1、 _ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising ther
2、efrom, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2017 SAE International All rights reserved. No part of this
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4、70 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/standards.sae.org/ARP60493 AEROSPACE RECOMMENDED PRACTICE ARP60493 Issued 2017-10 Guide to Civil Aircraft Electr
5、omagnetic Compatibility (EMC) RATIONALE This document provides guidance for demonstrating that electrical and electronic systems installed on civil aircraft can operate without adversely affecting, or without being affected by, the operation of other aircraft electrical and electronic systems. It in
6、cludes guidance for defining appropriate electromagnetic compatibility requirements for the electrical and electronic equipment. It also includes methods for aircraft electromagnetic compatibility analysis and tests. TABLE OF CONTENTS 1. SCOPE 4 1.1 Purpose . 4 2. REFERENCES 4 2.1 Applicable Documen
7、ts 4 2.1.1 EUROCAE Publications 4 2.1.2 RTCA Publications 5 2.1.3 U.S. Military Specifications and Standards . 5 2.1.4 FAA Publications . 5 2.2 Abbreviations 6 2.3 Acronyms 6 3. AIRCRAFT EMC CONCEPTS 6 3.1 Inter-System EMC . 7 3.2 Characteristics of Electromagnetic Emissions 7 4. AIRCRAFT EMC REGULA
8、TIONS AND GUIDANCE . 9 4.1 Aircraft EMC Regulations 9 4.2 Regulatory Guidance on Electromagnetic Compatibility . 10 5. DESIGN CONSIDERATIONS . 11 5.1 General Equipment Qualification Process 12 5.2 General Installation Qualification Process 12 6. AIRCRAFT EMC PROCESS 12 6.1 New or Derivative Aircraft
9、 and Complex Change to Existing Aircraft . 14 6.2 Simple Change to Existing Aircraft . 17 6.3 EMC Certification Plan 20 6.4 Establishing Pass Criteria . 20 6.5 Documentation 21 6.6 Continued Airworthiness . 21 SAE INTERNATIONAL ARP60493 Page 2 of 54 7. EQUIPMENT LEVEL EMC DEMONSTRATION . 21 7.1 Purp
10、ose of Equipment Level EMC Demonstrations . 22 7.2 Equipment Approval 24 7.3 Equipment Qualification Tests and Standards 24 7.3.1 Equipment Qualification Tests 24 7.3.2 Equipment EMC Test Standards 25 7.4 Equipment Level Requirement Considerations 27 7.4.1 Criticalities . 27 7.4.2 Installation Locat
11、ion 28 7.4.3 Installation Details . 28 7.4.4 Operating Modes . 28 7.4.5 Test Simulation and Monitoring Equipment 29 7.5 Equipment Level Test Acceptance Criteria . 29 7.5.1 Emissions Acceptance Criteria . 29 7.5.2 Susceptibility Acceptance Criteria . 31 7.6 Procedure Content 31 7.7 Report Content 32
12、7.8 Similarity Assessment . 33 7.8.1 Hardware Considerations 33 7.8.2 Software Considerations . 34 8. AIRCRAFT LEVEL EMC DEMONSTRATION 34 8.1 Purpose of Aircraft Level EMC Demonstrations . 34 8.2 Aircraft Ground Test Setup . 39 8.3 Aircraft Source/Victim Ground Test 39 8.3.1 Source/Victim Test Matri
13、x . 39 8.3.2 Victim Equipment Monitoring 40 8.3.3 Equipment Designation . 40 8.3.4 Operating Modes . 40 8.3.5 Aircraft Power Considerations 40 8.3.6 Electro-Explosive Device EMC Demonstration . 40 8.3.7 Source and Victim Test Process . 41 8.4 Non-Instrumented Radio Ground Test 41 8.5 Instrumented Ra
14、dio Ground Test 42 8.6 Aircraft EMC Flight Test 43 8.7 Aircraft Functional Flight Test . 44 8.8 Aircraft EMC Analysis and Computation . 44 8.8.1 Identify Selected Sources and Victims 45 8.8.2 Develop an Analysis Plan . 45 8.8.3 Calculate Transfer Functions from Sources to Victims . 46 8.8.4 Calculat
15、e Coupled Response Levels 46 8.8.5 Assure EMC Compliance 47 8.9 Aircraft EMC Similarity Assessment . 47 8.10 Software Changes . 47 8.11 Telecommunication Authority Licensing and Calibration 47 9. NOTES 48 9.1 Revision Indicator 48 Figure 1 Example of RF emission (radiated or conducted) . 8 Figure 2
16、Scope of change versus level of rigor . 13 Figure 3 Determining scope of change . 14 Figure 4 Flow diagram for new derivative or complex change to existing aircraft 16 Figure 5 Flow diagram for simple change to existing aircraft 19 Figure 6 Discrete radiated RF emissions example . 30 Figure 7 Broad
17、spectrum radiated RF emissions example . 30 Figure 8 Aircraft EMC demonstration flow 36 SAE INTERNATIONAL ARP60493 Page 3 of 54 Table 1 Characteristics of electromagnetic emissions . 8 Table 2 Potential coupling path should be considered 9 Table 3 Stringent immunity requirements - equipment with maj
18、or and minor failures . 18 Table 4 Scope of equipment EMC qualification . 23 Table 5 Recommended RTCA/DO-160 and EUROCAE/ED-14 equipment EMC qualification tests 25 Table 6 Approaches for aircraft EMC demonstration . 37 Table 7 Typical decision thresholds and analyzer settings 43 SAE INTERNATIONAL AR
19、P60493 Page 4 of 54 1. SCOPE This guide provides detailed information, guidance, and methods for demonstrating electromagnetic compatibility (EMC) on civil aircraft. This guide addresses aircraft EMC compliance for safety and functional performance of installed electrical and electronic systems. The
20、 EMC guidance considers conducted and radiated electromagnetic emissions and transients generated by the installed electrical and electronic systems which may affect other installed electrical and electronic systems on the aircraft. Application of appropriate electrical and electronic equipment EMC
21、requirements are discussed. Methods for aircraft EMC tests and analysis are described. This guide does not address aircraft compatibility with the internal electromagnetic environments of portable electronic devices (PED) or with the external electromagnetic environments, such as high-intensity radi
22、ated fields (HIRF), lightning, and precipitation static. 1.1 Purpose This document provides technical guidance that can be used to demonstrate that aircraft electrical and electronic systems are electromagnetically compatible with other aircraft systems, that is, inter-system electromagnetic compati
23、bility. This guide may be applied to new aircraft and modifications to existing aircraft. The electromagnetic compatibility demonstrations apply to all aircraft electrical and electronic systems, including power distribution systems, electrical generating systems, electronic engine control systems,
24、electronic flight control systems, navigation, communication, flight reference systems, and passenger entertainment and convenience systems. The term systems refers to electrical and electronic equipment; interconnecting power, signal, and control wiring; indicators; control panels; sensors; and sof
25、tware. This document emphasizes the EMC demonstrations required to achieve appropriate aircraft safety, but can also be used to demonstrate acceptable performance for any aircraft electrical and electronic system. The approach for achieving aircraft EMC includes appropriate system design, qualificat
26、ion, and installation. This document only addresses aircraft inter-system electromagnetic compatibility. For other electromagnetic environments, reference the appropriate regulations, requirements, standards, and guides. To avoid confusion with other electromagnetic environments and to provide a mea
27、ns of readily identifying the engineering associated with these regulations, the term electromagnetic compatibility will be used along with the abbreviation EMC in this document. Prior to the publication of this document, there were no standard methods defined for demonstrating electromagnetic compa
28、tibility on civil aircraft, resulting in a wide range of compliance techniques. This document standardizes the EMC demonstration approaches and methods to ensure common application of regulations, consistent evaluation of the results, and confidence in the overall safety of the aircraft. 2. REFERENC
29、ES The following publications form a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. The applicable issue of other publications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this do
30、cument and references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 2.1 Applicable Documents 2.1.1 EUROCAE Publications Available from EUROCAE Secretariat, 102 rue
31、 Etienne Dolet, 92240 Malakoff, France, Tel: +33 1 40 92 79 30, . EUROCAE/ED-14G, “Environmental Conditions and Test Procedures for Airborne Equipment”, May 2011 EUROCAE/ED-118, “Report on Electromagnetic Compatibility Between Passenger Carried Portable Electronic Devices (Peds) and Aircraft Systems
32、”, November 2003 SAE INTERNATIONAL ARP60493 Page 5 of 54 2.1.2 RTCA Publications Available from RTCA, Inc., 1150 18th Street, NW, Suite 910, Washington, DC 20036, Tel: 202-833-9339, www.rtca.org. RTCA/DO-160G, “Environmental Conditions and Test Procedures for Airborne Equipment”, December 8, 2010 RT
33、CA/DO-307, “Aircraft Design and Certification for Portable Electronic Device (PED) Tolerance”, October 11, 2007 RTCA/DO-313, “Certification Guidance for Installation of Non-Essential, Non-Required Cabin Systems and Equipment”, October 2, 2008 RTCA/DO-357, “User Guide: Supplement to DO-160G”, Decembe
34、r 16, 2014 RTCA/DO-363, “Guidance for the Development of Portable Electronic Devices (PED) Tolerance for Civil Aircraft”, December 15, 2016 2.1.3 U.S. Military Specifications and Standards Copies of these documents are available online at http:/quicksearch.dla.mil. MIL-STD-461G, “Requirements for th
35、e Control of Electromagnetic Interference Characteristics of Subsystems and Equipment”, December 11, 2015 MIL-STD-464C, “Electromagnetic Environmental Effects Requirements for Systems”, December 1, 2010 MIL-STD-704F, “Aircraft Electric Power Characteristics”, December 30, 2008 MIL-STD-810G, “Environ
36、mental Engineering Considerations and Laboratory Tests”, October 31, 2008 2.1.4 FAA Publications Available from Federal Aviation Administration, 800 Independence Avenue, SW, Washington, DC 20591, Tel: 866-835-5322, www.faa.gov. FAA Order 8100.4C, “Type Certification”, December 20, 2011 FAA Advisory
37、Circular 20-158A, “The Certification of Aircraft Electrical and Electronic Systems for Operation in the High-intensity Radiated Fields (HIRF) Environment”, May 30, 2014 FAA Advisory Circular 20-168, “Certification Guidance for Installation of Non-Essential, Non-Required Aircraft Cabin Systems sectio
38、ns (a)(1), (b), and (e) 14 CFR 23.1431, CS-23.1431, TCCA 523.1431 Electronic equipment; section (b) FAA 14 CFR 25, EASA CS-25, TCCA Chapter 525 14 CFR 25.1309, TCCA 525.1309 Equipment, systems, and installations; sections (a) and (e) CS-25.1309 Equipment, systems, and installations; sections (a)(1)
39、and (a)(2) 14 CFR 25.1353, CS-25.1353, TCCA 525.1353 Electrical equipment and installations; section (a) 14 CFR 25.1431, CS-25.1431, TCCA 525.1431 Electronic equipment; sections (c) and (d) 14 CFR 25.1707, CS-25.1707, TCCA 525.1707 Electrical Wiring Interconnection Systems (EWIS) section (b) FAA 14
40、CFR 27, EASA CS-27, TCCA Chapter 527 14 CFR 27.865, CS-27.865, TCCA 527.865 External loads; section (b)(3) 14 CFR 27.1309, CS27.1309, TCCA 527.1309 Equipment, systems, and installations; section (a) 14 CFR 27, CS-27 /Chapter 527 Appendix B Airworthiness Criteria for Helicopter Instrument Flight; sec
41、tion VIII. The basic equipment and installation must comply with 29.1431 FAA 14 CFR 29, EASA CS-29, TCCA Chapter 529 14 CFR 29.865, CS-29.865, TCCA 529.865 External loads; section (b)(3) 14 CFR 29.1309, CS-29.1309, TCCA 529.1309 Equipment, systems, and installations; section (a) and (g) 14 CFR 29.13
42、53, CS-1353, TCCA 529.1353 Electrical equipment and installations; section (a) 14 CFR 29.1431, CS-29.1431, TCCA 529.1431 Electronic equipment; section (b) 4.2 Regulatory Guidance on Electromagnetic Compatibility Early aviation authority guidance for aircraft EMC was very general, and in some cases i
43、neffective. For example, now cancelled FAA Advisory Circular 25-10, “Guidance for Installation of Miscellaneous, Non-Required Electrical Equipment”, included the following guidance: “Operate communications and navigation equipment on at least one low, high and mid-band frequency.” The electronic sys
44、tems used in aircraft now have potential sources of RF emissions from electronic oscillators and clocks that are very narrowband and stable. Therefore, operating multi-channel communication and navigation radio receivers at one low, high, and mid-band frequency would be unlikely to find radio interf
45、erence that occurs at a specific frequency. More recently, AC 20-168, “Certification Guidance for Installation of Non-Essential, Non-Required Aircraft Cabin Systems including the consideration of the worst-case installation configuration for all aspects of design, installation, operation, and mainte
46、nance. The systems and equipment should be designed and certified appropriate for the location in which they will be installed and operated on the aircraft. The aircraft size, type, passenger capacity, and mission will impact the systems and equipment operation and EMI. SAE INTERNATIONAL ARP60493 Pa
47、ge 13 of 54 5.1 General Equipment Qualification Process Electrical and electronic equipment and components should be designed and qualified to determine their appropriateness for all foreseeable conditions in which they will be installed and operated. Guidelines relating to proper category or severi
48、ty selection are given in Section 7. 5.2 General Installation Qualification Process Systems and equipment should be designed and installed on aircraft in a manner to minimize the susceptibility and any adverse effects on other systems by considering the aircrafts specific environment, systems config
49、urations, functions, malfunctions, discrepancies, and failure conditions. To mitigate the EMI and their adverse effects, adequate shielding, electrical interconnection wiring systems routing, separation, and segregation should be incorporated in design and installation of the electrical and electronic systems and equipment on the aircraft. In addition to complying with the applicable regulation
