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 theref
2、rom, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2010 SAE International All rights reserved. No part of this publication ma
3、y be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-4970 (outside US
4、A) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.orgSAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/ARP5583AAEROSPACERECOMMENDEDPRACTICEARP5583 REV. A Issued 2003-01 Revised 2010-06Superseding AR
5、P5583 (R) Guide to Certification of Aircraft in a High-IntensityRadiated Field (HIRF) EnvironmentRATIONALEThis revision incorporates changes throughout that are consistent with new Federal Aviation Administration HIRF certification regulations and certification guidance adopted in 2007. It also incl
6、udes revised test methods that were developed after the original release of this ARP. The organization of the ARP was revised to be consistent with the certification steps described in AC 20-158. Due to the extensive re-work and re-organization of this revision the standard change bar indications fo
7、r the changes are not shown, therefore, an R has been placed before the document title. TABLE OF CONTENTS 1. SCOPE 61.1 Purpose . 61.2 Aircraft and HIRF 62. REFERENCES 72.1 SAE International Publications 72.2 Other Publications . 72.3 Applicable Documents 82.3.1 Federal Aviation Administration Docum
8、ents . 82.3.2 Joint Airworthiness Authorities Documents 82.3.3 EASA Documents . 82.3.4 RTCA Publications 82.3.5 EUROCAE Documents . 82.4 Related Documents 92.4.1 U.S. Government Documents . 92.4.2 Military Standards . 92.5 Abbreviations 92.6 Acronyms 103. ELECTROMAGNETIC ENVIRONMENT 123.1 Environmen
9、t Development Process . 133.2 How the Environment was Computed 143.3 Fixed Wing Severe HIRF Environment . 143.3.1 Assumptions for the Calculation of the Fixed Wing Severe HIRF Environment . 163.3.2 Fixed Wing Severe HIRF Environment Tables . 173.4 Rotorcraft Severe HIRF Environment (HIRF Environment
10、 III) 173.4.1 Assumptions for the Calculation of the Rotorcraft HIRF Environment III . 193.4.2 HIRF Environment III (Rotorcraft Severe Environment) Tables . 193.5 HIRF Environment I (Certification HIRF Environment) . 203.5.1 Assumptions for the Calculation of the HIRF Environment I (Certification HI
11、RF Environment) . 203.5.2 HIRF Environment I (Certification HIRF Environment) Tables . 21Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE ARP5583A Page 2 of 1303.6 HIRF Environment II (Normal HIRF
12、 Environment) 223.6.1 Assumptions for the Calculation of the HIRF Environment II (Normal HIRF Environment) . 223.6.2 HIRF Environment II (Normal HIRF Environment) Tables 223.7 Internal Aircraft Environment 233.8 Aircraft Exposure to HIRF . 244. PRACTICAL DESIGN CONSIDERATIONS . 244.1 HIRF Environmen
13、t Reduction . 254.1.1 Coupling Mechanism/Frequency Bands . 254.1.2 Entry Points . 264.1.3 Design Options for HIRF Environment Reduction 274.1.4 Grounding . 274.1.5 Bonding . 284.1.6 Shielding . 284.1.7 Wire Shielding . 294.1.8 Filtering . 304.1.9 Fiber Optic Cables 324.1.10 Maintenance and Design 33
14、4.2 Electrical/Electronic System Robustness . 334.2.1 System Architecture Considerations . 334.2.2 Hardware Design 344.2.3 Circuit Design Measures . 344.2.4 Analog Devices . 344.2.5 Digital Devices 354.2.6 Software Design 354.3 Empirical Methods. 364.4 Analytical Methods 364.5 HIRF Protection Main C
15、ontributors . 384.5.1 Structure 384.5.2 Harness . 394.5.3 System Hardware 394.5.4 System Software . 395. ROUTES TO HIRF COMPLIANCE . 405.1 HIRF Compliance Requirements 435.1.1 HIRF Rule Conflict Provision Clarification 445.1.2 Assessment of the 18 GHz to 40 GHz Frequency Range 455.2 HIRF Compliance
16、Step 1 Safety Assessment . 455.2.1 Considerations in the Safety Assessment 465.2.1.1 Aggravating Factors 465.2.1.2 System Availability and Integrity Considerations in the Safety Assessment 475.2.2 HIRF Safety Assessment Considerations for Combined Effects on Systems 475.3 HIRF Requirements and Rotor
17、craft Hoist Operations 485.4 HIRF Compliance Step 2 Define Aircraft and System HIRF Protection 485.5 Level A System HIRF Verification . 495.5.1 Level A Display Systems 495.5.2 HIRF Verification for Level A Systems 495.5.3 Level A Verification Considerations 505.6 Level B and C System HIRF Verificati
18、on 515.6.1 Aircraft-Derived Test Levels 515.6.2 Level B/C Verification Considerations 515.6.2.1 RF Susceptibility Considerations for Aircraft Systems Exposed to Portable Electronic Devices (PEDs) 525.7 Assess Immunity . 525.8 Corrective Measures . 525.9 HIRF Protection Compliance 526. AIRCRAFT LEVEL
19、 VERIFICATION LEVEL A SYSTEMS . 536.1 Aircraft Assessment Decision (Step 7) . 536.2 Aircraft Test Decision (Step 8) 536.3 Aircraft High-Level Tests (Step 9) . 556.3.1 Aircraft High-Level Test Considerations . 556.3.2 Frequency Coverage and Required Modulation . 55Copyright SAE International Provided
20、 by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE ARP5583A Page 3 of 1306.3.3 Test Safety 576.3.3.1 Personnel Hazards . 576.3.3.2 Aircraft Safety 576.3.3.3 Fuel Ignition . 586.3.4 High Level Direct Drive Test Methodology . 586.3.5 Hi
21、gh Level Radiated Test Methodology 626.3.6 High-Level Tests in a Reverberation Chamber 636.3.7 Antenna Positioning for High Level Radiated Test . 636.3.8 Test Procedure 676.3.9 Field Calibration 686.3.10 Aircraft Illumination 686.3.11 Susceptibility Threshold Measurements . 686.3.12 Data Logging Dur
22、ing Test . 696.3.13 Data Reporting 696.3.14 Aircraft Operating Modes During Test 696.3.15 Degradation Criteria 696.4 Aircraft Low-Level Coupling Tests (Step 10) 696.4.1 Skin Current Analysis (Step 10a): . 706.4.2 Low-Level Direct Drive Test (Step 10b): . 716.4.3 Low-Level Swept Current Test (Step 10
23、c) 736.4.3.1 Using 3D Modeling 776.4.3.2 Alternative to 3D-Modeling 786.4.3.3 Example Final LLSC Test Results 806.4.3.4 Problem Areas 806.4.4 Low-Level Swept Field Test (Step 10d) 816.4.5 Example Averaged LLSF Test Results . 826.5 Generic Transfer Functions for Level A Display Systems (Step 11) 836.
24、6 Aircraft Similarity Assessment (Step 12) 846.6.1 Aircraft Modifications . 846.6.2 Aircraft Stretches . 846.6.3 Practical Use of Demonstration by Similarity 846.7 Other Methods 856.8 RF Spectrum Limitations . 857. COMPLIANCE FOR LEVEL A SYSTEMS 857.1 System Test Level Selection . 867.1.1 System Tes
25、t Level Development using Aircraft Low-Level Coupling (LLC) Data 867.1.1.1 Conducted Susceptibility System Test Level Development . 867.1.1.2 Radiated Susceptibility System Test Level Development 887.1.2 System Test Level Development using Generic Coupling Data . 907.1.2.1 Conducted Susceptibility S
26、ystem Test Level Development . 907.1.2.2 Radiated Susceptibility Test Level Development 947.1.2.3 Application of DO-160/ED-14 Categories . 967.1.3 System Test Level Development Using Similarity 977.1.3.1 Test Level Development Using Similar Aircraft Test Data 977.1.3.2 Conducted Susceptibility Test
27、Level Development 987.1.3.3 Radiated Susceptibility Test Level Development 1007.1.3.4 System Level Verification Using Similarity 1017.2 Equipment Tests . 1027.3 Integrated Systems Rig Tests . 1027.3.1 Integrated System Rig Setup 1037.3.2 General Setup Requirements . 1047.3.3 Additional Test Setup De
28、tails 1047.3.4 Test Setup for Multiple Similar Installations 1057.3.5 Software Used During HIRF Tests . 1057.3.6 Multiple Simultaneous Cable Tests 1067.3.7 Additional Guidance on Test Setups for Radiated Tests 1077.3.8 Anechoic Chamber Tests 1087.3.9 Reverberation Chamber Tests 1087.3.10 Pass Criter
29、ia 108Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE ARP5583A Page 4 of 1307.3.11 Degraded Test Setup Considerations . 1097.3.12 Modulation . 1097.3.13 Dwell Time 1107.3.14 Test Level Limits . 1
30、107.3.15 Window Effects . 1107.3.16 Additional Level A System Test Setup Guidelines 1117.4 System Tests on Aircraft . 1117.4.1 Conducted Susceptibility Tests with Systems Installed on Aircraft 1127.4.2 Radiated Susceptibility Tests with System Installed on Aircraft . 1127.5 Radio Receiver and Antenn
31、a Tests 1137.6 Certification Report . 1148. COMPLIANCE FOR LEVEL B OR LEVEL C SYSTEMS . 1148.1 System Assessment and Definition 1148.2 Certification by Similarity . 1148.3 Equipment Test . 1158.3.1 Conducted and Radiated Susceptibility Test 1158.4 Immunity Assessment . 1168.5 Corrective Measures . 1
32、168.6 HIRF Protection Compliance 1168.7 Considerations for Level B/C Equipment Integrated into Higher Level Systems . 1168.8 Differences between FAA and EASA Requirements 1169. MAINTENANCE, PROTECTION ASSURANCE, AND MODIFICATIONS . 1169.1 Maintenance Definitions 1179.2 Maintenance Procedures and HIR
33、F Protection 1189.2.1 Relationship between Design and Maintenance 1189.2.2 Development of Scheduled Maintenance Procedures . 1199.2.2.1 Determination If Degradation Is Likely 1199.2.2.2 Allowable HIRF Protection Effectiveness Variation 1199.2.2.3 Identification and Selection of Applicable Tasks. 120
34、9.2.2.4 Determination of Task Intervals 1209.2.3 Maintenance of Aircraft Structure Shielding . 1229.2.4 Maintenance of Electrical Wiring Installation Protection . 1239.2.5 Equipment Maintenance . 1249.3 Aircraft Modification and HIRF Protection . 1259.3.1 Structure and Harness Modification 1259.3.2
35、Equipment Modification . 1269.3.3 Impact of Modification on the Maintenance and Assurance Program 1279.4 Protection Assurance Program . 1279.4.1 Protection Assurance Program Goals 1279.4.2 Scope of Surveillance . 1289.4.3 Selection of Aircraft . 1299.4.4 Frequency and Duration of Surveillance Progra
36、m 1299.5 In-Service Maintenance Test Techniques 12910. NOTES 130LIST OF FIGURES FIGURE 1 SCHEMATIC DIAGRAM SHOWING FILTERS MOUNTED IN A SHIELDED COMPARTMENT BEHIND THE INPUT/OUTPUT CONNECTOR 31FIGURE 2 ROUTES TO COMPLIANCE FOR LEVEL A SYSTEMS 41FIGURE 3 AIRCRAFT LOW-LEVEL COUPLING TESTS - LEVEL A SY
37、STEMS 42FIGURE 4 ROUTES TO HIRF COMPLIANCE - LEVEL B AND C SYSTEMS 43FIGURE 5 TYPICAL DIRECT INJECTION WITH CAGE RETURN WIRE NETWORKTEST LAYOUT NOSE/TAIL 60FIGURE 6 TYPICAL DIRECT INJECTION WITH CAGE RETURN WIRE NETWORKTEST LAYOUT NOSE/TAIL (TOP VIEW). 61FIGURE 7 TYPICAL DIRECT INJECTION WITH CAGE R
38、ETURN WIRE NETWORKTEST LAYOUT NOSE/WING (TOP VIEW) 62FIGURE 8 FIXED WING AIRCRAFT AND ROTORCRAFT ANTENNA POSITIONS 400 MHZ 66FIGURE 10 MEASUREMENT POSITIONS FOR COCKPIT AREA . 67FIGURE 11 ELECTRONICS BAY MEASUREMENT POSITIONS 67FIGURE 12 TEST SETUP FOR LLSC CALIBRATION 73FIGURE 13 TYPICAL FIELD CALI
39、BRATION FOR HORIZONTALLY POLARIZED FIELDS IN THE HF BAND 74FIGURE 14 LLSC TEST ARRANGEMENT 75FIGURE 15 DETAILED LLSC TEST CONFIGURATION . 76FIGURE 16 EXAMPLE OF GROUND EFFECT ON AIRCRAFT MAGNETIC SURFACE FIELD 79FIGURE 17 EXAMPLE LLSC TEST RESULTS . 80FIGURE 18 EXAMPLE LLSF TEST RESULTS 83FIGURE 19
40、EXAMPLE AIRCRAFT LLSC TEST RESULTS EXTRAPOLATED TO HIRF ENVIRONMENT I . 87FIGURE 20 EXAMPLE DEVELOPMENT OF OCTAVE ENVELOPING 88FIGURE 21 EXAMPLE LLSC OCTAVE ENVELOPING FINAL RESULTS 88FIGURE 22 EXAMPLE AIRCRAFT LLSF TEST RESULTS EXTRAPOLATED TO HIRF ENVIRONMENT I . 89FIGURE 23 EXAMPLE LLSF ENVELOPED
41、 RESULTS . 90FIGURE 24 TYPICAL GENERIC INDUCED BUNDLE CURRENT TRANSFER FUNCTIONNORMALIZED TO 1 V/M 92FIGURE 25 GENERIC TRANSFER FUNCTION FOR ALL AIRCRAFT TYPES EXTRAPOLATEDTO PEAK HIRF ENVIRONMENT II 93FIGURE 26 GENERIC TRANSFER FUNCTION FOR ALL AIRCRAFT TYPES EXTRAPOLATEDTO PEAK HIRF ENVIRONMENT I
42、. 93FIGURE 27 COMPARISON OF BCI INDUCED CURRENT WITH GENERIC TRANSFER FUNCTION EXTRAPOLATED TO A HIRF ENVIRONMENT . 94FIGURE 28 OVERLAY OF 3 INDIVIDUAL WIRE BUNDLE CURVES 99FIGURE 29 WORST CASE FROM OVERLAY OF 3 CURVES . 99FIGURE 30 FINAL ENVELOPED LEVELS TO BE USED FOR TEST 100FIGURE 31 EXAMPLE OF
43、AVERAGING AND ENVELOPING OF PEAK LLSF DATA 101FIGURE 32 TEST SETUP FOR MULTIPLE BUNDLE CONDUCTED SUSCEPTIBILITY TESTS 107FIGURE 33 TYPICAL ON-AIRCRAFT RADIATED SUSCEPTIBILITY TEST SETUP . 113LIST OF TABLES TABLE 1 FIXED WING SEVERE HIRF ENVIRONMENT 17TABLE 2 ROTORCRAFT SEVERE HIRF ENVIRONMENT (HIRF
44、ENVIRONMENT III) 20TABLE 3 HIRF ENVIRONMENT I (CERTIFICATION HIRF ENVIRONMENT) 21TABLE 4 HIRF ENVIRONMENT II (NORMAL HIRF ENVIRONMENT) . 23TABLE 5 SIGNALS COUPLING EFFECTS . 25TABLE 6 HIRF COMPLIANCE REQUIREMENTS PER AC 20-158 44TABLE 7 HIRF FAILURE CONDITIONS AND EQUIPMENT/SYSTEM HIRF CERTIFICATION
45、 LEVELS 51TABLE 8 HIGH LEVEL AIRCRAFT TEST USING REDUCED FREQUENCY COVERAGE . 56TABLE 9 MODULATION CRITERIA FOR HIGH LEVEL TESTS. 57TABLE 10 WIRING LOCATION VS. INCIDENT PLANE WAVE COULD BE SET TO PROPAGATE . 71TABLE 11 ANTENNAS . 74TABLE 12 AC 20-158 GENERIC CURVES VS. DO-160/ED-14 CONDUCTED SUSCEP
46、TIBILITY . 96TABLE 13 ATTENUATION VALUES VS. DO-160/ED-14 RADIATED SUSCEPTIBILITY CATEGORIES . 97TABLE 14 ENVELOPING BANDS FOR HIRF ENVIRONMENT I . 101TABLE 15 APPLICABLE MAINTENANCE TASKS FOR HIRF PROTECTION MEASURES 121TABLE 16 AIRCRAFT STRUCTURE SHIELDING 123TABLE 17 WIRING INSTALLATION PROTECTION . 124Copyright SAE International Provided by IHS under license with SAENot for ResaleNo r
