Honeywell DMA-37B2 DMA-37B DME Interrogator, 066-50013-1101, -1212 User Manual MM DME 37B DME System 1137 1 Rev 3

Honeywell International Inc. DMA-37B DME Interrogator, 066-50013-1101, -1212 MM DME 37B DME System 1137 1 Rev 3

Users Manual

Page HL-110 Oct 200734-51-02 HIGHLIGHTS© Honeywell International Inc. Do not copy without express permission of Honeywell.Honeywell International Inc.P.O. Box 97001Redmond, Washington 98073-9701U.S.ACAGE 97896Telephone: (800) 601-3099 (U.S.A.)Telephone: (602) 365-3099 (International)Web site: http://portal.honeywell.com/wps/portal/aeroTO HOLDERS OF MAINTENANCE MANUAL, PUB NO. 1137-1, DMA-37B DME SYSTEMREVISION NO. 003 DATED 10 OCT 2007HIGHLIGHTSThis revision is a full replacement. All changed pages have a new date, as identified in the List of Effective Pages. Revision bars are not used because the structure has changed.Remove and discard all pages of the manual and replace them with the attached pages. The Record of Revisions page has been brought up-to-date for you.Remove Page Insert Page Description of Change--- --- Revised the header and footer on all pages.T-1, PN-1 T-1 thru T-4 Revised to show the revision date of this manual. Added the ECCN number. Replaced the proprietary notice with the new Honeywell confidentiality notice, Materials License Agreement, and Copyright Notice.RH-1/RH-2 --- Deleted REVISION HIGHLIGHTS.RR-1, RR-2 RR-1, RR-2 Revised and issued this section.--- RTR-1, RTR-2 Added RECORD OF TEMPORARY REVISIONS. LEP-1, LEP-2 LEP-1, LEP-2 Revised to show where changes are made in this manual. TC-1/TC-2 TC-1 thru TC-4 Revised to show the location of the data in this manual.INTRO-1 INTRO-1 thru INTRO-6Revised format. Added proprietary, export, precautionary, and content data.0 thru 21/22 1 thru 20 Revised and issued this section.101 thru 116 1001 thru 1016 Revised and issued this section.201 thru 226 2001 thru 2024 Revised and issued this section.
Page HL-210 Oct 2007MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.34-51-02Blank Page
Honeywell International Inc.P.O. Box 97001Redmond, Washington 98073U.S.A.CAGE: 97896Telephone: (800) 601-3099 (U.S.A.)Telephone: (602) 365-3099 (International)Web site: http://portal.honeywell.com/wps/portal/aeroPage T-1Publication Number 1137-1, Revision 003 Revised 10 Oct 2007Oct 1995© Honeywell International Inc. Do not copy without express permission of Honeywell.34-51-02This document contains technical data and is subject to U.S. export regulations. These commodities, technology, or software were exported from the United States in accordance with the export administration regulations. Diversion contrary to U.S. law is prohibited.ECCN: 7E994, no license required.Maintenance ManualDMA-37B DME System
Page T-210 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Honeywell – ConfidentialTHIS COPYRIGHTED WORK AND ALL INFORMATION ARE THE PROPERTY OF HONEYWELL INTERNATIONAL INC., CONTAIN TRADE SECRETS AND MAY NOT, IN WHOLE OR IN PART, BE USED, DUPLICATED, OR DISCLOSED FOR ANY PURPOSE WITHOUT PRIOR WRITTEN PERMISSION OF HONEYWELL INTERNATIONAL INC. ALL RIGHTS RESERVED. Honeywell Materials License AgreementThe documents and information contained herein (“the Materials”) are the proprietary data of Honeywell International Inc. and Honeywell Intellectual Properties Inc (collectively “Honeywell”). These Materials are provided for the exclusive use of Honeywell Service Centers; Honeywell-authorized repair facilities; operators of Honeywell aerospace products subject to an applicable product support agreement, their wholly owned-subsidiaries or a formally designated third party service provider; and direct recipients of Materials from Honeywell’s Aerospace Technical Publication Distribution. The terms and conditions of this License Agreement govern your use of these Materials, except to the extent that any terms and conditions of another applicable agreement with Honeywell regarding the operation, maintenance, or repair of Honeywell aerospace products conflict with the terms and conditions of this License Agreement, in which case the terms and conditions of the other agreement will govern. However, this License Agreement will govern in the event of a conflict between its terms and conditions and those of a purchase order or acknowledgement. 1. License Grant - If you are a party to an applicable product support agreement, a Honeywell Service Center agreement, or an authorized repair facility agreement, Honeywell hereby grants you a limited, non-exclusive license to use these Materials to operate, maintain, or repair Honeywell aerospace products only in accordance with that agreement. If you are a direct recipient of these Materials from Honeywell’s Aerospace Technical Publication Distribution and are not a party to an agreement related to the operation, maintenance or repair of Honeywell aerospace products, Honeywell hereby grants you a limited, non-exclusive license to use these Materials to maintain or repair the subject Honeywell aerospace products only at the facility to which these Materials have been shipped ("the Licensed Facility"). Transfer of the Materials to another facility owned by you is permitted only if the original Licensed Facility retains no copies of the Materials and you provide prior written notice to Honeywell.2. Rights In Materials - Honeywell retains all rights in these Materials and in any copies thereof that are not expressly granted to you, including all rights in patents, copyrights, trademarks, and trade secrets. No license to use any Honeywell trademarks or patents is granted under this License Agreement.3. Confidentiality - You acknowledge that these Materials contain information that is confidential and proprietary to Honeywell. You agree to take all reasonable efforts to maintain the confidentiality of these Materials.4. Assignment And Transfer - This License Agreement may be assigned to a formally designated service designee or transferred to a subsequent owner or operator of an aircraft containing the subject Honeywell aerospace products. However, the recipient of any such assignment or transfer must assume all of your obligations under this License Agreement. No assignment or transfer shall relieve any party of any obligation that such party then has hereunder. 5. Copies of Materials - Unless you have the express written permission of Honeywell, you may not make or permit making of copies of the Materials. Notwithstanding the foregoing, you may make copies of only portions of the Material for your internal use. You agree to return the Materials and any copies thereof to Honeywell upon the request of Honeywell.
Page T-310 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.6. Term - This License Agreement is effective until terminated as set forth herein. This License Agreement will terminate immediately, without notice from Honeywell, if you fail to comply with any provision of this License Agreement or will terminate simultaneously with the termination or expiration of your applicable product support agreement, authorized repair facility agreement, or your formal designation as a third party service provider. Upon termination of this License Agreement, you will return these Materials to Honeywell without retaining any copies and will have one of your authorized officers certify that all Materials have been returned with no copies retained.7. Remedies - Honeywell reserves the right to pursue all available remedies and damages resulting from a breach of this License Agreement.8. Limitation of Liability - Honeywell does not make any representation regarding the use or sufficiency of the Materials. THERE ARE NO OTHER WARRANTIES, WHETHER WRITTEN OR ORAL, EXPRESS, IMPLIED OR STATUTORY, INCLUDING, BUT NOT LIMITED TO, (i) WARRANTIES ARISING FROM COURSE OF PERFORMANCE, DEALING, USAGE, OR TRADE, WHICH ARE HEREBY EXPRESSLY DISCLAIMED, OR (ii) WARRANTIES AGAINST INFRINGEMENT OF INTELLECTUAL PROPERTY RIGHTS OF THIRD PARTIES, EVEN IF HONEYWELL HAS BEEN ADVISED OF ANY SUCH INFRINGEMENT. IN NO EVENT WILL HONEYWELL BE LIABLE FOR ANY INCIDENTAL DAMAGES, CONSEQUENTIAL DAMAGES, SPECIAL DAMAGES, INDIRECT DAMAGES, LOSS OF PROFITS, LOSS OF REVENUES, OR LOSS OF USE, EVEN IF INFORMED OF THE POSSIBILITY OF SUCH DAMAGES. TO THE EXTENT PERMITTED BY APPLICABLE LAW, THESE LIMITATIONS AND EXCLUSIONS WILL APPLY REGARDLESS OF WHETHER LIABILITY ARISES FROM BREACH OF CONTRACT, WARRANTY, TORT (INCLUDING BUT NOT LIMITED TO NEGLIGENCE), BY OPERATION OF LAW, OR OTHERWISE.9. Controlling Law - This License shall be governed and construed in accordance with the laws of the State of New York without regard to the conflicts of laws provisions thereof. This license sets forth the entire agreement between you and Honeywell and may only be modified by a writing duly executed by the duly authorized representatives of the parties.Copyright - NoticeCopyright 1995, 2007, Honeywell International Inc. All rights reserved.Honeywell is a registered trademark of Honeywell International Inc. All other marks are owned by their respective companies.
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Page RR-110 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.RECORD OF REVISIONSFor each revision, put the revised pages in your manual and discard the superseded pages. Write therevision number and date, date put in manual, and the incorporator’s initials in the applicable columnson the Record of Revisions. The initial H shows Honeywell is the incorporator.Revision Number Revision Date Date Put In Manual By Revision Number Revision Date Date Put In Manual By 1 Not available Not available H2 13 Jul 1999 13 Jul 1999 H3 10 Oct 2007 10 Oct 2007 H
Page RR-210 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Revision Number Revision Date Date Put In Manual By Revision Number Revision Date Date Put In Manual By
Page RTR-110 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.RECORD 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.TemporaryRevision Number TemporaryRevision Date TemporaryRevisionStatusDate Put in Manual ByDateRemovedFrom Manual By
Page RTR-210 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.TemporaryRevision Number TemporaryRevision Date TemporaryRevisionStatusDate Put in Manual ByDateRemovedFrom Manual By
MAINTENANCE MANUALDMA-37B DME SystemPage LEP-1 10 Oct 2007© Honeywell International Inc. Do not copy without express permission of Honeywell.34-51-02indicates a changed or added pageF indicates a foldout pageLIST OF EFFECTIVE PAGESSubheading and Page DateTitle 0T-1 10 Oct 2007T-2 10 Oct 2007T-3 10 Oct 2007T-4 10 Oct 2007Record of Revisions 0RR-1 10 Oct 2007RR-2 10 Oct 2007Record of Temporary Revisions 0RTR-1 10 Oct 2007RTR-2 10 Oct 2007List of Effective Pages 0LEP-1 10 Oct 2007LEP-2 10 Oct 2007Table of Contents 0TC-1 10 Oct 2007TC-2 10 Oct 2007TC-3 10 Oct 2007TC-4 10 Oct 2007Introduction 0INTRO-1 10 Oct 2007INTRO-2 10 Oct 2007INTRO-3 10 Oct 2007INTRO-4 10 Oct 2007INTRO-5 10 Oct 2007INTRO-6 10 Oct 2007Description and Operation 0110 Oct 2007210 Oct 2007310 Oct 2007410 Oct 2007510 Oct 2007610 Oct 2007710 Oct 2007810 Oct 2007910 Oct 200710 10 Oct 200711 10 Oct 200712 10 Oct 200713 10 Oct 200714 10 Oct 200715 10 Oct 200716 10 Oct 200717 10 Oct 200718 10 Oct 200719 10 Oct 200720 10 Oct 2007Fault Isolation 10001001 10 Oct 20071002 10 Oct 20071003 10 Oct 20071004 10 Oct 20071005 10 Oct 20071006 10 Oct 20071007 10 Oct 20071008 10 Oct 20071009 10 Oct 20071010 10 Oct 20071011 10 Oct 20071012 10 Oct 20071013 10 Oct 20071014 10 Oct 20071015 10 Oct 20071016 10 Oct 2007Subheading and Page Date
MAINTENANCE MANUALDMA-37B DME SystemPage LEP-2 10 Oct 2007© Honeywell International Inc. Do not copy without express permission of Honeywell.34-51-02indicates a changed or added pageF indicates a foldout pageMaintenance Practices 20002001 10 Oct 20072002 10 Oct 20072003 10 Oct 20072004 10 Oct 20072005 10 Oct 20072006 10 Oct 20072007 10 Oct 20072008 10 Oct 20072009 10 Oct 20072010 10 Oct 20072011 10 Oct 20072012 10 Oct 20072013 10 Oct 20072014 10 Oct 2007F 2015/2016 10 Oct 2007F 2017/2018 10 Oct 2007F 2019/2020 10 Oct 2007F 2021/2022 10 Oct 2007F 2023/2024 10 Oct 2007Subheading and Page Date
Page TC-1Oct 8/0734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.TABLE OF CONTENTSSubject PageINTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-11. How to Use This Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-1A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-1B. Symbols. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-1C. Weights and Measurements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-12. Customer Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-2A. Honeywell Aerospace Online Technical Publications Web Site . . . . . . . . . . . . . . INTRO-2B. Complete Customer Care Center . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-23. Data Verification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-2A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-24. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-3A. Honeywell Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-3B. Other Publications. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-35. Acronyms and Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-4A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-4DESCRIPTION AND OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .11. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1A. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1B. Purpose of Equipment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3C. Equipment Part Numbers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3D. Equipment Required but Not Supplied . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5E. Configurations Available . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .52. System Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .7A. Unit Specifications. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .7B. Environmental Certification (066-50013-0101, -0202, and -0303 only). . . . . . . . . . . . . . . .9C. Environmental Certification (066-50013-1101 only) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .10D. Environmental Certification (066-50013-1212 only) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .123. System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .13A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .134. System Component Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .15A. DMA-37B DME Interrogator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .15B. Other Components in the System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .15
Page TC-2Oct 8/0734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.5. Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17B. Basic Theory . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10011. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001A. Description for -0101, -0202, and -0303 Only . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001B. Selt-Test Mode for -0101, -0202, and -0303 Only . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1003C. Display-Failures Mode for -0101, -0202, and -0303 Only. . . . . . . . . . . . . . . . . . . . . . . 1005D. Mainentance Mode for -0101, -0202, and -0303 Only . . . . . . . . . . . . . . . . . . . . . . . . . 1010E. Flight Fault Memory Mode for -0101, -0202, and -0303 Only . . . . . . . . . . . . . . . . . . . . 1014MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20011. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001A. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001B. Inspection After Unpacking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001C. Preinstallation Testing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001D. Equipment Changes and Marking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001E. Interchangeability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20012. Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2002A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2002B. Location of Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2002C. Interwiring and Cable Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2002D. Installation of System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20073. Inspection and System Check Procedures. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2008A. Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2008B. System Checkout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20094. Removal and Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014A. Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014B. Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20145. Maintenance Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014A. Adjustments and Alignments. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014B. System Protection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014C. Lubrication Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014D. Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014
Page TC-3Oct 8/0734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.List of IllustrationsFigure PageFigure Intro-1. Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-1Figure 1. DMA-37B DME Interrogator, 066-50013-0101, -0202, and -0303 . . . . . . . . . . . . .1Figure 2. DMA-37B DME Interrogator, 066-50013-1101 and -1212 . . . . . . . . . . . . . . . . . . .2Figure 3. DMA-37B DMA System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .14Figure 4. DMA-37B DME Interrogator Simplified Block Diagram . . . . . . . . . . . . . . . . . . . .16Figure 1001. Typical Normal Mode Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1001Figure 1002. LCD Control Flow. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1002Figure 1003. Test in Progress Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1003Figure 1004. Test Complete, No Failures Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1004Figure 1005. Test Complete, Failures Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1004Figure 1006. DME Receiver OK, External Failures Present Screen. . . . . . . . . . . . . . . . . . .1005Figure 1007. DME Receiver Failed, External Failures Also Present Screen . . . . . . . . . . . .1005Figure 1008. DME Receiver Failed, External Failures Not Present Screen . . . . . . . . . . . . .1006Figure 1009. Tuning Port A Failure Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1007Figure 1010. Tuning Port B Failure Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1007Figure 1011. SDI 0 Program Pin Failure Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1008Figure 1012. SDI 1 Program Pin Failure Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1008Figure 1013. Antenna Monitor Program Pin Failure Screen . . . . . . . . . . . . . . . . . . . . . . . . .1009Figure 1014. CMC Port Failure Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1009Figure 1015. DME Receiver Status (OK, FAILED) Screen . . . . . . . . . . . . . . . . . . . . . . . . . .1010Figure 1016. Tuning Port Status (NML, TST, NCD, NODA) Screen . . . . . . . . . . . . . . . . . . . 1011Figure 1017. Discrete Input Status Page 1 (OPEN, GRND) Screen. . . . . . . . . . . . . . . . . . . 1011Figure 1018. Discrete Input Status Page 2 (OPEN, GRND) Screen. . . . . . . . . . . . . . . . . . .1012Figure 1019. SDI Program Pin Status Page (OPEN, COMM) Screen . . . . . . . . . . . . . . . . .1012Figure 1020. Antenna Monitor Program Pin Status Page (OPEN, COMM) Screen . . . . . . .1013Figure 1021. CMC Port Status (ACTIVE, INACTIVE) Screen. . . . . . . . . . . . . . . . . . . . . . . .1013Figure 1022. Old Failures Page Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1014Figure 1023. Previous Flight Legs Failures First Page Screen. . . . . . . . . . . . . . . . . . . . . . .1015Figure 1024. Previous Flight Legs Failures Data Page Screen (Three Screens for Each Flight Leg).. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1015Figure 2001. Typical Normal Mode Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2010Figure 2002. Test in Progress Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2011Figure 2003. Test Complete, No Failures Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2012Figure 2004. Test Complete, Failures Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2012Figure 2005. DMA-37B DME Interrogator Dimensional Outline Drawing . . . . . . . . . . . . . . .2015Figure 2006. DMA-37B DME System Interwiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . .2023
Page TC-4Oct 8/0734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.List of TablesTable PageTable Intro-1. Data Verification. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-2Table 1. DMA-37B DME System Components (Honeywell Supplied). . . . . . . . . . . . . . . . . 4Table 2. Equipment Required but Not Supplied . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5Table 3. DMA-37B DME Interrogator Available Configurations. . . . . . . . . . . . . . . . . . . . . . 5Table 4. DMA-37B DME Interrogator Features . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6Table 5. Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7Table 6. Environmental Certification (066-50013-0101, -0202, and -0303 only) . . . . . . . . . 9Table 7. Environmental Certification (066-50013-1101 only). . . . . . . . . . . . . . . . . . . . . . . 10Table 8. Environmental Certification (066-50013-1212 only) . . . . . . . . . . . . . . . . . . . . . . 12Table 2001. DMA-37B Interrogator Connector Determinants . . . . . . . . . . . . . . . . . . . . . . . 2003Table 2002. Inspection/Check Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2009Table 2003. Table of Test Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2009
Page INTRO-110 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.INTRODUCTION1. How to Use This ManualA. General(1) The instructions in this manual give the data necessary to do all recommended maintenance functions to put the DMA-37B DME System in serviceable condition. The instructions in this manual do not give standard maintenance procedures that technicians must know.(2) Honeywell recommends that you do the tests in TESTING AND FAULT ISOLATION before you disassemble the unit. These tests can show the condition of the DMA-37B DME System or most possible cause of a malfunction. If a malfunction occurs, repair as necessary.(3) Warnings, cautions, and notes in this manual give the data that follows:• A WARNING gives a condition that, if you do not obey, can cause injury or death.• A CAUTION gives a condition that, if you do not obey, can cause damage to the equipment.• A NOTE gives data to make the work easier or gives direction to go to a procedure.(4) Warnings and cautions go before the applicable paragraph or step. Notes follow the applicable paragraph or step.(5) All personnel who operate equipment and do the specified maintenance must know and obey the safety precautions.B. Symbols(1) The symbols in Figure Intro-1 identify ESDS and moisture sensitive devices in this manual, if applicable.Figure Intro-1. SymbolsC. Weights and Measurements(1) All weights and measurements are in U.S. values and S.I. (metric) values. ESDS Moisture Sensitive
Page INTRO-210 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.2. Customer SupportA. Honeywell Aerospace Online Technical Publications Web Site(1) If you have access to the Internet, go to the Honeywell Online Technical Publications web site at http://portal.honeywell.com/wps/portal/aero/ to:• Download or see publications online• Make an order for a publication• Tell Honeywell of a possible data error in a publication.B. Complete Customer Care Center(1) If you do not have access to the the Honeywell Online Technical Publications web site, send an e-mail message or a fax, or speak to a person at the Complete Customer Care Center:• E-mail: cas-publications-distribution@honeywell.com• Fax: 602-822-7272• Phone: 1-800-601-3099 (U.S.A.)• Phone: 1-602-365-3099 (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. Data VerificationA. General(1) Verification of these technical instructions is done by performance or by simulation of the necessary procedures. Checks of the manual by the engineering staff make sure that the instructions and description data agree with the applicable engineering specifications and drawings and are accurate and sufficient. The dates of verification for this manual are as follows:(2) Honeywell will revise this manual as necessary to give current data. The sources for data supplied in this manual include engineering drawings and change orders released as of 28 Sep 2007.Table Intro-1. Data VerificationNumber Type DateTesting By performance 09 Oct 2007Fault Isolation By performance 09 Oct 2007Maintenance Practices By performance 09 Oct 2007
Page INTRO-310 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.4. ReferencesA. Honeywell Publications(1) The list that follows identifies Honeywell publications that are related to this manual:• ATA No. 34-51-35 (Pub. No. 1137A-3), CMM, DMA-37B DME Interrogator• ATA No. 34-51-36 (Pub. No. 1137A-4), CMM, DMA-37B DME Interrogator• ATA No. 34-51-37 (Pub. No. 012-0824-001), CMM, DMA-37B DME• ATA No. 34-51-38 (Pub. No. 012-0828-001), CMM, DMA-37B DME Interrogator• JcAIR Pub. No. TR-0762-05, DMA-37B DME Interrogator Test Procedure.NOTE: Order the DMA-37B DME Interrogator Test Procedure from JcAIR, Documentation Control Department, 400 New Century Parkway, New Century, KS 66031.B. Other Publications(1) These publications are standard references:• The United States Government Printing Office (GPO) Style Manual 2000 (available at http://www.gpoaccess.gov/stylemanual/browse.html)• ANSI/IEEE Std 260 (1978), Standard Letter Symbols for Units of Measurement (available from the American National Standards Institute, New York, NY)• ASME Y14.38-1999 (Formerly ASME Y1.1-1989), Abbreviations for Use on Drawings and in Text (available from the American National Standards Institute, New York, NY)• ANSI/IEEE Std 315-1975 (Replaces ANSI Y32.2-1975), Graphic Symbols for Electrical and Electronics Diagrams (available from the American National Standards Institute, New York, NY)• ANSI/IEEE Std 91 (1984), Graphic Symbols for Logic Functions (available from the American National Standards Institute, New York, NY)• H4/H8 Commercial and Government Entity (CAGE) Codes (available at http://www.dlis.dla.mil/cage_welcome.asp).
Page INTRO-410 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.5. Acronyms and AbbreviationsA. General(1) Refer to the list that follows for acronyms and abbreviations in this manual. List of Acronyms and AbbreviationsTerm Full TermAF audio frequencyANSI American National Standards InstituteARINC Aeronautical Radio, IncorporatedASME American Society of Mechanical EngineersATC air traffic controlBCD binary coded decimalBITE built-in test equipmentCAGE Commercial and Government EntityCFDIU centralized fault display interface unitCFDS central fault display systemCMC central maintenance computerCPU central processor unitCW continuous waveDITS digital information transfer systemDME data measuring equipmentDSP digital signal processorECCN export control classification numberEUROCAE European Organisation for Civil Aviation EquipmentESD electrostatic dischargeESDS electrostatic discharge sensitiveFPGA field-programmable gate arrayFPLA field-programmable logic arrayGPO Government Printing OfficeHIRF high intensity radiation fieldsHPN Honeywell part number
Page INTRO-510 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.I/O input/outputIEEE Institute of Electrical and Electronics EngineersLCD liquid crystal displayLRU line replaceable unitMOPS minimum operational performance standardsNCD no-computed-dataNo. numberPCMCIA Personal Computer Memory Card International AssociationRF radio frequencyRTCA Radio Technical Commission for AeronauticsSDI source/destination identifierSSM sign status matrixStd standardTACAN tactical air navigationTCAS traffic alert and collision avoidance systemTSO technical standard orderVFR visual flight rulesVHF very high frequencyVOR VHF omnirangeVORTAC VHF omnirange tactical air navigationU.S.A. United States of AmericaList of Acronyms and Abbreviations (cont)Term Full Term
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Page 110 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.DESCRIPTION AND OPERATION1. GeneralA. Description(1) This section contains descriptive information covering the DMA-37B DME System and lists other components required for system operation. The DMA-37B DME Interrogator is illustrated in Figure 1 and Figure 2.Figure 1. DMA-37B DME Interrogator, 066-50013-0101, -0202, and -0303
Page 210 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 2. DMA-37B DME Interrogator, 066-50013-1101 and -1212
Page 310 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.B. Purpose of Equipment(1) The DMA-37B DME System is designed to provide the flight crew with accurate slant-range distance information in digital format as measured from the aircraft to a selected ground-based DME transponder. Depending upon the DME display, DMA-37B adds ground speed and time for the aircraft to reach the selected ground-base station at the current velocity can be derived from the slant-range.(2) A DME is co-located at ground-based VHF Omnirange Distance Measuring Equipment (VOR-DME) and VHF Omnirange Tactical Air Navigation (VORTAC) stations. The DMA-37B is capable of receiving the distance measurement from military Tactical Air Navigation (TACAN) stations. A few DMEs are co-located with ILS systems presenting distance and aircraft speed to the runway as the aircraft approaches for landing.(3) DME is used in conjunction with a primary navigation source, like VOR, to measure distance along a route of flight toward the VORTAC station. For some instrument approaches, it is used with VOR to fly where a DME arc or VOR-DME equipment is required for approach.(4) The DMA-37B DME Interrogator is a very powerful scanning DME. In addition to stations selected by the crew, it searches automatically for up to five stations within a 300-nautical mile range.(5) The operating range of the DMA-37B DME System is zero to 300 nautical miles. The DMA-37B DME System consists of an airborne DMA-37B DME Interrogator, a mount, a DME indicator, and an antenna.(6) The DMA-37B DME Interrogator design conforms to industry standards Aeronautical Radio Incorporated (ARINC) 709-8 Airborne Distance Measuring Equipment, Radio Technical Commission for Aeronautics (RTCA) document number DO-189 Minimum Operational Performance Standards (MOPS) for Airborne Distance Measuring Equipment (DME), and European Organisation for Civil Aviation Equipment (EUROCAE) ED-54 Minimum Operational Performance Requirements for Distance Measuring Equipment Interrogator, and digital guidance data conforms to ARINC 429-14 Mark 33 Digital Information Transfer System (DITS) format.(7) The DMA-37B DME Interrogator is fully interchangeable with the earlier ARINC 709 DMA-37A DME Interrogator for backward compatibility.(8) In addition, the DMA-37B provides fast scan and digital Morse Code decoding outputs, fault memory, and built-in test equipment (BITE) interfaces for use in a Central Maintenance Computer (CMC) in accordance with ARINC 604 to transfer maintenance data or in a Central Fault Display System (CFDS) in accordance with ARINC 604, and Airbus Industrie ABDO048C or McDonnell Douglas software requirements.C. Equipment Part Numbers(1) Components of the DMA-37B DME System supplied by Honeywell are listed in Table 1. Table 1 lists the currently available components of the system, along with part numbers and equipment type numbers.
Page 410 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Table 1. DMA-37B DME System Components (Honeywell Supplied)Equipment Type Number Equipment Description Part NumberDMA-37B DME InterrogatorA microprocessor-based distance measuring equipment used to determine the slant-range distance as measured from the aircraft to a selected ground-based DME transponder. Derived distance information is made available for visual display to the pilot, and for use by an automatic flight control system.Design conforms to ARINC 809-8 and EUROCAE ED-54; digital guidance data output ports (binary digital distance, BCD digital distance, station identification and BCD channel selected) conforms to ARINC 429 format; two digital input ports for frequency/function select data input and source select capability operate in accordance with ARINC 429.In addition to the automatic self-test feature, the unit contains an loperator-initiated self-test feature, located on the DMA-37B front panel, that provides a comprehensive test of all sections of the unit and operation of its outputs.Complies with DO-178B software requirements and enhanced BITE requirements of Airbus, Boeing, and McDonnell Douglas. Capable of interfacing CMC in accordance with ARINC 604.Capable of data recording and loading through the front of the unit.Meets D0-160C lightning protection and 200 ms power interrupt transparency requirements.Meets HIRF requirements and ICAO Annex 10 requirements.Valid station identification is output for the Ident channel only, BCD distance is output for all foreground channels (only the Display Channel is valid) and output label 035 has its sign status matrix (SSM) set to NORMAL in the standby mode.066-50013-0101Same as -0101, except valid station identification is output for all foreground channels simultaneously (multichannel Ident), BCD distance is output only for the Display Channel (unless no Display Channel is selected) and output label 035 has its SSM set to no-computed-data (NCD) in the standby mode.Capable of interfacing CFDS in accordance with ARINC 604 and Airbus Industrie ABDO048C.066-50013-0202Same as -0202 except capable of interfacing CFDS in accordance to McDonnell Douglas software requirements (replaces ABDO048C implementation).066-50013-0303Same as the -0101 except upgraded to DO-160E configuration. Unit also upgraded with variable frequency capability with harmonic correction for input power. Front panel consists of easy to use LED fault and status indicators in place of LCD display.066-50013-1101Same as the -0202 except upgraded to DO-160E configuration. Unit also upgraded with variable frequency capability with harmonic correction for input power. Front panel consists of easy-to-use LED fault and status indicators in place of LCD display. In addition, the ARINC 429 capability has been upgraded to have a burst mode capability.066-50013-1212
Page 510 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.D. Equipment Required but Not Supplied(1) Table 2 lists equipment required for the RVA-36B VOR/Marker System, but not supplied by Honeywell.E. Configurations Available(1) Table 3 lists the available configurations of the DMA-37B and the features contained in each configuration. Table 4 contains a brief description of each feature.Table 2. Equipment Required but Not SuppliedEquipment DescriptionPower Source AC power supply of 115 V, 400 Hz as defined by Radio Technical Commission for Aeronautics, Inc. (RTCA) D0-160C. The -1101 and 1212 are rated for DO-160E variable frequency operation with harmonic content correction.NAV Control Panel DME frequency automatically paired with NAV frequency. Must provide remote control of frequency selection in serial digital ARINC 429 format, power on-off, and self-test in ARINC 429 format.Distance Indicator A display which indicates distance to the selected DME ground station. Communication with DMA-37B is on an ARINC 429 data bus.Audio Distribution System Audio system with an input impedance of 200 to 10,000 ohms.DME Antenna L-Band, vertically polarized antenna capable of receiving DME signals over a frequency range of 962.00 MHz to 1213.00 MHz, and capable of transmitting DME signals over a frequency range of 1025 MHz to 1150 MHz.4 MCU Unit Mount Interrogator in the aircraft. Designed in accordance with ARINC 600. Mount connector will allow mating of DMA-37B low-insertion force, size 2, ARINC 600 connector with three inserts. The middle insert will be used for aircraft interconnections. The bottom insert will be used for input power. The middle insert is also used for coaxial antenna connections. Keying pins will be indexed to pin code 03.Cooling Source Aircraft supplied ARINC 600 forced-air cooling is required for the DMA-37B.Cable and Connectors Necessary connectors, power cables, RF cables, and aircraft interwiring are shown in DMA-37B DME System Interwiring Diagram, Figure 2006.Table 3. DMA-37B DME Interrogator Available ConfigurationsHPNFeaturesBasic Unit Fault MemoryInterfaceBoeing CMC Airbus CFDSMcDonnell Douglas CFDS066-50013-0101 X X X066-50013-0202 X X X066-50013-0303 X X X066-50013-1101 X X X066-50013-1212 X X X
Page 610 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Table 4. DMA-37B DME Interrogator Features Feature DescriptionBasic Unit A microprocessor-based distance measuring equipment used to determine the slant-range distance as measured from the aircraft to a selected ground-based DMEtransponder. Derived distance information is made available for visual display to the pilot, and for use by an automatic flight control system.Design conforms to ARINC 709-8 and EUROCAE ED-54; digital guidance data output ports (binary digital distance, BCD digital distance and BCD channel selected) conforms to ARINC 429 format; two digital input ports for frequency/function select data input and source select capability operate in accordance with ARINC 429.In addition to the automatic self-test feature, the unit contains an operator-initiated self-test feature, located on the DMA-37B front panel, that provides a comprehensive test of all sections of the unit and operation of its outputs.The -1101 and -1212 units feature LEDs. The other dash numbers have an LCD display.Complies with DO-178B software requirements and enhanced BITE requirements of Airbus, Boeing, and McDonnell Douglas.With the exclusion of -1101 and -1212 the remaining dash numbers are capable of data recording and loading through the front of the unit.Meets D0-160C lightning protection and 200 ms power interrupt transparency requirements. The -1101 and -1212 units are also rated for DO-160E operation.Meets HIRF requirements and ICAO Annex 10 requirements.Fault Memory A nonvolatile, single-chip fault memory that allows the recording of faults associated with a particular flight leg. Sixty-four flight legs are available with each flight leg made up of a flight-leg information header containing a fault record section for recordingten airborne faults and three ground faults. When all flight legs have been used, the oldest flight leg is reused.CMC Interface The DMA-37B interfaces fault memory and BITE data between DME Interrogator and line maintenance Centralized Maintenance Computer (CMC) for the purpose of extracting maintenance information and initiating tests. Designed to conform with ARINC 429 interfaces and ARINC 604.CFDS Interface The DMA-37B interfaces fault memory and BITE data between DME Interrogator and line maintenance Centralized Fault Display Interface Unit (CFDIU) for the purpose of extracting maintenance information and initiating tests. Designed to conform with ARINC 429 interfaces, ARINC 604 and Airbus Industrie ABDO048C or McDonnell Douglas software requirementsDigital Morse Code Provides capability of receiving ground-facility digital Morse Code Ident signals and decoding them to ARINC 429 data word format for use on the DME Interrogator system ARINC 429 data output bus.Multichannel Ident Valid station identification is output for all foreground channels simultaneously, BCD distance is output only for the display channel (unless no display channel is selected), and output label 035 has its SSM set to NCD in standby mode; otherwise, without multichannel ident, valid station identification is output for the Ident channel only, BCD distance is output for all foreground channels (only the display channel is valid), and output label 035 has its SSM set to NORMAL in standby mode.
Page 710 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.2. System Leading ParticularsA. Unit Specifications(1) Table 5 lists the leading particulars for the DMA-37B DME System.Table 5. Leading ParticularsCharacteristics DescriptionGeneralPower Requirements 115 V ac, 380 to 420 Hz, 22 W (-0101, -0202, and -0303 only)115 V ac, 360 to 800 Hz, 25 W (-1101 and -1212 only)Weight 9.8 lb (4,45 kg)Dimensions See Figure 2005.Form Factor ARINC 600 4 MCUCooling ARINC 600 forced airTemperature• Operating -67 to +158 °F (-55 to +70 °C) for -0101, -0202, and -0303 only+5 to +158 °F (-15 to +70 °C) for -1101 and -1212 only• Storage -85 to +158 °F (-65 to +85 °C)Humidity Zero to 95% Relative HumidityWarm-up period Stable operation within one minute after application of powerFrequency Selection Serial digital in accordance with ARINC 429Range Zero to 300 Nautical MilesAltitude 50,000 feet above mean sea levelVelocity Zero to 1000 KnotsSelf Test Continuous, automatic; Manual from discrete ARINC 429, CMC, or Front PanelIntegrity Monitoring Continuous self-monitoringFault Reporting ARINC 429 and ABD 0048B Centralized Maintenance InterfacesData Outputs ARINC 429 Distance and CMC InterfaceCertification• -0101, -0202, and -0303 TSO C66cDO-160C Environmental Category/A2D2/ZCA/MNB/XXXXXXAEAEZUZ/XXE2/XXICAO Annex 10 FM ImmunityDO-189, DO-178B•-1101 TSO C66cDO-160E Environmental Category[(A2)(B2)V]BAB[SB]XXXXXXAA(WF)XA[R(WF)][ZW]RRRL[ZZZZ]XXACICAO Annex 10 FM ImmunityDO-189, DO-178B
Page 810 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.• -1212 TSO C66cDO-160E Environmental Category[(A2)(D2)Z]BAB[SB]XXXXXXAA(WF)HA[R(WF)][ZW]R[RR]L[ZZZZ]XXACICAO Annex 10 FM ImmunityDO-189, DO-178BTransmitterFrequency Range 1025.00 MHz to 1150.00 MHz, 1MHz channel spacingFrequency Stability ± 80 kHzPower Output 700 Watts, TypicalPulse Code Spacing• X-Channel 12.0 ± 0.4 microseconds• Y-Channel 36.0 ± 0.4 microsecondsFrequency Spectrum 90% of total pulse energy within ± 0.25 MHz of channel frequencyRise Time (maximum) 2.8 Microseconds (consistent with pulse spectrum)CW Leakage at Antenna Connector-79 dBm maximumAntenna Mismatch No damage to transmitter with antenna open or short circuitReceiverFrequency 962.00 MHz to 1213 MHz (252 Channels)Sensitivity -90 dBm minimum lock-on levelSelectivityDynamic Range 80 dB minimumImage Rejection 60 dB minimumCW Rejection 60 dB minimumAudio Output Capable of 40 milliwatts minimum into a 200-ohm to 10,000 ohm resistive load with -87 dBm input signal level.Harmonic Distortion Less than 15% with 1000 microvolts modulated 30% at 1000 Hz and less than 20% with 90% modulation for rated audio output into a 200-ohm to 600-ohm resistive loadAudio Output Regulation Less than 6-dB voltage change from a 25-milliwatt reference level into 200 ohms for resistive load variations of 200 ohms to 10,000 ohmsLess than 0.31-dB voltage change from a 40-milliwatt level into 600-ohm reference for resistive load variations of 453 ohms to 2400 ohms.Table 5. Leading Particulars (cont)Characteristics DescriptionAttenuation BandwidthLess than 6 dB 95 kHzMore than 50 dB ±800 kHz
Page 910 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.B. Environmental Certification (066-50013-0101, -0202, and -0303 only)(1) The DMA-37B DME Interrogator meets the environmental conditions of the Radio Technical Commission for Aeronautics (RTCA) document number D0-160C, Environmental Conditions and Test Procedures for Airline Electronic/Electrical Equipment and Instruments (refer to Table 6). The environmental certification categories of the DMA-37B are /A2D2/ZCA/MNB/XXXXXXAEAEZUZ/XXE2/XX (refer to Table 6).Audio Noise Level Greater than 30 dB below audio reference level.Digital Range Output Distance available in fractional binary format and BCD format in accordance with ARINC 709 and ARINC 429 standards.Warning Signals Digital warning signals provided in accordance with ARINC 709 and ARINC 429 standardsDistance AccuracyTable 6. Environmental Certification (066-50013-0101, -0202, and -0303 only)Test CategoryTemperature and Altitude A2D2In-Flight Loss of Cooling ZTemperature Variation CHumidity AOperational Shocks and Crash Safety Operational ShockVibration MNBExplosion Proofness XWaterproofness XFluids Susceptibility XSand and Dust XFungus Resistance XSalt Spray XMagnetic Effect APower Input EVoltage Spike ATable 5. Leading Particulars (cont)Characteristics DescriptionSignal Level AccuracyLock-on to -80 dBm 0.2 NMLock-on from -80 to -10 dB 0.1 NM
Page 1010 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.C. Environmental Certification (066-50013-1101 only)(1) The DMA-37B DME Interrogator meets environmental conditions of RTCA document number DO-160E In addition to several Boeing Specific requirements (refer to Table 7). The environmental certification categories for the -1101 DMA-37B DME Interrogator are [(A2)(B2)V]BAB[SB]XXXXXXAA(WF)XA[R(WF)][ZW]RRRL[ZZZZ]XXAC (refer to Table 7).Audio Frequency Conducted Susceptibility - Power InputsEInduced Signal Susceptibility ZRadio Frequency Susceptibility(Radiated and Conducted)UEmission of Radio Frequency Energy ZLightning-Induced Transient Susceptibility XXE2Lightning-Direct Effects XIcing XTable 7. Environmental Certification (066-50013-1101 only)Test CategoryGround Survival Low Temperature A2 Short Term Operating Low Temperature A2 Operating Low Temperature A2 Ground Survival High Temperature A2 Short Term Operating High Temperature A2 Operating High Temperature A2 In-Flight Loss of Cooling V Altitude B2 Decompression A2 Overpressure A2 Temperature Variation B Humidity A Acceleration XVibration Due to Fan Blade Loss (Windmilling) XBench Handling Shock XShipping Container XOperational Shock (Emergency Landing and Bird Strike) B Table 6. Environmental Certification (066-50013-0101, -0202, and -0303 only) (cont)Test Category
Page 1110 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Vibration S Explosive Atmosphere N/A Waterproofness N/A Fluids Susceptibility N/A Sand and Dust N/A Fungus Resistance N/A Salt Fog N/A Magnetic Effect A Power Input A(WF) Voltage Spikes A Voltage Waveform - Individual Harmonic Content (AF Conducted Susceptibility) R(WF) AF Magnetic Field Susceptibility – Equipment ZW AF Magnetic Field Susceptibility – Wiring ZW AF Electric Field Susceptibility – Wiring ZW Spikes Induced into Interconnecting Cables ZW Radio Frequency Conducted Susceptibility R Radio Frequency Radiated Susceptibility R Certification HIRF Environment I by Direct Injection Method XAF Conducted Emissions, AF Capacitive Coupling XAF Conducted Emissions, AF Inductive Coupling XRF Conducted Emissions (Narrowband) M RF Conducted Emissions (Broadband) XRF Radiated Emissions (Narrowband) M RF Radiated Emissions (Broadband) XLightning-Induced Transient Susceptibility, Pin Injected ZZZZZ Lightning-Induced Transient Susceptibility, Cable Injected ZZZZZ Lightning-Induced Transient Susceptibility, Ground Injected ZZZZZ Lightning-Induced Transient Susceptibility, Multiple Burst XLightning Direct Effects N/A Icing N/A Electrostatic Discharge (ESD) A Fire, Flammability C Table 7. Environmental Certification (066-50013-1101 only) (cont)Test Category
Page 1210 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.D. Environmental Certification (066-50013-1212 only)(1) The DMA-37B DME Interrogator meets environmental conditions of RTCA document number DO-160E In addition to several Boeing Specific requirements (refer to Table 8). The environmental certification categories for the -1212 DMA-37B DME Interrogator are [(A2)(D2)Z]BAB[SB]XXXXXXAA(WF)HA[R(WF)][ZW]R[RR]L[ZZZZ]XXAC (refer to Table 8).Table 8. Environmental Certification (066-50013-1212 only)Test CategoryTemperature Test A2 In-Flight Loss of Cooling Z Temperature Variation B Altitude Test D2 Decompression Test A2 Overpressure Test A2 Humidity A Operational Shock And Crash Safety B Vibration S Vibration Due to Fan Blade Loss (Windmilling) XVibration: Due to Landing Gear Tyre Burst XExplosive Atmosphere XWaterproofness XFluids Susceptibility XSand and Dust XFungus Resistance XSalt Fog XMagnetic Effect A Power Input A (WF) Voltage Spike A Audio Frequency Conducted Susceptibility R(WF) AF Electric Field Susceptibility – Wiring ZW AF Magnetic Field Susceptibility – Wiring ZW AF Magnetic Field Susceptibility – Equipment ZW Spikes Induced into Interconnecting Cables ZW Radio Frequency Conducted Susceptibility R Radio Frequency Radiated Susceptibility R
Page 1310 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.3. System DescriptionA. General(1) The DMA-37B DME System is an airborne distance measuring system which determines the slant-range distance from an aircraft to a selected ground based DME transponder (see Figure 3). The DMA-37B DME Interrogator transmits a pulse-pair signal on any one of 126 frequencies within the range of 1025 MHz to 1150 MHz. One hundred of the DMA-37B transmit frequencies are automatically selected by tuning the NAV control to a frequency between 108.00 and 117.95 MHz. The other 26 frequencies can be selected by tuning the NAV control to frequencies between 133.30 and 135.95 MHz, these channels are normally used for military TACAN stations. The data loader and data recorder capability in Figure 3 are used in the -0101, -0202, -0303 only(2) The signals transmitted by the airborne DMA-37B are received by the ground station assigned to the selected channel frequency. After a built-in delay of 50 microseconds, a reply pulse-pair is automatically transmitted on the channel frequency assigned to the ground station. There are 252 channels within the frequency band of 962 to 1213 MHz set aside for DME ground stations.(3) The DMA-37B receives the response to the interrogations and processes these signals to determine the precise amount of time that has elapsed between transmission of a pulse pair and reception of the response. The DMA-37B computes the slant-range distance by subtracting the 50 microsecond delay and dividing the result by 12.359 microseconds (time required for DME signal to travel to and return from a DME ground station that is one mile away). The distance is computed every time a pulse pair response is received from the ground station.(4) An operator initiated self-test feature is also included in theDMA-37B. The self-test is initiated by pressing the TEST pushbutton on the front panel of the DMA-37B. There are one or more additional means of initiating the self test; these switches can be located on the DME tuning source, DME indicator, or an EFIS (electronic flight instrument system) indicator.RF Conducted Emissions (Narrowband) L RF Radiated Emissions (Narrowband) L Lightning-Induced Transient Susceptibility, Pin Injected ZZZZZ Lightning-Induced Transient Susceptibility, Multiple Pulse (Burst) ZZZZZ Lightning-Induced Transient Susceptibility, Multiple Stroke ZZZZZ Lightning Direct Effects XIcing XESD Susceptibility A Fire, Flammability C Table 8. Environmental Certification (066-50013-1212 only) (cont)Test Category
Page 1410 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 3. DMA-37B DMA System(5) An automatic self-test feature is also built into the DMA-37B. This test is controlled by the microprocessor program. Approximately once every 1.5 seconds the program automatically instructs the unit to go into self test. The results of the test are monitored and compared against information stored in memory. If any results of the test indicate a malfunction, a DME invalid flag is generated and routed to DME distance users through the ARINC 429 output.(6) The DME ground station transmits a station-identification signal along with the other data. The DMA-37B detects the station-identification signal and applies it to the aircraft audio system. (7) The DMA-37B generates a suppression pulse for internal use and also makes the pulse available at the rear connector of the unit. The pulse can be used to suppress other receivers when DME interrogation pulses are being transmitted. The DMA-37B can also receive suppression pulses from external equipment on the mutual suppression line.
Page 1510 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.4. System Component DescriptionA. DMA-37B DME Interrogator(1) The DMA-37B DME Interrogator is packaged in an ARINC 600 Characteristic, 4 MCU standard form factor case. It contains the electronics required to transmit and receive the pulse modulated L-band signal required by the ground station transponder and to interface with the aircraft systems.(2) The basic -0101, -0202, and -0303 DMA-37B consists of a RF module, a synthesizer/modulator module, a video processor module, CPU-I/O module, power supply assembly, HIRF/rear interconnect assembly, front panel assembly, and memory card interface module (see Figure 4).(3) The basic -1101 and -1212 DMA-37B consists of a RF assembly, an integrated video main processor assembly, a variable frequency power factor corrected power supply assembly, a rear interconnect assembly containing lightning protection, and a front panel assembly (see Figure 4).(4) The DMA-37B uses a low insertion force, size two shell, ARINC 600 rear panel connector with three inserts. The top insert is not used. The middle insert is used for aircraft interconnections and coaxial antenna connector, and the bottom insert is used for input power and suppression coaxial connectors. The keying pins are set to index pin code 03.(5) Forced air cooling, in accordance with ARINC specification 600, is required for cooling the DMA-37B. (6) Data interfaces to the aircraft systems are through slow-speed ARINC 429 ports.(7) A variety of discrete and strap pins provide additional information to and from the DME.(8) The -0101, -0202, and -0303 front panel display provides an interface to an operator with a liquid crystal display (LCD) that is visible from the front of the DMA-37B to display messages in simple language in one of four modes: normal operation, BITE display, maintenance, and software loading.(9) Software loading and data recording to/from the CPU is through the front panel Personal Computer Memory Card International Association (PCMCIA) slot. Intel Series 2 Flash Cards with capabilities ranging from 1, 2, or 4 megabytes are supported.(10) Intel Series 2 Flash Cards with capabilities ranging from 4, 10, and 20 megabytes (up to 64 megabytes, when available) are also supported.(11) Two pushbutton switches allow operator interface with the DMA-37B LCD.(12) In normal operation, the front panel LCD displays the unit's characteristics: unit identification, part number, and serial number (-0101, -0202, and -0303 only). The BITE display mode is activated after manual self-test has been exercised either from the front panel test pushbutton or remotely. In the BITE mode, BITE status is reported and, in the event of a detected failure, additional help screens are provided to locate the detected failure to a module. BITE help pages are provided. In the maintenance mode, a set of maintenance words are displayed and decoded showing the names of data fields and the value of the data. Maintenance help pages are provided. For loading software, a series of screens direct the operator during the data loading process. Software version and loading status are provided during the update process.(13) The -1101 and -1212 front panel assembly consists of three easy to see LED indicators that display the status of the unit.B. Other Components in the System(1) Other DMA-37B DME System components are not supplied by Honeywell. Information on these units must be obtained from their respective manufacturers.
Page 1610 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.NOTE: In the -1101 and -1212 units, the synthesizer modulator is included in the RF module. In addition,the video processor module is included in the CPU/IO module.Figure 4. DMA-37B DME Interrogator Simplified Block Diagram
Page 1710 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.5. OperationA. General(1) The DMA-37B DME Interrogator transmits a pair of pulses through the antenna on one frequency and waits for a ground station reply on a frequency offset by 63 MHz. The ground station replies to this interrogation 50 microseconds later, somewhat like a delayed radar reflection.(2) The 50-microsecond delay allows completion of the interrogation. If not delayed at close ranges, the returned signal would come back to the receiver before the transmitted pulses have left the aircraft antenna. When a DME unit measures 50 microseconds from transmit time until the beginning of the received pulse, the aircraft is at 0.0 mile range.(3) Like radar, the unit calculates the distance from the station based on speed of the transmitted pulses through the air, divided by time. Speed of signal propagation equals one nautical mile per 12.369 microseconds.(4) Each DME unit must distinguish its own pulse return from other DME returns or squitters (unsolicited replies emitted by the ground station). To do this, reply/squitter distances from multiple interrogations are saved and compared to determine actual reply distance to the ground station. The DME is capable of simultaneously maintaining track of up to five different ground stations that are tuned by a Flight Management System.B. Basic Theory(1) RF Module(a) This module consists of a single PC board that is mounted in a closed aluminum chassis. It contains the transmitter, receiver, circulator and a low-pass filter.(b) The solid-state transmitter contains a six-stage amplifier followed by a 700 W (typical) final amplifier. The pulse modulation is applied to the first six stages of amplification. It is tuned to frequencies in the range 1025 to 1150 MHz.(c) The single-conversion superheterodyne receiver consists of a varactor tuned preselector, 1-GHz preamplifier, mixer, SAW band-pass filters, and a 63-MHz logarithmic IF amplifier. The preselector is tuned to frequencies in the 962 to 1213 MHz range.(d) The circulator routes the transmitter output to the antenna and the antenna received signal to the receiver. It provides isolation to protect the transmitter output amplifier devices from reflected signals due to high VSWR conditions.(e) The low-pass filter prevents internal transmitter harmonics from being passed to the antenna.(2) Synthesizer/Modulator AssemblyNOTE: On the -1101 and -1212 units, the synthesizer/modulator assembly has been combined into the RF assembly.(a) This module contains the digital frequency synthesizer and transmitter modulator circuits.(b) The digital frequency synthesizer supplies an RF signal used both as the local oscillator input to the receiver mixer and as the low-level CW signal into the transmitter. This circuit consists of a phase-locked loop and VCO which is tuned to the desired channel frequency by a serial tuning word supplied by the video processor module.
Page 1810 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.(c) The modulator supplies the on/off signal that corresponds to the X or Y pulse pairs associated with the channel frequency. An interrogation is transmitted by triggering the series of on/off modulation to control the transmitter amplifier stages that drive the final amplifier.(3) Main Processor (CPU and I/O) AssemblyNOTE: On the -1101 and -1212, units the the main processor function and video processor function have been combined on one module.(a) This module contains the CPU that executes the signal processing using an 80486SX microprocessor.(b) It also contains the I/O section consisting of ARINC 429 transmitters and receivers, and discrete I/O logic to provide the interfaces with other aircraft systems, including the Central Maintenance Computer (CMC) and displays.(c) ARINC 429 inputs and outputs are processed by a specially designed ARINC 429 LSI transceiver device. External level converters are used to satisfy the ARINC 429 characteristics for the transmitters and convert input ARINC 429 signals to logic levels.(d) All discrete inputs and outputs external to the DME are processed by discrete components to provide level shifting and latching.(e) The following types of devices are employed:• Digital-to-analog converter devices to generate control and test signals• Field Programmable Logic Array (FPLA) devices to accept, decode and generate discrete signals• Memory devices (bootstrap, program, nonvolatile, and data)• Data recorder interface• Front panel display driver• RS-232 interface• Clock generators.
Page 1910 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.(4) Video Processor(a) This module contains a field programmable gate array (FPGA) which is the control center for the video processor. The video processor provides the following operations:• Converts tuning commands from CPU to serial data to tune the transmit/receive frequency synthesizer• Generates the corresponding receiver preselector tuning voltage• Generates the corresponding X or Y pulse modulation for the interrogation• Generates the output mutual suppression pulse for an interrogation• Detects the input mutual suppression pulse and inhibits reception and video processing• Determines the log IF noise threshold setting• Starts the range (distance) counter when an interrogation is transmitted• Digitizes the video signals from the receiver log IF amplifier• Validates the amplitude, spacing, and width of the digitized video pulse pairs• Stores the range counter value in a FIFO when each valid pulse pair is decoded• Analog-to-digital converter devices to process the received signals and BITE test point voltages• Generates the audio tone for the Morse code station identity aural output• Provides for integrity testing.(5) Power Supply Assembly(a) This module is a self-contained, high-efficiency power supply that converts the 115 V ac, 400 Hz AC power into the required DC operating voltages. It includes an EMI filter to reduce electromagnetic interference from being radiated from the power lines.(b) The power supply for the -1101 and -1212 units can operate in accordance with the DO-160E VF 360 Hz to 800 Hz mode and has harmonic content (power factor) correction.(6) HIRF/Rear Interconnect(a) The rear connector assembly provides the interwiring from the aircraft interface to the internal modules. A combination of series resistors, transorb devices, and ferrite pin filters provide HIRF and lightning protection.(b) For the -0101, -0202, and -0303 units only, to prevent High Intensity Radiation Fields (HIRF) or lightning from affecting operation by entering through rear connector cables, an HIRF compartment is formed in the rear of the DMA-37B. The signal and power cables are filtered by using discrete and distributed filter elements and limiting devices on the rear interconnect module located inside this HIRF compartment. The filtered lines are then fed to the appropriate points in the DMA-37B. The DMA-37B is packaged in an aluminum casting. This seamless main frame ensures HIRF cannot enter the unit through structural seams. The slots formed by the removable side covers are sealed against HIRF with protective gaskets and metal covers.
Page 2010 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.(7) Front Panel Display Module, -0101, -0202, and -0303 Only(a) The front panel display module is mounted behind the front panel and provides an interface to an operator through a low-power liquid crystal display (LCD) that is visible from the front of the DMA-37B. In addition to the LCD, the module contains Light Pipe back lighting, temperature compensation circuitry, and a PC board containing an associated LCD driver, two pushbutton switches used to enter functional test and to control the display menus, and a D-sub, nine-pin, RS-232 serial type connector.(b) The RS-232 front panel connector is used for testing the DMA-37B through a compatible test set or test panel.(c) The LCD is a bit-mapped display capable of displaying alphanumeric and graphical symbols. Simple messages written in plain language minimize the potential for misunderstanding or incorrect interpretation. The LCD displays the following:• Part Number/Software Identification•Status• Results of Level i BITE Tests• Maintenance Help Pages• Shop Maintenance Data• Flight Fault Memory Contents• Software Loading Status• Capable of Customizing for Airline Unique Maintenance Messages.(d) The memory card interface module is used to load software program data into the CPU or record data from the CPU. The memory card interface module supports Series 2 FLASH cards through the front panel Personal Computer Memory Card International Association (PCMCIA) slot. Intel Series 2 cards with capabilities ranging from 4, 10, and 20 megabytes (up to 64 megabytes, when available) are all supported. The FLASH card is inserted through the front panel. In one mode, data stored on the flash card memory module is used to update program or data memory in the DME Interrogator. In another mode, the flash card memory module functions as a data recorder for the software program stored in the CPU.(8) Front Panel Display Module, -1101 and -1212 Only(a) The front panel display module for the -1101 and -1212 units contain LEDs to indicate unit operational status and a push button to initiate self test. In addition there is a 25 pin D connector for a sperate tester interface.(9) Memory Card Interface Module, -0101, -0202, and -0303 Only(a) The memory card interface module is used to load software program data into the CPU or record data from the CPU. The memory card interface module supports Series 2 FLASH cards through the front panel Personal Computer Memory Card International Association (PCMCIA) slot. Intel Series 2 cards with capabilities ranging from 4, 10, and 20 megabytes (up to 64 megabytes, when available) are all supported. The FLASH card is inserted through the front panel. In one mode, data stored on the flash card memory module is used to update program or data memory in the DME Interrogator. In another mode, the flash card memory module functions as a data recorder for the software program stored in the CPU.
Page 100110 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.FAULT ISOLATION1. GeneralA. Description for -0101, -0202, and -0303 Only(1) Fault isolation is the process of isolating the source of a system failure to an LRU (line replaceable unit) or to the aircraft wiring.(2) For the -1101 and -1212 units, the front panel display indicates the status of the unit. The top LED shows the internal status and shows RED with an internal fault. The center LED is normally off and when displaying RED indicates an external failure with either the ARINC 429 inputs or unit strapping. The bottom LED shows RED if there is a problem with the antenna connection. A separate connector on the units can be used with an adapter to show the indications and functionality described below with the LCD functions. The LEDs show amber during the self test function described in the following procedure.(3) Fault isolation in the DMA-37B DME System includes a continuity check of the interwiring, and the assurance that proper installation techniques and procedures have been followed.(4) A functional self test of the LRU can be initiated by pressing the test key pushbutton switch as designated on the front panel LCD, see Figure 1001. Although the normal-mode screen indicates that this actuated from the right key, the left key has the same function if pressed while the DMA-37B is in its normal mode.(5) A complete functional test of the system can be performed as described in the MAINTENANCE PRACTICES section of this manual.(6) Figure 1002 illustrates the control flow of the LCD screens (except for the data loading and data recording screens).Figure 1001. Typical Normal Mode Screen
Page 100210 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 1002. LCD Control Flow
Page 100310 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.B. Selt-Test Mode for -0101, -0202, and -0303 Only(1) The self-test mode starts by displaying the Test in Progress screen, see Figure 1003, one second after pressing the test key. This is displayed for four seconds with a moving thermometer along the bottom of the LCD indicating the progress of the test from one to five seconds.Figure 1003. Test in Progress Screen(2) The Normal Mode screen (Figure 1001) is displayed for the first second of the test sequence.(3) Once complete, the Test Complete, No Failures screen is displayed (Figure 1004), or the Test Complete, Failures screen is displayed (Figure 1005). Both screens contain two key selections each: MAINT and RETURN or MAINT and WHY?, respectively.• MAINT For both screens, MAINT is located on the left key. This allows the initiation of the extended maintenance pages of the system for troubleshooting. Refer to Paragraph D.• RETURN In the Test Complete, No Failures screen, the RETURN key to the right returns the system to its normal mode screen (Figure 1001).• WHY? In the Test Complete, Failures screen, the WHY? key to the right puts the system into the display-failures mode where individual system failures are displayed one on each page. Refer to Paragraph C.(4) While in the self-test mode, not pressing either key for five minutes causes the system to return to the Normal Mode screen (Figure 1001).
Page 100410 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 1004. Test Complete, No Failures ScreenFigure 1005. Test Complete, Failures Screen
Page 100510 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.C. Display-Failures Mode for -0101, -0202, and -0303 Only(1) One of three failure possibilities exist: the DMA-37B is okay, but there are external failures (Figure 1006), the DMA-37B failed and there are external failures (Figure 1007), and the DMA-37B failed, but there are no external failures (Figure 1008).Figure 1006. DME Receiver OK, External Failures Present ScreenFigure 1007. DME Receiver Failed, External Failures Also Present Screen
Page 100610 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 1008. DME Receiver Failed, External Failures Not Present Screen(2) All Display-Failures Mode screens have the MORE selection on the right key. The only exception is when there is only one failure page. This only happens when the DMA-37B itself has failed and no other external failure exists Figure 1008).• MORE Pressing this key cycles through all of the failures present. When on the last page, the MORE key causes a return to the first displayed failure page (Figure 1006 or Figure 1007).(3) All Display-Failures Mode screens have the RETURN selection on the left key.• RETURN Pressing this key causes the system to return to the Normal Mode screen (Figure 1001).(4) While in the display-failures mode, not pressing either key for five minutes causes the system to return to the Normal Mode screen (Figure 1001).(5) Figure 1009 thru Figure 1014 show typical display-failure modes that can be encountered.
Page 100710 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 1009. Tuning Port A Failure ScreenFigure 1010. Tuning Port B Failure Screen
Page 100810 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 1011. SDI 0 Program Pin Failure ScreenFigure 1012. SDI 1 Program Pin Failure Screen
Page 100910 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 1013. Antenna Monitor Program Pin Failure ScreenFigure 1014. CMC Port Failure Screen
Page 101010 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.D. Mainentance Mode for -0101, -0202, and -0303 Only(1) The maintenance mode is entered from either one of the two Test Complete screens (Figure 1004 or Figure 1005). The maintenance mode allows troubleshooting of all components of the DMA-37B DME System, both internal and external.(2) All pages have the MORE selection on the right key.• MORE Pressing this key cycles through all of the maintenance pages. When on the last page, the MORE key causes a return to the first displayed maintenance screen.(3) All pages have the RETURN selection on the left key.• RETURN Pressing this key causes the system to return to the Normal Mode screen (Figure 1001).(4) There is no timeout in the maintenance mode when the aircraft is on the ground. But, while in the air, not pressing a key for five minutes causes the system to return to the Normal Mode screen (Figure 1001).(5) Figure 1015 thru Figure 1021 show typical maintenance-mode pages that can be encountered.(6) In Figure 1016, row one, PORT X will be either PORT A or PORT B. Lines 2 thru 7 display the status of up to six tuning words by showing the contents of their SSM, Mode, Ident, Display, and Frequency fields. Mode 0 thru 5 frequencies are displayed if a Mode 0 (standby) frequency is being received. If the DMA-37B is not in standby, then Mode I thru 6 frequencies will be displayed. Column six displays either I, D, or B, when the Ident bit is on, when the Display is on, and when both Ident and Display bits are on, respectively. If the selected port does not meet the minimum total update rate check for Default Mode then all fields display X.NOTE: The Status field displays FAILED if either an external or an internal failure is detected.Figure 1015. DME Receiver Status (OK, FAILED) Screen
Page 101110 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 1016. Tuning Port Status (NML, TST, NCD, NODA) ScreenFigure 1017. Discrete Input Status Page 1 (OPEN, GRND) Screen
Page 101210 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 1018. Discrete Input Status Page 2 (OPEN, GRND) ScreenFigure 1019. SDI Program Pin Status Page (OPEN, COMM) Screen
Page 101310 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 1020. Antenna Monitor Program Pin Status Page (OPEN, COMM) ScreenFigure 1021. CMC Port Status (ACTIVE, INACTIVE) Screen
Page 101410 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.E. Flight Fault Memory Mode for -0101, -0202, and -0303 Only(1) When the flight-fault memory contains failures from previous flight legs, an Old Failures screen (Figure 1022) is presented as the last page of the maintenance mode screens. This page allows the viewing of previous flight leg failures, one flight leg at a time by pressing the YES key. Pressing the MORE key from this page bypasses this function and returns the system back to the first page of the maintenance data.(2) Once in the flight fault memory mode, flight legs are displayed from the most recent, backwards. Four pages are required for each flight leg. The first page of each flight leg contains the date, flight number, aircraft number, and departure/destination stations (Figure 1023). Three pages follow for each flight leg to contain the 13 possible failures (Figure 1024).(3) All flight fault memory pages have the MORE selection on the right key.• MORE Pressing the key cycles through all of the flight fault memory pages. When on the last page, the MORE key causes a return to the first page.(4) All flight fault memory pages have the RETURN selection on the left key.• RETURN Pressing this key causes the system to return to normal mode (Figure 1001).(5) There is no timeout in this mode when the aircraft is on the ground. But, while in the air, not pressing a key for five minutes causes the system to return to the Normal Mode screen (Figure 1001).Figure 1022. Old Failures Page Screen
Page 101510 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 1023. Previous Flight Legs Failures First Page ScreenNOTE: FC is fault code, UTC is time, R is repetition count, P is phase, O is origin.Figure 1024. Previous Flight Legs Failures Data Page Screen(Three Screens for Each Flight Leg)
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Page 200110 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.MAINTENANCE PRACTICES1. GeneralA. Description(1) This section of the manual provides service personnel with installation and maintenance information for the DMA-37B DME System. Installation instructions are supported by mechanical outline drawings and an electrical interconnection diagram. These drawings, located at the back of this section, must be reviewed by the installer, and requirements peculiar to the airframe must be established before starting the installation.B. Inspection After UnpackingCAUTION: THIS EQUIPMENT CONTAINS ELECTROSTATIC DISCHARGE SENSITIVE (ESDS) DEVICES. EQUIPMENT, MODULES, AND ESDS DEVICES MUST BE HANDLED WITH APPROPRIATE PRECAUTIONS.(1) Visually inspect the DMA-37B DME System and all associated equipments for possible damage which can occur during shipment. Inspect for dents, deep abrasions, chipped paint, etc. If any equipment is damaged, notify the transportation carrier immediately.(2) A Honeywell test and inspection record and quality report tag is included with each shipped unit. This notifies the customer that the necessary production tests and inspection operations have been performed on that particular unit.(3) One copy of the quality report tag is affixed to each unit by the first assembly inspector. As the unit proceeds through production and stock to the shipping area, the appropriate blocks on the test and inspection record of the tag are stamped. This tag accompanies the unit when it is shipped to the customer. Customers are requested to complete the quality report portion of the tag and return it to the Honeywell Quality Assurance Department, Fort Lauderdale, Florida. This portion of the tag provides Honeywell with the necessary information required to evaluate shipping methods as well as test and inspection effectiveness.(4) Completed cards are accumulated to provide information for a periodic analysis.C. Preinstallation Testing(1) The components in the DMA-37B DME System are adjusted and tested prior to shipment. Therefore, preinstallation testing is not required. However, if preinstallation testing of the units is desired, refer to the customer acceptance criteria given in the Component Maintenance Manual for the appropriate unit in the system. Refer to Paragraph 4 in the INTRODUCTION section of this manual for a list of related Component Maintenance Manuals.D. Equipment Changes and Marking(1) Honeywell uses a standardized marking system to identify equipment and their subassemblies which have had changes incorporated. Refer to the front of the appropriate Component Maintenance Manual for a list of Service Bulletins affecting the unit.E. Interchangeability(1) The DMA-37B DME System will operate in any installation that complies with ARINC characteristic 709-8; it also operates as an DME-37A DME System replacement in any installation that complies with ARINC 709. See Figure 2006 for particulars.
Page 200210 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.2. InstallationA. General(1) The DMA-37B DME System must be installed in the aircraft in a manner consistent with acceptable workmanship and engineering practices, and in accordance with the instructions set forth in this publication. To make sure that the system has been properly and safely installed in the aircraft, the installer must make a thorough visual inspection and conduct an overall operational and functional check of the system on the ground prior to flight.CAUTION: AFTER INSTALLATION OF THE CABLING AND BEFORE INSTALLATION OF THE EQUIPMENT, A CHECK MUST BE MADE WITH AIRCRAFT PRIMARY POWER BEING SUPPLIED TO THE MOUNT CONNECTORS TO MAKE SURE THAT POWER IS APPLIED ONLY TO THE PINS SPECIFIED IN FIGURE 2006.B. Location of Equipment(1) Location of the DMA-37B DME System in the aircraft is not critical, as long as the environment is compatible with the equipment design. Refer to the Leading Particulars, Table 5, in the DESCRIPTION AND OPERATION section of this manual. Forced air cooling is required for cooling the DMA-37B DME Interrogator in accordance with ARINC Characteristic 600. The associated cooling equipment must be mounted in accordance with the manufacturer’s instructions. (2) Antenna mounting must be in accordance with the manufacturer’s instructions for the antenna being used. The coaxial cable connecting the antenna to the mount must be as short and direct as possible and any required bends must be gradual. When two or more DMA-37B DME Systems are installed in an aircraft, it is necessary to provide adequate space isolation between antennas of each system to make sure that the use of one unit does not interfere with reception from another system. A minimum of 35 dB of space isolation must be provided, and any steps which can be taken to provide further isolation must be considered.(3) Control unit location and mounting can be determined by mutual agreement between the user and airframe manufacturer.C. Interwiring and Cable Fabrication(1) General(a) Figure 2006 is a complete interwiring diagram for a single DMA-37B DME System and associated components. This diagram requires thorough study before the installer begins installation of the aircraft wiring.(b) When two systems are being installed in the aircraft, the interconnecting wiring shown in Figure 2006, as well as all other installation instructions must be duplicated.(c) Cabling must be fabricated by the installer in accordance with Figure 2006. Wires connected to parallel pins must be approximately the same length, so that the best distribution of current can be effected. Honeywell recommends that all wires, including spares, shown in Figure 2006, be included in the fabricated harness. However, if full ARINC wiring is not desired, the installer must make sure that the minimum wiring requirements for the features and functions to be used are incorporated.
Page 200310 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.(d) When the cables are installed in the aircraft, they must be supported firmly enough to prevent movement and must be carefully protected against chafing. Additional protection must also be provided in all locations where the cables can be subject to abuse. In wire bundles, the cabling must not be tied tightly together as this tends to increase the possibility of noise pick-up and similar interference. When routing cables through the airframe, try to avoid running cables or wire close to power sources (400-Hz generator, etc). If unavoidable, the cables must cross high-level lines at a right angle, or high-quality shielded conductors must be used.(e) If a cable must pass through a bulkhead between pressurized and unpressurized zones, this passage must conform to the aircraft manufacturer’s specifications.(f) The assembler must be knowledgeable of any system variations peculiar to the installation, and must thoroughly understand the complexities associated with handling related problems of line lengths, capacitance, and of susceptibility to interference.(g) Table 2001 lists the determinants that are the responsibility of the installation agency for fabrication of the wiring harness. See Figure 2006 also.Table 2001. DMA-37B DME Interrogator Connector DeterminantsPin Type Signal Name FunctionMP1A Output Audio Output (HI) An analog output of the demodulated ground station identification audio signal to the audio distribution systemMP1B Output Audio Output (LO)MP1C Input SDI Bit 1 Used for encoding the location (system number) of the DMA-37B in the aircraft; used with pins MPID (SDI Bit 0) and MP1E (common)MP1D Input SDI Bit 0 Used for encoding the location (system number) of the DMA-37B in the aircraft; used with pins MPIC (SDI Bit 1) and MP1E (common)MP1E --- SDI Common Ground for the SDI code inputs from pins MP1C and/or MP1DMP1F --- Siggest ARINC 709 Spare No. 1 ---MP1G Output DME Distance Data Output No. 1 (A) One of two low speed ARINC 429 data output ports to provide DME distance outputs to other equipment on the aircraft.Used to transmit the range words, the DME ground station identification words, and to repeat the selected frequency words if received over the frequency tuning interfaces. Maintenance data information will also be transmitted on these ports.MP1H Output DME Distance Data Output No. 1 (B)MP1J --- Spare ---MP1K Output Siggest ARINC 709 Spare No. 2 ---MP2A --- Spare ---MP2B --- Spare ---MP2C --- Spare ---MP2D --- Spare ---
Page 200410 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.MP2E --- Spare ---MP2F --- Spare ---MP2G --- Spare ---MP2H --- Spare ---MP2J --- Spare ---MP2K --- Spare ---MP3A Input Freq/Funct Select Data I/P Port A (A) One of two low speed 429 data input ports to receive tuning information, Ident and Display channel selection, DME Mode and Source/Destination Identifier selection.MP3B Input Freq/Funct Select Data I/P Port A (B)MP3C --- Spare ---MP3D Input Freq/Funct Select Data I/P Port A (A) One of two low speed 429 data input ports to receive tuning information, Ident and Display channel selection, DME Mode and Source/Destination Identifier selection.MP3E Input Freq/Funct Select Data I/P Port A (B)MP3F --- Spare ---MP3G Output DME Distance Data Output No. 2 (A) One of two low speed ARINC 429 data output ports to provide DME distance outputs to other equipment on the aircraft.Used to transmit the range words, the DME ground station identification words, and to repeat the selected frequency words if received over the frequency tuning interfaces. Maintenance data information will also be transmitted on these ports.MP3H Output DME Distance Data Output No. 2 (B)MP3J --- Spare ---MP3K --- Spare ---MP4A --- Spare ---MP4B --- Spare ---MP4C --- Spare ---MP4D --- Spare ---MP4E --- Spare ---MP4F --- Spare ---MP4G --- Spare ---MP4H --- Spare ---MP4J --- Spare ---MP4K --- Spare ---Table 2001. DMA-37B DME Interrogator Connector Determinants (cont)Pin Type Signal Name Function
Page 200510 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.MP5A Input Default Scan Inhibit Discrete input indicates default mode of operation.If this program pin is grounded when no tuning input is received and like-labelled words fall below five per second, DMA-37B automatically reverts to standby operation and invalidates its computed range measurement.If this program pin is open when no tuning input is received and like-labelled words fall below five per second, DMA-37B automatically reverts to free scan operation.MP5B Input Freq/Funct Data Source Select Discrete Discrete input determines which input tuning port will be selected. Port A (MP3A & MP3B) are used when the discrete is in the ground state. Port B (MP3D & MP3E) are used when the discrete is in the open state. When the DMA-37B is installed in an aircraft in which a dedicated control panel supplies the tuning information, Port B must be used. When the DMA-37B is installed in an aircraft in which a Centralized Radio Management system supplies the tuning information, Port A must be used as the primary control source, and Port B as the secondary or backup control source.MP5C Input Functional Test Discrete Discrete input that activates LRU functional test function. Gnd/Low = activate functional test.MP5D Input Indicator No. 1 Status Input Discrete input indicates the status of indicator No. 1. The input is open to indicate the indicator has failed.MP5E Input Indicator No. 2 Status Input Discrete input indicates the status of indicator No. 2. The input is open to indicate the indicator has failed.MP5F --- Spare ---MP5G --- Spare ---MP5H --- Spare ---MP5J Input Reserved for Maintenance Display ResetResets failure reporting of DME System.MP5K Input Air/Ground Logic Discrete input is open when the aircraft is on the ground and grounded when the aircraft is airborne.MP6A --- Spare ---MP6B --- Spare ---MP6C --- Spare ---MP6D --- Spare ---Table 2001. DMA-37B DME Interrogator Connector Determinants (cont)Pin Type Signal Name Function
Page 200610 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.MP6E Input CFDS Data Bus Input A Low speed ARINC 429 data input port receives maintenance data from the CFDS/CMCMP6F Input CFDS Data Bus Input BMP6G --- Spare ---MP6H Input DC Antenna Monitor Enable Discrete input indicates whether or not the antenna monitoring function is activated. Antenna monitoring is activated when this input is connected to the Antenna Monitor Common (MP6J).MP6J Output DC Antenna Monitor Common Discrete supplies the return (ground) for the Antenna Monitor Enable (MP6H) when antenna monitoring is active.MP6K --- Spare ---MP7A --- Spare ---MP7B Output 115V AC Indicator Panel Power Out (HOT)115 V ac, 400Hz is available on these pins for routing to an indicator panel in those installations which use an individual indicator panel.MP7C Output 115V AC Indicator Panel Power Out (COLD)MP7D --- Spare ---MP7E --- Spare ---MP7F --- Spare ---MP7G --- Spare ---MP7H Output 115V AC Control Panel Power Out (HOT)115 V ac, 400Hz is available on these pins for routing to a control panel in those installations which use an individual control panel rather than an integrated frequency/function selection system supplied with aircraft power directly.MP7J Output 115V AC Control Panel Power Out (COLD)MP7K --- Spare ---BP1 Input 115VAC (HOT) (2A Circuit Breaker)Primary input power to DMA-37BBP2 --- --- ---BP3 --- --- ---BP4 --- --- ---BP5 --- --- ---BP6 --- --- ---BP7 Input 115VAC (COLD)(AC common)Primary power returnBP8 --- --- ---BP9 --- --- ---Table 2001. DMA-37B DME Interrogator Connector Determinants (cont)Pin Type Signal Name Function
Page 200710 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.(2) Reserved and Spare Wires(a) If the installer does not wish to connect all wires, he can select wires reserved for optional functions which his system does not contain and delete these wires. He must also decide which future spare wires to include in the installation. Reserved and spare wires are identified in interwiring diagram Figure 2006.(3) Source/Destination Identifier (SDI) Encoding(a) A connection is required from the common pin MP6C to the appropriate source/destination identifier (SDI) pin to identify each DMA-37B in multiple system installations. Installations having only one DMA-37B must include a connection identifying it as the No. 1 system. These connections must not be omitted from any installation. See Figure 2006 notes for the SDI encoding scheme for pins MP1C, MP1D, and MP1E.D. Installation of System(1) Mounting Base(a) The selected mounting base for the DMA-37B DME Interrogator must be wired according to the system interwiring diagram, Figure 2006, and installed according to the manufacturer’s instructions. The mounts are designed to be removed without rewiring the connectors. Follow the equipment manufacturer’s installation instructions to install the mount into the airframe.(b) To wire the mounts into the system, first remove the mount connector cover and connector plate assembly. Then crimp or solder (as applicable) the interconnecting wiring to the appropriate connector pins. Finally, return the connector plate assembly and cover to their original positions.NOTE: To allow for inspection or repair of the connector, or the wiring to the connector, sufficient lead length must be left so that the rear connector assembly can be pulled forward several inches when the mounting hardware for the rear connector assembly is removed. A bend must be made in the harness near the connector to allow water droplets, that might form on the harness from condensation, to drip off at the bend and not collect at the connector.BP10 --- --- ---BP11 Input Chassis Ground Chassis groundBP12 Input/OutputSuppressor This analog port is both an input and an output. When the DMA-37B is receiving, this line will receive suppression pulses from other pulse equipment, and when the DMA-37B is transmitting, this line will transmit suppression pulses to other pulse equipment.BP13 Output Reserved for Video Output Output for the video output signal from the DMA-37B receiver.Table 2001. DMA-37B DME Interrogator Connector Determinants (cont)Pin Type Signal Name Function
Page 200810 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.(2) DMA-37B DME Interrogator(a) The DMA-37B DME Interrogator is installed in the mount as follows:1Slide the DMA-37B into the mount until the guide pins are aligned and the electrical connectors are firmly engaged.2Secure the front of the DMA-37B to the mount by tightening the two knurled screw clamps (located on the front of the mount) until they are firmly seated over hold-down hooks located on the front of the unit.3Safety-wire the two screw clamps.(3) NAV Control Panel(a) The selected NAV control panel must be wired according to the system interwiring diagram, Figure 2006, and the manufacturer's instructions. For installation procedure and mounting dimensions, refer to the applicable manufacturer's instructions.(4) DME Display(a) The selected DME display must be mounted in the aircraft instrument panel to provide easy visibility and to conform to customer requirements and the installation instructions of the manufacturer. Interwiring must be in accordance with Figure 2006, system interwiring diagram.(5) DME Antenna(a) Install the DME antenna in accordance with the manufacturer's instructions. Maximum insertion loss of the coax run from the DMA-37B to the antenna is 3 dB.(6) Mutual Suppression(a) In dual DMA-37B installations, mutual suppression pulse connections are required between units.(b) Mutual suppression pulse connectors are also required between DMA-37B units, air traffic control (ATC) transponders, and Traffic Alert and Collision Avoidance System (TCAS).3. Inspection and System Check ProceduresCAUTION: INSPECTION AND CHECK PROCEDURES FOR THE DMA-37B INCLUDES CHECKOUT OF ALL INTERFACING UNITS THAT CAN AFFECT PERFORMANCE OF THE DMA-37B.A. Inspection(1) Table 2002 is a visual inspection check procedure and must be performed after system installation, prior to system checkout. In addition, the procedure must be used as a periodic inspection check.
Page 200910 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.B. System Checkout(1) General(a) After installation of the DMA-37B DME System and inspection of the equipment in accordance with Table 2002, perform a continuity and visual check of the system interwiring in accordance with Paragraph 3.B.(2). A post-installation test in accordance with Paragraph 3.B.(3) must then be performed.(2) System Interwiring Check(a) Visually check the system interwiring for abnormalities, such as cables rubbing unprotected metal edges or tightly stretched cables. Check continuity of all interwiring. In particular, check the following:• Check that the DMA-37B is properly installed and the hold-down screw clamps are tight.• Check the wiring harness connectors for security and connection to the DMA-37B.• Check that the antenna transmission line connectors are securely fastened.• Check that the control panel connectors are securely fastened.• Check that the DME display is securely fastened.• Check that the cables do not interfere with aircraft controls or other equipment.(3) Post-lnstallation Check(a) Test Equipment Required1Table 2003 lists a ramp test set that can be used to determine if the DMA-37B DME System is operating properly. Test sets other than that listed in Table 2003 can be used if their characteristics fulfill those listed under Characteristics Required.Table 2002. Inspection/Check ProceduresEquipment Inspection/Check Procedure4 MCU Unit Mount As defined by manufacturer's instructions.DMA-37B DME Interrogator 1. Check that unit is fully inserted in mount and that Interrogator the knurled screw clamps which secure the unit in the mount are tight and safety wired.2. Inspect the case for deformation, dents, corrosion, and damage to finish; make sure that ventilation holes in the unit are not clogged.NAV Control Panel As defined by manufacturer's instructions.DME Display As defined by manufacturer's instructions.DME Antenna As defined by manufacturer's instructions.Table 2003. Table of Test EquipmentDescription Characteristics Required Representative TypeTransponder and DME Test SetMust have an X-channel and a Y-channel output. Selected range must be variable from 0.1 to 400 nautical miles. Must transmit an ident tone.Instrument Flight Research Corp. (IFR) Model ATC-6OOA or equivalent
Page 201010 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.(b) DMA-37B Initiated System Test, -0101, -0202, and -0303 Only1A functional self test of the DMA-37B DME System can be initiated by pressing the test key pushbutton switch as designated on the front panel LCD (Figure 2001). Although the normal-mode screen indicates that this is actuated from the right key, the left key has the same function if pressed while the DMA-37B LCD is in its normal mode.2The self-test mode starts by displaying the Test in Progress screen (Figure 2002) one second after pressing the test key. This is displayed for five seconds with a moving thermometer along the bottom of the LCD indicating the progress of the test from one to five seconds.3The Normal-Mode screen (Figure 2001) is displayed for the first second of the test sequence.Figure 2001. Typical Normal Mode Screen
Page 201110 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 2002. Test in Progress Screen4Once complete, the Test Complete, No Failures screen is displayed (Figure 2003), or the Test Complete, Failures screen is displayed (Figure 2004). Both screens contain two key selections each: MAINT and RETURN or MAINT and WHY?, respectively.• MAINT For both screens, MAINT is located on the left key. This allows the initiation of the extended maintenance pages of the system for troubleshooting. Refer to Paragraph D of the FAULT ISOLATION section of this manual.• RETURN In the Test Complete, No Failures screen, the RETURN key to the right returns the system to its normal mode screen (Figure 2001).• WHY? In the Test Complete, Failures screen, the WHY? key to the right puts the system into the display-failures mode where individual system failures are displayed one on each page. Refer to Paragraph C of the FAULT ISOLATION section of this manual.5While in the self-test mode, not pressing either key for five minutes causes the system to return to the Normal Mode screen (Figure 2001).
Page 201210 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 2003. Test Complete, No Failures ScreenFigure 2004. Test Complete, Failures Screen
Page 201310 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.(c) Front Panel Test Initiation, -1101 and -1212 Only1On the front panel, observe that the green status LED is lit.2On the front panel, push the self test button.3Make sure that all LEDs turn amber and then turn green (indicating normal operation).(d) Cockpit-Initiated System Test1If provisions have been made in the aircraft installation for cockpit initiated DMA-37B self-test procedure, that procedure must be verified. The results of the test can be indicated on the EFIS or DME displays depending upon the installation.(e) Ramp testNOTE: The following test instructions are written in general terms. Refer to the DME test set instruction manual for specific DME test set operating instructions.1Set up ramp test set as recommended in accordance with test set manufacturer's instruction manual. Position DME ramp test set in vicinity of aircraft.2Apply power to DMA-37B DME System.3If the Post-lnstallation Check System Test has not been accomplished, perform the System Test as described in Paragraph 3.B.(3) to verify self-test operation.4Set NAV control to select a DME frequency corresponding to that set in the DME ramp test set.5Verify that the DME distance readout is equal to that set in the DME ramp test set. 6Set DME ramp test set for an audio Ident output.7Verify that the audio Ident is heard through the cockpit speaker.8Repeat steps 4 and 5 for one or more additional frequencies and distances.(f) Flight Tests1Preflight TestaGeneral(1) The following test procedure gives instructions for a preflight test which make sures that the DMA-37B DME System is functioning in an acceptable manner prior to takeoff.bTest Procedures(1) Perform the System Test, Cockpit Initiated procedure as described in Paragraph 3.B.(3)(d) of this section.2In-Flight Confidence TestaGeneral(1) Upon completion of the post-installation and preflight checks, a local flight can be made to verify system operation. Perform the following In-Flight Confidence Test procedures.
Page 201410 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.bTest Procedures(1) Apply power to DMA-37B DME System.(2) Set NAV control to frequency of a nearby DME station.(3) Note distance readout of DME display to the selected DME station and compare this to calculated distance on a visual flight rules (VFR) chart. Verify that the two distances agree within 0.1 nautical mile.4. Removal and ReplacementA. Removal(1) Loosen the two knurled screw clamps (located on the front of mount) that secure the DMA-37B to the mount.(2) Gently pull the DMA-37B forward until it is disconnected from the rear connector and guide pins.B. Replacement(1) Slide the DMA-37B onto the tray of the mount and then gently push the DMA-37B until the guide pins are aligned and the connectors make a firm connection.(2) Tighten the two knurled screw clamps located on the front of the mount until they are firmly seated over the hold-down hooks located on the front of the DMA-37B.(3) Safety wire the two knurled screw clamps.5. Maintenance ProceduresA. Adjustments and Alignments(1) There are no adjustments or alignments required for the DMA-37B DME System. All alignment and adjustment procedures are accomplished during bench maintenance. The technician must remove the unit from the aircraft and reference must be made to the related maintenance manual when unit performance indicates an adjustment or an alignment is required.B. System Protection(1) The system must be protected by a 2-ampere circuit breaker located at the circuit breaker panel in the aircraft. C. Lubrication Practices(1) There are no requirements for periodic lubrication of any DMA-37B DME System components while mounted in the aircraft. Reference must be made to the applicable maintenance manual for lubrication procedures during routine maintenance of individual units. Refer to Paragraph 4 in the INTRODUCTION section of this manual for a list of related maintenance manual publications.D. Cleaning(1) When deemed necessary, depending upon the environment to which the equipment is exposed and the intensity of use, periodic cleaning must be performed. Any dust on the DMA-37B DME System LRUs must be wiped off with a lint-free cloth.NOTE: Any cleaning of equipment interiors must be limited to that required when performing overhaul (bench-type) work.
10 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 2005. (Sheet 1). DMA-37B DME Interrogator Dimensional Outline DrawingPage 2015/2016
10 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 2005 (Sheet 2). DMA-37B DME Interrogator Dimensional Outline DrawingPage 2017/2018
10 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 2005 (Sheet 3). DMA-37B DME Interrogator Dimensional Outline DrawingPage 2019/2020
10 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 2005 (Sheet 4). DMA-37B DME Interrogator Dimensional Outline DrawingPage 2021/2022
10 Oct 200734-51-02MAINTENANCE MANUALDMA-37B DME System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 2006. DMA-37B DME System Interwiring DiagramPage 2023/2024

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