Honeywell RTA-50D VHFAIRBORNE VOICE / DATA TRANSCEIVER User Manual User s Manual

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User's Manual

Honeywell International Inc.

15001 N.E. 36 Street

Redmond, Washington 98052-5317

U.S.A.

CAGE: 97896

Telephone: (800) 601-3099 (Toll Free U.S.A./Canada)

Telephone: (602) 365-3099 (International Direct)

Telephone: 00-800-601-30999 (EMEA Toll Free)

Telephone: 420-234-625-500 (EMEA Direct)

Web site: www.myaerospace.com

Maintenance Manual

RTA-50D VHF Data Radio System

Part Number CAGE

965-1696-021 97896

965-1696-051 97896

Legal Notice

Export Control

This document contains technical data and is subject to U.S. export regulations. These commodities, technology, or

software were exported from the United States in accordance with the export administration regulations. Diversion contrary

to U.S. law is prohibited.

ECCN: 7E994, NLR Eligible.

23-20-59

Page T-1

Publication Number D201010000047, Revision 0 Initial 1 Mar 2011

©Honeywell International Inc. Do not copy without express permission of Honeywell.

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Proprietary Information Honeywell - Confidential

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6. Term - This License Agreement is effective until terminated as set forth herein. This License Agreement

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WARNING: BEFORE THE MATERIALS CALLED OUT IN THIS PUBLICATION ARE USED, KNOW THE

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CAN RESULT IN PERSONAL INJURY OR DISEASE.

This publication describes physical and chemical processes which can make it necessary to use chemicals,

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materials to be used. The user must know the manufacturer/supplier data and obey the procedures,

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WARNING: HONEYWELL ASSUMES NO RESPONSIBILITY FOR ANY HONEYWELL EQUIPMENT

WHICH IS NOT MAINTAINED AND/OR REPAIRED IN ACCORDANCE WITH HONEYWELL’S

PUBLISHED INSTRUCTIONS AND/OR HONEYWELL’S FAA/SFAR 36 REPAIR AUTHORIZATION.

NEITHER DOES HONEYWELL ASSUME RESPONSIBILITY FOR SPECIAL TOOLS AND TEST

EQUIPMENT FABRICATED BY COMPANIES OTHER THAN HONEYWELL.

WARNING: INCORRECTLY REPAIRED COMPONENTS CAN AFFECT AIRWORTHINESS OR

DECREASE THE LIFE OF THE COMPONENTS. INCORRECTLY FABRICATED SPECIAL TOOLING

OR TEST EQUIPMENT CAN RESULT IN DAMAGE TO THE PRODUCT COMPONENTS OR GIVE

UNSATISFACTORY RESULTS.

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Honeywell is a registered trademark of Honeywell International Inc.

All other marks are owned by their respective companies.

THIS IS THE CMM FOSI - DATE: 20101217

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TRANSMITTAL INFORMATION

THIS IS AN INITIAL RELEASE OF RTA-50D VHF DATA RADIO SYSTEM MM ATA NO. 23-20-59 AND IS

ISSUED FOR USE IN SUPPORT OF THE FOLLOWING:

Table TI-1. Applicable Components

Component PN Nomenclature

965-1696-021RTA-50D VHF Data Radio System

965-1696-051 RTA-50D VHF Data Radio System

Revision History

Table TI-2 shows the revision history of this MM.

Table TI-2. Revision History

Revision Number Revision Date

01 Mar 2011

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RECORD OF REVISIONS

For each revision, write the revision number, revision date, date put in the manual, and your initials in the

applicable column.

NOTE: Refer to the Revision History in the TRANSMITTAL INFORMATION section for revision data.

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RECORD OF TEMPORARY REVISIONS

Instructions on each page of a temporary revision tell you where to put the pages in your manual. Remove

the temporary revision pages only when discard instructions are given. For each temporary revision, put the

applicable data in the record columns on this page.

Definition of Status column: TR can be active, cancelled, or incorporated. If TR is incorporated, list the revision

number. For example, enter: INC Rev 7. If TR is replaced by another TR, then put “Cancelled”. For example:

Cancelled by TR NN-NN. “Active” is entered by the holder of manual.

Date Date

Temporary Put Removed

Revision Page Issue in from

Number Status Number Date Manual By Manual By

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SERVICE BULLETIN LIST

Service Bulletin / Date Put in

Revision Number Title Modification Manual

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Subheading and Page Date Subheading and Page Date

Title

T-1 1 Mar 2011

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Transmittal Information

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TI-2 1 Mar 2011

Record of Revisions

RR-1 1 Mar 2011

RR-2 1 Mar 2011

Record of Temporary Revisions

RTR-1 1 Mar 2011

RTR-2 1 Mar 2011

Service Bulletin List

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SBL-2 1 Mar 2011

List of Effective Pages

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Table of Contents

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Introduction

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Description and Operation

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Fault Isolation

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Maintenance Practices

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TABLE OF CONTENTS
LIST OF SECTIONS
Title Page
INTRODUCTION
1. How to Use This Manual (TASK 23-20-59-99F-801-A01)................................ INTRO-1
A. General (Subtask 23-20-59-99F-001-A01) .......................................... INTRO-1
B. Observance of Manual Instructions (Subtask 23-20-59-99F-002-A01) .......... INTRO-1
C. Symbols (Subtask 23-20-59-99F-003-A01) ......................................... INTRO-1
D. Units of Measure (Subtask 23-20-59-99F-004-A01) ............................... INTRO-4
E. Page Number Block Explanation (Subtask 23-20-59-99F-005-A01) ............. INTRO-4
F. Application of Maintenance Task Oriented Support System
(MTOSS) (Subtask 23-20-59-99F-006-A01) ........................................ INTRO-4
G. Standard Practices Manual (Subtask 23-20-59-99F-007-A01) ................... INTRO-14
H. Electrostatic Discharge (Subtask 23-20-59-99F-008-A01) ........................ INTRO-14
2. Customer Support (TASK 23-20-59-99F-802-A01) ....................................... INTRO-14
A. Honeywell Aerospace Online Technical Publications Web
Site (Subtask 23-20-59-99F-009-A01)............................................... INTRO-14
B. Global Customer Care Center (Subtask 23-20-59-99F-010-A01) ................ INTRO-14
3. References (TASK 23-20-59-99F-803-A01) ............................................... INTRO-14
A. Honeywell/Vendor Publications (Subtask 23-20-59-99F-011-A01) ............... INTRO-14
B. Other Publications (Subtask 23-20-59-99F-012-A01).............................. INTRO-15
4. Acronyms and Abbreviations (TASK 23-20-59-99F-804-A01) ........................... INTRO-15
A. General (Subtask 23-20-59-99F-013-A01) .......................................... INTRO-15
5. Process Verification (TASK 23-20-59-99F-805-A01) ..................................... INTRO-19
A. Verification Data (Subtask 23-20-59-99F-014-A01) ................................ INTRO-19
DESCRIPTION AND OPERATION
1. Description (TASK 23-20-59-870-801-A01) ............................................... 1
A. General (Subtask 23-20-59-870-001-A01) .......................................... 1
B. Job Setup Data (Subtask 23-20-59-99C-001-A01) ................................. 5
C. Purpose of Equipment (Subtask 23-20-59-870-002-A01) ......................... 6
D. Equipment Required but Not Supplied (Subtask 23-20-59-870-003-A01) ....... 7
2. Configurations Available (TASK 23-20-59-870-802-A01) ................................ 7
A. General (Subtask 23-20-59-870-004-A01) .......................................... 7
B. Environmental Certification (Subtask 23-20-59-870-005-A01) .................... 8
3. System Description (TASK 23-20-59-870-803-A01) ...................................... 9
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TABLE OF CONTENTS (Cont)
LIST OF SECTIONS (Cont)
Title Page
A. RTA-50D VDR Data Radio System (Subtask 23-20-59-870-006-A01) ........... 9
B. Description of Equipment (Subtask 23-20-59-870-007-A01) ...................... 10
C. ARINC 716 Data Mode (Subtask 23-20-59-870-008-A01) ........................ 12
D. ARINC 750 Mode A and Mode 2 (Subtask 23-20-59-870-009-A01) ............. 13
4. System Component Description (TASK 23-20-59-870-804-A01) ....................... 14
A. RTA-50D VDR (Subtask 23-20-59-870-010-A01) .................................. 14
B. Other Components in the System (Subtask 23-20-59-870-011-A01) ............ 15
5. Operation (TASK 23-20-59-870-805-A01) ................................................. 15
A. Voice Mode (Subtask 23-20-59-870-012-A01) ..................................... 15
B. Mode 0 Data (Subtask 23-20-59-870-013-A01) .................................... 15
C. Mode A Data (Subtask 23-20-59-870-014-A01) .................................... 16
D. VDL Mode 2 (Subtask 23-20-59-870-015-A01)..................................... 16
E. VDL Mode 3 (Subtask 23-20-59-870-016-A01)..................................... 17
F. VDL Mode 4 (Subtask 23-20-59-870-017-A01)..................................... 18
6. Theory of Operation (TASK 23-20-59-870-806-A01) ..................................... 19
A. VDR Overview (Subtask 23-20-59-870-018-A01) .................................. 19
B. RTA-50D VDR System Architecture (Subtask 23-20-59-870-019-A01) .......... 25
C. RF CCA (Subtask 23-20-59-870-020-A01) ......................................... 29
D. Digital Processor CCA (Subtask 23-20-59-870-021-A01) ......................... 37
E. Front Panel I/O Board (Subtask 23-20-59-870-022-A01) .......................... 45
F. Power Supply (Subtask 23-20-59-870-023-A01) ................................... 45
G. Rear Interconnect (Subtask 23-20-59-870-024-A01) .............................. 45
FAULT ISOLATION
1. Planning Data (TASK 23-20-59-99C-801-A01) ........................................... 1001
A. Reason for the Job (Subtask 23-20-59-99C-002-A01)............................. 1001
B. Job Setup Data (Subtask 23-20-59-99C-003-A01) ................................. 1001
2. Procedure (TASK 23-20-59-810-801-A01) ................................................ 1001
A. Job Setup (Subtask 23-20-59-810-001-A01) ....................................... 1001
B. Functional Self-Test (Subtask 23-20-59-810-002-A01) ............................ 1001
C. RTA-50D VDR Test Results (Subtask 23-20-59-810-003-A01) ................... 1002
D. Job Close-up (Subtask 23-20-59-810-004-A01) .................................... 1005
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TABLE OF CONTENTS (Cont)
LIST OF SECTIONS (Cont)
Title Page
MAINTENANCE PRACTICES
1. Planning Data (TASK 23-20-59-99C-802-A01) ........................................... 2001
A. Reason for the Job (Subtask 23-20-59-99C-004-A01)............................. 2001
B. Job Setup Data (Subtask 23-20-59-99C-005-A01) ................................. 2001
2. Inspection After Unpacking (TASK 23-20-59-000-801-A01) ............................. 2001
A. General (Subtask 23-20-59-000-001-A01) .......................................... 2001
3. Preinstallation Testing (TASK 23-20-59-000-802-A01) ................................... 2001
A. Overview (Subtask 23-20-59-000-002-A01) ........................................ 2001
4. Equipment Changes and Marking (TASK 23-20-59-000-803-A01) ..................... 2002
A. Overview (Subtask 23-20-59-000-003-A01) ........................................ 2002
5. Interchangeability (TASK 23-20-59-000-804-A01) ........................................ 2002
A. Overview (Subtask 23-20-59-000-004-A01) ........................................ 2002
6. Installation (TASK 23-20-59-000-805-A01) ................................................ 2002
A. General (Subtask 23-20-59-000-005-A01) .......................................... 2002
B. Location of Equipment (Subtask 23-20-59-000-006-A01) ......................... 2002
C. Interwiring and Cable Fabrication (Subtask 23-20-59-000-007-A01) ............ 2003
D. Installation of System (Subtask 23-20-59-000-008-A01) .......................... 2008
7. Inspection and System Check Procedures (TASK 23-20-59-000-806-A01) ........... 2009
A. Inspection (Subtask 23-20-59-000-009-A01) ....................................... 2009
B. System Checkout (Subtask 23-20-59-000-010-A01)............................... 2009
C. Flight Tests (Subtask 23-20-59-000-011-A01) ...................................... 2010
8. Removal and Replacement (TASK 23-20-59-000-807-A01)............................. 2010
A. Removal (Subtask 23-20-59-000-012-A01) ......................................... 2010
B. Replacement (Subtask 23-20-59-000-013-A01) .................................... 2011
9. Maintenance Procedures (TASK 23-20-59-000-808-A01) ............................... 2011
A. Adjustments and Alignments (Subtask 23-20-59-000-014-A01) .................. 2011
B. System Protection (Subtask 23-20-59-000-015-A01) .............................. 2011
C. Lubrication Practices (Subtask 23-20-59-000-016-A01) ........................... 2011
D. Cleaning (Subtask 23-20-59-000-017-A01) ......................................... 2011
10. Diagrams (TASK 23-20-59-000-809-A01) ................................................. 2011
A. RTA-50D VDR Diagrams (Subtask 23-20-59-000-018-A01) ...................... 2011
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TABLE OF CONTENTS (Cont)
LIST OF FIGURES
Figure Description Page
INTRO-1 Geometric Tolerance Symbols (GRAPHIC 23-20-59-99B-801-A01) ................ INTRO-2
INTRO-2 Symbols (GRAPHIC 23-20-59-99B-802-A01) ......................................... INTRO-4
INTRO-3 MTOSS Code Positions (GRAPHIC 23-20-59-99B-803-A01) ....................... INTRO-5
1 Typical RTA-50D VDR (GRAPHIC 23-20-59-99B-804-A01) ......................... 5
2 VHF Communications for Voice Operation (GRAPHIC 23-20-59-99B-805-A01) .. 10
3 Module and Assembly Locations (GRAPHIC 23-20-59-99B-806-A01) ............. 11
4 ACARS Audio Interface (GRAPHIC 23-20-59-99B-807-A01)........................ 13
5 RTA-50D VDR External Interfaces (ARINC 750 Mode) (GRAPHIC 23-20-59-
99B-808-A01).............................................................................. 14
6 RTA-50D VDR Interface Context Diagram (GRAPHIC 23-20-59-99B-809-A01) .. 21
7 RTA-50D VDR Internal Architecture (GRAPHIC 23-20-59-99B-810-A01) .......... 27
8 RF CCA (GRAPHIC 23-20-59-99B-811-A01) ......................................... 31
9 Digital Processor CCA Block Diagram (GRAPHIC 23-20-59-99B-812-A01) ....... 39
1001 RTA-50D VDR Front Panel Functional Self-Test Interface (GRAPHIC 23-20-59-
99B-813-A01).............................................................................. 1002
2001 RTA-50D VDR Detail/Interwiring Diagram (GRAPHIC 23-20-59-99B-814-A01) ... 2013
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TABLE OF CONTENTS (Cont)

LIST OF TABLES

Table Description Page

INTRO-1 Page Number Blocks ..................................................................... INTRO-4

INTRO-2 MTOSS Function Code Definitions ...................................................... INTRO-5

INTRO-3 Verification Data ........................................................................... INTRO-20

1 Leading Particulars ....................................................................... 1

2 Equipment Required but Not Supplied .................................................. 7

3 RTA-50D VDR Configurations Available ................................................ 8

4 RTA-50D VDR Features .................................................................. 8

5 RTA-50D VDR Environmental Certification Categories ............................... 8

6 Module and Assembly Designations .................................................... 10

7 Modes of Operation ....................................................................... 12

1001 Front Panel Functional Self-Test Results ............................................... 1002

2001 RTA-50D VDR Communications Transceiver Connector Determinants ............. 2003

2002 Inspection/Check Procedures............................................................ 2009

2003 Initial Control Settings .................................................................... 2010

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INTRODUCTION

1. How to Use This Manual (TASK 23-20-59-99F-801-A01)

A. General (Subtask 23-20-59-99F-001-A01)

(1) This publication gives maintenance instructions for the equipment shown on the Title page.

(2) Standard maintenance procedures that technicians must know are not given in this manual.

(3) This publication is written in agreement with the ATA Specification.

(4) Warnings, cautions, and notes in this manual give the data that follows:

• A WARNING gives a condition or tells personnel what part of an operation or maintenance

procedure, which if not obeyed, can cause injury or death

• A CAUTION gives a condition or tells personnel what part of an operation or maintenance

procedure, which if not obeyed, can cause damage to the equipment

• A NOTE gives data, not commands. The NOTE helps personnel when they do the related

instruction.

(5) Warnings and cautions go before the applicable paragraph or step. Notes follow the applicable

paragraph or step.

B. Observance of Manual Instructions (Subtask 23-20-59-99F-002-A01)

(1) The procedures used must be consistent with standard shop practices and be carefully

examined to make sure that all safety, efficiency, and operation procedures of the unit are

obeyed.

(2) All personnel who operate equipment and do maintenance specified in this manual must know

and obey the safety precautions.

C. Symbols (Subtask 23-20-59-99F-003-A01)

(1) The symbols and special characters are in agreement with IEEE Publication 260 and IEC

Publication 27. Special characters in text are spelled out.

(2) The signal mnemonics, unit control designators, and test designators are shown in capital

letters.

(3) The signal names followed by an “*” show an active low signal.

(4) Some figures in this manual incorporate standard geometric characteristic symbols. Refer to

Figure INTRO-1 for the geometric characteristic symbols.

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Figure INTRO-1. (Sheet 1 of 2) Geometric Tolerance Symbols (GRAPHIC 23-20-59-99B-801-A01)

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Figure INTRO-1. (Sheet 2 of 2) Geometric Tolerance Symbols (GRAPHIC 23-20-59-99B-801-A01)

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(5) The symbols in Figure INTRO-2 show ESDS and moisture sensitive devices.

Figure INTRO-2. (Sheet 1 of 1) Symbols (GRAPHIC 23-20-59-99B-802-A01)

D. Units of Measure (Subtask 23-20-59-99F-004-A01)

(1) Measurements, weights, temperatures, dimensions, and other values are expressed in the

USMS followed by the appropriate SI metric units in parentheses. Some standard tools or

parts such as drills, taps, bolts, nuts, etc., do not have an equivalent.

E. Page Number Block Explanation (Subtask 23-20-59-99F-005-A01)

(1) The data in this manual is divided into sections. A standard page number block system is

used. Page number blocks are shown in Table INTRO-1.

TableINTRO-1. PageNumberBlocks

Section Page Number Block

Description and Operation 1thru999

Fault Isolation 1001 thru 1999

Maintenance Practices 2001 thru 2999

F. Application of Maintenance Task Oriented Support System (MTOSS) (Subtask 23-20-59-

99F-006-A01)

(1) In accordance with the ATA Specification 2200, this publication uses a Maintenance Task

Numbering System which make the maintenance procedures in this manual compatible with

an automated shop environment.

(2) The system uses standard and unique number combinations to identify maintenance tasks

and subtasks.

(3) The MTOSS structure is the logical approach to organizing maintenance tasks and subtasks.

The MTOSS numbering system includes the ATA Chapter-Section-Subject number as well as a

function code and unique identifiers. The purpose of incorporating the MTOSS numbering

system is to give a means for the automated sorting, retrieval, and management of digitized

data.

(4) Section and Subsection Numbering System

(a) All procedures in this publication have TASK and SUBTASK numbers at key data retrieval

points. The numbers give the following:

• Identification of the hardware (parts or parts) primary to the TASK

• Identification of the maintenance function applied to the part or parts

• A unique identifier for a set of instructions (known as TASK or SUBTASK)

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• Identification of alternate methods and configuration differences that change the

procedure applied to the TASK

• Identification of airline changes to a TASK or SUBTASK.

(5) Components of Task and Subtask Number

(a) The numbering system is an expansion of the ATA three-element numbering system. The

number has seven elements. The first five elements are necessary for each TASK or

SUBTASK. The sixth and seventh elements are applied only when necessary. Refer to

Figure INTRO-3.

(b) Elements 1, 2, and 3 identify the ATA Chapter-Section-Subject number of the page block.

position element. The third position is zero filled when further definition is not required. If

required, the manufacturer will use the numbers 1 thru 9 or letters A thru Z, excluding the

letters I and O. Refer to Table INTRO-2.

(d) Element 5 provides a unique identification for each TASK or SUBTASK number which is

similarly numbered through the first four elements as follows:

• TASKS are numbered from 801 thru 999

• SUBTASKS are numbered from 001 thru 800.

(e) Element 6 is a three position alphanumeric element used for identification of differences

in configurations, methods or techniques, variations of standard practice applications, etc.

(f) Element 7 provides coding of those tasks or subtasks that have been changed by the

customer (e.g., those tasks or subtasks accomplished by an outside repair source).

Figure INTRO-3. (Sheet 1 of 1) MTOSS Code Positions (GRAPHIC 23-20-59-99B-803-A01)

Table INTRO-2. MTOSS Function Code Definitions

Code Function Definition

000 REMOVAL AND DISASSEMBLY

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Table INTRO-2. MTOSS Function Code Definitions (Cont)

Code Function Definition

010 Removal Removal of the engine/component from a

workstand, transport dolly, test stand, etc., or

aircraft.

020 Remove Modular Sections This is the first echelon of disassembly which

has sectionalization of the unit/engine into

primary modular sections. Modular sections

are identified by the third element of the ATA

number when removed from the unit/engine.

030 Disassemble Modular Sections This is the second echelon of disassembly

which has disassembly of the modular sections

into subassemblies after removal from the

unit/engine. Modular section designations

appear in the second element of the ATA

number for this echelon of disassembly.

040 Disassemble Subassemblies This is the third echelon of engine disassembly

which has disassembly of subassemblies

to the piece part level. The subassemblies

are identified by the third element of the ATA

number.

050 Remove Accessory/Power Plant Components This has removing individual accessory/power

plant components from either installed or

uninstalled engines.

060 Disassemble Accessory This involves disassembly of accessories

/components into subassemblies.

070 Disassemble Accessory Subassembly This involves disassembly of accessories

/components subassemblies into piece parts.

080 Remove Test Equipment This has removing equipment and

instrumentation after accessory/component

test.

090 Disassemble Support Equipment This has disassembly of support equipment

required to maintain said support equipment.

100 CLEANING

110 Chemical Removal of surface deposits from a part by

use of a chemical cleaning agent. After being

dissolved, the deposit is washed or rinsed away

after a soaking period. Also includes chemical

power flushing.

120 Abrasive Removal of surface deposits from a part by wet

or dry particle impingement.

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Table INTRO-2. MTOSS Function Code Definitions (Cont)

Code Function Definition

130 Ultrasonic Removal of surface deposits and entrapped

material by use of high frequency sound waves

to produce cavitation at the surface of the

part. Cleaning is performed in a liquid bath

that transmits the sound energy and keeps the

removed material in suspension.

140 Mechanical Removal of surface deposits from a part by use

of a brush, felt bob, sandpaper, or other hand

or mechanical action.

150 Unassigned

160 Miscellaneous Removal of deposits from parts with

compressed air, miscellaneous hand cleaning,

and various combinations of cleaning

procedures.

170 Foam/Water Wash Removal of post emulsified fluorescent

penetrant through an agitated water wash,

automatic spray rinse, or an aqueous remover

aeratedtoproduceafoam.

180 Testing of Solutions Test used to assist in identifying certain

materials by electro-mechanically determining

the presence or absence of known constituents.

190 Unassigned

200 INSPECTION

210 Check A thorough visual examination of components,

accessories, subsystems, and piece parts

to detect structural failure, deterioration

or damage and to determine the need for

corrective action. For example: exterior

surfaces, electronic circuit cards, gears, control

systems, linkages, accessories, components,

tubing, wiring and connections, safety wiring,

fasteners, clamps, etc., are inspected to

verify correct condition and acceptability for

continued service.

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Table INTRO-2. MTOSS Function Code Definitions (Cont)

Code Function Definition

220 Visual/Dimensional A comparison of the dimensions and material

conditions of parts, subassemblies, and

assemblies with the specifications contained

in technical manuals and/or blueprints, to

detect deviations from established standard

and limits and determine the acceptability for

continued service, repair, or need to discard

the item. A visual/dimensional function code is

also required to verify that correct corrective

maintenance has been accomplished.

Although some of these tasks do not require

measurements, a complete spectrum of

tasks/sub tasks requires a variety of measuring

equipment to determine runout, concentricity,

flatness, parallelism, hardness, thickness,

clarity, dimensions, etc.

230 Penetrant Fluorescent penetrant inspection to detect

surface cracks.

240 Magnetic Magnetic particle inspection to detect surface

cracks in magnetic materials.

250 Eddy Current Inspection for subsurface cracks, porosity,

inclusions, or other nonhomogeneous

material structure by use of high frequency

electromagnetic wave equipment. Parts are

scanned and compared to similar parts or test

specimens having known material defects.

260 X-Ray Inspection for subsurface cracks, porosity,

inclusions, or other nonhomogeneous material

structure by use of x-ray techniques.

270 Ultrasonic Inspection for subsurface cracks, porosity,

inclusions, or other nonhomogeneous material

structure by use of contact pulse echo

ultrasonic techniques.

280 Special Any special inspection to determine the

integrity of a part for continued operation

In-Service or qualitative analysis.

290 Unassigned

300 REPAIR

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Table INTRO-2. MTOSS Function Code Definitions (Cont)

Code Function Definition

310 Welding and Brazing The joining of pieces by welding (fusion,

resistance, spot, electron beam, plasma arc),

brazing (furnace, torch, induction), or soldering.

This category includes hard facing.

320 Machining The process of obtaining a desired shape or

finish by grinding, turning, boring, reaming,

broaching, milling, drilling, lapping, honing,

sizing, polishing, buffing, cutting, forming,

stamping, blanking, etc.

330 Stripping and Plating Removing or applying a metallic coating on a

surface by mechanical, chemical, or electrical

means. Plating of chromium, cadmium, tin,

etc., to build up the size of a part or supply

surface protection. Includes masking or waxing

before the process.

340 Plasma and Flame Spraying The application of a protective coating to a

part by feeding a powder into an ionized gas

stream. Flame spraying uses a fuel oxygen

flame to melt and propel metal onto parts to

build up the size or supply surface protection.

350 Miscellaneous Repairs Repairing parts by hand (cutting, drilling,

polishing, grinding, lapping, riveting, blending,

routing, fitting, burring, planishing, sanding,

sawing, recambering, drilling, tapping,

heating, chilling) and including miscellaneous

disassembly and assembly required.

360 Bonding and Molding/Sealing Joining and curing of parts with an adhesive or

fusible material (including silicone, fiberglass,

glues).

370 Heat Treating Controlled heating and cooling of a material to

obtain the desired physical property (includes

annealing, tempering, quenching, stress

relieving, solution heat treat, etc.).

380 Surface Treating Treating the surface of a part by painting,

varnishing, aluminizing, Teflon coating, zinc

chromate priming, tumble finishing, shot

peening, etc. Baking and masking processes

are included.

390 Machine Riveting and Flaring Joining of parts by riveting and flaring the rivet.

400 INSTALLATION AND ASSEMBLY

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Table INTRO-2. MTOSS Function Code Definitions (Cont)

Code Function Definition

410 Install Installation of the unit/engine onto a workstand,

transport dolly, test stand, or aircraft.

420 Install Modular Sections The third echelon of assembly consisting of

assembly of the modular assemblies into a

complete unit/engine assembly. The modular

sections are identified by the third element of

the ATA number.

430 Assemble Modular Sections The second echelon of assembly consisting

of assembling subassemblies into modular

sections. The modular section is identified by

the second element of the ATA number.

440 Assemble Subassemblies The first echelon of assembly consisting of

assembling piece parts into subassemblies.

The subassemblies are identified by the third

element of the ATA number.

450 Install/Close Items Removed/Opened for

Access Installation or closing of access plates, closing

of ports, installation of components, tubing

or any item which was removed or opened in

order to supply access to do the task.

460 Assemble Accessory Assemble accessory components.

470 Assemble Accessory Subassembly Assembly of accessory subassembly

components.

480 Install Test Equipment Install equipment and instrumentation required

for accessory component test.

490 Assemble Support Equipment Any assembly required to maintain support

equipment.

500 MATERIAL HANDLING

510 Shipping The movement of any part, subassembly,

assembly, or component from the time it is

packaged until it reaches its destination.

520 Receiving The receipt activity for any incoming part,

subassembly, assembly, or component.

530 Packing Installing parts, subassemblies, assemblies, or

components into shipping containers.

540 Unpacking Removing parts, subassemblies, assemblies,

or components from shipping containers.

550 Storage Safekeeping of parts, subassemblies,

assemblies, or components until required for

use.

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Table INTRO-2. MTOSS Function Code Definitions (Cont)

Code Function Definition

560 Marshaling/Positioning Marshaling is collection of parts,

subassemblies, and accessories before

release for assembly. Positioning is movement

from one fixed state to another.

570 Engine Ferry/Pod Maintenance Necessary preparations before and after

transporting an engine by aircraft ferry method.

580 Unassigned

590 Unassigned

600 SERVICING/PRESERVING/LUBRICATING

610 Servicing Action required to sustain a unit or system in

correct operating status including priming with

applicable fluids before use.

620 Preserving Preparation of a unit, part, assembly, etc.,

for safekeeping from decomposition or

deterioration. Includes preparation for storage

(applying a preservative layer, desiccants, etc.).

630 Depreserving Removing preservatives, desiccants, etc., from

a unit, part, assembly, etc., before installation

or operation.

640 Lubricating Applying oil, grease, dry film, or silicon

lubricants on moving parts to decrease friction

or cool the item.

650 Unassigned

660 Unassigned

670 Unassigned

680 Unassigned

690 Unassigned

700 TESTING/CHECKING

710 Oil Flow Measuring the flow of oil through components

or compartments under specific conditions.

720 Air Flow Measuring the flow of air through components

or compartments under specific conditions.

730 Fuel Flow Function checks and flow measurements

through the part or system being tested.

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Table INTRO-2. MTOSS Function Code Definitions (Cont)

Code Function Definition

740 Water Flow Function checks and flow measurements

through the part or system being tested.

750 Electrical/Return to Service Functional tests (manual or ATE) of the system

or component as well as measurement of

electrical or electronic parameters designed to

determine whether the item can be returned to

service. May include fault isolation procedures

for components that require close correlation

between test results and fault indications.

760 Engine Operation of an engine to establish systems

function or operation under specific conditions

to measure performance.

770 Accessory/Bite Testing of an accessory to make sure of correct

operation or function.

780 Pressure Check Testing to establish the ability of a normally

pressurized component or system to operate

correctly.

790 Leak Check Determine the ability of a component or system

to operate without leaking.

800 MISCELLANEOUS

810 Fault Isolation Operation of an engine at constant thrust

level or identical engine pressure ratio engine

pressure ratio to locate the prime suspect

deficient system operating an incorrectly

functioning system or component to locate

the cause; or performing a series of checks to

isolate a failed part or component.

820 Adjusting/Aligning/Calibrating Makingaphysicalcorrectiontomakesureof

correct placement or operation of a system or

component.

830 Rigging Hooking-up, arranging, or adjusting a

component or accessory linkage for correct

operation.

840 Service Bulletin Incorporation Performing the work specified in the

service bulletin. Provides for identification

of modification tasks at the task level with

subtasks recognizing any functional changes

(chemical, visual/dimensional, cleaning,

machining, etc.) necessary to incorporate the

service bulletin.

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Table INTRO-2. MTOSS Function Code Definitions (Cont)

Code Function Definition

850 Part Number Change/Re-identification Change of part number, application of part

number by transfer, engrave repair number, etc.

860 Unassigned

870 Description and Operation Electrical and mechanical description of the

unit or component. Includes leading particulars,

descriptions, limitations, specifications, and

theory of operation.

880 Approved Vendor Processes Includes processes that can be proprietary and

controlled by a particular manufacturer, or by

nonproprietary and approved for application by

conforming vendors.

890 Airline Maintenance Program (Customer Use)

900 Unassigned

910 Special Equipment Maintenance Identification of tasks to maintain special

support equipment.

920 Standard Equipment Maintenance Identification of tasks to maintain standard

support equipment.

930 Tool Fabrication Includes fabricating any tool for which

procedures to use are included in the manual.

940 Special Tools, Equip, and Consumables Listing Listing of all special tools, standard equipment,

special equipment, and consumables required

to do maintenance on the unit or component.

94A Consumables

94B Special Tools/Non Std Tools

94C Fixtures/Test Equipment

94D Standard Tools

950 Illustrated Parts List (Detailed Parts List) Section of IPL/IPC that contains parts

description and identification in top-down break

down sequence.

960 Illustrated Parts List (Equipment Designation

Index) Section of IPL/IPC that contains equipment

designators cross-referenced to detailed parts

list.

970 Illustrated Parts List (Numerical Index) Section of IPL/IPC that contains an

alphanumeric listing of all parts in the unit

cross-referenced to the detailed parts list.

980 Illustrated Parts List (Alternate Vendor Index) Optional section of IPL/IPC that contains an

alphanumeric listing of all parts in the unit that

have more than one vendor source.

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Table INTRO-2. MTOSS Function Code Definitions (Cont)

Code Function Definition

990 Illustrations, Tables, Front Matter, Etc.

99A Tables

99B Illustrations

99C Front Matter Pageblock (TASK Level MTOSS)

Front Matter Task (Collection of Subtask

MTOSS)

99D Access

99E References

99F General/Introduction

G. Standard Practices Manual (Subtask 23-20-59-99F-007-A01)

(1) Standard cleaning, check, repair, and assembly procedures applicable to multiple models can

be found in a standard practices manual. Refer to Paragraph 3 (TASK 23-20-59-99F-803-A01).

H. Electrostatic Discharge (Subtask 23-20-59-99F-008-A01)

(1) Touch the items susceptible to electrostatic discharge in accordance with MIL-HDBK-263.

Refer to MIL-STD-1686 for definition of the standards and conditions.

2. Customer Support (TASK 23-20-59-99F-802-A01)

A. Honeywell Aerospace Online Technical Publications Web Site (Subtask 23-20-59-99F-009-A01)

(1) Go to the Honeywell Online Technical Publications Web site at (www.myaerospace.com).

• To download or see publications online

• To order a publication

• To tell Honeywell of a possible data error in a publication.

B. Global Customer Care Center (Subtask 23-20-59-99F-010-A01)

(1) If you do not have access to the Honeywell Technical Publications Web site, or if you need to

speak to personnel about non-Technical Publication matters, the Honeywell Aerospace Global

Customer Care Center gives 24/7 customer service to Air Transport & Regional, Business &

General Aviation, and Defense & Space customers around the globe.

• Telephone: 800-601-3099 (Toll Free U.S.A./Canada)

• Telephone: 602-365-3099 (International)

• Telephone: 00-800-601-30999 (EMEA Toll Free)

• Telephone: 420-234-625-500 (EMEA Direct).

3. References (TASK 23-20-59-99F-803-A01)

A. Honeywell/Vendor Publications (Subtask 23-20-59-99F-011-A01)

(1) Related Honeywell publications in this manual are shown in the list that follows:

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• ATA No. 23-20-56 (Pub. No. 012-0797-001), CMM, RTA-50D VHF Data Radio

• Pub. No. A09-1100-004, Standard Repair Procedures for Honeywell Avionics Equipment

Instruction Manual.

B. Other Publications (Subtask 23-20-59-99F-012-A01)

(1) These publications are standard references. Check for latest version of publication.

• The United States GPO Style Manual 2000 (available at http://www.gpoaccess.gov

/stylemanual/browse.html)

• IEEE Std 260, Standard Letter Symbols for Units of Measurement (available from the

American National Standards Institute, New York, NY)

• ASME Y14.38, Abbreviations for Use on Drawings and in Text (available from the American

National Standards Institute, New York, NY)

• ANSI/IEEE Std 91, Graphic Symbols for Logic Functions (available from the American

National Standards Institute, New York, NY)

• H4/H8 CAGE Codes (available at http://www.dlis.dla.mil/cage_welcome.asp)

• IEEE 315/ANSI Y32.2, Graphic Symbols for Electrical and Electronics Diagrams (available

from the American National Standards Institute, New York, NY)

• MIL-HDBK-263, Electrostatic Discharge Control Handbook for Protection of Electrical and

Electronic Parts, Assemblies and Equipment (Excluding Electrically Initiated Explosive

Devices) (Metric) (available from any military standards database)

• MIL-STD-1686, Electrostatic Discharge Control Program for Protection of Electrical and

Electronic Parts, Assemblies and Equipment (Excluding Electrically Initiated Explosive

Devices) (Metric) (available from any military standards database).

4. Acronyms and Abbreviations (TASK 23-20-59-99F-804-A01)

A. General (Subtask 23-20-59-99F-013-A01)

(1) The abbreviations are used in agreement with ASME Y14.38.

(2) Acronyms and non-standard abbreviations used in this publication are as follows.

List of Acronyms and Abbreviations

Term Full Term

A/D analog-to-digital

ACARS airborne communications addressing and reporting system

ACR aircraft communications router

ADC analog-to-digital converter

ADS-B automatic dependent surveillance broadcast

AGC automatic gain control

ALC automatic level control

AM amplitude modulation

AMM aircraft maintenance manual

AMP ampere

ANSI American National Standards Institute

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List of Acronyms and Abbreviations (Cont)

Term Full Term

AOA airborne communications addressing and reporting system over

aviation very-high frequency link control

AOC airline operational communications

ARINC Aeronautical Radio, Incorporated

ASCII American Standard Code for Information Interchange

ASME American Society of Mechanical Engineers

ATA Air Transport Association

ATC air traffic control

ATE automated test equipment

ATN aeronautical telecommunication network

ATR Air Transport Radio

ATSU air traffic services unit

BIT built-in test

BITE built-in test equipment

BOP bit oriented protocol

CCA circuit card assembly

CFDS central fault display system

CMC central maintenance computer

CMM component maintenance manual

CMU communications management unit

CODEC coder-decoder

CPDLC controller pilot data link communication

CSMA carrier sense multiple access

D/A digital-to-analog

DC direct current

DDC digital down converter

DSB-AM double side band-amplitude modulation

DSP digital signal processor

DUC digital up converter

ECC error correction control

ECCN export control classification number

EEPROM electronically erasable programmable read only memory

EMEA Europe, the Middle East, and Africa

ESDS electrostatic discharge sensitive

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List of Acronyms and Abbreviations (Cont)

Term Full Term

EUROCAE Equipment and European Organization for Civil Aviation Equipment

FANS future air navigation system

FM frequency module

FPGA field-programmable gate array

GPO Government Printing Office

GPS global positioning system

HIRF high-intensity radiated field

HPI host port interface

Hz hertz

I/O input/output

ICAO International Civil Aviation Organization

ID identification

IEC International Electrotechnical Commission

IEEE Institute of Electrical and Electronics Engineers

IF intermediate frequency

IPC illustrated parts catalog

IPL illustrated parts list

Kbit kilobit

Kbps kilobyte per second

LED light-emitting diode

LNA low noise amplifier

LO local oscillator

LRU line-replaceable unit

MAX maximum

MCBSP multichannel buffered serial port

MCU micro-controller unit

MHz megahertz

MIC microphone

MIN minimum

MM maintenance manual

MOPS minimum operational performance standard

MSK minimum shift keying

MTOSS maintenance task oriented support system

MU management unit

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List of Acronyms and Abbreviations (Cont)

Term Full Term

MUX multiplexor

Mbit megabit

NA not applicable

NLR no license required

No. number

OEM original equipment manufacturer

OMS on-board maintenance system

PA power amplifier

PC personal computer

PCI peripheral component interconnect

PLL phase-locked loop

PN part number

POA plain old airborne communications addressing and reporting system

PPM parts per million

PS power supply

PTT push-to-talk

Pub. publication

RAM random access memory

RF radio frequency

RTCA Radio Technical Commission for Aeronautics

RTP radio tuning panel

Rx receive

SAW surface acoustical wave

SDI source/destination identifier

SDRAM synchronous dynamic random access memory

SELCAL selective calling

SEU single event upset

SI International System of Units

SINAD signal noise and distortion

SNR signal-to-noise ratio

SPI serial peripheral interface

STDMA self-organizing time division multiple access

TCXO temperature-controlled crystal oscillator

TDMA time division multiple access

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List of Acronyms and Abbreviations (Cont)

Term Full Term

TR temporary revision

Tx transmit

USMS United States Measurement System

UTC universal time coordinated

VCO voltage-controlled oscillator

VDC volt, direct current

VDL very-high frequency data link

VDR very-high frequency data radio

VHF very-high frequency

VSWR voltage standing wave ratio

Vrms volt, root mean square

bps bytes per second

dB decibel

dBm decibel (referenced to one milliwatt)

kHz kilohertz

kbps kilobyte per second

kg kilogram

mW milliwatt

mm millimeter

ms millisecond

5. Process Verification (TASK 23-20-59-99F-805-A01)

A. Verification Data (Subtask 23-20-59-99F-014-A01)

(1) Honeywell does a verification of these technical instructions by performance or by simulation

of the necessary procedures. Performance shows that the procedures were checked by the

use of the manual. Simulation shows that the applicable personnel looked at the procedure

in the manual and that the procedure is technically correct. The dates of verification for

this manual are given in Table INTRO-3.

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Table INTRO-3. Verification Data

Section Method Date

Fault Isolation 1Performance 11 Feb 2011

NOTE:

1Only the TESTING portion of the FAULT ISOLATION section was done by performance.

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DESCRIPTION AND OPERATION

1. Description (TASK 23-20-59-870-801-A01)

A. General (Subtask 23-20-59-870-001-A01)

(1) This section contains a description of the RTA-50D VDR and lists other components required

for system operation.

(2) Refer to Table 1 for the leading particulars.

Table 1. Leading Particulars

Characteristic Specification

Weight 9.0 pounds (4.1 kg)

Length 12.72 to 12.80 inches (323.1 to 325.1 mm)

Width 3.58 inches (90.9 mm)

Height 7.88 inches (200 mm)

Power:

• Receive 20 to 32 VDC 1.5 AMP MAX

• Transmit 8.0 AMP MAX

Frequency range 118.000 to 136.975 MHz

Frequency control Dual ARINC 429 (serial digital) low-speed (13 kbps)

inputs

Channel spacing:

•Allmodes 25 kHz

• DSB-AM voice only 8.33 kHz

Cooling Forced air in accordance with ARINC Specification

600

Transmitter (DSB-AM voice and data)

Output power 25 watts (nominal)

Output impedance 50 ohm

Frequency stability ±0.0005%

Voice modulation level 90% MIN modulation for an input level of 0.25 Vrms

at 1,000 Hz

Voice audio distortion 6% MAX for 30% modulation and 10% MAX for 90%

modulation with a 0.5-volt input and a modulating

frequency from 300 to 2,500 Hz

Voice audio frequency response Flat within 6 dB from 300 to 2,500 Hz

Spurious radiation 118 dB MIN below desired carrier level

Harmonic radiation 60 dB MIN below desired carrier level

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Table 1. Leading Particulars (Cont)

Characteristic Specification

Mode 0 data modulation level 70% modulation MIN for a frequency of 1,000 Hz at

10 dBm level

Mode 0 data input frequency response Flat within 5.5 dB from 600 to 6,600 Hz

Mode 0 data input distortion 9.5% MAX for up to 90% modulation from 600 to

6,600 Hz

Receiver (DSB-AM voice and data)

Sensitivity Greater than 6 dB SINAD for 107 dBm signal

modulated 30% at 1,000 Hz

Input Impedance 50 ohm

Frequency stability ±0.0005%

Selectivity:

• 8.33-kHz channel spacing at 6-dB bandwidth ±2.78 kHz

• 8.33-kHz channel spacing at 60-dB bandwidth ±7.365 kHz

• 25-kHz channel spacing at 6-dB bandwidth ±8 kHz

• 25-kHz channel spacing at 60-dB bandwidth ±17 kHz

Cross modulation Meets requirements of ARINC Characteristic 716,

Section 3.6.4

Intermodulation Meets ICAO Annex 10, RTCA DO-186B, ED-23B

AGC Audio output will vary not more than 3 dB with inputs

of 5 to 100,000 microvolts and not more than 6 dB

to 500 millivolts

Audio output 40 mW MIN into a 600 ohm ±20% resistive load

Audio distortion Total harmonic distortion will not exceed 5% with a

1,000-microvolt input signal modulated 30% at 1,000

Audio frequency response Within6dBfrom300to2,500Hz

Audio output regulation: From a 10-mW reference level into 600 ohms

• Resistive load variations between 450 to 2,400

ohms

Less than 2-dB voltage change

•Re

sistive load variations between 200 to 20,000

ohms

No more than 6 dB voltage change

Undesired responses 80 dB MIN

SELCAL/data output 0.6 Vrms MIN with a 2-microvolt signal modulated

30% at 1,000 Hz into a 600-ohm load

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Table 1. Leading Particulars (Cont)

Characteristic Specification

SELCAL/data response ±2.5 dB from 312 to 1,200 Hz (post-detection

response with respect to 1,000 Hz is ±4.5 dB from

300to6,600Hz)

SELCAL/data distortion 4.5% MAX for a 1,000-microvolt input modulated

30% at 1,000 Hz producing 0.5 Vrms into 600 ohms

Phase shift Audio output does not depart from that of the

positive-going modulation envelope at the receiver

input by more than 30 to +120 degrees with a

1,000-microvolt input signal modulated 30% at 1,000

Transmitter (Mode 2 data)

Output power 17.5 watts (nominal)

Frequency stability ±0.0005%

Modulation D8PSK at 31.5 kilobits/second

Error vector magnitude (distortion) 6% MAX

Adjacent channel emissions Less than 18 dBm in 16 kHz centered ±25 kHz

away from the transmit frequency

Less than 28 dBm in 25 kHz centered ±50 kHz

away from the transmit frequency

Less than 38 dBm in 25 kHz centered ±100 kHz

away from the transmit frequency

Less than 48 dBm in 25 kHz centered ±400 kHz

away from the transmit frequency

Less than 53 dBm in 25 kHz centered ±800 kHz or

greater away from the transmit frequency

Spurious emissions Meets requirements of RTCA DO-281A and

EUROCAE ED-92A

Harmonic spurious emissions Meets requirements of RTCA DO-281A and

EUROCAE ED-92A

Mode 2 data input physical interface ARINC 429 high-speed bus

Mode 2 data input protocol In accordance with ARINC 750-3, Attachment 10

Receiver (Mode 2 data)

Sensitivity Less than 0.001 uncorrected bit error rate for 98

dBm received signal

Frequency stability ±0.005%

Selectivity (25-kHz channel) Less than 44-dB adjacent channel rejection

Interference rejection Meets requirements of RTCA DO-281A and

EUROCAE ED-92A

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Table 1. Leading Particulars (Cont)

Characteristic Specification

Intermodulation performance Meets requirements of RTCA DO-281A and

EUROCAE ED-92A

Mode 2 data output physical interface ARINC 429 high-speed bus

Mode 2 data output protocol In accordance with ARINC 750-3, Attachment 10

Tuning time 100 ms MAX

(3) Refer to Figure 1 for a typical RTA-50D VDR.

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Figure 1. (Sheet 1 of 1) Typical RTA-50D VDR (GRAPHIC 23-20-59-99B-804-A01)

B. Job Setup Data (Subtask 23-20-59-99C-001-A01)

(1) The list that follows identifies Honeywell publications that are related to this section:

• Not applicable.

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C. Purpose of Equipment (Subtask 23-20-59-870-002-A01)

(1) The RTA-50D VDR system is an airborne VHF communications transceiver that provides voice

and data communication between on-board aircraft systems, other aircraft systems, and

ground-based systems. It can operate in analog DSB-AM analog voice mode, VHF ACARS

data modes (Mode A and Mode 0), and VDL Mode 2 data mode. It also provides future support

for VDL Mode 3 digital voice and data modes.

(2) The RTA-50D VDR agrees with the standards and specifications for VHF radios that operate in

the 118 to 137-MHz band as follows:

• ARINC 716-11 airborne VHF communications transceiver

• ARINC 750-4 airborne VHF data radio

• EUROCAE ED-23B minimum performance specification for airborne VHF communications

equipment operating in the frequency range 117,975 to 137,000 MHz

• EUROCAE ED-92A MOPS for airborne VDL Mode 2 transceiver operating in the frequency

range 118-136.975 MHz

• RTCA DO-186B MOPS for airborne radio communications equipment operating within the

radio frequency range 117.975 to 137.000 MHz

• RTCA DO-207 MOPS for devices that prevent blocked channels used in two-way radio

communications due to unintentional transmissions

• RTCA DO-281A MOPS for aircraft VDL Mode 2 transceiver physical, link and network layer.

(3) The RTA-50D VDR operates as a voice transceiver that agrees with the voice mode defined

in ARINC Characteristic 716 when operated as a 716 voice radio. Microphone audio and

PTT audio are inputs and side-tone audio is output. The RF signal is double sideband AM.

Frequency and channel bandwidth selection is made through a low-speed ARINC 429 bus

input interface to an RTP.

(4) The RTA-50D VDR operates as a transceiver when used as a 716 data radio. In this mode, it

agrees with the external data modem interface defined in ARINC Characteristic 716. The data

modem audio input, data key-line input, and data modem audio output interface to an ACARS

MU. The ACARS data modem audio input and output are 2,400-bps MSK modulated signals.

The RF signal is a double sideband AM-MSK signal. Channel frequency selection is made

through a second low-speed ARINC 429 bus input interface to the ACARS MU.

(5) The data modem audio output can be wired to a SELCAL decoder when the radio is not wired

to support 716 data mode operation. In ARINC 750 Data Mode A, the RTA-50D VDR provides

2,400-bps MSK modem functionality within the radio with ARINC 429 digital data input/output

interfaces to a CMU as defined in ARINC Characteristic 750. The command and data transfer

protocol between the VDR and CMU uses the ARINC 429 Williamsburg BOP Version 1 or

Version 3. The RF signal is a double sideband AM-MSK signal. Channel frequency selection is

made through the ARINC 429 interface to the CMU.

(6) When operated in Mode 2, the VDR supplies Mode 2 functionality defined in ARINC

Characteristic 750 and a 31,500-bps D8PSK modem functional internal to the radio. The Mode

2 radio uses ARINC 429 digital data input/output interfaces to a CMU as specified in ARINC

Characteristic 750. The command and data transfer protocol between the VDR and CMU uses

the ARINC 429 Williamsburg BOP Version 3. The RF signal is a D8PSK-modulated RF carrier.

Channel frequency selection is made through the ARINC 429 interface to the CMU.

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(7) The RTA-50D VDR system requires an antenna for its RF inputs and outputs, a control head or

radio management panel, an audio input source and output sink for its analog voice functions,

and an ACARS MU or a CMU for its digital control and data functions. The VDR system can

also be connected to a CMC to transfer maintenance data. To give future support for VDL

Mode 3 data and enhanced voice features, the RTA-50D VDR requires interface to two sources

of aircraft ICAO address such as Mode S transponder Number 1 and Number 2.

(8) When operated in voice mode, the RTA-50D VDR supplies both 25-kHz and 8.33-kHz channel

spacing to meet European airspace requirements. The unit is fully interchangeable with

older ARINC 716 communications equipment for backward compatibility. Older equipment

includes the former Allied Signal or Bendix RTA-44A, RTA-44D, and RTA-83B VHF radios,

and Collins VHF 700 and VHF 700A radios.

D. Equipment Required but Not Supplied (Subtask 23-20-59-870-003-A01)

(1) Table 2 lists the equipment required for the RTA-50D VDR system that is not supplied

by Honeywell.

Table 2. Equipment Required but Not Supplied

Equipment Description

Power source: DC power supply of 27.5 volts

• Receive 1.5 AMP

• Transmit 8AMP

Audio distribution system Audio system with an input impedance of 200 to 10,000 ohms

Control panel Provides remote control of frequency selection for 25-kHz or 8.33-kHz

channel spacing system operation (serial digital ARINC 429-7 and

ARINC 716 Supplement 8), power on/off, volume, and squelch control in

accordance with ARINC 716

MU/CMU/ATSU Provides control and data source/sink when operating in the 750 data mode

Mount Provides a means of mounting RTA-50D VDR in the aircraft

VHF antenna Capable of receiving and transmitting VHF signals over a frequency range

of 118.000 to 136.975 MHz.

Microphone 150-ohm impedance microphone (either carbon or transistor) operating

from approximately 16-volt power supply

Cables and connectors Necessary connectors and cables

2. Configurations Available (TASK 23-20-59-870-802-A01)

A. General (Subtask 23-20-59-870-004-A01)

(1) Table 3 lists the available configurations of the RTA-50D VDR and the features contained in

each configuration. Table 4 contains a brief description of each feature.

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Table 3. RTA-50D VDR Configurations Available

8.33-kHz

Channel

Spacing ACARS Mode A Mode 2

Airbus

CFDS

/CMC Boeing

CMC

965-1696-021X X X X X

965-1696-051 X X X X X

Table 4. RTA-50D VDR Features

Description

118.000 to 136.975 MHz operation

8.33-kHz and 25-kHz channel spacing

ICAO Annex 10 FM immunity

ACARS MSK (Mode A) data link function

VDL Mode 2 (D8PSK) data link function

Growth function to VDL Mode 3 digital voice and data transmission

Growth function to single-channel VDL Mode 4 data for data link communications applications only

Dual ARINC 429 tuning interfaces

CMC/CFDS maintenance system interface

200-ms power interrupt transparency

DO-160E environmental test compliant

HIRF protection

Lightning protection (Level 3)

35-second stuck mike protection and protection disable circuitry

RS-232 PC maintenance port

B. Environmental Certification (Subtask 23-20-59-870-005-A01)

(1) The RTA-50D VDR communications transceiver meets the environmental conditions

of the RTCA DO-160E, Environmental Conditions and Test Procedures for

Airline Electronic/Electronical Equipment and Instruments. The environmental

certification categories of the RTA-50D VDR, PN 965-1696-021 and -051, are

[(A2)(D2)Z]BAE[RB1]XXXXXXZAAZ[CC][RR]M[ZZZZZ]XXA. Refer to Table 5.

Table 5. RTA-50D VDR Environmental Certification Categories

Test PN 965-1696-021 PN 965-1696-051

Temperature and altitude A2D2 A2D2

In-flight loss of cooling Z (18 hours) Z (18 hours)

Temperature variation B B

Humidity A A

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Table 5. RTA-50D VDR Environmental Certification Categories (Cont)

Test PN 965-1696-021 PN 965-1696-051

Operational shocks and crash safety E E

Vibration RB1 RB1

Explosion proofness X X

Waterproofness X X

Fluids and susceptibility X X

Sand and dust X X

Fungus resistance X X

Salt spray X X

Magnetic effect Z Z

Power input A A

Voltage spike A A

Audio frequency conducted susceptibility - Power inputs Z Z

Induced signal susceptibility CC CC

Radio frequency susceptibility (radiated and conducted) RR RR

Emission of radio frequency energy M M

Lightning induced transient susceptibility ZZZZZ ZZZZZ

Lightning direct effects X X

Icing X X

Electrostatic discharge A A

3. System Description (TASK 23-20-59-870-803-A01)

A. RTA-50D VDR Data Radio System (Subtask 23-20-59-870-006-A01)

(1) The items that follow are necessary for the RTA-50D VDR:

• An antenna for RF input and output

• A control head or radio management panel for voice/data mode and voice channel selection

• An audio input source and output destination for voice functions, and/or a data link input

source and output destination for data link functions.

(2) The RTA-50D VDR can also transfer maintenance data to an on-board maintenance system.

(3) Three VHF radios are necessary for typical commercial air transport aircraft installations. Two

radios are for voice communications. The third radio is for data communications and for voice

communications when the other radios do not work. Refer to Figure 2.

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Figure 2. (Sheet 1 of 1) VHF Communications for Voice Operation (GRAPHIC 23-20-59-99B-805-A01)

B. Description of Equipment (Subtask 23-20-59-870-007-A01)

(1) Refer to Table 6 for a list of all modules and assemblies in the unit. Refer to Figure 3 for the

location of the modules and assemblies.

Table 6. Module and Assembly Designations

PN Module/Assembly

700-1768-002 Rear interconnect assembly

700-1782-001 Main processor assembly

700-1854-001 Front panel assembly

710-0361-001 Power supply assembly

722-4444-006 RF transceiver module

722-4445-006 Main processor module

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Table 6. Module and Assembly Designations (Cont)

PN Module/Assembly

722-4446-002 Front panel module

722-4576-003 DC to DC converter

722-4577-005 Power supply output module

722-4600-004 Rear interconnect module

722-4767-001 Power supply input module

727-0008-001 RF transceiver assembly

965-1696-051 Final assembly

Figure 3. (Sheet 1 of 1) Module and Assembly Locations (GRAPHIC 23-20-59-99B-806-A01)

(2) Electrical Description

(a) The RTA-50D VDR provides high-speed data link communications as well as voice and

data modes. The RTA-50D VDR can provide for future Mode 3 operation which requires

digital voice and data transmission at the same time, or Mode 4 data link only.

(b) When in voice mode, the RTA-50D VDR provides both 25-kHz and 8.33-kHz channel

spacing to meet European airspace requirements. The unit can be interchanged

with older ARINC 716 communications equipment such as the former AlliedSignal or

Bendix RTA-44A, RTA-44D, and RTA-83B VHF radios, and Collins VHF 700 and VHF

700A radios.

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VDL Modes A and 2, and can provide future VDL Mode 3 digital voice and data, and

single-channel VDL Mode 4 data services.

(d) Refer to Table 7 for the modes of operation supported by the RTA-50D VDR.

Table 7. Modes of Operation

Mode Modulation

Scheme Channel

Spacing Access

Scheme Data Rate

(bits/sec) User Traffic

Type Interface

Voice DSB-AM 25/8.33 kHz PTT NA Voice audio Analog audio

Mode 0 data DSB-AM

MSK 25 kHz CSMA 2,400 ACARS

(POA) Analog audio

Mode A data DSB-AM

MSK 25 kHz CSMA 2,400 ACARS

(POA) A429

Mode 2 data D8PSK 25 kHz CSMA 31,500 Simultaneous

ACARS and

ATN data

A429

Mode3voic

and data 1D8PSK 25 kHz TDMA 31,500 Simultaneous

ACARS and

ATN data

Analog audio

and A429

Mode4data

12 GFSK 25 kHz TDMA 19,200 ATN data A429

NOTES:

1Requires software upgrade.

2May also require hardware modifications.

C. ARINC 716 Data Mode (Subtask 23-20-59-870-008-A01)

(1) In ACARS, the VDR system is a simple transceiver with an analog interface to the ACARS MU.

RefertoFigure4.

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Figure 4. (Sheet 1 of 1) ACARS Audio Interface (GRAPHIC 23-20-59-99B-807-A01)

D. ARINC750ModeAandMode2 (Subtask 23-20-59-870-009-A01)

(1) Figure 5 illustrates the same interfaces when the radio is operating in ARINC 750 Mode with a

compatible CMU, ACARS MU, or ATSU. This wiring configuration would be used for Mode

A and Mode 2 operation. The Mode A and Mode 2 VDR can be installed in an ARINC 716

configuration if Mode A and Mode 2 operation is not required.

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Figure 5. (Sheet 1 of 1) RTA-50D VDR External Interfaces (ARINC 750 Mode) (GRAPHIC 23-20-59-

99B-808-A01)

4. System Component Description (TASK 23-20-59-870-804-A01)

A. RTA-50D VDR (Subtask 23-20-59-870-010-A01)

(1) The VDR is a VHF transmitter-receiver that provides modulation for double-sideband amplitude

modulation for analog voice/data operation in the 25-kHz or 8.33-kHz spaced channels of the

118.000 to 136.975 MHz. Frequency is provided through a serial-digital format in accordance

with ARINC Specification 429.

(2) The VDR is completely solid-state and is housed in a 3MCU case in accordance with ARINC

Characteristic 600. A handle is located on the front panel of the VDR to facilitate installation,

removal, and transport of the VDR.

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(3) The VDR uses a low insertion force, Size 1 shell ARINC 600 rear panel connector with two

inserts. The middle insert is used for aircraft interconnections and the bottom insert is used for

input power and coaxial antenna connectors. The keying pins are set to index pin code 04.

(4) Forced air cooling, in accordance with ARINC Specification 600, is required for cooling the

VDR.

(5) Three front panel LEDs provides visual indication of real-time BITE status as follows:

• Internal fault status monitoring

• External controller status

• External antenna status.

(6) One front panel push-button switch allows activation of manual self-test.

(7) The VDR is partitioned into five subassemblies as follows:

• Front panel module

• Main processor module

• Power supply module

• Rear interconnect module

• RF module.

B. Other Components in the System (Subtask 23-20-59-870-011-A01)

(1) Other VDR system components are not supplied by Honeywell. Information on these units

must be obtained from their respective manufacturers.

5. Operation (TASK 23-20-59-870-805-A01)

A. Voice Mode (Subtask 23-20-59-870-012-A01)

(1) In voice mode, the RTA-50D VDR supports simplex PTT communications in any of the

760 channels with 25-kHz spacing or 2,280 channels with 8.33-kHz spacing in the 118

to 136.975-MHz range.

(2) DSB-AM is used for voice communications where the voice audio from the microphone

modulates the VHF carrier frequency. The spectrum required for this type of modulation is less

than 7 kHz. When operating in a 25-kHz channel, the excess bandwidth of the channel is used

as a guard band to reduce emissions into adjacent channels.

(3) Voice channel selection is controlled from the flight deck by a radio tuning panel. In installations

where a radio can be used in either voice or data mode, voice and data can be set from the

flight deck by the radio tuning panel.

B. Mode 0 Data (Subtask 23-20-59-870-013-A01)

(1) Mode 0 and Mode A support data link communications that use protocols now called POA.

POA uses ASCII character-oriented message formats and protocols to ensure end-to-end

error-free delivery of messages. The difference between these two modes is the interface to

the source and destination of the POA messages.

(2) Mode 0 connects to a legacy ARINC 724 or 724B ACARS MU or CMU through an analog

audio interface. Data is transmitted between the MU/CMU and VDR units at a rate of 2,400 bits

each second by MSK modulated audio signals. The MSK audio modem is in the MU or CMU.

The MSK audio signal produced by the modem is a 1,200 or 2,400-Hz tone that indicates if the

polarity of the transmitted data bit is the same as the previous bit or is different.

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(3) The 1,200 or 2,400-Hz tones sent by the MU or CMU modulate the amplitude of the VHF

carrier generated by the VDR. This modulated signal is a DSB-AM signal whose amplitude is

modulated at 2,400 bps. The MU/CMU controls the access to the channel and initiates the

transmission of a message by a data key line discrete input to the VDR. The MU/CMU also

controls the data link channel selection through one of the low-speed (13 Kbps) ARINC 429

tuning inputs. Mode 0 operation is backward compatible with legacy ARINC 716 radios.

C. Mode A Data (Subtask 23-20-59-870-014-A01)

(1) Mode A allows the RTA-50D VDR to exchange downlink and uplink POA data messages with

an Airbus ATSU or an ARINC 758 CMU through a transmit/receive pair of 100 Kbps ARINC

429 digital interfaces instead of the analog audio interfaces used by Mode 0.

(2) The downlink message data bits transferred to the VDR modulate the RF carrier at a rate of

2,400 bps using the same DSB-AM MSK modulation scheme used in Mode 0. The difference

is that the MSK modem functionality resides in the RTA-50D VDR.

(3) The VDR also controls when to access the channel to transmit data. The channel access

protocol is the same CSMA employed by the MU/CMU in Mode 0 operation. The data link

channel selection is still controlled by the ATSU/CMU, but channel selection messages are

exchanged through the same high-speed ARINC 429 interface used to exchange POA

messages which simplifies wiring.

D. VDL Mode 2 (Subtask 23-20-59-870-015-A01)

(1) The newest VHF data link communication mode is VDL Mode 2. VDL Mode 2 is the term

used to describe a suite of air/ground protocols that increases the data rate of the air/ground

link to 31,500 bps.

(2) VDL Mode 2 allows the transition from character-oriented ACARS protocols for end-to-end

delivery of messages to one that uses bit-oriented ATN protocols using the same VHF ground

and aircraft radios. The RTA-50D VDR Mode 2 capability supports the transmission and

reception of standard ACARS messages such as those generated by FANS A and FANS 1

applications using a protocol referred to as AOA.

(3) The RTA-50D VDR Mode 2 capability also supports the transmission and reception of

bit-oriented ATN application messages such as CPDLC. The delivery of FANS A over AOA

and CPDLC over ATN/VDL Mode 2 is supported concurrently. The set of VDL Mode 2

protocols consist of the physical layer protocol, channel access protocol, data link service and

management protocol, and Mode 2 network access protocol. The physical layer protocol

includes the modulation, data rate, and forward error correction techniques used to transmit

data over the air/ground link.

(4) The channel access protocol is the method that allows multiple aircraft to communicate

with the ground stations on the same frequency. The data link service and management

protocol includes procedures to establish, maintain and hand-off an air/ground link, and ensure

error-free delivery of messages. The network access protocol is the interface between users

and the Mode 2 air/ground link service providers. As in Mode A, only the physical layer and

channel access protocols are performed by the RTA-50D VDR while the data link service and

management, and the network access protocols are performed by the CMU.

(5) The VDL Mode 2 physical layer protocol employs a bit transmission rate of 31,500 bps over

the air/ground link on a single 25-kHz channel. The increased utilization of the 25-kHz

channel is achieved by use of a bandwidth modulation scheme known as D8PSK. A D8PSK

transmitter transmits a carrier whose phase is modulated by the data. The phase can be 0, 45,

90, 135, 180, 225, 270, or 315 degrees. The rate at which the carrier phase is changed is

the modulation rate.

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(6) The phase difference or D8PSK symbol between successive phase changes can be equal

to 0, 45, 90, 135, 180, 225, 270, or 315 degrees. Since there are eight possible phase

differences, each phase change (D8PSK symbol) represents three bits of information: 000,

001, 011, 010, 110, 111, 101, or 100.

(7) For example, if the phase changes at a 10.5-kHz rate, the bit transmission rate is equal to 31.5

Kbps. The VDL Mode 2 D8PSK modulator uses the bits in the message, three at a time, to

select the carrier phase change at a rate of 10,500 D8PSK symbols each second. A 10.5-kHz

D8PSK phase modulation rate corresponds to a D8PSK bit transmission rate of 31.5 Kbps.

(8) The VDL Mode 2 channel access protocol is CSMA modified to let all terminals to have

equal chances to access the channel when multiple terminals have data to transmit. The

ability to optimize the CSMA protocol is included in the VDL Mode 2 channel access protocol

specification.

(9) As in Mode A, the Mode 2 data link channel selection is controlled by the ATSU/CMU through

the same high-speed ARINC 429 interface used to exchange downlink and uplink AOA or

ATN messages. The ATSU/CMU also dynamically controls the switching between Mode

A and Mode 2 operation subject to available coverage. Since the VDL Mode 2 data rate

and modulation scheme differ from those used in Mode A, separate VHF frequencies and

ground-based VHF equipment must be used to give POA and AOA/ATN service coverage. As a

result, the availability of high-speed AOA service depends on the availability of ground stations.

E. VDL Mode 3 (Subtask 23-20-59-870-016-A01)

(1) VDL Mode 2 is a data link protocol that has been optimized for efficient delivery of as much

data traffic as possible within a 25-kHz channel assignment and with radio transmitters limited

to 15 watts output power. It requires dedicated 25-kHz channel assignments. However, there

is also a need to increase the number of VHF channels available in the 118 to 137-MHz

band. To provide for additional voice and data channels, the FAA is developing a VHF digital

transmission mode known as VDL Mode 3.

(2) The RTA-50D VDR has been designed to support VDL Mode 3 voice and data operation

through a software upgrade. Although VDL Mode 3 functionality is not available in the current

FAA ground stations, a prototype software upgrade to the RTA-50D VDR has proven the

functionality with FAA VDL Mode 3 test ground stations.

(3) VDL Mode 3 takes a 25-kHz frequency assignment and breaks it up into 120-ms frames with

four time slots of 30-ms duration each. Each time slot is a different channel. Each channel

(frequency and time slot) can be assigned for use by a different ATC sector. The selection of

which VDL Mode 3 frequency and time slot to use is initially performed by the Pilot using a

radio control panel in the same way 25-kHz or 8.33-kHz channel selection is now performed.

Frequency division into time slots (channels) and the assigned use of the channels (slots) to

differentsectorsiscalledTDMA.Theslotscanbeusedtotransmitpacketsofdigitizedvoiceor

data sized to fit in the appropriate time slot.

(4) VDL Mode 3 uses TDMA to allow access to multiple voice and data users on the same 25-kHz

frequency assignment. VDL Mode 3 ground stations can be configured to support different

combinations of voice and data services.

(5) VDL Mode 3 ground stations can be configured so that each of the four time slots is assigned

to voice traffic only (4V configuration). Slot use can be assigned to a different sector. When an

aircraft enters a sector that has been assigned a particular frequency and time slot (channel),

the Pilot can select the appropriate channel on the radio control panel.

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(6) The aircraft radio would then tune to the frequency associated with the channel and would

look for an uplink from the sectors ground station to synchronize its receive time slot clocks

with those of the ground station. VDL Mode 3 ground stations transmit management burst

uplinks in their allocated time slots to allow aircraft to synchronize their clocks. If the aircraft

does not receive any uplink transmissions from the ground station, it cannot synchronize its

clock and communication with the ground is not possible.

(7) When the aircraft is synchronized with the ground station, voice communications between the

aircraft and the ground station on the selected time slot can proceed. When operating in VDL

Mode 3, voice communications is initiated with a “listen before PTT” procedure. When the VDL

3 radio uses a selected time slot, all digital voice traffic received on the selected time slot is

sent to the radio speaker. Voice traffic received on any other time slot is discarded.

(8) VDL Mode 3 ground stations can be also be configured so that two time slots are used for

voice traffic and two used for data traffic (2V/2D configuration). Each sector is assigned a voice

and a data channel pair. When the airborne radio is tuned to a sector’s voice channel, it also

automatically tunes to the sectors data channel. If the ground station supports data services

in addition to basic voice services as indicated in its management bursts, the radio sends a

net entry request message to the ground station on the selected time slot to gain access to

the data services. When the VDL Mode 3 ground station receives a net entry request, a net

response message is sent to the aircraft to configure access.

(9) The net entry request message includes the 24-bit ICAO identifier assigned to the aircraft. To

support the enhanced features, VDL Mode 3 radios require access to a source of ICAO ID

such as the Mode S transponder.

(10) Downlink data transmission on the data channel is sent on slots reserved by the ground station

for exclusive use by the aircraft. Reservation request messages can be sent by the aircraft

using either slotted aloha random access protocol or in response to polling from the ground

station. The maximum number of contiguous slots requested is 15.

(11) The 2V/2D configurations require the airborne VDR to process voice audio and data link

traffic simultaneously. For example, while the VDR outputs received voice audio or digitizes

and compresses transmit voice audio, it must also process and deliver received uplink data

messages or accept and transmit downlink data messages. As a result, the processing load is

significantly higher than that required for operation in a voice-only or data-only mode.

(12) Like VDL Mode 2, VDL Mode 3 uses D8PSK modulation at a bit transmission rate of 31,500

bps to deliver digitized and compressed speech as well as data messages. Note that VDL

Mode 3 requires that the modulation rate have an accuracy of ±5 PPM, where VDL Mode 2

requires a modulation rate accuracy of ±50 PPM. As a result, VDL Mode 3 requires transmitter

clocks that are 10 times more accurate than VDL Mode 2. The greater accuracy is needed to

provide aircraft at the edges of the coverage area to maintain time slot synchronization with the

VDL Mode 3 ground station. This synchronization ensures that transmissions from aircraft at

the edge of the coverage area do not interfere with transmissions in adjacent time slots.

(13) VDL Mode 3 operation requires radio management panels to have the capability to select the

VDL 3 channel as well as to support unique enhanced voice services.

F. VDL Mode 4 (Subtask 23-20-59-870-017-A01)

(1) VDL Mode 2 provides data link throughput and VDL Mode 3 provides communications capacity

enhancements and simultaneous voice and data communications. VDL Mode 4 provides both

broadcast surveillance applications and air/ground data link communications. The surveillance

application supported by VDL Mode 4 allows aircraft to periodically broadcast their position and

monitor and display the position of other similarly equipped aircraft.

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(2) VDL Mode 4 subdivides each 25-kHz channel into periodic slots of 13.33-ms duration to

allow short periodic transmissions from many aircraft. VDL Mode 3 requires each aircraft to

synchronize its TDMA slot timing to that of a ground station. VDL Mode 4 stations synchronize

their TDMA slot timing to UTC derived from a source such as GPS.

(3) VDL Mode 4 uses a slot reservation protocol that allows VDL Mode 4 stations to access the

network and assure that ADS-B transmission will not be interfered with, without the need for

coordination through a ground station. The access protocol used by VDL Mode 4 is STDMA.

(4) VDL Mode 2 and VDL Mode 3 operate in simplex mode; that is, they operate in either

transmit or receive mode on the same frequency. ADS-B operation over VDL Mode 4,

requires concurrent transmission and reception on two different frequencies. Use of VDL

Mode 4 for both ADS-B surveillance and applications and for data link applications requires

concurrent transmission and reception on three different frequencies. If VDL Mode 4 is used

only for data link communications, transmission and reception on only one frequency at a

time is required. As a result the required applications determine the type of radio required

to support VDL Mode 4.

6. Theory of Operation (TASK 23-20-59-870-806-A01)

A. VDR Overview (Subtask 23-20-59-870-018-A01)

(1) The RTA-50D VDR is an airborne VHF radio whose function is to provide aircraft with

line-of-sight air/ground ATC voice and AOC data communications capability in the 118 to

136.975-MHz VHF frequency band. The RTA-50D VDR is capable of operating in DSB-AM

analog voice mode, VHF ACARS data modes (Mode A and Mode 0), and VDL Mode 2 data

mode.

(2) A typical aircraft installation consists of two VDRs dedicated for ATC voice communications

and one VDR for data link communications and back up voice communications. Each VDR

interfaces to its own dedicated VHF blade antenna so that simultaneous operation of all

threeVDRsispossible.

(3) Figure 6 shows the interfaces between the RTA-50D VDR and other avionics equipment.

NOTE: Figure 6 also shows the inputs and outputs that are processed in each of the

modes of operation. Interfaces that apply to typical new aircraft installations are

shown as solid lines. Interfaces that apply to legacy retrofit DSB-AM voice-only

installations that do not require VDL Mode A or VDL Mode 2 functionality are

shown as dashed lines.

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Figure 6. (Sheet 1 of 2) RTA-50D VDR Interface Context Diagram (GRAPHIC 23-20-59-99B-809-A01)

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Figure 6. (Sheet 2 of 2) RTA-50D VDR Interface Context Diagram (GRAPHIC 23-20-59-99B-809-A01)

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(4) Voice Communications Installations

(a) Each VHF radio is controlled through one or two RTPs. The RTA-50D VDR provides

ARINC 429 interfaces to two RTPs. A discrete input labeled "frequency port select input"

is used to determine which of the two RTP inputs controls the operation of the VDR.

The contents of the ARINC 429 words received from the RTP are used by the VDR to

determine the voice channel (frequency) selected, as well as the type of voice channel:

• DSB-AM voice with 8.33-kHz channel spacing

• DSB-AM voice with 25-kHz channel spacing.

(b) An analog audio input and output pair provide the interfaces to the microphone and

speakers. A discrete input labeled PTT provides the means to switch between

transmit and receive operation. When the VDR is operating in transmit mode (PTT is

grounded), the transmitted audio is output to the Rx audio/side-tone output port. The

Rx audio/side-tone output is muted during transmit operation if an internal VDR failure

prevents the radio from transmitting RF.

interface protocols are supported as follows:

• Airbus CMC/CFDS protocol

• Boeing CMC protocol.

(d) However, only one of the OMS interface protocols is supported at a time, depending on

the software version loaded (VDR part number).

(5) Data Link Communications Installations

(a) Data link capable installations can support data communications only or they can be

wired to support both data and voice communications. When supporting voice and data

communications, one or two RTPs provide the means to select the mode of operation

(voice or data) and the means to select the voice channel. The mode of operation is

determined from the contents of the ARINC 429 words received from the RTP or from a

discrete input labeled "voice/data select input" depending on the aircraft installation.

(b) The RTA-50D VDR provides ARINC 429 data link interfaces to a CMU, ATSU, or ACR

which is the source of the transmitted data messages and the destination of the received

data messages. A second CMU, ATSU, or ACR may be operated in standby mode if the

aircraft installation supports ATC data link communications.

the particular data-only mode is determined from the presence or absence of ARINC 429

data on the ARINC 429 data link interfaces to the two CMUs/ATSUs/ACRs.

B. RTA-50D VDR System Architecture (Subtask 23-20-59-870-019-A01)

(1) A high-level block diagram of the internal architecture of the RTA-50D VDR is shown in Figure

7. The RTA-50D VDR consists of five subassemblies as follows:

• Digital processor CCA

• Front panel CCA

• Power supply module

• Rear interconnect module

•RFCCA.

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(2) The RTA-50D VDR is packaged in a 3MCU standard form factor. A low insertion force, Size

1 shell ARINC 600 connector with three inserts provides the means to interface to other

onboard avionics as well as the antenna and aircraft power. The top plug and middle plug

inserts are used for system interconnects. The bottom plug insert is used for input power

and coaxial antenna connections.

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Figure 7. (Sheet 1 of 1) RTA-50D VDR Internal Architecture (GRAPHIC 23-20-59-99B-810-A01)

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C. RF CCA (Subtask 23-20-59-870-020-A01)

(1) General

(a) The RF CCA performs the basic VHF receive and transmit functions of the VDR in all

voice and data modes of operation. The RF CCA circuitry is comprised of five processing

sections:

• Receiver section

• Transmitter section

• LO frequency synthesizer section

•RFcontrol

• BIT monitoring circuits.

(b) A block diagram of the RF CCA is shown in Figure 8.

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Figure 8. (Sheet 1 of 1) RF CCA (GRAPHIC 23-20-59-99B-811-A01)

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(2) Receiver

(a) The receiver section of the RF CCA employs a heterodyne architecture to convert

a received RF signal in the 118 to 136.975-MHz range to baseband quadrature digital

samples.

(b) A preselector filter followed by an LNA and another preselector filter first limit the RF

bandwidth to about less than 2 MHz centered about the selected operating frequency.

The preselectors center frequency is voltage controlled. The voltage level is selected

by the RF control FPGA from a table of settings prestored in an EEPROM whenever a

new operating frequency is selected. A pin-diode variable attenuator preceding the first

preselector provides the means to attenuate the received RF signal when the output

of the second preselector exceeds the level at which the RF-to-IF conversion mixer

becomes nonlinear.

signal in the 139.825 to 158.800-MHz range to produce an IF signal at 21.825 MHz. A

four-pole crystal filter with nominal 25-kHz bandwidth which follows the mixer provides

enough rejection of undesired signals occupying channels adjacent to the selected

frequency to prevent aliasing and/or desensitization in the A/D conversion process.

(d) The IF signal is then digitized at 50.4 mega-samples each second by an ADC and

digitally down converted to baseband in-phase and quadrature digital sample streams

using a programmable DDC integrated circuit. The DDC also performs the 25 or

8.33-kHz channel selectivity filtering to reject adjacent channel signals. The DDC channel

selectivity is preprogrammed and the desired channel bandwidth is selected by the RF

control FPGA whenever a new channel is selected. The filtered in-phase and quadrature

digital sample streams are decimated by the DDC and sent to the digital processor CCA

at an 84-kHz rate through a serial bus interface provided by the RF control FPGA.

(e) The input signal level at the ADC is held constant by means of an AGC amplifier circuit.

The AGC control signal is generated by a DSP in the digital processor CCA and passed

on to the RF CCA through the serial bus connection to the RF control FPGA.

(3) Transmitter

(a) The transmitter section of the RF CCA also utilizes a heterodyne architecture for

conversion of in-phase and quadrature digital samples to a RF signal in the 118 to

136.975-MHz band.

(b) Baseband in-phase and quadrature digital sample streams generated by the digital

processor CCA are sent to the RF CCA at a 252-kHz rate in serial format through the

serial bus connection to the RF control FPGA. A preprogrammed DUC up samples and

interpolates the in-phase and quadrature digital sample streams to a 50.4-MHz sample

rate and up converts them to an analog IF signal at 21.825 MHz.

and spurious of the D/A conversion process. This IF signal is amplified and up converted

to the selected VHF channel by mixing it with the same 139.825 to 158.800-MHz LO used

by the receiver. A SAW filter with 20-MHz bandwidth (centered on the 118 to 137-MHz

band), followed by a post selector filter with about a 4-MHz bandwidth (centered about

the selected operating frequency) are then used to reject LO leakage and harmonic

products of the mixer. The post selectors center frequency is voltage controlled. The

voltage level is selected by the RF control FPGA from a table of settings prestored in an

EEPROM whenever a new operating frequency is selected.

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(d) The filtered RF signal is then amplified to produce a 25-watt average RF output signal

when operating in DSB-AM voice or ACARS Mode A data mode, or a 17.5-watt average

RF output signal when operating in VDL Mode 2 data mode. An ALC signal generated

by the RF control FPGA is used to set the transmitter output power at the desired level

for the operating mode during the ramp-up transition from receive to transmit. When

operating in DSB-AM voice or data mode, the ALC signal is also used to maintain the

output signal level at the desired level throughout the transmission.

(e) A 20-dB coupler at the output of the transmitter is used to obtain low-power forward and

reverse voltage replicas of the transmitted RF signal. The forward and reverse voltages

are envelope detected and digitized for downstream processing by the RF control FPGA

and DSPs on the digital processor CCA. The forward voltage signal is used by the FPGA

to derive the ALC control signal and by the DSPs to derive transmit audio side tone when

operating in DSB-AM voice mode. The forward and reverse voltages are used by the

DSP to monitor the antenna VSWR during transmit operation in all modes.

(f) An antenna DC ground monitoring circuit is also used at the antenna port to detect

antenna faults on aircraft installations that use DC grounded antennas (pin programming

selectable).

(4) LO Frequency Synthesizer

(a) The LO frequency synthesizer section of the RF CCA generates the 139.825 to

158.800-MHz LO signal that is used by the transmitter and receiver chains. The LO

frequency synthesizer is comprised of a reference oscillator, a PLL frequency synthesizer

integrated circuit, and VCO.

(b) The reference oscillator is a TCXO that generates a 50.4-MHz reference clock signal

that is used to generate the LO frequency as well as the clocks for the ADC, DDC,

DUC, and for the digital processor circuitry.

provided by the TCXO. The LO frequency selection (tuning) is controlled by the digital

processor CCA and the synthesizer programming data is passed to the LO frequency

synthesizer through the RF control FPGA. The LO frequency synthesizer provides an

indication (synthesizer lock) to the RF control FPGA when it has tuned to the selected

frequency.

(5) RF Control

(a) The RF control functions are implemented in a Xilinx Spartan lIe FPGA with 300,000

gates. The RF control FPGA is responsible for managing the flow of transmit and receive

digital data samples, and command and control data by interfaces to the devices that

follow:

• TMS320C6711 DSP bi-directional serial communications port (MCBSP) interface

• MPC8250 processor SPI

• Transmitter DUC interface

• Receiver DDC interface

• Receiver high-speed A/D converter (ADC) interface

• Frequency synthesizer interface

• RF BIT MUX A/D converter interface

• Voltage monitoring BIT MUX A/D converter interface

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• Digital potentiometer interface

• Serial EEPROM interface

• Transmitter ALC

• External discrete I/O interface.

(b) The RF control FPGA receives 24-bit command data consisting of alternating 14-bit I and

Q transmit data samples, 6-bit control words, and 4-bit command code sent from the

TMS6711 DSP on the downstream MCBSP serial bus at a 504-kHz rate. The RF control

FPGA writes the 14-bit I or Q data to the DUC if transmit mode is enabled (appropriate bit

in control word is set), and decodes the 6-bit control words to control various transceiver

components on the RF CCA. The transceiver functions controlled are as follows:

• Enabling of Tx function

• Antenna Tx/Rx switching

• LO Tx/Rx switching

•Driver/PA

Tx bias enabling

• Forced termination of Tx data flow.

RF control FPGA to program and configure the DUC and DDC during power up and

after mode changes.

(d) The RF control FPGA sends 192-bit data frames to the TMS6711 DSP on a second

(upstream) MCBSP serial bus at an 84-kHz rate. The 192-bit frame contains:

• The 32-bit I and Q receive data from DDC channel 0 for data demodulation

• The 32-bit I and Q receive data from DDC channel I for adjacent channel interference

detection

• The 32-bit ADC output values for AGC

• The 32-bit frame ID/BIT data values for frame synchronization and fault/event detection.

(e) The BIT data content of the last 32 bits of each frame rotates on an 8-frame cycle. The

17-bit data consists of an 8-bit field that alternates between data samples of:

• Driver bias monitor

• PA bias monitor

• Temperature sense

• An Rx RF monitor

• A 28-volt monitor

• Rx LO level monitor

• Requested data ID or requested data

• An 8-bit field that alternates between samples of forward power and reverse power

• A 1-bit field that alternates between antenna DC monitor, synthesizer lock, FPGA SEU

flag, FPGA watchdog, and DUC overflow flag status.

(f) The transmission of each frame is periodic and synchronized to the receiver DDC frame

synchronization signal. An automatic upstream mode also exists to send data when the

DDC is not operating.

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(g) In transmit mode, the RF control FPGA uses the RF BIT MUX forward power samples

to derive an automatic level control signal to adjust the PA gain using the digital

potentiometer interface.

(h) Other functions performed by the RF control FPGA include:

• MPC8250 processor and TMS6711 DSP write access to the LO frequency synthesizer

device to select the LO frequency

• TMS6711 DSP read/write access to the serial EEPROM through commands

• TMS6711 DSP write access to the serial pot interface to update 1 of 16 available

digital potentiometers

• TMS6711 DSP write access to various FPGA mode and discrete output registers

• TMS6711 DSP read access to RF control FPGA revision and discrete input bits.

(6) BIT Monitoring

(a) The RF CCA incorporates BIT circuitry to detect failures both during normal operation as

well as during power on self-test and operator-initiated self-test.

(b) The Tx/Rx BIT signals continuously monitored (RF BIT MUX) during normal transmit

and receive operation include:

• Transmit forward power measured at the antenna port during transmit operation

• Reflected power measured at the antenna port during transmit operation

• Primary 28-volt input to the RTA-50D VDR

• DC bias voltages of the driver and final PA devices

• Temperature of the RF CCA

• Received signal level at down converter mixer

• LO output level.

• 9-volt regulator output

• 6-volt regulator output

• 5-volt regulator output

• 3.3-volt regulator output

• -5-volt regulator output

• 1.8-volt regulator output.

(d) Other signals continuously monitored are the synthesizer lock detector output.

(e) During power on self-test, the RF CCA performs an antenna continuity test to detect the

presence or absence of an antenna connection and a receiver functionality test under the

control of the digital processor CCA. The receiver functionality test consists of looping

back a test RF signal generated by the DUC that is injected into the receiver chain and

measuring the SNR of the received signal. Refer to Figure 8.

(f) When self-test is initiated by the operator, the RF CCA performs the antenna continuity

test and receiver functionality test as well as a transmitter/antenna test. The

transmitter/antenna test consists of the transmission of a test signal at 118 MHz and

the measurement of the forward transmitted and reflected powers at the antenna port.

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Reporting of the measurements to the digital processor CCA for computation of the

VSWR then takes place.

D. Digital Processor CCA (Subtask 23-20-59-870-021-A01)

(1) General

(a) The digital processor CCA comprises nine processing sections:

• MPC8250 main processor

• TMS320C6711 digital signal processor (main DSP)

• TMS320VC5410A digital signal processor (auxiliary DSP)

• Audio I/O circuitry

• ARINC 429 I/O circuitry

• Discrete I/O circuitry

• Clock generation circuitry

• Monitoring circuitry

• Manufacturing and engineering support I/O circuitry.

(b) A block diagram of the digital processor CCA is shown in Figure 9.

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Figure 9. (Sheet 1 of 1) Digital Processor CCA Block Diagram (GRAPHIC 23-20-59-99B-812-A01)

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(2) Main Processor

(a) The main processor is a Motorola MPC8250 Power PC with 64 Mbit of external flash

for boot/program memory, 256 Mbit of external SDRAM for program and data memory,

64 Mbit of external SDRAM for program and data memory ECC, and 256 Kbit external

EEPROM for fault and configuration memory.

(b) The MPC8250 processor interfaces to the ARINC 429 I/O FPGA through a PCI bus and

to discrete inputs and outputs to determine the mode of operation and frequency/channel

selection. The MPC8250 processor performs the tuning of the VHF transceiver LO

synthesizer according to the selected mode and channel through the RF control FPGA on

the RF CCA by means of a SPI.

shared memory messages accessed by HPI built into each DSP. The HPI is a parallel

port through which the MPC8250 can directly access the DSP shared memory. When

operating in the Mode A or Mode 2 data modes, the MPC8250 manages the delivery of

uplink data messages received from the TMS6711 DSP to the ARINC 429 transmitter

within the ARINC 429 I/O FPGA that interfaces to the external user (ATSU or CMU). It

also controls the flow of downlink data messages received from the ARINC 429 receiver

that interfaces to ATSU or CMU to the TMS6711 DSP.

(d) The MPC8250 processor also interfaces on an external OMS through an ARlNC 429

transmitter/receiver pair synthesized within the ARINC 429 I/O FPGA to report fault

data collected by BIT function.

(e) The MPC8250 processor BIT function controls three different modes of self-test that are

used to monitor the health of the RTA-50D VDR and detect faults:

• Power on self-test

• Operator initiated functional self-test

• Background (continuous monitoring) self-test.

(f) Power on self-test is initiated each time the power is cycled on the unit. Some tests

are intrusive meaning that some VDR to aircraft interfaces can not be read or driven

according to normal aircraft operation. The list that follows describes the functional

blocks that are tested but not in what order:

• MPC8250 register test

• MPC8250 SDRAM

• MPC8250 FLASH

• MPC8250 EEPROM

• DSP HPI interface

• TMS6711 DSP register test

• TMS6711 DSP SDRAM

• TMS5410 DSP register test

• Audio CODEC register test

• ARINC 429 I/O FPGA PCI register test

•SDIdiscretetest

• Antenna monitor discrete test

• ARINC 429 I/O loopback

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• Ethernet loopback

• RF control FPGA interface test

• Voltage monitor.

(g) Operator-initiated functional self-test can be initiated by pressing the front panel switch,

grounding the functional test discrete or OMS command. The set of tests executed are

the same as in the power on self-test plus additional transmitter and receiver loop back

tests that check the functionality of the transmitter, antenna, interface, and receiver. This

mode is useful in diagnosing problems only seen after the RTA-50D VDR has been

running for some time.

(h) Background self-tests are run continuously in the RTA-50D VDR as long as power is

applied. These tests only exercise circuitry in a way that is nonintrusive to system

operation. The background self-tests listed as follows are a subset of the functional

self-tests but, where possible, use the same test software routines:

• MPC8250 SDRAM

• MPC8250 FLASH

• MPC8250 EEPROM

• DSP HPI interface

• TMS6711 DSP SDRAM

• Ethernet loopback

• RF control FPGA interface test

• Voltage monitor.

(3) Main DSP

(a) The main DSP is a Texas Instruments TMS320C6711 DSP with 64 Mbit of external

SDRAM for program and data memory.

(b) The TMS6711 DSP interfaces to the RF control FPGA through a MCBSP serial bus

and to the TMS5410 DSP through a second MCBSP serial bus. The TMS6711 DSP

interfaces to the MPC8250 through shared memory accessed by its HPI interface. The

shared memory is configured as 64 message buffers of 4,096 bytes for each transfer

direction as well as a 592-byte control/status buffer. The TMS6711 DSP program is

loaded into its internal RAM and external SDRAM by the MPC8250 on power up.

the receiver AGC loop control voltage in all voice and data receive modes of operation.

(d) When operating in voice mode, the TMS6711 DSP monitors the PTT input to determine

when to switch between receive and transmit operation, and controls the switching of the

TMS5410 DSP between transmit and receive operation.

(e) When operating in voice transmit mode, the TMS6711 DSP performs the real-time

DSB-AM of digitized voice samples received from the TMS5410 DSP and delivers

252-kilo sample each second streams of I and Q digital modulation samples to the

RF CCA for RF carrier modulation and downlink transmission. Simultaneously while

transmitting the modulation samples, the TMS6711 DSP delivers the forward power

samples received from the RF CCA to the TMS5410 for side-tone output.

(f) When operating in voice receive mode, the TMS6711 DSP performs envelope detection

of the 84-kilo sample each second I and Q digital data streams received from the RF CCA

and delivers the demodulated samples to the TMS5410 DSP.

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(g) When operating in Mode A or Mode 2 data mode, the TMS6711 DSP monitors the

receiver AGC control loop voltage to determine when the channel is idle and available

for transmit operation. When the channel is idle and a data message is queued for

transmission, the TMS6711 DSP switches to data transmit operation; otherwise it

operates in data receive mode. When operating in data transmit mode, the TMS6711

DSP performs the encoding of data messages received from the MPC8250 and

generates a 252-kilo sample each second. Streams of I and Q digital samples of the

modulation waveform correspond to the data mode selected by the user. When operating

in data receive mode, the TMS6711 DSP performs message detection, decoding, error

detection, and address screening, and delivers the error-free decoded messages with

matching address to the MPC8250 for up-stream delivery.

(4) Auxiliary DSP

(a) The auxiliary DSP is a Texas Instruments TMS320VC5410 DSP with no external memory.

(b) The TMS5410 DSP interfaces to the TMS6711 DSP through McBSP serial bus and to the

audio input/output CODEC through a second McBSP serial bus. The TMS5410 DSP

interfaces to the MPC8250 through shared memory accessed by its HPI interface. The

shared memory is configured as 8 message buffers of 176 bytes for data transfer to the

MPS8250, 12 message buffers of 176 bytes for data transfer from the MPC8250, and a

16-byte control/status buffer. The TMS5410 DSP program is loaded into its internal RAM

bytheMPC8250onpowerup.

digitized audio input samples provided by the audio CODEC at 42-kilo samples each

second and sends the filtered transmit audio samples to the TMS6711 DSP for DSB-AM

modulation and up-sampling. The demodulated transmit audio which is simultaneously

received from the TMS6711 DSP is sent to the side-tone output of the audio CODEC.

(d) When operating in receive mode the TMS5410 DSP performs the audio bandpass filtering

and squelch control processing functions and sends the 42-kilo sample each second

stream of digital audio samples to the receive/side-tone output of the audio CODEC.

(5) Audio I/O Circuitry

(a) The audio I/O circuitry is comprised of an Analog Devices ADI836AS audio CODEC

integrated circuit that supports A/D and D/A conversion of up to four channels, and audio

input/output conditioning (low-pass filters) for each audio signal.

(b) Three CODEC A/D channels are used to support the following audio inputs:

• Microphone audio input for use on installations that support DSB-AM voice

• Modem audio input for use on installations that support Mode 0 data

• Remote squelch control input for use on installations that support remote squelch

control of DSB-AM voice audio.

• Received audio/side-tone output to the speaker for use on installations that support

DSB-AM voice

• SELCAL audio output for use on installations that support DSB-AM voice or Mode 0

data link modem audio output for use on Mode 0 data installations

• Analog AGC control voltage to support DSB-AM MOPS compliance testing.

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(6) ARINC 429 I/O Circuitry

(a) The ARINC 429 I/O transmitter encoding and receiver decoding logic is implemented

in an Actel ProASIC Plus flash FPGA with 600,000 gates. Digital logic-to-CMOS level

translation circuits are provided externally for each transmitter and receiver.

(b) The ARINC429 I/O FPGA interfaces to the MPC8250 through a PCI bus interface. The

ARINC 429 I/O FPGA supports 4 ARINC 429 transmitters and 11 ARINC 429 receivers

with automatic speed detection.

• Data link output high-speed transmitter

• OMS output low-speed transmitter

• Two spare transmitters.

(d) The ARINC 429 receivers are used to do the following functions:

• Two frequency select tuning input receivers

• Two data link input receivers

• Two OMS input receivers

• Five spare receivers.

(7) Clock Generator

(a) The clocks for the various processors are generated by a Cypress Semiconductor

programmable clock generator integrated circuit. The clock generator derives the

following clocks from a 50.4-MHz clock input from RF CCA:

• 58-MHz clock provided to the MPC8250

• 50-MHz clock provided to the TMS5410 DSP

• 35-MHz clock provided to the TMS6711 DSP

• 25-MHz clock provided to the Ethernet transceiver

• 10.24-MHz clock provided to the audio CODEC.

(8) Monitoring Circuitry

(a) The monitoring circuitry consists of voltage level monitoring circuits and a processor

watchdog circuit. The digital processor regulator voltage levels monitored are as follows:

•+12volts

•12 volts

•+5volts

•+3.3volts

•+2.5volts

•+1.9volts

•+1.5volts

• +1.26 volts.

(b) The ARINC 429 I/O FPGA provides a supervisory watchdog function used to monitor

the MPC8250 main processor. If the MPC8250 fails to monitor the watchdog register at

10-ms intervals, the MPC8250 is reset by the ARINC 429 I/O FPGA.

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(9) Manufacturing and Engineering Support I/O Circuitry

(a) The manufacturing and engineering support I/O circuitry consists of:

• Ethernet interface used for data loading and troubleshooting

• RS232 port used for test equipment support.

E. Front Panel I/O Board (Subtask 23-20-59-870-022-A01)

(1) The front panel I/O board performs the conditioning of the signals that drive three LED lights

and monitors a push-button switch on the front panel of the RTA-50D VDR to initiate LRU

self-test. No self-test is available for this subassembly.

F. Power Supply (Subtask 23-20-59-870-023-A01)

(1) The power supply subassembly is a self-contained high-efficiency power supply that converts

the 28-VDC power into the DC operating voltages required by each subassembly. The power

supply circuitry is grouped into three sections:

• Power hold circuitry

• Input voltage conditioning circuitry

• DC-to-DC voltage conversion and output voltage conditioning.

(2) The power supply is capable of holding power up during power input interrupts lasting

up to 200 ms. Each of the power supply output voltages are monitored on either the RF

subassembly or the processor subassembly.

G. Rear Interconnect (Subtask 23-20-59-870-024-A01)

(1) The rear interconnect subassembly consists of the ARINC 600 connector that provides the

means to interface the power supply module, the processor CCA, and the RF CCA to the

aircraft wiring, and HIRF and lightning protection circuitry for each input/output. The RF

and power supply inputs are in the bottom plug. Discrete, ARINC 429, and analog audio

inputs/outputs are in the middle plug and the top plug.

(2) There is no active circuitry on this assembly and thus it has a low failure rate. No self-test is

available for the rear interconnect.

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FAULT ISOLATION

1. Planning Data (TASK 23-20-59-99C-801-A01)

A. Reason for the Job (Subtask 23-20-59-99C-002-A01)

(1) Use the procedures in this section to isolate faults.

(2) Fault isolation is the process of isolating the source of a system failure to an LRU or to the

aircraft wiring.

(3) It is recommended that a system test of the RTA-50D VDR be done in accordance with the

instructions provided in the aircraft manufacturer’s AMM to confirm the reported fault condition.

(4) Access to the equipment bay is necessary to view the RTA-50D VDR front panel maintenance

status information and/or to initiate a self-test of the RTA-50D VDR equipment.

(5) Fault isolation in the RTA-50D VDR includes a continuity check of the interwiring and the

assurance that correct installation techniques and procedures have been followed.

B. Job Setup Data (Subtask 23-20-59-99C-003-A01)

(1) The list that follows identifies Honeywell publications that are related to this section:

• Not applicable.

2. Procedure (TASK 23-20-59-810-801-A01)

A. Job Setup (Subtask 23-20-59-810-001-A01)

CAUTION: USE INDUSTRY APPROVED ELECTROSTATIC DISCHARGE SENSITIVE

PRECAUTIONS. THE RTA-50D VERY-HIGH FREQUENCY DATA RADIO CONTAINS

ELECTROSTATIC DISCHARGE SENSITIVE ITEMS.

CAUTION: DO NOT DROP OR HIT THE RTA-50D VERY-HIGH FREQUENCY DATA RADIO

DURING THESE PROCEDURES. THE RTA-50D VERY-HIGH FREQUENCY DATA

RADIO CONTAINS AN ASSEMBLY THAT CAN BE DAMAGED FROM INCORRECT

USE.

(1) Obey the precautions.

B. Functional Self-Test (Subtask 23-20-59-810-002-A01)

(1) A functional self-test of the RTA-50D VDR can be initiated by pressing the test key push-button

on the front panel.

(2) Results of the functional self-test are displayed on the LEDs located on the front panel. Refer

to Figure 1001.

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Figure 1001. (Sheet 1 of 1) RTA-50D VDR Front Panel Functional Self-Test Interface

(GRAPHIC 23-20-59-99B-813-A01)

C. RTA-50D VDR Test Results (Subtask 23-20-59-810-003-A01)

(1) Apply power to the RTA-50D VDR in accordance with the aircraft manufacturer’s AMM and

confirm that the circuit breaker associated with the RTA-50D VDR equipment is closed.

(2) Locate the RTA-50D VDR in the equipment bay and observe the status of the LEDs according

to the information provided in Table 1001.

(3) In the event that a failure condition is indicated, do a self-test on the RTA-50D VDR as follows.

(a) While power is applied to the RTA-50D VDR, momentarily depress the TEST push

button on the front panel.

(b) Observe the LEDs according to the information provided in Table 1001.

action associated with the indicated fault condition.

Table 1001. Front Panel Functional Self-Test Results

Mode RTA-50D

Power VDR

Status Control

Fault Antenna

Fault Reported

Condition

Possible

Corrective

Action Comment

Power off Off Off Off Off LRU powered

off None LRU power

not applied

Normal

operation On Green Off Off Normal

operation None LRU

operational,

no errors

detected

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Table 1001. Front Panel Functional Self-Test Results (Cont)

Mode RTA-50D

Power VDR

Status Control

Fault Antenna

Fault Reported

Condition

Possible

Corrective

Action Comment

General

fault On Off Off Off 1. Breaker

malfunction

2. LRU

malfunction

1. Check

aircraft

breaker to

LRU

2. Reapply

power to

LRU, remove

if condition

repeats

1. Power

not reaching

LRU due

to breaker

problem or

2. LRU

has internal

malfunction

External

fault

(control)

On Green Amber Off 1. RTP

and/or CMC

controller not

present

2. Internal

malfunction

of RTP/CMC

interface

1. Check

aircraft RTP

and CMC

controllers

and/or

connections

2. Press

functional

self-test

button,

remove if

condition

repeats

1. RTP

and/or CMC

controller is

not present or

2. LRU

has internal

malfunction

of RTP/CMC

interface 1

External

fault

(antenna)

On Green Off Amber 1. Antenna is

not present.

2. Internal

malfunction

of antenna

interface.

1. Check

aircraft

antenna,

and antenna

connection

2. Press

functional

self-test

button,

remove if

condition

repeats

1. Antenna

or antenna

connection is

not present or

2. LRU

has internal

malfunction

of antenna

interface 2

External

fault

(control

/antenna)

On Green Amber Amber Refer to

external

(control) fault

and external

(antenna)

fault

Refer to

External

(control) fault

and external

(antenna)

fault

Refer to

external

(control) fault

and external

(antenna)

fault

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Table 1001. Front Panel Functional Self-Test Results (Cont)

Mode RTA-50D

Power VDR

Status Control

Fault Antenna

Fault Reported

Condition

Possible

Corrective

Action Comment

Internal

fault

(boot)

On Amber Amber Amber LRU did not

complete

boot

sequence

Reapply

power to

LRU, remove

if condition

repeats

Boot

sequence

did not

complete due

to internal

malfunction

Internal

fault On Red Off or

Amber Off or

Amber LRU reports

internal

malfunction

1. Press

functional

self-lest

button

2. If condition

repeats,

reapply

power to LRU

3. If condition

repeats,

remove LRU

LRU has

detected

internal

malfunction

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Table 1001. Front Panel Functional Self-Test Results (Cont)

Mode RTA-50D

Power VDR

Status Control

Fault Antenna

Fault Reported

Condition

Possible

Corrective

Action Comment

Internal

fault On Amber Off or

Amber Off or

Amber LRU reports

internal

malfunction

1. Press

functional

self-test

button

2. If condition

repeats,

reapply

power to LRU

3. If condition

repeats,

remove LRU

LRU has

detected

internal

malfunction

Internal

fault On Off Off or

Amber Off or

Amber LRU reports

internal

malfunction

1. Press

functional

self-test

button

2. If condition

repeats,

reapply

power to LRU

3. If condition

repeats,

remove LRU

LRU has

detected

internal

malfunction

NOTES:

1Only remove LRU if both RTP ports and both CMC ports are known to be connected and operating at

time of fault inspection.

2Only remove LRU if antenna is known to be good and antenna connection is verified to be good at time of

fault inspection.

D. Job Close-up (Subtask 23-20-59-810-004-A01)

(1) Not applicable.

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MAINTENANCE PRACTICES

1. Planning Data (TASK 23-20-59-99C-802-A01)

A. Reason for the Job (Subtask 23-20-59-99C-004-A01)

(1) This section gives service personnel installation and maintenance information for the RTA-50D

VDR. Installation instructions are supported by mechanical outline drawings and an electrical

interconnection diagram. These drawings must be reviewed by the installer and requirements

unique to the airframe must be established before starting the installation.

(2) Use these diagrams as an aid to fault isolate the RTA-50D VDR.

B. Job Setup Data (Subtask 23-20-59-99C-005-A01)

(1) The list that follows identifies Honeywell publications that are related to this section:

• Not applicable.

2. Inspection After Unpacking (TASK 23-20-59-000-801-A01)

A. General (Subtask 23-20-59-000-001-A01)

CAUTION: THIS EQUIPMENT CONTAINS ELECTROSTATIC DISCHARGE SENSITIVE (ESDS)

DEVICES. EQUIPMENT, MODULES, AND ESDS DEVICES MUST BE HANDLED

WITH APPROPRIATE PRECAUTIONS.

(1) Visually inspect the RTA-50D VDR and all associated equipment for possible damage which

can have occurred during shipment. Inspect for dents, deep abrasions, chipped paint, etc. If

any equipment is damaged, notify the transportation carrier immediately.

(2) The Honeywell test, inspection record, and quality report tag is included with each shipped

unit. This informs the customer that the necessary production tests and inspection operations

have been performed on that particular unit.

(3) One copy of the 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 Honeywell Airlines and

Avionics Products quality report portion of the tag and return it to the Honeywell Airlines and

Avionics Products Quality Assurance Department. 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 give information for a periodic analysis.

3. Preinstallation Testing (TASK 23-20-59-000-802-A01)

A. Overview (Subtask 23-20-59-000-002-A01)

(1) The components in the RTA-50D VDR have been adjusted and tested before shipment.

Preinstallation testing is not required. However if preinstallation testing of the RTA-50D VDR is

desired, refer to the customer acceptance criteria given in the CMM for the appropriate unit in

the system. Refer to Paragraph 3.A. (Subtask 23-20-59-99F-011-A01) in the INTRODUCTION

(PGBLK 23-20-59-0) section for a list of related CMMs.

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4. Equipment Changes and Marking (TASK 23-20-59-000-803-A01)

A. Overview (Subtask 23-20-59-000-003-A01)

(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 CMM for a list of

service bulletins affecting the unit.

5. Interchangeability (TASK 23-20-59-000-804-A01)

A. Overview (Subtask 23-20-59-000-004-A01)

(1) The RTA-50D VDR will operate in any installation that complies with ARINC Characteristic

566A. Refer to Figure 2001.

NOTE: Contact the OEM for certification status.

6. Installation (TASK 23-20-59-000-805-A01)

A. General (Subtask 23-20-59-000-005-A01)

CAUTION: AFTER INSTALLATION OF THE CABLING AND BEFORE INSTALLATION OF THE

EQUIPMENT, A CHECK MUST BE MADE WITH AIRCRAFT PRIMARY POWER

SUPPLIED TO THE MOUNT CONNECTORS TO MAKE SURE THAT POWER IS

APPLIED ONLY TO THE PINS SPECIFIED IN INTERWIRING DIAGRAM. REFER TO

FIGURE 2001.

(1) The RTA-50D VDR must be installed in the aircraft in a manner consistent with acceptable

workmanship and engineering practices, and in accordance with the instructions in this

manual. 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 before flight.

B. Location of Equipment (Subtask 23-20-59-000-006-A01)

(1) Location of the RTA-50D VDR in the aircraft is not critical as long as the environment is

compatible with the equipment sign. Refer to Table 1 in the DESCRIPTION AND OPERATION

(PGBLK 23-20-59-1) section. Forced air cooling is required for cooling the RTA-50D VDR

communications transceiver in accordance with ARINC Characteristic 404A. The associated

cooling equipment must be mounted in accordance with the manufacturer’s instructions.

(2) The RTA-50D VDR can use the existing MTA-43A mount or any other equivalent mounting

tray that is compatible for securing a unit meeting the 1/2 ATR short form factor according to

ARINC Characteristic 404.

(3) 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 RTA-50D VDR

systems are installed in an aircraft, it is necessary to give adequate space isolation between

the 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 give further isolation must be considered.

(4) Control unit location and mounting can be determined by mutual agreement between the

user and airframe manufacturer.

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C. Interwiring and Cable Fabrication (Subtask 23-20-59-000-007-A01)

(1) General

(a) Figure 2001 is the complete aircraft interwiring diagram for a single RTA-50D VDR system

and associated components. This diagram requires complete study before the installer

begins installation of the aircraft wiring.

(b) When two or more systems are being installed in the aircraft, the interconnecting wiring

as well as all other installation instructions must be duplicated.

approximately the same length so that the best distribution of current can be effected.

Honeywell recommends that all wires including the spares must 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 are

incorporated. Refer to Figure 2001.

NOTE: To allow for inspection or repair of the connector or the wiring to the connector,

sufficient lead length must be provided. This will let the rear connector

assembly to 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 let water condensation drip off at the bend

and not collect at the connector.

(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 unique to the installation

and must completely understand the complexities associated with handling related

problems of line lengths, capacitance, and of susceptibility to interference.

(g) The following determinants are the responsibility of the installation agency for fabrication

of the wiring harness. Refer to Table 2001.

Table 2001. RTA-50D VDR Communications Transceiver Connector Determinants

Pin No. Type Signal Name Function

MPA1 Input MIC audio input (high) Microphone audio input. Part of the standard four wire

microphone interwiring as described in Attachment

6 of ARINC 716-10. Required for ARINC 716 VHF

communication only.

MPB1 Input MIC audio input (low) Microphone audio input. Part of the standard four wire

microphone interwiring as described in Attachment

6 of ARINC 716-10. Required for ARINC 716 VHF

communication only.

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Table 2001. RTA-50D VDR Communications Transceiver Connector Determinants (Cont)

Pin No. Type Signal Name Function

MPC1 Input MIC PTT Microphone PTT discrete input.

Ground/low = transmitter keyed.

Open/high = transmitter not keyed.

Part of the standard four-wire MIC interwiring as

described in Attachment 6 of ARINC 716·10. Required

for ARINC 716 VHF communication only.

MPD1 Output Key event Discrete input to flight recorder. Follows the state of

MIC PTT input.

Ground/low = transmitter keyed

Open/high = transmitter not keyed

Required for ARINC 716 VHF communication only.

MPA2 Input MAX transmit time cutoff

function Discrete input that enables the MAX transmit cutoff

function.

Ground/Low = cutoff disabled

Open/High = cutoff enabled

MPB2 NA MIC input ground Required for ARINC 716 VHF communication only.

MPC2 Input Data loader input Bus A A high-speed ARINC 429 input port to allow on-board

data loading for software.

MPD2 Input Data loader input Bus B Ahigh-sp

eed ARINC 429 input port to allow on-board

data loading for software.

MPA3 Input Optional remote squelch

(high) To accommodate an optional remote squelch

adjustment if so required or provided. Required for

ARINC 716 VHF communication only.

MPB3 Input Optional remote squelch

(arm) To accommodate an optional remote squelch

adjustment if so required or provided. Required for

ARINC 716 VHF communication only.

MPC3 Input Optional remote squelch

(low) To accommodate an optional remote squelch

adjustment if so required or provided. Required for

ARINC 716 VHF communication only.

MPD3 NA DC ground Required for both ARINC 716 VHF communication and

ARINC 750 VDR; functions are identical.

MPA4 Input Functional test Discrete input that activates LRU functional test

function. ground/low = activate functional test.

Required for ARINC 716 VHF communication.

MPB4 NA Audio ground Required for ARINC 716 VHF communication only.

MPC4 Output Data loader output Bus A A high-speed ARINC 429 output port to allow on-board

data loading for software.

MPD4 Output Data loader output Bus B A high-speed ARINC 429 output port to allow on-board

data loading for software.

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Table 2001. RTA-50D VDR Communications Transceiver Connector Determinants (Cont)

Pin No. Type Signal Name Function

MPA5 Input Data link data input (high) Analog 2,400-bps ACARS data input. Required for

ARINC 716 VHF communication only.

MPB5 Input Data link data input (low) Analog 2,400-bps ACARS data input. Required for

ARINC 716 VHF communication only.

MPC5 NA Reserved No. 1 Leave open.

MPD5 Output 8.33 kHz programming Discrete output that indicates to control panel the VDR

is capable of 8.33 or 25-kHz operation. This output is

internally grounded.

MPA6 Input Data from OMS/CFDS No.

1 Input Port (A) One of two low-speed ARINC 429 data input ports

provided for dual OMS/CFDSs. Required for both

ARINC 716 VHF communication and ARINC 750 VDR;

functions are identical.

MPB6 Input Data from OMS/CFDS No.

1 Input Port (B) One of two low-speed ARINC 429 data input ports

provided for dual OMS/CFDSs. Required for both

ARINC 716 VHF communication and ARINC 750 VDR;

functions are identical.

MPC6 Input Data from OMS/CFDS No.

2 Input Port (A) One of two low-speed ARINC 429 data input ports

provided for dual OMS/CFDSs. Required for ARINC

750 VDR only.

MPD6 Input Data from OMS/CFDS No.

2 Input Port (B) One of two low-speed ARINC 429 data input ports

provided for dual OMS/CFDSs. Required for ARINC

750 VDR only.

MPA7 InputFrequency/function select

data l/P Port B (A) One of two low-speed ARINC 429 input ports to

provide frequency tuning data. Required for ARINC

716 VHF communication only.

MPB7 Input Frequency/function select

data l/P Port B (B) One of two low-speed ARINC 429 input ports to

provide frequency tuning data. Required for ARINC

716 VHF communication only.

MPC7 Input Voice/data select Discrete input that enables either the PTT key line

(MPC1) or the Data key line (MPD7).

Ground/low = data Key line enabled

Open/High = PTT enabled.

Required for ARINC 716 VHF communication only.

MPD7Input Data key line Discrete input that keys the transmitter.

Ground/low = transmitter keyed.

Open/high = transmitter not keyed.

Required for ARINC 716 VHF communication only.

MPA8 Input Antenna monitor enable

input Discrete input that allows antenna monitor function

at power-up.

Ground/low = monitor enabled.

Open/high = monitor disabled.

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Table 2001. RTA-50D VDR Communications Transceiver Connector Determinants (Cont)

Pin No. Type Signal Name Function

MPB8 Input Data loader enable input Discrete input to allow on-board data loading of

software. Required for ARINC 750 VDR only.

MPC8 Input Frequency offset enable Not implemented.

MPD8 NA Data key line return Required for ARINC 716 VHF communication only.

MPA9 Input SDI Bit 0 program A discrete input pair pre-wired at the rear connector to

identify the specific VHF radio location in the aircraft.

Required for both ARINC 716 VHF communication and

ARINC 750 VDR; functions are identical.

MPB9 Input SDI Bit 1 program A discrete input pair pre-wired at the rear connector to

identify the specific VHF radio location in the aircraft.

Required for both ARINC 716 VHF communication and

ARINC 750 VDR; functions are identical.

MPC9 NA SPI program pin common Ground for the SDI code inputs. Required for ARINC

716 VHF communication only.

MPD9 Output AGC out AGC output signal for test purposes.

MPA10 NA Spare NA

MPB10 NA Spare NA

MPC10 Output Data to CMU No. 1, CMU

No. 2 output Port (A) A high-speed ARINC 429 output port to CMU/MU/ATSU

No. 1 and No. 2. Required for ARINC 750 VDR only.

MPD10 Output Data to CMU No. 1, CMU

No. 2 output Port (B) A high-speed ARINC 429 output port to CMU/MU/ATSU

No. 1 and No. 2. Required for ARINC 750 VDR only.

MPA11 Input Frequency/function select

data I/P Port A (A) One of two low-speed ARINC 429 input ports to

provide frequency tuning data. Required for ARINC

716 VHF communication only.

MPB11 Input Frequency/function select

data I/P Port A (B) One of two low-speed ARINC 429 input ports to

provide frequency tuning data. Required for ARINC

716 VHF communication only.

MPC11 Input Maintenance system ID 1 Identifies CFDS type along with MPA14.

MPD11 Input Frequency port select Discrete input used to select either frequency/function

select data l/P Port A or B.

Ground/low = Select Port A.

Open/high = Select Port B.

Required for both ARINC 716 VHF communication and

ARINC 750 VDR; functions are identical.

MPA12 Input CMU No. 1 input Bus A A high-speed ARINC 429 input port from

CMU/MU/ATSU No. 1. Used to receive

commands/status/data in Williamsburg files,

and periodic and aperiodic ARINC 429 words.

Required for ARINC 750 VDR only.

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Table 2001. RTA-50D VDR Communications Transceiver Connector Determinants (Cont)

Pin No. Type Signal Name Function

MPB12 Input CMU No. 1 input Bus B A high-speed ARINC 429 input port from

CMU/MU/ATSU No. 1. Used to receive

commands/status/data in Williamsburg files,

and periodic and aperiodic ARINC 429 words.

Required for ARINC 750 VDR only.

MPC12 Input CMU No. 2 input Bus A A high-speed ARINC 429 input port from

CMU/MU/ATSU No. 2. Used to receive

commands/status data in Williamsburg files,

and periodic and aperiodic ARINC 429 words.

Required for ARINC 750 VDR only.

MPD12 Input CMU No. 2 input Bus B A high-speed ARINC 429 input port from

CMU/MU/ATSUNo.2.Usedtoreceive

commands/status data in Williamsburg files,

and periodic and aperiodic ARINC 429 words.

Required for ARINC 750 VDR only.

MPA13 Output SELCAL audio and data

link output (high) An analog output to provide 2400-bps MSK data to the

ACARSMU.MayalsobeusedforSELCALprovisions.

Required for ARINC 716 VHF communication only.

MPB13 Output SELCAL audio and data

link output (low) An analog output to provide 2400-bps MSK data to the

ACARSMU.MayalsobeusedforSELCALprovisions.

Required for ARINC 716 VHF communication only.

MPC13 Input Squelch disable Adisc

rete input to provide squelch override or

disable capability. Required for ARINC 716 VHF

communication only.

MPD13 NA Squelch disable return A discrete input to provide squelch override or

disable capability. Required for ARINC 716 VHF

communication only.

MPA14 Input Maintenance system ID 0 Identifies CFDS type along with MPC11.

MPB14 Input Air/ground discrete Adi

screte input to indicate if the aircraft is in the air or

on the ground.

Ground/low = airborne.

Open/high = on ground.

Required for both ARINC 716 VHF communication and

ARINC 750 VDR; functions are identical.

MPC14 Output Data to OMS/CFDS output

Port A A low-speed ARINC 429 output port to one or two

OMS/CFDSs. Required for both ARINC 716 VHF

communication and ARINC 750 VDR. Functions are

identical.

MPD14 Output Data to OMS/CFDS output

Port B A low-speed ARINC 429 output port to one or two

OMS/CFDSs. Required for both ARINC 716 VHF

communication and ARINC 750 VDR. Functions are

identical.

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Table 2001. RTA-50D VDR Communications Transceiver Connector Determinants (Cont)

Pin No. Type Signal Name Function

MPA15 Output Audio/side-tone output

(high) An analog output for receiver audio during receive

mode and side-tone audio during voice transmit

modes. Required for ARINC 716 VHF communication

only.

MPB15 Output Audio/side-tone output

(low) An analog output for receiver audio during receive

mode and side-tone audio during voice transmit

modes. Required for ARINC 716 VHF communication

only.

MPC15 Output Muting An optional two wire discrete output to provide a switch

closure internal to the VHF communication for external

system muting applications during transmit modes.

Open = muting off.

Ground = muting on.

Required for ARINC 716 VHF communication only.

MPD15 NA Muting return An optional two wire discrete output to provide a switch

closure internal to the VHF communication for external

system muting applications during transmit modes.

Open = muting off.

Ground = muting on.

Required for ARINC 716 VHF communication only.

BP1 Input

/output Antenna RF input Required for both ARINC 716 VHF communication and

ARINC 750 VDR; functions are identical.

BP2 Input DC power input +27.5

VDC Required for both ARINC 716 VHF communication and

ARINC 750 VDR; functions are identical.

BP3 NA Spare NA

BP4 NA DC power ground Required for both ARINC 716 VHF communication and

ARINC 750 VDR; functions are identical.

BP5 NA Spare NA

(2) Reserved and Spare Wires

(a) It is not necessary to connect all wires. Wires reserved for optional functions can be

selected, which the system does not contain, and deleted. Also decide which future

spare wires to include in the installation. The reserved and spare wires are identified in

Table 2001 and in Figure 2001.

D. Installation of System (Subtask 23-20-59-000-008-A01)

(1) The RTA-50D VDR is secured in the airframe with 3 MCU unit mounts. 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.

(2) To wire the mounts into the system, perform the steps that follow.

(a) Remove the mount connector cover and connector plate assembly.

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(b) Crimp or solder (as applicable) the interconnecting wiring to the appropriate connector

pins.

(3) To install the RTA-50D VDR in the mount, perform the steps that follow.

(a) Slide the RTA-50D VDR into the mount until the guide pins are aligned and the electrical

connectors are firmly engaged.

(b) Attach the front of the RTA-50D VDR to the mount by tightening 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 unit.

7. Inspection and System Check Procedures (TASK 23-20-59-000-806-A01)

A. Inspection (Subtask 23-20-59-000-009-A01)

(1) Inspection and check procedures for the RTA-50D VDR include checkout of all interfacing

units that can affect performance of the VDR.

(2) Table 2002 is a visual inspection check procedure and must be performed after system

installation, before system checkout. In addition, the procedure must be used as a periodic

inspection check.

Table 2002. Inspection/Check Procedures

Equipment Inspection/check Procedure

3MCU unit mount As defined by manufacturer’s instructions.

RTA-50D VDR 1. Check that unit is fully inserted in mount and that the knurled screw

clamps, which attach the unit in the mount, are tight and safety wired.

2. Inspect the case for deformation, dents. corrosion, and damage to

finish; make sure that ventilation holes in the unit are not clogged.

ARINC 716/750 control panel As defined by manufacturer’s instructions.

ARINC 716/750 VHF antenna As defined by manufacturer’s instructions.

B. System Checkout (Subtask 23-20-59-000-010-A01)

(1) General

(a) After installation of the RTA-50D VDR and inspection of the equipment, do a continuity and

visual check of the system interwiring. A post-installation test 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.

Specifically check the following:

• Check that the RTA-50D VDR is properly installed and the hold-down screw clamps

are tight.

• Check the wiring harness connectors for security and connection to the RTA-50D VDR.

• Check that antenna transmission line connectors are securely fastened.

• Check that cables do not interfere with aircraft controls or other equipment.

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(3) Post-Installation Check

(a) Required Test Equipment

1Not applicable.

(b) System Test

1A functional self-test of the LRU can be initiated by pressing the test key push-button

on the front panel. Refer to Figure 1001.

2The result of the functional self-test is displayed on the LEDs located on the front

panel.

3After completion of functional self-test, the RTA-50D VDR status LED must be

green and all other LEDs must be off. For more information, refer to the FAULT

ISOLATION (PGBLK 23-20-59-1000) section.

C. Flight Tests (Subtask 23-20-59-000-011-A01)

(1) Preflight Test

(a) The following test procedure gives instructions for a preflight test which ensures that the

RTA-50D VDR is functioning in an acceptable manner before takeoff.

(b) Test Procedure

1Establish the initial control settings. Refer to Table 2003.

Table 2003. Initial Control Settings

Control Panel Position

Power On.

Frequency selector Tune to any local VHF frequency (local control tower or ground control

frequency).

Volume control Midrange.

2Use the system headphones (or speaker) and microphone to check operation

of the RTA-50D VDR.

3Key the microphone and speak into it. Request a radio check and release the

PTT button.

4As soon as possible, a local flight check must be made to verify system operation

for both local and distant stations.

(2) In-Flight Confidence Test

(a) After completion of the post-installation and preflight checks, a local flight can be made to

verify system operation for both local and distant stations. Repeat the test procedure

found in Paragraph 7.C. (Subtask 23-20-59-000-011-A01)(1)(b).

8. Removal and Replacement (TASK 23-20-59-000-807-A01)

A. Removal (Subtask 23-20-59-000-012-A01)

(1) Loosen the two knurled screw clamps (located on the front of the mount) that attach the

RTA-50D VDR to the mount.

(2) Gently pull the RTA-50D VDR forward until it is disconnected from the rear connector and

the guide pins.

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B. Replacement (Subtask 23-20-59-000-013-A01)

(1) Slide the RTA-50D VDR onto the tray of the mount and then gently push the RTA-50D VDR

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 RTA-50D VDR.

(3) Safety wire the two knurled screw clamps.

9. Maintenance Procedures (TASK 23-20-59-000-808-A01)

A. Adjustments and Alignments (Subtask 23-20-59-000-014-A01)

(1) There are no adjustments or alignments required for the RTA-50D VDR. 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 (Subtask 23-20-59-000-015-A01)

(1) The system must be protected by a 10-AMP circuit breaker located at the circuit breaker

panel in the aircraft.

C. Lubrication Practices (Subtask 23-20-59-000-016-A01)

(1) There are no requirements for lubrication of any RTA-50D VDR components.

D. Cleaning (Subtask 23-20-59-000-017-A01)

(1) When deemed necessary, depending on the environment to which the equipment is exposed

and the intensity of use, periodic cleaning can be performed. Any dust on the RTA-50D

VDR must be wiped off with a lint-free cloth.

NOTE: Any cleaning of equipment interiors must be limited to that required when

performing overhaul (bench-type) work.

10. Diagrams (TASK 23-20-59-000-809-A01)

A. RTA-50D VDR Diagrams (Subtask 23-20-59-000-018-A01)

(1) Diagrams for the RTA-50D VDR are listed in Figure 2001.

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Blank Page

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Figure 2001. (Sheet 1 of 4) RTA-50D VDR Detail/Interwiring Diagram (GRAPHIC 23-20-59-99B-814-A01)

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Figure 2001. (Sheet 2 of 4) RTA-50D VDR Detail/Interwiring Diagram (GRAPHIC 23-20-59-99B-814-A01)

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Figure 2001. (Sheet 3 of 4) RTA-50D VDR Detail/Interwiring Diagram (GRAPHIC 23-20-59-99B-814-A01)

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Figure 2001. (Sheet 4 of 4) RTA-50D VDR Detail/Interwiring Diagram (GRAPHIC 23-20-59-99B-814-A01)

EFFECTIVITY

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Honeywell RTA-50D VHFAIRBORNE VOICE / DATA TRANSCEIVER User Manual User s Manual

Honeywell International Inc. VHFAIRBORNE VOICE / DATA TRANSCEIVER User s Manual

User's Manual

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