ASTM F3236-17 Standard Specification for High Intensity Radiated Field (HIRF) Protection in Small Aircraft.pdf

1、Designation: F3236 17Standard Specification forHigh Intensity Radiated Field (HIRF) Protection in SmallAircraft1This standard is issued under the fixed designation F3236; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of

2、last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification covers international standards for thehigh intensity radiated field (HIRF) protection aspects ofair

3、worthiness and design for “small” aircraft.1.2 The applicant for a design approval must seek theindividual guidance for their respective CAA body concerningthe use of this specification as part of a certification plan. Forinformation on which CAA regulatory bodies have acceptedthis specification (in

4、 whole or in part) as a means of compli-ance to their Small Aircraft Airworthiness regulations (herein-after referred to as “the Rules”), refer to ASTM F44 webpage(www.astm.org/committeee/F44.htm) which includes CAAwebsite links.1.3 The values stated in SI units are to be regarded asstandard. No oth

5、er units of measurement are included in thisstandard.1.4 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility o

6、f regulatory limitations prior to use.2. Referenced Documents2.1 Following is a list of external standards referencedthrough this document; the earliest revision acceptable for useis indicated. In all cases later document revisions are accept-able if shown to be equivalent to the listed revision, or

7、 ifotherwise formally accepted by the governing civil aviationauthority; earlier revisions are not acceptable.2.2 ASTM Standards:2F3060 Terminology for AircraftF3061/F3061M Specification for Systems and Equipment inSmall Aircraft2.3 Other Standards:EUROCAE ED-107, Rev A Guide to Certification of Air

8、-craft in a High-Intensity Radiated Field (HIRF) Environ-ment3FAA-S-8081-14B, Change 5 Private Pilot Practical TestStandards for Airplane42.4 SAE Standard:5SAE ARP 5583, Rev A Guide to Certification of Aircraft ina High-Intensity Radiated Field (HIRF) Environment3. Terminology3.1 Terminology specifi

9、c to this specification is providedbelow. For general terminology, refer to Terminology F3060.3.2 Definitions of Terms Specific to This Standard:3.2.1 aircraft type code, nan Aircraft Type Code (ATC) isdefined by considering both the technical considerations re-garding the design of the aircraft and

10、 the airworthiness levelestablished based upon risk-based criteria; the method ofdefining an ATC applicable to this specification is defined inSpecification F3061/F3061M.3.2.2 continued safe flight and landing, ncontinued safeflight and landing as applicable to this standard is defined inSpecificati

11、on F3061/F3061M.4. High-Intensity Radiated Field (HIRF) ProtectionNOTE 1Table 1 provides correlation between various Aircraft TypeCodes and the individual requirements contained within this section; referto 3.2.1. For each subsection, an indicator can be found under each ATCcharacter field; three in

12、dicators are used:An empty cell ( ) in all applicable ATC character field columnsindicates that an aircraft must meet the requirements of that subsection.A white circle () in multiple columns indicates that the requirementsof that subsection are not applicable to an aircraft only if all such ATCchar

13、acter fields are applicable.A mark-out () in any of the applicable ATC character field columnsindicates that the requirements of that subsection are not applicable to anaircraft if that ATC character field is applicable.ExampleAn aircraft with anATC of 1SRLLDLN is being considered.Since all applicab

14、le columns are empty for 4.2.1, that subsection is1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.50 onSystems and Equipment.Current edition approved Feb. 15, 2017. Published March 2017. DOI: 10.1520/

15、F3236-17.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM website.3Available from Engineering360, http:/.4Available fr

16、om Federal Aviation Administration (FAA), 800 IndependenceAve., SW, Washington, DC 20591, http:/www.faa.gov.5Available from SAE International (SAE), 400 Commonwealth Dr., Warrendale,PA 15096, http:/www.sae.org.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19

17、428-2959. United StatesThis international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for theDevelopment of International Standards, Guides and Recommendations issued by the World Trade Organization Tech

18、nical Barriers to Trade (TBT) Committee.1applicable to the aircraft. Since both the “L” stall speed column and the“D” meteorological column for 4.1.1 contain white circles, then thatsubsection is not applicable; however, for an aircraft with an ATC of1SRMLDLN, 4.1.1 would be applicable since the “M”

19、 stall speed columndoes not contain a white circle.NOTE 2Guidance in addition to the following sections may be foundin either SAE ARP 5583 or EUROCAE ED-107.4.1 Electrical and Electronic Systems HIRF Protection:4.1.1 Each electrical and electronic system that performs afunction whose failure would p

20、revent the continued safe flightand landing of the aircraft must be designed and installed sothat it meets the requirements of 4.1.1.1 4.1.1.3.4.1.1.1 In showing compliance with 4.1.1, the function mustnot be adversely affected during and after the time the aircraftis exposed to HIRF Environment “I”

21、 as described in 4.2.1.4.1.1.2 In showing compliance with 4.1.1, each electrical orelectronic system must automatically recover normal operationof its function, in a timely manner, after the aircraft is exposedto HIRF Environment “I” as described in 4.2.1, unless thesystems recovery conflicts with o

22、ther operational or functionalrequirements of the system.4.1.1.3 In showing compliance with 4.1.1, each electrical orelectronic system must not be adversely affected during andafter the time the aircraft is exposed to HIRF Environment “II”as described in 4.2.2.4.1.2 Each electrical and electronic sy

23、stem that performs afunction whose failure would significantly reduce the capabil-ity of the aircraft or the ability of the flight crew to respond toan adverse operating condition must be designed and installedso the system is not adversely affected when the equipmentproviding the function is expose

24、d to Equipment HIRF TestLevel 1 as described in 4.2.3 or Equipment HIRF Test Level 2as described in 4.2.4.4.1.3 Each electrical and electronic system that performs afunction whose failure would reduce the capability of theaircraft or the ability of the flight crew to respond to an adverseoperating c

25、ondition must be designed and installed so thesystem is not adversely affected when the equipment providingthe function is exposed to Equipment HIRF Test Level 3 asdescribed in 4.2.5.4.2 HIRF Environments and Test Levels4.2.1 4.2.5specify the HIRF environments and equipment HIRF testlevels for elect

26、rical and electronic systems. The field strengthvalues for the HIRF environments and equipment HIRF testlevels are expressed in root-mean-square units measured dur-ing the peak of the modulation cycle.4.2.1 HIRF Environment “I” is specified in Table 2.4.2.2 HIRF Environment “II” is specified in Tabl

27、e 3.4.2.3 Equipment HIRF Test Level 1 is specified in 4.2.3.1 4.2.3.54.2.3.1 From 10 kilohertz (kHz) to 400 megahertz (MHz),use conducted susceptibility tests with continuous wave (CW)and 1 kHz square wave modulation with 90 % depth or greater.The conducted susceptibility current must start at a min

28、imumof 0.6 milliamperes (mA) at 10 kHz, increasing 20 decibels(dB) per frequency decade to a minimum of 30 mAat 500 kHz.TABLE 1 ATC Compliance Matrix, Section 4SectionAirworthiness Level Number ofEnginesType ofEngine(s)Stall Speed CruiseSpeedMeteorologicalConditionsAltitude Maneuvers1234SMRTLMHLHDNI

29、LHNA44.14.1.1 CC4.1.1.14.1.1.24.1.1.34.1.24.1.3 CC4.24.2.14.2.24.2.34.2.3.14.2.3.24.2.3.34.2.3.44.2.3.54.2.44.2.54.2.5.14.2.5.24.2.5.34.2.5.4TABLE 2 HIRF Environment “I”AFrequencyField Strength(volts/meter)Peak Average10 kHz to 2 MHz 50 502 MHz to 30 MHz 100 10030 MHz to 100 MHz 50 50100 MHz to 400

30、MHz 100 100400 MHz to 700 MHz 700 100700 MHz to 1 GHz 700 1001 GHz to 2 GHz 2000 2002 GHz to 6 GHz 3000 2006 GHz to 8 GHz 1000 2008 GHz to 12 GHz 3000 30012 GHz to 18 GHz 2000 20018 GHz to 40 GHz 600 200AIn this table, the higher field strength applies at the frequency band edges.F3236 1724.2.3.2 Fr

31、om 500 kHz to 40 MHz, the conducted suscepti-bility current must be at least 30 mA.4.2.3.3 From 40 to 500 MHz, use conducted susceptibilitytests, starting at a minimum of 30 mA at 40 MHz, decreasing20 dB per frequency decade to a minimum of 3 mA at 400MHz.4.2.3.4 From 100 to 400 MHz, use radiated su

32、sceptibilitytests at a minimum of 20 volts per meter (V/m) peak with CWand 1 kHz square wave modulation with 90 % depth or greater.4.2.3.5 From 400 MHz to 8 gigahertz (Ghz), use radiatedsusceptibility tests at a minimum of 150 V/m peak with pulsemodulation of 4 % duty cycle with a 1 kHz pulse repeti

33、tionfrequency. This signal must be switched on and off at a rate of1 Hz with a duty cycle of 50 %.4.2.4 Equipment HIRF Test Level 2 is HIRF Environment“II” as specified in 4.2.2, reduced by acceptable aircrafttransfer function and attenuation curves.Testing must cover thefrequency band of 10 kHz to

34、8 GHz.4.2.5 Equipment HIRF Test Level 3 is specified in 4.2.5.1 4.2.5.4.4.2.5.1 From 10 kHz to 400 MHz, use conducted suscepti-bility tests, starting at a minimum of 0.15 mA at 10 kHz,increasing 20 dB per frequency decade to a minimum of 7.5mA at 500 kHz.4.2.5.2 From 500 kHz to 40 MHz, use conducted

35、 suscepti-bility tests at a minimum of 7.5 mA.4.2.5.3 From 40 to 400 MHz, use conducted susceptibilitytests, starting at a minimum of 7.5 mA at 40 MHz, decreasing20 dB per frequency decade to a minimum of 0.75 mA at 400MHz.4.2.5.4 From 100 MHz to 8 GHz, use radiated susceptibilitytests at a minimum

36、of 5 V/m.5. Keywords5.1 HIRF; HIRF protection; radiated fieldsASTM International takes no position respecting the validity of any patent rights asserted in connection with any item mentionedin this standard. Users of this standard are expressly advised that determination of the validity of any such

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41、, Danvers, MA 01923, Tel: (978) 646-2600; http:/ 3 HIRF Environment “II”AFrequencyField Strength(volts/meter)Peak Average10 kHz to 500 kHz 20 20500 kHz to 2 MHz 30 302 MHz to 30 MHz 100 10030 MHz to 100 MHz 10 10100 MHz to 200 MHz 30 10200 MHz to 400 MHz 10 10400 MHz to 1 GHz 700 401 GHz to 2 GHz 1300 1602 GHz to 4 GHz 3000 1204 GHz to 6 GHz 3000 1606 GHz to 8 GHz 400 1708 GHz to 12 GHz 1230 23012 GHz to 18 GHz 730 19018 GHz to 40 GHz 600 150AIn this table, the higher field strength applies at the frequency band edges.F3236 173