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

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Honeywell International Inc.
P.O. Box 97001
Redmond, Washington 98073-9701
U.S.A
CAGE 97896
Telephone: (800) 601-3099 (U.S.A.)
Telephone: (602) 365-3099 (International)
Web site: http://portal.honeywell.com/wps/portal/aero
TO HOLDERS OF MAINTENANCE MANUAL, PUB NO. 1137-1, DMA-37B DME SYSTEM
REVISION NO. 003 DATED 10 OCT 2007
HIGHLIGHTS
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Honeywell International Inc.
P.O. Box 97001
Redmond, Washington 98073
U.S.A.
CAGE: 97896
Telephone: (800) 601-3099 (U.S.A.)
Telephone: (602) 365-3099 (International)
Web site: http://portal.honeywell.com/wps/portal/aero
Maintenance Manual
DMA-37B DME System
This document contains technical data and is subject to U.S. export regulations. These commodities,
technology, or software were exported from the United States in accordance with the export administration
regulations. Diversion contrary to U.S. law is prohibited.
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Oct 1995
MAINTENANCE MANUAL
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Honeywell – Confidential
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RECORD OF REVISIONS
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TABLE OF CONTENTS
Subject
Page
INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-1
1. How to Use This Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-1
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-1
B. Symbols. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-1
C. Weights and Measurements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-1
2. Customer Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-2
A. Honeywell Aerospace Online Technical Publications Web Site . . . . . . . . . . . . . . INTRO-2
B. Complete Customer Care Center . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-2
3. Data Verification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-2
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-2
4. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-3
A. Honeywell Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-3
B. Other Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-3
5. Acronyms and Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-4
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-4
DESCRIPTION AND OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1
1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1
A. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1
B. Purpose of Equipment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3
C. Equipment Part Numbers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3
D. Equipment Required but Not Supplied . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5
E. Configurations Available . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5
2. System Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .7
A. Unit Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .7
B. Environmental Certification (066-50013-0101, -0202, and -0303 only). . . . . . . . . . . . . . . .9
C. Environmental Certification (066-50013-1101 only) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .10
D. Environmental Certification (066-50013-1212 only) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .12
3. System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .13
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .13
4. System Component Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .15
A. DMA-37B DME Interrogator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .15
B. Other Components in the System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .15
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5. Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
B. Basic Theory . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001
1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001
A. Description for -0101, -0202, and -0303 Only . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001
B. Selt-Test Mode for -0101, -0202, and -0303 Only . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1003
C. Display-Failures Mode for -0101, -0202, and -0303 Only . . . . . . . . . . . . . . . . . . . . . . . 1005
D. Mainentance Mode for -0101, -0202, and -0303 Only . . . . . . . . . . . . . . . . . . . . . . . . . 1010
E. Flight Fault Memory Mode for -0101, -0202, and -0303 Only . . . . . . . . . . . . . . . . . . . . 1014
MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001
1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001
A. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001
B. Inspection After Unpacking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001
C. Preinstallation Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001
D. Equipment Changes and Marking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001
E. Interchangeability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001
2. Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2002
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2002
B. Location of Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2002
C. Interwiring and Cable Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2002
D. Installation of System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2007
3. Inspection and System Check Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2008
A. Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2008
B. System Checkout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2009
4. Removal and Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014
A. Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014
B. Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014
5. Maintenance Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014
A. Adjustments and Alignments. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014
B. System Protection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014
C. Lubrication Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014
D. Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014
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List of Illustrations
Figure
Page
Figure Intro-1. Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-1
Figure 1.
DMA-37B DME Interrogator, 066-50013-0101, -0202, and -0303 . . . . . . . . . . . . .1
Figure 2.
DMA-37B DME Interrogator, 066-50013-1101 and -1212 . . . . . . . . . . . . . . . . . . .2
Figure 3.
DMA-37B DMA System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .14
Figure 4.
DMA-37B DME Interrogator Simplified Block Diagram . . . . . . . . . . . . . . . . . . . .16
Figure 1001.
Typical Normal Mode Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1001
Figure 1002.
LCD Control Flow. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1002
Figure 1003.
Test in Progress Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1003
Figure 1004.
Test Complete, No Failures Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1004
Figure 1005.
Test Complete, Failures Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1004
Figure 1006.
DME Receiver OK, External Failures Present Screen. . . . . . . . . . . . . . . . . . .1005
Figure 1007.
DME Receiver Failed, External Failures Also Present Screen . . . . . . . . . . . .1005
Figure 1008.
DME Receiver Failed, External Failures Not Present Screen . . . . . . . . . . . . .1006
Figure 1009.
Tuning Port A Failure Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1007
Figure 1010.
Tuning Port B Failure Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1007
Figure 1011.
SDI 0 Program Pin Failure Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1008
Figure 1012.
SDI 1 Program Pin Failure Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1008
Figure 1013.
Antenna Monitor Program Pin Failure Screen . . . . . . . . . . . . . . . . . . . . . . . . .1009
Figure 1014.
CMC Port Failure Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1009
Figure 1015.
DME Receiver Status (OK, FAILED) Screen . . . . . . . . . . . . . . . . . . . . . . . . . .1010
Figure 1016.
Tuning Port Status (NML, TST, NCD, NODA) Screen . . . . . . . . . . . . . . . . . . . 1011
Figure 1017.
Discrete Input Status Page 1 (OPEN, GRND) Screen. . . . . . . . . . . . . . . . . . . 1011
Figure 1018.
Discrete Input Status Page 2 (OPEN, GRND) Screen. . . . . . . . . . . . . . . . . . .1012
Figure 1019.
SDI Program Pin Status Page (OPEN, COMM) Screen . . . . . . . . . . . . . . . . .1012
Figure 1020.
Antenna Monitor Program Pin Status Page (OPEN, COMM) Screen . . . . . . .1013
Figure 1021.
CMC Port Status (ACTIVE, INACTIVE) Screen. . . . . . . . . . . . . . . . . . . . . . . .1013
Figure 1022.
Old Failures Page Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1014
Figure 1023.
Previous Flight Legs Failures First Page Screen. . . . . . . . . . . . . . . . . . . . . . .1015
Figure 1024.
Previous Flight Legs Failures Data Page Screen
(Three Screens for Each Flight Leg).. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1015
Figure 2001.
Typical Normal Mode Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2010
Figure 2002.
Test in Progress Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2011
Figure 2003.
Test Complete, No Failures Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2012
Figure 2004.
Test Complete, Failures Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2012
Figure 2005.
DMA-37B DME Interrogator Dimensional Outline Drawing . . . . . . . . . . . . . . .2015
Figure 2006.
DMA-37B DME System Interwiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . .2023
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List of Tables
Table
Page
Table Intro-1.
Data Verification. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-2
Table 1.
DMA-37B DME System Components (Honeywell Supplied). . . . . . . . . . . . . . . . . 4
Table 2.
Equipment Required but Not Supplied . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
Table 3.
DMA-37B DME Interrogator Available Configurations. . . . . . . . . . . . . . . . . . . . . . 5
Table 4.
DMA-37B DME Interrogator Features . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
Table 5.
Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
Table 6.
Environmental Certification (066-50013-0101, -0202, and -0303 only) . . . . . . . . . 9
Table 7.
Environmental Certification (066-50013-1101 only). . . . . . . . . . . . . . . . . . . . . . . 10
Table 8.
Environmental Certification (066-50013-1212 only) . . . . . . . . . . . . . . . . . . . . . . 12
Table 2001.
DMA-37B Interrogator Connector Determinants . . . . . . . . . . . . . . . . . . . . . . . 2003
Table 2002.
Inspection/Check Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2009
Table 2003.
Table of Test Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2009
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INTRODUCTION
1.
How to Use This Manual
A.
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.
B.
(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.
Symbols
(1)
The symbols in Figure Intro-1 identify ESDS and moisture sensitive devices in this
manual, if applicable.
ESDS
Moisture Sensitive
Figure Intro-1.
C.
Symbols
Weights and Measurements
(1)
All weights and measurements are in U.S. values and S.I. (metric) values.
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2.
Customer Support
A. Honeywell Aerospace Online Technical Publications Web Site
(1) If you have access to the Internet, go to the Honeywell Online Technical Publications
web site at http://portal.honeywell.com/wps/portal/aero/ to:
• Download or see publications online
• Make an order for a publication
• Tell Honeywell of a possible data error 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:
• Fax:
(2)
cas-publications-distribution@honeywell.com
602-822-7272
• Phone:
1-800-601-3099
(U.S.A.)
• Phone:
1-602-365-3099
(International).
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 Verification
A.
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:
Table Intro-1.
Number
Data Verification
Type
Date
Testing
By performance
09 Oct 2007
Fault Isolation
By performance
09 Oct 2007
Maintenance Practices
By performance
09 Oct 2007
(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.
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4.
References
A. 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).
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5.
Acronyms and Abbreviations
A. General
(1)
Refer to the list that follows for acronyms and abbreviations in this manual.
List of Acronyms and Abbreviations
Term
Full Term
AF
audio frequency
ANSI
American National Standards Institute
ARINC
Aeronautical Radio, Incorporated
ASME
American Society of Mechanical Engineers
ATC
air traffic control
BCD
binary coded decimal
BITE
built-in test equipment
CAGE
Commercial and Government Entity
CFDIU
centralized fault display interface unit
CFDS
central fault display system
CMC
central maintenance computer
CPU
central processor unit
CW
continuous wave
DITS
digital information transfer system
DME
data measuring equipment
DSP
digital signal processor
ECCN
export control classification number
EUROCAE
European Organisation for Civil Aviation Equipment
ESD
electrostatic discharge
ESDS
electrostatic discharge sensitive
FPGA
field-programmable gate array
FPLA
field-programmable logic array
GPO
Government Printing Office
HIRF
high intensity radiation fields
HPN
Honeywell part number
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List of Acronyms and Abbreviations (cont)
Term
Full Term
I/O
input/output
IEEE
Institute of Electrical and Electronics Engineers
LCD
liquid crystal display
LRU
line replaceable unit
MOPS
minimum operational performance standards
NCD
no-computed-data
No.
number
PCMCIA
Personal Computer Memory Card International Association
RF
radio frequency
RTCA
Radio Technical Commission for Aeronautics
SDI
source/destination identifier
SSM
sign status matrix
Std
standard
TACAN
tactical air navigation
TCAS
traffic alert and collision avoidance system
TSO
technical standard order
VFR
visual flight rules
VHF
very high frequency
VOR
VHF omnirange
VORTAC
VHF omnirange tactical air navigation
U.S.A.
United States of America
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Blank Page
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DMA-37B DME System
DESCRIPTION AND OPERATION
1. General
A. 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
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Figure 2.
DMA-37B DME Interrogator, 066-50013-1101 and -1212
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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.
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Table 1.
Equipment
Type Number
DMA-37B DME
Interrogator
DMA-37B DME System Components (Honeywell Supplied)
Equipment Description
Part Number
A 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.
066-50013-0101
Same 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.
066-50013-0202
Same as -0202 except capable of interfacing CFDS in accordance
to McDonnell Douglas software requirements (replaces ABDO048C
implementation).
066-50013-0303
Same 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.
066-50013-1101
Same 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
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D. Equipment Required but Not Supplied
(1) Table 2 lists equipment required for the RVA-36B VOR/Marker System, but not supplied
by Honeywell.
Table 2.
Equipment Required but Not Supplied
Equipment
Description
Power 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.
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 3.
DMA-37B DME Interrogator Available Configurations
Features
Interface
HPN
Basic Unit
Fault Memory
Boeing CMC
066-50013-0101
066-50013-0202
066-50013-0303
066-50013-1101
066-50013-1212
McDonnell
Airbus CFDS Douglas CFDS
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Table 4.
Feature
DMA-37B DME Interrogator Features
Description
Basic Unit
A 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 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 recording
ten 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 requirements
Digital 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.
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2. System Leading Particulars
A. Unit Specifications
(1) Table 5 lists the leading particulars for the DMA-37B DME System.
Table 5.
Leading Particulars
Characteristics
Description
General
Power 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 MCU
Cooling
ARINC 600 forced air
Temperature
• 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 Humidity
Warm-up period
Stable operation within one minute after application of power
Frequency Selection
Serial digital in accordance with ARINC 429
Range
Zero to 300 Nautical Miles
Altitude
50,000 feet above mean sea level
Velocity
Zero to 1000 Knots
Self Test
Continuous, automatic; Manual from discrete ARINC 429, CMC, or Front Panel
Integrity Monitoring
Continuous self-monitoring
Fault Reporting
ARINC 429 and ABD 0048B Centralized Maintenance Interfaces
Data Outputs
ARINC 429 Distance and CMC Interface
Certification
• -0101, -0202, and -0303
TSO C66c
DO-160C Environmental Category
/A2D2/ZCA/MNB/XXXXXXAEAEZUZ/XXE2/XX
ICAO Annex 10 FM Immunity
DO-189, DO-178B
• -1101
TSO C66c
DO-160E Environmental Category
[(A2)(B2)V]BAB[SB]XXXXXXAA(WF)XA[R(WF)][ZW]RRRL[ZZZZ]XXAC
ICAO Annex 10 FM Immunity
DO-189, DO-178B
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Table 5.
Leading Particulars (cont)
Characteristics
• -1212
Description
TSO C66c
DO-160E Environmental Category
[(A2)(D2)Z]BAB[SB]XXXXXXAA(WF)HA[R(WF)][ZW]R[RR]L[ZZZZ]XXAC
ICAO Annex 10 FM Immunity
DO-189, DO-178B
Transmitter
Frequency Range
1025.00 MHz to 1150.00 MHz, 1MHz channel spacing
Frequency Stability
± 80 kHz
Power Output
700 Watts, Typical
Pulse Code Spacing
• X-Channel
12.0 ± 0.4 microseconds
• Y-Channel
36.0 ± 0.4 microseconds
Frequency Spectrum
90% of total pulse energy within ± 0.25 MHz of channel frequency
Rise Time (maximum)
2.8 Microseconds (consistent with pulse spectrum)
CW Leakage at Antenna
Connector
-79 dBm maximum
Antenna Mismatch
No damage to transmitter with antenna open or short circuit
Receiver
Frequency
962.00 MHz to 1213 MHz (252 Channels)
Sensitivity
-90 dBm minimum lock-on level
Selectivity
Attenuation
Bandwidth
Less than 6 dB
95 kHz
More than 50 dB
±800 kHz
Dynamic Range
80 dB minimum
Image Rejection
60 dB minimum
CW Rejection
60 dB minimum
Audio 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 load
Audio 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 ohms
Less 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.
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Table 5.
Leading Particulars (cont)
Characteristics
Description
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 standards
Distance Accuracy
Signal Level
Accuracy
Lock-on to -80 dBm
0.2 NM
Lock-on from -80 to -10 dB
0.1 NM
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).
Table 6.
Environmental Certification (066-50013-0101, -0202, and -0303 only)
Test
Category
Temperature and Altitude
A2D2
In-Flight Loss of Cooling
Temperature Variation
Humidity
Operational Shocks and Crash Safety
Vibration
Operational Shock
MNB
Explosion Proofness
Waterproofness
Fluids Susceptibility
Sand and Dust
Fungus Resistance
Salt Spray
Magnetic Effect
Power Input
Voltage Spike
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Table 6.
Environmental Certification (066-50013-0101, -0202, and -0303 only) (cont)
Test
Category
Audio Frequency Conducted Susceptibility Power Inputs
Induced Signal Susceptibility
Radio Frequency Susceptibility
(Radiated and Conducted)
Emission of Radio Frequency Energy
Lightning-Induced Transient Susceptibility
XXE2
Lightning-Direct Effects
Icing
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).
Table 7.
Environmental Certification (066-50013-1101 only)
Test
Category
Ground 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
Altitude
B2
Decompression
A2
Overpressure
A2
Temperature Variation
Humidity
Acceleration
Vibration Due to Fan Blade Loss (Windmilling)
Bench Handling Shock
Shipping Container
Operational Shock (Emergency Landing and Bird Strike)
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Table 7.
Environmental Certification (066-50013-1101 only) (cont)
Test
Category
Vibration
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
Power Input
A(WF)
Voltage Spikes
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
Radio Frequency Radiated Susceptibility
Certification HIRF Environment I by Direct Injection Method
AF Conducted Emissions, AF Capacitive Coupling
AF Conducted Emissions, AF Inductive Coupling
RF Conducted Emissions (Narrowband)
RF Conducted Emissions (Broadband)
RF Radiated Emissions (Narrowband)
RF Radiated Emissions (Broadband)
Lightning-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
Lightning Direct Effects
N/A
Icing
N/A
Electrostatic Discharge (ESD)
Fire, Flammability
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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
Category
Temperature Test
A2
In-Flight Loss of Cooling
Temperature Variation
Altitude Test
D2
Decompression Test
A2
Overpressure Test
A2
Humidity
Operational Shock And Crash Safety
Vibration
Vibration Due to Fan Blade Loss (Windmilling)
Vibration: Due to Landing Gear Tyre Burst
Explosive Atmosphere
Waterproofness
Fluids Susceptibility
Sand and Dust
Fungus Resistance
Salt Fog
Magnetic Effect
Power Input
A (WF)
Voltage Spike
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
Radio Frequency Radiated Susceptibility
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Table 8.
Environmental Certification (066-50013-1212 only) (cont)
Test
Category
RF Conducted Emissions
(Narrowband)
RF Radiated Emissions (Narrowband)
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
Icing
ESD Susceptibility
Fire, Flammability
3. System Description
A. 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.
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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.
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4. System Component Description
A. 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.
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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
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5. Operation
A. 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 Assembly
NOTE: 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.
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(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) Assembly
NOTE: 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.
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(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.
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(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.
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FAULT ISOLATION
1. General
A. 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
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Figure 1002.
LCD Control Flow
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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).
•
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.
WHY?
(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).
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Figure 1004.
Figure 1005.
Test Complete, No Failures Screen
Test Complete, Failures Screen
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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.
Figure 1007.
DME Receiver OK, External Failures Present Screen
DME Receiver Failed, External Failures Also Present Screen
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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.
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Figure 1009.
Tuning Port A Failure Screen
Figure 1010.
Tuning Port B Failure Screen
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Figure 1011.
SDI 0 Program Pin Failure Screen
Figure 1012.
SDI 1 Program Pin Failure Screen
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Figure 1013.
Antenna Monitor Program Pin Failure Screen
Figure 1014.
CMC Port Failure Screen
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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
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Figure 1016.
Tuning Port Status (NML, TST, NCD, NODA) Screen
Figure 1017.
Discrete Input Status Page 1 (OPEN, GRND) Screen
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Figure 1018.
Figure 1019.
Discrete Input Status Page 2 (OPEN, GRND) Screen
SDI Program Pin Status Page (OPEN, COMM) Screen
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Figure 1020.
Antenna Monitor Program Pin Status Page (OPEN, COMM) Screen
Figure 1021.
CMC Port Status (ACTIVE, INACTIVE) Screen
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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
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Figure 1023.
Previous Flight Legs Failures First Page Screen
NOTE: 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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DMA-37B DME System
MAINTENANCE PRACTICES
1. General
A. 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 Unpacking
CAUTION:
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.
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DMA-37B DME System
2. Installation
A. 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.
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(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.
Pin
Type
DMA-37B DME Interrogator Connector Determinants
Signal Name
Function
MP1A
Output Audio Output (HI)
MP1B
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 MP1D
MP1F
---
Siggest ARINC 709 Spare No. 1
---
MP1G
Output DME Distance Data Output No. 1 (A)
MP1H
Output DME Distance Data Output No. 1 (B)
MP1J
---
MP1K
Output Siggest ARINC 709 Spare No. 2
---
MP2A
---
Spare
---
MP2B
---
Spare
---
MP2C
---
Spare
---
MP2D
---
Spare
---
Spare
An analog output of the demodulated ground
station identification audio signal to the audio
distribution system
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.
---
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Table 2001.
Pin
Type
DMA-37B DME Interrogator Connector Determinants (cont)
Signal Name
Function
MP2E
---
Spare
---
MP2F
---
Spare
---
MP2G
---
Spare
---
MP2H
---
Spare
---
MP2J
---
Spare
---
MP2K
---
Spare
---
MP3A
Input
Freq/Funct Select Data I/P Port A (A)
MP3B
Input
Freq/Funct Select Data I/P Port A (B)
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.
MP3C
---
Spare
---
MP3D
Input
Freq/Funct Select Data I/P Port A (A)
MP3E
Input
Freq/Funct Select Data I/P Port A (B)
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.
MP3F
---
Spare
---
MP3G
Output DME Distance Data Output No. 2 (A)
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
---
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.
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Table 2001.
Pin
Type
DMA-37B DME Interrogator Connector Determinants (cont)
Signal Name
Function
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
Reset
Resets 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
---
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Table 2001.
Pin
Type
DMA-37B DME Interrogator Connector Determinants (cont)
Signal Name
Function
MP6E
Input
CFDS Data Bus Input A
Low speed ARINC 429 data input port receives
maintenance data from the CFDS/CMC
MP6F
Input
CFDS Data Bus Input B
MP6G
---
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)
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)
MP7J
Output 115V AC Control Panel Power Out
(COLD)
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.
MP7K
---
Spare
---
BP1
Input
115VAC (HOT)
(2A Circuit Breaker)
Primary input power to DMA-37B
BP2
---
---
---
BP3
---
---
---
BP4
---
---
---
BP5
---
---
---
BP6
---
---
---
BP7
Input
115VAC (COLD)
(AC common)
Primary power return
BP8
---
---
---
BP9
---
---
---
115 V ac, 400Hz is available on these pins for
routing to an indicator panel in those installations
which use an individual indicator panel.
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Table 2001.
Pin
DMA-37B DME Interrogator Connector Determinants (cont)
Type
Signal Name
Function
BP10
---
---
---
BP11
Input
Chassis Ground
Chassis ground
BP12
Input/ Suppressor
Output
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.
(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.
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(2) DMA-37B DME Interrogator
(a) The DMA-37B DME Interrogator is installed in the mount as follows:
Slide the DMA-37B into the mount until the guide pins are aligned and the
electrical connectors are firmly engaged.
Secure 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.
Safety-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 Procedures
CAUTION:
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.
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Table 2002.
Inspection/Check Procedures
Equipment
Inspection/Check Procedure
4 MCU Unit Mount
As defined by manufacturer's instructions.
DMA-37B DME Interrogator
1.
2.
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.
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.
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 Required
Table 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 2003.
Description
Table of Test Equipment
Characteristics Required
Transponder and DME
Test Set
Must 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.
Representative Type
Instrument Flight Research
Corp. (IFR) Model ATC-6OOA
or equivalent
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(b) DMA-37B Initiated System Test, -0101, -0202, and -0303 Only
A 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.
The 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.
The Normal-Mode screen (Figure 2001) is displayed for the first second of the
test sequence.
Figure 2001.
Typical Normal Mode Screen
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Figure 2002.
Test in Progress Screen
Once 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.
While in the self-test mode, not pressing either key for five minutes causes the
system to return to the Normal Mode screen (Figure 2001).
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Figure 2003.
Figure 2004.
Test Complete, No Failures Screen
Test Complete, Failures Screen
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(c) Front Panel Test Initiation, -1101 and -1212 Only
On the front panel, observe that the green status LED is lit.
On the front panel, push the self test button.
Make sure that all LEDs turn amber and then turn green (indicating normal
operation).
(d) Cockpit-Initiated System Test
If 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 test
NOTE: The following test instructions are written in general terms. Refer to
the DME test set instruction manual for specific DME test set
operating instructions.
(f)
Set up ramp test set as recommended in accordance with test set
manufacturer's instruction manual. Position DME ramp test set in vicinity of
aircraft.
Apply power to DMA-37B DME System.
If 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.
Set NAV control to select a DME frequency corresponding to that set in the
DME ramp test set.
Verify that the DME distance readout is equal to that set in the DME ramp test
set.
Set DME ramp test set for an audio Ident output.
Verify that the audio Ident is heard through the cockpit speaker.
Repeat steps 4 and 5 for one or more additional frequencies and distances.
Flight Tests
Preflight Test
General
(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.
Test Procedures
(1) Perform the System Test, Cockpit Initiated procedure as described in
Paragraph 3.B.(3)(d) of this section.
In-Flight Confidence Test
General
(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.
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Test 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 Replacement
A. 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 Procedures
A. 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.
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Figure 2005. (Sheet 1). DMA-37B DME Interrogator Dimensional Outline Drawing
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Figure 2005 (Sheet 2). DMA-37B DME Interrogator Dimensional Outline Drawing
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Figure 2005 (Sheet 3). DMA-37B DME Interrogator Dimensional Outline Drawing
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Figure 2005 (Sheet 4). DMA-37B DME Interrogator Dimensional Outline Drawing
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Figure 2006. DMA-37B DME System Interwiring Diagram
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