ASTM F3236-21a

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it may not be technically possible to adequately depict all changes accurately, ASTM recommends that users consult prior editions as appropriate. In all cases only the current version
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Designation: F3236 − 21 F3236 − 21a
Standard Specification for
High Intensity Radiated Field (HIRF) Protection in Small
Aircraft
This standard is issued under the fixed designation F3236; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope
1.1 This specification covers international standards for the high intensity radiated field (HIRF) protection aspects of airworthiness
and design for “small” aircraft.
1.2 The applicant for a design approval must seek the individual guidance for their respective civil aviation authority (CAA) body
concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have
accepted this specification (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations
(hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.astm.org/committeee/F44.htm), which includes CAA
website links. Annex A1 maps the Means of Compliance described in this specification to EASA CS-23, amendment 5, or later,
and FAA 14 CFR Part 23, amendment 64, or later.
1.3 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility
of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of
regulatory limitations prior to use.
1.5 This international standard was developed in accordance with internationally recognized principles on standardization
established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued
by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
2. Referenced Documents
2.1 Following is a list of external standards referenced through this document; the earliest revision acceptable for use is indicated.
In all cases later document revisions are acceptable if shown to be equivalent to the listed revision, or if otherwise formally
accepted by the governing civil aviation authority; earlier revisions are not acceptable.
2.2 ASTM Standards:
F3060 Terminology for Aircraft
F3061/F3061M Specification for Systems and Equipment in Small Aircraft
2.3 EASA Standard:
CS-23 Normal, Utility, Aerobatic and Commuter Aeroplanes
This specification is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsibility of Subcommittee F44.50 on Systems
and Equipment.
Current edition approved Sept. 1, 2021Nov. 1, 2021. Published September 2021November 2021. Originally approved in 2017. Last previous edition approved in 20172021
as F3236-17.–21. DOI: 10.1520/F3236-21.10.1520/F3236-21A.
For referenced ASTM standards, visit the ASTM website, www.astm.org, or contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM Standards
volume information, refer to the standard’s Document Summary page on the ASTM website.
Available from European Union Aviation Safety Agency (EASA), Konrad-Adenauer-Ufer 3, D-50668 Cologne, Germany, https://www.easa.europa.eu.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
F3236 − 21a
2.4 EUROCAE Standard:
EUROCAE ED-107, Rev A Guide to Certification of Aircraft in a High-Intensity Radiated Field (HIRF) Environment
2.5 FAA Standards:
14 CFR Part 23 Airworthiness Standards: Normal Category Airplanes
FAA-S-8081-14B, Change 5 Private Pilot Practical Test Standards for Airplane
2.6 SAE Standard:
SAE ARP 5583, Rev A Guide to Certification of Aircraft in a High-Intensity Radiated Field (HIRF) Environment
3. Terminology
3.1 Terminology specific to this specification is provided below. For general terminology, refer to Terminology F3060.
3.2 Definitions of Terms Specific to This Standard:
3.2.1 aircraft type code, n—an Aircraft Type Code (ATC) is defined by considering both the technical considerations regarding
the design of the aircraft and the airworthiness level established based upon risk-based criteria; the method of defining an ATC
applicable to this specification is defined in Specification F3061/F3061M.
3.2.2 continued safe flight and landing, n—continued safe flight and landing as applicable to this standard is defined in
Specification F3061/F3061M.
4. High-Intensity Radiated Field (HIRF) Protection
NOTE 1—Table 1 provides correlation between various Aircraft Type Codes and the individual requirements contained within this section; refer to 3.2.1.
For each subsection, an indicator can be found under each ATC character field; three indicators are used:
An empty cell ( ) in all applicable ATC character field columns indicates that an aircraft must meet the requirements of that subsection.
A white circle (○) in multiple columns indicates that the requirements of that subsection are not applicable to an aircraft only if all such ATC character
fields are applicable.
A mark-out (×) in any of the applicable ATC character field columns indicates that the requirements of that subsection are not applicable to an aircraft
if that ATC character field is applicable.
Example—An aircraft with an ATC of 1SRLLDLN is being considered. Since all applicable columns are empty for 4.2.1, that subsection is applicable
to the aircraft. Since both the “L” stall speed column and the “D” meteorological column for 4.1.1 contain white circles, then that subsection is not
applicable; however, for an aircraft with an ATC of 1SRMLDLN, 4.1.1 would be applicable since the “M” stall speed column does not contain a white
circle.
TABLE 1 ATC Compliance Matrix, Section 4
Airworthiness Level Number of Type of Stall Speed Cruise Meteorological Altitude Maneuvers
Section Engines Engine(s) Speed Conditions
1 2 3 4 S M R T L M H L H D N I L H N A
4.1
4.1.1 C C
4.1.1.1 C C
4.1.1.2 C C
4.1.1.3 C C
4.1.2 C C
4.1.3 C C
4.2
4.2.1
4.2.2
4.2.3
4.2.3.1
4.2.3.2
4.2.3.3
4.2.3.4
4.2.3.5
4.2.4
4.2.5
4.2.5.1
4.2.5.2
4.2.5.3
4.2.5.4
Available from EUROCAE, 9-23 rue Paul Lafargue, “Le Triangle” building, 93200 Saint-Denis, France, https://www.eurocae.net.
Available from Federal Aviation Administration (FAA), 800 Independence Ave., SW, Washington, DC 20591, http://www.faa.gov.
Available from SAE International (SAE), 400 Commonwealth Dr., Warrendale, PA 15096, http://www.sae.org.
F3236 − 21a
NOTE 2—Guidance in addition to the following sections may be found in 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 a function whose failure would prevent the continued safe flight and
landing of the aircraft must be designed and installed so that 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 must not be adversely affected during and after the time the aircraft is
exposed to HIRF Environment “I” as described in 4.2.1.
4.1.1.2 In showing compliance with 4.1.1, each electrical or electronic system must automatically recover normal operation of its
function, in a timely manner, after the aircraft is exposed to HIRF Environment “I” as described in 4.2.1, unless the system’s
recovery conflicts with other operational or functional requirements of the system.
4.1.1.3 In showing compliance with 4.1.1, each electrical or electronic system must not be adversely affected during and after the
time the aircraft is exposed to HIRF Environment “II” as described in 4.2.2.
4.1.2 Each electrical and electronic system that performs a function whose failure would significantly reduce the capability of the
aircraft or the ability of the flight crew to respond to an adverse operating condition must be designed and installed so the system
is not adversely affected when the equipment providing the function is exposed to Equipment HIRF Test Level 1 as described in
4.2.3 or Equipment HIRF Test Level 2 as described in 4.2.4.
4.1.3 Each When required by regulation, each electrical and electronic system that performs a function whose failure would reduce
the capability of the aircraft or the ability of the flight
...