C406-N SERIES
EMERGENCY LOCATOR TRANSMITTER
Description, Operation, Installation And Maintenance Manual
This manual includes data for the equipment that follows:
Component
Emergency Locator Transmitter 453-5060 C406-N
Emergency Locator Transmitter 453-5061 C406-N HM
Part No. Model No.
ACR ELECTRONICS, INC / ARTEX PRODUCTS
5757 Ravenswood Rd, Ft. Lauderdale, FL 33312
25-62-13
Cage Code: 18560
Page 1 of 109
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570-5060 Rev. H
Initial Issue MAY 12/2003
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
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
REV NO. DCN NO. DCN DATE REV NO. DCN NO. DCN DATE
- RELEASE May 12/2003
A DCN 2227 Jul 11/2003
A DCN 2273 Sep 08/2003
B DCN 2380 Mar 22/2004
C DCN 2444 Aug 05/2004
C DCN 2730 Mar 09/2006
C DCN 2870 Oct 05/2006
D DCN 2961 Mar 13/2007
D DCN 2968 Mar 20/2007
E DCA W9414 Apr 06/2010
F ECO 14756 Jul 28/2011
G ECO 15149 Jul 31/2012
H ECO 15329 Mar 1/2013
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THIS IS A BLANK PAGE
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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 Mar 1/13 Description and Operation 30 Jul 31/12
Notices 2 Jul 31/12 (cont.) 31 Jul 31/12
Record of Revisions 3 Jul 31/12 32 Jul 31/12
4 BLANK 33 Jul 31/12
Service Bulletin List 5 Jul 31/12 34 Jul 31/12
6 Jul 31/12 35 Jul 31/12
List of Effective Pages 7 Jul 31/12 36 Jul 31/12
8 Jul 31/12 37 Jul 31/12
Table of Contents 9 Jul 31/12 38 Jul 31/12
10 Jul 31/12 Test and Fault Isolation 39 Jul 31/12
11 Jul 31/12 40 Jul 31/12
12 Jul 31/12 41 Jul 31/12
13 Jul 31/12 42 Jul 31/12
14 BLANK 43 Jul 31/12
List of Figures 15 Jul 31/12 44 Jul 31/12
16 BLANK 45 Jul 31/12
Introduction 17 Jul 31/12 46 Jul 31/12
18 Jul 31/12 47 Jul 31/12
19 Jul 31/12 48 Jul 31/12
20 Jul 31/12 49 Jul 31/12
21 Jul 31/12 50 Jul 31/12
22 Jul 31/12 51 Jul 31/12
23 Jul 31/12 52 Jul 31/12
24 Jul 31/12 Removal 53 Jul 31/12
25 Jul 31/12 54 Jul 31/12
26 Jul 31/12 55 Jul 31/12
27 Jul 31/12 56 BLANK
28 BLANK Installation 57 Jul 31/12
Description and Operation 29 Jul 31/12 58 Jul 31/12
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SUBJECT PAGE DATE SUBJECT PAGE DATE
Installation (cont.) 59 Jul 31/12 Appendix B (cont.) 89 Jul 31/12
60 Jul 31/12 90 BLANK
61 Jul 31/12 Appendix C 91 Jul 31/12
62 Jul 31/12 92 Jul 31/12
63 Jul 31/12 93 Jul 31/12
64 Jul 31/12 94 Jul 31/12
65 Jul 31/12 95 Jul 31/12
66 Jul 31/12 96 Jul 31/12
67 Jul 31/12 97 Jul 31/12
68 Jul 31/12 98 Jul 31/12
69 Jul 31/12 99 Jul 31/12
70 Jul 31/12 100 Jul 31/12
71 Jul 31/12 Illustrated Parts List 101 Jul 31/12
72 Jul 31/12 102 Jul 31/12
73 Jul 31/12 103 Jul 31/12
74 Jul 31/12 104 Jul 31/12
75 Jul 31/12 105 Jul 31/12
76 Jul 31/12 106 Jul 31/12
77 Jul 31/12 107 Jul 31/12
78 Jul 31/12 108 Jul 31/12
79 Jul 31/12 109 Jul 31/12
80 Jul 31/12
81 Jul 31/12
82 Jul 31/12
Appendix A 83 Jul 31/12
84 Mar 1/13
85 Jul 31/12
Appendix B 86 Jul 31/12
87 Mar 1/13
88 Jul 31/12
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TABLE OF CONTENTS
RECORD OF REVISIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
SERVICE BULLETIN LIST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
LIST OF EFFECTIVE PAGES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
LIST OF FIGURES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
INTRODUCTION
1. Manual Usage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
B. Application . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
2. Model Descriptions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
A. C406-N. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
B. C406-N HM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
3. Approvals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
A. C406-N and C406-N HM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
B. Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
C. RTCA DO-160D Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
Table 1. Environmental Categories Breakdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
4. Frequency Allocations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
A. Application . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
B. Discussion. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
5. List of Acronyms, Abbreviations, and Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
6. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
A. Regulatory Documents. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
B. Other Documents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
DESCRIPTION AND OPERATION
1. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
A. Functional Overview. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
B. Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
2. Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
A. Operational Overview. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
B. Normal Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
C. Manual Activation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
D. ELT Reset . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
E. Functional Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
3. Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36
A. Environmental and Physical . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36
Table 2. Environmental and Physical Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36
B. Electrical. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
Table 3. Electrical Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
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C. Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38
Table 4. Antenna Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38
TEST AND FAULT ISOLATION
1. Inspection and Test Regulatory Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39
A. United States . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39
B. Canada . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39
C. Other Countries. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40
2. Inspection and Test Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
A. Checklist. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
Table 5. ELT Inspection and Test Checklist . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
B. Preparation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42
C. Coax Cable and Wiring Connections Inspection – Item 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . 42
D. ELT Mounting Tray and Hardware Inspection – Item 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42
E. Battery Pack Inspection – Item 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42
F. G-Switch Functional Check – Item 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
G. Performance Testing Setup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
H. 121.5 MHz Frequency Measurement – Item 5a. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44
I. Audio Modulation Check – Item 5b . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44
J. 121.5/243.0 MHz Power Output Measurement – Item 5c. . . . . . . . . . . . . . . . . . . . . . . . . . . 45
K. 406 MHz Frequency Measurement – Item 5d . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45
L. 406 MHz Power Output Measurement – Item 5e. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45
M. Current Draw Test – Item 5f . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
N. Digital Message Verification – Item 5g . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47
O. ELT Reset Check – Item 5h . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48
P. Installed Transmitter Test – Item 6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48
Q. Antenna Test – Item 7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49
R. Inspection and Test Documentation – Item 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49
3. Fault Isolation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50
A. Self-Test Error Troubleshooting Guidelines. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50
Table 6. ELT Self-Test Error Codes Troubleshooting Guide. . . . . . . . . . . . . . . . . . . . . . . . . 50
B. ELT Troubleshooting Guidelines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52
Table 7. ELT Troubleshooting Guide . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52
REMOVAL
1. ELT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53
A. ELT Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53
2. Battery. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54
A. Battery Pack Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54
3. Material or Equipment Return . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55
A. Shipment Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55
B. Return Material Authorization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
INSTALLATION
1. Regulatory Requirements and Guidelines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57
A. TSO C126, Paragraph D . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57
B. FAA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57
C. Canada. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57
D. Other Countries . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58
E. RTCA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58
2. Mounting Tray. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59
A. Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59
B. Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60
3. Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62
A. Selection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62
B. Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62
C. Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62
4. Remote Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65
A. Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65
B. Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65
5. Buzzer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66
A. Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66
B. Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66
6. Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 67
A. General Considerations and Recommendations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 67
B. Remote Switch Harness Fabrication. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 67
C. ELT 22-Pin Plug Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72
D. Cockpit Remote Switch 9-Pin Plug Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73
E. Wiring Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73
F. Antenna Connection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74
G. Cockpit Remote Switch Power Connection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74
H. ELT Power Connection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74
I. Airframe Ground Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74
J. Buzzer Connection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74
K. Remote Switch Final Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75
7. ELT Installation and Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76
A. Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76
B. Post-Installation Testing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 77
C. Installation Documentation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 77
8. Battery Pack Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78
A. Battery Reinstallation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78
B. New Battery Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80
9. Helicopter Installations - Special Considerations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81
A. Background. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81
B. Recommendations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81
C. Orientation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82
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APPENDIX A – ELT REGISTRATION
1. Background Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83
A. Hex ID Code . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83
B. Reason for Registration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83
C. Registration Information Resources. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83
2. Registration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84
A. Responsibility . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84
B. Required Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84
C. Where to Register . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84
APPENDIX B – PROGRAMMING ADAPTER OPTION
1. Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85
A. Purpose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85
B. Physical Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85
C. PA Programming . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86
D. Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86
2. Installation and Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87
A. Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87
B. Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88
C. Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 89
D. Aircraft ID Verification Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 89
APPENDIX C – REMOTE SWITCH CONTROL PANEL OPTION
1. Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91
A. Purpose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91
B. Control Panel Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91
C. Modified Buzzer Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92
D. Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92
2. Remote Switch Control Panel Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93
A. Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93
B. Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93
3. Modified Buzzer Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94
A. Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94
B. Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94
4. Wiring and Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95
A. Remote Switch Control Panel Wiring Fabrication. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95
B. Modified Buzzer Wiring Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 97
C. Remote Switch Control Panel Wiring Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 97
D. Modified Buzzer Wiring Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 98
E. Standard Buzzer Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 98
F. Remote Switch Control Panel Final Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 98
G. Remote Switch Control Panel Functional Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .100
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ILLUSTRATED PARTS LIST
1. Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101
A. Purpose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101
B. IPL Usage Guide . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101
2. Manufacturer Name and Address . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102
A. Ordering Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102
3. Explanation of Detailed Parts List Entries . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103
A. Fig # & Item Column . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103
B. Part # Column. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103
C. Nomenclature Column . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103
D. UPA (Units Per Assembly) Column . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104
4. Detailed Parts List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105
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THIS IS A BLANK PAGE
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LIST OF FIGURES
Figure 1. ELT Orthogonal Axes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
Figure 2. C406-N Series ELT and Mounting Frame Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
Figure 3. Cockpit Remote Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
Figure 4. Buzzer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
Figure 5. Battery Pack Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
Figure 6. Rod and Whip Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
Figure 7. Blade Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
Figure 8. ELT Operational Flow Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
Figure 9. Performance Tests Equipment Setup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44
Figure 10. Current Draw Test Setup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
Figure 11. Long 406 MHz Message Example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47
Figure 12. ELT Removal Sequence . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53
Figure 13. Battery Pack Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54
Figure 14. C406-N Series ELT Outline and Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59
Figure 15. Typical Mounting Tray Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60
Figure 16. Rod Antenna 110-338 and Whip Antenna 110-343 Outlines and Dimensions . . . . . . . . . . . . . 63
Figure 17. Blade Antennas 110-340 and 110-341 Outlines and Dimensions . . . . . . . . . . . . . . . . . . . . . . 64
Figure 18. Remote Switch Outline and Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65
Figure 19. Buzzer Outline and Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66
Figure 20. Remote Switch Harness Arrangement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68
Figure 21. Remote Switch Harness Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69
Figure 22. Harness ELT 22-Pin Plug Arrangement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72
Figure 23. ELT Installation Sequence . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76
Figure 24. Battery Pack Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78
Figure 25. Battery Pack Screw Tightening Pattern . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79
Figure 26. ELT Orthogonal Axes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81
Figure 27. Orientation of ELT for Helicopter Installations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82
Figure 28. Programming Adapter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85
Figure 29. Programming Adapter Interface Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87
Figure 30. Programming Adapter Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 89
Figure 31. Remote Switch Control Panel Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91
Figure 32. Cockpit Remote Switch Panel Outline and Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93
Figure 33. Modified Buzzer Outline and Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94
Figure 34. Remote Switch Control Panel Wiring Diagram (130-4005 Modified Buzzer) . . . . . . . . . . . . . . 96
Figure 35. Remote Switch Control Panel Wiring Diagram (130-4004 Buzzer) . . . . . . . . . . . . . . . . . . . . . 99
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Illustrated Parts List
Figure 36. C406-N Series ELT Main Assembly and Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .105
Figure 37. Electrical Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .107
Figure 38. Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .109
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C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-990-801
1. Manual Usage
SUBTASK 25-62-13-990-001
A. General
(1) This manual describes the operation, installation, and maintenance of the Model C406-N
Series emergency locator transmitter (ELT). The 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 for the
latest information and any updates to this manual.
(2) Information on COSPAS-SARSAT emergency locator beacon registration requirements and
procedures is provided in Appendix A – ELT Registration on page 83.
INTRODUCTION
(3) Web links provided in this manual were accurate at time of printing but may be subject to
change.
(4) ACR Electronics reserves the right to add approved components to the ELT system; including,
but not limited to antennas, remote switches, and coaxial cables.
(5) 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 25-62-13-990-002
B. Application
(1) This manual constitutes supporting data/documentation for the C406-N Series ELT, including:
(a) Description and Operation
(b) Test and Fault Isolation (includes inspection criteria)
(c) Removal
(d) Installation
(e) Registration
(f) Illustrated Parts List
(2) In the United States, the C406-N Series ELT 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 C406-N Series ELT must be installed and maintained in accordance with the
requirements herein and Canadian Aviation Regulations (CAR), Part V, Paragraph 551.104 and
other CAR airworthiness requirements, as applicable.
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(4) C406-N Series ELT installation and maintenance in all other countries must comply with the
requirements herein and applicable national airworthiness requirements.
(5) The accessories (i.e., remote switch and antennas) addressed in this manual are the
accessories most commonly associated with the C406-N Series ELT. Other options, such as a
different remote switch configuration, should be installed and maintained in accordance with
the written instructions specific to the accessory.
NOTE
: Contact ACR Electronics for optional accessories approved for use with a C406-N
Series ELT.
(6) 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 C406-N
Series ELT.
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+X
+Z
-Z
FWD
-Y
+Y
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-990-802
2. Model Descriptions
SUBTASK 25-62-13-990-001
A. C406-N
(1) The C406-N is a type AF (Automatic Fixed) ELT, which transmits on 121.5, 243.0, and 406
MHz.
(2) The ELT is enclosed within a multi-piece mounting frame consisting of a mounting tray,
protective top cover and mounting frame cap.
(3) When ordered as a system, an installation kit, cockpit remote switch, coax cable, audible
buzzer, and single input antenna are provided.
SUBTASK 25-62-13-990-002
B. C406-N HM
(1) The C406-N HM ELT was developed for helicopter installations and features an additional 5-
axis G-Switch module, which allows the ELT to be activated in any of the six orthogonal axes.
See "Figure 1. ELT Orthogonal Axes".
(2) The C406-N HM ELT is identical to the C406-N ELT in all other aspects.
-X
Figure 1. ELT Orthogonal Axes
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C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-990-803
3. Approvals
SUBTASK 25-62-13-990-001
A. C406-N and C406-N HM
(1) FAA TSO C126, Type AF
(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) Transport Canada - Type Certificate Data Sheet AP-56
(3) Industry Canada - Certification Number 1215B-C406N AF
(4) ETSO-2C126
(5) COSPAS-SARSAT - Certificate No. 135
SUBTASK 25-62-13-990-002
B. Battery
CAUTION
(1) The lithium battery pack used on the C406-N Series ELT is certified under TSO C142.
SUBTASK 25-62-13-990-003
C. RTCA DO-160D Compliance
(1) DO-160D Environmental Categories: [D1]XBC[B204][204]XRXXXXXZAZZ[204]H[XXXX]XXX
(2) The DO-160D environmental categories breakdown is detailed in Table 1 on page 21.
: LITHIUM BATTERY SAFETY CONCERNS INCLUDE THE POSSIBILITY OF FIRE, VENTING
VIOLENTLY, AND VENTING OF TOXIC GASES.
(a) The conditions and tests required for TSO approval of this battery are minimum
performance standards. It is the responsibility of those desiring to install this battery in a
specific type or class of aircraft to determine that the aircraft installation conditions are
within the TSO standards. The battery may be installed only if further evaluation by
applicant documents an acceptable installation and is approved by the Administrator.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
Table 1. Environmental Categories Breakdown
CATEGORY SECTION DESCRIPTION
D1 4.0 Temperature/Altitude
X 4.5.4 In-Flight Loss of Cooling
B 5.0 Temperature Variation
C6.0 Humidity
B204 7.0 Operational Shock and Crash Safety
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
H 21.0 Emission of RF Energy
XXXX 22.0 Lightning
X 23.0 Lightning Direct Effects
X 24.0 Icing
X 25.0 Electrostatic Discharge
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-990-804
4. Frequency Allocations
SUBTASK 25-62-13-990-001
A. Application
(1) This section addresses the 406.0-406.1 MHz transmitter window and the specific frequency
band allocations residing above 406.028 MHz, which are assigned or reserved within the
406.0-406.1 MHz distress frequency window.
SUBTASK 25-62-13-990-002
B. Discussion
(1) The 406 MHz transmitter frequency of the C406-N Series ELT was originally 406.028 MHz. In
order to comply with COSPAS-SARSAT frequency allocation requirements, changes to the 406
MHz frequency may occur since the original release of this product.
(2) While the original C406-N Series ELTs covered by this manual transmit on 406.028 MHz,
current C406-N Series ELTs may not. The product identification label on each ELT specifies the
transmitting frequencies of the individual ELT. The 406 MHz component may be 406.028,
406.037 MHz, etc. Allocation of frequencies, based on beacon population per specified
frequency band, is controlled by COSPAS-SARSAT.
(3) The frequency references throughout this manual for the 406 MHz component should be
considered the baseline and the specific frequency indicated on the ELT product label should
be substituted if it differs from 406.028 MHz.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-990-805
5. List of Acronyms, Abbreviations, and Definitions
SUBTASK 25-62-13-990-001
Term
AC Advisory Circular – A Federal Aviation Administration (USA) bulletin
AWG American Wire Gauge – An electrical wire diameter standard. Look for
BNC CONNECTOR A very common type of coax cable connector having a 50 imped-
CAR Canadian Aviation Regulations – The rules and regulations governing
CFR Code of Federal Regulations – The general and permanent rules pub-
CONTAINER The term “Container”, within the context of this document, refers to a
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.
ance and used for RF signal connections.
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.
device designed to suppress RF signals, such that the broadcast of an
ELT placed in the container cannot reach the SAR satellite system.
COSPAS-SARSAT 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.
DER Designated Engineering Representative – An individual qualified and
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.
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C406-N (453-5060), C406-N HM (453-5061)
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.
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.
G-SWITCH A velocity switch that detects sudden de-acceleration and is used to
automatically activate an ELT. May also be referred to as a “crash
sensor”.
LED Light Emitting Diode – Semiconductor device that emits light when
current is passed through it. Usually used as a status or warning indicator.
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).
PA Programming Adapter – An optional device that automatically
updates the programming of an ELT when it is moved from one aircraft to another.
P/N Part Number – Refers to an ACR Electronics part number, unless oth-
erwise 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.
RF Radio Frequency – The range of electromagnetic radiation that con-
stitutes the radio spectrum and corresponds to the frequency of alternating current electrical signals used to produce and detect radio
waves.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
RTCA Radio Technical Commission for Aeronautics – Organization that
makes recommendations for airworthiness. Refer to http://
www.rtca.org/aboutrtca.asp for more information.
RTV A rubbery silicon-based adhesive typically used to prevent vibration
problems and water intrusion.
SAR Search and Rescue
SCREEN ROOM The term “Screen Room”, within the context of this document, refers
to a room designed to suppress RF signals, such that the broadcast of
an ELT placed in the screen room cannot reach the SAR satellite system.
SERVICE LOOP A length of wire or cable, at the connection point, of sufficient length
to allow a component to be withdrawn from its mounting position and
disconnected from its associated wiring.
TETHER A tether is a cord or similar device that anchors something movable
to a stationary point or anchors two items together, such that they
cannot become separated beyond the length of the tether.
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.
VHF Very High Frequency – The 30 MHz to 300 MHz radio frequency band.
VSWR Voltage Standing Wave Ratio – Electrical signals will “echo” back on a
wire if load impedance is not matched to the impedance of the wire.
VSWR is a measurement of the amount of voltage being “echoed,”
compared to the original signal.
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TASK 25-62-13-990-806
6. References
SUBTASK 25-62-13-990-001
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-160D, “Environmental Conditions and Test Procedures for Airborne Equipment”
(b) DO-178B, “Software Considerations in Airborne Systems and Equipment Certification”
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(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 25-62-13-990-002
B. Other Documents
(1) The following documents are available on-line at the Artex products web site at
www.acrartex.com, or from ACR Electronics upon request.
(a) 570-1000, “ELT Test Set (ETS) Operation Manual”
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THIS IS A BLANK PAGE
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-870-801
1. Description
SUBTASK 25-62-13-870-001
A. Functional Overview
(1) The ELT automatically activates during a crash and transmits the standard sweep tone on
121.5 and 243.0 MHz. Approximately every 50 seconds, for up to 520 milliseconds (long
message protocol), the 406 MHz transmitter turns on. During that time, an encoded digital
message is sent to the COSPAS-SARSAT Search and Rescue (SAR) satellite system.
(2) The information contained in the message includes:
(a) Serial number assigned to the ELT by the beacon manufacturer or the national beacon
registration authority, or
DESCRIPTION AND OPERATION
(b) Aircraft identification (24-bit address) or registration number, and
NOTE
: When the optional C406-N Programming Adapter (PA) is installed, ELTs can be
moved between aircraft and the PA reprograms the ELT with either the aircraft
24-bit address or registration number. See Appendix B – Programming Adapter
Option on page 86.
(c) Country of registration and country code; plus
(d) Position coordinates provided by the aircraft navigation system.
NOTE
: The C406-N Series ELT supports ARINC 429 data bus formats for receiving
position data from the aircraft navigation system. Other formats, such as RS232, RS-422, etc., are not supported.
(3) The 406 MHz transmitter will operate for 24 hours and then shuts down automatically. The
121.5/243.0 transmitter will continue to operate until the batteries are exhausted, which is
typically at least 50 hours.
(4) The 406 MHz transmitter produces a much more accurate position, typically 3 kilometers as
compared with 15 to 20 kilometers for 121.5/243.0 MHz transmitters. When coupled to the
aircraft navigation system, the accuracy improves to approximately 100 meters.
(5) The ELT transmits a digital message that allows search and rescue authorities to contact the
owner/operator of the aircraft through information contained in a database. Information
contained in the database includes:
(a) Type of aircraft and aircraft registration number,
(b) Owner address and telephone number, and
(c) Alternate emergency contact.
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PROTECTIVE TOP
COVER ASSY
MOUNTING FRAME
CAP ASSY
ELT MAIN
ASSEMBLY
MOUNTING
TRAY ASSY
A
A
CONTROL
SWITCH
INTERFACE
CONNECTOR
ANTENNA BNC
CONNECTOR
LED
ANNUNCIATOR
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(6) After the ELT is activated and the 406 MHz signal is detected by the SAR satellite system and
a position is calculated, the 121.5/243.0 MHz transmissions are used to home in on the crash
site.
NOTE
: Effective February 1, 2009, COSPAS-SARSAT has terminated the satellite processing
of distress signals from 121.5 and 243.0 MHz beacons.
(7) Aircraft communications transceivers are not capable of receiving 406 MHz transmissions;
therefore, the only methods of monitoring the ELT are:
(a) The blinking cockpit remote switch LED,
(b) The buzzer, or
(c) 121.5/243.0 MHz transmissions, which can be monitored using the aircraft
communications transceiver or an AM radio tuned to 121.5 MHz.
SUBTASK 25-62-13-870-002
B. Components
(1) The C406-N Series ELT main assembly is housed in a high impact, fire resistant, polycarbonate
plastic case, which is enclosed in a protective mounting frame assembly made of similar
material. See "Figure 2. C406-N Series ELT and Mounting Frame Assembly".
NOTE
: The ELT main assembly and its mounting frame assembly are capable of
withstanding extremely harsh environments and have been subjected to the rigorous
environmental testing required by COSPAS-SARSAT for certification.
Figure 2. C406-N Series ELT and Mounting Frame Assembly
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ARTEX
ON
ARM
Press ON
Wait 1 Second
Press ARM
EMERGENCY USE ONLY
Test/Reset
ELT
LED
SWITCH
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(2) The cockpit-mounted remote switch assembly is comprised of an ELT status LED and control
switch, which allows an operator to monitor ELT status and manually turn on the ELT (i.e.,
activating) for testing and resetting (i.e., deactivating) the ELT. See "Figure 3. Cockpit Remote
Switch".
NOTE
: The ELT CANNOT be disarmed or disabled from the cockpit. Cockpit operation is
limited to deactivating or manually activating the ELT.
Figure 3. Cockpit Remote Switch
(3) The buzzer (i.e., horn) provides an audible alert when the ELT is active. See "Figure 4.
Buzzer".
Figure 4. Buzzer
(4) The battery pack for the C406-N Series ELT consists of four “D” size lithium manganese
dioxide cells connected in series. In an effort to increase the safety of the battery pack, a
number of features were designed into the battery pack. To prevent the cells from being
charged, diodes are connected across each cell and fuses are connected to the output. See
"Figure 5. Battery Pack Assembly".
Figure 5. Battery Pack Assembly
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110-338
110-343
110-340
110-341
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(5) Four single-input antennas are approved for use with the C406-N Series ELT. Selection of the
proper antenna is dependent upon end use, aircraft configuration and speed, and other
factors. See "Figure 6. Rod and Whip Antennas" and "Figure 7. Blade Antennas".
Figure 6. Rod and Whip Antennas
Figure 7. Blade Antennas
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ELT
“INACTIVE”
ELT “ACTIVE”
BUZZER “ON”
LED “ON”
ELT
SWITCH
“ON”
REMOTE
SWITCH
“ON”
G-SWITCH
“ON”
ELT OR
REMOTE SW
“RESET”
YES
YES
NO
NO
NO
YES
NO
YES
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-870-803
2. Operation
SUBTASK 25-62-13-870-001
A. Operational Overview
(1) See "Figure 8. ELT Operational Flow Diagram".
(2) A primary feature of the C406-N Series ELT is its simplicity of operation. As long as the ELT is
connected to the remote switch harness ELT connector, such that pins 12 and 13 are
jumpered (G-switch loop), it will activate in the event of a crash.
NOTE
: Neither the cockpit remote switch or the ELT local switch can be positioned in such a
manner as to prevent automatic activation when the ELT is connected properly.
(3) ELT operation is designed to prevent human error and misuse in regards to automatic
activation. The ELT cannot be activated by dropping, rough handling or during shipping.
Figure 8. ELT Operational Flow Diagram
(4) When the ELT is activated, the presence of the emergency sweep tone and the flashing
cockpit remote switch panel LED indicates an active, normal functioning ELT. The remote
switch LED must immediately begin to flash continuously upon ELT activation.
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C406-N (453-5060), C406-N HM (453-5061)
(5) The ELT is considered to be either “ACTIVE” or “INACTIVE”. When “INACTIVE”, the ELT is in a
state of rest and performs no functions. Taking the ELT from the “INACTIVE” state to the
“ACTIVE” state requires a positive switch transition from either the cockpit remote switch, ELT
local switch, or G-switch.
(a) It is possible the primary G-switch or one of the auxiliary G-switches could activate the
ELT in either a fixed or rotor wing aircraft as the result of severe maneuvers or a very
hard landing.
(b) To take the ELT from an “ACTIVE” state back to an “INACTIVE” state, a “RESET” must
occur. See SUBTASK 25-62-13-870-004.
(6) A warning buzzer is required under C126 TSO approval. The buzzer is powered by the ELT and
therefore not dependent upon the aircraft battery for operation. It is not designed to operate
continuously, but sounds at predetermined intervals and runs for shorter periods toward the
end of ELT battery life.
(7) The ELT is connected to the aircraft navigation system, receives position data, and encodes
the data into the 406 MHz message. The ELT has an on-board power supply backup that
enables the ELT to retain position data for >36 seconds if aircraft power is lost.
SUBTASK 25-62-13-870-002
B. Normal Operation
(1) The cockpit remote switch is in the “ARM” position (i.e., down).
(2) The local switch on the ELT is in the “OFF” position (i.e., down).
(3) Aircraft navigation system active.
NOTE
: The aircraft navigation system must be active and sending position data to the ELT
for the ELT to incorporate position data into the 406 MHz message.
SUBTASK 25-62-13-870-003
C. Manual Activation
(1) The ELT may be manually activated by placing either the remote switch or the ELT local
switch in the “ON” position.
NOTE
: As long as the cockpit remote switch and the ELT local switch are in the ARM/OFF
positions respectively, the ELT will automatically activate on impact.
SUBTASK 25-62-13-870-004
D. ELT Reset
(1) If the ELT is activated accidently, it will need to be reset.
(2) Reset the ELT from the cockpit by moving the remote switch to the “ON” position, waiting
approximately one second, and then moving it back to the “ARM” position. If the switch is
already in the “ON” position, move it to the “ARM” position.
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(3) Reset the ELT locally by moving the switch on the ELT to the “ON” position, waiting
approximately one second, and then moving it back to the “OFF” position. If the switch is
already in the “ON” position, move it to the “OFF” position.
NOTE
: The ELT cannot be reset if either the cockpit remote switch or the ELT local switch is
in the “ON” position.
SUBTASK 25-62-13-750-001
E. Functional Check
(1) A monthly functional check is recommended to verify operational status of the ELT.
(2) Perform this functional check in accordance with SUBTASK 25-62-13-750-011 on page 48.
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TASK 25-62-13-870-803
3. Specifications
SUBTASK 25-62-13-870-001
A. Environmental and Physical
(1) Table 2 lists the environmental and physical specifications of the C406-N Series ELT.
NOTE
: For automatic activation, the higher threshold of 4.5 ft/sec (2.3 g) is specified in
accordance with Eurocae ED-62. Use of the higher threshold crash sensor has been
approved by the FAA as a deviation to TSO C126 (FAA Reference #98-130S-108,
February 6, 1998).
Table 2. Environmental and Physical Specifications
CRITERIA PARAMETER CHARACTERISTIC
Temperature
Mechanical
Automatic Activation
Weight
Dimensions (LxHxW)
Storage -55° C to +85° C
Operating -20° C to +55° C
Vibration 10
Shock 500
Crashworthiness 100
Humidity 95% for 50 hours
Penetration 55 lbs from 6 in. (25 kg from 15 cm)
Crush 1,000 lbs (454 kg)
Altitude 55,000 ft (16,764 m)
C406-N Series
(Primary G-Switch)
C406-N HM
(Auxiliary Five G-Switches)
ELT Complete w/Battery Pack,
Mounting Tray, and Covers
ELT Complete w/Battery Pack,
Mounting Tray, and Covers
g
, 5 Hz to 2,000 Hz
g
for 4 ms
g
for 23 ms
4.5 ±0.5 ft/sec (2.3
12
g
4.25 lbs (1.9 kg)
11.63 x 3.90 x 3.76 in.
(295 x 99 x 96 mm)
g
)
Software In accordance with RTCA/DO-178B, Level D
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-870-002
B. Electrical
(1) Table 3 lists the electrical specifications of the C406-N Series ELT.
CRITERIA PARAMETER CHARACTERISTIC
Operating Frequencies
Table 3. Electrical Specifications
± 1 KHz (Initial)
406.028 MHz, or higher
121.5 and 243.0 MHz ± 0.005%
+2/-5 KHz (5 years)
2 parts/10E9 in 100 ms
Modulation
121.5 and 243.0 MHz Amplitude Modulation (3K20A3X)
Transmitter Duty Cycle
121.5 and 243.0 MHz Continuous
Peak Effective Radiated
Power (PERP)
121.5 and 243.0 MHz
Occupied Bandwidth
121.5 and 243.0 MHz 25 KHz max.
Spurious Emissions
121.5 and 243.0 MHz Per CFR Title 47 (FCC), Part 87
Input Power NAV Function
406 MHz Bi-Phase L (16K0G1D)
440 ms (± 1%), or
406 MHz
406 MHz
Min. 50 mW (17 dBm) PERP for 50 hrs
(20 dBm) for 48 hrs @ -20° to +55° C
406 MHz 20 KHz max.
406 MHz Per RTCA/DO-204
520 ms (± 1%), every
50 seconds (± 5%)
5 W (37 ± 2 dB) PERP, or
EIRP for 24 hrs @ -20° to +55° C
@ -20° to +55° C or 100 mW EIRP
+28 VDC ± 5 VDC, 120 mA Max.
(60 mA nominal)
Position Data Input Protocol
Output Master Caution (Pin 7)
Type of Cell Lithium Manganese Dioxide
Battery
Voltage 12.0
Amp-Hour Rating 10.0
ARINC 429, High Speed, Low Speed
GAMA High, GAMA Low
Labels 310 (Lat.), 311 (Long.)
Vmax = 30 VDC, Imax = 25 mA, Imax
for Logic Level Low <1 mA
Active low switch to ground, pulled up
25-62-13
externally
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-870-003
C. Antennas
(1) Table 4 lists the specifications of the antennas approved for use with the C406-N Series ELT.
Table 4. Antenna Specifications
CHARACTERISTIC
PARAMETERS
110-338 110-340 110-341 110-343
Style Rod Blade Blade Whip
Frequencies 121.5, 243.0, 406 MHz
VSWR
Polarization Vertical Monopole
Radiation Pattern
Impedance
(ohms)
Weight
Drag
Coax Cable RG-142
Connector BNC Female
Dimensions
(Base-to-Tip)
121.5 and 243.0 MHz - 2.0:1 Max.
406 MHz - 1.5:1 Max.
121.5 and 243.0 MHz - Omnidirectional
0.45 lbs
(0.20 kg)
2.9 lbs (1.3 kg) @
350 KTS, 25,000 ft
15.5 in.
(39.4 cm)
1.40 lbs
(0.64 kg)
1.3 lbs (0.6 kg)
@ 241 KTS
7.75 in.
(19.7 cm)
406 MHz - Hemispherical
50 Nominal
EAS
121.5/243.0 MHz -
1.75:1 or better
406 MHz - 1.5:1 or
better
0.80 lbs
(0.36 kg)
8 lbs (3.6 kg) @
350 KTS
EAS
10.1 in.
(25.7 cm)
121.5/243.0 MHz -
2.5:1 or less
406 MHz - 1.5:1 or
less
0.31 lbs
(0.14 kg)
Minimal
17.1 in.
43.4 cm)
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TEST AND FAULT ISOLATION
TASK 25-62-13-750-801
1. Inspection and Test Regulatory Requirements
SUBTASK 25-62-13-990-001
A. United States
(1) In accordance with FAR Part 91, Subpart C, § 91.207 (d), the ELT must be inspected within 12
calendar months after the last inspection for:
(a) Proper installation;
(b) Battery corrosion;
(c) Operation of controls and crash sensor; and
(d) The presence of a sufficient signal radiated from its antenna.
(2) All maintenance shall be performed in accordance with FAR Part 43, Appendix D, which
requires the following inspections at each annual or 100-hour inspection:
(a) ELT and mount for improper installation;
(b) Wiring and conduits for improper routing, insecure mounting, and obvious defects;
(c) Bonding and shielding for improper installation and poor condition; and
(d) Antenna, including trailing antenna, for poor condition, insecure mounting, and improper
operation.
SUBTASK 25-62-13-990-002
B. Canada
(1) CAR Part VI, Standard 625, Appendix C, requires the ELT to be inspected at intervals not
exceeding 12 months.
(2) All maintenance and testing shall be performed in accordance with the requirements of CAR
Part V, Standard 571, Appendix G, which requires:
(a) Corrosion inspection;
(b) Operational testing;
(c) Performance testing, including:
1
Measured peak power after 3 minutes of operation,
2
Measured frequency after 3 minutes of operation,
3
Audio modulation, which shall be recognizable as a typical ELT signal,
4
Measured current draw in the “OFF” (ARM) and in the “ON” position, as specified
by the manufacturer, and
5
The automatic activation system.
Page 39 of 109
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-990-003
C. Other Countries
(1) For all other countries, maintenance and testing shall be conducted in accordance with the
requirements of applicable national regulatory authorities and the requirements herein, as
applicable. Local regulations and requirements shall take precedence.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-750-802
2. Inspection and Test Procedures
SUBTASK 25-62-13-990-001
A. Checklist
(1) Table 5 provides a list of the ELT inspection and testing requirements, a copy of which may be
used as a checklist to verify inspection and test completion. The item numbers in the table
correspond to the item identifiers for each task.
NOTE
: Items 5a through 5h are mandatory requirements only in Canada, in addition to
meeting the other inspection and test requirements listed in Table 5.
Table 5. ELT Inspection and Test Checklist
ITEM NO. DESCRIPTION BY
1 Coax Cable and Wiring Connections Inspection
2 ELT Mounting Tray and Hardware Inspection
3 ELT Battery Pack Inspection
4 G-Switch Functional Check
5a 121.5 MHz Frequency Measurement
5b Audio Modulation Check
5c 121.5/243.0 MHz Power Output Measurement
5d 406 MHz Frequency Measurement
5e 406 MHz Power Output Measurement
5f Current Draw Test
5g Digital Message Verification
5h ELT Reset Check
6 Installed Transmitter Test
7 Antenna Test
8 Inspection and Test Documentation
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-000-001
B. Preparation
(1) Remove the ELT in accordance with SUBTASK 25-62-13-010-001 on page 53.
(2) Remove the battery pack in accordance with SUBTASK 25-62-13-050-001 on page 54.
SUBTASK 25-62-13-220-001
C. Coax Cable and Wiring Connections Inspection – Item 1
(1) Check remote switch harness connector for corrosion bent or broken pins and other damage.
(2) Check antenna coax cable BNC connectors for corrosion, bent or broken center conductor, and
other damage.
NOTE
: Pay special attention to the center conductor, which is prone to retracting into the
connector housing.
(3) Check aircraft navigation system interface wiring connections for damage and deterioration.
SUBTASK 25-62-13-220-002
D. ELT Mounting Tray and Hardware Inspection – Item 2
(1) Inspect mounting tray for cleanliness, cracks, and other damage.
(2) Check mounting tray hardware for corrosion and security.
SUBTASK 25-62-13-220-003
E. Battery Pack Inspection – Item 3
CAUTION
CAUTION
(1) Check battery cells, components, and connectors for corrosion and other damage.
(2) Check wiring for breaks, damaged insulation, and improper or damaged connections.
: THE BATTERY PACK CONTAINS ELECTROSTATIC DISCHARGE SENSITIVE (ESD)
COMPONENTS AND, AS SUCH, IT MUST BE HANDLED WITH CARE. IF POSSIBLE, WEAR
A GROUNDED WRIST STRAP WHEN HANDLING THE BATTERY PACK DURING
INSPECTION AND MAINTENANCE ACTIVITIES. TAKE PARTICULAR CARE TO AVOID
TOUCHING THE EXPOSED CIRCUIT BOARD AND CONNECTOR PINS ON THE BOARD.
: DO NOT USE CONTACT CLEANER ON ELT COMPONENTS. SUCH CHEMICAL AGENTS
CAN BE HIGHLY DESTRUCTIVE TO THE MOUNTING HARDWARE AND ELT HOUSING,
CAUSING CRACKING, FRACTURING AND OTHER DAMAGE.
(3) Check housing for cracks and other visual damage.
(4) Remove any corrosion residue from the underside of the ELT.
(5) Check the battery pack expiration date.
(6) Replace the battery pack if any of the following conditions are true:
(a) After use in an emergency;
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(b) After an inadvertent activation of unknown duration;
(c) When the total of all known transmissions exceeds one hour; or
(d) On or before battery replacement (expiration) date.
SUBTASK 25-62-13-750-001
F. G-Switch Functional Check – Item 4
CAUTION
(1) Reinstall the battery in accordance with SUBTASK 25-62-13-450-001 on page 78.
(2) Perform this functional check within the first 5 minutes after the hour (UTC), as required by
(3) Notify any nearby control tower of your intentions.
(4) Install the C406-N Test Loop Back Plug (151-5060) on the ELT receptacle or a jumper
(5) Verify the ELT switch is in the “OFF” position.
(6) Monitor 121.5 MHz on an AM receiver.
(7) Activate the ELT by using a rapid forward (i.e., throwing) motion in the direction of the arrow
: A JUMPER IS REQUIRED TO PERFORM THIS CHECK. DUE TO THE POTENTIAL OF
PHYSICAL DAMAGE IF THE JUMPER IS IMPROPERLY INSTALLED, THIS STEP SHOULD
ONLY BE PERFORMED BY AN EXPERIENCED TECHNICIAN/MECHANIC.
NOTE
: If tests 5a through 5h are going to be performed, the battery may be temporarily
installed with only two screws, located on a diagonal from each other.
AC 43.13-1, Chapter 12, § 12-22, Note 3.
between Pins 12 and 13 of the ELT receptacle.
NOTE
: The ELT cannot be activated using this procedure unless Pins 12 and 13 on the ELT
plug are jumpered. See "Figure 21. Remote Switch Harness Wiring Diagram”, on
page 69.
on the ELT label, followed by a rapid reversing action.
(8) Verify activation by listening for the aural sweep tone on the receiver.
(9) Reset the ELT by toggling the control switch to the “ON” position and then back to the “OFF”
position.
SUBTASK 25-62-13-750-002
G. Performance Testing Setup
NOTE
: The ELT software routine logs battery life in 30-second increments. A minimum of 30
seconds is added to the battery usage total each time the ELT is activated and de-activated.
If the ELT is left activated beyond the first 30 seconds, additional time is added in 30second increments.
NOTE
: Careful planning of the performance tests is necessary to avoid activating the ELT more
than necessary. Plan the performance testing in a manner that allows tests to be run
concurrently and test equipment settings to be quickly switched from one test to another.
By doing so, the three-minute warm-up requirement can be eliminated from a number of
tests and battery run time minimized to a large extent.
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
ELT ANTENNA
BNC CONNECTOR
30 dB
ATTENUATOR
(if required)
MEASURING
DEVICE
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(1) Place the ELT in a container or screen room capable of substantially attenuating RF signals, or
the transmitter power output shall be connected to a suitable dummy load to minimize
radiation.
(2) Use the ELT’s own battery pack as the power source for these measurements. An alternate
power source can be used where lengthy servicing, other than the performance tests, is
anticipated.
(3) Ensure that adequate attenuation rated for 406 MHz is installed between the ELT antenna
output and the measurement equipment to prevent damaging input circuitry, if required. At a
minimum, the attenuator should be rated at 30 dB, and 5 watts for a ½-second duration. As
shown in "Figure 9. Performance Tests Equipment Setup".
Figure 9. Performance Tests Equipment Setup
SUBTASK 25-62-13-750-003
H. 121.5 MHz Frequency Measurement – Item 5a
(1) Connect the measuring device, referring to SUBTASK 25-62-13-750-002 on page 43.
(2) Activate the ELT by placing the control switch in the “ON” position.
(3) Wait three minutes.
(4) Perform SUBTASK 25-62-13-750-004 during the three-minute waiting period.
(5) Measure the frequency after the three-minute waiting period. The frequency must be within
the tolerance specified in Table 3 on page 37.
NOTE
: If the 121.5 MHz carrier frequency is within specified tolerance, the 243.0 MHz
frequency will also be within tolerance.
SUBTASK 25-62-13-750-004
I. Audio Modulation Check – Item 5b
(1) Perform this check in conjunction with SUBTASK 25-62-13-750-003.
(2) Monitor 121.5 MHz on an AM receiver.
(3) Listen for the aural sweep tone on the receiver. The audio should “sound” like an ELT.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-750-005
J. 121.5/243.0 MHz Power Output Measurement – Item 5c
(1) Connect the measuring device, referring to SUBTASK 25-62-13-750-002 on page 43.
(2) Activate the ELT, if necessary, by placing the control switch in the “ON” position.
(3) Wait three minutes.
(4) Read the displayed amplitude. The amplitude must be within the minimum specified for 121.5
MHz in Table 3 on page 37, at the terminal output.
(5) Change to 243.0 MHz and repeat the procedure for 243.0 MHz.
SUBTASK 25-62-13-750-006
K. 406 MHz Frequency Measurement – Item 5d
CAUTION
(1) Connect the measuring device, referring to SUBTASK 25-62-13-750-002 on page 43.
(2) Activate the ELT, if necessary, by placing the control switch in the “ON” position.
(3) Wait three minutes.
(4) Measure the frequency. The frequency must be within the tolerance specified in Table 3 on
SUBTASK 25-62-13-750-007
L. 406 MHz Power Output Measurement – Item 5e
CAUTION
(1) Connect the measuring device, referring to SUBTASK 25-62-13-750-002 on page 43.
(2) Activate the ELT, if necessary, by placing the control switch in the “ON” position.
: POWER OUTPUT IS APPROXIMATELY 37 DB (5 WATTS). BE SURE ADEQUATE
ATTENUATION IS INSERTED IN-LINE BETWEEN THE ELT ANTENNA OUTPUT AND THE
MEASURING DEVICE TO PROTECT THE INPUT CIRCUITS OF THE MEASURING DEVICE.
page 37.
NOTE
: The exact 406 MHz frequency used is printed on the ELT product label.
: POWER OUTPUT IS APPROXIMATELY 37 DB (5 WATTS). BE SURE ADEQUATE
ATTENUATION IS INSERTED IN-LINE BETWEEN THE ELT ANTENNA OUTPUT AND THE
MEASURING DEVICE TO PROTECT THE INPUT CIRCUITS OF THE MEASURING DEVICE.
(3) Wait three minutes.
(4) Read the displayed amplitude of the 406 MHz burst that follows the three-minute wait period.
The amplitude must be within the minium specified for 406 MHz in Table 3 on page 37, at the
output terminal.
(5) Deactivate the ELT by placing the control switch in the “OFF” position.
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+
A
—
CIRCUIT BOARD IN
BATTERY PACK
TO ELT
611-0024
TEST HARNESS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-750-008
M. Current Draw Test – Item 5f
CAUTION
CAUTION
(1) Verify the ELT control switch is in the “OFF” position.
(2) Separate the battery pack from the ELT.
(3) Disconnect the 2-wire ELT power connector.
(4) Install test harness 611-0024, or equivalent, in the power circuit. See "Figure 10. Current
: EXERCISE EXTREME CAUTION TO AVOID CAUSING A SHORT CIRCUIT CONDITION,
WHICH WILL BLOW THE FUSES IN THE BATTERY PACK. THIS TEST SHOULD ONLY BE
PERFORMED BY AN EXPERIENCED TECHNICIAN/MECHANIC.
: ALL “ON” STATE CURRENT MEASUREMENTS MUST BE MADE WITH THE RF OUTPUT
(I.E., ELT ANTENNA CONNECTOR) LOADED WITH 50 OHMS RATED FOR 5 WATTS.
EITHER A RESISTIVE LOAD OR EQUIPMENT WITH 50 OHM IMPEDANCE PADDED WITH
10 DB/5 WATT ATTENUATOR. SEE SUBTASK 25-62-13-750-002 ON PAGE 43.
Draw Test Setup".
Figure 10. Current Draw Test Setup
(5) Read the current draw on the ammeter. Measured current should be 0 µA (micro-amps), and
must not be more than 6 µA.
(6) Verify the ammeter is set to accommodate a range of at least 3.5 amps.
(7) Activate the ELT by placing the control switch in the “ON” position.
Page 46 of 109
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
Sarsat Beacon Reader
Beacon ID = 2DC75B534AFFBFF
Message Type = Test, Long
Country = 366 USA
A/C ICAO Addr = 50170364N16SQ
Type Approval # = 135
Position Invalid
121.5 MHz Beacon = Yes
Nov 15, 2009 10:06 am 25 sec
ClearDonePrint
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(8) Allow the ELT to stabilize for at least 30 seconds to avoid false readings.
(9) Read the current draw on the ammeter. Steady state current draw must not exceed 200 mA.
(10) Deactivate the ELT by placing the control switch in the “OFF” position.
(11) Remove the test harness.
(12) Reinstall the battery pack in accordance with SUBTASK 25-62-13-450-001 on page 78.
SUBTASK 25-62-13-750-009
N. Digital Message Verification – Item 5g
(1) Activate the ELT by placing the control switch in the “ON” position.
(2) Allow the ELT to transmit for 15 to 30 seconds, but not more than 40 seconds.
(3) 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.
(4) Deactivate the ELT and read the test message broadcast at “turn-off”. A message example is
shown in "Figure 11. Long 406 MHz Message Example".
(a) 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 COSPASSARSAT satellites to ignore the message.
(b) The "Figure 11. Long 406 MHz Message Example" is an ELT programmed for “Standard
Location Protocol ELT with 24-Bit Address”. Actual messages will vary depending on the
protocol and information programmed into the ELT.
(c) When the ELT is disconnected from the aircraft navigation system, or the navigation
system is not active, the message will indicate “Position Invalid” in lieu of position data,
as shown in "Figure 11. Long 406 MHz Message Example".
Figure 11. Long 406 MHz Message Example
(5) 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. If continued attempts to read the
message fail, check for self-test error codes and refer to Table 6 on page 50.
Page 47 of 109
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-750-010
O. ELT Reset Check – Item 5h
(1) Place the ELT control switch in the “ON” position.
(2) Return the switch to the “OFF” position.
(3) If the ELT is working properly, the LED will stay on for approximately 1 second and then turn
off. If a series of flashes are displayed, refer to Table 6 on page 50.
NOTE
: A 5-flash error indication will occur if the ELT is programmed with a location protocol,
since no navigation input data is present.
SUBTASK 25-62-13-750-011
P. Installed Transmitter Test – Item 6
CAUTION
(1) Reinstall the ELT in accordance with SUBTASK 25-62-13-410-001 on page 76.
(2) Perform the following functional check within the first 5 minutes after the hour (UTC), as
(3) Notify any nearby control tower of your intentions.
(4) Tune a receiver, usually the aircraft transceiver, to 121.5 MHz.
(5) Activate the ELT by placing the cockpit remote switch in the “ON” position. The LED will begin
(6) Listen for 3 audible sweeps on the receiver, which takes about 1 second.
(7) Verify the buzzer sounds immediately upon activation.
(8) Return the cockpit remote switch to the “ARM” (OFF) position while paying close attention to
: DO NOT ALLOW THE DURATION OF THIS TEST TO EXCEED 5 SECONDS. THE ELT
WILL TRANSMIT A 406 MHZ SIGNAL AFTER THE ELT IS ACTIVATED FOR
APPROXIMATELY 47 SECONDS. THE COSPAS-SARSAT SATELLITE SYSTEM WILL
CONSIDER THE 406 MHZ TRANSMISSION TO BE A VALID DISTRESS SIGNAL.
required by AC 43.13-1, Chapter 12, § 12-22, Note 3.
NOTE
: An AM radio may be used to receive the signal.
flashing continuously.
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.
NOTE
: This test also completes the requirement to check ELT controls by verifying operation
of the remote switch.
(9) Refer to Table 6 on page 50 if the LED displays a series of error code flashes.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-750-012
Q. Antenna Test – Item 7
CAUTION
(1) Tune a low quality AM receiver (i.e., radio) to 121.5 MHz.
(2) Place the radio approximately six inches from the antenna.
(3) Activate the ELT by placing the cockpit remote switch in the “ON” position.
(4) Listen for 3 audible sweeps on the radio, which takes about 1 second. An audible signal
(5) Reset the ELT by placing the cockpit remote switch in the “ARM” position.
SUBTASK 25-62-13-750-013
R. Inspection and Test Documentation – Item 8
(1) Make an appropriate entry in the aircraft maintenance records (i.e., logbook), including the
: Do not allow the duration of this test to exceed 5 seconds.
NOTE
: The aircraft transceiver is not recommended for this test, because it is too sensitive
to verify the integrity of the antenna system and it may pick up a weak signal even if
the antenna is disconnected from the ELT. An AM radio provides a better level of
confidence for this test.
NOTE
: Perform this test within the first five minutes after the hour UTC.
verifies energy is being transmitted by the antenna.
date the ELT inspection and testing was satisfactorily completed.
(2) In addition to the requirements of Step 1, for aircraft operating under Canadian authority and
following satisfactory completion of performance testing, the date on which the test was
performed shall be marked on the ELT external casing in a legible and permanent manner.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-810-801
3. Fault Isolation
SUBTASK 25-62-13-810-001
A. Self-Test Error Troubleshooting Guidelines
(1) Table 6 describes the ELT self-test LED error codes (i.e., flash codes), their probable causes,
and possible solutions. The 5-flash error is not present when the ELT is programmed with a
serial user protocol (short message).
NOTE
: Upon activation, the LED will display a long single flash, which is normal. Any self-
test error codes will display following this initial flash. Do not confuse the initial flash
with a 1-flash error code. If there are multiple errors, there is a 0.5 to 1.0 second
pause between each error code.
Table 6. ELT Self-Test Error Codes Troubleshooting Guide
CODE PROBABLE CAUSE POSSIBLE SOLUTION
Indicates a G-switch loop open (Pins 12 and 13)
1-Flash
2-Flash
(long/short)
Remote switch harness connector loose or
disconnected at ELT
ELT connector pins bent or broken
Connector pins 12 and 13 jumper open
(internal to remote switch harness
connector at ELT end)
Indicates a programming adapter problem
Jumper missing between Pin 3 and Pin 4
of ELT plug or connection interrupted and
Programming Adapter (PA) not in use
PA is used and not programmed
PA is used and there is a communications
or wiring error
Indicates a 406 MHz transmission problem
Check connector and tighten as necessary
Check condition of connector pins and
repair or replace as necessary
Repair open jumper
Install jumper or repair connection
Program PA - See Appendix B -
Programming Adapter Installation and
Operation
Repair or replace as necessary
3-Flash
Open or short condition on antenna
output or coax cable
Verify the coax cable/antenna is
connected and in good condition
Perform continuity check of center
conductor and shield
Check for a shorted cable
Check for intermittent connection in the
coax cable
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
CODE PROBABLE CAUSE POSSIBLE SOLUTION
Check with a VSWR meter. Check antenna
Antenna or installation faulty
for opens, shorts, or a resistive ground
plane connection
3-Flash
(cont.)
5-Flash
Impedance presented by antenna
Insufficient ground plane
Upright metal structure obstructing
antenna causing re-radiation
Low power output
Improper programming Verify 406 MHz programming
Transmitter module faulty
Indicates there is no navigation position data present
Aircraft navigation system off Turn on navigation system
Faulty system interface wiring or
connections
Indicates a battery problem
Lengthen or shorten antenna coax cable
length by 4 to 6 inches
Provide ground plane at least 12 inches in
diameter
Stay at least 10-12 inches away from
upright metal structures
Battery low
3A fuse on battery pack circuit board
faulty
Cannot be repaired in field - Return to
factory for servicing
Check wiring and connections for
continuity and security
7-Flash
Operating time is >1 hour
Replace battery pack
Electrical circuits faulty
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-810-002
B. ELT Troubleshooting Guidelines
(1) Table 7 provides ELT troubleshooting guidelines for installation and operational issues.
SYMPTOM PROBABLE CAUSE POSSIBLE SOLUTION
Table 7. ELT Troubleshooting Guide
Improper wiring Verify wiring
Remote switch LED always on
(steady)
ELT will not turn off
Check for frayed insulation
Short circuit
Battery too low to support 406
burst and causes circuit to reset
Turn off ELT using local switch - If ELT turns off:
Defective remote switch harness
reset circuit wiring
Defective remote switch Replace remote switch
If ELT does not turn off using local switch:
ELT defective
Verify integrity of all crimp and
solder connections
Remove battery pack to disable
ELT and replace battery pack
Check wiring continuity and
repair as necessary
Remove battery pack to disable
ELT and return ELT to factory for
servicing
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PROTECTIVE TOP
COVER ASSY
ELT MAIN
ASSEMBLY
MOUNTING
TRAY ASSY
MOUNTING FRAME
CAP ASSY
3
2
6
4
5
DISCONNECT COAX
CABLE
DISCONNECT
HARNESS
1
LOOSEN THUMBSCREW
(2 PLCS)
NOTE: Coax cable and
wiring harness not
shown for clarity.
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-000-801
1. ELT
SUBTASK 25-62-13-010-001
A. ELT Removal
(1) See "Figure 12. ELT Removal Sequence".
REMOVAL
Figure 12. ELT Removal Sequence
(2) Loosen the mounting frame cap thumbscrews.
(3) Slide the mounting frame cap back away from the ELT.
(4) Lift the protective top cover up, away from the ELT and set it aside.
(5) Disconnect the antenna coax cable from the ELT.
NOTE
NOTE
: The receptacle may disconnect when the mounting frame cap is pulled back.
: Careful use of a flat blade screwdriver as a lever will make this step easier.
25-62-13
(6) Disconnect the harness receptacle from the ELT, if necessary.
(7) Lift the ELT up from the connector end.
(8) Slide the ELT up and out, away from the mounting tray.
Page 53 of 109
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
NOTE: Plug is recessed in
ELT Assembly RTV puddle
ELT
ASSEMBLY
BATTERY
PACK
SCREW
(4 PLCS)
DISCONNECT
DISCONNECT
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-050-801
2. Battery
SUBTASK 25-62-13-050-001
A. Battery Pack Removal
CAUTION
: THE BATTERY PACK CONTAINS ELECTROSTATIC DISCHARGE SENSITIVE (ESD)
COMPONENTS AND, AS SUCH, IT MUST BE HANDLED WITH CARE. IF POSSIBLE, WEAR
A GROUNDED WRIST STRAP WHEN HANDLING THE BATTERY PACK DURING
INSTALLATION ACTIVITIES. TAKE PARTICULAR CARE TO AVOID TOUCHING THE
EXPOSED CIRCUIT BOARD AND CONNECTOR PINS ON THE BOARD
CAUTION
: THE BATTERY PACK IS CONNECTED TO THE ELT VIA SHORT INTERCONNECT
HARNESSES, WHICH LIMIT THE DISTANCE THE TWO COMPONENTS CAN BE
SEPARATED UNTIL THE HARNESSES ARE DISCONNECTED.
(1) See "Figure 13. Battery Pack Removal".
(2) Turn the ELT upside down, such that the battery pack is bottom side up.
(3) Remove the four retaining screws.
(4) Lay the ELT on its side, while keeping the ELT and battery pack securely held together.
(5) Separate the battery pack from the ELT, taking care not to put strain on the short interconnect
(6) Disconnect the large harness from the 8-pin header on the small circuit board mounted in the
(7) Disconnect the battery pack 2-wire harness from the connector recessed in the ELT body.
harnesses.
battery pack.
Figure 13. Battery Pack Removal
25-62-13
Page 54 of 109
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-500-801
3. Material or Equipment Return
SUBTASK 25-62-13-510-001
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:
• 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.
SUBTASK 25-62-13-580-001
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:
(a) Failure to obtain a RMA number and provide the details listed in SUBTASK 25-62-13-510-
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.
Repair and Overhaul
ACR Electronics, Inc.
5757 Ravenswood Road
Fort Lauderdale, FL 33312 USA
Phone: (954) 981-3333
Fax: (954) 983-5087
NOTE
: Do not use “International Commercial Airlines”, such carriers may cause a loss
of returned material or equipment.
Page 55 of 109
25-62-13
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
THIS IS A BLANK PAGE
25-62-13
Page 56 of 109
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
INSTALLATION
TASK 25-62-13-410-801
1. Regulatory Requirements and Guidelines
SUBTASK 25-62-13-990-001
A. TSO C126, Paragraph D
(1) TSO approval of the ELT does not constitute installation approval. All ELT 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.
(a) The remote switch is a requirement of TSO C126 and installation is not optional.
(b) The buzzer is a requirement of TSO C126 and installation is not optional.
SUBTASK 25-62-13-990-002
B. 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 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) All installation processes and interconnections related to interfacing with the aircraft
navigation system should adhere to the guidelines and requirements set forth in AC 20-130
and AC 138. In addition, the Global Positioning System/Flight Management Computer (GPS/
FMC) manufacturer’s installation instructions must be consulted regarding details specific to
the GPS/FMC and the interface with the C406-N Series ELT.
(4) By signing the aircraft logbook, and FAA Form 337, the installer is stating that 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 25-62-13-990-003
C. Canada
(1) All installations must be performed in accordance with Canadian Aviation Regulations (CAR)
Part V, Chapter 551, Paragraph 551.104.
25-62-13
Page 57 of 109
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-990-004
D. 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.
SUBTASK 25-62-13-990-005
E. 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.
(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.
(c) The antenna coax cable should not cross any production breaks, e.g., major structure
sections, such that the ELT and antenna are in the same section of the aircraft and as
close together as possible.
(d) If the ELT and external antenna are on opposite sides of an airframe production break,
the components should be secured to each other by a tether that can support a 100
load (ELT weight x 100). The interconnecting antenna-to-ELT coax cable should have
sufficient slack on both ends that it will not be subjected to any tensile load and should
be tied loosely to the tether.
g
load, (ELT weight x 100, ELT antenna weight x
g
25-62-13
Page 58 of 109
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
FLIGHT
5.21
(132)
1.71
(43)
11.63
(295)
5.50
(140)
3.42
(87)
2.00
(51)
3.76
(96)
3.90
(99)
0.165 (4.2) Ø MOUNTING
HOLES (4 PLCS)
Dimensions in inches (mm)
NOTE: Allow a minimum of
5 inches (127 mm) of clearance
in front of the mounting frame cap
to facilitate cap removal.
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-450-801
2. Mounting Tray
SUBTASK 25-62-13-450-001
A. Location
CAUTION
: MANY ORIGINAL ELT INSTALLATIONS ARE INADEQUATE AS FAR AS UNIT LOCATION
AND SURFACE RIGIDITY ARE CONCERNED. BECAUSE OF THE CRITICAL FUNCTION AN
ELT PERFORMS, IT IS IMPORTANT THE INSTALLATION FOLLOWS THE INSTRUCTIONS
AND RECOMMENDATIONS HEREIN.
CAUTION
: THE MOUNTING SURFACE MUST BE EXTREMELY RIGID; THEREFORE, MOUNTING AN
ELT DIRECTLY TO THE AIRCRAFT SKIN IS UNACCEPTABLE. MOUNTING THE ELT
DIRECTLY TO THE AIRCRAFT SKIN INDUCES “CRASH HIDING” VIBRATIONS AND
PROVIDES A VERY POOR MOUNTING SURFACE.
CAUTION
: AVOID LOCATING THE ELT WHERE IT WILL BE SUBJECTED TO UNPROTECTED
EXPOSURE TO HARSH CHEMICAL FLUIDS SUCH AS DEICING COMPOUNDS. THESE
TYPES OF CHEMICAL FLUIDS CAN PROMOTE CRACKING AND FRACTURING OF THE
ELT MOUNTING FRAME AND HOUSING COMPONENTS BY DEGRADING THE
STRUCTURAL INTEGRITY OF THESE COMPONENTS. THESE SAME CHEMICAL AGENTS
MAY ALSO CAUSE CORROSION OF ELECTRICAL CONNECTIONS.
(1) Select a suitable location for the mounting tray. See "Figure 14. C406-N Series ELT Outline
and Dimensions". Refer to these dimensions when determining mounting location.
Figure 14. C406-N Series ELT Outline and Dimensions
25-62-13
Page 59 of 109
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
8-32 x 5/8 SCREW
(4 PLCS)
#8 FLAT WASHER
(4 PLCS)
#8 LOCK WASHER
(4 PLCS)
8-32 X 1/4 HEX NUT
(4 PLCS)
AIRFRAME
STRUCTURE (REF.)
EQUIPMENT MOUNTING
PLATE (REF.)
MOUNTING
TRAY
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(2) Locate the mounting tray such that the ELT mounting frame cap has at least 5 inches (127
mm) of clearance for installation and removal.
(3) Mount the ELT as far aft as practical, but where it can be easily retrieved for maintenance.
NOTE
: Statistics show that the tail section of an airplane is likely to be less damaged during
a crash; therefore, providing a good mounting environment for the ELT.
(4) Additional installation guidance may be found in AC 43.13-2, Chapter 2, Paragraph 28, which
specifically addresses ELT installations.
SUBTASK 25-62-13-450-002
B. Installation
(1) See "Figure 15. Typical Mounting Tray Installation".
Figure 15. Typical Mounting Tray Installation
(2) Install the necessary mounting structure as appropriate for the specific installation.
(3) Align the mounting tray (452-5050) on the mounting structure, such that the arrow on the
tray is within 10° of the longitudinal axis of the aircraft and pointing in the direction of flight.
NOTE
: Refer to TASK 25-62-13-410-803 on page 81 for guidelines on ELT orientation in a
helicopter.
(4) Mark the four holes needed for mounting the tray, using the tray as a pattern. The hole
pattern is also illustrated in "Figure 14. C406-N Series ELT Outline and Dimensions”, on
page 59.
Page 60 of 109
25-62-13
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(5) Drill the four mounting holes with a #19 or 4.25 mm drill.
(6) Install the mounting tray with the 8-32 x 5/8” SS pan head phillips screws, flat washers, lock
washers, and nuts provided in the installation kit (455-7421), as shown in "Figure 15. Typical
Mounting Tray Installation”, on page 60.
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).
25-62-13
Page 61 of 109
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-450-802
3. Antenna
SUBTASK 25-62-13-990-001
A. Selection
(1) Use only antennas approved for use with the C406-N Series ELT. The ELT will not work
properly without being connected to an antenna for which it was designed.
(2) Verify the antenna selected matches the requirements of the specific installation.
Considerations include aircraft maximum rated speed, location restrictions, and any other
considerations specific to the installation.
SUBTASK 25-62-13-450-001
B. Location
(1) Select a suitable location for the antenna.
(a) Place the antenna in a location where the antenna can be installed within 15° of vertical
and with at least 30 inches (762 mm) of clearance from other antennas, particularly
VHF, in accordance with RTCA/DO-204, § 3.1.10.2.
NOTE
: AC 43.13-2, Chapter 3 recommends a minimum distance of 36 inches (914
mm) clearance between antennas.
(b) Additional location guidance may be found in AC 43.13-2, Chapter 3, which deals
specifically with antenna installations.
SUBTASK 25-62-13-450-002
C. Installation
NOTE
: Refer to the airframe manufacturer’s written instructions and AC 43.13-2, Chapter 3 for antenna
installation practices and requirements.
(1) Install a doubler plate if necessary to meet rigidity requirements. A 20 lb (9.1 kg) force applied
to the antenna in all directions should not cause an appreciable distortion in the aircraft skin.
(2) Install a ground plane if necessary. In certain applications, particularly those where antennas
are installed on composite, fabric, or wood airframes, a ground plane is required.
(3) Drill the antenna mounting holes and a coax cable connector hole referring to the appropriate
antenna illustration for hole patterns and hole sizes.
(a) See "Figure 16. Rod Antenna 110-338 and Whip Antenna 110-343 Outlines and
Dimensions”, on page 63 and "Figure 17. Blade Antennas 110-340 and 110-341 Outlines
and Dimensions”, on page 64.
(4) Mount the antenna referring to the appropriate antenna illustration for hardware
requirements, torque, and other applicable installation requirements.
(5) A coax cable, 6 feet (1.8 m) long, is provided as part of the ELT kit.
Page 62 of 109
25-62-13
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
13.00
(330)
3.5
(89)
3.3
(84)
15.50 MAX
(394)
2.70 MAX
(69)
1.625 (41.3)
0.812 (20.6)
0.750 (19.1)
0.90 (23)
1.750 (44.5)
4.40 MAX
(112)
RF CONNECTOR
BNC FEMALE
4 - 100° CSK HOLES
Ø 0.170 (4.3)
110-338
Dimensions in inches (mm)
C.G.
INSTALLATION NOTES:
1. MOUNT ANTENNA USING #8-32 SS 100° C’SK
MACHINE SCREWS AND ASSOCIATED
HARDWARE.
2. PROVIDE 0.625 (5/8”) (16 MM) Ø HOLE
IN AIRCRAFT FOR BNC CONNECTOR.
3. PROVIDE 0.182 (4.6 MM) Ø HOLES (4 PLCS)
IN AIRCRAFT FOR ATTACHING SCREWS.
4. APPLY A LAYER OF ANTI-CORROSION BONDING
GREASE BETWEEN AICRAFT AND ANTENNA BASE.
5. GASKET NOT SUPPLIED AND USE OPTIONAL.
REQUEST P/N 280-0320 IF ONE IS DESIRED.
GASKET (OPTIONAL)
SUPPLIES
17.09 MAX
(434)
33º
0.95 (24) MAX
0.79 (20) MAX
0.92 (23)
(TYP.)
33º
0.64 (16) Ø
CLEARANCE HOLE
VERTICAL INSTALLATION
0.64 (16)
0.74 (19)
MOUNTING NUT
0.19 (5) MAX
AIRCRAFT SKIN: DOUBLER PLATE
TO BE USED AS NECESSARY
TAPERED ELEMENT
RF CONNECTOR BNC FEMALE
INSTALLATION NOTES:
1. ANTENNA MAYBE MOUNTED VERTICALLY OR AT 33º ANGLE
3. APPLY A BEAD OF SEALANT AROUND MOUNTING NUT
Dimensions in inches (mm)
110-343
CLEARANCE HOLE
33º INSTALLATION
WIRE LOCKING
HOLES (TYP.)
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
Figure 16. Rod Antenna 110-338 and Whip Antenna 110-343 Outlines and Dimensions
Page 63 of 109
25-62-13
MAR 1/13
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
7.75
(197)
30º
15º
2.70
(69)
2.89
(73)
2.25
(57)
0.562 (14.3)
8.25
(210)
6.000
(152.4)
3.000
(76.2)
1.620 (41.2)
1.500
(38.1)
0.750 (19.1)
1.25 (32)
0.625 (15.9)
0.201 (5.1) Ø (6 PLCS)
RF CONNECTOR BNC FEMALE
Dimensions in inches (mm)
C.G.
110-340
INSTALLATION NOTES:
1. MOUNT ANTENNA USING #10-32 SS MACHINE
SCREWS AND ASSOCIATED HARDWARE.
2. PROVIDE 0.625 (5/8”) (16 MM) Ø HOLE
FOR BNC CONNECTOR.
3. PROVIDE 0.213 (5.4 MM) Ø HOLES (6 PLCS)
FOR ATTACHING HARDWARE.
4. BONDING THROUGH MOUNTING SCREWS
NOT REQUIRED.
5. APPLY A LAYER OF ANTI-CORROSION BONDING
GREASE BETWEEN AICRAFT AND ANTENNA BASE.
6. GASKET NOT SUPPLIED AND USE OPTIONAL.
REQUEST P/N 280-0340 IF ONE IS DESIRED.
1.160 (29.5)
3.80 EST
(97)
3.15 EST
(80)
C.G.
3.8 MAX
(97)
10.1 MAX
(257)
4.90 MAX
(125)
2.38
(61)
0.90 (23)
1.19 (30)
1.38 (35)
1.06 (27)
2.05 MAX (52)
0.200 - 0.207 Ø (6 PLCS)
(5.1 - 5.3 Ø)
RF CONNECTOR BNC FEMALE
Dimensions in inches (mm)
110-341
INSTALLATION NOTES:
1. MOUNT ANTENNA USING #10-32 SS MACHINE
SCREWS AND ASSOCIATED HARDWARE.
2. PROVIDE 0.625 (5/8”) (16 MM) Ø HOLE
FOR BNC CONNECTOR.
3. PROVIDE 0.213 (5.4 MM) Ø HOLES (6 PLCS)
FOR ATTACHING SCREWS.
4. THIS ANTENNA BONDED BY THE BASE PLATE
BONDING THROUGH MOUNTING SCREWS
NOT REQUIRED.
5. APPLY A LAYER OF ANTI-CORROSION
BONDING GREASE BETWEEN AICRAFT
AND ANTENNA BASE.
ACR ELECTRONICS, INC / ARTEX PRODUCTS
C406-N (453-5060), C406-N HM (453-5061)
Figure 17. Blade Antennas 110-340 and 110-341 Outlines and Dimensions
25-62-13
Page 64 of 109
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
1.10
(28)
0.044
(1.1)
0.140
(3.6)
1.59
(40)
OUTLINE OF REMOTE
SWITCH BODY
0.1405 (3.57) Ø
USE #28 (3.6) DRILL
(4 PLCS)
NOTE: HATCHED AREA
IS CUTOUT PATTERN
1.04
(26)
1.73
(44)
1.30
(33)
2.00
(51)
1.20
(30)
0.50
(13)
1.70
(43)
1.06
(27)
1.45
(37)
FRONT VIEW
SIDE VIEW
HOLE CUTOUT GUIDE FOR INSTALLATION
OF 345-6196-04 (FRONT VIEW)
RECOMMENDED
CUTOUT PATTERN
DIMENSIONS IN INCHES (MM)
ARTEX
ON
ARM
Press ON
Wait 1 Second
Press ARM
EMERGENCY USE ONLY
Test/Reset
ELT
TOLERANCE: ±0.03 (1)
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-450-803
4. Remote Switch
SUBTASK 25-62-13-450-001
A. Location
(1) Select a suitable location for the remote switch assembly. The switch assembly must be
mounted in the cockpit where the pilot can easily reach the switch and see the LED.
NOTE
: This procedure is applicable to the most commonly used remote switch (345-6196-
04). If an optional switch is installed in lieu of this one, the applicable installation
instructions should be consulted.
NOTE
: Refer to Appendix C – Remote Switch Control Panel Option on page 91, for
installation instructions covering the optional 453-0161 (G737) remote control panel.
(2) The switch assembly requires a space approximately 2.0 x 1.3 in. (51 x 33 mm) on the panel
surface and behind the panel. See "Figure 18. Remote Switch Outline and Dimensions".
Figure 18. Remote Switch Outline and Dimensions
SUBTASK 25-62-13-450-002
B. Installation
(1) Mark out the cutout on the cockpit panel. See "Figure 18. Remote Switch Outline and
Dimensions".
(2) Fit the switch assembly into the cutout and mark the four screw holes, then remove the
switch.
(3) Drill the screw holes with a #28 or 3.6 mm drill.
(4) Install the switch assembly using the 4-40 x ½ in. pan head screws, nuts and lock washers
provided in the remote switch installation kit (455-6196).
NOTE
: Step 4 may be completed after wiring is completed and the harness plug has been
plugged into the switch assembly, in accordance with the requirements of SUBTASK
(5) Apply the “For Aviation Emergency Use Only/Unauthorized Use Prohibited” placard (591-
0428), provided in the installation kit, as close to the switch as practical.
25-62-13-450-010 on page 75. If such is the case, perform a fit check at this time.
25-62-13
Page 65 of 109
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
+
ARTEX
+
-
-
1.68
(43)
1.75
(45)
1.115
(28.3)
PANEL MOUNTING NUT
0.445
(11.3)
FRONT VIEW
SIDE VIEW
REAR VIEW
Dimensions are
reference only
130-4004
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-450-804
5. Buzzer
SUBTASK 25-62-13-450-001
A. Location
CAUTION
: PLACING THE BUZZER IN THE COCKPIT IS NOT RECOMMENDED DUE TO THE
POTENTIAL FOR DISTRACTION. THE BUZZER PRODUCES A LOUD, SIREN-TYPE
SOUND WHEN THE ELT IS ACTIVATED. SINCE THE BUZZER OPERATES IN TANDEM
WITH THE COCKPIT LED, IT WOULD ONLY SERVE AS A REDUNDANT WARNING
INDICATOR IN THE COCKPIT.
(1) Select a suitable location for the buzzer.
NOTE
: The buzzer may be located anywhere in the aircraft; however, the recommended
location is near the ELT, as the buzzer is loud enough to be heard outside the aircraft
when the engine(s) is not running. When the engine(s) is running, the LED on the
cockpit remote switch assembly will warn the pilot the ELT is active.
SUBTASK 25-62-13-450-002
B. Installation
(1) See Appendix C – Remote Switch Control Panel Option on page 91 for instructions on
installation of an alternate, modified buzzer used with the optional remote switch control
panel in Boeing configurations.
(2) Fabricate a bracket suitable for supporting the buzzer. Buzzer dimensions are shown in
"Figure 19. Buzzer Outline and Dimensions".
NOTE
: Refer to the aircraft manufacturer’s written instructions or AC 43.13-2, as applicable,
for approved bracket fabrication and installation methods.
Figure 19. Buzzer Outline and Dimensions
(3) Attach the bracket to the airframe such that the buzzer is adequately supported and does not
show any significant evidence of distorting the airframe skin.
(4) Install the buzzer in the bracket.
(a) Remove the panel mounting nut and insert the buzzer in the bracket.
(b) Install the panel mounting nut and tighten it securely.
25-62-13
Page 66 of 109
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-450-805
6. Wiring
SUBTASK 25-62-13-990-001
A. General Considerations and Recommendations
CAUTION
CAUTION
CAUTION
(1) The following wiring and grounding considerations and recommendations are applicable:
: IF GROUND OR OTHER CONNECTIONS ARE BROKEN OR OTHERWISE DAMAGED, THE
ELT IS STILL CAPABLE OF AUTOMATIC ACTIVATION; HOWEVER, THE COCKPIT
REMOTE SWITCH MAY BE INCAPABLE OF RESETTING THE ELT AND OPERATION MAY
NOT BE INDICATED ON THE REMOTE SWITCH LED.
: INCORRECT TERMINATION OF THE WIRING IN THE CONNECTORS MAY DAMAGE THE
ELT, CAUSE TRANSMISSION ISSUES, OR RESULT IN A NON-FUNCTIONING REMOTE
SWITCH. VERIFY THE WIRING AGAINST THE WIRING DIAGRAM AND PERFORM A
CONTINUITY CHECK TO CONFIRM GOOD CONNECTIONS AND PROPER PIN
LOCATIONS.
: TO PREVENT INADVERTENT ELT ACTIVATION OR POSSIBLE COMPONENT DAMAGE,
DO NOT CONNECT THE HARNESS TO THE ELT OR COCKPIT REMOTE SWITCH UNTIL
ALL POWER AND GROUND WIRING CONNECTIONS ARE COMPLETED.
(a) Minimum 22 AWG wire size.
(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” in the remote switch harness connection to the ELT to divert
moisture from the connector. See TASK 25-62-13-990-805 on page 23 for a definition.
(e) Provide a “Service Loop” in the remote switch harness connection to the remote switch
assembly, such that the assembly can be withdrawn from the panel far enough to easily
disconnect the harness plug. See TASK 25-62-13-990-805 on page 23 for a definition.
(f) All grounds required for this installation must be common to aircraft ground.
SUBTASK 25-62-13-450-001
B. Remote Switch Harness Fabrication
(1) See "Figure 20. Remote Switch Harness Arrangement”, on page 68.
(2) Fabricate a 5-wire harness long enough to reach from the ELT to the cockpit remote switch,
allowing enough slack to provide a drip loop at the ELT end and a service loop at the cockpit
remote switch end.
(a) Strip approximately 0.15 in. (3 mm) of insulation from the remote switch ends of each of
the five cable wires and 0.19 in. (5 mm) from the ELT ends.
(b) Dress and tin the bare wires to prevent the strands from fraying during terminal
crimping operations.
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
TO ARINC 429 SOURCE
TO ANTENNA
REMOTE SWITCH
ELT
PROTECTIVE
TOP COVER
MOUNTING FRAME
CAP ASSEMBLY
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
Figure 20. Remote Switch Harness Arrangement
(3) Fabricate a shielded, twisted pair of sufficient length to reach from the harness ELT plug to
the aircraft navigation system ARINC 429 output.
(a) Strip approximately 0.19 in. (5 mm) from the ELT ends.
(b) Prepare the wire ends at the navigation system ARINC 429 output in accordance with
the manufacturer’s written instructions.
(c) Dress and tin the bare wires to prevent the strands from fraying during terminal
crimping operations.
(4) See "Figure 21. Remote Switch Harness Wiring Diagram”, on page 69.
25-62-13
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MAR 1/13
6
7
8
5
2
7
1
4
NC
NC
3
6
9
LIGHT
ELT ON
RST 1
RST 2
EXTERNAL ON
G-SWITCH LOOP
G-SWITCH LOOP
GROUND
HORN POWER
HORN GROUND
+5VDNGL
DDCS
9
8
12
13
19
20 NC
NC
NC
22
10
21
3
4
1
2
15
16
14
11
18
PINS 3 AND 4 MUST BE JUMPERED UNLESS OPTIONAL
PROGRAMMING ADAPTER (PA) IS INSTALLED. SEE APPENDIX B
FOR PA INSTALLATION DETAILS (PINS 1, 2, 3, 4, 15, AND 16).
17
5
A
B
ARINC 429 INPUT
TWISTED PAIR
(SHIELDED)
ELT
PLUG
COCKPIT REMOTE
SWITCH PLUG
+28 VDC
AIRCRAFT POWER
SWITCHABLE POWER SOURCE WITH 1-AMP BREAKER OR
SLO-BLO FUSE. MAXIMUM CURRENT DRAW IS 120 mA.
USE MINIMUM
22 AWG WIRE
1
1
2
2
2
+28 VDC
3
3
CONNECT REMOTE SWITCH POWER DIRECTLY TO AIRCRAFT
BATTERY VIA 1-AMP FUSE OR BREAKER. MAXIMUM CURRENT
DRAW IS 100 mA.
SEE APPENDIX C FOR OPTIONAL CONTROL PANEL INSTALLATION
DETAILS AND MASTER CAUTION PANEL CONNECTION TO PIN 7.
4
4
5
5
6
6
+
PINS 6 AND 9 OF REMOTE SWITCH ARE INTERNALLY TIED.
IF AIRCRAFT GROUND INTEGRITY BETWEEN THE ELT AND
REMOTE SWITCH CANNOT BE GUARANTEED, REMOTE SWITCH
PIN 6 IS WIRED TO ELT PIN 11 (OR GROUND POINT COMMON
TO ELT PIN 11 AS CLOSE TO ELT AS POSSIBLE). IF GROUND
INTEGRITY IS GOOD, THE CONNECTION BETWEEN REMOTE
SWITCH PIN 6 AND ELT PIN 11 IS NOT REQUIRED.
USE OF SHIELDED CABLE IS RECOMMENDED, PARTICULARLY FOR
LONG CABLE RUNS AND WHERE EMI IS A CONCERN.
7
7
CONNECT STRAIN RELIEF TO AIRCRAFT GROUND AS CLOSE TO
ELT AS POSSIBLE.
PIN INSERTION END OF MOLEX
PLUG FOR REMOTE SWITCH
ASSEMBLY. HOLE NUMBERING
IS IDENTICAL TO THAT INSCRIBED
ON ACTUAL PLUG. ORIENTATION
SHOWN IS SAME AS INSERTION
ORIENTATION FOR INSTALLED
SWITCH.
ELT MATING PLUG
(CIRCULAR CONNECTOR)
PIN INSERTION VIEW
1
22
21
AIRCRAFT
GROUND (TYP.)
4
HORN
9
8
7
6
5
4
3
2
1
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
Figure 21. Remote Switch Harness Wiring Diagram
25-62-13
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(5) Fabricate the following wires.
(a) Fabricate a ground wire long enough to reach from Pin 11 of the harness ELT plug to
aircraft ground.
NOTE
: This wire will be crimped in the same pin as the wire running from Pin 11 of the
ELT plug to the cockpit remote switch plug Pin 6, if the Pin 11 to Pin 6
connection is required. See Note 4 in "Figure 21. Remote Switch Harness
Wiring Diagram”, on page 69. Alternatively, the wires may be spliced in a
manner acceptable to the aircraft manufacturer, or as described in AC 43.13-1,
Paragraph 11-167.
(b) Fabricate a ground wire long enough to reach from Pin 9 of the remote switch plug to
aircraft ground.
(c) Fabricate a ground wire long enough to reach from the harness ELT plug strain relief to
aircraft ground.
(d) Fabricate a power wire long enough to reach from the remote switch plug (Pin 3) to a
+28 VDC battery power source.
(e) Fabricate a power wire long enough to reach from the ELT plug (Pin 10) to a +28 VDC
power source.
(f) Fabricate two wires of sufficient length to reach from the harness ELT plug to the
buzzer.
NOTE
: These wires provide power and ground for the buzzer. Use appropriate means
of identification for the wires, such that the wires can be readily identified.
(g) Prepare the wires as follows:
1
Strip approximately 0.15 in. (3 mm) of insulation from the remote switch wire ends
and 0.19 in. (5 mm) from the ELT wire ends.
2
Dress and tin the bare wires to prevent the strands from fraying during terminal
crimping operations.
(6) Crimp contact sockets (151-6657) on the harness wire ends at the ELT, as follows:
NOTE
: Use crimp tool M22520/7-01 and die M22570/7-06, or equivalent.
(a) The Pin 11 ground wire. The wire running from Pin 11 to remote switch Pin 6 is
terminated in the same pin, if this wire is required. See "Figure 21. Remote Switch
Harness Wiring Diagram”, on page 69. Make a note of the wire identification for later
reference.
(b) On each of the remaining wire ends at the harness ELT end.
(c) The +28 VDC switchable power source wire.
(d) The buzzer power and ground wires.
(e) On each of the twisted pair ARINC 429 input wires.
(7) Crimp appropriately sized ring terminals on the buzzer ends of the buzzer power and ground
wires.
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(8) Crimp appropriately sized ring terminals on the airframe ends of the following wires:
(a) Harness ELT plug Pin 11 ground wire.
(b) Harness ELT plug strain relief ground wire.
(c) Remote switch plug ground wire.
(9) Crimp appropriately sized ring terminals on the airframe ends of the following wires:
NOTE
: If desired, the power wires may be spliced or otherwise connected to their individual
power sources in a manner acceptable to the aircraft manufacturer, or as described
in AC 43.13-1, Paragraph 11-167.
(a) Harness ELT plug +28 VDC switchable power source wire. Use a power source
controlled by the avionics switch or master switch. This circuit draws power at all times
and will drain the battery if not switched off. See SUBTASK 25-62-13-450-006 on
page 74 for circuit protection requirements.
(b) Harness remote switch plug +28 VDC battery power source wire. This power source
must be direct from the battery. Use the clock circuit or a similar source of battery
power. See SUBTASK 25-62-13-450-007 on page 74 for circuit protection requirements.
(10) Provide a means of termination on the airframe end of the ARINC 429 twisted pair of wires
compatible with the aircraft navigation system ARINFC 429 output source.
(11) Crimp female terminal pins (151-6628) to the cockpit remote switch end, as follows:
NOTE
: Use Molex crimp tool 63811-3300, or an equivalent tool for 0.062 in. terminal pins.
(a) Each harness wire.
(b) Remote switch ground wire.
(c) Remote switch +28 VDC battery power wire.
(12) Bundle the wiring into a complete harness, with breakouts as appropriate, such that the wiring
can be properly supported and attached to the airframe. Refer to the aircraft manufacturer’s
written instructions or AC 43.13-1, Chapter 11, § 9 through 12, as applicable.
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
TO AIRCRAFT
GROUND
1
11
21
22
FRONT VIEW
1
22
21
11
REAR VIEW
STRAIN RELIEF
SEALING GROMMET PLUG
SOCKET CONTACT
150-5061
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-450-002
C. ELT 22-Pin Plug Installation
(1) Refer to "Figure 21. Remote Switch Harness Wiring Diagram”, on page 69, and "Figure 22.
Harness ELT 22-Pin Plug Arrangement".
Figure 22. Harness ELT 22-Pin Plug Arrangement
(2) Fabricate two short jumper wires, approximately 1.5 in. (38 mm) long.
(a) Strip approximately 0.19 in. (5 mm) of insulation from both ends of each of the wire.
(b) Dress and tin the bare wire ends to prevent the strands from fraying during terminal
crimping operations.
(c) Crimp contact sockets (151-6657) on the wire ends.
NOTE
: Use crimp tool M22520/7-01 and die M22570/7-06, or equivalent.
(3) Terminate the jumpers in the harness ELT 22-position plug (150-5061) as follows:
CAUTION
: THE ELT WILL NOT AUTOMATICALLY ACTIVATE IF THE G-SWITCH LOOP
JUMPER (PINS 12 AND 13) IS NOT PROPERLY INSTALLED IN THE HARNESS ELT
PLUG.
(a) Insert the contact sockets of one jumper in Pins 12 and 13 (G-switch loop).
NOTE
: Use insertion tool MS27495A22MS, or equivalent, and extraction tool
MS27495R22MS, or equivalent.
NOTE
: Each contact socket should “click” into place when properly seated.
(b) Insert the contact sockets of the other jumper in Pins 3 and 4.
(4) Slip the strain relief (151-5061) over the wiring terminating in the harness ELT plug.
NOTE
: Slide heat shrink tubing of suitable size over the wires, if desired.
(5) Insert the harness and other wiring contact sockets in the harness ELT plug as follows:
(a) Harness wires connecting to the remote switch plug.
1
Make a record of wire identification and pin relationships for reference when
terminating the harness wires in the remote switch plug.
(b) The airframe ground wire (Pin 11).
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(c) The buzzer power and ground wires (Pins 14 and 21, respectively).
(d) The +28 VDC power source wire.
(e) The ARINC 429 twisted pair wires (Pins 5 and 17).
(6) Fill the empty plug pin locations as follows:
NOTE
: Filling the empty plug pin locations is important not only for preventing moisture
penetration, but also preventing the inserted contact sockets from cocking and
possibly causing a short circuit by touching each other.
(a) Insert contact sockets in all empty pin locations.
(b) Insert sealing grommet plugs (151-6658), large diameter first, in the empty contact
sockets.
(7) Shrink the heat shrink tubing if installed in Step (4).
(8) Screw the strain relief onto the plug.
(9) Tighten the strain relief clamp.
SUBTASK 25-62-13-450-003
D. Cockpit Remote Switch 9-Pin Plug Installation
(1) Inert the wiring pins in the 151-5009 Molex 9-pin cockpit remote switch plug. See "Figure 21.
Remote Switch Harness Wiring Diagram”, on page 69.
(a) Insert each harness female pin into the plug.
NOTE
: Refer to the wire identification and pin relationships recorded in Step C.(5)(a)1.
NOTE
: Terminal pins may be removed from the plug using Molex extraction tool
11030002, or equivalent.
(b) Insert the remote switch power wire female pin into Pin 3 of the plug.
(c) Insert the remote switch ground wire into Pin 9 of the plug.
SUBTASK 25-62-13-450-004
E. Wiring Installation
(1) Route the remote switch harness wire bundle and breakout wiring through the airframe.
(2) Route the antenna coax cable through the airframe.
NOTE
: A longer coax cable, up to 20 feet (6.1 m), may be fabricated if the cable provided is
too short. Use RG-142 or RG-400 coax cable.
(3) Support the wiring and coax cable 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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ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-450-005
F. Antenna Connection
(1) Connect the coax cable to the antenna, making sure the cable is routed and supported such
that there is no tensile load (i.e., strain) on the connection.
SUBTASK 25-62-13-450-006
G. Cockpit Remote Switch Power Connection
(1) Connect the remote switch power wire directly to battery power using a 1-amp in-line fuse or
circuit breaker.
NOTE
: If the wire is spliced, fabricate the splice in a manner acceptable to the aircraft
manufacturer or as described in AC 43.13-1, § 13.
NOTE
: This power source provides energy for the remote switch assembly LED, but has no
effect on switch functions, as the switch will control the ELT with or without power.
SUBTASK 25-62-13-450-007
H. ELT Power Connection
(1) Connect the ELT power wire to a +28 VDC source controlled by the avionics switch or master
switch using a 1-amp, in-line, slo-blo fuse or circuit breaker.
NOTE
: If the wire is spliced, fabricate the splice in a manner acceptable to the aircraft
manufacturer or as described in AC 43.13-1, § 13.
NOTE
: This power source provides energy for the ELT navigation functions.
SUBTASK 25-62-13-450-008
I. Airframe Ground Connections
(1) Connect the following grounds to the airframe in accordance with the aircraft manufacturer’s
written instructions or as described in AC 43.13-1, Chapter 11, § 15. See "Figure 21. Remote
Switch Harness Wiring Diagram”, on page 69.
(a) Harness ELT plug ground from Pin 11.
(b) Harness ELT plug strain relief ground.
(c) Harness remote switch plug ground from Pin 9.
(d) ARINC 429 twisted pair shield ground.
SUBTASK 25-62-13-450-009
J. Buzzer Connection
(1) Connect the power wire to the buzzer positive (+) terminal.
(2) Connect the ground wire to the buzzer negative (–) terminal.
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-450-010
K. Remote Switch Final Installation
(1) Insert the harness plug into the remote switch receptacle.
(2) Install the remote switch assembly, referring to SUBTASK 25-62-13-450-002 on page 65.
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
PROTECTIVE TOP
COVER ASSY
ELT MAIN
ASSEMBLY
MOUNTING
TRAY ASSY
MOUNTING FRAME
CAP ASSY
4
5
1
2
3
CONNECT COAX
CABLE
CONNECT
HARNESS
6
NOTE: Coax cable and
wiring harness not
shown for clarity.
TIGHTEN THUMBSCREW
(2 PLCS)
Tighten to no more than
18 lb-in (203 Ncm)
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-410-802
7. ELT Installation and Test
SUBTASK 25-62-13-410-001
A. Installation
(1) See "Figure 23. ELT Installation Sequence".
Figure 23. ELT Installation Sequence
(2) Verify the ELT local switch is in the “OFF” position.
(3) Insert the ELT into the mounting tray at an angle, such that the locking ears at the end
opposite the direction-of-flight arrow fit into the mounting tray locking slots.
(4) Press the ELT down until it is fully seated in the mounting tray.
(5) Install the protective top cover assembly (452-3052) on the ELT by fitting the cover locking
slots over the locking ears on the ELT.
(6) Push the cover toward the connector end of the ELT and seat it down in place on the ELT.
(7) Route the antenna coax cable and remote switch harness plug through the appropriate access
holes in the mounting frame cap (452-5066).
(8) Connect the antenna coax cable to the ELT.
(9) Connect the 22-pin harness plug to the ELT.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(10) Slide the mounting frame cap into place over the mounting tray and protective top cover.
(11) Secure the mounting frame cap to the mounting tray with the thumbscrews and tighten them
to no more than 18 lb-in (203 N•cm).
(12) Tie up excess slack in the harness and coax cable, such that they form drip loops and there is
enough slack, approximately 5 in. (127 mm), to allow the mounting frame cap to be easily
pulled back.
NOTE
: Steps 1 through 11 are applicable any time the ELT has been removed and
undergoes reinstallation. Step 12 is only applicable at initial installation or if the
wiring or coax cable has been disturbed.
SUBTASK 25-62-13-750-001
B. Post-Installation Testing
(1) Test the ELT installation in accordance with the requirements of SUBTASK 25-62-13-750-011
on page 48.
NOTE
: It is very important the cockpit remote switch LED immediately begins flashing
continuously upon ELT activation. If the light fails to start flashing, recheck the
interface wiring and connections between the ELT and the cockpit remote switch.
(2) Comply with the GPS/FMC manufacturer’s written post-installation checkout instructions and
verify connection to the C406-N Series ELT has not caused any degradation in GPS/FMC
performance.
NOTE
: For all “live” RF testing of the 406 MHz message output, only the “test message”
transmitted at ELT turn-off is required to verify C406-N functions. See SUBTASK 2562-13-750-009 on page 47.
SUBTASK 25-62-13-410-002
C. Installation Documentation
(1) Make appropriate logbook (i.e., aircraft records) entries and submit FAA Form 337, along with
any supporting data required by the FAA for approval of the installation, as applicable.
NOTE
: Refer to TASK 25-62-13-410-801 on page 57 for additional information on installation
approvals.
(2) In countries other than the United States, make appropriate aircraft records entries and
submit documentation as required for installation approval in accordance with national
regulatory authorities.
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
NOTE: Plug is recessed in
ELT Assembly RTV puddle
ELT
ASSEMBLY
BATTERY
PACK
CONNECT
CONNECT
SCREW WITH O-RING
P/N 217-0606
(4 PLCS)
RUBBER
SEAL
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-450-806
8. Battery Pack Installation
SUBTASK 25-62-13-450-001
A. Battery Reinstallation
CAUTION
: THE BATTERY PACK CONTAINS ELECTROSTATIC DISCHARGE SENSITIVE (ESD)
COMPONENTS AND, AS SUCH, IT MUST BE HANDLED WITH CARE. IF POSSIBLE, WEAR
A GROUNDED WRIST STRAP WHEN HANDLING THE BATTERY PACK DURING
INSTALLATION ACTIVITIES. TAKE PARTICULAR CARE TO AVOID TOUCHING THE
EXPOSED CIRCUIT BOARD AND CONNECTOR PINS ON THE BOARD.
(1) This subtask applies to reinstallation of an existing battery that was removed for inspection
and testing.
(2) See "Figure 24. Battery Pack Installation".
(3) Apply a thin coating of non-petroleum based silicone grease, such as GE G-635, to the rubber
(4) Lay the battery pack and ELT on their sides, such that the two components are aligned, but
(5) Connect the ELT lead 8-pin connector to the header on the battery pack circuit board.
(6) Connect the power harness 2-pin connector to the recessed connector inside the ELT body.
Figure 24. Battery Pack Installation
seal to facilitate installation and allow the ELT and battery pack to slide together without
binding on the rubber seal.
separated enough to allow the electrical connections to be made.
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SWITCH/CONNECTOR
END
1
2
3
4
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(7) Reset the ELT by toggling the ELT local control switch to “ON” and back to “OFF” after 1-2
seconds.
NOTE
: This step is necessary because the ELT will occasionally activate when power is
connected to it in Step 6.
(8) Fit the battery pack into place on the ELT, while dressing the wires away from the standoffs to
avoid pinching the wires between the standoffs and battery pack.
(9) Turn the battery pack bottom face up to facilitate installing the screws, while securely holding
the ELT and battery pack together.
(10) Install the four battery pack retaining screws about half way (i.e., leave them loose).
(11) Tighten and torque the screws as shown in "Figure 25. Battery Pack Screw Tightening
Pattern". Torque to 6-8 lb-in (68-90 N•cm).
Figure 25. Battery Pack Screw Tightening Pattern
(12) Perform an ELT self-test as follows:
(a) Set the ELT local control switch in the “ON” position. The LED will begin flashing every 3-
4 seconds.
(b) Return the switch to the “OFF” position after 1-2 seconds. If the ELT is working properly,
the LED will stay on for approximately 1 second and then flash the following expected
error codes, which should be ignored.
1
1-flash and 3-flash errors, which are generated because the ELT is not installed
and connected to the antenna, etc.
2
A 5-flash error will be indicated if the ELT is programed with a location protocol,
and is generated because the ELT is not connected to the navigation system and
receiving position data.
(c) If a 7-flash error code is indicated, there is a problem with the battery or battery
connection wiring. Refer to Table 6 on page 50.
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-450-002
B. New Battery Installation
CAUTION
(1) This subtask applies to installation of a new (i.e., replacement) battery.
(2) Verify the bottom of the ELT is clean and free of battery corrosion residue. Clean as
(3) Remove the paper backing from the rubber seal at the connector end of the battery pack.
(4) Perform the procedure outlined in SUBTASK 25-62-13-450-001 on page 78.
(5) Place a new battery expiration date label on the ELT mounting frame cap or other visible
(6) Enter the pertinent battery replacement information in the logbook (i.e., aircraft records) and
: DO NOT USE CONTACT CLEANER ON ELT COMPONENTS. SUCH CHEMICAL AGENTS
CAN BE HIGHLY DESTRUCTIVE TO THE MOUNTING HARDWARE AND ELT HOUSING,
CAUSING CRACKING, FRACTURING AND OTHER DAMAGE.
necessary.
location.
NOTE
: The new label is supplied with the new battery pack.
fill out any other required documentation.
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+X
+Z
-Z
FWD
-Y
+Y
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-410-803
9. Helicopter Installations - Special Considerations
SUBTASK 25-62-13-990-001
A. Background
(1) There are few guidelines, aside from experience, regarding the best way to mount an ELT in
helicopters.
(2) Before the availability of multi-axis G-switch modules, manufacturers advised installing ELTs
with the sensitive axis pointing approximately 45° downward from the normal forward
direction of flight.
(a) This mounting attitude was adapted due to a combination of the directional sensing
limitations of a single-axis G-switch and the flight characteristics of helicopters.
(b) Mounting the ELT at this attitude and orientation is currently specified by CAR, Part 5,
Subpart 551.104.
(c) Experience has indicated this mounting angle tends to preload the G-switch and
“nuisance” activation can occur as a result of severe aircraft maneuvers, and abrupt
takeoffs and landings.
(3) ACR Electronics does not recommend installing ELTs designed with a single-axis G-switch in
helicopters due the limitations and issues cited above.
SUBTASK 25-62-13-990-002
B. Recommendations
(1) ACR Electronics recommends installation of the C406-N HM ELT in helicopters. The C406-N
HM ELT is equipped with a 5-axis G-switch module in addition to the usual primary G-switch,
which is oriented to the direction of flight. See "Figure 26. ELT Orthogonal Axes".
-X
Figure 26. ELT Orthogonal Axes
(2) The six-axis coverage of the C406-N HM design accommodates the flight characteristics of
helicopters, while allowing “normal” installation and eliminating or significantly reducing
“nuisance” ELT activations.
Page 81 of 109
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
0° TO 25°
FLIGHT
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-410-001
C. Orientation
(1) Mount the C406-N HM ELT parallel to the waterline of the fuselage, along the longitudinal
axis, with the direction-of-flight arrow on the ELT pointing forward. See "Figure 27.
Orientation of ELT for Helicopter Installations".
NOTE
: This is the orientation of the primary G-switch in the ELT.
(2) The ELT may be angled downward as much as 25°, if necessary.
NOTE
: Keep in mind, the steeper the mounting angle, the more pre-load on the primary G-
switch and the increased likelihood of “nuisance” activations.
(3) All other installation requirements contained herein are applicable and must be adhered to.
Figure 27. Orientation of ELT for Helicopter Installations
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
APPENDIX A – ELT REGISTRATION
TASK 25-62-13-990-801
1. Background Information
SUBTASK 25-62-13-990-001
A. Hex ID Code
(1) Each 406 MHz ELT is programmed with a unique hex ID code (i.e., registration code) that is
transmitted to the SAR satellite system. At a minimum, this code provides information
regarding:
(a) Unique aircraft or ELT identification,
(b) Country of origin, and
(c) Latitude and longitude position data, when connected to aircraft navigation system.
SUBTASK 25-62-13-990-002
B. Reason for Registration
(1) ELT registration aids the Rescue Coordination Center (RCC) in determining if an actual
emergency exists by accessing a database containing the registration information, which
facilitates inquiries as to the whereabouts of the aircraft, existence of a flight plan, etc.
(a) Owner’s name,
(b) Address,
(c) Telephone number,
(d) Aircraft type, and registration number.
SUBTASK 25-62-13-990-003
C. Registration Information Resources
(1) Refer to COSPAS-SARSAT documents G.005 and S.007 for information regarding ELT
programming and registration. These documents are available at www.cospas-sarsat.org.
25-62-13
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-990-802
2. Registration
SUBTASK 25-62-13-990-001
A. Responsibility
(1) It is the responsibility of the aircraft owner to register the ELT.
(a) If an ELT is moved to a different aircraft (i.e., an aircraft other than the one it was
originally installed on), and/or the aircraft is registered in a new country, the ELT must
be re-registered.
(b) If the aircraft is registered in a new country, the ELT must be re-registered.
(c) The product label must re-marked with the new HEX ID code to indicate new
programming, if applicable.
SUBTASK 25-62-13-990-002
B. Required Information
(1) The following information is required when registering an ELT:
(a) The unique Hex ID code printed on the ELT product label,
(b) The information listed in SUBTASK 25-62-13-990-003 on page 83.
(2) The information (i.e., address, telephone number, etc.), filed as part of the registration
process, should be kept up to date.
25-62-13
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-990-003
C. Where to Register
(1) In the United States, the National Oceanic and Atmospheric Administration (NOAA) is the
registration agency.
(2) Specific registration web sites and information may be found at:
(a) The Artex products web site at www.acrartex.com, which has links to on-line registration
sites and also a link to registration forms and instructions for a number of countries.
(b) An ELT may also be registered in the United States by going directly to the NOAA ELT
registration web site at www.beaconregistration.noaa.gov.
NOTE
: NOAA may also be contacted by mail at:
US MAIL ONLY FEDEX OR UPS ONLY
SARSAT Beacon Registration SARSAT Beacon Registration
NSOF, E/SPO53 NSOF, E/SPO53
1315 East West Highway 4231 Suitland Road
Silver Spring, MD 20910-9684 Suitland, MD 20746-4304
or by phone at 1-888-212-7283 or 301-817-4565.
(3) In other countries, the national civil aviation authority in the applicable country should be
contacted to obtain registration information.
25-62-13
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
TO REMOTE
SWITCH, ETC.
STRAIN RELIEF
PROGRAMMING ADAPTER
ELT MATING PLUG
ASSEMBLED VIEW
POTTED AREA
WIRE PATH
REAR VIEW
NOTE: ORIENT PA AS SHOWN AT INSTALLATION
TO PREVENT MOISTURE ACCUMULATION.
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
APPENDIX B – PROGRAMMING ADAPTER OPTION
TASK 25-62-13-870-801
1. Description and Operation
SUBTASK 25-62-13-870-001
A. Purpose
(1) The Programming Adapter (PA) is a C406-N Series ELT option that provides the means to
reprogram the ELT automatically every time the PA determines a new ELT with different
programming has been placed in an aircraft.
(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.
SUBTASK 25-62-13-870-002
B. Physical Description
(1) The PA is housed in a backshell extension designed for use with the remote switch harness
(2) The PA circuitry is encapsulated in the backshell extension and has six wires, with pre-installed
(3) A wire path through the backshell allows passage of the remote switch wires and other wires
22-position plug that mates with the ELT.
contact sockets, that exit the rear of the PA. See "Figure 28. Programming Adapter".
associated with ELT installation.
Figure 28. Programming Adapter
25-62-13
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-870-003
C. PA Programming
CAUTION
(1) The PA may be programmed with any aircraft ID [i.e., 24-bit address or registration number
(2) The 453-5078 PA is available from ACR Electronics pre-programmed with an aircraft ID.
(3) An alternative version of the PA (453-5068) is available unprogrammed (blank).
(4) Either version of the PA can be programmed in the field. Contact ACR Electronics for the
SUBTASK 25-62-13-870-004
D. Operation
(1) PA operation is automatic.
(2) The ELT is reprogrammed with aircraft ID information when +28 VDC aircraft power is applied
: 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. SEE
APPENDIX A – ELT REGISTRATION ON PAGE 83.
(tail number)].
hardware and software required to program the PA.
to the ELT.
25-62-13
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-450-801
2. Installation and Test
SUBTASK 25-62-13-450-001
A. Wiring
(1) Coordinate installation of the PA with installation of the remote switch harness ELT plug. Refer
to SUBTASK 25-62-13-450-002 on page 72.
(2) If the PA is undergoing installation on an aircraft with an existing ELT and remote switch
harness, perform the following procedure, otherwise proceed to Step (3):
(a) Loosen the strain relief clamp and unscrew the strain relief from the plug body.
(b) Remove the wiring from the ELT mating plug by extracting the contact sockets using
extraction tool MS27495R22MS, or equivalent.
(c) Remove the jumper from Pin 3 and Pin 4.
(d) Remove the sealing grommet plugs and empty contact sockets from Pin locations 1, 2,
15, and 16.
(3) Loop the PA wires back through the wire path such that they exit at the front of the PA. See
"Figure 28. Programming Adapter”, on page 86.
(4) Terminate the contact sockets of the six PA wires in the remote switch harness ELT plug using
insertion tool MS27495A22MS, or equivalent. See "Figure 29. Programming Adapter Interface
Wiring Diagram”, on page 88.
ELT
PLUG
5
17
7
6
9
8
18
SEE FIGURE 21:
REMOTE SWITCH
HARNESS WIRING
DIAGRAM
PROGRAMMING
ADAPTER
BROWN
RED
YELLOW
GREEN
ORANGE
BLACK
NOTE: GROUND STRAIN RELIEF TO AIRFRAME
AS CLOSE TO ELT AS POSSIBLE.
12
13
19
20
22
10
11
14
21
DDCS
3
4
+5VDNGL
1
BDIN
BDCLK
2
15
BDOUT
DGND
16
Figure 29. Programming Adapter Interface Wiring Diagram
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
(5) Feed the remote switch harness wires and other wires associated with the ELT installation
through the strain relief.
NOTE
: Slide heat shrink tubing of suitable size over the wires, if desired. The diameter of the
tubing must be large enough to accommodate the PA wire loop the extends back
beyond the strain relief clamp.
(6) Feed the remote switch harness wires and other wires associated with the ELT installation
through the PA wire path.
(7) Terminate the remote switch harness wires and other wires associated with the ELT
installation in ELT plug in accordance with SUBTASK 25-62-13-450-002 on page 72.
SUBTASK 25-62-13-450-002
B. Assembly
CAUTION
(1) Screw the PA body (i.e., backshell extension) onto the ELT plug, taking care not to twist the
(2) Shrink the heat shrink tubing, if installed.
(3) Screw the strain relief onto the backshell extension.
(4) Tighten the strain relief clamp.
(5) Verify the strain relief is grounded to the airframe in accordance with SUBTASK 25-62-13-450-
: ORIENT THE PA BODY TO THE PLUG SUCH THAT THE WIRE PATH IS AT THE
BOTTOM. THIS ORIENTATION PREVENTS MOISTURE BUILDUP IN THE PA AND
AROUND THE BACK OF THE PLUG.
wires while rotating the backshell extension coupling. See "Figure 28. Programming Adapter”,
on page 86, for PA body orientation.
NOTE
: Apply finger pressure in the center of the ELT plug face to prevent it from rotating
and twisting the wires while tightening the coupling.
008 on page 74.
25-62-13
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
PROGAMMING
ADAPTER
REMOTE SWITCH
TO ANTENNA
ARINC 429, POWER,
GROUND, ETC.
ELT
PROTECTIVE
TOP COVER
MOUNTING FRAME
CAP ASSEMBLY
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-450-003
C. Installation
(1) See "Figure 30. Programming Adapter Installation".
(2) Install the PA assembly on the ELT in the same manner that the remote switch harness ELT
plug is normally coupled to the ELT receptacle. See SUBTASK 25-62-13-410-001 on page 76.
Figure 30. Programming Adapter Installation
SUBTASK 25-62-13-750-001
D. Aircraft ID Verification Test
(1) Apply +28 VDC power to the ELT. The ELT is not activated, only the +28 VDC power source
for the ELT is active, which initiates ELT reprogramming. Refer to Table 6 on page 50 if a
long/short 2-flash error code is displayed on the ELT status LED when power is applied.
(2) Disconnect the antenna coax cable at the ELT.
(3) Read the ELT message following the instructions in SUBTASK 25-62-13-750-009 on page 47.
(4) Reregister the ELT, if necessary, in accordance with the instructions in Appendix A – ELT
Registration on page 83.
(5) Remark the ELT product label with the new hex ID code and country of registry, as applicable.
See Appendix A – ELT Registration on page 83.
THIS IS A BLANK PAGE
25-62-13
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
ON
ELT
ELT
ARM
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
APPENDIX C – REMOTE SWITCH CONTROL PANEL OPTION
TASK 25-62-13-870-801
1. Description and Operation
SUBTASK 25-62-13-870-001
A. Purpose
(1) The G737 control panel (453-0161) is an optional replacement for the standard 345-6196-04
cockpit remote switch.
(2) This panel is principally for use in Boeing aircraft, which are pre-wired for this type of ELT
control panel. However, this appendix does provide wiring instructions for aircraft that are not
provisioned for this type of panel.
(3) These instructions include installation of a buzzer modified for use with the Boeing
configuration. In addition, instructions and a wiring diagram are provided for installing the
standard buzzer with the remote switch control panel. The difference between the two buzzer
options is the means by which the buzzer is activated and controlled.
(a) The modified buzzer is activated by the “ELT ON” circuit and powered by the aircraft
battery.
(b) The standard buzzer is controlled and powered by the ELT.
SUBTASK 25-62-13-870-002
B. Control Panel Description
(1) The control panel is backlit panel comprised of an ELT status indicator light and a control
switch, which allows an operator to manually activate the ELT for testing and reset (i.e.,
deactivate) the ELT. See "Figure 31. Remote Switch Control Panel Assembly".
NOTE
: The ELT CANNOT be disarmed or disabled from the cockpit. Cockpit operation is
limited to deactivating the ELT (i.e., reset) or manually activating the ELT.
Figure 31. Remote Switch Control Panel Assembly
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-870-003
C. Modified Buzzer Description
(1) A buzzer (130-4005), modified for compatibility with Boeing ELT provisions, provides an
audible alert when the ELT is active. The buzzer is similar in appearance with the 130-4004
buzzer. See "Figure 4. Buzzer”, on page 31.
(2) This buzzer is used in lieu of the 130-4004 buzzer used with the standard remote switch
installation.
SUBTASK 25-62-13-870-003
D. Operation
(1) The remote switch control panel switch operates and controls the ELT in the same manner as
the standard remote switch. See the operating procedures contained in TASK 25-62-13-870803 on page 33.
(2) The indicator light on the panel illuminates and stays on steady when the ELT is activated,
unlike the standard remote switch LED, which flashes when the ELT is active.
25-62-13
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
CONTROL PANEL
ARTEX AIRCRAFT SUPPLIES,INC
ON
ELT
ELT
ARM
5.74
(146)
5.365
(136.3)
0.185 (4.7)
0.555 (14.1)
1.125 (28.6)
2.24
(57)
4.969
+0.030
-0.000
(126.2 +0.8/-0.0)
3.000 ±0.015
(76.2 ±0.4)
1.13 (29) MAX.
0.69 (18) MAX.
0.37 (9) MIN.
0.06 (2) MIN.
2.094
+0.030
-0.000
(53.2+0.8/-0.0)
FRONT VIEW
TOP VIEW
BACK VIEW
453-0161
DIMENSIONS IN INCHES (MM)
FASTENERS (4)
280-0010
(DZUS PA35-38X1426)
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-450-801
2. Remote Switch Control Panel Installation
SUBTASK 25-62-13-450-001
A. Location
(1) The control panel must be mounted in the cockpit where the pilot can easily reach the switch
and see the status light.
NOTE
: In most cases, panel space and wiring have been pre-provisioned by the aircraft
manufacturer for the control panel; however, location and installation requirements
are defined for installations in aircraft not pre-provisioned for this control panel.
(2) The panel assembly requires a space approximately 5.74 x 2.24 in. (146 x 57 mm) on the
panel or console surface, with a depth of 3.00 in. (77 mm), excluding room for the harness
connection. See "Figure 32. Cockpit Remote Switch Panel Outline and Dimensions".
Figure 32. Cockpit Remote Switch Panel Outline and Dimensions
SUBTASK 25-62-13-450-002
B. Installation
(1) Provide an opening in the instrument panel or other mounting location which meets the
dimensional requirements shown in "Figure 32. Cockpit Remote Switch Panel Outline and
Dimensions".
(2) Mount Dzus rails on the sides of the opening, if necessary. See "Figure 32. Cockpit Remote
Switch Panel Outline and Dimensions" for rail center line dimensions.
(3) Install the remote switch panel assembly.
NOTE
: Step (3) may be completed after wiring is completed on the ELT end and the harness
plug has been plugged into the panel assembly, in accordance with the requirements
of SUBTASK 25-62-13-450-006 on page 98. If such is the case, perform a fit check at
this time.
(4) Apply a “For Aviation Emergency Use Only/Unauthorized Use Prohibited” placard as close to
the switch as practical, if required.
NOTE
: This placard is recommended for installations on aircraft that are not pre-placarded
for remote ELT control. If desired, the placard (591-0428) may be ordered from ACR
Electronics.
25-62-13
Page 93 of 109
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
1.68
(43)
1.75
(45)
1.115
(28.3)
PANEL MOUNTING NUT
0.445
(11.3)
FRONT VIEW
SIDE VIEW (Rotated 90°)
Dimensions are
reference only
130-4005
HORN MOD ELT BUZZER
+
BLUE
RED
YELLOW
BLACK
RTV
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-450-802
3. Modified Buzzer Installation
SUBTASK 25-62-13-450-001
A. Location
CAUTION
: PLACING THE BUZZER IN THE COCKPIT IS NOT RECOMMENDED DUE TO THE
POTENTIAL FOR DISTRACTION. THE BUZZER PRODUCES A LOUD, SIREN-TYPE
SOUND WHEN THE ELT IS ACTIVATED. SINCE THE BUZZER OPERATES IN TANDEM
WITH THE COCKPIT LED, IT WOULD ONLY SERVE AS A REDUNDANT WARNING
INDICATOR IN THE COCKPIT.
(1) Select a suitable location for the buzzer.
NOTE
: The buzzer may be located anywhere in the aircraft; however, the recommended
location is near the ELT, as the buzzer is loud enough to be heard outside the aircraft
when the engine(s) is not running. When the engine(s) is running, the LED on the
cockpit remote switch panel will warn the pilot the ELT is active.
SUBTASK 25-62-13-450-002
B. Installation
(1) Fabricate a bracket suitable for supporting the buzzer. See "Figure 33. Modified Buzzer Outline
and Dimensions".
NOTE
: Refer to the aircraft manufacturer’s written instructions or AC 43.13-2, as applicable,
for approved bracket fabrication and installation methods.
Figure 33. Modified Buzzer Outline and Dimensions
(2) Attach the bracket to the airframe such that the buzzer is adequately supported and does not
show any significant evidence of distorting the airframe skin.
(3) Install the buzzer in the bracket.
(a) Remove the panel mounting nut and insert the buzzer in the bracket.
(b) Install the panel mounting nut and tighten it securely.
25-62-13
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DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
TASK 25-62-13-450-803
4. Wiring and Test
SUBTASK 25-62-13-450-001
A. Remote Switch Control Panel Wiring Fabrication
(1) In most cases, Boeing aircraft have been provisioned with wiring for connecting the ELT to the
control panel. Install a remote switch control panel harness in accordance with the following
instructions ONLY if wiring has not been provided and/or spare wires are not available.
NOTE
: Terminate the wiring in accordance with "Figure 34. Remote Switch Control Panel
Wiring Diagram (130-4005 Modified Buzzer)”, on page 96, and the procedures
herein.
(2) Fabricate a 4-wire harness long enough to reach from the ELT to the remote switch control
panel, allowing enough slack to provide a drip loop at the ELT end and a service loop at the
remote switch panel end.
NOTE
: A 5 or 6-wire harness may be necessary if a ground wire is connected between ELT
Pin 11 and remote switch panel Pin 9; and/or ELT Pin 2 must be connected to remote
switch panel Pin 8 if a horn is not installed. See "Figure 34. Remote Switch Control
Panel Wiring Diagram (130-4005 Modified Buzzer)”, on page 96.
(a) Strip approximately 0.15 in. (3 mm) of insulation from the ends of each of the harness
wires.
(b) Dress and tin the bare wires to prevent the strands from fraying during terminal
crimping operations.
(3) Fabricate the additional wires needed to connect the remote switch panel; referring to "Figure
34. Remote Switch Control Panel Wiring Diagram (130-4005 Modified Buzzer)”, on page 96,
and the specific aircraft wiring diagrams to determine appropriate connection points.
(a) Pin 3 to the selected +28V aircraft power source.
(b) Pin 4 to the selected +28V/+16V aircraft power source.
(c) Pin 6 to the Master Caution +17V circuit.
(d) Pin 8 to the BLUE wire on the buzzer (i.e., horn).
(e) Pin 9 to aircraft ground.
(f) Pin 10 to the Master Caution Pulse circuit.
(g) Pin 11 to the Master Caution Steady State circuit.
(h) Pin 12 to the Master Lighting Test circuit.
(i) Pin 13 to the 5VAC Lighting circuit.
(j) Pin 14 to aircraft ground.
(k) Prepare the wires as described in Steps (2)(a) and (2)(b).
25-62-13
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6
7
8
5
7
LIGHT
ELT ON
RST 1
RST 2
EXTERNAL ON
G-SWITCH LOOP
G-SWITCH LOOP
GROUND
+5VDNGL
DDCS
9
8
12
13
19
20
NC
NC
NC
22
10
21
3
4
1
2
15
16
14
11
18
PINS 3 AND 4 MUST BE JUMPERED UNLESS OPTIONAL
PROGRAMMING ADAPTER (PA) IS INSTALLED. SEE APPENDIX B
FOR PA INSTALLATION DETAILS (PINS 1, 2, 3, 4, 15, AND 16).
17
5
A
B
ARINC 429 INPUT
TWISTED PAIR
(SHIELDED)
ELT
PLUG
REMOTE SWITCH
CONTROL PANEL
+28 VDC
AIRCRAFT POWER
SWITCHABLE POWER SOURCE WITH 1-AMP BREAKER OR
SLO-BLO FUSE. MAXIMUM CURRENT DRAW IS 120 mA.
USE MINIMUM
22 AWG WIRE
1
2
2
2
4
4
5
5
ENSURE ALL GROUNDS ARE COMMON. IF AIRCRAFT GROUND
INTEGRITY BETWEEN THE ELT AND REMOTE SWITCH PANEL
CANNOT BE GUARANTEED, REMOTE SWITCH PANEL PIN 9
TO ELT PIN 11 (OR GROUND POINT COMMON TO ELT PIN 11
AS CLOSE TO ELT AS POSSIBLE). OTHERWISE, THE CONNECTION
BETWEEN PIN 9 AND PIN 11 IS OPTIONAL.
USE OF SHIELDED CABLE IS RECOMMENDED, PARTICULARLY FOR
LONG CABLE RUNS AND WHERE EMI IS A CONCERN.
3
3
CONNECT STRAIN RELIEF TO AIRCRAFT GROUND AS CLOSE TO
ELT AS POSSIBLE.
ELT MATING PLUG
(CIRCULAR CONNECTOR)
PIN INSERTION END
1
22
21
AIRCRAFT GROUND
HORN
1
23
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
PIN INSERTION END OF MS24266R16B2457
CONNECTOR FOR REMOTE SWITCH CONTROL
PANEL ASSEMBLY. HOLE NUMBERING SAME AS
INSCRIBED ON ACTUAL CONNECTOR
15
2
4+28V/+16V
+28V
AURAL CHIME
MASTER CAUTION +17V
MASTER CAUTION PULSE
DC GROUND
MASTER CAUTION STEADY STATE
MASTER LIGHTING TEST
5VAC LIGHTING
AC GROUND
6
10
9
11
3
1
12
13
14
RED
BLACK
YELLOW
BLUE
AIRCRAFT BATTERY
+28 VDC
NOTE: IF HORN IS NOT USED, CONNECT
REMOTE SWITCH CONTROL PANEL PIN 8
DIRECTLY TO ELT PIN 2.
NC
NC
1
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
Figure 34. Remote Switch Control Panel Wiring Diagram (130-4005 Modified Buzzer)
25-62-13
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ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-450-002
B. Modified Buzzer Wiring Fabrication
(1) Fabricate the following wires, which correspond with the wires on the buzzer:
NOTE
: Use appropriately coded wires, such that the wires can be identified and terminated
at the appropriate locations.
(a) YELLOW wire to harness ELT receptacle.
(b) BLACK wire to aircraft ground.
(c) RED wire to +28 VDC aircraft battery power source.
(d) BLUE wire to Pin 8 of the remote switch panel connector.
(e) Strip approximately 0.15 in. (3 mm) of insulation from the ends of each of the harness
wires.
(f) Dress and tin the bare wires to prevent the strands from fraying during terminal
crimping operations.
SUBTASK 25-62-13-450-003
C. Remote Switch Control Panel Wiring Installation
(1) Terminate the remote switch control panel end of all wires in an MS24266R16B24S7
connector in accordance with the aircraft manufacturer’s written instructions or AC43.13-1, as
applicable. See "Figure 34. Remote Switch Control Panel Wiring Diagram (130-4005 Modified
Buzzer)”, on page 96.
NOTE
: Identify the wires and connector pin relationships, such that the wiring can be
terminated at the appropriate locations at the ELT mating plug.
(2) Install the remote switch control panel harness as follows:
(a) Bundle the wiring into a complete harness, with breakouts as appropriate, such that the
wiring can be properly supported and attached to the airframe. Refer to the aircraft
manufacturer’s written instructions or AC 43.13-1, Chapter 11, § 9 through 12, as
applicable.
(b) Route the wire bundle through the airframe.
(c) Support the wire bundle 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.
(3) Terminate the aircraft side of the wires fabricated in Step (3) at the appropriate connection
points in accordance with the aircraft manufacturer’s written instructions or AC 43.13-1, as
applicable. See "Figure 34. Remote Switch Control Panel Wiring Diagram (130-4005 Modified
Buzzer)”, on page 96, and aircraft wiring diagrams.
(4) Refer to TASK 25-62-13-450-805 on page 67 for applicable subtask instructions at the ELT
end of the remote switch control panel harness and other wiring and connection requirements
related to the ELT installation.
25-62-13
Page 97 of 109
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-450-004
D. Modified Buzzer Wiring Installation
(1) Splice the wires fabricated in SUBTASK 25-62-13-450-002 on page 97, to the buzzer wires in a
manner acceptable to the aircraft manufacturer, or as described in AC 43.13-1, Paragraph 11167, as applicable.
(2) Route the buzzer wiring through the airframe.
(3) 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.
(4) Terminate the buzzer wires in accordance with "Figure 34. Remote Switch Control Panel
Wiring Diagram (130-4005 Modified Buzzer)”, on page 96, as follows:
(a) BLUE wire to remote switch control panel connector Pin 8. Coordinate with SUBTASK 25-
62-13-450-003 on page 97, Step (1).
(b) YELLOW wire to ELT mating plug Pin 7. Coordinate with SUBTASK 25-62-13-450-002 on
page 72.
(c) RED wire to the +28 VDC aircraft battery power source.
(d) BLACK wire to aircraft ground. See SUBTASK 25-62-13-450-008 on page 74.
SUBTASK 25-62-13-450-005
E. Standard Buzzer Installation
(1) See "Figure 35. Remote Switch Control Panel Wiring Diagram (130-4004 Buzzer)”, on
page 99.
(2) Fabricate buzzer wiring in accordance with SUBTASK 25-62-13-450-001 on page 67.
(3) Terminate the buzzer wires in the remote switch harness ELT plug in accordance with
SUBTASK 25-62-13-450-002 on page 72.
(4) Install the buzzer in accordance with SUBTASK 25-62-13-450-002 on page 94.
(5) Terminate the buzzer wires to the buzzer in accordance with SUBTASK 25-62-13-450-008 on
page 74.
SUBTASK 25-62-13-450-006
F. Remote Switch Control Panel Final Installation
(1) Connect the remote switch control panel harness plug the remote switch control panel.
(2) Install the remote switch control panel assembly, referring to SUBTASK 25-62-13-450-002 on
page 93.
25-62-13
Page 98 of 109
MAR 1/13
6
7
8
5
7
LIGHT
ELT ON
RST 1
RST 2
EXTERNAL ON
G-SWITCH LOOP
G-SWITCH LOOP
GROUND
HORN POWER
HORN GROUND
+5VDNGL
DDCS
9
8
12
13
19
20
NC
NC
NC
22
10
21
3
4
1
2
15
16
14
11
18
PINS 3 AND 4 MUST BE JUMPERED UNLESS OPTIONAL
PROGRAMMING ADAPTER (PA) IS INSTALLED. SEE APPENDIX B
FOR PA INSTALLATION DETAILS (PINS 1, 2, 3, 4, 15, AND 16).
17
5
A
B
ARINC 429 INPUT
TWISTED PAIR
(SHIELDED)
ELT
PLUG
REMOTE SWITCH
CONTROL PANEL
+28 VDC
AIRCRAFT POWER
SWITCHABLE POWER SOURCE WITH 1-AMP BREAKER OR
SLO-BLO FUSE. MAXIMUM CURRENT DRAW IS 120 mA.
USE MINIMUM
22 AWG WIRE
1
2
2
2
4
4
5
5
+
ENSURE ALL GROUNDS ARE COMMON. IF AIRCRAFT GROUND
INTEGRITY BETWEEN THE ELT AND REMOTE SWITCH PANEL
CANNOT BE GUARANTEED, REMOTE SWITCH PANEL PIN 9
TO ELT PIN 11 (OR GROUND POINT COMMON TO ELT PIN 11
AS CLOSE TO ELT AS POSSIBLE). OTHERWISE, THE CONNECTION
BETWEEN PIN 9 AND PIN 11 IS OPTIONAL.
USE OF SHIELDED CABLE IS RECOMMENDED, PARTICULARLY FOR
LONG CABLE RUNS AND WHERE EMI IS A CONCERN.
3
3
CONNECT STRAIN RELIEF TO AIRCRAFT GROUND AS CLOSE TO
ELT AS POSSIBLE.
ELT MATING PLUG
(CIRCULAR CONNECTOR)
PIN INSERTION END
1
22
21
AIRCRAFT GROUND
HORN
1
23
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
PIN INSERTION END OF MS24266R16B2457
CONNECTOR FOR REMOTE SWITCH CONTROL
PANEL ASSEMBLY. HOLE NUMBERING SAME AS
INSCRIBED ON ACTUAL CONNECTOR
15
2
4+28V/+16V
+28V
AURAL CHIME
MASTER CAUTION +17V
MASTER CAUTION PULSE
DC GROUND
MASTER CAUTION STEADY STATE
MASTER LIGHTING TEST
5VAC LIGHTING
AC GROUND
6
10
9
11
3
1
12
13
14
1
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
Figure 35. Remote Switch Control Panel Wiring Diagram (130-4004 Buzzer)
25-62-13
Page 99 of 109
MAR 1/13
ACR ELECTRONICS, INC / ARTEX PRODUCTS
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-N (453-5060), C406-N HM (453-5061)
SUBTASK 25-62-13-750-001
G. Remote Switch Control Panel Functional Test
(1) Coordinate functional testing of the remote switch control panel with the post-installation ELT
testing requirements in SUBTASK 25-62-13-750-001 on page 77.
(2) Place the remote switch in the “ON” position.
(3) Verify the cockpit remote switch panel light illuminates immediately. If the light fails to
illuminate immediately and stay on steady, recheck the interface wiring and connections
between the ELT and the remote switch control panel.
(4) Place the remote switch in the “ARM” position.
(5) Verify the ELT deactivates.
25-62-13
Page 100 of 109
MAR 1/13
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