Honeywell RTA-44DM2 RTA-44D VHF Data Radio User Manual 1144 1Rev5 1144 1r5frontmatter

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Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
TO:
Holders of RTA-44D VHF Data Radio System Maintenance Manual, I.B. 1144-1.
REVISION NO. 5
to
MAINTENANCE MANUAL, I.B. 1144-1
Covering
Date of Original Publication
Date of Revision No. 1
Date of Revision No. 2
Date of Revision No. 3
Date of Revision No. 4
Date of Revision No. 5
Sep/93
Jul/95
Nov/95
Sep/97
Feb 01/00
Mar 01/02
INSTRUCTIONS:
1.
This revision is a completely revised reissue of I.B. 1144-1, which contains the information printed in the
original manual and all subsequent revisions. The manual was extensively revised to reflect the latest
manufacturing configurations and up-to-date information.
2.
Discard the original issue and all previous issues of this publication, and replace with Revision Number 5,
dated Mar 01/02.
3.
A bar in the left-hand column indicates where changes were made in this latest revision.
4.
Revision stripes are applied where data has changed.
5.
Discard this information page after completion.
I.B. 1144-1
23-20-02
Honeywell
System
Maintenance Manual
RTA-44D
VHF Data Radio System
Honeywell
CAGE Code 97896
I.B. 1144-1
23-20-02
T-1
Sep/93
Rev 5: Mar 01/02
Honeywell
NOTE
IF ANY UNUSUAL OR SPECIAL SERVICE PROBLEMS ARISE,
CONTACT HONEYWELL AIRLINES AND AVIONICS PRODUCTS
CUSTOMER SUPPORT DEPARTMENT.
PROPRIETARY NOTICE
This document contains proprietary information
and such information may not be disclosed to
others for any purpose, nor used for manufacturing purposes without written permission from
Honeywell International, Inc.
23-20-02
PN-1
No Date
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
REVISION NO. 5
Mar 01/02
REVISION HIGHLIGHTS
Pages that have been revised are listed below, together with the highlights of the revision.
- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - PAGE NUMBER
DESCRIPTION OF CHANGE
T-1
Updated Title Page format to current standards.
RH-1/RH-2
Updated Revision Highlights pages for Revision No. 5.
LEP-1/LEP-2
Updated "List of Effective Pages" for this revision.
Added reference to Mode 2 functionality of VDR.
Added -2000 and -2051 units to RTA-44D VHF Data Radio System
Components table, Figure 2.
Added reference to -2000 and -2051 units in Related Publications table,
Figure 4.
Added reference to VDR Mode 2 functionality and made corrections to
Configurations Available table, Figure 5.
Added Mode 2 VDR functionality to RTA-44D VHF Data Radio Features table,
Figure 6.
Added VDR Mode 2 units to Leading Particulars listing, Figure 7.
Changed number of pages in Figure 7.
Changed number of pages in Figure 7.
8.1
Added 750 Digital Mode to Leading Particulars table, Figure 7.
8.2
Added ARINC 429 Input Labels table, Figure 7.1
8.3/8.4
Added ARINC 429 Output Labels table, Figure 7.2
Added -2000 and -2051 units to Environmental Certification table, Figure 8.
10
Restructured Paragraph 4 to preserve logical order.
Figure 10.
11
Restructured Paragraph 4 to preserve logical order. Figure 10 moved to
Figure 10.1.
12
Restructured Paragraph 4 to preserve logical order. Figure 13 moved to
Figure 11. Added VDR Mode 2 to primary modes of operation listing.
13
Added Auxiliary Processor Module to System Component Description.
14
Added VDR Mode 2 Units (-2000 and -2051) Internal Architecture Diagram,
Figure 13. (This replaced old Figure 13, which moved to become 11.)
16
Added reference to Production Test Mode (PTM) Tool Quantum Line Tester to
I/O Section discussion. Added Basic Theory of Operation of Auxiliary
Processor Module paragraph.
17/18
Adjusted formatting to accommodate added Theory of Operation of Auxiliary
Processor Module paragraph.
I.B. 1144-1
23-20-02
Figure 11 moved to
RH-1
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
101
Added VDR Mode 2 Units, (-2000 and -2051) "Normal Screen" diagram to
Figure 101. Corrected screen nomenclature for consistency.
102
Updated LCD Control Flow by adding CMU PORT STATUS page to Figure
101.1
103
Corrected screen nomenclature for consistency.
106
Corrected screen nomenclature for consistency.
107
Added explanation of numeric/alpha notation to display screens.
109
Moved text from page 110 to page 109 to accommodate Figures 114.1 and
114.2.
110
Added new Failure pages from VDR Mode 2 units (-2000 and -2051), as
Figures 114.1 and 114.2. Corrected screen nomenclature for consistency.
111
Added "Tuning Port Status Page" Screen for VDR Mode 2 units (-2000 and
-2051) as Figure 116.1.
112
Added Valid Data Examples of "Tuning Port Status Page" Screen (-2000 and
-2051) as Figure 116.2.
113
Added "Discrete Input Status Page 4" Screen for VDR Mode 2 units (-2000
and -2051) as Figure 119.1.
114
Eliminated Figure 122.
115
Updated discussion of Previous Flight Legs Failure data. Corrected screen
nomenclature for consistency.
116
Corrected "Previous Flight Legs Failures Data Page" Screen, Figure 125.
202
Added mention of maximum cable loss specification.
203
Added mention of ARINC specification for ground path resistance.
204
Updated Radio Connector Determinants Table, Figure 201, Sheet 3.
205
Updated Radio Connector Determinants Table, Figure 201, Sheet 4
206
Updated Radio Connector Determinants Table, Figure 201, Sheet 5
207
Updated Radio Connector Determinants Table, Figure 201, Sheet 6
209
Added Software On Board Loadable Instructions.
210
Added Software On Board Loadable Instructions.
211
Added Software On Board Loadable Instructions
212
Added Software On Board Loadable Instructions
213
Added Software On Board Loadable Instructions
214
Added "Normal Mode" Screen for VDR Mod 2 units (-2000 and -2051), Figure
203.1.
215
Text moved from previous revision to accommodate new data on previous
pages and correction to "Test Complete, Failures" Screen, Figure 206 .
216
Text moved from previous revision to accommodate new data on previous
pages .
217/218
Text moved from previous revision to accommodate new data on previous
pages and Figure 207 updated.
219/220
Text moved from previous revision to accommodate new data on previous
pages and Figure 208 updated.
I.B. 1144-1
23-20-02
RH-2
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
RECORD OF REVISIONS
REV.
NO.
REVISION
DATE
DATE
INSERTED
BY
REV.
NO.
REVISION
DATE
DATE
INSERTED
BY
Complete through
Revision No. 5
I.B. 1144-1
23-20-02
RR-1
No Date
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
RECORD OF REVISIONS
REV.
NO.
I.B. 1144-1
REVISION
DATE
DATE
INSERTED
BY
REV.
NO.
23-20-02
REVISION
DATE
DATE
INSERTED
BY
RR-2
No Date
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
RECORD OF TEMPORARY REVISIONS
T.R.
NO.
DATE
DATE
INSERTED
BY
DATE
REMOVED
BY
Complete Through
Temporary Revision 23-5
I.B. 1144-1
23-20-02
RTR-1
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
RECORD OF TEMPORARY REVISIONS
T.R.
NO.
I.B. 1144-1
DATE
DATE
INSERTED
BY
23-20-02
DATE
REMOVED
BY
RTR-2
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
LIST OF EFFECTIVE PAGES
SUBJECT
PAGE
DATE
SUBJECT
Title Page
*T-1
Mar 01/02
Proprietary
Notice
PN-1
No Date
Revision
Highlights
*RH-1
*RH-2
Mar 01/02
Mar 01/02
Record of
Revisions
RR-1
RR-2
No Date
No Date
Record of
Temporary
Revisions
RTR-1
RTR-2
Mar 01/02
Mar 01/02
List of
Effective
Pages
*LEP-1
LEP-2
Mar 01/02
Blank
Table of
Contents
TC-1
TC-2
Mar 01/02
Blank
Introduction
INTRO-1
Mar 01/02
Description
and Operation
*2
*3
*4
*5
*6
*7
*8
*8.1
*8.2
*8.3
*8.4
*9
*10
*11
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*13
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15
*16
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18
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Fault Isolation
*101
*102
*103
104
Mar 01/02
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I.B. 1144-1
Maintenance
Practices
23-20-02
PAGE
DATE
105
*106
*107
108
*109
*110
*111
*112
*113
*114
*115
*116
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*202
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*205
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208
*209
*210
*211
*212
*213
*214
*215
*216
F*217
F 218
F*219
F*220
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LEP-1/LEP-2
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
TABLE OF CONTENTS
Paragraph/Title
Page
DESCRIPTION AND OPERATION
- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
FAULT ISOLATION
- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 101
MAINTENANCE PRACTICES
- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 201
I.B. 1144-1
23-20-02
TC-1/TC-2
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
INTRODUCTION
This manual, I.B. 1144-1 (23-20-02), contains
information covering description and operation,
installation, and flight-line checkout procedures for the
Honeywell International, Airlines and Avionics Products
RTA-44D VHF Data Radio System
I.B. 1144-1
23-20-02
INTRO-1
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
RTA-44D VHF Data Radio
Figure 1
I.B. 1144-1
Page 0
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
DESCRIPTION AND OPERATION
1.
General
This section contains descriptive information covering the RTA-44D VHF Data Radio (VDR) System and
lists other components required for system operation. The RTA-44D VHF Data Radio (VDR) is illustrated
in Figure 1.
A. Purpose of Equipment
The RTA-44D VHF Radio (VDR) System is an airborne VHF Communications Transceiver designed to
provide voice and data communication between on-board aircraft systems, to other aircraft systems,
and to ground-based systems.
The VDR is designed to Aeronautical Radio Incorporated (ARINC) 716 Airborne VHF Communications
Transceiver and ARINC 750 Airborne VHF Data Radio Specifications, Radio Technical Commission for
Aeronautics (RTCA) documents number DO-186a Minimum Operational Performance Standards
(MOPS) for Airborne Radio Communications Equipment Operating within the Radio Frequency Range
117.975 - 137.000 Megahertz and number DO-207 MOPS for Devices that Prevent Blocked Channels
Used in Two-Way Radio Communications Due to Unintentional Transmissions, and European
Organization for Civil Aviation Equipment (EUROCAE) ED-23B Minimum Performance Specification for
Airborne VHF Communications Equipment Operating in the Frequency Range 117.975 - 137.000 MHz.
The VDR is fully interchangeable with the earlier ARINC 716 RTA-44A VHF Communications
Transceiver for backward compatibility.
In an Aircraft Communications Addressing and Reporting System (ACARS), the VDR is a simple
transceiver with an analog interface to the ACARS Management Unit (MU) or a MSK modem.
In Mode 2, the VDR contains a D8PSK modem and a digital high speed ARINC 429 link to the
MU/CMU/ATSU per Mode 2 functionality in ARINC 750-3.
The 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, CMU
or ATSU for its digital control and data functions. The VDR system may also be connected to a Central
Maintenance Computer (CMC) or Central Fault Display System (CFDS) to transfer maintenance data.
Depending upon the selected mode, the VDR operates with the following equipment:
• an ARINC 597, 724, or 724B ACARS MU,
• an ARINC 604 and Airbus Industrie ABD-0048C Centralized Fault Display Interface Unit
(CFDIU),
• an ARINC 716 voice audio input source and output sink,
• an ARINC 716 voice frequency control source,
• an ARINC 758 CMU or ATSU.
• an antenna.
B. Equipment Part Numbers
Components of the RTA-44D VHF Data Radio System supplied by Honeywell are listed in Figure 2. The
figure lists the currently available components of the system, along with part numbers and equipment
type numbers.
I.B. 1144-1
23-20-02
Page 1
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
EQUIPMENT
TYPE NUMBER
RTA-44D
VHF Data Radio
EQUIPMENT DESCRIPTION
Airborne VHF Data Radio (VDR) capable of VHF
COM (ARINC 716, EUROCAE ED-23B) voice and
analog data processing through digital signal processing (DSP) over a frequency range of 118.000
to 136.975 MHz with 25-kHz channel spacing. The
VDR contains 8.33-kHz channel spacing capability
per ARINC 716, Supplement 8. VDR is also capable of RTCA DO-207 "stuck mike" detection without warning tone. Complies with DO-178B.
Capable of interfacing CMC per ARINC 604.
Honeywell
PART NUMBER
064-50000-0101
Capable of data recording and loading from the
front of the unit, and software loading from the rear
connector through an ARINC 615 data loader.
The VDR contains an RS-232 port on the front
panel for ease of maintenance. Meets DO-160C
lightning protection and 200-ms power interrupt
transparency requirements. Meets HIRF requirements and ICAO Annex 10 requirements (RTCA
DO-186a).
Same as -0101, except added new software to
adjust squelch when 8.33-kHz channel spacing is
selected.
064-50000-0110
Same as -0101, except "stuck mike" detection
emits a 1-khz interrupted warning sidetone during
last five seconds of 35-second transmission.
064-50000-0202
Capable of interfacing CFDS per ARINC 604 and
Airbus Industrie ABD-0048C.
Same as -0202, except capable of interfacing
CFDS in accordance to McDonnell Douglas software requirements (replaces ABD-0048C implementation).
064-50000-0303
Same as -0202, except it adds Mode A functionality per ARINC 750-3.
064-50000-0505
Same as -0110, except it adds Mode A and Mode 2
functionality specified in ARINC 750-3 and meets
DO-160D requirements.
064-50000-2000
Same as -0505, except it adds Mode 2 functionality
specified in ARINC 750-3 and meets DO-160D
requirements.
064-50000-2051
RTA-44D VHF Data Radio System Components
(Honeywell Supplied)
Figure 2
I.B. 1144-1
23-20-02
Page 2
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
C. Equipment Required but Not Supplied
Figure 3 lists equipment required for the RTA-44D VHF Data Radio System, but not supplied by
Honeywell.
EQUIPMENT
DESCRIPTION
Power Source
DC power supply of 27.5 volts.
Receive - 1 ampere, Transmit - 7 amperes (at stated input voltage.)
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 in conformance to ARINC 716.
MU/CMU/ATSU
Provides control and data source/sink when operating in the 750 data
mode.
3 MCU Unit Mount
Provides a means of mounting RTA-44D VHF Data Radio in the aircraft.
VHF Antenna
Capable of receiving and transmitting VHF signals over a frequency range
of 118.000 through 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 as shown in RTA-44D VHF Data Radio
System Interwiring Diagram, Figure 208.
Equipment Required but Not Supplied
Figure 3
D. Related Publications
Figure 4 lists the publications covering the RTA-44D VHF Data Radio and test procedure supporting the
system.
HoneywelI
IDENTIFICATION
NUMBER
PUBLICATION
ATA
IDENTIFICATION
NUMBER
RTA-44D VHF Data Radio
Part Numbers 064-50000-0101, -0110 and -2000
Component Maintenance Manual
I.B. 1144A-2
23-20-36
RTA-44D VHF Data Radio
Part Numbers 064-50000-0202, -0303, -0505 and -2051
Component Maintenance Manual
I.B. 1144A-3
23-20-38
Related Publications
Figure 4
I.B. 1144-1
23-20-02
Page 3
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
2.
Configurations Available
Figure 5 lists the available configurations of the RTA-44D VHF Data Radio and the features contained in
each configuration. Figure 6 contains a brief description of each feature.
FEATURES
COMPATIBILITY
INTERFACE
Honeywell
PART
NUMBER
064-50000
BASIC
UNIT
FAULT
MEMORY
-0101
-0110
STUCK
MIKE
ALARM
8.33-kHz
CHANNEL
SPACING
Mode
Mode
ACARS
BOEING
CMC
-0202
X1
X3
-0303
X2
-0505
X1
-2000
X4
-2051
X1
X4
CFDS
1 = Airbus CFDS interface software.
2 = McDonnell Douglas CFDS interface software.
3 = All -0202 hardware capable. 02/02 software required for squelch adjustment for 8.3-kHz channel spacing.
4 =On Board Loadable Dependent.
RTA-44D VHF Data Radio, Configurations Available
Figure 5
FEATURE
DESCRIPTION
Basic Unit
Airborne solid-state VDR is capable of receiving and transmitting ARINC
716 voice and ARINC 716 data over a frequency range of 118.000 to
136.975 MHz with 25-kHz channel spacing. Channel spacing capability
of 8.33-kHz per ARINC 716, Supplement 10 is available as well as RTCA
DO-207 "stuck mike" detection. Complies with DO-178B software
requirements and enhanced BITE requirements of Airbus, Boeing, and
McDonnell Douglas.
RTA-44D VHF Data Radio Features
Figure 6
Sheet 1 of 2
I.B. 1144-1
23-20-02
Page 4
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
FEATURE
Basic Unit (Continued)
DESCRIPTION
Capable of data recording and loading from the front of the VDR, and
software loading from the rear connector through an ARINC 615 data
loader. Contains an RS-232 port on the front panel for ease of
maintenance. Meets RTCA DO-160C lightning protection and 200 ms
power interrupt transparency requirements. Meets HIRF requirements
and ICAO Annex 10 requirements (RTCA DO-186a). Front panel LCD
displays unit's characteristics (part number, serial number), BITE
status with fault location help pages, line maintenance values with help
pages, and software data loading help screens.
Fault Memory
A nonvolatile, single-chip fault memory that allows the recording of
faults associated with a particular flight leg. Sixty-four flight legs are
available with each flight leg made up of a flight-leg information header
containing a fault record section for recording ten airborne faults and
three ground faults. When all flight legs have been used, the oldest
flight leg shall be reused.
Stuck Microphone Alarm
After the VDR detects that the microphone is in the transmit (keyed)
position for a time duration longer than 30 seconds, a 1 kHz
interrupted tone (½ second on, ½ second off) is emitted for five
seconds via the audio/sidetone output. After a total of 35 seconds, the
VDR turns off the transmitter and the 1 kHz interrupted sidetone. To
reactivate the transmitter, the microphone push-to-talk button must be
released and then rekeyed.
ACARS Compatible
CMC Interface
The VDR ensures proper processing of the ACARS messages.
CFDS Interface
The VDR interfaces fault memory and BITE data between the VDR
and line maintenance Centralized Fault Display Interface Unit (CFDIU)
for the purpose of extracting maintenance information and initiating
tests. Designed to conform with ARINC 429 interfaces, ARINC 604
and Airbus Industrie ABD-0048C or McDonnell Douglas software
requirements.
8.33-kHz Channel
Spacing Capability
The VDR is capable of 8.33-kHz channel spacing to meet the
European narrow-band (8.33-kHz) VHF voice communications
systems. The narrow-band mode of operation is limited to voice
communications.
Mode A
The Mode A VDR contains an ACARS MSK modem and a digital high
speed ARINC 429 link to the MU/CMU/ATSU per the Mode A
functionality specified in ARINC 750-3.
Mode 2
The Mode 2 VDR contains a D8PSK modem and a digital high speed
ARINC 429 link to the MU/CMU/ATSU per Mode 2 functionality in
ARINC 750-3. The Mode 2 VDR meets DO-160D requirements.
The VDR interfaces fault memory and BITE data between the VDR
and line maintenance Centralized Maintenance Computer (CMC) for
the purpose of extracting maintenance information and initiating tests.
Designed to conform with ARINC 429 interfaces and ARINC 604
requirements.
RTA-44D VHF Data Radio Features
Figure 6 (Sheet 2 of 2)
I.B. 1144-1
23-20-02
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Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
3.
System Leading Particulars
A. Unit Specifications
Figure 7 lists the leading particulars for the RTA-44D VHF Data Radio System.
CHARACTERISTICS
DESCRIPTION
General - Overall VDR
Form Factor
3 MCU (ARINC 600)
Dimensions
Refer to outline drawing, Figure 207.
Weight
9.6 LBS., (4,4Kg) Maximum
General - Overall VDR
Power Requirements
27.5 Vdc nominal (+10%, -20%)
1.0A - Receive (-0101, -0110, -0202, -0303 and -0505)
1.5A - Receive (-2000 and -2051)
7.0A - Transmit (All Units)
Temperature
Operating
Storage
-55°C to +70°C (-67°F to +158°F) (-0101, -0110, -0202, -0303 and -0505)
-15°C to +70°C (5°F to 158°F)
(-2000 and -2051)
-65°C to +85°C (-85°F to +185°F) (All Units)
Cooling
ARINC 600
Humidity
Zero to 95%
Altitude
To 15,240 meters (50,000 feet)
Warm-up period
None; stable operation after power application.
Frequency Control
ARINC, 429 Mark, 33 (Serial Digital)
Frequency Range
118.000 MHz to 136.975 MHz
Channel Spacing
25-kHz and 8.33-kHz
Frequency Stability
±0.0005%
Duty Cycle
Continuous operation from -55°C to +70°C with ARINC 600 cooling.
Certification
-0101, -0110, -0202, -0303 and
-0505 Units
-2000, -2051 Units
General - Analog Voice/Data
Channel Changing Time
Transmit to Receive Recovery
TSO C37d Class 3 and 5 and C38d Class C and E;
DO-160C Categories
/A2D2/ZCA/MNB/XXXXXXAAAZZUZ/XXE2/XX
DO-186a, DO-178B, DO-207 AND EUROCAE ED-23B
TSO C37d Class 3 and 5 and C38d Class C and E;
DO-160D Categories
[(A2)(D2)Z]BAB[RB1]XXXXXXZAAZCRRL[A2C2]XXA
DO-186a, DO-178B, DO-207 AND EUROCAE ED-23B
Less than 50 milliseconds to stabilize on a new channel frequency.
Less than 50 milliseconds after transmission to provide 90% of its output
at an input level of 10 µV modulated 30% at 1000 Hz.
Leading Particulars
Figure 7 (Sheet 1 of 4)
I.B. 1144-1
23-20-02
Page 6
Mar 01/02
Honeywell
MAINTENANCE MANUAL
RTA-44D VHF DATA RADIO SYSTEM
CHARACTERISTICS
Analog Voice Receiver
Sensitivity
Selectivity
25-kHz Channel Spacing
8.33-kHz Channel Spacing
DESCRIPTION
Greater than 6 dB SINAD for -107 dBm signal modulated
30% at 1000 Hz.
±8-kHz at 6 dB bandwidth, ±17-kHz at 60 dB bandwidth.
±2.78-kHz at 6 dB bandwidth, ±7.365-kHz at 60 dB
bandwidth.
Cross Modulation
Meets requirements of ARINC 716, Section 3.6.4.
AGC
Within 3 dB with inputs from 5 µV to 100,000 µV and not
more than 6 dB with inputs from 5 µV to 500,000 µV.
Audio Output
40 milliwatts maximum into a 600 ±20% ohm resistive
load, factory set at 10 mW at 1000 Hz.
Audio Output Frequency Response
Within 6 dB from 300 to 2500 Hz.
Audio Output Harmonic Distortion
Total harmonic distortion will not exceed 5% with
1000 µV input signal modulated 30% at 1000 Hz.
Audio Output Regulation
No more than 2 dB voltage change from a 10 mW
reference level into 600 ohms for resistive load
variations between 450 ohms to 2400 ohms, and no
more than 6 dB voltage change for resistive load
variations between 200 ohms and 20k ohms.
Voice Phase Shift Limit
Audio output does not depart from that of the
positive-going modulation envelope at the receiver input
by more than -30° to +120° with a 1000 µV input signal
modulated 30% at 1000 Hz and an output level adjusted
for 40 milliwatts into a 600-ohm resistive load.
Undesired Responses
80 dB
Input Impedance
50 ohms, nominal
Analog Voice Transmitter
Output Power
25 watts (nominal)
Harmonic and Spurious Emission
Any harmonics of the desired frequency is attenuated at
least 60 dB below the desired carrier level and any other
emission will be attenuated at least 118 dB below the
carrier level.
Leading Particulars
Figure 7 (Sheet 2 of 4)
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CHARACTERISTICS
DESCRIPTION
Analog Voice Transmitter (Con’t)
Transmitter Modulation Frequency
Response
Flat within 6 dB from 300 Hz to 2500 Hz.
Audio Distortion
6% maximum for 30% modulation and 10% maximum
for 90% modulation with a 0.5 volt input and a
modulating frequency from 300 Hz to 2500 Hz.
Modulation Level
90% modulation minimum for an input level of 0.25 volts
rms at 1000 Hz.
Analog Data Receiver
Gain SELCAL/Output
0.6 volts rms minimum with a 2 µV signal modulated
30% at 1000 Hz into a 600-ohm load.
Frequency Response SELCAL
Output
±2.5 dB from 312 Hz to 1200 Hz (post detection
response with respect to 1000 Hz is ±4.5 dB from
300 Hz to 6600 Hz).
Distortion SELCAL Output
4.5% maximum with an input signal of 1000 µV
modulated 30% at 1000 Hz and a level adjusted to
provide 0.5 volts into a 600-ohm load.
AGC Attack Time SELCAL Output
Reaches 90% of its steady-state value within
30 milliseconds maximum after the step application of an
RF carrier of 1000 µV modulated 30% at 1000 Hz.
AGC Decay Time SELCAL Output
Reaches 90% of its steady-state value within
45 milliseconds maximum after the receiver input of
1000 µV modulated 30% at 1000 Hz is step reduced to
10 µV.
Analog Data Transmitter
Modulation Level Data Input
70% modulation minimum for a frequency of 1000 Hz at
a -10 dBm level.
Frequency Response Data Input
Flat within 5.5 dB from 600 Hz to 6600 Hz.
Distortion Data Input
9.5% maximum distortion at modulation level up to 90%
over frequency range of 600 Hz to 6600 Hz.
Leading Particulars
Figure 7 (Sheet 3 of 4)
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RTA-44D VHF DATA RADIO SYSTEM
CHARACTERISTICS
DESCRIPTION
Digital Data Receiver (750 Mode)
Sensitivity
<0.01 message error rate @ -104 dBm (Mode A)
<10-3 Uncorrected BER @ -98 dBm (Mode 2)
Dynamic Range
Min. -7 dBm.
Adjacent Channel Rejection
+/-25-kHz
+/-50-kHz
+/-100-kHz and beyond
+44 dBc
+50 dBc
+60 dBc
Interference Rejection
Out-of-Band
Co-Channel
Per ARINC 750-3, para 4.3.4.3
-20 dBc Interferer
Channel Sensing
Modulated Signal Sensed (Mode A)
Carrier Sensed (Mode 2)
Digital Data Transmitter (750 Mode)
Output Power
25W nominal (Mode A)
17.5 +/- 2W (Mode 2)
Modulation Type and Data Rate
2400 bps Amplitude Modulated Minimum Shift
Keying, AM-MSK (Mode A)
31,500 bps Differential 8-Phase Shift Keying, D8PSK
(Mode 2).
Duty Cycle
20% as defined in ARINC 750-3 para. 4.2.2
Transmitter Emissions (Mode)
Adjacent Channel
+/- 25kHz (25kHz BW)
+/- 25kHz (16kHz BW)
+/- 50kHz (25kHz BW)
+/- 100kHz (25kHz BW)
Wideband Noise
+2 dBm
-18 dBm
-28 dBm
-38 dBm
Decreases 5 dB/octave from +/-100-kHz to -53 dBm max
emission in 25-kHz BW (118-136.975 MHz)
Phase/Amplitude Balance (Mode 2)
8% Error Vector Magnitude
Spurious Radiation
Per ARINC 750-3 para. 4.2.8.6
Tuning Time
100 ms
Transmitter Ramp-up
2 ms for Pre-key (Mode A)
reaches 90% at least 3 symbols prior to
Preamble (Mode 2)
Data Clock Stability
0.005%
Leading Particulars
Figure 7 (Sheet 4 of 4)
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429 INPUT LABEL
RATE
DESCRIPTION
Tuning Bus A and B (Low Speed)
030
047
276
200 ms
200 ms
500 ms
Tuning Frequency 25-kHz
Tuning Frequency 8.33-kHz
Voice/Data Indication
270
1 second
CMU Status Word
250, 251, 252, 253 (When Own Aircraft
SDI is 0, 1, 2, or 3 respectively
Whenever Data
available
CMU Solo words and BOP files
Follows ARINC
615 protocol
ARINC 615 Data loader
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
1 second (+.5)
City Pair 1
City Pair 2
City Pair 3
UTC
Flight Phase
Aircraft Configuration 1
Aircraft Configuration 2
Aircraft Configuration 3
Command Word
Flight Number 1
Flight Number 2
Flight Number 3
Flight Number 4
Flight Number 5
Date
Flight Number
Aircraft ID 1
Aircraft ID 2
Aircraft ID 3
Aircraft ID 4
CMU Input Bus 1 and 2 (High Speed)
(-0505, -2000, -2051)
Data Loader Input Bus (High Speed)
251
CMC Data Input Bus 1 and 2 (Low Speed)
040
041
042
125
126
1551
1561
1571
227
233
234
235
236
237
260
2612
301
302
303
304
NOTES:
For Airbus Only (-0202, -0505, -2051)
For McDonnell Douglas Only (-0303)
VDR ARINC 429 Input Labels
Figure 7.1
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429 OUTPUT LABEL
RATE
DESCRIPTION
CMU Output Bus (High Speed)
(-0505, -2000, -2051)
270
1 second
VDR Status Word
172
1 second
System Address Label
377
1 second
Equipment Identifier
304
Whenever data to send to
CMU
VDR Solo words and BOP Files
Follows ARINC 615
protocol
ARINC 615 Data Loader
350
750 ms
Fault Summary Word
354
50 ms to 250 ms
LRU Identification (P/N and S/N)
50 ms to 250 ms
3 ms and 3 seconds max.
ISO 5 Fault Message
Normal Mode
Interactive Mode
1 second maximum
ARINC 429 Equipment Identification
Data Loader Output Bus (High Speed)
226
CMC Output Bus (Low Speed)
356
377
VDR ARINC 429 Output Labels
Figure 7.2
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B. Environmental Certification
The RTA-44D VHF Data Radio meets the environmental conditions of the Radio
Technical Commission for Aeronautics (RTCA) document number DO-160C
(DO-160D for -2000 and -2051), "Environmental Conditions and Test Procedures for
Airline Electronic/Electronical Equipment and Instruments". The environmental
certification categories of the VDR, P/N 064-50000-0101, -0110, -0202, -0303 and
-0505, are: /A2D2/ZCA/MNB/XXXXXXAAAZZUZ/XXE2/XX.
The environmental certification categories of the VDR, P/N 064-50000-2000 and
-2051 are: [(A2)(D2)Z]BAB[RB1]XXXXXXZAAZCRRL[A2C2]XXA.
TEST
CATEGORY FOR UNITS P/N
064-50000
-0101, -0110, -0202,
-0303, -0505
-2000, -2051
Temperature and Altitude
A2D2
A2D2
In-Flight Loss of Cooling
Temperature Variation
Humidity
Meets Specification
MNB
RB1
Explosion Proofness
Waterproofness
Fluids and Susceptibility
Sand and Dust
Fungus Resistance
Salt Spray
Magnetic Effect
Power Input
Voltage Spike
Audio Frequency Conducted Susceptibility - Power Inputs
Induced Signal Susceptibility
Radio Frequency Susceptibility (Radiated and Conducted)
RR
Emission of Radio Frequency Energy
XXE2
A2C2
Lightning Direct Effects
Icing
Operational Shocks and Crash Safety
Vibration
Lightning Induced Transient Susceptibility
Electrostatic Discharge
Environmental Certification Categories of RTA-44D
Figure 8
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4.
System Description
Figure 9 Deleted by Revision 3
A. VDR System
The VDR system consists of an antenna for its rf inputs and outputs, a control head or radio
management panel (RMP) (refer to Figure 10) and an audio input source and output sink for its analog
voice functions. The VDR system may also be connected to a Central Maintenance Computer (CMC)
or Centralized Fault Display System (CFDS) to transfer maintenance data.
VHF Communications for Voice Operation
Figure 10
There are four primary modes of operation in the VDR system:
• ARINC 716 voice compatibility mode, 25-kHz or 8.33-kHz channel spacing,
• ARINC 716 data compatibility mode.
• ARINC 750 Mode A
• ARINC 750 Mode 2
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The ARINC 716 voice and data modes emulate the current ARINC 716 radio functions found in the previous
RTA-44A VHF Transceiver System.
B. ARINC 716 Data Mode
In ACARS, the VDR system is a simple transceiver with an analog interface to the ACARS Management
Unit (MU) (refer to Figure 10.1).
ACARS Audio Interface
Figure 10.1
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C. ARINC 750 Modes A and 2
Figure 11 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.
RTA-44D External Interfaces (ARINC 750 Mode)
Figure 11
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5.
System Component Description
A. RTA-44D VHF Data Radio
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 from
118.000 MHz to 136.975 MHz. Frequency selection is provided through a serial-digital format in
accordance with ARINC Specification 429.
The VDR is completely solid state and is housed in an ARINC 3-MCU case per ARINC
Specification 600. A handle is located on the front panel of the VDR to facilitate installation, removal,
and transport of the VDR.
The VDR uses a low insertion force, size one 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".
Forced air cooling, in accordance with ARINC specification 600, is required for cooling the VDR.
For maintenance purposes, a microphone jack and headphone jack are provided on the front panel of
the VDR. A front panel display provides an interface to an operator via a liquid crystal display (LCD)
that is visible from the front of the VDR to display messages in simple language in one of four modes:
normal operation, BITE display, maintenance, and software loading.
Software loading and data recording of data to/from the CPU is via the front panel Personal Computer
Memory Card International Association (PCMCIA) slot. Intel Series 1 Flash Cards with capabilities
ranging from 1 up to 64 megabytes are supported.
Two pushbutton switches allow operator interface with the VDR LCD.
In normal operation, the front panel LCD displays the unit's characteristics: unit identification, part
number, and serial number. The BITE display mode is activated after manual self-test has been
exercised either from the front panel test pushbutton or remotely. In the BITE mode, BITE status is
reported and in the event of a detected failure, additional help screens are provided to locate the
detected failure to a module. BITE help pages are provided. In the maintenance mode, a set of
maintenance words are displayed and decoded showing the names of data fields and the value of the
data. Maintenance help pages are provided. For loading software, a series of screens direct the
operator during the data loading process. Software version and loading status are provided during the
update process.
The VDR is partitioned into six subassemblies: RF Module, Main Processor Module, HIRF/Interconnect
Module, Power Supply Assembly, Display Assembly, and Flash Card Memory Module (refer to
Figure 12). An Auxiliary Processor Module was added for ARINC 750 Mode 2 (-2000, -2051) operation
(refer to Figure 13).
B. Other Components in the System
Other VDR system components are not supplied by Honeywell AIrlines and Avionics Products.
Information on these units must be obtained from their respective manufacturers.
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RTA-44D VHF Data Radio, Simplified Block Diagram
Figure 12
RTA-44D Internal Architecture (-2000, -2051)
Figure 13
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6.
Operation
A. General
Operation of the VDR is either controlled by a control unit (for voice operation) which provides squelch
threshold and operating frequency or by the MU or data operation.
The VDR has two basic areas of operation: as a standard double sideband AM analog voice transceiver
and as a data-capable transceiver. Depending on the selected data mode, the VDR performs
transceiver, modem, and/or link layer functions.
In an AVPAC system, the VDR is either a simple transceiver with an analog interface or a link layer
bridge for the subnetwork. In an ACARS system, the VDR is either a simple transceiver with analog
interface to the ACARS Management Unit or a MSK modem.
Three modes of operation are available: ARINC 716 voice mode compatibility, ARINC 716 data mode
compatibility, and ARINC 750 data mode. The ARINC 716 voice and data modes emulate the current
ARINC 716 radio functions. While in the ARINC 750 data mode, the VDR bridges ACARS traffic
between the MU/VDR digital bus and its internal 2.4 Kbps MSK modem or bridge AVPAC traffic between
the MU/VDR digital bus and its 2.4 Kbps MSK modem or its 31.5 Kbps DPSK modems.
The ARINC 716 voice mode is the basic VHF communications transceiver compatible voice mode
defined in ARINC 716 and retained for backward compatibility. Voice signals are provided via normal
audio I/O, with transmit and receive conditions initiated by the operator with the microphone. The RF
signal in space is a double sideband amplitude modulation. Tuning/frequency selection is made by
low-speed ARINC 429 data words from an associated radio control panel.
The ARINC 716 data mode is the basic VHF communications transceiver compatible data mode
defined in ARINC 716 and retained for backward compatibility. Data is transferred via analog discrete
methods using two conductor twisted pairs. Tuning data is provided via a low-speed ARINC 429 data
bus, while transmit/receive commands are discrete digital signals from the management unit. Operating
air/ground protocols are either ARINC 618 (ACARS) or ARINC 631 (AVPAC).
When in the ARINC 750 data mode, both tuning and digital data is received over a high-speed
ARINC 429 port. While in the ARINC 750 mode, the management unit (MU) may command the VDR
to operate as either an ACARS MAC bridge or as an AVPAC link layer bridge. While in this mode, the
data rate and modulation scheme is determined by the management unit.
B. Basic Theory
(1) RF Module
When receiving, the VDR RF Module amplifies and converts the RF signals received by the
antenna into analog signals for processing by the digital-signal processor (DSP) section of the
main processor module. Conversely, when transmitting, the RF Module modulates the analog
signals provided by the DSP section into RF signals for transmission through the antenna.
(2)
Main Processor Module
The Main Processor controls the VDR’s mode of operation, the aircraft interfaces, and the data
displayed on the front panel. In the receive mode, the Main Processor Module processes the
analog signals from the RF Module and generates the voice and MSK audio output when in the
ARINC 716 voice or data mode. In the transmit mode, the Main Processor Module processes the
voice and MSK audio inputs when in the ARINC 716 voice and data modes, and generates analog
signals to the RF Module.
(a)
DSP Section
The DSP section is used to process the analog outputs from the RF Module and to generate
some of the control signals to the RF Module for transmit modulation, automatic gain control,
and test signals.
The receiver 455-kHz I-F from the RF Module is digitized using an A/D converter. The A/D
converter is also used to monitor signals from the BITE test points on the RF Module and
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the power supply voltages. The digitized data from the A/D converter is stored in a FIFO
which is accessed by the DSP.
A D/A converter routes the DSP generated AGC and test control signals to the RF Module.
A second D/A converter provides the audio outputs which are amplified to provide up to
40 milliwatts into a load ranging from 200 ohms to 600 ohms.
Data is exchanged with the CPU section through a dual-port RAM (random access memory)
providing maximum throughput of both processors.
(b)
CPU Section
The CPU section is used to process the data from the DSP section, to provide information
to the front panel display, and to provide the data and control signals to the I/O section.
The microprocessor in the CPU section controls all major functions to the VDR.
Programmable logic devices serve as the microprocessor controller and provide the
interfaces to the memory devices (boot routine, program, fault, and data), the data
recorder/data loader flash card, and the front panel display driver.
Data is exchanged with the DSP section through a dual-port RAM.
(c)
I/O Section
The I/O section provides the interfaces with other aircraft systems including the ACARS
Management Unit (MU), Central Maintenance Computer (CMC), Data Loader, control
panels, and displays.
ARINC 429 inputs from the tuning control panels, data loader, and CMC are processed by
the ARINC 429 LSIs. These LSIs also provide the ARINC 429 data loader, and CMC
outputs. External buffers are used to satisfy the ARINC 429 characteristics for the
transmitters.
All discrete inputs and outputs external to the VDR are processed by discrete components
and digital latches.
The I/O section also contains an RS-232C test interface. This test interface is also used to
update serial number, part number and memory configuration, as applicable, utilizing the
stand alone version of the Production Test Mode (PTM) Tool or PTM utility in the RTS
software when the Main Processor Module is replaced.
(3)
Auxiliary Processor Module
The Auxiliary Module’s DSP communicates with the Main Processor’s TMS320C31 via a single,
bi-directional, on-chip serial port. 84-kHz sampled RF receiver data are transferred serially from
the Main Processor’s DSP to the Auxiliary Processor’s DSP to be processed. The Auxiliary
Module’s higher performance TMS320VC33 DSP is then used to perform decimation, frequency
correction, symbol synchronization, equalization, time tracking, D8PSK symbol decoding,
descrambling, de-interleaving, RS block error correction, flag and bit removal, transmission
header decoding, preamble detection, frequency error estimation and symbol timing estimation.
(4)
Power Supply Module
The 27.5 volts dc aircraft power is converted by the Power Supply Module into the dc operating
voltages required by the various modules within the VDR. A self-contained, high efficiency
switching power supply is used to minimize power dissipation.
(5)
HIRF/Rear Interconnect
To prevent High Intensity Radiation Fields (HIRF) or lightning from affecting operation by entering
via rear connector cables, a HIRF compartment is formed in the rear of the VDR. The signal and
power cables are filtered by using discrete and distributed filter elements and limiting devices on
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the Rear Interconnect Module located inside this HIRF compartment. The filtered lines are then
fed to the appropriate points in the VDR.
The VDR is packaged in an aluminum casting. This seamless main frame ensures HIRF cannot
enter the unit through structural seams. The slots formed by the removable side covers are
sealed against HIRF with protective gaskets and metal covers.
(6)
Front Panel Display Assembly
The Front Panel Display Module is mounted behind the front panel and provides an interface to
an operator via a low-power liquid crystal display (LCD) that is visible from the front of the VDR.
In addition to the LCD, the module contains "Light Pipe" backlighting, temperature compensation
circuitry, and a PC board containing an associated LCD driver, two pushbutton switches, and a
D-sub, nine-pin, RS-232 serial type connector.
The LCD is a bit-mapped display capable of displaying alphanumeric and graphical symbols.
Simple messages written in plain language minimize the potential for misunderstanding or
incorrect interpretation. The LCD displays the following:
• Part Number/Software Identification,
• Status,
• Results of Level 1 BITE Tests,
• Maintenance Help Pages,
• Shop Maintenance Data,
• Flight Fault Memory Contents,
• Software Loading Status
(7)
Memory Card Interface Module
The Memory Card Interface Module is used to load software program data into the CPU or record
software program data from the CPU. The Memory Card Interface Module supports Series 2
FLASH cards via the front panel Personal Computer Memory Card International Association
(PCMCIA) slot. Cards with the capabilities ranging from 1 up to 64 megabytes are supported. The
FLASH card is inserted through the front panel. In one mode, data stored on the flash card
memory module is used to update program or data memory in the VDR. In another mode, the
flash card memory module functions as a data recorder.
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FAULT ISOLATION
1.
General
Fault isolation is the process of isolating the source of a system failure to an LRU (line replaceable unit) or
to the aircraft wiring.
Fault isolation in the RTA-44D VHF Data Radio System includes a continuity check of the interwiring, and
the assurance that proper installation techniques and procedures have been followed.
A functional self test of the LRU may be initiated by pressing the "test" key pushbutton switch as designated
on the front panel LCD (Figure 101). Although the "Normal Mode" Screen indicates that this is actuated
from the right key, the left key has the same function if pressed while the VDR LCD is in its Normal Mode.
↓
↓
Typical "Normal Mode" Screen (-0101, -0110, -0202, -0303 and -0505)
↓
↓
NOTE: "Wrong AC Type" appears only if discretes are not correct at MP-C11 and MP-A14 - see
Figure 208 11 .
Typical "Normal Mode" Screen (-2000 and -2051)
Figure 101
Figure 101.1 illustrates the control flow of the LCD screens (except for the data loading and data recording
screens).
A complete functional test of the system can be performed as described in paragraph 7.B. in "Maintenance
Practices" Section 200 of this manual.
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LCD Control Flow
Figure 101.1
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2.
Self-Test Mode
The Self-Test Mode starts by displaying the "Test in Progress" Screen (Figure 102) one second after
pressing the "test" key. This is displayed for four seconds with a moving thermometer along the bottom of
the LCD indicating the progress of the test from one to five seconds.
"Test in Progress" Screen
Figure 102
The "Normal Mode" Screen (Figure 101) is displayed for the first second of the test sequence.
Once complete, the "Test Complete, No Failures" Screen is displayed (Figure 103), or the "Test Complete,
Failures" Screen is displayed (Figure 104). Both screens contain two key selections each: "MAINT" and
"RETURN" or "MAINT" and "WHY?", respectively.
• "MAINT"
For both screens, "MAINT" is located on the left key. This allows the initiation
of the extended maintenance pages of the system for troubleshooting. Refer
to paragraph 4.
• "RETURN"
In the "Test Complete, No Failures" Screen, the "RETURN" key to the right
returns the system to its "Normal Mode" Screen (Figure 101).
• "WHY?"
In the "Test Complete, Failures" Screen, the "WHY?" key to the right puts the
system into the Display-Failures Mode where individual system failures are
displayed one per page. Refer to paragraph 3.
While in the Self-Test Mode, not pressing either key for five minutes causes the system to return to the
"Normal Mode" Screen (Figure 101).
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"Test Complete, No Failures" Screen
Figure 103
↓
"Test Complete, Failures" Screen
Figure 104
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3.
Display-Failures Mode
One of three failure possibilities exist: the VDR is okay, but there are external failures (Figure 105), the VDR
failed and there are external failures (Figure 106), and the VDR failed, but there are no external failures
(Figure 107).
↓
"VHF Data Radio OK, External Failures Present" Screen
Figure 105
↓
"VHF Data Radio Failed, External Failures Present" Screen
Figure 106
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"VHF Data Radio Failed, External Failures Not Present" Screen
Figure 107
All "Display-Failures Mode" Screens have the "MORE" selection on the right key. The only exception is
when there is only one failure page. This only happens when the VDR itself has failed and no other external
failure exists (Figure 107).
• "MORE"
Pressing this key cycles through all of the failures present. When on the last
page, the "MORE" key causes a return to the first displayed failure page
(Figure 105 or 106).
All "Display-Failures Mode" Screens have the "RETURN" selection on the left key.
• "RETURN"
Pressing this key causes the system to return to the "Normal Mode" Screen
(Figure 101).
While in the Display-Failures Mode, not pressing either key for five minutes causes the system to return to
the "Normal Mode" Screen (Figure 101).
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NOTE: Designation of pin names can be shown with numeric/alpha position in either format ANN or
NNA, e.g. MP-11A is equivalent to MP-A11.
"Tuning Port A Failure" Screen
Figure 108
"Tuning Port B Failure" Screen
Figure 109
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Figure 110 deleted by Revision No. 4
"SDI 0 Program Pin Failure" Screen
Figure 111
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"SDI 1 Program pin Failure" Screen
Figure 112
"CMC Port #1 Failure" Screen
Figure 113
"CMC Port#2 Failure" Screen
Figure 114
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"CMU/ATSU Failure Page" Screen (-2000 and -2051)
Figure 114.1
"LGCIU Failure Page" Screen (-2000 and -2051)
Figure 114.2
4.
Maintenance Mode
The Maintenance Mode is entered from either one of the two "Test Complete" Screens (Figures 103 or 104).
The Maintenance Mode allows troubleshooting of all components of the VDR system, both internal and
external.
All pages have the "MORE" selection on the right key.
• "MORE"
Pressing this key cycles through all of the maintenance pages. When on the
last page, the "MORE" key causes a return to the first displayed
maintenance screen.
All pages have the "RETURN" selection on the left key.
• "RETURN"
Pressing this key causes the system to return to the "Normal Mode" Screen
(Figure 101).
There is no timeout in the Maintenance Mode when the aircraft is on the ground. But while in the air, not
pressing a key for five minutes causes the system to return to the "Normal Mode" Screen (Figure 101).
Figures 115 through 122 show typical Maintenance Mode Pages that may be encountered.
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NOTE:
The "Status" field displays "FAILED" if either an external or an internal failure is detected.
"VDR Unit Status (OK, Failed)" Screen
Figure 115
"Tuning Port Status (NORM, FAIL, TEST, NCD, NODAT)" Screen
Figure 116
"Tuning Port Status Page" Screen (-2000 and -2051)
Figure 116.1
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VARIABLE FIELD
VALID DATA
SSTATE
BERTM (S0)
716VN (S1
716DM (S2)
FRE.QUE
Operating Frequency (e.g. 131.550)
A, B
STATS
NORM, TEST, NCD, NODAT
CMUS
NULL, CMU1, CMU2
CHSTAT
N/A, TX. RXBUSY, RXIDLE
NOTE:
716VP (S3)716DB (S6)750DSA (S7-A)
716DP (S4)750DN (S7-N)750DR2 (S7-R2)
716VB (S5)750DRA (S7-RA)750DS2 (S7-2)
See ARINC 750 specification for data definitions.
Valid Data Field Examples of "Tuning Port Status Page " Screen (-2000 and -2051)
Figure 116.2
"Discrete Input Status Page 1 (OPEN, GRND)" Screen
Figure 117
"Discrete Input Status Page 2 (OPEN, GRND)" Screen
Figure 118
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"Discrete Input Status Page 3 (OPEN, GRND)" Screen
Figure 119
"Discrete Input Status Page 4 (OPEN, GRND)" Screen (-2000 and -2051)
Figure 119.1
"SDI Program Pin Status Page (OPEN, COMM)" Screen
Figure 120
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"CMC Port Status (ACTIVE, INACTIVE)" Screen
Figure 121
Figure 122 is eliminated by Revision 5 of this Maintenance Manual.
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5.
Flight Fault Memory Mode
When the Flight-Fault Memory contains failures from previous flight legs, an "Old Failures" Screen (Figure
123) is presented as the last page of the Maintenance Mode Screens. This page allows the viewing of
previous flight leg failures, one flight leg at a time by pressing the "YES" key. Pressing the "MORE" key from
this page bypasses this function and returns the system back to the first page of the maintenance data.
Once in the Flight-Fault Memory Mode, flight legs are displayed from the most recent, backwards. The VDR
stores up to 10 "in air" failures and up to 3 "on ground" failures per flight leg, there will be up to four pages
displayed on the LCD. There are over 120 different fault codes that can be stored for each of the 13 failures.
These are described in the Component Maintenance Manuals (CMM) I.B. 1144A-2 (23-20-36) and
I.B.1144A-3 (23-20-38), in the "Testing and Troubleshooting" Section.
The first page of each flight leg contains the date, flight number, aircraft number, and departure/destination
stations, as shown in the "Previous Flight Legs Failures First Page" Screen (Figure 124). The second page
displays failures 1-5, the third page displays failures 6-10 and the fourth page displays failures 11-13, as
shown in the "Previous Flight Legs Data Page" Screens (Figure 125).
All flight fault memory pages have the "MORE" selection on the right key.
• "MORE"
Pressing the key cycles through all of the Flight-Fault Memory pages. When
on the last page, the "MORE" key causes a return to the first page.
All flight fault memory pages have the "RETURN" selection on the left key.
• "RETURN"
Pressing this key causes the system to return to Normal Mode Screen
(Figure 101).
There is no timeout in this mode when the aircraft is on the ground. But, while in the air, not pressing a key
for five minutes causes the system to return to the "Normal Mode" Screen (Figure 101)
"Old Failures Page" Screen
"Previous Flight Legs Failures First Page" Screen
Figure 123
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"Previous Flight Legs Failures First Page" Screen
Figure 124
NOTE:
"FC" is fault code, "UTC" is time, "R" is repetition count, "P" is phase, "O" is origin.
"Previous Flight Legs Failures Data Page" Screen
(Three Screens per Flight Leg)
Figure 125
All "Display-Failures Mode" Screens have the "RETURN" selection on the left key.
• "RETURN"
Pressing this key causes the system to return to the "Normal Mode" Screen
(Figure 101).
While in the Display-Failures Mode, not pressing either key for five minutes causes the system to return to
the "Normal Mode" Screen (Figure 101).
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RTA-44D VHF DATA RADIO SYSTEM
MAINTENANCE PRACTICES
1.
General
This section of the manual provides service personnel with installation and maintenance information for the
RTA-44D VHF Data Radio (VDR) System. Installation instructions are supported by mechanical outline
drawings and a electrical interconnection diagram. These drawings, located at the back of this section,
should be reviewed by the installer, and requirements peculiar to the airframe should be established before
starting the installation.
2.
Inspection After Unpacking
CAUTION: THIS EQUIPMENT CONTAINS ELECTROSTATIC DISCHARGE SENSITIVE (ESDS)
DEVICES. EQUIPMENT, MODULES, AND ESDS DEVICES MUST BE HANDLED WITH
APPROPRIATE PRECAUTIONS.
Visually inspect the RTA-44D VHF Data Radio System and all associated equipments for possible damage
which may have occurred during shipment. Inspect for dents, deep abrasions, chipped paint, etc. If any
equipment is damaged, notify the transportation carrier immediately.
A Honeywell Airlines and Avionics Products test and inspection record and quality report tag is included with
each shipped unit. This ensures the customer that the necessary production tests and inspection
operations have been performed on that particular unit.
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 Airlines and Avionics Products with the necessary information required to evaluate
shipping methods as well as test and inspection effectiveness.
Completed cards are accumulated to provide information for a periodic analysis.
3.
Preinstallation Testing
The components in the RTA-44D VHF Data Radio System have been adjusted and tested prior to shipment.
Therefore, preinstallation testing is not required. However, if preinstallation testing of the units is desired,
refer to the customer acceptance criteria given in the Component Maintenance Manual for the appropriate
unit in the system. Refer to Figure 4 in the "Description and Operation" Section of this manual for a list of
related Component Maintenance Manuals.
4.
Equipment Changes and Marking
Honeywell Airlines and Avionics Products uses a standardized marking system to identify equipment and
their subassemblies which have had changes incorporated. Refer to the front of the appropriate Component
Maintenance Manual for a list of Service Bulletins affecting the unit.
5.
Interchangeability
The RTA-44D VHF Data Radio System will operate in any installation that complies with ARINC
Characteristic 750; it will also operate as a RTA-44A VHF Transceiver System replacement in any
installation that complies with ARINC 716. Refer to System Interwiring Diagram, Figure 208, for particulars.
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6.
Installation
A. General
The RTA-44D VHF Data Radio System should be installed in the aircraft in a manner consistent with
acceptable workmanship and engineering practices, and in accordance with the instructions set forth in
this publication. To ensure that the system has been properly and safely installed in the aircraft, the
installer should make a thorough visual inspection and conduct an overall operational and functional
check of the system on the ground prior to flight.
CAUTION: AFTER INSTALLATION OF THE CABLING AND BEFORE INSTALLATION OF THE
EQUIPMENT, A CHECK SHOULD BE MADE WITH AIRCRAFT PRIMARY POWER
BEING SUPPLIED TO THE MOUNT CONNECTORS TO ENSURE THAT POWER IS
APPLIED ONLY TO THE PINS SPECIFIED IN INTERWIRING DIAGRAM FIGURE 208.
B. Location of Equipment
Location of the RTA-44D VHF Data Radio System in the aircraft is not critical, as long as the
environment is compatible with the equipment design. Refer to the Leading Particulars, Figure 7, in the
"Description and Operation" section of this manual. Forced air cooling is required for cooling the
RTA-44D VHF Data Radio in accordance with ARINC Characteristic 600. The associated cooling
equipment must be mounted in accordance with the manufacturer's instructions.
Antenna mounting should be in accordance with the manufacturer's instructions for the antenna being
used. The coaxial cable connecting the antenna to the mount should be as short and direct as possible
and any required bends should be gradual. When two or more RTA-44D VHF Data Radios are installed
in an aircraft, it is necessary to provide adequate space isolation between antennas of each system to
ensure that the use of one transceiver does not interfere with reception from another system. A
minimum of 35 dB of space isolation should be provided, and any steps which can be taken to provide
further isolation should be considered. Maximum cable loss should be < 3dB.
Control unit location and mounting can be determined by mutual agreement between the user and
airframe manufacturer.
C. Interwiring and Cable Fabrication
(1)
General
Figure 208 is the complete aircraft interwiring diagram for a single RTA-44D VHF Data Radio
System and associated components. This diagram requires thorough study before the installer
begins installation of the aircraft wiring.
When two or more systems are being installed in the aircraft, the interconnecting wiring shown in
Figure 208, as well as all other installation instructions must be duplicated.
Cabling must be fabricated by the installer in accordance with Figure 208. Wires connected to
parallel pins should be approximately the same length, so that the best distribution of current can
be effected. Honeywell Airlines and Avionics Products recommends that all wires, including
spares, shown on interwiring diagram Figure 208 be included in the fabricated harness. However,
if full ARINC wiring is not desired, the installer should ensure that the minimum wiring
requirements for the features and functions to be used are incorporated.
NOTE: To allow for inspection or repair of the connector, or the wiring to the connector, sufficient
lead length should be left so that the rear connector assembly can be pulled forward
several inches when the mounting hardware for the rear connector assembly is removed.
A bend should be made in the harness near the connector to allow water droplets, that
might form on the harness from condensation, to drip off at the bend and not collect at
the connector.
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When the cables are installed in the aircraft, they must be supported firmly enough to prevent
movement and should be carefully protected against chafing. Additional protection should also
be provided in all locations where the cables may be subject to abuse. In wire bundles, the cabling
should 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 should cross high-level
lines at a right angle, or high-quality shielded conductors should be used.
If a cable must pass through a bulkhead between pressurized and unpressurized zones, this
passage must conform to the aircraft manufacturer's specifications.
The assembler must be knowledgeable of any system variations peculiar to the installation, and
must thoroughly understand the complexities associated with handling related problems of line
lengths, capacitance, and of susceptibility to interference.
Electrical bonding interface characteristics per ARINC 600 Section 3.2.4 states that ground path
resistance should not exceed 0.5 milliohms.
The following determinants are the responsibility of the installation agency for fabrication of the
wiring harness, see Figures 201 and 208.
PIN NO.
TYPE
SIGNAL NAME
FUNCTION
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 COMM only.
MPA1
Input
Mic Audio Input (HI)
MPB1
Input
Mic Audio Input (LO)
MPC1
Input
Mic PTT
Microphone push-to-talk discrete input.
Gnd/Low = Transmitter keyed;
Open/High = Transmitter not keyed.
Part of the standard four wire microphone
interwiring as described in Attachment 6 of
ARINC 716-10. Required for ARINC 716
VHF COMM only.
MPD1
Output
Key Event
Discrete input to Flight Recorder. Follows
the state of Mic PTT input.
Gnd/Low = Transmitter keyed;
Open/High = Transmitter not keyed.
Required for ARINC 716 VHF COMM only.
MPA2
Input
Max. Trans Time
Cutoff Function
Discrete input that enables the maximum
transmit cutoff function.
Gnd/Low = Cutoff disabled;
Open/High = Cutoff enabled.
RTA-44D VHF Data Radio Connector Determinants
Figure 201
Sheet 1 of 6
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PIN NO.
TYPE
SIGNAL NAME
FUNCTION
Mic Input Ground
Required for ARINC 716 VHF COMM only.
A high speed ARINC 429 input port to allow
onboard data loading for software.
MPB2
MPC2
Input
Data Loader Input Bus A
MPD2
Input
Data Loader Input Bus B
MPA3
Input
Optional Remote Squelch
(HI)
MPB3
Input
Optional Remote Squelch
(ARM)
MPC3
Input
Optional Remote Squelch
(LO)
MPD3
MPA4
To accommodate an optional remote
squelch adjustment if so required or provided. Required for ARINC 716 VHF
COMM only.
DC Ground
Required for both ARINC 716 VHF COMM
and ARINC 750 VDR; functions are identical.
Input
Functional Test
Discrete input that activates LRU functional
test function. Gnd/Low = activate functional
test. Required for ARINC 716 VHF COMM
MPB4
Audio Ground
Required for ARINC 716 VHF COMM only.
MPC4
Output
Data Loader Output Bus A
A high speed ARINC 429 output port to
allow onboard data loading for software.
MPD4
Output
Data Loader Output Bus B
MPA5
Input
Data Link Data Input (HI)
MPB5
Input
Data Link Data Input (LO)
MPC5
Reserved #1
Analog 2400 bps ACARS data input.
Required for ARINC 716 VHF COMM only.
Leave open.
RTA-44D VHF Data Radio Connector Determinants
Figure 201
Sheet 2 of 6
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PIN NO.
TYPE
SIGNAL NAME
FUNCTION
MPD5
Output
8.33-kHz Programming
Discrete output that indicates to control
panel the VDR is capable of 8.33-kHz or
25- kHz operation. This output is internally
grounded.
MPA6
Input
Data from OMS/CFDS #1
Input Port (A)
MPB6
Input
Data from OMS/CFDS #1
Input Port (B)
One of two low speed ARINC 429 data
input ports provided for dual OMS/CFDS's.
Required for both ARINC 716 VHF COMM
and ARINC 750 VDR; functions are identical.
MPC6
Input
Data from OMS/CFDS #2
Input Port (A)
MPD6
Input
Data from OMS/CFDS #2
Input Port (B)
MPA7
Input
Freq/Funct Select Data I/P
Port B (A)
MPB7
Input
Freq/Funct Select Data I/P
Port B (B)
MPC7
Input
Voice/Data Select
Discrete input that enables either the PTT
key line (MPC1) or the Data key line
(MPD7).
Gnd/Low = Data Key line enabled;
Open/High = PTT enabled. Required for
ARINC 716 VHF COMM only.
MPD7
Input
Data Key Line
Discrete input that keys the transmitter.
Gnd/Low = Transmitter keyed;
Open/High = Transmitter not keyed.
Required for ARINC 716 VHF COMM only.
MPA8
MPB8
Input
One of two low speed ARINC 429 data
input ports provided for dual OMS/CFDS's.
Required for ARINC 750 VDR only.
One of two low speed ARINC 429 input
ports to provide frequency tuning data.
Required for ARINC 716 VHF COMM only.
Spare
Data Loader Enable Input
Discrete input to allow onboard data loading
of software. Required for ARINC 750 VDR
only.
RTA-44D VHF Data Radio Connector Determinants
Figure 201
Sheet 3 of 6
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PIN NO.
TYPE
SIGNAL NAME
FUNCTION
Freq Offset Enable
Discrete input that enables the offsetting of
the transmit frequency by a board-strap
programmable value.
Gnd/Low = Frequency offset enabled;
Open/High = Frequency offset disabled.
Required for ARINC 716 VHF COMM only.
Data Key Line Return
Required for ARINC 716 VHF COMM only.
A discrete input pair prewired at the rear
connector to identify the specific VHF radio
location in the aircraft. Required for both
ARINC 716 VHF COMM and ARINC 750
VDR; functions are identical.
MPC8
Input
MPD8
MPA9
Input
SDI Bit 0 Prog
MPB9
Input
SDI Bit 1 Prog
MPC9
MPD9
Output
MPA10
Spare
MPB10
Spare
MPC10
Output
Data to CMU #1, CMU #2
Output Port (A)
MPD10
Output
Data to CMU #1, CMU #2
Output Port (B)
MPA11
Input
Freq/Funct Select Data I/P
Port A (A)
MPB11
Input
Freq/Funct Select Data I/P
Port A (B)
MPC11
Input
Maintenance System ID 1
Identifies CFDS type along with MPA14
(See Figure 208).
MPD11
Input
Freq Port Select
Discrete input used to select either Frequency/Function Select Data I/P Port A or
B. Gnd/Low = Select Port A,
Open/High = Select Port B. Required for
both ARINC 716 VHF COMM and
ARINC 750 VDR; functions are identical.
SDI Prog Pin Common
Ground for the SDI code inputs. Required
for ARINC 716 VHF COMM only.
AGC OUT
AGC output signal for test purposes.
A high speed ARINC 429 output port to
CMU/MU/ATSU’s #1 and #2. Required for
ARINC 750 VDR only.
One of two low speed ARINC 429 input
ports to provide frequency tuning data.
Required for ARINC 716 VHF COMM only.
RTA-44D VHF Data Radio Connector Determinants
Figure 201
Sheet 4 of 6
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PIN NO.
TYPE
SIGNAL NAME
FUNCTION
A high speed ARINC 429 input port from
CMU/MU/ATSU #1. Used to receive commands/status/data in Williamsburg files,
and periodic and aperiodic ARINC 429
words. Required for ARINC 750 VDR only.
MPA12
Input
CMU #1 Input Bus A
MPB12
Input
CMU #1 Input Bus B
MPC12
Input
CMU #2 Input Bus A
MPD12
Input
CMU #2 Input Bus B
MPA13
Output
SELCAL Audio and Data
Link Output (HI)
MPB13
Output
SELCAL Audio and Data
Link Output (LO)
MPC13
Input
MPD13
MPA14
Input
Maintenance System ID 0
Identifies CFDS type along with MPC11
(See Figure 208).
MPB14
Input
Air/Ground Discrete
A discrete input to indicate if the aircraft is
in the air or on the ground.
Gnd/Low = Airborne, Open/High = On
Ground. Required for both ARINC 716 VHF
COMM and ARINC 750 VDR; functions are
identical.
MPC14
Output
Data to OMS/CFDS Output
Port A
MPD14
Output
Data to OMS/CFDS Output
Port B
A low speed ARINC 429 output port to one
or two OMS/CFDS's. Required for both
ARINC 716 VHF COMM and ARINC 750
VDR; Functions are identical.
MPA15
Output
Audio/Sidetone Output (HI)
MPB15
Output
Audio/Sidetone Output
(LO)
Squelch Disable
Squelch Disable Return
A high speed ARINC 429 input port from
CMU/MU/ATSU #2. Used to receive commands/status/data in Williamsburg files,
and periodic and aperiodic ARINC 429
words. Required for ARINC 750 VDR only.
An analog output to provide 2400 bps MSK
data to the ACARS MU. May also be used
for SELCAL provisions. Required for
ARINC 716 VHF COMM only.
A discrete input to provide squelch override
or disable capability. Required for
ARINC 716 VHF COMM only.
An analog output for receiver audio during
receive mode and sidetone audio during
voice transmit modes. Required for
ARINC 716 VHF COMM only.
RTA-44D VHF Data Radio Connector Determinants
Figure 201
Sheet 5 of 6
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RTA-44D VHF DATA RADIO SYSTEM
PIN NO.
TYPE
SIGNAL NAME
FUNCTION
MPC15
Input
Muting
MPD15
An optional two wire discrete output to provide a switch closure internal to the VHF
COMM for external system muting applications during transmit modes.
Open = Muting Off, Gnd = Muting On.
Required for ARINC 716 VHF COMM only.
Muting Return
BP1
Input/
Output
Antenna RF Input
Required for both ARINC 716 VHF COMM
and ARINC 750 VDR; functions are identical.
BP2
Input
DC Power Input +27.5VDC
Required for both ARINC 716 VHF COMM
and ARINC 750 VDR; functions are identical.
BP3
Spare
BP4
DC Power GND
BP5
Spare
Required for both ARINC 716 VHF COMM
and ARINC 750 VDR; functions are identical.
RTA-44D VHF Data Radio Connector Determinants
Figure 201
Sheet 6 of 6
(2)
Reserved and Spare Wires
If the installer does not wish to connect all wires, he may select wires reserved for optional
functions which his system does not contain and delete these wires. He should also decide which
future spare wires to include in the installation. Reserved and spare wires are identified in Figure
201 and in interwiring diagram Figure 208.
D. Installation of System
The RTA-44D VHF Data Radio 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.
To wire the mounts into the system, first remove the mount connector cover and connector plate
assembly. Then crimp or solder (as applicable) the interconnecting wiring to the appropriate connector
pins. Finally, return the connector plate assembly and cover to their original positions.
The RTA-44D VHF Data Radio (VDR) is installed in the mount as follows.
(1)
Slide the VDR into the mount until the guide pins are aligned and the electrical connectors are
firmly engaged.
(2)
Secure the front of the VDR to the mount by tightening the two knurled screw clamps (located on
the front of the mount) until they are firmly seated over hold-down hooks located on the front of
the unit.
(3)
Safety-wire the two screw clamps.
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7.
Inspection and System Check Procedures
NOTE:
Inspection and check procedures for the RTA-44D VHF Data Radio System includes
checkout of all interfacing units that may affect performance of the VDR.
A. Inspection
Figure 202 is a visual inspection check procedure and should be performed after system installation,
prior to system checkout. In addition, the procedure should be used as a periodic inspection check.
EQUIPMENT
INSPECTION/CHECK PROCEDURE
3 MCU Unit Mount As defined by manufacturer's instructions.
RTA-44D VHF
Data Radio
(1) Check that unit is fully inserted in mount and that the knurled screw
clamps which secure the unit in the mount are tight and safety wired.
(2) Inspect the case for deformation, dents, corrosion, and damage to finish;
ensure 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.
Inspection/Check Procedures
Figure 202
B. System Checkout
(1)
General
After installation of the RTA-44D VHF Data Radio System, and inspection of the equipment per
previous Figure 202, perform a continuity and visual check of the system interwiring per paragraph
7.B.(2). A post-installation test per paragraph 7.B.(3) should then be performed.
(2)
System Interwiring Check
Visually check the system interwiring for abnormalities, such as cables rubbing unprotected metal
edges or tightly stretched cables. Check continuity of all interwiring. In particular, check the
following:
(3)
(a)
Check that the VDR is properly installed and the hold-down screw clamps are tight.
(b)
Check wiring harness connectors for security and connection to the VDR.
(c)
Check that antenna transmission line connectors are securely fastened.
(d)
Check that cables do not interfere with aircraft controls or other equipment.
Software On Board Loadable Instructions
The VDR Mode 2 is capable of on board software loadability. The following describes this
process:
(a)
I.B. 1144-1
Loosen Phillips head screw on cover, left of handle, to expose the front panel PCMCIA slot.
When the main program card is inserted into this slot, the front panel LCD will display either
the "Program Prompt" Screen (Figure 202.1) or the "Invalid Card" Screen (Figure 202.2).
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↓
↓
"Program Prompt" Screen
Figure 202.1
"Invalid Card" Screen
Figure 202.2
I.B. 1144-1
(b)
When the "Start" key of the "Program Prompt" Screen (Figure 202.1) is pressed, program
loading starts and the front panel LCD displays the "Programming in Progress" Screen,
(Figure 202.3).
(c)
The "S....S" field in the third row of the display is a string that shows the module presently
loading. After loading of the individual modules ends, the "S...S" field momentarily shows
the software part number.
(d)
The moving thermometer-type display near the bottom half of the display indicates the
percent completion of the program load.
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"Programming in Progress" Screen
Figure 202.3
(e)
When the program loading is complete, the front panel LCD displays either the "Load
Complete" Screen (Figure 202.4) if the program loading was successful, or the "Load
Failed" Screen (Figure 202.5) if the program loading failed.
"Load Complete" Screen
Figure 202.4
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"Load Failed" Screen
Figure 202.5
(f)
If the program was successfully loaded, the front panel LCD displays the "Verifying
Program" Screen (Figure 202.6) when the program card is removed. The verification
consists of checking the cyclic redundancy check (CRC) of the loaded program.
"Verifying Program" Screen
Figure 202.6
(g)
I.B. 1144-1
When the program verification is completed, the front panel LCD displays either the "Normal
Mode" Screen (Figure 203.1) if the verification succeeded, or the "Invalid Load" Screen
(Figure 202.7) if the verification failed.
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"Invalid Load" Screen
Figure 202.7
(4)
Post-Installation Check
(a)
Test Equipment Required
None required.
(b)
System Test
A functional self test of the RTA-44D VHF Data Radio System may be initiated by pressing
the "test" key pushbutton switch as designated on the front panel LCD (Figures 203 and
203.1). Although the "Normal Mode" Screen indicates that this is actuated from the right
key, the left key has the same function if pressed while the VDR LCD is in its normal mode.
↓
↓
"Normal Mode" Screen (-0101, -0110, -0202, -0303 and -0505)
Figure 203
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↓
↓
"Normal Mode" Screen (-2000 and -2051)
Figure 203.1
The Self-Test Mode starts by displaying the "Test in Progress" Screen (Figure 204) one
second after pressing the "test" key. This is displayed for four seconds with a moving
thermometer along the bottom of the LCD indicating the progress of the test from one to five
seconds
"Test in Progress" Screen
Figure 204
The "Normal Mode" Screen (Figures 203 and 203.1) is displayed for the first second of the
test sequence. Once complete, the "Test Complete, No Failures" Screen is displayed
(Figure 205), or the "Test Complete, Failures" Screen is displayed (Figure 206). Both
screens contain two key selections each: "MAINT" and "RETURN" or "MAINT" and "WHY?",
respectively.
• "MAINT" - For both screens, "MAINT" is located on the left key. This allows the
initiation of the extended maintenance pages of the system for
troubleshooting. Refer to Paragraph 4 of "Fault Isolation" Section 100 of
this manual.
•"RETURN"
I.B. 1144-1
In the "Test Complete, No Failures" Screen, the "RETURN" key to the
right returns the system to its "Normal Mode" Screen (Figures 203 and
203.1).
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- In the "Test Complete, Failures" Screen, the "WHY?" key to the right puts
the system into the Display-Failures Mode where individual system
failures are displayed one per page. Refer to Paragraph 3 of "Fault
Isolation" Section 100 of this manual.
•"WHY?"
While in the Self-Test Mode, not pressing either key for five minutes causes the system to
return to the "Normal Mode" Screen (Figures 203 and 203.1)
"Test Complete, No Failures" Screen
Figure 205
↓
"Test Complete, Failures" Screen
Figure 206
C. Flight Tests
(1)
Preflight Test
(a)
General
The following test procedure gives instructions for a preflight test which ensures that the
RTA-44D VHF Data Radio System is functioning in an acceptable manner prior to takeoff.
(b)
Test Procedures
1 Establish the initial control settings listed below.
POSITION
CONTROL PANEL
Power
Frequency Selector
Volume Control
I.B. 1144-1
On
Tune to any local VHF frequency (local
control tower or ground control frequency)
Midrange
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2 Using the system's headphone (or speaker) and microphone, check operation of the
RTA-44D VHF Data Radio System.
3 Key the microphone and speak into it; speech should be audible. Request a radio check,
and release the push-to-talk button.
4 Listen through the headphones (or speaker) and press the SQ/TEST pushbutton. A
squelch break should be audible.
5 As soon as possible, a local flight check should be made to verify system operation for
both local and distant stations.
(2)
In-Flight Confidence Test
Upon completion of the post-installation and preflight checks, a local flight may be made to verify
system operation for both local and distant stations. Repeat the test procedure found in
paragraph 7.C.(1)(b).
8.
Removal and Replacement
9.
A. Removal
(1) Loosen the two knurled screw clamps (located on the front of mount) that secure the VDR to the
mount.
(2) Gently pull the VDR forward until it is disconnected from the rear connector and guide pins.
B. Replacement
(1) Slide the VDR onto the tray of the mount and then gently push the 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 VDR.
(3) Safety wire the two knurled screw clamps.
Maintenance Procedures
A. Adjustments and Alignments
There are no adjustments or alignments required for the RTA-44D VHF Data Radio System. All
alignment and adjustment procedures are accomplished during bench maintenance. The technician
should remove the unit from the aircraft and reference should be made to the related maintenance
manual when unit performance indicates an adjustment or an alignment is required.
B. System Protection
The system should be protected by a 10-ampere circuit breaker located at the circuit breaker panel in
the aircraft.
C. Lubrication Practices
There are no requirements for lubrication of any RTA-44D VHF Data Radio System components.
D. Cleaning
When deemed necessary, depending upon the environment to which the equipment is exposed and the
intensity of use, periodic cleaning should be performed. Any dust on the RTA-44D VHF Data Radio
System LRU's should be wiped off with a lint-free cloth.
NOTE: Any cleaning of equipment interiors should be limited to that required when performing overhaul
(bench-type) work.
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RTA-44D VHF Data Radio Dimensional Outline Drawing
Figure 207
I.B. 1144-1
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RTA-44D VHF Data Radio System Interwiring Diagram
Figure 208
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