ELT/NAV INTERFACE
Description, Operation, Installation and Maintenance Manual
This manual includes data for the equipment that follows:
Component
ELT/NAV Interface 453-6500 N/A
Part No. Model No.
ARTEX PRODUCTS / ACR ELECTRONICS, INC.
5757 Ravenswood Rd, Ft. Lauderdale, FL 33312
25-69-10
Cage Code: 60253
Page 1 of 58
APR 30/12
570-4602 Rev. H
Initial Issue FEB 10/1998
ARTEX PRODUCTS / ACR ELECTRONICS, INC.
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
453-6500
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, Inc. 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, Inc. makes
no warranty with regard to the documentation or data contained herein. ACR Electronics, Inc. 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, Inc. 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, Inc.
5757 Ravenswood Rd, Fort Lauderdale, FL 33312. Telephone (954) 981-3333
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RECORD OF REVISIONS
REV NO. DCN NO. DCN DATE REV NO. DCN NO. DCN DATE
- RELEASE Feb 10/1998
A ECO 811 Apr/24/1998
B ECO 887 Jul 23/1998
B ECO 948 Oct 14/1998
C ECO 1167 Oct 15/1999
D ECO 1394 May 15/2000
D DCN 1748 Jul 19/2001
D DCN 1791 Sep 19/2001
E DCN 1848 Nov 26/2001
E DCN 1968 Apr 12/2002
E DCN 2033 Jun 18/2002
E DCN 2702 Jan 23/2006
F DCA W9414 Apr 06/2010
G ECO 14756 Jul 28/2011
H ECO 15051 Apr 30/2012
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SERVICE BULLETIN LIST
SERVICE
BULLETIN NO
ISSUE
DATE
SUBJECT
MANUAL
REV NO
MANUAL
REV DATE
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LIST OF EFFECTIVE PAGES
SUBJECT PAGE DATE SUBJECT PAGE DATE
Title Page 1 Apr 30/12 30 Apr 30/12
Notices 2 Apr 30/12 Test and Fault Isolation 31 Apr 30/12
Record of Revisions 3 Apr 30/12 32 Apr 30/12
4 BLANK 33 Apr 30/12
Service Bulletin List 5 Apr 30/12 34 Apr 30/12
6 BLANK 35 Apr 30/12
List of Effective Pages 7 Apr 30/12 36 Apr 30/12
8 BLANK 37 Apr 30/12
Table of Contents 9 Apr 30/12 38 Apr 30/12
10 Apr 30/12 Removal 39 Apr 30/12
11 Apr 30/12 40 Apr 30/12
12 BLANK Installation 41 Apr 30/12
List of Figures 13 Apr 30/12 42 Apr 30/12
14 BLANK 43 Apr 30/12
Introduction 15 Apr 30/12 44 Apr 30/12
16 Apr 30/12 45 Apr 30/12
17 Apr 30/12 46 Apr 30/12
18 Apr 30/12 47 Apr 30/12
19 Apr 30/12 48 Apr 30/12
20 Apr 30/12 49 Apr 30/12
21 Apr 30/12 50 Apr 30/12
22 Apr 30/12 51 Apr 30/12
Description and Operation 23 Apr 30/12 52 BLANK
24 Apr 30/12 Illustrated Parts List 53 Apr 30/12
25 Apr 30/12 54 Apr 30/12
26 Apr 30/12 55 Apr 30/12
27 Apr 30/12 56 Apr 30/12
28 Apr 30/12 57 Apr 30/12
29 Apr 30/12 58 Apr 30/12
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TABLE OF CONTENTS
RECORD OF REVISIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
SERVICE BULLETIN LIST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
LIST OF EFFECTIVE PAGES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
LIST OF FIGURES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
INTRODUCTION
1. Manual Usage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
B. Application . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
2. Model Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
A. ELT/NAV Interface. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
B. Compatibility. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
Table 1. ELT Compatibility List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
3. Approvals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
A. Certification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
B. RTCA DO-160C Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
Table 2. Environmental Categories Breakdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
4. List of Acronyms, Abbreviations, and Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
5. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
A. Regulatory Documents. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
B. Other Documents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
DESCRIPTION AND OPERATION
1. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
A. Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
B. Physical Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
C. Position Data Functionality . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
D. 24-Bit Address Reprogramming Functionality . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
2. Navigation System Interface Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
A. ARINC 429 Latitude and Longitude Data Input . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
B. RS-232 Latitude and Longitude Data Input. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
3. Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
A. Position Data Processing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
B. 24-Bit Address Reprogramming. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
4. Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
A. Physical and Environmental . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
Table 3. Physical and Environmental Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
B. Input/Output. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
Table 4. Input/Output Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
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C. Electrical . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
Table 5. Electrical Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
TEST AND FAULT ISOLATION
1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
A. Applicability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
B. Regulatory Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
2. Periodic Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
A. Inspection Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
3. Periodic Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
A. Position Data ELT Self-Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
4. Post-Installation Functional Testing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
B. Position Data Verification Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
C. 24-Bit Address Reprogramming Verification Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36
5. Post-Reprogramming Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
A. 15-Digit Hex ID Verification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
6. Fault Isolation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38
A. Troubleshooting Guidelines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38
Table 6. Troubleshooting Guide . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38
REMOVAL
1. ELT/NAV Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39
A. Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39
2. Material or Equipment Return . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40
A. Shipment Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40
B. Return Material Authorization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40
INSTALLATION
1. Regulatory Requirements and Guidelines. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
A. Applicability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
B. TSO C126, Paragraph D . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
C. FAA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
D. Canada . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
E. Other Countries. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
F. RTCA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42
2. Mechanical . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
A. Chassis Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
B. Chassis Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
3. Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45
A. General Considerations and Recommendations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45
B. ELT and Navigation System Interfaces. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
C. 24-Bit Address Reprogramming – Hard Wire Method. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49
D. 24-Bit Address Reprogramming – Switch Block Method . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50
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ILLUSTRATED PARTS LIST
1. Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53
A. Purpose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53
B. IPL Usage Guide . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53
2. Manufacturer Name and Address . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54
A. Ordering Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54
3. Explanation of Detailed Parts List Entries . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55
A. Fig # & Item Column . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55
B. Part # Column. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55
C. Nomenclature Column . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55
D. UPA (Units Per Assembly) Column . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56
4. Detailed Parts List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57
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LIST OF FIGURES
Figure 1. ELT/NAV Interface System Integration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
Figure 2. ELT/NAV Interface Isometric View . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
Figure 3. Examples of Location Protocol 406 MHz Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
Figure 4. 406 MHz Location Message without Position Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
Figure 5. ELT/NAV Interface Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39
Figure 6. ELT/NAV Interface Outline and Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
Figure 7. ELT/NAV Interface Mechanical Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44
Figure 8. ELT/NAV Interface Wiring Diagram. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
Figure 9. Wiring Installation at ELT End . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47
Figure 10. ELT/NAV Interface Wiring Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48
Figure 11. Octal/Hexadecimal to Binary Conversion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49
Illustrated Parts List
Figure 12. ELT/NAV Interface Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57
Figure 13. Electrical Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58
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TASK 25-69-10-990-801
1. Manual Usage
SUBTASK 25-69-10-990-001
A. General
(1) This manual describes the operation, installation, and maintenance of the ELT/NAV Interface.
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.acrartex.com
this manual.
(2) Web links provided in this manual were accurate at time of printing but may be subject to
change.
453-6500
INTRODUCTION
for the latest information and any updates to
(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 25-69-10-990-002
B. Application
(1) This manual constitutes supporting data/documentation for the ELT/NAV Interface, including:
(a) Description and Operation
(b) Test and Fault Isolation (includes inspection criteria)
(c) Removal
(d) Installation
(e) Illustrated Parts List
(2) In the United States, the ELT/NAV Interface 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.
(3) In Canada, the ELT/NAV Interface 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.
(4) ELT/NAV Interface installation and maintenance in all other countries must comply with the
requirements herein and applicable national airworthiness requirements.
(5) To ensure proper operation, only parts listed in the Illustrated Parts List of this manual or
those recommended by ACR Electronics, Inc. may be used as replacement parts for the ELT/
NAV Interface.
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2. Model Description
SUBTASK 25-69-10-990-001
A. ELT/NAV Interface
(1) The ELT/NAV Interface provides the means to transmit position data received from the aircraft
navigation system to the ELT.
(2) The ELT/NAV Interface is available in two installation configurations:
(a) 24-bit auto reprogramming and position data, or
(b) Position data only.
SUBTASK 25-69-10-990-002
B. Compatibility
453-6500
(1) Table 1 lists the ELTs compatible with the ELT/NAV Interface.
Table 1. ELT Compatibility List
ELT MODEL
NUMBER
110-406 NAV* 453-0421
110-406HM NAV* 453-0422
110-406ED NAV* 453-0424
B406-2* 453-0003
C406-1 453-5002
C406-1HM 453-5003
C406-2 453-5000
C406-2HM 453-5001
B406-4 453-5004
G406-4 453-5012
PART NUMBER
G406-1* 453-5100
G406-2* 453-5102
*Discontinued Product
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3. Approvals
SUBTASK 25-69-10-990-001
A. Certification
(1) FAA TSO C126 System Component
NOTE
: Details of TSO certification for the ELT/NAV Interface are available in the “TSO
Qualification Test Report for the ELT/NAV Interface System” (Document 6288).
(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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SUBTASK 25-69-10-990-002
B. RTCA DO-160C Compliance
(1) DO-160C Environmental Categories: C1-204A204204XRXXXXXBABA204BXXX
(2) A breakdown of the DO-160C environmental categories is provided in Table 2.
Table 2. Environmental Categories Breakdown
CATEGORY SECTION DESCRIPTION
C1 4.0 Temperature/Altitude
- 4.5.4 In-Flight Loss of Cooling
204 5.0 Temperature Variation
A6.0 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
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CATEGORY SECTION DESCRIPTION
X 15.0 Magnetic Effect
B 16.0 Power Input
A 17.0 Voltage Spike
B 18.0 Audio Frequency Susceptibility
A 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
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4. List of Acronyms, Abbreviations, and Definitions
SUBTASK 25-69-10-990-001
Term
AC Advisory Circular – A Federal Aviation Administration (USA) bulletin
AWG American Wire Gauge – An electrical wire diameter standard. Look for
CAR Canadian Aviation Regulations – The rules and regulations governing
CFR Code of Federal Regulations – The general and permanent rules pub-
COSPAS-SARSAT The international search and rescue consortium that governs the
DER Designated Engineering Representative – An individual qualified and
Definition
with special information. For the purposes of this document, the acronym AC does not refer to electrical alternating current.
this acronym in front of or following a wire size number.
the manufacture, certification, operation, maintenance, and alteration
of aircraft in Canada.
lished in the Federal Register by the executive departments and
agencies of the Federal Government. Title 14, “Aeronautics and
Space” contains the FARs.
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 by the FAA to approve, or recommend approval, of technical data to the FAA.
DRIP LOOP 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.
ELT 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.
EMI 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.
EUROCAE European Organization for Civil Aviation Equipment – EUROCAE docu-
ments are widely referenced as a means of compliance to European
Technical Standard Orders (ETSOs) and other regulatory documents.
FAA Federal Aviation Administration – The United States government
agency for aircraft safety and regulation.
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FAR Federal Aviation Regulations – The rules and regulations governing
the manufacture, certification, operation, maintenance, repair, and
alteration of aircraft in the United States.
FORM 337 FAA Form 337 is required anytime a major repair and/or major altera-
tion 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.
FSDO Flight Standards District Office – FAA district offices responsible for
aircraft certification, operation, maintenance, and modification issues,
approvals and enforcement.
MIL The three-letter acronym that stands for “Military” and proceeds mili-
tary specifications and standards numbers (e.g., MIL-W-xxxx would
indicate a wire specification and MIL-STD-xxxx would indicate a standard).
P/N Part Number – Refers to an ACR Electronics, Inc. part number, unless
otherwise noted. Part numbers are also indicated with parentheses
(e.g., XXX-XXXX).
PLUG The term “Plug”, within the context of this document, refers to the
male half of an electrical connector.
RECEPTACLE The term “Receptacle”, within the context of this document, refers to
the female half of an electrical connector.
RTCA Radio Technical Commission for Aeronautics – Organization that
makes recommendations for airworthiness. Refer to http://
www.rtca.org/aboutrtca.asp for more information.
SAR Search and Rescue
TSO Technical Standard Order – A TSO is a minimum performance stan-
dard issued by the FAA for specified materials, parts, processes, and
appliances used on civil aircraft.
UTC 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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5. References
SUBTASK 25-69-10-990-001
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”
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(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”
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(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)”
SUBTASK 25-69-10-990-002
B. Other Documents
(1) The following documents are available on-line at the Artex products web site at
www.acrartex.com
(a) 570-1000, “ELT Test Set (ETS) Operation Manual”
(b) 6288, “TSO Qualification Test Report for the ELT/NAV Interface System”
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, or from ACR Electronics, Inc. upon request.
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1. Description
SUBTASK 25-69-10-870-001
A. Overview
(1) The ELT/NAV Interface is integrated into the ELT system. See "Figure 1. ELT/NAV Interface
System Integration".
ELT/NAV
INTERFACE
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DESCRIPTION AND OPERATION
PROTECTIVE TOP
COVER (REF.)
TO
ANTENNA (REF.)
NOTE: DUAL OUTPUT FOR
ANTENNA SHOWN, SINGLE
INPUT SIMILAR
REMOTE SWITCH (REF.)
MOUNTING
TRAY (REF.)
OPTIONAL 24-BIT ADDRESS WIRING
ARINC 429/RS-232 INPUT FROM NAVIGATION SYSTEM
AIRCRAFT POWER
ELT (REF.)
Figure 1. ELT/NAV Interface System Integration
(2) The ELT/NAV Interface is designed to work with “ELT with 24-bit Address” and “ELT with
Serial Number” location protocols. In both cases, the ELT/NAV Interface 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
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
reprogramming receptacle (P1) is capped and the unit only provides position data to the
ELT.
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B. Physical Description
(1) The ELT/NAV Interface 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 Isometric View".
Figure 2. ELT/NAV Interface Isometric View
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SUBTASK 25-69-10-870-003
C. Position Data Functionality
(1) The ELT/NAV Interface receives position coordinates (latitude and longitude) from the aircraft
onboard navigation system.
(2) The ELT/NAV Interface is capable of receiving data from the aircraft navigation system via the
following protocols:
(a) ARINC 429 - See SUBTASK 25-69-10-870-001, on page 26, for requirements.
(b) RS-232 - See SUBTASK 25-69-10-870-002, on page 26, for requirements.
(3) The ELT/NAV Interface 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.
(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 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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D. 24-Bit Address Reprogramming Functionality
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CAUTION
(1) The ELT/NAV Interface provides the means to reprogram ELTs with 24-bit address location
(2) This capability facilitates swapping ELTs from one aircraft to another when performing routine
(3) If the ELT is not programmed with a 24-bit address location protocol, the ELT/NAV Interface
: 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.
protocol programming.
maintenance, etc., without losing a significant amount of time reprogramming ELTs.
will not reprogram the ELT.
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TASK 25-69-10-870-802
2. Navigation System Interface Requirements
SUBTASK 25-69-10-870-001
A. ARINC 429 Latitude and Longitude Data Input
(1) The ELT/NAV Interface 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 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.
SUBTASK 25-69-10-870-002
B. RS-232 Latitude and Longitude Data Input
CAUTION
(1) For navigation systems that output only RS-232, the ELT/NAV Interface accepts the following
(2) The RS-232 format must have:
: DO NOT CONNECT ARINC 429 AND RS-232 INPUTS AT THE SAME TIME.
RS-232 format only.
(a) Baud Rate (fixed): 9600
(b) Parity: None
(c) Data Bits: 8
(d) Stop Bits: 1
(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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3. Operation
SUBTASK 25-69-10-870-001
A. Position Data Processing
(1) Operation of ELT/NAV Interface 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) The following conditions must be true for ELT/NAV Interface 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.
453-6500
(3) Once the ELT is activated, it stops receiving position data; however, the ELT/NAV Interface
continues to transmit as long as it has power and is receiving position data.
SUBTASK 25-69-10-870-002
B. 24-Bit Address Reprogramming
(1) Operation of the ELT/NAV Interface 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, it reads the ELT 24-bit address
data and compares it to the 24-bit address data hard wired to the ELT/NAV Interface.
(3) If a difference in 24-bit address programming is found, the ELT/NAV Interface 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 takes no action.
(5) If the ELT is programmed with a protocol other than 24-bit address, the ELT/NAV Interface
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 and the ELT is
programmed with a protocol other than 24-bit address, an error will be displayed by the
ELT and remote switch LEDs.
(b) See SUBTASK 25-69-10-750-002, on page 36, and Table 6, on page 38.
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4. Specifications
SUBTASK 25-69-10-870-001
A. Physical and Environmental
(1) Table 3 lists the ELT/NAV Interface physical and environmental specifications.
Table 3. Physical and Environmental Specifications
PARAMETER CHARACTERISTIC
Temperature (Storage) -55° C to +85° C
Temperature (Operating) -20° C to +55° C
Altitude 55,000 ft (16,764 m)
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Vibration 10
Shock 500
Crashworthiness 100
Humidity 95% for 50 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)
g
from 5 Hz to 2,000 Hz
g
for 4 ms
g
for 23 ms
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B. Input/Output
(1) Table 4 lists the ELT/NAV Interface input/output specifications.
PIN DESCRIPTION CHARACTERISTIC
453-6500
Table 4. Input/Output Specifications
P2-1 Power Input
P2-2 5.6 VDC Output
P2-3
P2-4
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
ARINC 429-A Input
(Auto Speed Select)
ARINC 429-B Input
(Auto Speed Select)
+28 VDC ±5 VDC
300 mA max.
Vmax = 6.0 VDC
Vmin = 5.3 VDC
High/Low
Standard or GAMA
High/Low
Standard or GAMA
Ground =1
Open = 0
P1-25 and 26 24-bit Address Return 24-bit Ground
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C. Electrical
(1) Table 5 lists the ELT/NAV Interface electrical specifications.
PARAMETER CHARACTERISTIC
Power Input Per RTCA/DO-160C
Voltage Spike Per RTCA/DO-160C
Audio Frequency Susceptibility Per RTCA/DO-160C
Induced Signal Susceptibility Per RTCA/DO-160C
Radio Frequency Susceptibility Per RTCA/DO-160C and DO-204
Emission of RF Energy Per RTCA/DO-160C
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Table 5. Electrical Specifications
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1. General
SUBTASK 25-69-10-990-001
A. Applicability
(1) This section only covers inspection, testing, and fault isolation procedures specific to the ELT/
NAV Interface.
(2) Refer to the applicable ELT abbreviated component maintenance manual associated with the
ELT/NAV Interface to coordinate the requirements herein with the requirements for
inspection, test, and fault isolation of the ELT system as a whole.
SUBTASK 25-69-10-990-002
453-6500
TEST AND FAULT ISOLATION
B. Regulatory Requirements
(1) The ELT/NAV Interface 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 for references to the regulatory requirements.
(3) Inspection and testing of the ELT/NAV Interface must be accomplished in conjunction with
and on the same schedule as the ELT and other system components.
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2. Periodic Inspection
SUBTASK 25-69-10-220-001
A. Inspection Procedures
(1) Remove the ELT/NAV Interface in accordance with SUBTASK 25-69-10-050-001, on page 39.
(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.
453-6500
(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 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 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 in accordance with SUBTASK 25-69-10-450-002, on page 43.
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3. Periodic Testing
SUBTASK 25-69-10-750-001
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 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.
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(b) Turn on the aircraft navigation system and verify it is receiving valid position data.
(c) Verify the ELT/NAV Interface 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 cockpit remote switch in the “ON” position. The 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 cockpit remote switch to the “ARM” (OFF) position while paying close
attention to LED activity when the ELT enters the “ARM” condition. If the ELT is working
properly, the LED will stay on for approximately 1 second and then turn off.
(i) Refer to Table 6, on page 38, 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 25-69-10-750-001, on page 34.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
TASK 25-69-10-750-804
4. Post-Installation Functional Testing
SUBTASK 25-69-10-990-001
A. General
453-6500
CAUTION
(1) This task consists of three subtask testing requirements:
SUBTASK 25-69-10-750-001
B. Position Data Verification Test
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.
(a) A position data test, which verifies ELT/NAV Interface position data functionality by
reading and validating position data broadcast by the ELT.
(b) 24-bit address programming test, which verifies ELT/NAV Interface 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.
: 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 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 control switch or remote switch in the “ON” position.
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453-6500
(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.
(2) Message examples are shown in "Figure 3. Examples of Location Protocol 406 MHz Messages".
Sarsat Beacon Reader
Beacon ID = 2DC843B2F2574FF
Message Type = Test, Long
Country = 366 USA
Aviation ELT S/N = 6521
Type Approval # = 112
Position = N43º 30’ 0”
W63º 45’ 0”
Position Source = External
121.5 MHz Beacon = Yes
Nov 13, 2009 11:39 am 55 sec
ClearDonePrint
Sarsat Beacon Reader
Beacon ID = 2DC741E1E8574FF
Message Type = Test, Long
Country = 366 USA
A/C ICAO Addr = 50170364N16SQ
Position = N43º 30’ 0”
W63º 45’ 0”
Position Source = External
121.5 MHz Beacon = Yes
Nov 15, 2009 10:06 am 25 sec
ClearDonePrint
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 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"
Sarsat Beacon Reader
Beacon ID = 2DC75B534AFFBFF
Message Type = Test, Long
Country = 366 USA
A/C ICAO Addr = 50170364N16SQ
Position = Invalid
Position Source = External
121.5 MHz Beacon = Yes
Nov 15, 2009 10:06 am 25 sec
ClearDonePrint
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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453-6500
SUBTASK 25-69-10-750-002
C. 24-Bit Address Reprogramming Verification Test
This test procedure verifies the ELT/NAV Interface has updated the aircraft 24-bit address ID in the
ELT programming.
(1) Apply power to the ELT/NAV Interface, 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 LEDs on the ELT and remote switch will begin to flash rapidly if reprogramming was
NOT successful. See Table 6, on page 38, for troubleshooting guidelines.
(b) If the LEDs remain off after two minutes, the ELT has been reprogrammed. Proceed to
SUBTASK 25-69-10-750-001, on page 37.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
TASK 25-69-10-750-805
5. Post-Reprogramming Check
SUBTASK 25-69-10-750-001
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 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)
453-6500
(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 control switch or remote 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 35.
(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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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
TASK 25-69-10-810-801
6. Fault Isolation
SUBTASK 25-69-10-810-001
A. Troubleshooting Guidelines
(1) Table 6 provides ELT troubleshooting guidelines for installation and operational issues.
SYMPTOM PROBABLE CAUSE POSSIBLE SOLUTION
ELT and remote switch LED
display 5-flash error
(No navigation data present)
453-6500
Table 6. Troubleshooting Guide
Aircraft navigation system off Turn on navigation system
Turn on power
No power to ELT/NAV Interface
Faulty interface wiring or
connections
Check breaker/fuse
Check for frayed insulation
causing short or ground
Verify integrity of all crimp and
solder connections
ELT and remote switch LED flash
rapidly within two minutes after
ELT/NAV Interface power up
(24-bit address not accepted)
ELT not programmed for 24-bit
address location protocol
Faulty interface wiring or
connections
Check wiring continuity and
repair as necessary
Program ELT with 24-bit address
location protocol
Check for frayed insulation
causing short or ground
Verify integrity of all crimp and
solder connections
Check wiring continuity and
repair as necessary
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
TASK 25-69-10-050-801
1. ELT/NAV Interface
SUBTASK 25-69-10-050-001
A. Removal
(1) See "Figure 5. ELT/NAV Interface Removal".
(2) Disconnect ELT/NAV Interface plugs:
(a) P2, and
(b) P1, if installed.
(3) Install connector covers to protect the ELT/NAV Interface receptacles.
453-6500
REMOVAL
(4) Remove the screws attaching the ELT/NAV interface to the mounting structure.
ELT (REF.)
REMOVE SCREWS
(6 PLCS)
MOUNTING
STRUCTURE
(REF.)
3
REMOVE P1, IF INSTALLED
2
NOTE: CABLES AND PLUGS
ELT/NAV
INTERFACE
NOT SHOWN FOR CLARITY.
1
REMOVE P2
Figure 5. ELT/NAV Interface Removal
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
TASK 25-69-10-500-801
2. Material or Equipment Return
SUBTASK 25-69-10-510-001
A. Shipment Information
(1) If any material or equipment is to be returned to the factory, under warranty or otherwise,
ACR Electronics, Inc. must be notified prior to shipment with the following information:
• Model and serial number of equipment being returned,
• Date purchased,
• Date placed in service,
• Number of hours in service,
• Nature and cause of failure, and
• Remarks, if any.
453-6500
SUBTASK 25-69-10-580-001
B. Return Material Authorization
(1) Upon receipt of such notice, Wulfsberg Electronics will issue a Return Material Authorization
(RMA) number which then authorizes return of the material or equipment to the following
address:
(a) Failure to obtain a RMA number and provide the details listed in SUBTASK 25-69-10-510-
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.
Repair and Overhaul
ACR Electronics, Inc.
5757 Ravenswood Road
Fort Lauderdale, FL 33312
Phone: (954) 981-3333
Fax: (954) 983-5087
(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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453-6500
INSTALLATION
TASK 25-69-10-450-801
1. Regulatory Requirements and Guidelines
SUBTASK 25-69-10-990-001
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 and must be applied to the
ELT/NAV Interface. Where the word “ELT” is used in the following subtasks, read “ELT/NAV
Interface”.
SUBTASK 25-69-10-990-002
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 25-69-10-990-003
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 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 25-69-10-990-004
D. Canada
(1) All installations must be performed in accordance with Canadian Aviation Regulations (CAR)
Part V, Subparts 37, 51, and 71.
SUBTASK 25-69-10-990-005
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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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
SUBTASK 25-69-10-990-006
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
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.
453-6500
g
load, (ELT weight x 100, ELT antenna weight x
(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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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
TASK 25-69-10-450-802
2. Mechanical
SUBTASK 25-69-10-450-001
A. Chassis Location
453-6500
CAUTION
: AVOID LOCATING THE ELT/NAV INTERFACE 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 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 chassis and ELT are mounted to the same support structure in most
installations.
SUBTASK 25-69-10-450-002
B. Chassis Installation
(1) Coordinate ELT/NAV Interface chassis installation with ELT installation whenever possible. If
the ELT/NAV Interface is an add-on to an existing ELT installation, extend/modify the existing
ELT support structure to accommodate the ELT/NAV Interface.
(2) See "Figure 6. ELT/NAV Interface Outline and Dimensions".
2.00
P2
(51)
5.00
(127)
2.00
P1
(51)
Ø 0.187 (4.7)
±0.005 (0.13)
(6 PLCS)
2.75
(70)
0.25
(6)
1.88
(48)
453-6500
8.30 (211)
8.90 (226)
9.25 (235)
9.57 (243)
5.27 (134)
Dimensions in inches (mm) - Tolerances ±0.020 (0.5) except as noted
Figure 6. ELT/NAV Interface Outline and Dimensions
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1.15
(29)
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(3) Align the ELT/NAV Interface 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 Outline and Dimensions”, on page 43.
(5) Drill the six mounting holes with a #19 or 4.25 mm drill.
(6) Install the ELT/NAV Interface chassis with the 8-32 x 5/8” SS pan head phillips screws, flat
washers, lock washers, and nuts provided in the installation kit (455-6500), as shown in
"Figure 7. ELT/NAV Interface 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).
ELT (REF.)
SCREWS
(6 PLCS)
MOUNTING
STRUCTURE
(REF.)
ELT/NAV
INTERFACE
FLAT WASHER (6 PLCS)
LOCK WASHER (6 PLCS)
HEX NUT (6 PLCS)
Figure 7. ELT/NAV Interface Mechanical Installation
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453-6500
TASK 25-69-10-450-803
3. Wiring
SUBTASK 25-69-10-990-001
A. General Considerations and Recommendations
CAUTION
CAUTION
(1) The following wiring and grounding considerations and recommendations are applicable:
(2) Maximum interface and data line wire lengths are:
: IF GROUND OR OTHER CONNECTIONS ARE BROKEN OR OTHERWISE DAMAGED, THE
ELT IS STILL CAPABLE OF AUTOMATIC ACTIVATION; HOWEVER, ELT/NAV INTERFACE
OPERATION MAY BE AFFECTED AND POSITION DATA MAY NOT BE TRANSMITTED TO
THE ELT.
: INCORRECT TERMINATION OF THE WIRING IN THE CONNECTORS MAY DAMAGE THE
ELT/NAV INTERFACE. VERIFY THE WIRING AGAINST THE WIRING DIAGRAM AND
PERFORM A CONTINUITY CHECK TO CONFIRM GOOD CONNECTIONS AND PROPER
PIN LOCATIONS.
(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 plug and ELT receptacle to divert
moisture from the connections. See SUBTASK 25-69-10-990-001, on page 19, for a
definition.
(e) All grounds must be common to aircraft ground.
(a) Interface Harness - 3 feet (0.9 m)
(b) ARINC 429 - 360 feet (110 m)
NOTE
: Ground shield at every break. ELT/NAV Interface 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
and wiring must not exceed 3 feet (0.9 m) including strain relief.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
SUBTASK 25-69-10-450-001
B. ELT and Navigation System Interfaces
453-6500
CAUTION
: DO NOT CONNECT THE ELT/NAV INTERFACE 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 Wiring Diagram".
MSB
3
24-BIT ADDRESS
LSB
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
(BINARY)
17
18
19
20
21
22
23
24
25
26
ADD 1
ADD 2
ADD 3
ADD 4
ADD 5
ADD 6
ADD 7
ADD 8
ADD 9
ADD 10
ADD 11
ADD 12
ADD 13
ADD 14
ADD 15
ADD 16
ADD 17
ADD 18
ADD 19
ADD 20
ADD 21
ADD 22
ADD 23
ADD 24
GND
GND
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
2
2
9
10
12
P1
USE MINIMUM 22 AWG WIRE
P2
1
ELT/NAV INTERFACE
1
2
3
+28 VDC
3
ARINC 429 - A
4
ARINC 429 - B
5
NOT USED
6
NOT USED
7
NOT USED
8
RS-232 RX
11
SWITCHABLE POWER SOURCE WITH 2-AMP BREAKER OR
SLO-BLO FUSE.
P1 CAPPED IF NOT IN USE.
USED ONLY WITH 24-BIT ADDRESS LOCATION PROTOCOLS.
10
9
12
11
SEE APPLICABLE ELT
WIRING DIAGRAM
2 4 1 3 6 7 5 8
+5.6 VDC
RXDB
TXDB
GND
ELT
1
FROM ARINC 429
(STANDARD OR GAMA
HIGH OR LOW SPEED)
AIRCRAFT
GROUND (TYP.)
1
20
ELT/NAV INTERFACE MATING PLUG
10
P2
(24-POSITION)
PIN INSERTION VIEW
1
P1
24-BIT ADDRESS PLUG
(31-POSITION)
PIN INSERTION VIEW
13
24
20
30
Figure 8. ELT/NAV Interface Wiring Diagram
(2) Fabricate a shielded 4-wire harness long enough to reach between the ELT/NAV Interface 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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(4) Fabricate a ground wire of sufficient length to reach from the ELT/NAV Interface 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 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 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 Wiring Diagram”, on page 46.
NOTE
: Terminal pins may be removed from the receptacle using Molex extraction tool
11030002, or equivalent.
MOUNTING
FRAME CAP
MOLEX PLUG
(REF.)
PIN 12
PIN 10
PIN 1PIN 3
(REF.)
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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(11) Feed the interface wires at the ELT/NAV Interface end through the 183-6503 strain relief. See
"Figure 10. ELT/NAV Interface Wiring Installation".
P1 #18 31-PIN PLUG
CONTACT PINS
#18 STRAIN RELIEF
P2 #16 24-PIN PLUG
CONTACT SOCKETS
#16 STRAIN RELIEF
Figure 10. ELT/NAV Interface Wiring Installation
(12) Install the following wires at the ELT/NAV Interface 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 Wiring Diagram”, on page 46.
(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 Wiring Diagram”, on page 46.
NOTE
: Keep shield drain as short as possible.
(17) 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.
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(18) Connect the P2 plug to the ELT/NAV Interface.
(19) Install the 150-6504 protective cap on the ELT/NAV Interface P1 plug, if the 24-bit address
reprogramming option is not used.
(20) Test the installation in accordance with the procedure outlined in SUBTASK 25-69-10-750-001,
on page 34.
SUBTASK 25-69-10-450-002
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 25-69-10-450-003, on page 50, 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".
Example No. 1: Converting ICAO address 50134057 (octal) to
binary 24-bit address
ICAO Octal Address to 24-Bit Binary
40575013
101000001011100000101111
MSB
ADDRESS 1
Example No. 2: Converting ICAO address A0B82F (hexadecimal) to
binary 24-bit address
ICAO Hex Address to 24-Bit Binary
A0B82F
101000001011100000101111
MSB
ADDRESS 1
OCTAL/BINARY
EQUIVALENTS
Octal Binary
00 0 0
10 0 1
20 1 0
30 1 1
41 0 0
51 0 1
61 1 0
71 1 1
HEXADECIMAL/BINARY
EQUIVALENTS
Hex
Binary
0 0 0 0
0
0 0 0 1
1
0 0 1 0
2
0 0 1 1
3
0 1 0 0
4
0 1 0 1
5
0 1 1 0
6
0 1 1 1
7
Hex Binary
1 0 0 0
8
1 0 0 1
9
1 0 1 0
A
1 0 1 1
B
1 1 0 0
C
1 1 0 1
D
1 1 1 0
E
1 1 1 1
F
Figure 11. Octal/Hexadecimal to Binary Conversion
LSB
ADDRESS 24
LSB
ADDRESS 24
(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 each end of each of the ground
wire.
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(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 Wiring Diagram”, on page 46.
(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 Wiring Diagram”, on page 46.
(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.
(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 Wiring Installation”, on page 48.
(11) Connect the P1 plug to the ELT/NAV Interface.
(12) Test the installation in accordance with SUBTASK 25-69-10-750-002, on page 36.
SUBTASK 25-69-10-450-003
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
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 Wiring
Diagram”, on page 46.
(6) Feed the wires through strain relief 183-6502. See "Figure 10. ELT/NAV Interface Wiring
Installation”, on page 48.
(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 Wiring Diagram”, on page 46.
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(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 Wiring Diagram”, on page 46.
(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.
(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 49.
(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 25-69-10-750-002, on page 36.
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THIS IS A BLANK PAGE
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TASK 25-69-10-990-801
1. Introduction
SUBTASK 25-69-10-990-001
A. Purpose
(1) This illustrated parts list (IPL) illustrates and lists the spare parts, with attaching hardware,
applicable to the ELT/NAV Interface.
(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 25-69-10-990-002
B. IPL Usage Guide
453-6500
ILLUSTRATED PARTS LIST
(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.
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2. Manufacturer Name and Address
SUBTASK 25-69-10-990-001
A. Ordering Information
(1) Approved parts may be ordered from ACR Electronics, or any authorized dealer.
CONTACT INFORMATION
Sales, Artex Products / ACR Electronics, Inc.
Fort Lauderdale, FL 33312-6645, USA
Phone: (954) 981-3333
453-6500
5757 Ravenswood Rd
Fax: (954) 983-5087
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TASK 25-69-10-990-803
3. Explanation of Detailed Parts List Entries
SUBTASK 25-69-10-990-001
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 25-69-10-990-002
B. Part # Column
(1) This column contains the manufacturer’s part number for each part.
SUBTASK 25-69-10-990-003
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:
1 2 3
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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(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 postservice 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
The listed part is alternate to, and interchangeable
Alternate ALT
with, other parts within the same item number
variant group or other item numbers if
designated.
Superceded By SUPSD BY
Supersedes SUPSDS
Replaced By REPLD BY
Replaces REPLS
SUBTASK 25-69-10-990-004
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.
The part is replaced by and is not interchangeable
with the item number designated in the notation.
The part replaces and is not interchangeable with
the item number designated in the notation.
The part is replaced by and is interchangeable
with the item number designated in the notation.
The part replaces and is interchangeable with the
item number designated in the notation.
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4. Detailed Parts List
ARTEX PRODUCTS / ACR ELECTRONICS, INC.
453-6500
Figure 12. ELT/NAV Interface Installation
01
FIG # ITEM PART # 1234 NOMENCLATURE UPA
02
03
04
05
12 01 453-6500 Main Assembly, ELT/NAV Interface 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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Figure 13. Electrical Components
04
05
ELT/NAV
INTERFACE
(REF.)
01
02
03
06
FIG # ITEM PART # 1234 NOMENCLATURE UPA
13 01 150-6503 Connector, #16 Circular (24-Position) 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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