PRI> Lat (310) Data Fail (35 0 02)DESCRIPTION : A data failure condition associated with latitude data has been detected. The possiblefailure conditions are; latitude data update rate failure (ARINC latitude words received atless than the minimum update rate or more than the maximum update rate if the associatedbus is not inactive), a valid ARINC IRS data word (latitude, longitude, ground speed, trackangle, true heading, pitch or roll) received with the SSM status field set to the ’FailureWarning’ state or an ARINC latitude data word received with the SSM status field set to the’No Computed Data’ state.The maximum update rate for ARINC latitude words is 15 words in a one second intervaland the minimum is 3 words in a one second interval. Maximum and minimum update ratesare derived from minimum and maximum transmit intervals respectively as defined inSection 14 Attachment 2 Table 2 of this document, with a tolerance margin added.PARAMETERS : Last Latitude word received and the number of words received in the last second.FAIL CRITERIA : A ’Failure Warning’ or ’No Computed Data’ SSM status field state failure will be reportedimmediately. Update rate failures will be reported within five seconds of occurrence if theIRS is selected or within seven seconds if the IRS is being monitored for test purposes.RECOVERY CRIT. : Failure recovery will be reported within one second of recovery from all possible failurecriteria for this fault if this IRS is selected or within seven seconds if the IRS is beingRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--98monitored for test purposesREMARK : Reversion between IRS sources is discussed in Section 4.4.6, relating to the [nav]functional resource.4.4.5.53.20.3 <IRS--PRI> Spare (35 0 03)4.4.5.53.20.4 <IRS--PRI> Lon (311) Data Fail (35 0 04)DESCRIPTION : A data failure condition associated with longitude data has been detected. The possiblefailure conditions are; longitude data update rate failure (ARINC longitude words received at less than theminimum update rate or more than the maximum update rate if the associated bus is not inactive), a validARINC IRS data word (latitude, longitude, ground speed, track angle, true heading, pitch or roll) received withthe SSM status field set to the ’Failure Warning’ state or an ARINC longitude data word received with theSSM status field set to the ’No Computed Data’ state.The maximum update rate for ARINC longitude words is 15 words in a one second interval and the minimumis 3 words in a one second interval. Maximum and minimum update rates are derived from minimum andmaximum transmit intervals respectively with a tolerance margin added.PARAMETERS : Last Longitude word received and the number of words received in the last second.FAIL CRITERIA : A ’Failure Warning’ or ’No Computed Data’ SSM status field state failure will be reportedimmediately. Update rate failures will be reported within five seconds of occurrence if theIRS is selected or within seven seconds if the IRS is being monitored for test purposes.RECOVERY CRIT. : Failure recovery will be reported within one second of recovery from all possible failurecriteria for this fault if this IRS is selected or within seven seconds if the IRS is being monitored for testpurposes.REMARK : Reversion between IRS sources is discussed in Section 4.4.6, relating to the [nav]functional resource.<IRS--PRI> Spare (35 0 05)<IRS--PRI> Grd Spd (312) Data Fail (35 0 06)DESCRIPTION : A data failure condition associated with ground speed data has been detected. The possiblefailure conditions are; ground speed data update rate failure (ARINC ground speedwords received at less than the minimum update rate or more than the maximum update rate if theassociated bus is not inactive), a valid ARINC IRS data word (latitude, longitude, ground speed, track angle,true heading, pitch or roll) received with the SSM status field set to the ’Failure Warning’ state or an ARINCground speed data word received with the SSM status field set to the ’No Computed Data’ state. Themaximum update rate for ARINC ground speed words is 45 words in a one second interval and the minimumis 8 words in a one second interval. Maximum and minimum update rates are derived from minimum andmaximum transmit intervals respectively with a tolerance margin added.PARAMETERS : Last Ground Speed word received and the number of words received in the last second.FAIL CRITERIA : A ’Failure Warning’ or ’No Computed Data’ SSM status field state failure will be reportedimmediately. Update rate failures will be reported within five seconds of occurrence if theIRS is selected or within seven seconds if the IRS is being monitored for test purposes.RECOVERY CRIT. : Failure recovery will be reported within one second of recovery from all possible failurecriteria for this fault if this IRS is selected or within seven seconds if the IRS is being monitored for testpurposes.REMARK :<IRS--PRI> Spare (35 0 07)<IRS--PRI> Trk (313) Data Fail (35 0 08)DESCRIPTION : A data failure condition associated with track angle data has been detected. The possiblefailure conditions are; track angle data update rate failure (ARINC track angle wordsreceived at less than the minimum update rate or more than the maximum update rate if the associated busis not inactive), a valid ARINC IRS data word (latitude, longitude, ground speed, track angle, true heading,pitch or roll) received with the SSM status field set to the ’Failure Warning’ state or an ARINC track angledata word received with the SSM status field set to the ’No Computed Data’ state. Track angle wordsreceived with the SSM field set to the ’No Computed Data’ state shall only be considered as failure conditionsif the current ground speed indicates that the aircraft is airborne.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--99The maximum update rate for ARINC track angle words is 45 words in a one second interval and theminimum is 1 word in a one second interval. Maximum and minimum update rates are derived from minimumand maximum transmit intervals respectively with a tolerance margin added.COMMENTARYThe extremely low minimum update rate is specifically set to tolerate the Honeywell Laseref II Type HG 1075AE03, which outputs this word at only a 2 Hz rate. The preferred minimum rate is 18 words in a one secondinterval (which accommodates the minimum value of 20 words in a one second interval specified by ARINCCharacteristic 704).PARAMETERS : Last Track Angle word received and the number of words received in the last second.FAIL CRITERIA : A ’Failure Warning’ or ’No Computed Data’ SSM status field state failure will be reportedimmediately. Update rate failures will be reported within five seconds of occurrence if theIRS is selected or within seven seconds if the IRS is being monitored for test purposes.RECOVERY CRIT. : Failure recovery will be reported within one second of recovery from all possible failurecriteria for this fault if this IRS is selected or within seven seconds if the IRS is being monitored for testpurposes.REMARK : Reversion between IRS sources is discussed in Section 4.4.6, relating to the [nav]functional resource.<IRS--PRI> Spare (35 0 09)<IRS--PRI> True Hdg (314) Data Fail (35 0 0A)DESCRIPTION : A data failure condition associated with true heading data has been detected. The possiblefailure conditions are; true heading data update rate failure (ARINC true heading words received at less thanthe minimum update rate or more than the maximum update rate ifthe associated bus is not inactive), a valid ARINC IRS data word (latitude, longitude, ground speed, trackangle, true heading, pitch or roll) received with the SSM status field set to the ’Failure Warning’ state or anARINC true heading data word received with the SSM status field set to the ’No Computed Data’ state.The maximum update rate for ARINC true heading words is 45 words in a one second interval and theminimum is 18 words in a one second interval. Maximum and minimum update rates are derived fromminimum and maximum transmit intervals respectively with a tolerance marginadded.PARAMETERS : Last True Heading word received and the number of words received in the last second.FAIL CRITERIA : A ’Failure Warning’ or ’No Computed Data’ SSM status field state failure will be reportedimmediately. Update rate failures will be reported within five seconds of occurrence if theIRS is selected or within seven seconds if the IRS is being monitored for test purposes.RECOVERY CRIT. : Failure recovery will be reported within one second of recovery from all possible failurecriteria for this fault if this IRS is selected or within seven seconds if the IRS is being monitored for testpurposes.REMARK :<IRS--PRI>Spare(3500B)<IRS--PRI> Pitch (324) Data Fail (35 0 0C)DESCRIPTION : A data failure condition associated with pitch data has been detected. The possible failureconditions are; pitch data update rate failure (ARINC pitch words received at less than the minimum updaterate or more than the maximum update rate if the associated bus is notinactive), a valid ARINC IRS data word (latitude, longitude, ground speed, track angle, true heading, pitch orroll) received with the SSM status field set to the ’Failure Warning’ state oran ARINC pitch data word received with the SSM status field set to the ’No Computed Data’ state.The maximum update rate for ARINC pitch words is 120 words in a one second interval and the minimum is20 words in a one second interval. Maximum and minimum update rates are derived from minimum andmaximum transmit intervals respectively with a tolerance margin added.PARAMETERS : Last Pitch word received and the number of words received in the last second.FAIL CRITERIA : A ’Failure Warning’ or ’No Computed Data’ SSM status field state failure will be reportedimmediately. Update rate failures will be reported within five seconds of occurrence if theIRS is selected or within seven seconds if the IRS is being monitored for test purposes.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--100RECOVERY CRIT. : Failure recovery will be reported within one second of recovery from all possible failurecriteria for this fault if this IRS is selected or within seven seconds if the IRS is being monitored for testpurposes.REMARK :<IRS--PRI>Spare(3500D)<IRS--PRI> Roll (325) Data Fail (35 0 0E)DESCRIPTION : A data failure condition associated with roll data has been detected. The possible failureconditions are; roll data update rate failure (ARINC roll words received at less than the minimum update rateor more than the maximum update rate if the associated bus is notinactive), a valid ARINC IRS data word (latitude, longitude, ground speed, track angle, true heading, pitch orroll) received with the SSM status field set to the ’Failure Warning’ state oran ARINC roll data word received with the SSM status field set to the ’No Computed Data’ state.The maximum update rate for ARINC roll words is 120 words in a one second interval and the minimum is 20words in a one second interval. Maximum and minimum update rates are derived from minimum andmaximum transmit intervals respectively with a tolerance margin added.PARAMETERS : Last Roll word received and the number of words received in the last second.FAIL CRITERIA : A ’Failure Warning’ or ’No Computed Data’ SSM status field state failure will be reportedimmediately. Update rate failures will be reported within five seconds of occurrence if theIRS is selected or within seven seconds if the IRS is being monitored for test purposes.RECOVERY CRIT. : Failure recovery will be reported within one second of recovery from all possible failurecriteria for this fault if this IRS is selected or within seven seconds if the IRS is being monitored for testpurposes.REMARKIRS--SEC (Level 1 Code 36h)Same as for IRS--PRI except substitute IRS--SEC for IRS--PRI.CMC/CFDIU (Level 1 Code 39h)CMC/CFDIU, Unknown SRU (SRU Code 39h)Invalid OMS Data (39 0 01)DESCRIPTION : This fault is applicable prior to SDU Part Number 7516118--XX130/--xx140, and shall onlyapply to aircraft strapped for “Airbus” CFDS type. This fault is declared when any Airbus on--boardmaintenance system (OMS) “general parameter” data item (any one of labels 125, 126, 155--157, 227,233--237, 260, 301--303 [and 304 if processed] ---- is received with SSM = FW (where applicable) or the datais not received with an update period better than 10 times the period.PARAMETERS : The 32--bit Failure Parameter shall use single--bit coding per condition to indicate thespecific nature of the failure. The parameter is structured as follows:BIT NUMBER WEIGHT (HEX) MEANING0 0000 0001 Label 125 received with SSM = FW1 0000 0002 Label 126 “2 0000 0004 Label 155 “3 0000 0008 Label 156 “4 0000 0010 Label 157 “BIT NUMBER WEIGHT (HEX) MEANING5 0000 0020 Spare (0) [Label 227 has no SSM field]6 0000 0040 Label 233 received with SSM = FW7 0000 0080 Label 234 “8 0000 0100 Label 235 “9 0000 0200 Label 236 “10 0000 0400 Label 237 “11 0000 0800 Label 260 “12 0000 1000 Spare (0) [Label 301 has no SSM field]13 0000 2000 Spare (0) [Label 302 has no SSM field]14 0000 4000 Spare (0) [Label 303 has no SSM field]15 0000 8000 Spare (0)16 0001 0000 Label 125 received with update period > 10*NRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--10117 0002 0000 Label 126 “18 0004 0000 Label 155 “19 0008 0000 Label 156 “20 0010 0000 Label 157 “21 0020 0000 Spare (0) (Label 227 is covered by 59/0/01)22 0040 0000 Label 233 received with update period > 10*N23 0080 0000 Label 234 “24 0100 0000 Label 235 “25 0200 0000 Label 236 “26 0400 0000 Label 237 “27 0800 0000 Label 260 “28 1000 0000 Label 301 “29 2000 0000 Label 302 “30 4000 0000 Label 303 “31 8000 0000 Spare (0)BIT NUMBER WEIGHT (HEX) MEANINGN = The nominal period specified for that label.FAIL CRITERIA : This fault transitions to failure after any particular invalid condition persists for 60 secondsor 60 receipts of the OMS ARINC 429 label data (whichever occurs first), as longas failure 59 0 01 (CFDS bus inactive) is not already being declared.RECOVERY CRIT. : Immediately after the previously invalid OMS ARINC 429 label data is received as valid.REMARK : E.g., after finding a 40 second or worse update period for label 301, that condition must persist forat least 60 additional seconds before declaring this failure; or, after receiving alabel 125 word with SSM=FW, at least 60 additional such words must be received, or at least 60 seconds’worth of such words must be received, whichever occurs first, before declaring this failure. Since the MCSARINC 429 hardware handles parity checking and does not interrupt the processor for data with parity errors,but rather discards any such data, parity error coverage (required by Airbus) is handled under the dataupdate rate checks.Label 237 is not transmitted on A320s.COMMENTARYThe 32--bit failure parameter specified above was originally intended to permit multiple OMS ARINC 429 labeldata problems to share this single failure code, with the parameter field indicating the specific condition(s)causing the failure, such that multiple data failures occurring at different times could be captured by simplyupdating the stored parameter value. This proved to be impossible to properly implement in the software dueto the way it is structured for dealing with other existing requirements, such as the intermittent failureoccurrence counter. The 32--bit failure parameter is retained, but it is not capable of indicating multiple OMSdata problems occurring at different times.429 ICAO Address Source (Level 1 Code 40h)Unknown 429 ICAO Address Source SRU (SRU Code 0H)429 ICAO Address Fail (40 0 01)DESCRIPTION : This fault shall cover all problems with the SDU attempting to obtain the AES ID from a 429source of the ICAO Address, as directed by system configuration pin TP10A when it is in the “zero” state(reference Section 3.2.4.1). Once POST/PAST is complete, this fault shallbe declared if a valid ICAO address has not been obtained for any reason after a period of four seconds,including no activity on all three of the possible input buses, or if the received address is all zeros or all ones,or if the address cannot be determined because the SSM associated with either label shows other thannormal operation or no computed data.PARAMETERS : None.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : As soon as a valid AES ID can be constructed by the SDU from any of the 429 inputs.REMARK :Dual System Different 429 AES ID (40 0 02)DESCRIPTION : This fault is declared in a dual system if this SDU’s AES ID is obtained from an ARINC 429source, and a valid AES ID received from the other SDU on the cross--talk bus is different from this SDU’svalid AES ID.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--102PARAMETERS : 1st: This SDU’s AES ID2nd: Other SDU’s AES IDFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared if a valid AES ID is received from the other SDU which matchesthis SDU’s valid AES ID.REMARK : This fault is declared in both SDUs. No functional resource is indicted; however, one SDU willbecome disabled.CTU: Unknown SRU (SRU Code 0h)CCS ECL Not Established (42 0 01)DESCRIPTION : This fault is declared if the SDU cannot achieve full communications with the CTU on theECL link.Full communications have not been achieved when:-- the layer 2 SAPI 2 data link fails to establish after one second; or-- the layer 2 SAPI 2 data link is established but the CTU fails to respond to an ECL Request messageafter 10 seconds; or-- the layer 2 SAPI 2 data link is released.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediately (with the confirmation criteria included in thefailure description above).RECOVERY CRIT. : This failure is cleared when the SDU attains full communications on the ECL link.REMARK :CCS CCL Not Established (42 0 02)DESCRIPTION : This fault is declared if the SDU cannot achieve full communications with the CTU on theCCL link.Full communications have not been achieved when the layer 2 SAPI 0 data link fails toestablish within one second or is released.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediately (with the confirmation criteria included in thefailure description above).RECOVERY CRIT. : This failure is cleared when the layer 2 SAPI 0 data link is established.REMARK :CCS CTU Not Available (42 0 03)DESCRIPTION : This fault is declared if the CTU responds to an ECL ’Get CTU Availability’ request with aparameter other than ’Normal Operation’.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure if it is not cleared after 3 seconds.RECOVERY CRIT. : This failure is cleared when the CTU responds with ’Normal operation’.REMARK :CCS PDL Not Established (42 0 04)DESCRIPTION : This fault is declared if the SDU cannot achieve full communications with a packetdata--capable CTU on the PDL link, unless the SDU CEPT--E1 bus is inactive.Full communications have not been achieved when the layer 2 SAPI 16 data link fails toestablish after four retries or is released.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediately (with the confirmation criteria included in thefailure description above).RECOVERY CRIT. : This failure is cleared when the layer 2 SAPI 16 data link is established.REMARK :CPDF (Level 1 Code 43H)Same as for (C)MU--1, except substitute CPDF for (C)MU--1 and CMU, and removeAirbus references. In the failure descriptions, reference is made to the CMU declaring itself ’active’.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--103CPDF Spare (43 0 01)CPDF Status (270) Bad SSM (43 0 02)DESCRIPTION : This fault is raised if a Status word is received with anything other than “Normal Operation”(00b) in the SSM field.PARAMETERS : NoneFAIL CRITERIA : If the fault is active for five seconds.RECOVERY CRIT. : This failure shall clear as soon as a Status word is received with “Normal Operation” inits SSM field.REMARK :CPDF Master Protocol Error (43 0 03)DESCRIPTION : If this CPDF is the first CPDF to declare itself active after system init, and then itsubsequently does not respond with an ALR word after 3 transmissions of the ALO word to it, then this faultis declared if the SDU is configured as a single SDU or is the Master in a dual system.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : As soon as communication is re--established with this CPDF, a CDPF Bus Inactive faultis declared, or a CPDF Slave Protocol Error is declared.REMARK :CDPF Data Transmission Failure (43 0 04)DESCRIPTION : If the maximum number of RTS words have been sent to the CPDF without receiving a validCTS word or if the maximum number of attempts have been made for transmitting an LDU to the CPDFwithout receiving a valid ACK word when CPDF is the active DTE, this fault is declared.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : As soon as a successful transmission of an LDU has been made to the CPDF, or theCPDF responds to a SOLO TEST word, or when a CPDF Bus Inactive failure is declared.COMMENTARYA transmission failure indicates a break in the bus connecting the SDU output and the CPDF input. It shouldindict the [cpdf] resource because several back--to--back LDU transfers could prevent this being detected by aSOLO TEST/LOOP test. To make this failure recoverable it should be cleared once a SOLO TEST/LOOPtest succeeds (these are still carried out regardless of [cpdf] indictment).REMARK : Whenever the SDU has a data file ready to transmit to the CPDF, it follows the transferprocedure.CPDF Slave Protocol Error (43 0 05)DESCRIPTION : If this CPDF is the first CPDF to declare itself active after system init, and then itsubsequently does not respond with an ALR word after 3 transmissions of the ALO word to it, then this faultis declared if the SDU is the Slave in a dual system.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : As soon as communication is re--established with this CPDF, a CPDF Bus Inactive faultis declared, or a CPDF Master Protocol Error is declared.REMARK :CPDF Self--Declared Failure (43 0 06)DESCRIPTION : This fault is declared if the Fail bit (bit 16) of the Label 270 Status word received by the SDUfrom the CPDF is set.PARAMETERS : None.FAIL CRITERIA : This fault transitions to the failure state if it is continuously active for at least three seconds.RECOVERY CRIT. : As soon as a Status word is received with bit 16 cleared or a CPDF Bus Inactive fault isdeclared.REMARK : The three seconds of filtering is applied by the SDU to cover the possibility that the CPDF doesnot apply any time filtering to its activation of bit 16.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--104CPDF Master TEST/LOOP Failure (43 0 07)DESCRIPTION : If this CPDF fails to respond to two consecutive SOLO TEST words with the correct LOOPword, then this fault is declared if the SDU is either the sole SDU in a single system or the Master in a dualsystem.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : As soon as the CPDF responds to a SOLO TEST word with the correct LOOP word, aCPDF Bus Inactive fault is declared, or a CPDF Slave Protocol Error is declared.REMARK :CPDF Slave TEST/LOOP Failure (43 0 08)DESCRIPTION : If this CPDF fails to respond to two consecutive SOLO TEST words with the correct LOOPword, then this fault is declared if the SDU is the Slave in a dual system.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : As soon as the CPDF responds to a SOLO TEST word with the correct LOOP word, aCPDF Bus Inactive fault is declared, or a CPDF Master Protocol Error is declared.REMARK :SDU HSU1 Bus Inactive (50 0 01)DESCRIPTION : This fault is raised if no label 270 words have been received from the HSU in the last threeseconds of operation outside of the system--wide POST/PAST period.PARAMETERS : None.FAIL CRITERIA : This fault transitions to failure immediately when the HSU is outside the POST/PAST, andshall also transition to failure 15 seconds after HSU PAST has been requested.RECOVERY CRIT. : Immediately after receipt of a valid Label 270 word in each of two successive 1--secondperiods.REMARK : NoneHSU1 Self--Test Misoperation (50 0 02)DESCRIPTION : This fault covers all possible misbehaviour related to HSU Functional Test outside thesystem--wide POST/PAST period (i.e., SDU--initiated during CM, HSU POST, HSU PAST, or HSUspontaneously entering functional test during SDU CM). This fault is notdeclared if the HSU bus inactive fault is active.PARAMETERS : 01: The HSU has not responded to functional test commanded for 15 seconds by the SDU(CM), i.e., as a result of the raising of an HSU specific CM.02: The HSU has started functional test commanded by the SDU (CM), but the SDU has notreceived an HSU self--test complete response within 40 seconds prior to SDU Part Number7516118--XX130/--xx140 or within 60 seconds for SDU Part Number 7516118--XX130/--xx140and subsequent.03: The HSU has not entered functional test within 15 seconds of the PAST Requested bit inthe HSU Status Word being set.04: The HSU has entered un--commanded functional test as a result of an HSU POST.05: The HSU has spontaneously entered un--commanded functional test for an unknownreason.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure shall clear as soon as a fault clearance is declared, (i.e., if and when theHSU self--test finally completes).REMARK : Functional Test response checking is determined on the HSU Status Word’s SSM field. This faultis typically caused by the HSU breaker being pulled, which generates the (50 001) failure; when power is restored, the SDU will clear the Bus Inactivity failure (50 0 01), and the LRUself--test executes, which generates this self--test misoperation failure. Hence, this self test misoperationfailure is typically not indicative of an LRU failure, so it uses this bus inactive level 1 code (50) as opposed tothe HSU level 1 code (08 or 09 prior to SDU Part Number 7516118--XX130/--xx140, or 03 for SDU PartNumber 7516118--XX130/--xx140 and subsequent). The POST/PAST version of this fault is (08 0 84) prior toSDU Part Number 7516118--XX130/--xx140, or (03 0 84) for SDU Part Number 7516118--XX130/--xx140 andsubsequent.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--105HSU1 Periodic Data Rate Fail (50 0 03)DESCRIPTION : This fault is declared when the rate at which periodic ARINC 429 words are received fromthe HSU exceeds 22 words over a period of 1 second prior to SDU Part Number 7516118--XX130/--xx140 or48 words over a period of 1 second for SDU Part Number 7516118--XX130/--xx140 and subsequent. Allperiodic ARINC word transmissions by the HSU (labels 172, 270, 271, 272, 273, 274, 275 prior to SDU PartNumber 7516118--XX130/--xx140 and labels 172, 301 -- 306, 351, 352 for SDU Part Number7516118--XX130/--xx140 and subsequent) is monitored to generate the required word count.PARAMETERS : Monitored periodic word data rate.FAIL CRITERIA : This fault transitions into failure if the fault persists for at least 3 seconds.RECOVERY CRIT. : The SDU shall assert the HSU System Disable discrete for 10 seconds. This failure iscleared when, following the associated HSU reset, the SDU’s input bus from the HSU transitions from aninactive to an active state, with the SSM field of the Label 270 status word indicating Functional Test.REMARK : Under normal conditions, the SDU is expected to receive 11 periodic words per second prior toSDU Part Number 7516118--XX130/--xx140 and up to 24 periodic words per second for SDU Part Number7516118--XX130/--xx140 and subsequent; the failure threshold is double this value.4.4.5.80.3 HSU1 Solo Word Data Rate Fail (50 0 04)DESCRIPTION : This fault is declared when the rate at which solo words are received from the HSU exceeds200 words over a period of 1 second. ARINC label 276 (prior to SDU Part Number 7516118--XX130/--xx140)or label 300 (for SDU Part Number 7516118--XX130/--xx140 and subsequent) transmissions by the HSU ismonitored to generate the required word count.PARAMETERS : Monitored solo word data rate.FAIL CRITERIA : This fault transitions into failure if the fault persists for at least 3 seconds.RECOVERY CRIT. : The SDU shall assert the HSU System Disable discrete for 10 seconds. This failure iscleared when, following the associated HSU reset, the SDU’s input bus from the HSU transitions from aninactive to an active state, with the SSM field of the Label 270 status word indicating Functional Test.REMARK : Under normal conditions prior to SDU Part Number 7516118--XX130/--xx140, the SDU is requiredto receive no more than 200 words per second based on its use for Carrier On/Off commands (in 5--wordbursts), which should be separated by at least 25ms.HSU1 Williamsburg Data Rate Fail (50 0 05)DESCRIPTION : This fault is declared when the rate at which Williamsburg words are received from the HSUexceeds 120 words over a period of 1 second. ARINC label 307 (173 for SDU #2) transmissions by the HSUis monitored to generate the required word count.PARAMETERS : Monitored Williamsburg word data rate.FAIL CRITERIA : This fault transitions into failure if the fault persists for at least 3 seconds.RECOVERY CRIT. : The SDU shall assert the HSU System Disable discrete for 10 seconds. This failure iscleared when, following the associated HSU reset, the SDU’s input bus from the HSU transitions from aninactive to an active state, with the SSM field of the Label 270 status word indicating Functional Test.REMARK :SDU HSU2 Bus Inactive (Level 1 Code 51h)Same as for Level 1 code 50 X XX, except substitute “HSU2” for “HSU1”. Only applicable prior to SDU PartNumber 7516118--XX130/--xx140.CPDF To SDU Bus Inactive (52 0 01)Same as for (C)MU--1 Bus Inactive (Section 4.4.5.83).SDU CMU--1 Bus Inactive (53 0 01)DESCRIPTION : This fault is declared if no CMU status word has been received in the last three seconds ofoperation outside of the system--wide POST/PAST period prior to SDU Part Number 7516118--XX130/--xx140and in the last 10 seconds for packages 6.0 and beyond.PARAMETERS : None.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : If at least one status word is received with no parity errors in each of two successive onesecond periods.REMARK : The status word nominally arrives at 1Hz.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--106SDU CTU CEPT--E1 Bus Inactive (54 0 01)DESCRIPTION : This fault is declared if the CTU CEPT--E1 interface circuitry detects that the bus is notsynchronised and the CCS configuration strap indicates that the CTU is present.PARAMETERS : None.FAIL CRITERIA : Prior to SDU Part Number 7516118--XX130/--xx140, this fault transitions to failure if notcleared after 3 seconds. For SDU Part Number 7516118--XX130/--xx140 and subsequent, this fault transitionsto failure if not cleared after 120 seconds.RECOVERY CRIT. : When the CTU CEPT--E1 interface achieves synchronisation.REMARK :SDU SCDU/WSC--1 Bus Inactive (55 0 01)DESCRIPTION : Prior to Package 4.0, this fault is declared if no Label 377 Equipment Identification word hasbeen received from SCDU1 in the last three seconds of operation outside of the system--wide POST/PASTperiod.For Packages 4.0 and subsequent, this fault is used for an inactive bus on the SDU’s MP3C/D input, whetherinterfaced to an ARINC 739 SCDU or an ARINC 741 WSC, with thecontroller type indicated by the programming state of system configuration pin TP10H as specified in Section3.2.4.7. For the SCDU case, the definition is unchanged fromthat for prior software packages. For the WSC case, this fault is declared if no Label 270 status words havebeen received from WSC1 in the last three seconds of operation outside of the system--wide POST/PASTperiod.For Packages 6.0 and subsequent, for WSC configurations only (not for SCDU configurations), the criteria forthe period of label 270 inactivity is increased to 10 seconds.PARAMETERS : None.FAIL CRITERIA : This fault transitions to the failure state immediately.RECOVERY CRIT. : Prior to Package 4.0, if at least one Equipment Identification word is received fromSCDU1 with no parity errors.For Packages 4.0 and subsequent, for the SCDU case, the same as for prior software packages; for theWSC case, if at least one Label 270 Status word is received from WSC1 with no parity errors in each of twosuccessive one--second periods.REMARK : The SCDU Equipment Identification and WSC Status words are nominally received from theirrespective sources (depending on the installation configuration) at a rate of 1 Hz.SDU SCDU/WSC--2 Bus Inactive (56 0 01)Same as fault 55 0 01, except substitute SCDU2 or WSC2 for SCDU1 or WSC1.SDU CMU--2 Bus Inactive (57 0 01)Same as SDU CMU--1 Bus Inactive.SDU CFDS Bus Inactive (59 0 01)DESCRIPTION : This fault is declared if no label 227 words are received in the last 3 to 7 seconds ofoperation outside of the system--wide POST/PAST period prior to SDU Part Number7516118--XX130/--xx140, and in the last 10 seconds for packages 6.0 and beyond. This requirement appliesto all aircraft configurations and modes of operation, except for the “CAIMS wait” state of Maintenance Modein the CAIMS configuration (refer to SYP 4.3.7.3.2.2.6) ---- in this special case, the fault is declared if no label227 words are received in the last 3 minutes of operation.COMMENTARYThe pre--SDU Part Number 7516118--XX130/--xx140 software implementation has an indeterminatenature such that the declaration of this fault will occur after a minimum of 3 seconds and a maximum of 7seconds after receipt of the last label 227 word.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is cleared if at least one label 227 word is received without any parity errorsin each of two successive one--second periods.REMARK : This fault shall clear any current rate, protocol or data failures associated with the SDU’s inputfrom the CFDS. The nominal rate of arrival of label 227 words is 1Hz.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--107Invalid OMS Data (59 0 02)DESCRIPTION : This fault is applicable for SDU Part Number 7516118--XX130/--xx140 and subsequent, andshall only apply to aircraft strapped for “Airbus” CFDS type. This fault is declared when any Airbus on--boardmaintenance system (OMS) “general parameter” data item (any one of labels 125, 126, 155--157, 233--237,260, 301--303 [and 304 if processed] ---- is received with SSM = FW (where applicable) or the data is notreceived with an update period better than 10 times the period specified for the data.PARAMETERS : The 32--bit Failure Parameter shall use single--bit coding per condition to indicate thespecific nature of the failure. The parameter is structured as follows:BIT NUMBER WEIGHT (HEX) MEANING0 0000 0001 Label 125 received with SSM = FW1 0000 0002 Label 126 “2 0000 0004 Label 155 “3 0000 0008 Label 156 “4 0000 0010 Label 157 “5 0000 0020 Spare (0) [Label 227 has no SSM field]6 0000 0040 Label 233 received with SSM = FW7 0000 0080 Label 234 “8 0000 0100 Label 235 “9 0000 0200 Label 236 “10 0000 0400 Label 237 “11 0000 0800 Label 260 “12 0000 1000 Spare (0) [Label 301 has no SSM field]13 0000 2000 Spare (0) [Label 302 has no SSM field]14 0000 4000 Spare (0) [Label 303 has no SSM field]15 0000 8000 Spare (0)16 0001 0000 Label 125 received with update period > 10*N17 0002 0000 Label 126 “18 0004 0000 Label 155 “19 0008 0000 Label 156 “20 0010 0000 Label 157 “21 0020 0000 Spare (0) [Label 227 is covered by 59/0/01]22 0040 0000 Label 233 received with update period > 10*N23 0080 0000 Label 234 “24 0100 0000 Label 235 “25 0200 0000 Label 236 “26 0400 0000 Label 237 “27 0800 0000 Label 260 “28 1000 0000 Label 301 “29 2000 0000 Label 302 “30 4000 0000 Label 303 “31 8000 0000 Spare (0)N = The nominal period specified for that label in Section 4.3.7.4.1.FAIL CRITERIA : This fault transitions to failure after any particular invalid condition persists for 60 secondsor 60 receipts of the OMS ARINC 429 label data (whichever occurs first), as longas (per Section 4.3.3) failure 59 0 01 (CFDS bus inactive) is not already being declared.RECOVERY CRIT. : Immediately after the previously invalid OMS ARINC 429 label data is received as valid.REMARK : E.g., after finding a 40 second or worse update period for label 301, that condition must persist forat least 60 additional seconds before declaring this failure; or, after receiving a label 125 word with SSM=FW,at least 60 additional such words must be received, or at least 60 seconds’ worth of such words must bereceived, whichever occurs first, before declaring this failure. Since the MCS ARINC 429 hardware handlesparity checking and does not interrupt the processor for data with parity errors, but rather discards any suchdata, parity error coverage (required by Airbus) is handled under the data update rate checks.Label 237 is not transmitted on A320s.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--108COMMENTARYThe 32--bit failure parameter specified above was originally intended to permit multiple OMS ARINC 429label data problems to share this single failure code, with the parameter field indicating the specificcondition(s) causing the failure, such that multiple data failures occurring at different times could becaptured by simply updating the stored parameter value. This proved to be impossible to properlyimplement in the software due to the way it is structured for dealing with other existing requirements, suchas the intermittent failure occurrence counter. The 32--bit failure parameter is retained, but it is notcapable of indicating multiple OMS data problems occurring at different times.SDU Pri IRS Bus Inactive (5A 0 01)DESCRIPTION : A primary IRS bus inactive fault is reported if no ARINC latitude(310), longitude(311),ground speed(312), track angle(313), true heading(314), pitch(324) or roll(325) data words are received withinthe last one second of operation outside of the system--widePOST/PAST period.PARAMETERS : None.FAIL CRITERIA : Primary IRS bus inactive failure is reported if the primary IRS input is selected and noARINC words are received during a three second interval. The same fault is also reported if the primary IRSinput is being monitored for test purposes and no ARINC words arereceived during a seven second interval.RECOVERY CRIT. : Recovery from primary IRS bus inactive failure is reported if the primary IRS input isselected and ARINC words are received during a two second interval. Recovery is alsoreported if the primary IRS input is being monitored for test purposes and ARINC words are received during aseven second interval.REMARK :SDU Sec IRS Bus Inactive (5B 0 01)Same as SDU Pri IRS Bus Inactive, except replace Pri with Sec throughout.SDU HGA/IGA HPA BITE Bus Inactive (5C 0 01)DESCRIPTION : No ARINC 429 words (labels 143, 171, 350) without parity problems have been receivedwithin the last two successive one--second periods.PARAMETERS : None.FAIL CRITERIA : This fault transitions to failure if the fault persists for at least two seconds.RECOVERY CRIT. : The fault is cleared after any data is received without parity errors in each of twosuccessive one--second periods; the failure is cleared after a further seven seconds.REMARK : The seven second recovery timer is applied by the SDU to ensure that the [hga_subsys]functional resource remains indicted during the HPA self--tests, since the “Self TestMisoperation” CM fault is not raised when it is preceded by a bus inactivity fault.HGA/IGA HPA Self--Test Misoperation (5C 0 02)DESCRIPTION : This fault covers all possible CM misbehaviour related to HPA Functional Test. This fault isnot declared if the HGA HPA bus inactivity fault is being raised.PARAMETERS : 04: The HPA indicated functional test active outside the system--wide POST/PAST period(i.e., the HPA spontaneously entered functional test, or remained in functional test beyond the end of SystemInitialization and Self--Test).FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure shall clear as soon as a fault clearance is declared, (i.e., if and when thespontaneous or extended self test finally completes).REMARK : Functional Test response checking is determined on the HPA Status Word’s SSM field. This faultis typically caused by the HPA breaker being pulled, which generates the (5C 0 01) failure; when power isrestored, the LRU self--test executes, which generates this selftest misoperation failure and clears the businactive failure (5C 0 01). Hence, this self test misoperation failure is typically not indicative of an LRU failure,so it uses this bus inactive level 1 code (5C) as opposed to the HPA level 1 code (04).SDU LGA HPA BITE Bus Inactive (5F 0 01)Same as HGA HPA BITE Bus Inactive.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--109LGA HPA Self--Test Misoperation (5F 0 02)Same as HGA/IGA HPA Self--Test Misoperation.SDU Top/Port BSU/ACU BITE Bus Inactive (62 0 01)DESCRIPTION : No ARINC 429 words (labels 144, 350) without parity problems, have been received on thisbus in the last two successive one--second periods.PARAMETERS : None.FAIL CRITERIA : This fault transitions to failure if the fault persists for at least two seconds.RECOVERY CRIT. : The fault is cleared after any data is received without parity errors in each of twosuccessive one--second periods; the failure is cleared after a further seven seconds.REMARK : The seven second recovery timer is applied by the SDU to ensure that the [hga_subsys]functional resource remains indicted during the HPA self--tests, since the “Self TestMisoperation” CM fault is not raised when it is preceded by a bus inactivity fault. This fault will only bereported if Top/Port BSU is configured as present in system.Top/Port BSU/ACU Self--Test Misoperation (62 0 02)DESCRIPTION : This fault covers all possible CM misbehaviour related to BSU Functional Test. This fault isnot declared if the bus inactivity fault is being raised.PARAMETERS : 01 : The BSU indicated functional test active outside the system--wide POST/PAST period(i.e., the BSU spontaneously entered functional test, or remained in functional test beyond the end of SystemInitialization and Self--Test).FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure shall clear as soon as a fault clearance is declared, i.e. if and when thespontaneous or extended self test finally completes.REMARK : Functional Test response checking is determined on the BSU Maintenance word’s SSM field. Thisfault is typically caused by the BSU breaker being pulled, which generates the(62 0 01) failure; when power is restored, the LRU self--test executes, which generates this self--testmisoperation failure and clears the bus inactive failure (62 0 01). Hence, this self test misoperation failure istypically not indicative of an LRU failure, so it uses this bus inactive level 1 code (62) as opposed to the BSUlevel 1 code (13).SDU Stbd BSU BITE Bus Inactive (64 0 01)Same as Top/Port BSU BITE Bus Inactive except substitute Stbd BSU for Top/Port BSU.Starboard BSU/ACU Self--Test Misoperation (64 0 02)Same as Top/Port BSU/ACU Self Test Misoperation.SDU SCDU/WSC--3 Bus Inactive (66 0 01)Same as fault 55 0 01, except substitute SCDU3 or WSC3 for SCDU1 or WSC1.SDU Cross--Talk Bus Inactive (71 0 01)DESCRIPTION : This fault is declared in a dual system after the completion of POST/PAST if the cross--talkbus becomes inactive, i.e., no valid DCS words are received from the other SDUfor a period of 0.3 second.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if it persists for 3 seconds or longer.RECOVERY CRIT. : As soon as any data with valid parity is received in each of two successive 0.1 secondperiods.REMARK :HGA/IGA HPA Multicontrol Bus Inactive (Level 1 Code 90)HGA/IGA HPA 429 Maintenance Word Control Bus Inactive (90 0 01)DESCRIPTION : The last HPA Maintenance Word was received with bit #15 set.PARAMETERS : None.FAIL CRITERIA : This fault transitions to failure after the receipt of at least four consecutive maintenancewords with bit 15 set, and if the fault persists for more than three seconds.RECOVERY CRIT. : As soon as an HPA Maintenance Word is received with bit #15 cleared.REMARK : The additional four--sample filtering is applied by the SDU to cover the possibility of othermanufacturers’ HPAs not applying any filtering to their activation of Maintenance Word bit 15.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--110HGA/IGA HPA Multicontrol Bus Inactive (90 0 02)DESCRIPTION : The HPA has received no data with valid parity on the Multicontrol bus during the previoussecond; the HPA shall set bit 15 in its Maintenance words while this failure is active.PARAMETERS : None.FAIL CRITERIA : If the fault is active for three seconds or longer.RECOVERY CRIT. : As soon as any data with valid parity is received in each of two successive one--secondperiods.REMARK : The SDU will raise failure (90 0 01) per section 4.4.5.144.1 while bit 15 in the HPA Maintenanceword is set.LGA HPA Multicontrol Bus Inactive (96 0 01, 96 0 02)Same as HGA HPA Multicontrol bus Inactive.Top/Port BSU/ACU Multicontrol Bus Inactive (98 0 01)DESCRIPTION : Discrete bit #13 in Top/Port BSU/ACU Maintenance Word (350) set indicating Control BusInput inactive.PARAMETERS : None.FAIL CRITERIA : This fault transitions to failure after the receipt of four consecutive maintenance words withbit 13 set.RECOVERY CRIT. : As soon as a TOP/PORT BSU Maintenance Word is received with bit #13 clear.REMARK : The four--sample filtering is applied by the SDU to cover the possibility that the BSU/ACU doesnot apply any filtering to its activation of Maintenance Word bit 13.Port BSU Crosstalk Bus Inactive (9A 0 01)DESCRIPTION : Discrete bit #12 of Port BSU Maintenance Word is set indicating that the Crosstalk Input isinactive.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to failure after the receipt of four consecutive maintenance words withbit 12 set.RECOVERY CRIT. : As soon as a Port BSU Maintenance Word is received with bit #12 clear.REMARK : The four--sample filtering is applied by the SDU to cover the possibility that the BSU/ACU doesnot apply any filtering to its activation of Maintenance Word bit 12.Stbd BSU Multicontrol Bus Inactive (9C 0 01)Same as Top/Port Multicontrol Bus Inactive except substitute Stbd BSU for Top/Port BSU.Stbd BSU Crosstalk Bus Inactive (9D 0 01)Same as Top/Port Crosstalk Bus Inactive.HSU1 429 Control Bus Inactive ( 9E 0 01)DESCRIPTION : The SDU shall raise this fault when the SDU Signalling Bus bit of the HSU Status word isnot set, indicating that the HSU’s input bus is inactive.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to failure after this condition is indicated in at least 15 consecutiveHSU status words.RECOVERY CRIT. : Immediately after receipt of at least 10 consecutive valid HSU status words with theSDU Signalling Bus bit set.REMARK : None.HSU1 ICAO Address Invalid (9E 0 02)DESCRIPTION : This fault is applicable prior to SDU Part Number 7516118--XX130/--xx140 only, and israised by the SDU in response to the HSU Williamsburg file transfer for HSU fail code 0E/77 (L2/L3), i.e., theICAO address provided by the SDU to the HSU does not match the one programmed in theHSU CDM, or no ICAO address has been received from the SDU within 10 seconds ofachieving full communications (reference section 3.4.1.1.2).PARAMETERS :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--111* This 7--bit ASCII code is shifted left one bit position in order to have the Category bit in bit 0.FAIL CRITERIA : The fault transitions to failure immediately.RECOVERY CRIT. : Immediately upon receipt of a valid ICAO address by the HSU from the SDU, whichmatches the one programmed in the HSU CDM.REMARK :HSU1 Position Unavailable (9E 0 03)DESCRIPTION : This fault is applicable prior to SDU Part Number 7516118--XX130/--xx140 only, and israised by the SDU in response to the Williamsburg file transfer for HSU fail code 0E/78 (L2/L3), i.e., the HSUis not receiving valid latitude and/or longitude position data from the SDU, and also when a timeout of 15seconds has elapsed since the last position was received.PARAMETERS : HSU has received position data but latitude and/or longitude is invalid:SOUR: Failure Parameter Value -- 0000 534FxAssociated Parameter Value -- 0000 55A5x or 0000 55A4xMore than 15 seconds have elapsed since the last position was received:TIME: Failure Parameter Value -- 0000 5449xAssociated Parameter Value -- 0000 4D8Ax or 0000 4D8BxRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--112FAIL CRITERIA : The fault transitions to failure immediately.RECOVERY CRIT. : Immediately upon receipt of valid data by the HSU from the SDU.REMARK :HSU1 Velocity Unavailable (9E 0 04)DESCRIPTION : This fault is applicable prior to SDU Part Number 7516118--XX130/--xx140 only, and israised by the SDU in response to the HSU Williamsburg file transfer for HSU fail code 0E/79 (L2/L3), i.e., theHSU is not receiving aircraft velocity data from SDU.PARAMETERS : The HSU has not received a velocity ARINC word for the past 7.5 seconds:Lost: Failure Parameter Value -- 0000 4C6FxAssociated Failure Parameter -- 0000 73E8x or 0000 73E9xThe HSU has not received a velocity ARINC word within 30 seconds after establishing full communications:Miss: Failure Parameter Value -- 0000 4D69xAssociated Parameter Value -- 0000 73E6x or 0000 73E7xFAIL CRITERIA : The fault transitions to failure immediately.RECOVERY CRIT. : Immediately upon receipt of valid data by the HSU from the SDU.REMARK :HSU2 429 Control Bus Inactive (Level 1 Code 9Fh)Same as for Level 1 code 9E X XX, except substitute “HSU2” for “HSU1”. Only applicable prior to SDU PartNumber 7516118--XX130/--xx140.WSC1 Input Bus Inactive (A1 0 01)DESCRIPTION : The last label 270 WSC Status word from WSC1 was received with the pertinent bit setindicating an inactive input bus from “this” SDU (bit 21 if this is SDU 1, or bit 22 if this isSDU 2 in a dual system).PARAMETERS : “1” if the inactive input bus bit corresponding to the “other” SDU is also set in the WSC1Status word, for this WSC1 Status word or for any of the subsequent WSC1 Status words considered duringthe fault--to--failure interval defined in the Fail Criteria below; “0”otherwise.FAIL CRITERIA : This fault transitions to failure after the receipt of at least four consecutive WSC1 Statuswords with the pertinent bit set, and if the fault persists for more than three seconds.RECOVERY CRIT. : As soon as a WSC1 Status word is received with the pertinent bit cleared.REMARK :WSC2 Input Bus Inactive (A2 0 01)Same as for WSC1 Input Bus Inactive (A1 0 01), except substitute WSC2 for WSC1.WSC3 Input Bus Inactive (A3 0 01)Same as for WSC1 Input Bus Inactive (A1 0 01), except substitute WSC2 for WSC1.HSU Ethernet Port 1 Bus Inactive (A6 0 01)DESCRIPTION : This fault is applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent, andis declared by the HSU (via a Williamsburg Failure Report message with fault code 0/01) when the Ethernetport 1 interface is configured (as indicated by the Ethernet 1 Presence configuration strap, HSU pin MP2A)and no link pulses are observed on the Ethernet port 1 bus.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if the fault persists for 3 seconds.RECOVERY CRIT. : This failure is cleared when link pulses are detected on the Ethernet port 1 bus for atleast 2 seconds.REMARK : None.HSU Ethernet Port 2 Bus Inactive (A7 0 01)DESCRIPTION : This fault is applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent, andis declared by the HSU (via a Williamsburg Failure Report message with fault code 0/02) when the Ethernetport 2 interface is configured (as indicated by the Ethernet 2 Presence configuration strap, HSU pin MP2B)and no link pulses are observed on the Ethernet port 2 bus.PARAMETERS : None.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--113FAIL CRITERIA : This fault transitions to a failure if the fault persists for 3 seconds.RECOVERY CRIT. : This failure is cleared when link pulses are detected on the Ethernet port 2 bus for atleast 2 seconds.REMARK : None.HSUISDNPort1BusInactive(A8001)DESCRIPTION : This fault is applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent, andis declared by the HSU (via a Williamsburg Failure Report message with fault code 0/03) when the ISDN port1 interface is configured (as indicated by the ISDN 1 Presence configuration strap, HSU pin MP1E) and noactivity is observed on the ISDN port 1 bus.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if the fault persists for 3 seconds.RECOVERY CRIT. : This failure is cleared when activity is detected on the ISDN port 1 bus for at least 2seconds.REMARK : None.HSUISDNPort2BusInactive(A9001)DESCRIPTION : This fault is applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent, andis declared by the HSU (via a Williamsburg Failure Report message with fault code 0/04) when the ISDN port2 interface is configured (as indicated by the ISDN 2 Presence configuration strap, HSU pin MP1F) and noactivity is observed on the ISDN port 2 bus.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if the fault persists for 3 seconds.RECOVERY CRIT. : This failure is cleared when activity is detected on the ISDN port 2 bus for at least 2seconds.REMARK : None.SDU System Configuration Error (Level 1 Code C0h)SDU System Configuration Error, Unknown SRU (SRU Code 0h)SDU Straps Parity Error (C0 0 81)DESCRIPTION : During POST/PAST the configuration straps parity is tested. If the parity is even then thisfault is declared.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK :SDU Antenna Configuration Straps Error (C0 0 82)DESCRIPTION : During POST/PAST the antenna configuration straps is tested. If an invalid, unsupported orundefined configuration is read, then this fault is declared.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK :SDU CFDS Configuration Straps Error (C0 0 83)DESCRIPTION : During POST/PAST the CFDS configuration straps is tested. If an invalid or undefinedconfiguration is read, then this fault is declared.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK :SDU Straps Inconsistency (C0 0 84)DESCRIPTION : During POST/PAST the configuration straps is tested. If an inconsistency (as delineatedbelow) is read, then this fault is declared.PARAMETERS : (One bit per condition; multiple conditions may apply; if so, set all appropriate bits)RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--1141 = Not used/Spare.2 = Undefined Lamp/Chime Option.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK :Dual System -- Config Straps Error (C0 0 05)DESCRIPTION : This fault is declared in a dual system if the SDU Number received from the other SDU onthe cross--talk bus is the same as this SDU’s Number, and also when an SDU is strapped as single and DCSwords are received on the XTB.PARAMETERS : 1st: Strap parity (good or bad)2nd: SDU number, as follows:0SingleSDU1#1of22#2of2FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : If the straps parity is bad as per Section 3.2.3.1.23.1.3, the SDU will use the SDU Numberdifferent from the other SDU’s after a reversion reset.Dual System -- Cockpit Straps Incompatible (C0 0 06)DESCRIPTION : This fault is declared in a dual system when the configuration straps associated with cockpitfunctionalities are inconsistent between the two SDUs.PARAMETERS : (One bit per condition; multiple conditions may apply; if so, set all appropriate bits)1 = TP13A Priority 4 Call To/From Cockpit.2 = TP13C--TP13D Cockpit Voice Call Light/Chime Options.4 = TP13K Cockpit Hookswitch Signalling Method.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared after the other SDU resets and reads straps which are compatible.REMARK : When this failure is active, the behavior of cockpit voice will depend on the straps read by theSDU supporting the physical channel for the call.Manufactuer--Specific SDU Straps Parity Error (C0 0 87)DESCRIPTION : During POST/PAST, the manufacturer--specific SDU configuration straps is tested for parity.If the computed parity is odd, this fault is declared.PARAMETERS : None.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK :SDU WOW Miscompare Error (C1 0 81/01)DESCRIPTION : During CM, (1) if the configuration straps indicate no CFDS or IRS presence, or (2) if theaircraft type is Airbus, then the two Weight On Wheels discretes is compared once per second. Should therebe a mismatch in the readings then a ’SDU WOW Miscompare Error’ fault is declared.While in the fault state the two Weight On Wheels discretes is compared once per second. The ’SDU WOWMiscompare Error’ fault is cleared if the discretes agree. A similar test shall also be performed duringPOST/PAST (1) if the configuration straps indicate no CFDS or IRS presence, or (2) if the aircraft type isAirbus.PARAMETERS : None.FAIL CRITERIA : CM: This fault transitions into failure if it persists for ten seconds or more.POST/PAST: This fault transitions into failure if it persists for multiple samples for three seconds or more.RECOVERY CRIT. : CM: This failure is cleared, on receipt of a ’SDU WOW Miscompare Error’ fault clearedreport (see DESCRIPTION above), if no further ’SDU WOW Miscompare Error’ faults are reported for tenseconds or more.POST/PAST: This failure is not explicitly cleared.REMARK :RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--115SDU Dual System Select/Disable Error (Level 1 Code C2)SDU Dual System Select/Disable Test Error (C2 0 81)DESCRIPTION : During POST/PAST in a dual system, as long as the other SDU is not already disabled andthe cross--talk bus (XTB) input is active, each SDU shall test its ability to assert itsSelect/Disable output to the other SDU, and for the other SDU to report within 0.3 second (via its “My DisableIs Asserted” bit in its Dual Control/Status word on the XTB) that its Disable input is being asserted. Theasserting SDU shall release the test assertion after the positive indication from the other SDU, or after 0.3second, whicheveroccurs first. If the test cannot be carried out during POST/PAST, it is carried outonce, later, if the opportunity arises. Although carried out after POST/PAST, the code shallstill be C2 0 81.PARAMETERS : State of the Select input discrete during the test.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This fault is never explicitly cleared.REMARK : The other SDU is not actually disabled during this test since the Select/Disable must be assertedfor at least one second for that to occur. If the other SDU is already disabled (andthis test is therefore inhibited), failure C2 0 82 is declared.Select/Disable Test Not Initiated (C2 0 82)DESCRIPTION : Reference the Description for failure C2 0 81; if the Select/Disable Test cannot be initiateddue to the other SDU already being disabled or the XTB input being inactive, this fault is declared at the endof POST/PAST.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared if the test is able to be performed after POST/PAST (i.e., otherSDU no longer disabled, or XTB input no longer inactive).REMARK : This failure serves as a warning that a critical part of the normal POST/PAST procedure wasbypassed, hence the dual system cannot be positively declared to be 100% functional.SDU (ICAO) Address Bits (Straps) (Level 1 Code C3)SDU (ICAO) Address Bits (Straps) Error (C3 0 81)DESCRIPTION : Should there be no ARINC 429 source of ICAO aircraft address indicated as present in theconfiguration straps, and the discrete value when read during POST/PAST indicates all zero’s or all ones’s,then this fault is declared.PARAMETERS : The ICAO aircraft address read from the discretes.FAIL CRITERIA : This fault transitions into failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK :Dual System Different Straps AES ID (C3 0 02)DESCRIPTION : This fault is declared in a dual system if this SDU obtains its AES ID from its strappeddiscretes, and a valid AES ID received from the other SDU via the cross--talk bus is different from this AES’valid ID.PARAMETERS : 1st: This SDU’s AES ID2nd: Other SDU’s AES IDFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared if a valid AES ID is received from the other SDU which matchesthis SDU’s valid AES ID.REMARK : This fault is declared in both SDUs. No functional resource is indicted; however, one SDU willbecome disabled.HGA/IGA HPA Reflected Output Power (Level 1 Code C4)HGA/IGA HPA 429 Maintenance Word Output VSWR Bad (C4 0 01)DESCRIPTION : This fault is declared if bit #12 in the Maintenance Word received by the SDU from theHGA/IGA HPA was set.PARAMETERS : None.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--116FAIL CRITERIA : This fault transitions to failure after the receipt of four consecutive maintenance words withbit 12 set.RECOVERY CRIT. : As soon as an HPA Maintenance Word is received by the SDU with bit #12 cleared.REMARK : The Honeywell/Racal HPA sets bit 12 in its Maintenance words while failure C4 0 02 is active.HGA/IGA HPA Reflected Output Power Error (C4 0 02)DESCRIPTION : The HPA shall (for any software package resident in a 40W HPA having hardware/softwarecompatibility strap settings of 00h) declare this fault if the measured reflected output power exceeds 20 watts.For any software package operating in a 20W or 40W HPA having a hardware/software compatibility strapsetting of 02h or greater, the HPA shall declare and latch this fault if the measured reflected output powerexceeds half of the forward output power. The 60W HPA shall declare and latch this fault if the measuredreflected output power exceeds three tenths of the forward power and is greater than +24 dBm.PARAMETERS : 20W/40W HPA: The measured reflected output power; 60W HPA: None.FAIL CRITERIA : This fault transitions to failure (in HPAs having hardware/software compatibility strapsettings of 00h) if the fault persists for one second. This fault transitions to failure (in HPAs havinghardware/software compatibility strap settings of 02h or higher, or if the 60W HPA) if the fault persists for 100ms.RECOVERY CRIT. : This failure is cleared (for any software package resident in HPAs havinghardware/software compatibility strap settings of 00h) if the measured reflected output power is less than 20watts for one second. For any software package operating in HPAs having hardware/software compatibilitystrap settings of 02h or greater, this failure is cleared only if the measured reflected power is less than halfthe forward output power for 100 ms while forward output power is present at the detector. For the 60W HPA,this failure is cleared when the measured reflected power is less than three tenths of the forward power for100 ms while forward output power is present at the detector.REMARK : The HPA shall set bit 12 in its Maintenance words while this failure is active. The SDU will raisefailure (C4 0 01) while bit 12 in the HPA Maintenance word is set.SDU ORT/Configuration Straps Incompatibility (Level 1 Code C5)SDU ORT/Local Configuration Straps Incompatibility (C5 0 81/01)DESCRIPTION : When the ORT is uploaded, at POST/PAST and after a User partition ORT crossload in adual system, the values of items that depend on the physical configuration of the local system are checkedagainst the local system configuration straps. This failure is declared if any ORT item value is incompatiblewith any strap states.PARAMETERS : (One bit per condition; multiple conditions may apply; if so, set all appropriate bits)10x : ORT item vii indicates reservation of all necessary resources for one HEADSET call on cockpit channel1, but the straps don’t indicate wiring of codec A to the cockpit AMS (single system only).20x : ORT item vii indicates reservation of all necessary resources for one HEADSET call on cockpit channel2, but the straps don’t indicate wiring of codec B to the cockpit AMS (single system only).40x : ORT item xiii indicates routing to DPHONE, but the straps don’t indicate that the CCS is installed (singlesystem only).80x : ORT item xiii indicates routing to APHONE, but the straps don’t indicate the wiring of either codec to thecabin (single system only).100x : ORT item xiii indicates routing to HEADSET, but the straps don’t indicate the wiring of either codec tothe cockpit AMS (single system only).200x : ORT item xxxii indicates selection of the ACP mic switch call initiation method, but ORT item xxxi doesnot indicate selection of the SCDU telephone number preselect only option.400x : ORT item xiii indicates routing to HEADSET, but the strap TP13A indicates that APC calls to/from thecockpit are not allowed (single system only).800x : ORT item v contains telephone numbers assigned priority 4, but the strap TP13A indicates that APCcalls to/from the cockpit are not allowed (single system only).FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This fault is cleared once the ORT becomes compatible with the local straps.REMARK : The default value(s) of the ORT item(s) causing the incompatibility will be substituted for thecurrent power--up cycle to permit operation to proceed.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--117Dual ORT/Combined Configuration Straps Incompatibility (C5 0 02)DESCRIPTION : In a dual system, when the ORT is uploaded, after POST/PAST and after a User partitionORT crossload, the values of duplicated items that depend on the physical configuration of the remotesystem, and the values of common items that depend on system--wideconfiguration straps, is checked after the remote straps are available (i.e., when full cross--talkcommunications are established). This fault is declared if any ORT item value is incompatible with any strapstates.PARAMETERS : (One bit per condition; multiple conditions may apply; if so, set all appropriate bits)10x : ORT item vii indicates reservation of all necessary resources for one HEADSET call, but none of thefour codecs is Usable by the cockpit.20x : Not used.40x : ORT item xiii indicates routing to DPHONE, but none of both SDU system’s straps indicate that theCCS is installed.80x : ORT item xiii indicates routing to APHONE, but none of the four codecs is strapped as being wired tothe cabin.100x : ORT item xiii indicates routing to HEADSET, but none of the four codecs is strapped as being wired tothe cockpit AMS.200x : Not used.400x : ORT item xiii indicates routing to HEADSET, but either the TP13A straps on both SDUs indicate thatAPC calls to/from the cockpit are not allowed (set to “zero”), or only one SDU has codecs wired to AMS butits TP13A is set to “zero”.800x : ORT item v contains telephone numbers assigned priority 4, but TP13A strap on both SDUs indicatethat APC calls to/from the cockpit are not allowed.4000x : ORT item xlviii indicates Fixed, but there are more than two physical channels usable by the cockpit.8000x : ORT item xlviii indicates Shared, but a channel Usable by the cockpit is not matched by the samenumbered channel in the other SDU also being Usable by the cockpit.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This fault is cleared when the ORT becomes compatible with the remote or systemwidestraps.REMARK : The default value(s) of the ORT item(s) causing the incompatibility will be substituted for thecurrent power--up cycle to permit operation to proceed.LGA HPA Reflected Output Power Error (C6 0 01, C6 0 02)Same as HGA HPA Reflected Output Power Error except (i) substitute LGA HPA forHGAHPA;(ii)substituteC6002forC4002intheRemarks.HGA/IGA HPA Over Temp Warnings (Level 1 Code C7h)The failures listed in this section apply to both the HGA (40W/60W) and IGA (20W) Honeywell/Thales HPAs,as note in the description for each failure.HGA HPA PSU Over Temp Warning (C7 1 01)DESCRIPTION : During CM, the PSU temperature is tested four times per second and an Over TempWarning fault is declared if the PSU temperature is greater than or equal to +100 degrees Celsius and lessthan +130 degrees Celsius. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : PSU temperature sensor scaled analog voltage, and the warning temperature limit.FAIL CRITERIA : A failure is declared if the PSU temperature sensor scaled analog output is within the limitsspecified above for four consecutive readings.RECOVERY CRIT. : The failure is cleared if after four consecutive readings the PSU temperature sensorscaled analog output is less than +100 degrees Celsius.REMARK : The HPA shall set bit 13 in its Maintenance words while this failure is active.HGA HPA Processor (SRU Code 2h)HGA HPA CPU Over Temp Warning (C7 2 01)DESCRIPTION : During CM, the CPU temperature is tested four times per second and an Over TempWarning fault is declared if the CPU temperature is greater than or equal to +100 degrees Celsius and lessthan +130 degrees Celsius. This failure code shall only be applicable to the 20W and 40W HPAs.PARAMETERS : CPU temperature sensor scaled analog voltage, and the warning temperature limit.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--118FAIL CRITERIA : A failure is declared if the CPU temperature sensor scaled analog output is within the limitsspecified above for four consecutive readings.RECOVERY CRIT. : The failure is cleared if after four consecutive readings the CPU temperature sensorscaled analog output is less than +100 degrees Celsius.REMARK : The HPA shall set bit 13 in its Maintenance words while this failure is active.HGA HPA Over Temp Warning (C7 2 02)DESCRIPTION : During CM, if the PA temperature sensor detects a temperature greater than +100 degreesCelsius, an Over Temp Warning fault is declared. While this failure is active, the HPA shall reduce maximumavailable RMS power to 8dB below 40W. This failure code shall only be applicable to the 60W HPA.PARAMETERS : NoneFAIL CRITERIA : A failure is declared if two consecutive readings are above +100 degress Celsius.RECOVERY CRIT. : The failure is cleared if two consecutive readings drop below +85 degrees Celsius.REMARK : The 60W HPA will set bit 13 in its Maintenance words while this failure is active. The SDU willalso raise failure (C7 0 01) per section 4.4.5.199.20 while bit 13 in the HPA Maintenance word is set.HGA HPA Driver Over Temp Warning (C7 3 01)DESCRIPTION : During CM, the Driver temperature is tested four times per second and an OverTemp Warning fault is declared if the Driver temperature is greater than or equal to +100 degrees Celsius andless than +130 degrees Celsius. This failure code shall only be applicable to the 40W HPA.PARAMETERS : Driver temperature sensor scaled analog voltage.FAIL CRITERIA : A failure is declared if the Driver temperature sensor scaled analog output is within thelimits specified above for four consecutive readings.RECOVERY CRIT. : The failure is cleared if after four consecutive readings the Driver temperature sensorscaled analog output is less than +100 degrees Celsius.REMARK : The HPA shall set bit 13 in its Maintenance words while this failure is active.HGA HPA Combiner Over Temp Warning (C7 8 01)DESCRIPTION : During CM, the Combiner temperature is tested four times per second and an Over TempWarning fault is declared if the Combiner temperature is greater than or equal to +100 degrees Celsius andless than +130 degrees Celsius. This failure code shall only be applicable to the 40W HPA.PARAMETERS : Combiner temperature sensor scaled analog voltage.FAIL CRITERIA : A failure is declared if the Combiner temperature sensor scaled analog outputexceeds its limits for four consecutive readings.RECOVERY CRIT. : The failure is cleared if after four consecutive readings the Combiner temperaturesensor scaled analog output is less than +100 degrees Celsius.REMARK : The HPA shall set bit 13 in its Maintenance words while this failure is active.HGA HPA RFAM Over Temp Warning (C7 B 01)DESCRIPTION : During CM, the RFAM temperature is tested four times per second, and an Over TempWarning is declared if the RFAM temperature is greater than or equal to +100 degrees Celsius and less than+130 degrees Celsius. This failure code shall only be applicable to the 20W HPA.PARAMETERS : RFAM temperature sensor scaled analog voltage, and the warning temperature limit.FAIL CRITERIA : A failure is declared if the RFAM temperature sensor scaled analog output exceeds itslimits for four consecutive readings.RECOVERY CRIT. : The failure is cleared if after four consecutive readings the RFAM temperature sensorscaled analog output is less than +100 degrees Celsius.REMARK : The HPA shall set bit 13 in its Maintenance words while this failure is active.HGAHPAMNTNCWORDLRUOverTemp(C7001)DESCRIPTION : This fault is declared if bit #13 in the Maintenance Word from the HGA HPA was set.PARAMETERS : The maintenance word.FAIL CRITERIA : This fault transitions to failure after the receipt of four consecutive maintenance words withbit 13 set.RECOVERY CRIT. : As soon as an HPA Maintenance Word is received with bit #13 clearedREMARK : The Honeywell HPA does not generate this failure directly, nor log it internally, nor communicate itto the SDU. The SMPM is the “Tester”; it is simply responding to the Maintenance word bit 13. The HoneywellHPA controls bit.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--119GES Frequency Command Errors (Level 1 Code C8H)Invalid Frequency Command From GES (C8 0 01)DESCRIPTION : The SDU shall log this failure if it receives a frequency command from the GES that liesoutside of the specified transmit band for the specified channel rate/modulation type.PARAMETERS : The channel number.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The SDU executes a cold start after logging this failure.GNSS Interference Risk From GES (C8 0 02)DESCRIPTION : Per Section 3.3.1.3.4.1, the SDU shall log this failure if it receives a frequency commandfrom the GES that would cause a third-- or fifth--order MCS intermodulation product to fall into the GNSSfrequency band.PARAMETERS : The new channel number, as well as the fL and fH channel numbers.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The SDU executes a cold start after logging this failure.LGA HPA Over Temp Warnings (Level 1 Code C9)LGA HPA PSU Over Temp Warning (C9 1 01)Same as for the HGA HPA.LGA HPA Processor (SRU Code 2h)LGA HPA CPU Over Temp Warning (C9 2 01)Same as for the HGA HPA.LGA HPA Over Temp Warning (C9 2 02)Same as for the HGA HPA.LGA HPA Driver Over Temp Warning (C9 3 01)Same as for the HGA HPA.LGA HPA Over Temp (Combiner) Warning (C9 8 01)Same as for the HGA HPA.LGA HPA RFAM Over Temp Warning (C9 B 01)Same as for the HGA HPA.LGAHPAMNTNCWORDLRUOverTemp(C9001)Same as for the HGA HPA.LGA/LNA Control Driver Fail (CA 0 01)DESCRIPTION : The LGA/LNA output discrete is tested by comparing the level of the BITE tell--back with thecommanded state, as specified below. Should the output discrete’s BITE tell--backvalue not be the same as the commanded value for either the active or inactive state (or both), and theantenna subsystem configuration includes an LGA then this fault is declared.During POST/PAST, the LGA/LNA output discrete is tested for being able to achieve the active and inactivestates by commanding the LGA/LNA to the active state briefly, and then inactive again. If the first test paircycle fails (for either or both states), it is repeated. If the second test pair cycle also fails, then this fault isdeclared.During CM, the LGA/LNA output discrete is tested whenever its commanded state is changed for operationalreasons, and also once every thirty seconds.Test results for the discrete output successfully achieving the commanded state (active or inactive) isrecorded independently, and the fault shall only be cleared when both commanded states have beenrecorded as being achieved the last time they were tested.PARAMETERS : Parameter 1 is set to 1 if the active state is not achieved.Parameter 2 is set to 1 if the inactive state is not achieved.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--120FAIL CRITERIA : This fault transitions to a failure if the fault persists continuously for one second.RECOVERY CRIT. : This failure is cleared as soon as the fault is cleared, i.e., as soon as both commandedstates have been recorded as being achieved the last time they were tested.REMARK : This failure is Class 2, and does not indict [lga_subsys] nor [hga_subsys], because the reasoncould as likely be failure in the SDU BITE circuitry, and because other, moredefinitive tests (LGA LNA diplexer and LGA LNA RF continuity) cover this functionality.Level 3 failure code 81 is not used for the POST/PAST case second commentary, fourth paragraph (i.e., thePOST/PAST and CM tests are identical).In the actual implementation, if an LGA is installed, this discrete is repetitively commanded to its currentlyrequired state (whether on or off) at a rate of ~ 15 Hz. The CM test is performed after each such command,hence continuously at ~ 15 Hz (which includes the case of whenever a state change is commanded) as wellas once every thirty seconds. Since there is no separate Level 3 failure code 81 for the POST/PAST case,even the POST/PAST case includes the one--second fail criteria. The POST/PAST case also requires theretest fail criteria in order to avoid nuisance failures because there is no guarantee that the CM testing (whichmight otherwise clear a POST/PAST--detected fault) will begin or resume within one second of POST/PAST.HGA/IGA HPA Invalid SDI Strapping (CB 0 01)DESCRIPTION : HPA perspective: The HPA shall read the programmed state of its SDI pins at each coldstartand each functional test (i.e., each POST/PAST). This fault is declared if theSDI pins are set to any invalid state (Reserved or Unused). When this occurs, the HPA shall, in softwarepackages D2.0 and subsequent, aside from logging the failure, behave in every way as though it wasstrapped to be the HGA/IGA HPA.SDU perspective: The HGA/IGA HPA has reported this failure using the manufacturer specificblock transfer protocol.PARAMETERS : The as--read invalid SDI code.FAIL CRITERIA : HPA perspective: This fault transitions to a failure immediately.SDU perspective: This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : This failure results in the LGA HPA being unable to respond to all but all--call commands sent viathe ARINC 429 Multicontrol bus, which renders it virtually useless. Both HPAs shall use failure CB 0 01, sincethey cannot tell which HPA they are supposed to be.When the SDU receives a CB 0 01 block on the HGA/IGA HPA bus, it shall make the entry into the systemfailure log using code CB 0 01; conversely, it shall use code CC 0 01 if the CB 0 01 block is received on theLGA HPA bus (see below). Note that failure code 01 is used, even though the test is (only) performed duringPOST/PAST.Note: In HPA software packages prior to D2.0, upon detecting this failure, the HPA would use the “unused”SDI code (11b) in its transmitted ARINC 429 words, and would only respond to Command Words with SDIfields set to the “All Call” code.LGA HPA Invalid SDI Strapping (CC 0 01)DESCRIPTION : HPA perspective: Not used.SDU perspective: The LGA HPA has reported failure CB 0 01 using the manufacturer specificblock transfer protocol.PARAMETERS : The as--read invalid SDI code.FAIL CRITERIA : SDU perspective: This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The HPAs themselves do not use this failure ---- they use CB 0 01. When the SDU receives a CB0 01 block on the LGA HPA bus, it shall make the entry into the system failure logusing code CC 0 01. Note that failure code 01 is used, even though the test is (only) performed duringPOST/PAST.SDU POC/TOTC Reset (Level 1 Code CDh)SDU TOTC Auto/Manual Reset (CD 0 81/01)DESCRIPTION : The SDU has performed either an automatic (Level 3 code 81) or manual (code 01) TOTCreset.PARAMETERS : The value of the TOTC (in 10--minute increments) just prior to it being reset. This may bevalid, or it may be corrupted.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--121FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : This entry into the failure log is used to indicate that an SDU TOTC reset event has occurred.SDU POC Auto/Manual Reset (CD 0 82/02)DESCRIPTION : The SDU has performed either an automatic (Level 3 code 82) or manual (code 02) POCreset.PARAMETERS : The value of the POC just prior to it being reset. This may be valid, or it may be corrupted.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : This entry into the failure log is used to indicate that an SDU POC reset event has occurred.HGA/IGA HPA POC/TOTC Reset (Level 1 Code CFh)HGA/IGA HPA TOTC Auto/Manual Reset (CF 0 81/01)DESCRIPTION : HPA perspective: As specified in Section 4.3.6.3, the HGA/IGA HPA has performed eitheran automatic (Level 3 code 81) or manual (code 01) TOTC reset.SDU perspective: The HGA/IGA HPA has reported this failure using the manufacturerspecificblock transfer protocol.PARAMETERS : The value of the TOTC (in 10--minute increments) just prior to it being reset. This may bevalid, or it may be corrupted.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : This entry into the failure log is used to indicate that an HGA HPA TOTC reset event hasoccurred.HGA/IGA HPA POC Auto/Manual Reset (CF 0 82/02)DESCRIPTION : HPA perspectiveThe HGA/IGA HPA has performed either an automatic (Level 3 code 82) ormanual (code 02) POC reset.SDU perspective: The HGA/IGA HPA has reported this failure using the manufacturerspecificblock transfer protocol.PARAMETERS : The value of the POC just prior to it being reset. This may be valid, or it may be corrupted.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : This entry into the failure log is used to indicate that an HGA HPA POC reset event has occurred.LGA HPA POC/TOTC Reset (Level 1 Code D0h)LGA HPA TOTC Auto/Manual Reset (D0 0 81/01)DESCRIPTION : HPA perspective: As specified in Section 4.3.6.3, the LGA HPA has performed either anautomatic (Level 3 code 81) or manual (code 01) TOTC reset.SDU perspective: The LGA HPA has reported this failure using the manufacturer--specific block transferprotocol.PARAMETERS : The value of the TOTC (in 10--minute increments) just prior to it being reset. This may bevalid, or it may be corrupted.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : This entry into the failure log is used to indicate that an LGA HPA TOTC reset event hasoccurred.LGA HPA POC Auto/Manual Reset (D0 0 82/02)DESCRIPTION : HPA perspective: The LGA HPA has performed either an automatic (Level 3 code 82) ormanual (code 02) POC reset.SDU perspective: The LGA HPA has reported this failure using the manufacturer--specific block transferprotocol.PARAMETERS : The value of the POC just prior to it being reset. This may be valid, or it may be corrupted.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : This entry into the failure log is used to indicate that an LGA HPA POC reset event has occurred.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--122HGA HPA Wrong A429 SDI Code (D1 0 01)DESCRIPTION : An expected ARINC 429 Word (labels 143,350,171) received on the HGA HPA to SDU buscontains an SDI different from HGA HPA.PARAMETERS : First word containing the wrong SDI code.FAIL CRITERIA : This fault transitions to a fail immediately.RECOVERY CRIT. : Immediately when any of the expected ARINC 429 words received on this bus containan SDI indicating HGA HPA.REMARK :LGA HPA Wrong A429 SDI Code (D2 0 01)DESCRIPTION : An expected ARINC 429 Word (labels 143,350,171) received on the LGA HPA to SDU buscontains an SDI different from LGA HPA.PARAMETERS : First word containing the wrong SDI code.FAIL CRITERIA : This fault transitions to a fail immediately.RECOVERY CRIT. : Immediately when any of the expected ARINC 429 words received on this bus containan SDI indicating LGA HPA.REMARK :Top/Port BSU/ACU Wrong A429 SDI Code (D3 0 01)DESCRIPTION : An expected ARINC 429 Word (labels 144,350) received on the Top/Port BSU/ACU to SDUbus contains an SDI not equal to Port/Top or ACU.PARAMETERS : First word containing the wrong SDI code.FAIL CRITERIA : This fault transitions to a failure after three seconds.RECOVERY CRIT. : Immediately when any of the expected ARINC 429 words received on this bus contain acorrect SDI.REMARK :Starboard BSU Wrong A429 SDI Code (D4 0 01)DESCRIPTION : An expected ARINC 429 Word (labels 144,350) received on the Starboard BSU to SDU buscontains an SDI not equal to Starboard.PARAMETERS : First word containing the wrong SDI code.FAIL CRITERIA : This fault transitions to a failure after three seconds.RECOVERY CRIT. : Immediately when any of the expected ARINC 429 words received on this bus contain acorrect SDI.REMARK :SDU/RFUIA To HGA/IGA HPA Cable Loss (Level 1 Code D5)SDU/RFUIA To HGA/IGA HPA Calibration Error (D5 0 01)DESCRIPTION : This fault is declared if the calculated SDU/RFUIA to HPA Loss is outside acceptable limits(ie not within 10 to 30dB).PARAMETERS : Failure Param: A 1 shall indicate that the calibrated loss was calculated to be greater thanthe maximum value.A 0 shall indicate that the calibrated loss was calculated to be less than theminimum value.Assoc Param: The calculated loss in tenths of dB.FAIL CRITERIA : This fault transitions to a failure if the fault persists for at least two successivemeasurement samples.RECOVERY CRIT. : This failure can only be cleared whilst the HGA antenna is the currently selected one.REMARK : This test is not done during the PAST period but only on actual transmissions (e.g. during log--on).This means it will not show up on the CFDS Test Results page, and it is hard todetermine if it has been fixed without incrementing the flight leg after each attempt at fixing it. The test alsodepends on the correct functioning of the HPA’s output power detector and the expected HPA amplification(gain), so if the HPA is muted, or not amplifying correctly, this failure may result.Although “illegal” in either the too--high or too--low case, this failure is only a real operational problem if theloss is too high, and depending on variables such as geographic location, antenna gain, number of channelsin use, etc., the system may work to some extent even then. For SDU Part Number 7516118--XX130/--xx140and subsequent, if the calculated cable loss is less than 10dB and the selected HPA is a 60W HPA, the SDURELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--123shall attempt to set the input attenuator to give a nominal cable loss of 15dB in order to prevent potentialequipment damage to the HPA.The RFUIA is a passive and optional device which, if present, is ignored by the SDU. However, the RFUIAdoes affect the calibration test if it is present because it is included in the signal path. Maintenance personnelneed to be aware of the potential impact of the RFUIA if this failure occurs.SDU/RFUIA To Linear HGA/IGA HPA RF Continuity Fail (D5 0 02)DESCRIPTION : This fault is declared when the HPA is a Linear HPA and fails to detect any measurableActual Output Power while the SDU is sending a Log--On Request with the SDU/RFUIA to HGA/IGA HPALoss set to the maximum value.PARAMETERS : Failure Param: The last positively calibrated SDU/RFUIA to HGA/IGA HPA Loss in tenths ofdB, or the Factory Settings default value if no calibration has beenachieved.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : If during the burst the HPA reports a measurable Actual Output Power but the calibration of theSDU/RFUIA to HPA Loss cannot be performed (backoffs are set to the limit or the HPA reports an APO equalto 19 dBW), the fault is not raised. This test is not done during thePAST period but only on actual transmissions (e.g. during log--on). This means it will not show up on theCFDS Test Results page, and it is hard to determine if it has been fixed without incrementing the flight legafter each attempt at fixing it. The test also depends on the correct functioning of the HPA’s output powerdetector and the expected HPA amplification (gain), so if the HPA is not amplifying correctly, this failure mayresult. A basic troubleshooting guide can help determine the general location where the failure is most likelyto occur.This fault will also be declared whenever the HPA independently turns carriers off (i.e., not under normalcommand from the SDU), which causes any subsequent RF continuity test to fail. Such action is required forthe 20W HPA whenever a short circuit condition is detected on any of the secondary power supply outputvoltages externally wired to an HPA--controlled IGA. In such cases, all of the secondary output voltagestypically fail together. The 20W HPA power supply turns carriers off by disabling the +5VDC bias voltage,which subsequently results in that failure being raised as well. Reference failure 04 1 03, and failures 04 1 08through 04 1 0A.The RFUIA is a passive and optional device which, if present, is ignored by the SDU. However, the RFUIAdoes affect the calibration test if it is present because it is included in the signal path. Maintenance personnelneed to be aware of the potential impact of the RFUIA if this failure occurs.SDU/RFUIA To Class C HGA/IGA HPA RF Continuity Fail (D5 0 03)DESCRIPTION : This fault is declared when the HPA is a Class C HPA and fails to detect any measurableActual Output Power while the SDU is sending a Log--On Request with the HPA Maximum Output Power setto the minimum value.PARAMETERS : Failure Param: The last positively calibrated Class C maximum Output Power in tenths ofdB, or the Factory Settings default value if no calibration has been achieved.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : If during the burst the HPA reports a measurable Actual Output Power but the calibration of theClass C HPA Maximum Output Power cannot be performed (backoffs are set to the limit or the HPA reportsan APO equal to 19 dBW), the fault is not raised.The RFUIA is a passive and optional device which, if present, is ignored by the SDU. However, the RFUIAdoes affect the continuity test if it is present because it is included in the signal path. Maintenance personnelneed to be aware of the potential impact of the RFUIA if this failure occurs.SDU/RFUIA To HGA/IGA HPA Attenuator Calibration Error (D5 0 04)DESCRIPTION : This fault is only applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent,and is declared if the SDU/RFUIA to HPA Loss calculated during the input attenuator calibration for a 60WHPA is greater than 35dB.PARAMETERS : Failure Param: A 1 shall indicate that the calibrated loss was calculated to be greater thanthe maximum value.Assoc Param: The measured HPA input power in mW.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--124FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : This test is not done during the PAST period (refer to Section 3.3.1.3.2.8.6). This means it will notshow up on the CFDS Test Results page, and it is hard to determine if it has been fixed without incrementingthe flight leg after each attempt at fixing it. The RFUIA is a passive and optional device which, if present, isignored by the SDU. However, the RFUIA does affect the calibration test if it is present because it is includedin the signal path. Maintenance personnel need to be aware of the potential impact of the RFUIA if this failureoccurs.SDU/RFUIA To Linear HGA/IGA HPA Attenuator RF Continuity Fail (D5 0 05)DESCRIPTION : This fault is only applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent,and is declared when the HPA is a Linear 60W HPA and fails to detect any measurable input power while theSDU is performing the HPA input attenuator calibration.PARAMETERS : NoneFAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : This test is not done during the PAST period. This means it will not show up on the CFDS TestResults page, and it is hard to determine if it has been fixed without incrementing the flight leg after eachattempt at fixing it. The test also depends on the correct functioning of the HPA’s input power detector andinput attenuator, so if these devices are not operating correctly, this failure may result. A basictroubleshooting guide (reference Section 4.4.5.233 Commentary) can help determine the general locationwhere the failure is most likely to occur.The RFUIA is a passive and optional device which, if present, is ignored by the SDU. However, the RFUIAdoes affect the calibration test if it is present because it is included in the signal path. Maintenance personnelneed to be aware of the potential impact of the RFUIA if this failure occurs.The HS--720 HSU may be installed in place of the RFUIA. It contains a passive combiner that does affect thecalibration test because it is included in the signal path. Maintenance personnel need to be aware of thepotential impact of the HSU if this failure occurs.SDU/RFUIA To LGA HPA Cable Loss (Level 1 Code D6)SDU/RFUIA To LGA HPA Calibration Error (D6 0 01)Same as SDU/RFUIA to HGA HPA Calibration Error except this fault shall only be declared if the LGA HPA isa linear HPA.SDU/RFUIA To Linear LGA HPA RF Continuity Fail (D6 0 02)Same as SDU/RFUIA to Linear HGA HPA RF Continuity Fail.SDU/RFUIA To Class C LGA HPA RF Continuity Fail (D6 0 03)Same as SDU/RFUIA to Class C HGA HPA RF Continuity Fail.SDU/RFUIA To LGA HPA Attenuator Calibration Error (D6 0 04)Same as SDU/RFUIA to HGA HPA Attenuator Calibration Error except this fault shall only be declared if theLGA HPA is a linear HPA.SDU/RFUIA To Linear LGA HPA Attenuator RF Continuity Fail (D6 0 05)Same as SDU/RFUIA to Linear HGA HPA Attenuator RF Continuity Fail.Top/Port HGA LNA To SDU/RFUIA RF Continuity Fail (D8 0 81)DESCRIPTION : This fault is declared if the SDU does not indicate (via RFM narrowband AGCmeasurement) a rising noise floor level from an active Top/Port HGA LNA on any one of its three receivechannels within five seconds of the Top/Port HGA LNA having been turned on. This test shall only beperformed if the Top/Port BSU to SDU input bus is active, the Top/Port LNA BITE is Ok, and the Top/PortBSU is declaring the SDU Control Bus input as active and the three AGCs are at their respective LNA Offstates. This test is not performed if any BSU self--test misoperation failures [13/0/8A, 13/0/0A, 15/0/8A,15/0/0A] are declared.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--125REMARK : A basic troubleshooting guide can help determine the general location where the failure is mostlikely to occur. The RFUIA is a passive and optional device which, if present, is ignored by the SDU.However, the RFUIA does affect the continuity test if it is present because it is included in the signal path.Maintenance personnel need to be aware of the potential impact of the RFUIA if this failure occurs.Starboard HGA LNA To SDU/RFUIA RF Continuity Fail (D9 0 81)DESCRIPTION : This fault is declared if the SDU does not indicate (via RFM narrowband AGCmeasurement) a rising noise floor level from an active Starboard HGA LNA on any one of its three receivechannels within five seconds of the Starboard HGA LNA having been turned on. This test shall only beperformed if the Starboard BSU to SDU input bus is active, the Starboard LNA BITE is Ok, the StarboardBSU is declaring the SDU Control Bus input as active, and the three AGCs are at their respective LNA Offstates. This test is not performed if any BSU self--test misoperation failures [13/0/8A, 13/0/0A, 15/0/8A,15/0/0A] are declared.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : A basic troubleshooting guide can help determine the general location where the failure is mostlikely to occur. The RFUIA is a passive and optional device which, if present, is ignored by the SDU.However, the RFUIA does affect the continuity test if it is present because it is included in the signal path.Maintenance personnel need to be aware of the potential impact of the RFUIA if this failure occurs.LGA LNA To SDU/RFUIA RF Continuity Fail (DA 0 81)DESCRIPTION : This fault is declared if the SDU does not indicate (via RFM narrowband AGCmeasurement) a rising noise floor level from an active LGA LNA on any one of its three receive channelswithin five seconds of the LGA LNA having been turned on. This test shall only be performed if the LGA LNABITE is Ok and the three AGCs are at their respective LNA Off states. This test is not performed if any BSUself--test misoperation failures [13/0/8A, 13/0/0A, 15/0/8A, 15/0/0A] are declared.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : The RFUIA is a passive and optional device which, if present, is ignored by the SDU. However,the RFUIA does affect the continuity test if it is present because it is included in the signal path. Maintenancepersonnel need to be aware of the potential impact of the RFUIA if this failure occurs.LGA Log--on Test (Level 1 Code DBh)LGA Log--on Test Failure (DB 0 01)COMMENTARYIn a single or dual system containing more than one antenna and at least one LGA, it is likely that longperiods may elapse without using that LGA for normal communication. In order to detect latent faults, it isnecessary for the SDU with that LGA to perform a test logon regularly, and for a fault to be declared if the testlog--on fails, with suitable checks to minimise the occurrence of misleading failure reports due to signalblockage, etc. In a single pseudo--dual system (HGA+LGA), no equivalent test is required for the HGA, sincean unreported failure in the HGA subsystem which results in the HGA being unusable would be self--evident.DESCRIPTION : If more than one antenna is installed and at least one is an LGA, and both the LGA and atleast one other antenna are not failed, and the system is in automatic antenna selection mode then the SDUshall perform an LGA log--on test.If the LGA to be tested is on the current master SDU in a dual system, or on a single SDU, and in either casethe antenna configuration is HGA+LGA, the SDU shall test by selecting its LGA, renewing the log--on, thenswitching back to its HGA and again renewing the logon. A fault is declared if the SDU does not achievelog--on via the LGA, but subsequently does achieve log--on via the HGA.If the LGA is on the current slave system in a dual system, the master SDU shall test by requesting the slaveSDU to perform a log--on test (via its LGA), and then switching back to the master and its antenna (HGA orLGA) and renewing the log--on. A fault is declared by the slave SDU if the system does not achieve log--onvia the slave’s LGA, but does subsequently achieve log--on via the master’s antenna.COMMENTARYThis requires that SATCOM transmissions not be restricted while the aircraft is on ground.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--126PARAMETERS : Cumulative count of sequential test failures since the last factory settings restart or testpassing.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : Successful log--on via the LGA.REMARK : LGA log--on test failure is also reported in 270--28 and/or 276--11. If raised, this failure needs to beconsidered in conjunction with other failures, such as Rx continuity, Tx cable loss, etc. If no other failuresexist, the root cause must be cabling from HPA to DLNA, or the LGA itself, or the cable between LGA andDLNA.Note that it is not raised if the HGA system cannot log--on, so building blockage is not a likely cause.Slave LGA Log--on Test Not Initiated (DB 0 02)DESCRIPTION : This fault is declared if a slave LGA log--on test is not initiated because of equipment failure([r_sdu_min_op.X] OR [r_lga_subsys.X]), cross--talk bus (XTB) full communications not being established, orthe slave being disabled ([r_common.C]); or the master SDU attempts a test log--on via the slave, but noresponse is received from the slave via the XTBwithin five minutes; or if the test is aborted due to any of the reasons previously stated.PARAMETERS : 1 = slave LGA equipment not OK2 = XTB full communications not achieved3 = slave SDU is disabled4 = response timeoutFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : Performing a successful test log--on via the LGA, or upon a handover of mastery, orupon failure DB 0 01 (preceeding section) becoming active.REMARK : LGA slave log--on test not initiated is also reported in 276--11.No Declared Active (C)MU (DC 0 01)DESCRIPTION : This fault is declared when at least one (C)MU input bus is active, but no installed (C)MUindicates “Active” in its label 270 status words (bit 20).PARAMETERS : None.FAIL CRITERIA : This fault transitions to failure if the fault persists for 10 seconds.RECOVERY CRIT. : As soon as a label 270 status word is received from a (C)MU with an “Active” indicationin bit 20 or the busses from all installed (C)MUs are declared inactive.REMARK : This failure condition is reflected in the SDU’s label 270 status word (in bit 29) to the(C)MU, which is also read by the EICAS/ECAM/EDU.Secured ORT Error (Level 1 Code DDh)Item (i) -- Startup Logon Policy (DD 0 01)DESCRIPTION : Upon ORT upload, the Startup Log--on Policy setting is NOT within the acceptable rangedefined in Section 3.3.3.1.4.1 (i).PARAMETERS : The uploaded ORT item (i) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (viii) -- Response Capability To Log--On Interrogation (DD 0 03)DESCRIPTION : Upon ORT upload, the Log--On Interrogation Response setting is NOT within the acceptablerange.PARAMETERS : The uploaded ORT item (viii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xviii) -- Noise Insertion Level (DD 0 04)DESCRIPTION : Upon ORT upload, the Noise Insertion Level setting is NOT within the acceptable range.PARAMETERS : The uploaded ORT item (xviii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--127Item (xxii) -- Tx Gain Threshold (DD 0 05)DESCRIPTION : Upon ORT upload, the HGA and/or IGA Tx Gain Threshold settings is/are NOT within theacceptable ranges.PARAMETERS : Failure Param: The uploaded ORT item (xxii) value that has failed the range test.Assoc Param: A 0 shall indicate that the failure is associated with an HGA.A 1 shall indicate that the failure is associated with an IGA.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxiii) -- APHONE System Management Commands (DD 0 06)DESCRIPTION : Upon ORT upload, the APHONE System Management Commands setting is NOT withinthe acceptable range.PARAMETERS : The uploaded ORT item (xxiii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxviii) -- HPA Backoff Limits (DD 0 08)DESCRIPTION : Upon ORT upload, the HPA Backoff Limits setting is NOT within the acceptable range.PARAMETERS : The uploaded ORT item (xxviii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxix) -- HPA Minimum Reportable Actual Power Output (DD 0 09)DESCRIPTION : Upon ORT upload, the HPA Minimum Reportable Actual Power Output setting is NOT withinthe acceptable range.PARAMETERS : The uploaded ORT item (xxix) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxx) -- Default Assumed Global Beam Initial C--Channel EIRP (DD 0 0A)DESCRIPTION : Upon ORT upload, the Default Assumed Global Beam Initial C--Channel EIRP setting is lessthan 0 dBW or more than 25.5 dBW.PARAMETERS : The uploaded ORT item (xxx) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxxi) -- SCDU Telephone Number Preselect (DD 0 0B)DESCRIPTION : Upon ORT upload, the SCDU Telephone Number Preselect setting is NOT within theacceptable range.PARAMETERS : The uploaded ORT item (xxxi) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxxii) -- ACP Call Initiation (DD 0 0C)DESCRIPTION : Upon ORT upload, the ACP Call Initiation setting is NOT within the acceptable range.PARAMETERS : The uploaded ORT item (xxxii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--128Item (xxxviii) -- Failure Masking Data (DD 0 0D)DESCRIPTION : Upon ORT upload, the Failure Masking Data setting is NOT within the acceptable range.PARAMETERS : The uploaded ORT item (xxxviii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxxix) -- Elevation Handover Threshold (DD 0 0E)DESCRIPTION : Upon ORT upload, the Elevation Handover Threshold setting is NOT within the acceptablerange.PARAMETERS : The uploaded ORT item (xxxix) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xli) -- Automatic Transit Call GES Table (DD 0 0F)DESCRIPTION : Upon ORT upload, the Automatic Transit Call GES Table setting is NOT within theacceptable range.PARAMETERS : The uploaded ORT item (xli) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xlii) -- Air--to--Ground Chime (DD 0 10)DESCRIPTION : Upon ORT upload, the Air--to--Ground Chime setting is NOT within the acceptable range.PARAMETERS : The uploaded ORT item (xlii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xliii) -- SCDU Call Prompts (DD 0 11)DESCRIPTION : Upon ORT upload, the SCDU Call Prompts setting is NOT within the acceptable range.PARAMETERS : The uploaded ORT item (xliii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xliv) -- EIRP Overdraft Checking Priority (DD 0 12)DESCRIPTION : Upon ORT upload, the EIRP Overdraft Checking Priority setting is NOT within theacceptable range.PARAMETERS : The uploaded ORT item (xliv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xlvi) -- Cockpit Audio Level Settings (DD 0 13)DESCRIPTION : Upon ORT upload, the Cockpit Audio Level setting is NOT within the acceptable range.PARAMETERS : The uploaded ORT item (xlvi) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xlvii) -- HGA Retry Period (ground And Air) (DD 0 14)DESCRIPTION : Upon ORT upload, the HGA Retry Period setting is NOT within the acceptable range.PARAMETERS : The uploaded ORT item (xlvii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--129Item (xlviii) -- Cockpit Channel Interface Type For Dual (DD 0 15)DESCRIPTION : Upon ORT upload, the Cockpit Channel Interface Type for Dual setting is NOT within theacceptable range.PARAMETERS : The uploaded ORT item (xlviii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (l) -- “Disable/Reenable Other SATCOM” SCDU Prompts (DD 0 16)DESCRIPTION : Upon ORT upload, the “Disable/Reenable Other SATCOM” SCDU Prompts setting is NOTwithin the acceptable range.PARAMETERS : The uploaded ORT item (l) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (li) -- SCDU SATCOM Subsystem Prompts (DD 0 17)DESCRIPTION : Upon ORT upload, the SCDU SATCOM Subsystem Prompts setting is NOT within theacceptable range.PARAMETERS : The uploaded ORT item (li) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lii) -- SCDU Channel Label Suffixes (DD 0 18)DESCRIPTION : Upon ORT upload, the SCDU Channel Label Suffixes setting is NOT within the acceptablerange.PARAMETERS : The uploaded ORT item (lii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (liii) -- Secured ORT Description (DD 0 19)DESCRIPTION : Upon ORT upload, the Secured ORT Description setting is NOT within the acceptable rangeof 24 ISO--5 characters maximum as.PARAMETERS : The uploaded ORT item (liii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (liv) -- Composite ORT File Upload Allowed (DD 0 1A)DESCRIPTION : Upon ORT upload, the Composite ORT File Upload Allowed setting is NOT within theacceptable range.PARAMETERS : The uploaded ORT item (liv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Secured ORT Mismatch With Other SDU (DD 0 1B)DESCRIPTION : This fault is declared if the Secured ORT Partition CRC or the Secured ORT Description(ORT item liii) received from the other SDU on the cross--talk bus are different from this SDU’s Secured ORTCRC and Description.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared if the same Secured ORT Partition CRC and Description arereceived from the other SDU.REMARK : This fault is declared in both SDUs.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--130Item (lvi) -- Access To Zero--Preference GESs (DD 0 1C)DESCRIPTION : Upon ORT upload, the Access to Zero--Preference GESs setting is NOT within theacceptable range.PARAMETERS : The uploaded ORT item (lvi) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lv) -- Secured ORT Modified Flag (DD 0 1D)DESCRIPTION : Upon ORT upload, the Secured ORT Modified Flag setting is NOT within the acceptablerange.PARAMETERS : The uploaded ORT item (lv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lvii) -- L--Band Reference Offset Calibration Thresholds (DD 0 1E)DESCRIPTION : Upon ORT upload, the L--Band Reference Offset Calibration Thresholds setting is NOTwithin the acceptable range.PARAMETERS : The uploaded ORT item (lvii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lix) -- APHONE Audio Level Setting (DD 0 1F)DESCRIPTION : Upon ORT upload, the Aphone Audio Level setting is NOT within the acceptable range.PARAMETERS : The uploaded ORT item (lix) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lx) -- Aero--H Only Operation (DD 0 20)DESCRIPTION : Upon ORT upload, the Aero--H Only Operation setting is NOT within the acceptable range.PARAMETERS : The uploaded ORT item (lx) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.User ORT Error (Level 1 Code DEh)Item (ii) -- Satellite/GES Names (DE 0 01)DESCRIPTION : Upon ORT cross/upload, the Satellite/GES Names are NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (ii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (iii) -- GES Preference Values (DE 0 02)DESCRIPTION : Upon ORT cross/upload, the GES Preference Values setting is NOT within the acceptablerange.PARAMETERS : The cross/uploaded ORT item (iii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (iv) -- Maintenance Page Access (DE 0 03)DESCRIPTION : Upon ORT cross/upload, the Maintenance Page Access setting is NOT within theacceptable range.PARAMETERS : The cross/uploaded ORT item (iv) value that has failed the range test.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--131FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (v) -- Cockpit Telephone Numbers (DE 0 04)DESCRIPTION : Upon ORT cross/upload, the Cockpit Telephone Numbers setting is NOT within theacceptable range.PARAMETERS : The cross/uploaded ORT item (v) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (vii) -- Resources Reserved For Headset (DE 0 05)DESCRIPTION : Upon ORT cross/upload, the Resources Reserved for Headset setting is NOT within theacceptable range.PARAMETERS : The cross/uploaded ORT item (vii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (x) -- Ground--to--Air Circuit--Mode Data (DE 0 07)DESCRIPTION : Upon ORT cross/upload, the Ground--to--Air Circuit--Mode Data setting is NOT within theacceptable range.PARAMETERS : The cross/uploaded ORT item (x) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xiii) -- Ground--to--Air Calls (DE 0 08)DESCRIPTION : Upon ORT cross/upload, the Ground--to--Air Calls setting is NOT within the acceptablerange.PARAMETERS : The cross/uploaded ORT item (xiii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xiv) -- Call Camp--On Duration (DE 0 09)DESCRIPTION : Upon ORT cross/upload, the Call Camp--On Duration setting is NOT within the acceptablerange.PARAMETERS : The corss/uploaded ORT item (xiv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xv) -- Camp--On Timeout Action (DE 0 0A)DESCRIPTION : Upon ORT cross/upload, the Camp--On Timeout Action setting is NOT within the acceptablerange.PARAMETERS : The cross/uploaded ORT item (xv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xvi) -- Store APHONE Telephone Numbers (DE 0 0B)DESCRIPTION : Upon ORT cross/upload, the Store APHONE Telephone Numbers setting is NOT within theacceptable range.PARAMETERS : The cross/uploaded ORT item (xvi) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--132Item (xix) -- Ground--to--Air Call Preemption (DE 0 0C)DESCRIPTION : Upon ORT cross/upload, the Ground--to--Air Call Preemption setting is NOT within theacceptable range.PARAMETERS : The cross/uploaded ORT item (xix) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xx) -- Preferred Cockpit Call Routing (DE 0 0D)DESCRIPTION : Upon ORT cross/upload, the Preferred Cockpit Call Routing setting is NOT within theacceptable range.PARAMETERS : The cross/uploaded ORT item (xx) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxi) -- Preferred APHONE Call Routing (DE 0 0E)DESCRIPTION : Upon ORT cross/upload, the Preferred APHONE Call Routing setting is NOT within theacceptable range.PARAMETERS : The cross/uploaded ORT item (xxi) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxiv) -- APHONE Outgoing Call Barring Level (DE 0 0F)DESCRIPTION : Upon ORT cross/upload, the APHONE Outgoing Call Barring Level setting is NOT withinthe acceptable range.PARAMETERS : The cross/uploaded ORT item (xxiv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxv) -- Call Barring Security Code (DE 0 10)DESCRIPTION : Upon ORT cross/upload, the Call Barring Security Code setting is NOT within theacceptable range.PARAMETERS : The cross/uploaded ORT item (xxv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxvi) -- Shared APHONE Telephone Number Storage (DE 0 11)DESCRIPTION : Upon ORT cross/upload, the Shared APHONE Telephone Number Storage setting is NOTwithin the acceptable range.PARAMETERS : The cross/uploaded ORT item (xxvi) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxxiii) -- ORT Description (DE 0 12)DESCRIPTION : Upon ORT cross/upload, the ORT Description setting is NOT within the acceptable range of24 ISO--5 characters maximum.PARAMETERS : The cross/uploaded ORT item (xxxiii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--133Item (xxxiv) -- Airline Code (DE 0 13)DESCRIPTION : Upon ORT cross/upload, the Airline Code setting is NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (xxxiv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxxv) -- HEADSET Outgoing Call Barring Level (DE 0 14)DESCRIPTION : Upon ORT cross/upload, the HEADSET Outgoing Call Barring Level setting is NOT withinthe acceptable range.PARAMETERS : The cross/uploaded ORT item (xxxv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xxxvi) -- HEADSET Transit Call (DE 0 15)DESCRIPTION : Upon ORT cross/upload, the HEADSET Transit Call setting is NOT within the acceptablerange.PARAMETERS : The cross/uploaded ORT item (xxxvi) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xl) -- High Rate Data Transmit Support (DE 0 16)DESCRIPTION : Upon ORT cross/upload, the High Rate Data Transmit Support setting is NOT within theacceptable range.PARAMETERS : The cross/uploaded ORT item (xl) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (xlv) -- APHONE Called Terminal Id Assignment (DE 0 17)DESCRIPTION : Upon ORT cross/upload, the APHONE Called Terminal Id Assignment setting is NOT withinthe acceptable range.PARAMETERS : The cross/uploaded ORT item (xlv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (il) -- Mastery Handover Algorithm Weighting (DE 0 18)DESCRIPTION : Upon ORT cross/upload, the Mastery Handover Algorithm Weighting setting is NOT withinthe acceptable range.PARAMETERS : The cross/uploaded ORT item (il) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lviii) -- AES Position Reporting (DE 0 19)DESCRIPTION : Upon ORT cross/upload, the AES Position Reporting setting is NOT within the acceptablerange.PARAMETERS : The cross/uploaded ORT item (lviii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--134Item (lxi) -- HSD Preemption Preferences (DE 0 1A)DESCRIPTION : Upon ORT cross/upload, the HSD Preemption Preferences setting is NOT within theacceptable range.PARAMETERS : The cross/uploaded ORT item (lxi) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately, and the default setting is used in place of thefailed ORT setting.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The ORTool does not allow undefined selections of this parameter code.Item (lxii) -- Ongoing HSD Call EIRP (DE 0 1B)DESCRIPTION : Upon ORT cross/upload, the HSU Call Progress Reserved EIRP setting is NOT within theacceptable range defined in Section 3.3.3.1.4.1 (lxii).PARAMETERS : The cross/uploaded ORT item (lxii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting specified in Section 3.3.3.1.4.3.2 (lxii) is used in place of the failed ORTsetting.Item (xxxvii) -- ORT Modified Flag (DE 0 1C)DESCRIPTION : Upon ORT cross/upload, the ORT Modified Flag setting is NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (xxxvii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxiii) -- WSC Manual Dialing (DE 0 1D)DESCRIPTION : Upon ORT cross/upload, the WSC Manual Dialing setting is NOT within the acceptablerange.PARAMETERS : The cross/uploaded ORT item (lxiii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxiv) -- Minimum HSD Call EIRP (DE 0 1E)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the Minimum HSD Call EIRP setting is NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (lxiv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxv) -- HSD Registration Preference (DE 0 1F)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the HSD Registration Preference setting is NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (lxv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxvi) -- Swift64 M--ISDN LES Preference Values (DE 0 20)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the Swift64 M--ISDN LES Preference Values setting is NOT within the acceptable range.PARAMETERS : Param 1: 01 = Satellite Id out of range02 = LES Id out of range03 = LES preference out of rangeParam 2: The cross/uploaded ORT item (lxvi) value that has failed the range test.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--135FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxvii) -- Swift64 MPDS LES Preference Values (DE 0 21)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the Swift64 MPDS LES Preference Values setting is NOT within the acceptable range.PARAMETERS : Param 1: 01 = Satellite Id out of range02 = LES Id out of range03 = LES preference out of rangeParam 2: The cross/uploaded ORT item (lxvii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxviii) -- Ethernet MAC Address Assignment (DE 0 22)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the Ethernet MAC Address Assignment setting is NOT within the acceptable range.PARAMETERS : 01:The uploaded ORT duplicated item (lxviii) has identical non--zero values for SDU 1 andSDU 2.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxix) -- PPPoE Access--Concentrator Name (DE 0 23)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the PPPoE Access--Concentrator Name setting is NOT within the acceptable range.PARAMETERS : Param 1: 01 = The uploaded ORT duplicated item (lxix) has identical values for SDU 1 andSDU 2Any value other than 1 = The cross/uploaded ORT item (lxix) value that hasfailed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxx) -- Telnet Server Access (DE 0 24)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the Telnet Server Access setting is NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (lxx) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxxi) -- DHCP Server Access (DE 0 25)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the DHCP Server Access setting is NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (lxxi) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxxii) -- Telnet IP Address Assignment (DE 0 26)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the Telnet IP Address Assignment setting is NOT within the acceptable range.PARAMETERS : 01:The uploaded ORT duplicated item (lxxii) has identical values for SDU 1 and SDU 2.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--136Item (lxxiii) -- Telnet Subnet Mask Assignment (DE 0 27)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the Telnet Subnet Mask Assignment setting is NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (lxxiii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxxiv) -- Telnet Default Gateway Assignment (DE 0 28)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the Telnet Default Gateway Assignment setting is NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (lxxiv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxxv) -- DHCP IP Address Assignment (DE 0 29)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the DHCP IP Address Assignment setting is NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (lxxv) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxxvi) -- DHCP IP Address Pool Allocation (DE 0 2A)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the DHCP IP Address Pool Allocation setting is NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (lxxvi) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxxvii) -- BGAN PDP Session Parameters (DE 0 2B)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the BGAN PDP Session Parameters setting is NOT within the acceptable range.PARAMETERS : The cross/uploaded ORT item (lxxvii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Item (lxxviii) -- PSID Supplementary Frequencies (DE 0 2C)DESCRIPTION : Applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. Upon ORTcross/upload, the PSID Supplementary Frequencies setting is NOT within the acceptable range.PARAMETERS : Param 1: 01 = Satellite Id out of range02 = Psid frequency out of range03 = Table revision out of rangeParam 2: The cross/uploaded ORT item (lxxviii) value that has failed the range test.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The default setting is used in place of the failed ORT setting.Slave HGA/IGA Log--on Test (Level 1 Code DFh)Slave HGA/IGA Log--on Test Failure (DF 0 01)DESCRIPTION : If two HGAs and/or IGAs are installed in a dual system and not failed, and the system is inautomatic antenna selection mode the SDU shall perform an HGA/IGA log--on test. The conditions for thetest is the same as for the LGA log--on test.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--137COMMENTARYThis assumes that an HGA/IGA slave is not tested if the master is logged--on via anLGA. The master SDU shall test by requesting the slave SDU to perform a log--on via itsHGA/IGA, then switching back to the original master’s HGA/IGA and renewing the log--on.A fault is declared by the slave SDU if it does not achieve log--on, but log--on is subsequently successful viathe original master’s HGA/IGA.PARAMETERS : Cumulative count of sequential test failures since the last factory settings restart or testpassing.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : Successful log--on via this HGA/IGA, either due to a test log--on, or log--on beingachieved as master.REMARK : This failure condition is reported in 276--11.Slave HGA/IGA Log--on Test Not Initiated (DF 0 02)DESCRIPTION : This fault is declared if a slave HGA/IGA log--on test is not initiated because ofequipment failure ([r_sdu_min_op.X] OR [r_hga_subsys.X]) , cross--talk bus (XTB) full communications notbeing established, the slave being disabled ([r_common.C]), or the master only being logged--on via LGA; orif the master SDU attempts a test log--on via the slave, but no response is received from the slave via theXTB within five minutes; or if the test is aborted due to any of the reasons previously stated.PARAMETERS : 1 = slave HGA/IGA equipment not OK2 = XTB full communications not achieved3 = slave SDU is disabled4 = response timeout5=masterlog--onisLGAFAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : Performing a successful test log--on, or handover of mastery, or upon failure DF 0becoming active.REMARK : This failure condition is reported in 276--11.HSU1 System Disable Discrete Failure (E1 0 01)DESCRIPTION : The SDU’s HSU disable discrete is tested by comparing the level of the BITE tellback withthe commanded state, as specified below. Should the output discrete’s BITE tellbackvalue not be the same as the commanded value for either the active or inactive state (or both) after twosuccessive checks, then this fault is declared.During POST/PAST, the HSU disable discrete output is tested for being able to achieve the active andinactive states by commanding the HSU to the active state briefly (i.e., 10 ms), and then inactive again.During CM, the HSU disable discrete is tested whenever its commanded state is changed for operationalreasons, and also monitored for its currently commanded state once every 30 seconds.Test results for the discrete output successfully achieving the commanded state (active or inactive) isrecorded independently, and the fault shall only be cleared when both commanded states have beenrecorded as being achieved the last time they were tested.PARAMETERS : Parameter 1 is set to 1 if the active state is not achieved.Parameter 2 is set to 1 if the inactive state is not achieved.FAIL CRITERIA : This fault transitions immediately to a failure.RECOVERY CRIT. : This failure is cleared as soon as the fault is cleared, i.e., as soon as both commandedstates have been recorded as being achieved the last time they were tested.REMARK : This failure is Class 2 (Class 3 for Airbus), and does not indict [HSU1]/[HSU], because the reasoncould as likely be failure in the SDU BITE circuitry.Level 3 failure code 81 is not used for the POST/PAST case (i.e., the POST/PAST and CM tests areidentical).In the actual implementation, if an HSU is installed, this discrete is repetitively commanded to its currentlyrequired state (whether on or off) at a rate of ~ 15 Hz. The CM test is performed after each such command,hence continuously at ~ 15 Hz (which includes the case of whenever a state change is commanded) as wellas once every thirty seconds.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--138Since there is no separate Level 3 failure code 81 for the POST/PAST case, even the POST/PAST caseincludes the one--second fail criteria. The POST/PAST case also requires the retest fail criteria in order toavoid nuisance failures because there is no guarantee that the CM testing (which might otherwise clear aPOST/PAST--detected fault) will begin or resume within one second of POST/PAST.HSU2 System Disable Discrete Failure (E2 0 01)Same as E1 0 01 except substitute “HSU2” for “HSU1”. Only applicable prior to SDU Part Number7516118--XX130/--xx140.Unsupported Configuration (Level 1 Code E3h)These failures are only applicable prior to SDU Part Number 7516118--XX130/--xx140.Unsupported HSU1 Configuration (E3 0 01)DESCRIPTION : The SDU shall raise this fault when it detects an HSU configuration that is not allowed, asspecified below. The HSU “number” is determined per the part number informationtransferred by the HSU in its Build Identity message.PARAMETERS : 01: A lone HS--702 is installed on either HSU port (i.e., SDU is strapped for only oneHSU, and it is HS--702).02: Two HS--702 units are installed (i.e., SDU is strapped for two HSUs, and both areHS--702).03: HS--700 is installed on the HSU2 port, and HS--702 is installed on the HSU1 port(i.e., the units are not wired to the correct ports).04: A lone HS--700 is installed on the HSU2 port.FAIL CRITERIA : This fault transitions to failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : The SDU needs to be restarted to allow this failure to recover after the HSU configuration hasbeen corrected to a valid one. This is done in order to avoid the complexities of having to deal withunsupported configurations that might nonetheless be allowed to operate by the SDU due to an inactiveHSU1 input bus (i.e., a simultaneous unsupported configuration anda failure).Unsupported HSU2 Configuration (E3 0 02)Same as E3 0 01.COMMENTARYThis failure is raised when E3 0 01 is raised so that both functional resources [hsu1] and [hsu2] can beindicted when any of the unsupported configurations occur.HSU1/SDU Interface Version Incompatibility ( E4 0 81)DESCRIPTION : This fault is raised during the Initial Communications phase when the SDU determines thatthe bus interface version numbers between the HSU and SDU are incompatible (i.e., not identical). Prior toSDU Part Number 7516118--XX130/--xx140. For SDU Part Number 7516118--XX130/--xx140 and subsequent.PARAMETERS : The interface version number of the SDU as the least significant nibble of the parametervalue long word; the interface version number of the HSU as the least significant nibble of the associatedparameter value long word.FAIL CRITERIA : This fault transitions into failure after the receipt of 5 or more consecutive HSU statuswords containing the same incompatible version number.RECOVERY CRIT. : This failure is cleared after the receipt of 5 or more consecutive HSU status wordscontaining the same compatible version number.REMARK : Version 1 is the only acceptable value prior to SDU Part Number 7516118--XX130/--xx140, whileversion 2 is the only acceptable value for SDU Part Number 7516118--XX130/--xx140 and subsequent.HSU2/SDU Interface Version Incompatibility (E5 0 81)Same as for E4 0 01 except substitute “HSU2” for “HSU1”. Only applicable prior to SDU Part Number7516118--XX130/--xx140.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--139HSU/HPA Tx RF Signal Path (Level 1 Code E6)HSU1/HPA Tx RF Signal Path Failure (E6 0 81/01)DESCRIPTION : For SDU Part Number 7516118--XX130/--xx140 and subsequent, the POST/PAST fault isdeclared when the SDU fails to detect a transition in the reported HPA input power level when the HSUtransmits a CW test signal. This POST/PAST test shall only be performed when the installed HPA is a linear60W HPA.For Packages 3.0 and subsequent, the CM fault is declared when the HPA fails to report to the SDU anydetected output power while the HSU is transmitting its ocean region registration request. This CM test shallonly be performed if failure D5 0 02 is not currently active and only when the HSU carrier is the only onepresent.PARAMETERS : None.FAIL CRITERIA : The POST/PAST fault transitions to a failure if there is no transition in the reported HPAinput power level for two consecutive tests. The CM fault transitions to a failure after 5 consecutive attemptsby the HSU result in no measurable HPA output power level.RECOVERY CRIT. : Neither the POST/PAST or CM failure is explicitly cleared.REMARK : POST/PAST fault: For SDU Part Number 7516118--XX130/--xx140 and subsequent, thePOST/PAST test (combined with the SDU/HPA Tx RF continuity check) allows RF transmit continuity failuresto be isolated to either the HSU to HPA cable or the SDU to HSU cable without the need for the SDU to belogged on.CM fault: This test is not done during the PAST period but only on actual transmissions (e.g. during EIRPrequest for M--ISDN registration, for SDU Part Number 7516118--XX130/--xx140 and subsequent). Thismeans it will not show up on the CFDS Test Results page, and it is hard to determine if it has been fixedwithout incrementing the flight leg after each attempt at fixing it. The test also depends on the correctfunctioning of the HPA’s output power detector and the expected HPA amplification (gain), so if the HPA is notamplifying correctly, this failure may result. A basic troubleshooting guide can help determine the generallocation where the failure is most likely to occur.This CM fault will also be declared whenever the HPA independently turns carriers off (i.e., not under normalcommand from the SDU), which causes any subsequent RF signal path test to fail.Prior to SDU Part Number 7516118--XX130/--xx140: In order to facilitate the independent calibration of HSUto HPA cable losses and HSU/HPA Transmit RF continuity checks in dual HSU configurations, the SDU willdelay for 15 seconds the satellite data link availability indicator for HSU2 after the availability for HSU1 hasbeen established.COMMENTARYFor SDU Part Number 7516118--XX130/--xx140 and subsequent, the HSU shall delay the registration of allremaining HSD channels for 15 seconds following the registration of the first HSD channel, to allow the SDUto perform calibration of HSU to HPA cable loss and HSU/HPA Transmit RF continuity testing.HSU1 To HGA/IGA HPA Calibration Error (E6 0 02)DESCRIPTION : This fault is declared if the calculated HSU to HPA Loss for HSU channel 1 is outsideacceptable limits (ie not within 10 to 30dB).PARAMETERS : Failure Param: A 1 shall indicate that the calibrated loss was calculated to be greater thanthe maximum value.A 0 shall indicate that the calibrated loss was calculated to be less than the minimum value.Assoc Param: The calculated loss in tenths of dB.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is cleared following the first successful calibration (i.e. within the specifiedrange) of the HSU to HPA loss for HSU channel 1.REMARK : This test is not done during the PAST period but only on actual transmissions (e.g. during EIRPrequest for M--ISDN registration for SDU Part Number 7516118--XX130/--xx140 and subsequent). This meansit will not show up on the CFDS Test Results page, and it is hard to determine if it has been fixed withoutincrementing the flight leg after each attempt at fixing it. The test also depends on the correct functioning ofthe HPA’s output power detector and the expected HPA amplification (gain), so if the HPA is not amplifyingcorrectly, this failure may result.(e.g. during log--on).RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--140HSU2 To HGA/IGA HPA Calibration Error (E6 0 03)Same as for E6 0 02 except substitute “channel 2” for “channel 1”.HSU3 To HGA/IGA HPA Calibration Error (E6 0 04)Same as for E6 0 02 except substitute “channel 3” for “channel 1”.HSU4 To HGA/IGA HPA Calibration Error (E6 0 05)Same as for E6 0 02 except substitute “channel 4” for “channel 1”.HSU2/HPA Tx RF Signal Path Failure (E7 0 01)Same as for E6 0 01 except substitute “HSU2” for “HSU1”. Only applicable prior to SDU Part Number7516118--XX130/--xx140.DLNA/HSU1 Rx RF Signal Path Failure (E8 0 81)DESCRIPTION : For Packages 3.0 and subsequent, this fault is declared during POST/PAST when the HSUdoes not report to the SDU a valid (i.e., normal operation data, not NCD) RF input power measurement, viaLabel 277 prior to SDU Part Number 7516118--XX130/--xx140, or Label 306 for SDU Part Number7516118--XX130/--xx140 and subsequent that indicates a rising noise floor level from an active HGA LNAwithin five seconds of the HGA LNA having been turned on. This test shall only be performed if the BSU inputbus is active, the HGA LNA BITE is Ok, and the BSU is declaring the multi--control bus input as active. Thistest is not performed if any BSU self--test misoperation failures [13/0/8A, 13/0/0A, 15/0/8A, 15/0/0A] aredeclared or label 277/306 does not declare normal operation data.PARAMETERS : 16--bit Rx Power Level measurement.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is not explicitly cleared.REMARK : The HSU only outputs valid data for this test between the completion of its own POST and theSDU removing SSM = Functional Test from its HSU control word transmissions. Abasic troubleshooting guide (reference Section 4.4.5.233 Commentary) can help determine the generallocation where the failure is most likely to occur.HSU2/LNA RX RF Coax Continuity Failure (E9 0 81)Same as for E8 0 01 except substitute “HSU2” for “HSU1”. Only applicable prior to SDU Part Number7516118--XX130/--xx140.COMMENTARYAssuming a single failure in the Tx or Rx signal path, the block diagrams and tables that follow can be helpfulin determining which signal path segment is the single root cause from the available current failureinformation.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--141Figure 4.4.5.233--1 Single--Point Failure RF Signal Path Troubleshooting Guide (Pre--SDU PartNumber 7516118--XX130/--xx140)RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--142SIGNAL PATH FAILURES (Pre--SDU Part Number 7516118--XX130/--xx140)* This term is only required if HSU1 is wired (”X” otherwise)** This term is only required if HSU2 is wired (”X” otherwise)*** This condition (segment 7 failure) may exist, but it cannot be annunciated as such because the tests forfailures E6/0/01 and E7/0/01 are not performed if failure D5/0/02 (which is tested first) is already currentlyactive.Notes: X = Don’t careS=SDUH1 = HSU1H2 = HSU2Tx = TransmitRx = ReceiveNot all possible combinations are shown ---- only those for which there is a reasonably high probability ofdrawing conclusions regarding a single root cause.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--143SIGNAL PATH FAILURES (SDU Part Number 7516118--XX130/--xx140 and Subsequent)D5002and/orD5005*RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--144* This failure is only raised when the installed HPA is a linear 60W HPA (HP--720)** This condition (segment 3 failure) is annunciated by the tests associated with failures D5 0 05 and E6 081 when the installed HPA is a linear 60W HPA (HP--720). However, when the installed HPA is a linear 40WHPA (HP--600), this condition may exist, but it cannot be annunciated as such because the test for failureE6/0/01 is not performed if failure D5/0/02 (which is tested first) is already currently active.Notes: X = Don’t careS=SDUH=HSUTx = TransmitRx = ReceiveNot all possible combinations are shown ---- only those for which there is a reasonably highprobability of drawing conclusions regarding a single root cause.Dual HS--700 Config Warning (EA 0 01)DESCRIPTION : This warning is only applicable prior to SDU Part Number 7516118--XX130/--xx140, and israised when the SDU detects that two HS--700 units are installed when it is strapped for dual HSUconfiguration. The HSU “number” is determined per the part number information transferred by the HSU in itsBuild Identity message.PARAMETERS : NoneFAIL CRITERIA : ImmediatelyRECOVERY CRIT. : This warning is cleared when the HSU that is wired to the SDU’s HSU2 port reports thatit is an HS--702.REMARK : NoneNo Declared Active WSC (EB 0 01)DESCRIPTION : This fault is declared when at least one WSC input bus is active (which includesTP10H being strapped to the “WSC” state [reference Section 3.2.4.7], and at least one of TP12J, TP12K andTP13E being strapped for the respective WSC(s) “installed” as well as receipt of label 270 WSC statuswords), but no installed WSC indicates “Active” in its label 270 status words (bit 20).PARAMETERS : None.FAIL CRITERIA : This fault transitions to failure if the fault persists for 10 seconds.RECOVERY CRIT. : As soon as a label 270 status word is received from a WSC with an “Active” indication inbit 20, or the buses from all installed WSCs are declared inactive.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--145REMARK : [Related information] For the case of WSC Type = Honeywell MAU where only one MAU isexpected to be active at a time for the case of multiple MAUs, the SDU makes no attempt to deal with thepossible opposite condition of multiple MAUs declaring themselves to be active simultaneously [whereas itdoes maintain multiple Williamsburg sessions for WSC Type = Airbus RAIMP]. This includes no BIT for thatcondition.HSU Straps (Configuration Pins) Error (Level 1 Code ECh)HSU Configuration Straps Parity Error (EC 0 81)DESCRIPTION : This fault is applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent.During POST/PAST, the HSU configuration straps (reference Section 3.4.2) is tested for parity. If thecomputed parity is even, this fault is declared by the HSU (via a Williamsburg Failure Report message withfault code 0/8C).PARAMETERS : The HSU configuration strap and parity settings.FAIL CRITERIA : This fault transitions to failure if the fault persists for two out of three consecutive tests.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : None.HSU Configuration Straps Error (EC 0 82)DESCRIPTION : This fault is applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent, andis declared by the HSU during POST/PAST (via a Williamsburg Failure Report message with fault code 9/82)when there is no response from the hardware device used to access the HSU configuration straps.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure if there is no response from the Configuration Strapshardware device on two out of three consecutive tests.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : HSU is declared unserviceable.SDU ORT / HSU Configuration Straps Incompatibility (Level 1 Code EDh)HSU BGAN Configuration Error (ED 0 01)DESCRIPTION : This fault is applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent. It isdeclared by the HSU (via a Williamsburg Failure Report message with fault code 0/0F) when HSDRegistration Selection in the HSU configuration data passed to the HSU is set to “BGAN Always”, but theBGAN Enable HSU configuration strap (HSU pin MP 1B) is set to Disable”.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : HSU is declared unserviceable.HSU Forward Id Address Bits (Straps) Error (Level 1 Code EEh)HSU Forward Id Address Bits (Straps) Error (EE 0 81)DESCRIPTION : This fault is applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent, andis declared by the HSU during POST/PAST (via a Williamsburg Failure Report message with fault code 9/81)when there is no response from the hardware device used to access the strapped HSU Forward Id Address.PARAMETERS : The failure parameter indicates which hardware device failed and contains one of thefollowing values:1: PCA9554A I2C device2: PCA9555 I2C device3: Both I2C devices.FAIL CRITERIA : This fault transitions to a failure if there is no response from the hardware device used toaccess the HSU Forward Id Address Straps on two out of three consecutive tests.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : HSU is declared unserviceable.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page D--146Illegal HSU Forward Id Address (EE 0 82)DESCRIPTION : This fault is applicable to SDU Part Number 7516118--XX130/--xx140 and subsequent, andis declared by the HSU during POST/PAST (via a Williamsburg Failure Report message with fault code 0/90)when the strapped HSU Forward Id address is set to all zero’s, all one’s or to an invalid value as determinedby comparison with the internal look--up table held by the HSU.PARAMETERS : The HSU Forward Id address read from the discrete straps.FAIL CRITERIA : This fault transitions to a failure if the fault persists on two out of three consecutive tests.RECOVERY CRIT. : This failure is never explicitly cleared.REMARK : HSU is declared unserviceable.Pilot Event Marker (FD 0 01--16)DESCRIPTION : While either airborne or on the ground, the pilot observes an ’event’ and desires to have asnapshot of all system states and therefore presses the PEM switch in the cockpit. Thiscondition is flagged with a failure when the PEM is received from the CAIMS OMS.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediately upon receipt of CAIMS Label 226 with bit 29set to one when CAIMS is inactive.RECOVERY CRIT. : This failure transitions to normal when Label 226 bit 29 transitions to zero.REMARK : This condition is used to synchronize the log to a special event observed by the pilot while eitherin--flight or on the ground. This is unique in that subsequent activations of this fault ina specific flight leg increments the Failure index so that a specific time stamp can be assigned each time.External Power Supply Interrupt In--Flight (FE 0 01)DESCRIPTION : While airborne, the power to the SDU is interrupted. This condition is flagged with a failurewhen the POC is incremented and the current DC state is DC1 or DC1’.PARAMETERS : None.FAIL CRITERIA : This fault transitions to a failure immediatelyRECOVERY CRIT. : This failure transitions to normal immediately.REMARK : This condition is used to annunciate a special case of SDU power--up while in--flight. The failuremessage will preclude the unnecessary removal of the SDU when a power interruptoccurs and other LRUs indict the SDU. The failure is immediately removed from the current failures list toavoid an erroneous failure indication on the front panel alphanumeric display.RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page INDEX--1INDEXAAAC. See aeronautical administratiive communicationsACARS. See aircraft communications addressing andreporting systemACP. See audio control panelacronyms and abbreviations, INTRO--3actual power out status, 6--57ACU. See antenna control unitADL. See airborne data loaderADS. See automatic dependent surveillanceaeronautical administrative communications, 1--1aeronautical operational control, 1--1aeronautical passenger communications, 1--1, 3--2Aeronautical Radio, Inc., 1--2, 2--28AES. See aircraft earth stationAFIS. See aircraft flight information systemair filtration systems, B--1installation instructions, B--4air trafficcontrol, 1--1services, 1--1Air Transport Association, reference numbers, 6--89Airbus, 6--93, 6--94, 6--96, 6--98, 6--100, 6--101, 6--103,6--105Boeing, 6--90, 6--91, 6--92, 6--93McDonnell Douglas, 6--106, 6--107, 6--108, 6--109air--to--ground calls, 5--59airborne data loader, 1--8, 2--8, 2--11, 2--12, 2--13aircraft avionics, 1--8aircraft communications addressing and reporting system,1--1, 1--8peripheral function, 2--28aircraft earth station, 1--1, 1--2, 2--1, 2--2, 2--15, 2--16classifications, 1--9components, 1--2identification, 5--47management, 2--1operational modes for log--on, 2--3aircraft identification, 6--8, 6--68aircraft flight information system, 2--28alphanumeric display test, 6--6AMS. See audio management systemAMU. See audio management unitanalogaudio channel, 3--2connected telephone(s), 1--7, 3--1, 3--1, 3--11call barring level, 3--1, 3--3, C--4handset, 2--5, 2--6, 2--7stored telephone numbers, 3--3, C--5system management commands, 3--4, 3--5, C--4private branch exchange, 1--7, 3--1, 5--50interfaces, 3--7trunk lines, 3--2antennageneral removal instructions, 7--3hardware, 7--2removal and installation, 7--2weather protection, 7--2antenna control unit, 1--6, 5--53, 6--5, 6--8antenna subsystem, 1--6, 5--51, 5--52, 5--53AOC. See aeronautical operational controlAPBX. See analog private branch exchangeAPC. See aeronautical passenger communicationsAPHONE. See channels, analogAPOS. See actual power out statusARINC. See Aeronautical Radio, Inc.ARINC 600 connectorlayouts and contact arrangement, 5--1pin assignments, A--9requirements, 5--3ATA. See Air Transport AssociationATC. See air traffic, controlATS. See air traffic, servicesaudio control panel, 2--27, 3--10, 5--59audio interfaces, 3--3audio management system, 2--27audio management unit, 3--10automatic dependent surveillance, 1--1, 1--8aviation satellite communications system, 1--1Bbeam steeringfunction, 1--5unit, 1--6, 1--20, 1--24, 5--53, 6--5, 6--8, A--4, A--3, A--4,A--1BIT. See built--in testBITE. See built--in test equipmentbootstrapprogram, 2--8system table, 2--2BSU. See beam steering unitb u i l t -- i n t e s t , 6 -- 8 8 , A -- 3 , A -- 5built--in test equipment, 1--26, 1--30, 1--35, 5--53, 6--3,6--5, 6--7, 6--89requirements, 6--1, 6--18system communication, 6--1bulk data communication, 2--13RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page INDEX--2CC--channel. See RF channels, C--channelcabincommunications, 1--5, 3--1communications system, 1--5, 1--6, 3--1, 5--50, A--3,A--1packet data function, 2--17, 5--49telecommunications panel, 6--110telecommunications unit, 1--6, 2--17, 3--1voice services, 2--13cabin/passenger communications equipment, 1--6, 3--1cableattenuation, 4--2loss requirements, 4--2CAIMS. See central aircraft information and maintenancesystemcallinitiation from analog phone, 3--7termination, 2--7, 2--16, 3--1, 3--11CCS. See cabin, communications systemcentral aircraft information and maintenance system,6--10, 6--88central fault display system, 1--8, 5--53, 6--6, 6--7, 6--10,6--16, 6--17, 6--27, 6--38, 6--46, 6--68, 6--71, 6--79, 6--89Airbus, 6--84, 6--87McDonnell--Douglas, 6--84, 6--87pages, 6--10, 6--88central maintenance computer, 1--8, 5--53, 6--7, 6--10,6--16, 6--17, 6--46, 6--87Boeing 747--400, 6--84to SDU communication, 6--84centralized fault display interface unit, 6--87, 6--88communication with SDU, 6--87CFDIU. See centralized fault display interface unitCFDS. See central fault display systemCGU. See communications, gateway unitchannels, analog, C--3circuit--mode, 2--16, 2--20call setup, 2--15, 2--16data, 2--4, 2--13, 2--15, 3--6, 6--111services, 2--13, 2--16voice, 2--7, 2--13CM. See continuous monitoringCMC. See central maintenance computerCMT. See commissioning and maintenance terminalco--ordinated universal time, 6--68, 6--71, 6--75, 6--79,6--81cockpitcommunications, 3--10hookswitch signaling, 5--59voice, 1--5call light test, 6--33, 6--34call light/chime, 5--57channels, 2--27configurations, 2--27functionality, 2--27services, 2--13sources, 1--7codec dedication, 5--58codec--generatedmessages, 3--2pacifiers, 3--2, 3--11commissioning and maintenance terminal, 2--5, 2--7,2--12, 6--6, 6--10, 6--18, 6--72, 6--110interface, 6--17page, 2--11, 6--3panel lamps, 6--111communicationsgateway unit, 3--3management unit, 1--5, 5--47, 5--48, 5--55, A--4communications management unit, 5--47configuration data messages, 6--85configuration pins, 5--16, 5--45, 5--46, 5--47, 5--48, 5--49,5--51, 5--53, 5--54, 5--55, 5--56, 5--57, 5--58, 6--39, 6--45,6--46, 6--48, 6--49, 6--51, 6--85, 6--88, 6--89continued airworthiness, 7--5, B--1continuity, 5--16continuous monitoring, 6--4, 6--5, 6--7, 6--8, 6--9, 6--11,6--30failure, 6--11failure records, 6--8cooling requirements, 4--3, B--1CPDF. See cabin, packet data functionCRC. See cyclic redundancy checkcross talk, 5--54cross--talk bus, 2--17, 2--18, 2--19, 6--110CTM panel. See cabin, telecommunications panelCTU. See cabin, telecommunications unitcustomer assistance, INTRO--6cyclic redundancy check, 2--9, 6--17Ddatainterface unit, 2--15setdownload, 2--8upload, 2--8terminal equipment, 2--15digitally connected phones, 1--7, 3--1DIP. See dual in--line packagingdiplexer, 1--6, 1--23, 5--53, 6--5, 6--8, A--3, A--1DIU. See data, interface unitDTE. See data, terminal equipmentDTMF. See dual tone multifrequencydual in--line packaging, 1--25RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/700023--20--27 5 Feb 2008©Honeywell International Inc. Do not copy without express permission of Honeywell.Page INDEX--3dual SATCOM system, 2--10, 2--16, 5--54, 6--27antenna configurations, 2--19cockpit voice configurations, 2--27control/status, 2--17reversion, 2--18automatic, 2--18manual, 2--19SCDU page displays, 6--110wiring diagram, 2--18dual tone multifrequency, 1--7, 3--2, 3--2, 3--7, 3--8, 3--11Eeffective isotopic radiated power, 1--21, 1--23, 1--24, 2--5Electronic Cable Specialistsair filtration assemblies, A--2ARINC 600 connectorsbeam steering unit, A--2high power amplifier, A--2satellite data unit, A--2signal conditioning unit, A--2attenuators, A--1, A--2cabin communications system provisions, A--3cable, A--1, A--2connectors, A--1, A--2hardware component kits, A--4, A--1, A--2plenum shelf assemblies, A--3tray assemblies, A--4, 7--5, A--2elevation handover threshold, 2--5, 2--7encrypted voice/data communication, 2--13Ffacsimile, 1--5, 2--13, 2--15, 3--1failuredetection and reporting level, 6--3memory log, 6--8, 6--18, 6--68, 6--71, 6--75, 6--79, 6--81,6--83messages in normal mode, 6--87recording, 6--7reporting, 6--8fault codes, D--1fault warning processor, 6--88flightidentification number, 2--4leg, 6--8management computer, 5--48plan information, 5--48FMC. See flight, management computerfunctional tests, 6--4, 6--5, 6--8, 6--9, 6--11, 6--84failure, 6--12failure records, 6--8FWP. See fault warning processorGGES. See ground earth stationGES--specific data broadcast, 2--16global beam, 2--1, 2--3Global--Wulfsberg Flitephone WH--10, 1--7, 3--1commands, 3--3interface, 3--1Greenwich Mean Time, 6--8ground earth station, 1--1, 1--2, 1--10, 2--1, 2--2, 2--15,3--5, 3--8, 5--47communication links, 1--9preference, 2--5, 2--6, 2--7, 3--5tied preferences, 2--5ground speed, 6--77, 6--83ground--to--air calls, 2--4, 3--5, 3--6, 3--10, 5--56, C--3GSDB. See GES--specific data broadcastGSPD. See ground speedHhandover, 2--1, 2--2, 2--7automatic, 2--1, 2--2, 2--7of mastery, 2--17, 2--18, 2--20user command, 2--1, 2--7high gain antenna, 1--6, 1--23, 2--16, 2--19, 2--21, 2--22,2--23, 2--24, 2--25, 2--26, 2--27, 4--3, 5--53, 6--5, 6--7,6--16, 6--56, 6--58maximum permissible exposure level, INTRO--4high power amplifier, 1--5, 1--13, 1--15, 1--24, 3--13, 5--51,5--52, 5--53, 6--1, 6--2, 6--5, 6--6, 6--7, 6--9, 6--16, 6--17,6--19, 6--56, 6--58, 6--71, 6--85, 6--88, 6--111, A--4, A--4,B--1, B--4, B--620 watt, 1--13, 1--31, 1--35ARINC 600 connector requirements, 5--3configurations, 1--15cooling requirements, 4--3environmental categories, 1--37front panel, 1--35front panel connector, 5--1installation equipment, 1--13leading particulars, 1--36mechanical installation data, 4--1nameplates, 1--44portable data loader connector, 1--35rear connector, 1--35, 5--140 watt, 1--13, 1--30, 1--31ARINC 600 connector requirements, 5--3configurations, 1--14cooling requirements, 4--3environmental categories, 1--34front panel, 1--30front panel connector, 5--1installation equipment, 1--13leading particulars, 1--33mechanical installation data, 4--1RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page INDEX--4nameplates, 1--44portable data loader connector, 1--30rear connector, 1--30, 5--1failure reporting, 6--8front panelindicators and controls, 6--8light emitting diodes, 6--9software upload, 2--9software/database updates, 2--8high power relay, 4--3, 5--53, 6--5, A--3, A--1Hollingsead International, A--4ARINC 600 connectorsbeam steering unit, A--5communications management unit, A--5high power amplifier, A--5satellite data unit, A--5cabin communications system provisions, A--1engineering support, A--4installation kit components, A--5cables, A--5connectors, A--5tray assemblies, A--6, 7--7plenum shelf assemblies, A--1HPA. See high power amplifierHPR. See high power relayIICAO. See International Civil Aviation OrganizationIGA. See intermediate gain antennainertial navigation system, 1--5inertial reference system, 1--8, 1--24, 2--5, 5--51, 6--40,A--2initial signal unit, 3--8INMARSAT. See International Maritime SatelliteOrganizationINS. See inertial navigation systeminstallation, new, 4--1instructions for continued airworthiness, 7--5interactive data communication, 2--13intermediate gain antenna, 1--6, 1--24, 2--19maximum permissible exposure level, INTRO--4International Civil Aviation Organization, 1--1address, 2--16, 5--16, 5--47, 6--8, 6--38aircraft identification code, 2--4block strapping, 5--19International Maritime Satellite Organization, 1--10, 1--20,2--1, 2--13, 2--15four--region satellite coverage, 1--12International Organization for Standardization, 2--15, 3--9International Telecommunications Union, 1--1IRS. See inertial reference systemISO. See International Organization for StandardizationISU. See initial signal unitITU. See International Telecommunications UnionLlevel I failure messages, 6--12, 6--13, 6--14, 6--16, 6--89Airbus, 6--93, 6--94, 6--96, 6--98, 6--100, 6--101, 6--103,6--105Boeing, 6--90, 6--91, 6--92, 6--93McDonnell Douglas, 6--106, 6--107, 6--108, 6--109LGA. See low gain antennalight emitting diode, 1--30, 1--35, 6--8, A--3, A--5test, 6--6, 6--11line replaceable unit, 2--8, 6--4, 6--5, 6--75, 6--77, 6--81,6--86, 6--88, 6--89, 6--111, 7--1, 7--5, B--1, B--4, B--5, B--6,B--7coverage, 6--3data record, 6--87header record, 2--9identification, 6--16, 6--71installation, 7--3mechanical installation, 4--1removal, 7--3log--off, 2--1, 2--3, 2--6, 2--7, 6--23log--on, 2--1, 2--2, 2--3, 2--4, 2--5, 2--10, 2--16, 6--27, 6--33,6--34, 6--65automatic, 2--5, 2--6, 2--7constrained, 2--6, 2--7mode selection, 2--6policy, 2--3, 2--5, 3--4, C--1user command, 2--3low gain antenna, 1--6, 1--23, 2--5, 2--16, 2--19, 2--21,2--23, 2--24, 2--25, 2--26, 2--27, 5--53, 6--5, 6--7, 6--16,6--56, 6--58maximum permissible exposure level, INTRO--4low noise amplifier, 1--6, 5--53, 6--5, 6--8, A--3, A--1LRU. See line replaceable unitMmaintenanceactivity log, 6--18, 6--19activity record, 6--19panel assembly, 6--110management unit, 1--8, 1--20, 2--17MAR. See maintenance, activity recordmaximum permissible exposure level, INTRO--3high gain antenna, INTRO--4intermediate gain antenna, INTRO--4low gain antenna, INTRO--4radio frequency energy levels, INTRO--5MCDU. See multifunction control and display unitMCU. See modular concept unitmodular concept unit, 1--25MPEL. See maximum permissible exposure levelMU. See management unitRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page INDEX--5multi--channel SATCOM systemARINC 429 data requirements, 1--44, A--2, A--3avionics, 1--5, 1--13, 3--1block diagram, 1--17configurations, 1--25cooling requirements, 4--3physical description, 1--25software and hardware compatibility, 1--46failures, 6--1multifunction control and display unit, 1--5, 1--7, 2--11,3--10, 5--55, 5--57, 6--17, 6--20, 6--21Nnon--volatile memory, 6--88, C--1OOCXO. See oven--controlled crystal oscillatoroff--hook, 1--7, 3--2, 3--1, 3--3, 3--5, 3--7, 3--9, 3--10, 5--59OMS. See onboard maintenance systemon--board maintenance system, 1--8Boeing 777, 6--84CAIMS, 6--89on--hook, 1--7, 3--2, 3--3, 3--4, 3--5, 3--7, 3--8, 3--11, 5--59operational software, 2--8, 2--9ORT. See owner requirements tableoven--controlled crystal oscillator, 4--3, 6--5, 6--6owner requirements table, 1--8, 1--21, 1--23, 1--26, 3--3,3--4, 3--5, 3--6, 3--11, 3--13, 4--2, 5--56, 5--58, 6--27,6--64, 6--65, 6--110, C--1download/upload diskettes, 2--8, 2--11identification, 6--18, 6--71, 6--74, 6--85, 6--87, 6--88identification message, 6--11upload, 4--2, 7--4upload/download, 2--11PP--channel. See RF channels, P--channelPABX. See private automatic branch exchangepacket data, 1--6, 5--49messages, 1--5, 2--15services, 2--15, 2--16, 2--20packet--mode channels, 2--16part number block, 6--17PAST. See person--activated self--testPd--channel, 2--1, 2--2, 2--3, 2--4frequency, 2--3PDL. See portable data loaderperipherals, 1--25person--activated self--test, 1--46, 2--9, 2--10, 2--12, 2--13,5--47, 6--4, 6--6, 6--9, 6--29, 6--35, 6--38, 6--87personal computer, modem interface, 1--5phase--locked oscillator, 6--5, 6--6PMAT. See portable maintenance access terminalPOC. See power--on counterportable data loader, 1--8, 1--46, 2--8, 2--11, 2--12, 2--13,5--1connector, 1--26, 1--30, 1--35portable maintenance access terminal, 6--89POST. See power--on self--testpower interrupts, 6--4power supply unit, 6--6, 6--77, 6--83power--on counter, 6--77, 6--83power--on self--test, 1--46, 2--9, 5--47, 6--4, 6--5, 6--6, 6--9,6--29, 6--35priority 4 calls, 5--56private automatic branch exchange, 1--6, 3--1Psid--channel frequencies, 2--2, 2--6Psmc--channel, 2--1, 2--4, 2--5frequency, 2--2, 2--3, 2--6PSTN. See public switched telephone networkPSU. See power supply unitPTT. See push--to--talkpublic switched telephone network, 1--10push--to--talk, 1--7, 3--10, 6--6switched, 5--59RR--channel. See RF channels, R--channelradio frequency module, 6--6radio frequency unit interface adapter, 1--5, 1--13, 1--43ARINC 600 connector requirements, 5--3leading particulars, 1--44Rd--channel, 2--4, 2--5real--time clock, 6--19RF channels, 1--9C--channel, 1--9, 1--21, 1--22, 2--4, 2--7, 2--13, 2--15,2--16P--channel, 1--9, 2--1, 2--2, 2--3, 2--4, 2--6, 2--7R--channel, 1--9, 1--21, 1--22, 2--3, 2--4, 2--5T--channel, 1--9, 1--21, 1--22, 2--4, 2--5RF loop back test, 6--6RFM. See radio frequency moduleRFUIA. See radio frequency unit interface adapterRsmc--channel, 2--4, 2--5RTC. See real--time clockRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page INDEX--6SSATCOM control and display unit, 1--7, 1--24, 2--6, 2--17,2--19, 2--27, 3--10, 5--55, 5--57, 5--59, 6--6, 6--7, 6--8,6--10, 6--17, 6--20, 6--22, 6--87, 6--88display, 6--20, 6--21page, 2--11displays for dual systems, 6--110hierarchy, 6--25, 6--29pages, 6--10, 6--20, 6--24, 6--89configuration data, 6--27, 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, 6--51, 6--52, 6--54, 6--55, 6--56, 6--57, 6--59data loader, 6--59, 6--60, 6--61, 6--62, 6--63, 6--64,6--65, 6--66ground report, 6--27, 6--79, 6--80ground report troubleshooting data, 6--27, 6--81,6--82last leg class 3 faults, 6--27, 6--77, 6--78last leg report, 6--27, 6--66, 6--67LRU identification, 6--27, 6--71, 6--73, 6--74previous legs report, 6--27, 6--68, 6--69, 6--70, 6--71SATCOM main menu, 6--24, 6--26, 6--29, 6--110SATCOM maintenance, 6--27, 6--29, 6--59, 6--66,6--110SATCOM self--test, 6--35, 6--36, 6--37, 6--38SATCOM submenu, 6--27, 6--28, 6--66test, 6--27, 6--29, 6--30, 6--31, 6--32troubleshooting data, 6--27, 6--75, 6--76SATCOM main menu page, 3--11satellite data unit, 1--5, 1--13, 1--19, 1--26, 1--27, 2--5, 2--6,2--7, 2--10, 2--11, 2--12, 2--13, 2--16, 2--17, 2--18, 3--1,3--2, 3--1, 3--5, 3--8, 3--11, 5--47, 5--48, 5--49, 5--50,5--51, 5--53, 5--55, 5--56, 5--57, 5--59, 6--1, 6--3, 6--5,6--6, 6--7, 6--8, 6--9, 6--18, 6--19, 6--20, 6--22, 6--66,6--72, 6--84, 6--85, 6--87, 6--88, 6--89, 6--110, A--4, A--4,B--1, B--4, B--6, C--1portable data loader connector, 1--26ARINC 600 connector requirements, 5--3codec, 2--15, 2--27, 3--1, 3--10, 5--58configuration pin, 5--54cooling requirements, 4--3environmental categories, 1--29failure reporting, 6--10front panel, 1--26connector, 5--1indicators and controls, 6--10light emitting diodes, 6--11installation dependent considerations, 1--22, 4--2installation equipment, 1--13leading particulars, 1--27master, 2--16, 2--17, 2--18, 2--19mechanical installation data, 4--1modem, 1--20, 3--1nameplates, 1--44number, 5--54rear connector, 1--26, 5--1slave, 2--16, 2--17, 2--18, 2--19software upload, 2--9software/database updates, 2--8to WH10 handset actions, 3--1voice codec, 3--1, 3--2voice interface module, 1--20SCDU. See SATCOM control and display unitSCPC. See single channel per carrierscratchpad, 6--20, 6--21, 6--23, 6--65, 6--88SCU. See signal conditioning unitSDI. See source destination identiferSDU. See satellite data unitsecure voicecoding unit, 2--15interface, 1--5shop replaceable unit, 1--25, 6--3, 6--75, 6--77, 6--81sign/status matrix, 5--47, 6--4, 6--5, 6--6, 6--9, 6--84, 6--87,A--5, A--7, A--8signal conditioning unit, 1--5, 1--13, 1--44, A--4, A--3, A--2,A--3, A--4, A--5, A--7, A--8automatic input selection, A--5built--in test, A--3, A--5control functions, A--4front panel, A--3light emitting diode, A--3, A--5manual signal selection, A--4single channel per carrier, 1--9SMT. See surface--mount technologysoftware, upload, 2--8, 2--9validation, 2--9source destination identifier, 5--51, 5--54, 6--16, 6--84space segment, 1--1, 1--10spot beam, 1--12, 1--21, 1--24, 2--1, 2--2, 2--4, 2--5, 2--6handover, 2--6satellite, 2--1search table, 2--3SRU. See shop replaceable unitSSM. See sign/status matrixstandard ground test, 6--87strap parity, 5--49surface--mount technology, 1--25system address label, 2--9system components. See multi--channel SATCOM systemavionicssystem table, 2--2, 2--3, 3--5TT--channel. See RF channels, T--channelTDM. See time division multiplexTDMA. See time division multiple accessterminal interface function, 2--15terrestrial data and voice networks, 1--1, 1--10RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page INDEX--7time divisionmultiple access, 1--9multiplex, 1--9time since power--on, 6--77, 6--83total on--time clock, 6--18, 6--19UUTC. See co--ordinated universal timeVVCM. See voice codec modulevendor equipment, 1--28, 1--34, 4--4, A--1voice codec module, 3--10audio switching, 3--11dedication, 3--13sidetone, 3--11stored audio messages, 3--11voltage standing wave ratio, 4--2, A--2Wweight--on--wheels discrete, 6--7, 6--39XXTB. See cross--talk busRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUALMCS--4000/7000 Multi--Channel SATCOM System23--20--2730 Aug 2002Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page INDEX--8Blank PageRELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL INTERNATIONALUP86308

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