ACR Electronics ELT to Nav Interface Boeing Manual

ACR Electronics ELT to Nav Interface Boeing Manual
ELT/NAV INTERFACE – B
Description, Operation, Installation and Maintenance Manual
This manual includes data for the equipment that follows:
Component
ELT/NAV Interface
Part No.
453-6501
Model No.
-B
25-69-11
Page 1 of 49
NOV 22/13
570-6501 Rev. C
Initial Issue OCT 05/2000
ARTEX PRODUCTS / ACR ELECTRONICS, INC.
5757 Ravenswood Rd, Ft. Lauderdale, FL 33312
Cage Code: 18560
ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
PROPRIETARY INFORMATION
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 ACR Electronics.
Information in this manual is subject to change without notice. ACR Electronics makes no warranty, expressed
or implied, with regard to this manual, including but not limited to any implied warranties of merchantability,
fitness for a particular purpose, and non-infringement. In addition, ACR Electronics makes no warranty with
regard to the documentation or data contained herein. ACR Electronics is not liable in the event of incidentals,
special, consequential, or any other damages in connection with or arising from furnishing, performance, or use
of this manual.
Reproduction of this publication or any portion thereof by any means is prohibited. For further information
contact Sales, ACR Electronics, 5757 Ravenswood Rd, Fort Lauderdale, FL 33312. Telephone (954) 981-3333.
AIRWORTHINESS LIMITATIONS
The Airworthiness limitations section is FAA approved and specifies inspections and other maintenance required
under 14 CFR§ 43.16 and 91.403, unless an alternative program has been approved.
IMPORTANT NOTICE
ACR Electronics will be responsible for full distribution and revisions of ICA’s (Instructions for Continued
Airworthiness). For inquiries regarding the content and currency of this manual, contact ACR Electronics, 5757
Ravenswood Rd, Fort Lauderdale, FL 33312. Telephone (954) 981-3333.
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RECORD OF REVISIONS
REVISION
CHANGE
DATE
REVISION
CHANGE
25-69-11
DATE
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-B (453-6501)
SERVICE BULLETIN LIST
SERVICE
BULLETIN NO
ISSUE
DATE
SUBJECT
MANUAL
REV NO
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MANUAL
REV DATE
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
LIST OF EFFECTIVE PAGES
SUBJECT
PAGE
DATE
SUBJECT
PAGE
DATE
Title Page
1
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Test and Fault Isolation (cont)
26
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Notices
2
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27
Nov 22/13
Record of Revisions
3
Nov 22/13
28
Nov 22/13
Service Bulletin List
4
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29
Nov 22/13
List of Effective Pages
5
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30
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Table of Contents
6
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31
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7
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32
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List of Figures
8
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33
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Introduction
9
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34
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10
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Description and Operation
Test and Fault Isolation
Removal
Installation
Illustrated Parts List
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
TABLE OF CONTENTS
RECORD OF REVISIONS .................................................................................................................................3
SERVICE BULLETIN LIST ................................................................................................................................4
LIST OF EFFECTIVE PAGES .............................................................................................................................5
TABLE OF CONTENTS .....................................................................................................................................6
LIST OF FIGURES ...........................................................................................................................................8
INTRODUCTION .............................................................................................................................................9
1. Manual Usage .................................................................................................................................... 9
A. General .......................................................................................................................................9
B. Application ..................................................................................................................................9
2. Model Description ..............................................................................................................................10
A. ELT/NAV Interface -B ................................................................................................................10
B. Compatibility .............................................................................................................................10
3. Approvals ..........................................................................................................................................10
A. Certification ..............................................................................................................................10
B. RTCA DO-160C and DO-160D Compliance .................................................................................11
4. List of Acronyms, Abbreviations, and Definitions ................................................................................13
5. References ........................................................................................................................................15
A. Regulatory Documents ..............................................................................................................15
B. Other Documents ......................................................................................................................16
DESCRIPTION AND OPERATION ...................................................................................................................17
1. Description ........................................................................................................................................17
A. Overview ..................................................................................................................................17
B. Physical Description ..................................................................................................................18
C. Position Data Functionality ........................................................................................................18
D. 24-Bit Address Reprogramming Functionality ............................................................................19
2. Navigation System Interface Requirements .......................................................................................19
A. ARINC 429 Latitude and Longitude Data Input ..........................................................................19
B. RS-232 Latitude and Longitude Data Input................................................................................20
3. Operation ..........................................................................................................................................21
A. Position Data Processing ...........................................................................................................21
B. 24-Bit Address Reprogramming .................................................................................................21
4. Specifications ....................................................................................................................................22
A. Physical and Environmental.......................................................................................................22
B. Input/Output.............................................................................................................................23
C. Electrical ...................................................................................................................................24
TEST AND FAULT ISOLATION .......................................................................................................................25
1. General .............................................................................................................................................25
A. Applicability...............................................................................................................................25
B. Regulatory Requirements ..........................................................................................................25
2. Periodic Inspection ............................................................................................................................26
A. Inspection Procedures...............................................................................................................26
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3.
4.
5.
6.
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Periodic Testing.................................................................................................................................27
A. Position Data ELT Self-Test .......................................................................................................27
Post-Installation Functional Testing ...................................................................................................28
A. General .....................................................................................................................................28
B. Position Data Verification Test...................................................................................................28
C. 24-Bit Address Reprogramming Verification Test .......................................................................30
Post-Reprogramming Check ..............................................................................................................31
A. 15-Digit Hex ID Verification .......................................................................................................31
Fault Isolation ...................................................................................................................................32
A. Troubleshooting Guidelines .......................................................................................................32
REMOVAL .....................................................................................................................................................33
1. ELT/NAV Interface -B ........................................................................................................................33
A. Removal....................................................................................................................................33
2. Material or Equipment Return ............................................................................................................34
A. Shipment Information ...............................................................................................................34
B. Return Material Authorization ....................................................................................................34
INSTALLATION .............................................................................................................................................35
1. Regulatory Requirements and Guidelines...........................................................................................35
A. Applicability...............................................................................................................................35
B. TSO C126, Paragraph D ............................................................................................................35
C. FAA...........................................................................................................................................35
D. Canada .....................................................................................................................................35
E. Other Countries.........................................................................................................................35
F.
RTCA ........................................................................................................................................36
2. Mechanical ........................................................................................................................................37
A. Chassis Location........................................................................................................................37
B. Chassis Installation ...................................................................................................................37
3. Wiring ...............................................................................................................................................39
A. General Considerations and Recommendations .........................................................................39
B. ELT and Navigation System Interfaces ......................................................................................40
C. 24-Bit Address Reprogramming – Hard Wire Method .................................................................43
D. 24-Bit Address Reprogramming – Switch Block Method .............................................................44
ILLUSTRATED PARTS LIST............................................................................................................................45
1. Introduction ......................................................................................................................................45
A. Purpose ....................................................................................................................................45
B. IPL Usage Guide .......................................................................................................................45
2. Manufacturer Name and Address.......................................................................................................45
A. Ordering Information ................................................................................................................45
3. Explanation of Detailed Parts List Entries ...........................................................................................46
A. Fig # & Item Column ................................................................................................................46
B. Part # Column ..........................................................................................................................46
C. Nomenclature Column ...............................................................................................................46
D. UPA (Units Per Assembly) Column .............................................................................................47
4. Detailed Parts List .............................................................................................................................48
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
LIST OF FIGURES
Figure 1 ELT/NAV Interface -B System Integration.................................................................................17
Figure 2 ELT/NAV Interface -B Isometric View .......................................................................................18
Figure 3 Examples of Location Protocol 406 MHz Messages ...................................................................29
Figure 4 406 MHz Location Message without Position Data ....................................................................29
Figure 5 ELT/NAV Interface -B Removal.................................................................................................33
Figure 6 ELT/NAV Interface -B Outline and Dimensions .........................................................................37
Figure 7 ELT/NAV Interface -B Mechanical Installation ...........................................................................38
Figure 8 ELT/NAV Interface -B Wiring Diagram ......................................................................................40
Figure 9 Wiring Installation at ELT End ..................................................................................................41
Figure 10 ELT/NAV Interface -B Wiring Installation ................................................................................42
Figure 11 Octal/Hexadecimal to Binary Conversion ................................................................................43
Figure 12 ELT/NAV Interface -B Installation ...........................................................................................48
Figure 13 Electrical Components ............................................................................................................49
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
INTRODUCTION
TASK 25-69-11-990-801
1. Manual Usage
SUBTASK 25-69-11-990-001
A. General
1) This manual describes the operation, installation, and maintenance of the ELT/NAV Interface -B. This
information is provided to ensure initial and continued airworthiness. Information presented in this
manual is accurate at time of printing, but is subject to change. Refer to the Artex products web site at
www.acrelectronics.com for the latest information and any updates to this manual.
2) Web links provided in this manual were accurate at time of printing but may be subject to change.
3) Regulatory references contained herein are generally confined to United States and Canadian
requirements and, in any case, should not be considered all encompassing. Consult your national
aviation authority for applicable requirements.
SUBTASK 25-69-11-990-002
B. Application
1) This manual constitutes supporting data/documentation for the ELT/NAV Interface -B, including:
2)
3)
4)
5)
a) Description and Operation
b) Test and Fault Isolation (includes inspection criteria)
c) Removal
d) Installation
e) Illustrated Parts List
In the United States, the ELT/NAV Interface -B must be installed and maintained in accordance with the
requirements herein and 14 CFR, FAR Parts 43, and 91; and other airworthiness requirements, as
applicable.
In Canada, the ELT/NAV Interface -B must be installed and maintained in accordance with the
requirements herein and Canadian Aviation Regulations (CAR), Part V and other CAR airworthiness
requirements, as applicable.
ELT/NAV Interface -B installation and maintenance in all other countries must comply with the
requirements herein and applicable national airworthiness requirements.
To ensure proper operation, only parts listed in the Illustrated Parts List of this manual or those
recommended by ACR Electronics may be used as replacement parts for the ELT/NAV Interface -B.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
TASK 25-69-11-990-802
2. Model Description
SUBTASK 25-69-11-990-001
A. ELT/NAV Interface -B
1) The ELT/NAV Interface -B provides the means to transmit position data received from the aircraft
navigation system to the ELT.
2) The ELT/NAV Interface -B is available in two installation configurations:
a) 24-bit auto reprogramming and position data, or
b) Position data only.
SUBTASK 25-69-11-990-002
B. Compatibility
1) The ELT/NAV Interface -B is designed for use with the Model B406-4 ELT (P/N 453-5004) on Boeing
aircraft.
TASK 25-69-11-990-803
3. Approvals
SUBTASK 25-69-11-990-001
A. Certification
1) FAA TSO C126 System Component
NOTE:
Details of TSO certification for the ELT/NAV Interface -B are available in the “ELT/NAV
Interface -B System Qualification Report” (Document 572-0013).
a) The conditions and tests required for TSO approval of this article are minimum performance
standards. It is the responsibility of those installing this article either on or within a specific type or
class of aircraft to determine that the aircraft installation conditions are within TSO standards. TSO
articles must have separate approval for installation in an aircraft. The article may be installed only
if performed under 14 CFR Part 43 or the applicable airworthiness requirements.
2) JTSO-2C126
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
SUBTASK 25-69-11-990-002
B. RTCA DO-160C and DO-160D Compliance
1) Environmental Categories:
a) DO-160C: C1-BA204204XRXXXXXZAZZ204BXXX (Table 1 on page 11)
b) DO-160D: D1(A2)-BB[204(B)][204(C1)XRXXXXXZAZZ[204(T)]ZXXXX (Table 2 on page 12)
CATEGORY
SECTION
DESCRIPTION
C1
4.0
Temperature/Altitude
-
4.5.4
In-Flight Loss of Cooling
B
5.0
Temperature Variation
A
6.0
Humidity
204
7.0
Shock
204
8.0
Vibration
X
9.0
Explosion
R
10.0
Waterproofness
X
11.0
Fluids Susceptibility
X
12.0
Sand and Dust
X
13.0
Fungus
X
14.0
Salt Spray
X
15.0
Magnetic Effect
Z
16.0
Power Input
A
17.0
Voltage Spike
Z
18.0
Audio Frequency Susceptibility
Z
19.0
Induced Signal Susceptibility
204
20.0
Radio Frequency Susceptibility
B
21.0
Emission of Radio Frequency Energy
X
22.0
Lightning
X
23.0
Lightning Direct Effects
X
24.0
Icing
Table 1 DO-160C Environmental Categories Breakdown
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CATEGORY
SECTION
DESCRIPTION
D1(A2)
4.0
Temperature/Altitude
-
4.5.4
In-Flight Loss of Cooling
B
5.0
Temperature Variation
B
6.0
Humidity
204(B)
7.0
Shock
204(C1)
8.0
Vibration
X
9.0
Explosion
R
10.0
Waterproofness
X
11.0
Fluids Susceptibility
X
12.0
Sand and Dust
X
13.0
Fungus
X
14.0
Salt Spray
X
15.0
Magnetic Effect
Z
16.0
Power Input
A
17.0
Voltage Spike
Z
18.0
Audio Frequency Susceptibility
Z
19.0
Induced Signal Susceptibility
204(T)
20.0
Radio Frequency Susceptibility
Z
21.0
Emission of Radio Frequency Energy
X
22.0
Lightning
X
23.0
Lightning Direct Effects
X
24.0
Icing
X
25.0
Electrostatic Discharge
Table 2 DO-160D Environmental Categories Breakdown
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TASK 25-69-11-990-804
4. List of Acronyms, Abbreviations, and Definitions
SUBTASK 25-69-11-990-001
Term Definition
AC
AWG
CAR
CFR
COSPAS-SARSAT
DER
Drip Loop
ELT
EMI
Eurocae
FAA
FAR
Form 337
FSDO
MIL
P/N
Advisory Circular – A Federal Aviation Administration (USA) bulletin with special
information. For the purposes of this document, the acronym AC does not refer to
electrical alternating current.
American Wire Gauge – An electrical wire diameter standard. Look for this
acronym in front of or following a wire size number.
Canadian Aviation Regulations – The rules and regulations governing the
manufacture, certification, operation, maintenance, and alteration of aircraft in
Canada.
Code of Federal Regulations – The general and permanent rules published in the
Federal Register by the executive departments and agencies of the Federal
Government. Title 14, “Aeronautics and Space” contains the FARs.
The international search and rescue consortium that governs the international
satellite-based search and rescue distress alert detection and information
distribution system. For a complete description go to the official web site for the
International COSPAS-SARSAT Program.
Designated Engineering Representative – An individual qualified and designated
by the FAA to approve, or recommend approval, of technical data to the FAA.
Extra wire length used to form a U-shaped bend in a wire or cable. Water or other
fluids will flow down to the bottom of the loop and drip off. Electrical connections
are made at the top of the loop.
Emergency Locator Transmitter – ELTs are installed on aircraft and used to send
emergency signals to the SAR satellite system. The word “Beacon” is associated
with these devices.
Electromagnetic Interference – An undesirable disturbance that affects an
electrical circuit due to either electromagnetic conduction or electromagnetic
radiation emitted from an external source. Also called radio frequency interference
or RFI.
European Organization for Civil Aviation Equipment – EUROCAE documents are
widely referenced as a means of compliance to European Technical Standard
Orders (ETSOs) and other regulatory documents.
Federal Aviation Administration – The United States government agency for
aircraft safety and regulation.
Federal Aviation Regulations – The rules and regulations governing the
manufacture, certification, operation, maintenance, repair, and alteration of
aircraft in the United States.
FAA Form 337 is required anytime a major repair and/or major alteration is
performed on an aircraft. Refer to FAR, Part 43, Appendix A and the definitions of
Major Repair/Alteration contained in FAR, Part 1 for guidance.
Flight Standards District Office – FAA district offices responsible for aircraft
certification, operation, maintenance, and modification issues, approvals and
enforcement.
The three-letter acronym that stands for “Military” and proceeds military
specifications and standards numbers (e.g., MIL-W-xxxx would indicate a wire
specification and MIL-STD-xxxx would indicate a standard).
Part Number – Refers to an ACR Electronics part number, unless otherwise noted.
Part numbers are also indicated with parentheses (e.g., XXX-XXXX).
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Plug
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Receptacle
RTCA
SAR
TSO
UTC
The term “Plug”, within the context of this document, refers to the male half of an
electrical connector.
The term “Receptacle”, within the context of this document, refers to the female
half of an electrical connector.
Radio Technical Commission for Aeronautics – Organization that makes
recommendations for airworthiness. Refer to http://www.rtca.org/aboutrtca.asp
for more information.
Search and Rescue
Technical Standard Order – A TSO is a minimum performance standard issued by
the FAA for specified materials, parts, processes, and appliances used on civil
aircraft.
Coordinated Universal Time – A time standard based on International Atomic
Time. UTC is the time system used in aviation and is often associated with
Greenwich Mean Time (GMT) and/or “Zulu” time.
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TASK 25-69-11-990-805
5. References
SUBTASK 25-69-11-990-001
A. Regulatory Documents
1) The following regulatory documents are referred to herein. When referring to such documents, it is the
manual user’s responsibility to ensure they are using the latest revision or release of such documents. To
that end, the revision designator of specific document numbers has not been included, with the
exception of the RTCA document listing, which reflects the revision level of the documents at the time
of TSO testing and certification.
2) Except in the case of a printed manual, reference documents available on-line or source locations are
linked to applicable web sites.
3) United States
a) AC 20-130, “Airworthiness Approval of Navigation or Flight Management Systems Integrating
Multiple Navigation Sensors”
b) AC 20-138, “Airworthiness Approval of Global Navigation Satellite System (GNSS) Equipment”
c) AC 43-9, “Maintenance Records”
d) AC 43-210, “Standardized Procedures for Requesting Field Approval of Data, Major Alterations, and
Repairs”
e) AC 43.9-1, “Instructions for Completion of FAA Form 337”
f) AC 43-13-1, “Acceptable Methods, Techniques, and Practices – Aircraft Inspection and Repair”
g) AC 43.13-2, “Acceptable Methods, Techniques, and Practices - Aircraft Alterations”
h) FAR, Part 43, “Maintenance, Preventive Maintenance, Rebuilding, and Alteration”
i) FAR, Part 91, “General Operating and Flight Rules”
4) Canada
a) CAR, Part V, “Airworthiness”
b) CAR, Part VI, “General Operating and Flight Rules”
5) COSPAS-SARSAT
a) C/S G.005, “Cospas-Sarsat Guidelines on 406 MHz Beacon Coding, Registration and Type Approval”
b) C/S S.007, “Handbook of Beacon Regulations”
6) RTCA – The following documents are available for purchase at RTCA’s web site www.rtca.org, or by
mail:
a) DO-160C, “Environmental Conditions and Test Procedures for Airborne Equipment”
b) DO-178B, “Software Considerations in Airborne Systems and Equipment Certification”
c) DO-182, “Emergency Locator Transmitter (ELT) Equipment Installation and Performance”
d) DO-183, “Minimal Operational Performance Standards for Emergency Locator Transmitters Automatic Fixed-ELT (AF), Automatic Portable-ELT (AP), Automatic Deployable-ELT (AD),
Survival-ELT (S) Operating on 121.5 and 243.0 MHz”
e) DO-204, “Minimal Operational Performance Standards for 406 MHz Emergency Locator
Transmitters (ELT)”
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SUBTASK 25-69-11-990-002
B. Other Documents
1) The following documents are available on-line at the Artex products web site at
www.acrelectronics.com, or from ACR Electronics upon request.
a) 570-1000, “ELT Test Set (ETS) Operation Manual”
b) 572-0013, “ELT/NAV Interface -B System Qualification Report”
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DESCRIPTION AND OPERATION
TASK 25-69-11-870-801
1. Description
SUBTASK 25-69-11-870-001
A. Overview
1) The ELT/NAV Interface -B is integrated into the ELT system. See Figure 1 ELT/NAV Interface -B System
Integration.
Figure 1 ELT/NAV Interface -B System Integration
2) The ELT/NAV Interface -B is designed to work with “ELT with 24-bit Address” and “ELT with Serial
Number” location protocols. In both cases, the ELT/NAV Interface -B provides position coordinates
(latitude and longitude) to the ELT.
a) For aircraft using an “ELT with 24-bit Address” location protocol, the ELT/NAV Interface -B also
provides the means to reprogram an ELT automatically in the event an ELT programmed with a
different 24-bit address aircraft ID has been placed in the aircraft.
b) For aircraft using an “ELT with Serial Number” location protocol, the ELT/NAV Interface -B
reprogramming receptacle (P1) is capped and the unit only provides position data to the ELT.
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-B (453-6501)
SUBTASK 25-69-11-870-002
B. Physical Description
1) The ELT/NAV Interface -B components are housed in a 0.125 inch (3.2 mm) thick aluminum chassis;
finished with a chromate conversion primer and a safety orange, high solids epoxy or polyurethane
finish. See Figure 2 ELT/NAV Interface -B Isometric View.
Figure 2 ELT/NAV Interface -B Isometric View
SUBTASK 25-69-11-870-003
C. Position Data Functionality
1) The ELT/NAV Interface -B receives position coordinates (latitude and longitude) from the aircraft
onboard navigation system.
2) The ELT/NAV Interface -B is capable of receiving data from the aircraft navigation system via the
following protocols:
a) ARINC 429 - See SUBTASK 25-69-11-870-001 on page 19 for requirements.
b) RS-232 - See SUBTASK 25-69-11-870-002 on page 20 for requirements.
3) The ELT/NAV Interface -B converts the position data to a format compatible with the ELT and forwards
the data to the ELT via a second RS-232 port.
4) The ELT must be programmed with a location protocol (long message format) in order to receive,
assimilate, and broadcast position data provided by the ELT/NAV Interface -B.
5) The ELT stores the position data in RAM and broadcasts the position data, along with identification data,
when the ELT is activated.
6) Position data is continually updated and overwritten in the ELT RAM as long as the ELT is idle and waiting
for an activation signal.
7) If power to the ELT/NAV Interface -B is lost, the ELT holds the last known position data for 30 seconds
and the ELT must be activated within that time frame to transmit position information.
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-B (453-6501)
SUBTASK 25-69-11-870-004
D. 24-Bit Address Reprogramming Functionality
CAUTION:
THE PROGRAMMING AND LABELING OF THE ELT MUST MATCH THE AIRCRAFT IN
WHICH IT IS INSTALLED. REMARK THE ELT PRODUCT LABEL AS NECESSARY TO
REFLECT NEW PROGRAMMING AND/OR COUNTRY OF REGISTRY. CONTACT THE
LOCAL REGULATORY AUTHORITIES RESPONSIBLE FOR ELT REGISTRATION AND
REFER TO THE APPLICABLE ELT ABBREVIATED COMPONENT MAINTENANCE MANUAL
FOR ELT REGISTRATION REQUIREMENTS.
1) The ELT/NAV Interface -B provides the means to reprogram ELTs with 24-bit address location protocol
programming.
2) This capability facilitates swapping ELTs from one aircraft to another when performing routine
maintenance, etc., without losing a significant amount of time reprogramming ELTs.
3) If the ELT is not programmed with a 24-bit address location protocol, the ELT/NAV Interface -B will not
reprogram the ELT.
TASK 25-69-11-870-802
2. Navigation System Interface Requirements
SUBTASK 25-69-11-870-001
A. ARINC 429 Latitude and Longitude Data Input
1) The ELT/NAV Interface -B will accept signals “A” and “B” from any ARINC 429 navigation system.
2) The interface looks for labels “310” (latitude) and “311” (longitude), which contain position data.
3) The interface accepts data at:
(a) High speed,
(b)
Low speed,
(c)
GAMA high speed, or
(d)
GAMA low speed.
4) ARINC 429 output speed must not change during ELT/NAV Interface -B operation.
5) The interface automatically detects output speed after turn-on and locks on after 20 seconds.
6) ARINC 429 is the preferred output for navigation systems that support both ARINC 429 and RS-232
output.
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SUBTASK 25-69-11-870-002
B. RS-232 Latitude and Longitude Data Input
CAUTION:
DO NOT CONNECT ARINC 429 AND RS-232 INPUTS AT THE SAME TIME.
1) For navigation systems that output only RS-232, the ELT/NAV Interface -B accepts the following RS-232
format only.
a) Baud Rate (fixed): 9600
b) Parity: None
c) Data Bits: 8
d) Stop Bits: 1
2) The RS-232 format must have:
a) Start of Text (STX),
b) “A” identifier for latitude,
c) “B” identifier for longitude, and
d) End of Text (ETX).
3) The RS-232 format expects carriage returns, but will not operate if there are line feeds.
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TASK 25-69-11-870-803
3. Operation
SUBTASK 25-69-11-870-001
A. Position Data Processing
(1)
Operation of ELT/NAV Interface -B position data processing (i.e., receive, convert, and
transmit) is automatic and requires no operator interface other than activating the +28 VDC
power source.
(2)
(3)
The following conditions must be true for ELT/NAV Interface -B position data processing to
function:
(a)
+28 VDC aircraft power must be applied to the unit (i.e., the power source must be
switched on).
(b)
The aircraft navigation system must be on and transmitting position data to the ELT/NAV
Interface -B.
Once the ELT is activated, it stops receiving position data; however, the ELT/NAV Interface -B
continues to transmit as long as it has power and is receiving position data.
SUBTASK 25-69-11-870-002
B. 24-Bit Address Reprogramming
(1)
Operation of the ELT/NAV Interface -B 24-bit address reprogramming function is automatic and
requires no operator interface other than activating the +28 VDC power source.
(2)
When +28 VDC power is applied to the ELT/NAV Interface -B, it reads the ELT 24-bit address
data and compares it to the 24-bit address data hard wired to the ELT/NAV Interface -B.
(3)
If a difference in 24-bit address programming is found, the ELT/NAV Interface -B reprograms
the ELT to the data read from the hard wired installation.
(4)
When the two sets of 24-bit address data are identical, the ELT/NAV Interface -B takes no
action.
(5)
If the ELT is programmed with a protocol other than 24-bit address, the ELT/NAV Interface -B
attempts to reprogram the ELT with new aircraft identification data and fails.
(a)
If P1 (i.e., 24-bit address) is connected to the ELT/NAV Interface -B and the ELT is
programmed with a protocol other than 24-bit address, an error will be displayed by the
ELT LED.
(b)
See SUBTASK 25-69-11-750-002 on page 30 and Table 6 on page 32.
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TASK 25-69-11-870-804
4. Specifications
SUBTASK 25-69-11-870-001
A. Physical and Environmental
(1)
Table 3 lists the ELT/NAV Interface -B physical and environmental specifications.
PARAMETER
CHARACTERISTIC
Temperature (Storage)
-55° C to +85° C
Temperature (Operating)
-20° C to +70° C
Altitude
55,000 ft (16,764 m)
Vibration
10 g sinusoidal
6.1 g RMS Random
Shock
500 g for 4 ms
Crashworthiness
100 g for 23 ms
Humidity
95% for 240 hrs
Impact
55 lbs from 6 in. (24.9 kg from 152 mm)
Crush
1,000 lbs (453.6 kg)
Spurious Emissions
Per RTCA DO-204
Flammability
Self-Extinguishing
Weight
2.8 lbs (1.27 kg)
Dimensions
9.3 x 5.0 x 1.9 in. (236 x 127 x 48 mm)
Table 3 Physical and Environmental Specifications
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SUBTASK 25-69-11-870-002
B. Input/Output
1) Table 4 lists the ELT/NAV Interface -B electrical pinout specifications.
PIN
DESCRIPTION
CHARACTERISTIC
P2-1
Power Input
+28 VDC ±5 VDC
300 mA max.
P2-2
5.6 VDC Output
Vmax = 6.0 VDC
Vmin = 5.3 VDC
P2-3
ARINC 429-A Input
(Auto Speed Select)
High/Low
Standard or GAMA
P2-4
ARINC 429-B Input
(Auto Speed Select)
High/Low
Standard or GAMA
P2-5
Not Used
N/A
P2-6
Not Used
N/A
P2-7
Not Used
N/A
P2-8
RS-232 RX
RS-232
P2-9
TX Output
RS-232
P2-10
RX Input
TTL
P2-11
ELT/NAV Ground
Aircraft Ground
P2-12
ELT Ground
Aircraft Ground
P1-1 thru 24
24-bit Address Input
Ground =1
Open = 0
P1-25 and 26
24-bit Address Return
24-bit Ground
Table 4 Input/Output Specifications
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SUBTASK 25-69-11-870-003
C. Electrical
1) Table 5 lists the ELT/NAV Interface -B electrical specifications.
PARAMETER
CHARACTERISTIC
Power Input
Per RTCA/DO-160D
Voltage Spike
Per RTCA/DO-160D
Audio Frequency Susceptibility
Per RTCA/DO-160D
Induced Signal Susceptibility
Per RTCA/DO-160D
Radio Frequency Susceptibility
Per RTCA/DO-160D and DO-204
Emission of RF Energy
Per RTCA/DO-160D
Table 5 Electrical Specifications
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TEST AND FAULT ISOLATION
TASK 25-69-11-750-801
1. General
SUBTASK 25-69-11-990-001
A. Applicability
1) This section only covers inspection, testing, and fault isolation procedures specific to the ELT/NAV
Interface -B.
2) Refer to the applicable ELT abbreviated component maintenance manual associated with the ELT/NAV
Interface -B to coordinate the requirements herein with the requirements for inspection, test, and fault
isolation of the ELT system as a whole.
SUBTASK 25-69-11-990-002
B. Regulatory Requirements
1) The ELT/NAV Interface -B is considered an integral part to the ELT system, and as such is subject to the
periodic inspection and testing required by the regulatory authorities governing the installation,
operation, and maintenance of ELT systems.
2) Refer to the applicable ELT abbreviated component maintenance manual associated with the ELT/NAV
Interface -B for references to the regulatory requirements.
3) Inspection and testing of the ELT/NAV Interface -B must be accomplished in conjunction with and on the
same schedule as the ELT and other system components.
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TASK 25-69-11-750-802
2. Periodic Inspection
SUBTASK 25-69-11-220-001
A. Inspection Procedures
1) Remove the ELT/NAV Interface -B in accordance with SUBTASK 25-69-11-050-001 on page 33.
2) Perform a visual inspection of the chassis exterior, checking for:
a) Damage to the finish,
b) Corrosion,
c) Excessive wear of the mounting holes, and
d) Cracks in the mounting flanges.
3) Perform a visual inspection of the mounting hardware for condition and corrosion.
4) Perform a visual inspection of the connectors, checking for:
a) Corrosion,
b) Bent or broken pins, and
c) Security of wires in the pins and pins in the connector socket.
NOTE: A slight tug on each wire will reveal a wire loose in the pin (i.e., bad crimp) or an
improperly seated pin in the connector socket.
5) Inspect the P2 interface wiring between the ELT/NAV Interface -B and the ELT for:
a) Security,
b) Evidence of damage, and
c) Evidence of insulation deterioration.
6) Inspect the P1 24-bit address wiring between the ELT/NAV Interface -B and ground or 24-bit address
switch block for:
a) Security,
b) Damage,
c) Insulation deterioration, and
d) Grounding points for corrosion.
7) Reinstall the ELT/NAV Interface -B in accordance with SUBTASK 25-69-11-450-002 on page 43.
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TASK 25-69-11-750-803
3. Periodic Testing
SUBTASK 25-69-11-750-001
A. Position Data ELT Self-Test
1) This is a recommended periodic test.
2) The following test procedure incorporates the steps necessary to confirm operation of the ELT/NAV
Interface -B into the “Installed Transmitter Test” procedure defined in the applicable ELT abbreviated
component maintenance manual.
3) This test procedure initiates the ELT self-test routine, a part of which checks for position data.
4) Perform the following functional check within the first 5 minutes after the hour (UTC), as required by AC
43.13-1, Chapter 12, § 12-22, Note 3.
a) Notify any nearby control tower of your intentions.
b) Turn on the aircraft navigation system and verify it is receiving valid position data.
c) Verify the ELT/NAV Interface -B is powered up and has at least 30 seconds to initialize.
d) Tune a receiver, usually the aircraft transceiver, to 121.5 MHz.
NOTE:
An AM radio may be used to receive the signal.
e) Activate the ELT by placing the ELT local switch in the “ON” position. The cockpit panel status light
will stay on steady and the ELT LED will begin flashing continuously.
f) Listen for 3 audible sweeps on the receiver, which takes about 1 second.
g) Verify the buzzer sounds immediately upon activation.
h) Return the ELT local switch to the “OFF” position while paying close attention to ELT LED activity
when the ELT enters the “OFF” condition. If the ELT is working properly, the ELT LED will stay on for
approximately 1 second and then turn off.
i) Refer to Table 6 on page 32 if the LED displays a 5-flash error, which indicates the ELT is not
receiving position data.
NOTE:
Refer to the troubleshooting guide in the applicable ELT abbreviated component
maintenance manual for a complete breakdown of error codes, causes, and possible
solutions.
5) If verification of the position data contained in the 406 MHz message is desired, perform the
post-installation position data functional test in SUBTASK 25-69-11-750-001 on page 31.
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TASK 25-69-11-750-804
4. Post-Installation Functional Testing
SUBTASK 25-69-11-990-001
A. General
CAUTION:
ANY ELT RUNNING V133 SOFTWARE (SEE PRODUCT LABEL) MUST BE TESTED IN AN
RF CONTAINER, SCREEN ROOM, OR CONNECTED TO A DUMMY LOAD VIA THE
ANTENNA COAX CONNECTION, BECAUSE THE V133 SOFTWARE TRANSMITS A FIXED
TEST MESSAGE AT ELT RESET, NECESSITATING A “LIVE” BROADCAST TO READ THE
ACTUAL MESSAGE. ANY ELT RUNNING V134 OR V135 SOFTWARE TRANSMITS THE
ACTUAL 406 MHZ MESSAGE AT RESET AND MAY BE TESTED IN SITU.
1) This task consists of three subtask testing requirements:
a) A position data test, which verifies ELT/NAV Interface -B position data functionality by reading and
validating position data broadcast by the ELT.
b) 24-bit address programming test, which verifies ELT/NAV Interface -B 24-bit address
reprogramming functionality by initiating reprogramming and checking for an error indication.
c) 15-digit hex ID determination, which reads the programmed hex ID, country, and country code
broadcast in the 406 MHz message and provides instructions for relabeling and re-registering the
ELT, as applicable.
SUBTASK 25-69-11-750-001
B. Position Data Verification Test
CAUTION:
DO NOT ALLOW THE ELT TO STAY ACTIVE LONGER THAN 40 SECONDS DURING THIS
TEST. AFTER APPROXIMATELY 50 SECONDS THE ELT WILL BROADCAST A 406 MHZ
BURST AND THIS SIGNAL WILL BE INTERPRETED AS A VALID EMERGENCY SIGNAL BY
THE COSPAS-SARSAT SATELLITE SYSTEM.
1) Perform the following procedure within the first 5 minutes after the hour (UTC), as required by AC
43.13-1, Chapter 12, § 12-22, Note 3.
a) Notify any nearby control tower of your intentions.
b) Turn on the aircraft navigation system and verify it is receiving valid position data.
c) Verify the ELT/NAV Interface -B is powered up and has at least 30 seconds to initialize.
d) Set the 453-1000 ELT Test Set (ETS) beacon reader to receive and decode the ELT digital message.
Refer to the ETS operating manual (570-1000) for ETS operating instructions and additional details.
NOTE:
The ETS antenna should be within 30 feet of the aircraft 406 MHz antenna.
NOTE:
A beacon reader equivalent to the ETS may be used, provided it is capable of receiving
and decoding the 406 MHz digital message.
e) Activate the ELT by placing the local control switch or remote control panel switch in the “ON”
position.
f) Allow the ELT to transmit for approximately 5 seconds.
g) Deactivate the ELT and read the test message broadcast at “turn off”.
NOTE: The test message broadcast by the ELT at “turn-off” contains all the information
in an actual distress message, except there is a special digital prefix that informs
COSPAS-SARSAT satellites to ignore the message.
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2) Message examples are shown in Figure 3 Examples of Location Protocol 406 MHz Messages.
Figure 3 Examples of Location Protocol 406 MHz Messages
3) The left hand example in Figure 3 Examples of Location Protocol 406 MHz Messages is an ELT
programmed for “Standard Location Protocol ELT with Serial Number”. The right hand example is an ELT
programmed for “Standard Location Protocol ELT with 24-bit Address”.
a) Actual messages will vary depending on the protocol and information programmed into the ELT.
b) If the ELT is programmed with a location (long message) protocol and disconnected from the
ELT/NAV Interface -B or the aircraft navigation system is not transmitting position data, the
message will indicate “Position Invalid” in lieu of position data. See Figure 4 406 MHz Location
Message without Position Data.
Figure 4 406 MHz Location Message without Position Data
4) Repeat the activation and deactivation cycle if the ETS fails to read the message on the initial try. The
406 MHz oscillator may not be warmed up.
5) If continued attempts to read the message fail, check the ELT for self-test error codes and refer to the
applicable ELT abbreviated component maintenance manual.
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SUBTASK 25-69-11-750-002
C. 24-Bit Address Reprogramming Verification Test
This test procedure verifies the ELT/NAV Interface -B has updated the aircraft 24-bit address ID in the ELT
programming.
1) Apply power to the ELT/NAV Interface -B, while the ELT remains off (i.e, inactive). Re-programming
takes place within 30 seconds of power up.
2) Monitor the ELT for the next 2 minutes.
a) The LED on the ELT will begin to flash rapidly if reprogramming was NOT successful. See Table 6 on
page 32 for troubleshooting guidelines.
b) If the LED remains off after two minutes, the ELT has been reprogrammed. Proceed to SUBTASK
25-69-11-750-001 on page 31.
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TASK 25-69-11-750-805
5. Post-Reprogramming Check
SUBTASK 25-69-11-750-001
A. 15-Digit Hex ID Verification
1) 15-digit hex ID verification should be performed any time an ELT is installed in an aircraft to verify the
ELT is properly labeled and registered.
2) Perform the following procedure within the first 5 minutes after the hour (UTC), as required by AC
43.13-1, Chapter 12, § 12-22, Note 3.
a) Notify any nearby control tower of your intentions.
b) Verify the ELT/NAV Interface -B is powered up and has at least 30 seconds to initialize.
NOTE:
The aircraft navigation system is NOT turned on for this test. For ELT registration
purposes, the 15 digit hex ID shall contain the “default” value of no position data (i.e.,
always FFBFF)
c) Set the 453-1000 ELT Test Set (ETS) beacon reader to receive and decode the ELT digital message.
Refer to the ETS operating manual (570-1000) for ETS operating instructions and additional details.
NOTE:
A beacon reader equivalent to the ETS may be used, provided it is capable of receiving
and decoding the 406 MHz digital message.
d) Place the ETS within 30 feet of the aircraft 406 MHz antenna.
e) Activate the ELT by placing the local control switch or remote control panel switch in the “ON”
position.
f) Allow the ELT to transmit for approximately 5 seconds.
g) Deactivate the ELT and read the test message broadcast at “turn-off”. A message example is shown
in Figure 4 406 MHz Location Message without Position Data on page 29.
3) The 15 digit hex ID (i.e., Beacon ID) displayed by the ETS is compared to the hex ID on the ELT. If
identical, no further action is necessary. If different:
(a) Enter the new hex ID on label P/N 591-0999 and affix it to the ELT over the existing hex
ID on the product label.
(b)
If country and country code have changed, enter the new information on label P/N
591-0429-01 and affix it to the ELT over the existing information on the product label.
(c)
Re-register the ELT. Refer to the applicable ELT abbreviated component maintenance
manual for specific ELT registration information and instructions.
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TASK 25-69-11-810-801
6. Fault Isolation
SUBTASK 25-69-11-810-001
A. Troubleshooting Guidelines
(1)
Table 6 provides ELT troubleshooting guidelines for installation and operational issues.
SYMPTOM
PROBABLE CAUSE
POSSIBLE SOLUTION
Aircraft navigation system off
Turn on navigation system
No power to ELT/NAV
Interface -B
ELT LED displays 5-flash error
Turn on power
Check breaker/fuse
Check for frayed insulation
causing short or ground
(No navigation data present)
Faulty interface wiring or
connections
Verify integrity of all crimp and
solder connections
Check wiring continuity and repair
as necessary
ELT not programmed for 24-bit
address location protocol
Check for frayed insulation
causing short or ground
ELT LED flashes rapidly within
two minutes after ELT/NAV
Interface -B power up
(24-bit address not accepted)
Program ELT with 24-bit address
location protocol
Faulty interface wiring or
connections
Verify integrity of all crimp and
solder connections
Check wiring continuity and repair
as necessary
Table 6 Troubleshooting Guide
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REMOVAL
TASK 25-69-11-050-801
1. ELT/NAV Interface -B
SUBTASK 25-69-11-050-001
A. Removal
1) See Figure 5 ELT/NAV Interface -B Removal.
2) Disconnect ELT/NAV Interface -B plugs:
a) P2, and
b) P1, if installed.
3) Install connector covers to protect the ELT/NAV Interface -B receptacles.
4) Remove the screws attaching the ELT/NAV Interface -B to the mounting structure.
Figure 5 ELT/NAV Interface -B Removal
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TASK 25-69-11-500-801
2. Material or Equipment Return
SUBTASK 25-69-11-510-001
A. Shipment Information
1) If any material or equipment is to be returned to the factory, under warranty or otherwise, ACR
Electronics must be notified prior to shipment with the following information:
1. Model and serial number of equipment being returned,
2. Date purchased,
3. Date placed in service,
4. Number of hours in service,
5. Nature and cause of failure, and
6. Remarks, if any.
SUBTASK 25-69-11-580-001
B. Return Material Authorization
1) Upon receipt of such notice, ACR Electronics will issue a Return Material Authorization (RMA) number
which then authorizes return of the material or equipment to the following address:
Repair and Overhaul
ACR Electronics, Inc.
5757 Ravenswood Road
Fort Lauderdale, FL 33312 USA
Phone: (954) 981-3333
Fax: (954) 983-5087
a) Failure to obtain a RMA number and provide the details listed in SUBTASK 25-69-11-510-001 may
cause unnecessary delay and/or rejection of the returned material or equipment.
b) All material or equipment returned to the factory must be freight prepaid.
c) Acceptable methods of shipment for international return are Airborne, Burlington Air, DHL, Emery,
Federal Express, UPS International, and World Wide only.
NOTE:
Do not use “International Commercial Airlines”, such carriers may cause a loss of
returned material or equipment.
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INSTALLATION
TASK 25-69-11-450-801
1. Regulatory Requirements and Guidelines
SUBTASK 25-69-11-990-001
A. Applicability
1) The regulatory requirements and guidelines for ELT installations discussed in the following subtasks are
applicable to installation of the ELT/NAV Interface -B and must be applied to the ELT/NAV Interface -B.
Where the word “ELT” is used in the following subtasks, read “ELT/NAV Interface -B”.
SUBTASK 25-69-11-990-002
B. TSO C126, Paragraph D
1) TSO approval of the ELT does not constitute installation approval. All installations are subject to field
approval for a given airframe by either an approved FAA DER or FAA FSDO. For installations outside the
US, contact your local civil aviation regulatory agency for details.
SUBTASK 25-69-11-990-003
C. FAA
1) This manual constitutes supporting data, as described in AC43.9-1, Paragraph 6.h.(2) and AC 43-210,
Chapter 2, Paragraph 201(a)(6), and as such may be used as support for FAA field approval of the
ELT/NAV Interface -B installation.
2) In addition to the procedures outlined herein and in accordance with FAR Part 43, the installer must
adhere to the aircraft manufacturer’s instructions and recommendations and the guidelines provided by
FAA Advisory Circular AC 43.13-2 “Acceptable Methods, Techniques, and Practices - Aircraft
Alterations”, specifically Chapters 1 through 3, 11, and 13.
3) By signing the aircraft logbook, and FAA Form 337, the installer is stating the installation has been
performed in accordance with current FAR requirements and the procedures outlined herein. The
completed Form 337 is provided to the FAA and also becomes a permanent part of the aircraft
maintenance records in accordance with AC43-9, Paragraph 17.
SUBTASK 25-69-11-990-004
D. Canada
1) All installations must be performed in accordance with Canadian Aviation Regulations (CAR) Part V,
Subparts 37, 51, and 71.
SUBTASK 25-69-11-990-005
E. Other Countries
1) Installations in aircraft outside of the United States and Canada, must be performed in accordance with
applicable regulatory authority rules and regulations.
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SUBTASK 25-69-11-990-006
F. RTCA
1) DO-204, § 3.1.8 guidelines for mounting a ELT:
a) The ELT shall be mounted to primary aircraft load carrying structures, such as trusses, bulkheads,
longerons, spars, or floor beams.
b) The mounts shall have a maximum static local deflection no greater than 0.1 inches (2.5 mm) when
a force of 100 lbs (450 newtons) is applied to the mount in the most flexible direction. Deflection
measurements shall be made with reference to another part of the aircraft not less than 1 foot (0.3
meters) nor more than 3 feet (1.0 meters) from the mounting location.
2) DO-182, § 6.2.2.b recommends that:
a) To maximize the probability of the ELT transmitting a detectable signal after a crash, all ELT system
components, which must survive a crash intact, e.g., transmitter and external antenna, should be
attached to the airframe in such a manner that the attachment system can support a 100 g load,
(ELT weight x 100, ELT antenna weight x 100, etc.) applied through the center of gravity of the
component (ELT, antenna, etc.) in the plus and minus directions of the three principal axes of the
aircraft.
b) Post-crash critical components of the ELT system, e.g., transmitter and external antenna, should be
mounted as close to each other as possible.
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
TASK 25-69-11-450-802
2. Mechanical
SUBTASK 25-69-11-450-001
A. Chassis Location
CAUTION:
AVOID LOCATING THE ELT/NAV INTERFACE -B WHERE IT MAY BE SUBJECTED TO
UNPROTECTED EXPOSURE TO HARSH CHEMICAL FLUIDS, SUCH AS DEICING
COMPOUNDS. THESE TYPES OF CHEMICALS MAY CAUSE DAMAGE TO FASTENERS
AND ELECTRICAL COMPONENTS, AS WELL AS ELECTRICAL CONNECTOR CORROSION.
1) Mount the ELT/NAV Interface -B within 2 feet (610 mm) of the ELT, such that the interface harness does
not exceed 3 feet (914 mm) including strain relief.
2) The ELT/NAV Interface -B chassis and ELT are mounted to the same support structure in most
installations.
SUBTASK 25-69-11-450-002
B. Chassis Installation
1) Coordinate ELT/NAV Interface -B chassis installation with ELT installation whenever possible. If the
ELT/NAV Interface -B is an add-on to an existing ELT installation, extend/modify the existing ELT
support structure to accommodate the ELT/NAV Interface -B.
2) See Figure 6 ELT/NAV Interface -B Outline and Dimensions.
Figure 6 ELT/NAV Interface -B Outline and Dimensions
3) Align the ELT/NAV Interface -B on the mounting structure.
4) Mark the six holes needed for mounting, using the unit as a pattern. Hole pattern dimensions are also
illustrated in Figure 6 ELT/NAV Interface -B Outline and Dimensions.
5) Drill the six mounting holes with a #19 or 4.25 mm drill.
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
6) Install the ELT/NAV Interface -B chassis with the 8-32 x 5/8” SS pan head Philips screws, flat washers,
lock washers, and nuts provided in the installation kit (455-6500), as shown in Figure 7 ELT/NAV
Interface -B Mechanical Installation.
NOTE: The use of substitute mounting hardware is acceptable provided the hardware used
meets or exceeds the strength and corrosion resistance of the original hardware.
(a)
Torque to 12 ±1 lb-in (136 ± 11 N•cm).
Figure 7 ELT/NAV Interface -B Mechanical Installation
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
TASK 25-69-11-450-803
3. Wiring
SUBTASK 25-69-11-990-001
A. General Considerations and Recommendations
CAUTION:
IF GROUND OR OTHER CONNECTIONS ARE BROKEN OR OTHERWISE DAMAGED, THE
ELT IS STILL CAPABLE OF AUTOMATIC ACTIVATION; HOWEVER, ELT/NAV INTERFACE
-B OPERATION MAY BE AFFECTED AND POSITION DATA MAY NOT BE TRANSMITTED
TO THE ELT.
CAUTION:
INCORRECT TERMINATION OF THE WIRING IN THE CONNECTORS MAY DAMAGE THE
ELT/NAV INTERFACE -B. VERIFY THE WIRING AGAINST THE WIRING DIAGRAM AND
PERFORM A CONTINUITY CHECK TO CONFIRM GOOD CONNECTIONS AND PROPER
PIN LOCATIONS.
1) The following wiring and grounding considerations and recommendations are applicable:
a) Minimum 22 AWG wire size for interface wiring.
b) Shielding is recommended to help prevent EMI and RF interference.
c) Use high quality conductor meeting MIL-W-16878, M22759, M27500, or a commercial equivalent
acceptable for use in aircraft applications.
d) Provide a “Drip Loop” at the ELT/NAV Interface -B plug and ELT receptacle to divert moisture from
the connections. See SUBTASK 25-69-11-990-001 on page 13 for a definition.
e) All grounds must be common to aircraft ground.
2) Maximum interface and data line wire lengths are:
a) Interface Harness - 3 feet (0.9 m)
b) ARINC 429 - 360 feet (110 m)
NOTE:
Ground shield at every break. ELT/NAV Interface -B plug strain relief is not an
acceptable ground.
c) RS-232 - 50 feet (15 m)
3) Minimum 24 AWG wire size for 24-bit address reprogramming ground wires.
4) Switch block, if used, must be located less than 3 feet (0.9 m) from the ELT/NAV Interface -B and wiring
must not exceed 3 feet (0.9 m) including strain relief.
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
SUBTASK 25-69-11-450-001
B. ELT and Navigation System Interfaces
CAUTION: DO NOT CONNECT THE ELT/NAV INTERFACE -B POWER WIRE DIRECTLY TO THE
BATTERY. THE UNIT DRAWS POWER WHENEVER POWER IS APPLIED TO IT AND COULD
DRAIN THE AIRCRAFT BATTERY WHEN NOT IN USE.
1) See Figure 8 ELT/NAV Interface -B Wiring Diagram.
Figure 8 ELT/NAV Interface -B Wiring Diagram
2) Fabricate a shielded 4-wire harness long enough to reach between the ELT/NAV Interface -B and the
ELT, including strain relief and drip loop.
a) Strip approximately 0.15 in. (3 mm) of insulation from the ELT receptacle end of the four cable wires
and 0.19 in. (5 mm) from the ELT/NAV Interface end.
b) Dress and tin the bare wire ends to prevent the strands from fraying during terminal crimping
operations.
3) Fabricate a shielded, twisted pair ARINC 429 data cable.
NOTE:
Single, shielded wire for RS-232 data line.
a) Strip approximately 0.19 in. (5 mm) of insulation from the ELT end of the twisted pair.
b) Dress and tin the bare wire ends to prevent the strands from fraying during terminal crimping
operations.
c) Prepare the twisted pair wires at the navigation system end in accordance with the navigation
system manufacturer’s written instructions.
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
4) Fabricate a ground wire of sufficient length to reach from the ELT/NAV Interface -B to a suitable aircraft
ground location.
a) Strip approximately 0.19 in. (5 mm) of insulation from each end of each of the ground wire.
b) Dress and tin the bare wire ends to prevent the strands from fraying during terminal crimping
operations.
5) Fabricate a power wire of sufficient length to reach from the ELT/NAV Interface -B to a suitable aircraft
+28 VDC, switchable power source.
6) Crimp male terminal pins (151-6627) on the harness wire ends at the ELT.
NOTE: Use Molex crimp tool 63811-3300, or an equivalent tool for 0.062 in. terminal pins.
7) Crimp or solder contact sockets 151-2100 on the ELT/NAV Interface -B end of the following wires:
a) 4-wire harness,
b) Power wire,
c) Ground wire, and
d) Twisted pair data wires (ARINC 429) or RS-232 data wire.
8) Feed the wires going to the ELT through the ELT mounting frame cap. See Figure 9 Wiring Installation
at ELT End.
9) Install the wires at the ELT end into the Molex receptacle. See Figure 9 Wiring Installation at ELT End
and Figure 8 ELT/NAV Interface -B Wiring Diagram on page 40.
NOTE:
Terminal pins may be removed from the receptacle using Molex extraction tool
11030002, or equivalent.
Figure 9 Wiring Installation at ELT End
10) Seal the ELT receptacle in accordance with the applicable ELT abbreviated component maintenance
manual, once all tests have been completed satisfactorily.
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
11) Feed the interface wires at the ELT/NAV Interface -B end through the 183-6503 strain relief. See Figure
10 ELT/NAV Interface -B Wiring Installation.
Figure 10 ELT/NAV Interface -B Wiring Installation
12) Install the following wires at the ELT/NAV Interface -B end in the 150-6503, 24-position plug (P2):
a) The 4 interface harness wires,
b) ARINC 429 twisted pair (or RS-232 data wire),
c) +28 VDC power wire, and
d) Airframe ground wire.
13) Insert spare 151-2100 contact sockets and 151-2102 sealing plugs into unused plug positions.
14) Install strain relief on the plug and tighten the wire clamp.
15) Connect the ground wires to the airframe in accordance with the aircraft manufacturer’s written
instructions or as described in AC 43.13-1, Chapter 11, § 15, as applicable. See Figure 8 ELT/NAV
Interface -B Wiring Diagram on page 40.
16) Tie all shields to aircraft ground in accordance with the aircraft manufacturer’s written instructions or as
described in AC 43.13-1, Chapter 11, § 15, as applicable. See Figure 8 ELT/NAV Interface -B Wiring
Diagram on page 40.
17)
18)
19)
20)
NOTE:
Keep shield drain as short as possible.
Support the wiring by clamping or other suitable means, such that the wiring is properly supported and
protected from chaffing and strain. Refer to the aircraft manufacturer’s written instructions or as
described in AC 43.13-1, Chapter 11, § 9 through 12, as applicable.
Connect the P2 plug to the ELT/NAV Interface -B.
Install the 150-6504 protective cap on the ELT/NAV Interface -B P1 plug, if the 24-bit address
reprogramming option is not used.
Test the installation in accordance with the procedure outlined in SUBTASK 25-69-11-750-001 on page
31.
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
SUBTASK 25-69-11-450-002
C. 24-Bit Address Reprogramming – Hard Wire Method
1) The 24-bit address is composed of binary “1s” and “0s”, with a “1” electrically grounded to the airframe
and “0” electrically open.
2) Encoding is accomplished by either “hard wiring” the respective “1” pins to ground or by using a 24-bit
address switch block, which internally grounds selected addresses. Hard wiring is the preferred method.
See SUBTASK 25-69-11-450-003 on page 44 for 24-bit address switch block instructions.
3) Determine the appropriate binary 24-bit address based on the octal or hexadecimal ID code assigned to
the aircraft. See Figure 11 Octal/Hexadecimal to Binary Conversion.
Figure 11 Octal/Hexadecimal to Binary Conversion
4) Prepare the number of ground wires (binary “1”) necessary to encode the 24-bit address as follows:
(a) Strip approximately 0.19 in. (5 mm) of insulation from the ends of each of the ground
wire.
(b)
Dress and tin the bare wire ends to prevent the strands from fraying during terminal
crimping operations.
5) Crimp contact pins 151-2101 onto one end of each wire.
6) Insert the contact pins into the appropriate pin locations of the 150-6502 plug (P1). See Figure 8
ELT/NAV Interface -B Wiring Diagram on page 40.
7) Verify each pin is inserted into the pin location on the P1 plug that corresponds to the appropriate bit
address. See Figure 8 ELT/NAV Interface -B Wiring Diagram on page 40.
8) Connect the other end of each wire to pins P1-25 and P1-26, which are grounded through the chassis.
If the wires are spliced, fabricate the splices in a manner acceptable to the aircraft manufacturer or as
described in AC 43.13-1, § 13.
NOTE: Split the wires between P1-25 and P1-26, such that the number of wires going to each
pin are divided evenly.
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
9) Insert spare 151-2100 contact sockets and 151-2102 sealing plugs into unused plug positions.
10) Install the 183-6502 strain relief on the plug and tighten the wire clamp. See Figure 10 ELT/NAV
Interface -B Wiring Installation on page 42.
11) Connect the P1 plug to the ELT/NAV Interface -B.
12) Test the installation in accordance with SUBTASK 25-69-11-750-002 on page 30.
SUBTASK 25-69-11-450-003
D. 24-Bit Address Reprogramming – Switch Block Method
1) Locate and install the 24-bit switch block less than 3 feet (0.9 m) from the ELT/NAV Interface -B in
accordance with the manufacturer’s written instructions.
2) Prepare twenty-six (26) wires as follows:
a) Strip approximately 0.19 in. (5 mm) of insulation from the P1 plug end of each wire.
b) Dress and tin the bare wire ends to prevent the strands from fraying during terminal crimping
operations.
3) Prepare the switch block end of each wire in accordance with the switch block manufacturer’s written
instructions.
4) Crimp contact pins 151-2101 onto the plug end of each wire.
5) Insert the contact pins into the 150-6502 plug (P1). See Figure 8 ELT/NAV Interface -B Wiring Diagram
on page 40.
6) Feed the wires through strain relief 183-6502. See Figure 10 ELT/NAV Interface -B Wiring Installation on
page 42.
7) Install the strain relief on the P1 plug and tighten the wire clamp.
8) Identify the wires such that the pin locations and switch block terminations correspond to the 24-bit
addresses shown in Figure 8 ELT/NAV Interface -B Wiring Diagram on page 40.
9) Connect the other end of each wire to the switch block in accordance with the switch block
manufacturer’s written instructions.
10) Verify the wiring P1 plug pin locations and block switch positions are correct based on the applicable
24-bit address. See Figure 8 ELT/NAV Interface -B Wiring Diagram on page 40.
11) Support the wiring by clamping or other suitable means, such that the wiring is properly supported and
protected from chaffing and strain. Refer to the aircraft manufacturer’s written instructions or as
described in AC 43.13-1, Chapter 11, § 9 through 12, as applicable.
12) Connect the P1 plug to the ELT/NAV Interface -B.
13) Determine the appropriate binary 24-bit address based on the octal or hexadecimal ID code assigned to
the aircraft. See Figure 11 Octal/Hexadecimal to Binary Conversion on page 43.
14) Set the 24-bit address switch block switches as appropriate for the 24-bit address binary code
determined in the previous step.
15) Test the installation in accordance with SUBTASK 25-69-11-750-002 on page 30.
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
ILLUSTRATED PARTS LIST
TASK 25-69-11-990-801
1. Introduction
SUBTASK 25-69-11-990-001
A. Purpose
1) This illustrated parts list (IPL) illustrates and lists the spare parts, with attaching hardware, applicable to
the ELT/NAV Interface -B.
2) Parts and components not listed herein, are not field replaceable and repairs requiring parts outside the
scope of this manual must be accomplished by the manufacturer.
SUBTASK 25-69-11-990-002
B. IPL Usage Guide
1) If the part number is not known:
a) Find the part in the IPL Figure illustration.
b) Note the item number assigned to the part.
c) Refer to the associated parts list and find the item number in the “Fig # & Item” column.
2) If the part number is known:
a) Refer to the parts list and find the part in the “Part #” column.
b) Note the figure number and item number assigned to the part.
c) Refer to the illustration in the applicable IPL figure to find attaching hardware and related assembly
parts.
3) In cases where multiple item numbers are shown on an illustration for the same item, there is more than
one part number option associated with that item.
TASK 25-69-11-990-802
2. Manufacturer Name and Address
SUBTASK 25-69-11-990-001
A. Ordering Information
1) Approved parts may be ordered from ACR Electronics, or any authorized dealer.
CONTACT INFORMATION
Sales, ACR Electronics, Inc / Artex Products
5757 Ravenswood Rd
Fort Lauderdale, FL 33312-6645, USA
Phone: (954) 981-3333
Fax: (954) 983-5087
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
TASK 25-69-11-990-803
3. Explanation of Detailed Parts List Entries
SUBTASK 25-69-11-990-001
A. Fig # & Item Column
1) The first number at the top of the column is the figure number of the corresponding illustration.
2) The right hand number is the item number in the associated figure.
3) A dash (–) in front of an item means the part is not illustrated.
4) Alpha-variants A through Z (except I and O) are assigned to item numbers, when necessary to identify
added parts, alternate parts, and service bulletin modified parts.
SUBTASK 25-69-11-990-002
B. Part # Column
1) This column contains the manufacturer’s part number for each part.
SUBTASK 25-69-11-990-003
C. Nomenclature Column
1) This column contains descriptive nomenclature for each part, service bulletin numbers affecting the
part, and obsolete part numbers.
2) The indenture system used in the “Nomenclature” column indicates the relationship of one part to
another, as follows:
123
End Item or Major Assembly
ATTACHING PARTS
Attaching Parts for End Item or Major Assembly
***
. Detail Parts for End Item or Major Assembly
. Subassemblies
ATTACHING PARTS
. Attaching Parts for Subassemblies
***
. . Detail Parts for Subassemblies
ATTACHING PARTS
. . Attaching Parts for Detail Parts
***
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
3) Assemblies, subassemblies, and detail parts subject to modification, deletion, addition, or replacement
by an issued service bulletin, are annotated to indicate both pre- and post-service bulletin
configurations. The term (PRE SB XXXX) in the “Nomenclature” column designates the original
configuration, and the term (POST SB XXXX) identifies assemblies and parts after the modification has
been completed.
4) The terms defined below are used when applicable to indicate the interchangeability of parts.
TERM
ABBREVIATION
DEFINITION
Alternate
ALT
The listed part is alternate to, and interchangeable
with, other parts within the same item number
variant group or other item numbers if designated.
Superceded By
SUPSD BY
The part is replaced by and is not interchangeable
with the item number designated in the notation.
Supersedes
SUPSDS
The part replaces and is not interchangeable with
the item number designated in the notation.
Replaced By
REPLD BY
The part is replaced by and is interchangeable with
the item number designated in the notation.
Replaces
REPLS
The part replaces and is interchangeable with the
item number designated in the notation.
SUBTASK 25-69-11-990-004
D. UPA (Units Per Assembly) Column
1) The quantity shown in this column represents the units required for one next higher assembly or, when
referring to attaching parts, the quantity to attach one such item.
2) The abbreviation RF (reference) indicates the end item assembly is listed for reference purposes.
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
TASK 25-69-11-990-804
4. Detailed Parts List
Figure 12 ELT/NAV Interface -B Installation
FIG #
ITEM
PART #
12
01
453-6501
1234 NOMENCLATURE
Main Assembly, ELT/NAV Interface -B
UPA
1
ATTACHING PARTS
02
201-0810
Screw, PHP 8-32 x 5/8” SS
6
03
246-0008
Washer, Flat 1/2” SS #8
6
04
247-0800
Washer, Lock Internal Tooth SS #8
6
05
241-0832
Nut, 8-32 x 1/4” Hex SS
6
***
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ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
-B (453-6501)
Figure 13 Electrical Components
FIG #
ITEM
PART #
13
01
150-6503
1234 NOMENCLATURE
Connector, #16 Circular (24-Position)
UPA
1
***
02
151-2100
. Contact, Socket #20
26
03
183-6503
Strain Relief, #16
1
***
04
150-6502
Connector, #18 Circular (31-Position)
1
***
05
151-2101
. Contact Pin, #20
33
06
183-6502
Strain Relief, #18
1
***
–
151-2102
. Plug, Sealing #20
42
***
–
150-6504
Protective Cap, 31-Position Connector
1
***
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