ASTM F3115/F3115M-19
(Specification)Standard Specification for Structural Durability for Small Aeroplanes
Standard Specification for Structural Durability for Small Aeroplanes
SCOPE
1.1 This specification addresses the airworthiness requirements related to structural durability for the design of small aeroplanes. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Levels 1 through 4 Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable Civil Aviation Authorities (CAAs), including the guidance noted in Appendix X2 Guidance Material) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to ASTM F44 webpage (www.astm.org/COMMITTEE/F44.htm).
1.3 Units – This document may present information in either SI units, English Engineering units, or both; the values stated in each system may not be exact equivalents. Each system shall be used independently of the other; combining values from the two systems may result in nonconformance with the 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.
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Designation: F3115/F3115M −19
Standard Specification for
1
Structural Durability for Small Aeroplanes
This standard is issued under the fixed designation F3115/F3115M; 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 2. Referenced Documents
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1.1 This specification addresses the airworthiness require- 2.1 ASTM Standards:
ments related to structural durability for the design of small F3060 Terminology for Aircraft
aeroplanes. The material was developed through open consen- F3174 Specification for Establishing Operating Limitations
sus of international experts in general aviation. This informa- and Information for Aeroplanes
tion was created by focusing on Levels 1 through 4 Normal F3380 Practice for Structural Compliance of Very Light
Category aeroplanes. The content may be more broadly appli- Aeroplanes
cable; it is the responsibility of the applicant to substantiate
3. Terminology
broader applicability as a specific means of compliance.
3.1 The following are a selection of relevant terms. See
1.2 An applicant intending to propose this information as
Terminology F3060 for more definitions and abbreviations.
Means of Compliance for a design approval must seek guid-
ance from their respective oversight authority (for example,
3.2 Definitions:
published guidance from applicable Civil Aviation Authorities
3.2.1 catastrophic loss or catasrophic failure—failure con-
(CAAs), including the guidance noted in Appendix X2 Guid-
dition that is expected to result in fatalities of the occupants,
ance Material) concerning the acceptable use and application
normally with the loss of the aeroplane.
thereof. For information on which oversight authorities have
3.2.2 damage tolerance—the attribute of the structure that
accepted this standard (in whole or in part) as an acceptable
permits it to retain its required residual strength for a period of
Means of Compliance to their regulatory requirements (here-
use after the structure has sustained a given level of fatigue,
inafter “the Rules”), refer to ASTM F44 webpage
corrosion, accidental, or discrete source damage.
(www.astm.org/COMMITTEE/F44.htm).
3.2.3 failsafe—theattributeofthestructurethatpermitsitto
1.3 Units – This document may present information in
retain its required residual strength for a period of unrepaired
either SI units, English Engineering units, or both; the values
use after the failure or partial failure of a structural element.
stated in each system may not be exact equivalents. Each
3.2.4 fatigue—the process of progressive localized perma-
system shall be used independently of the other; combining
nent structural change occurring in a material subjected to
values from the two systems may result in nonconformance
conditions that produce fluctuating stresses and strains at some
with the standard.
point or points, which may result in damage or complete
1.4 This standard does not purport to address all of the
fracture after a sufficient number of fluctuations.
safety concerns, if any, associated with its use. It is the
3.2.5 life (or load) enhancement factor—an additional load
responsibility of the user of this standard to establish appro-
factor or test duration, or both, applied to structural repeated
priate safety, health, and environmental practices and deter-
load tests, relative to the intended design load and life values,
mine the applicability of regulatory limitations prior to use.
usedtoaccountformaterialvariability.Itisusedtodevelopthe
1.5 This international standard was developed in accor-
required level of confidence in data.
dance with internationally recognized principles on standard-
3.2.6 residual strength—the strength capability of a struc-
ization established in the Decision on Principles for the
ture after the structure has been damaged due to fatigue,
Development of International Standards, Guides and Recom-
corrosion, accidental, or discrete source damage. The residual
mendations issued by the World Trade Organization Technical
strength capability includes consideration of static strength,
Barriers to Trade (TBT) Committee.
fracture, and stiffness.
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ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
Aviation Aircraft and is the direct responsibility of Subcommittee F44.30 on
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Structures. For referenced ASTM standards, visit the ASTM website, www.astm.org, or
Current edition approved Nov. 1, 2019. Published December 2019. Originally contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
approved in 2015. Last previous edition approved in 2015 as F3115/F3115M-15. Standards volume information, refe
...
This document is not an ASTM standard and is intended only to provide the user of an ASTM standard an indication of what changes have been made to the previous version. Because
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
of the standard as published by ASTM is to be considered the official document.
Designation: F3115/F3115M − 15 F3115/F3115M − 19
Standard Specification for
1
Structural Durability for Small Airplanes
This standard is issued under the fixed designation F3115/F3115M; 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 addresses the airworthiness requirements related to structural durability for the design of small
airplanes.aeroplanes. The material was developed through open consensus of international experts in general aviation. This
information was created by focusing on Levels 1 through 4 Normal Category aeroplanes. The content may be more broadly
applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance.
1.2 This specification was originally conceived for small airplanes as defined in the F44 terminology standard but may find
broader applicability. Use of the term aircraft throughout this specification is intended to allow the relevant CAA(s) to accept this
standard as a means of compliance as they determine it to be appropriate, whether for small airplanes or for other types of aircraft.
1.2 The applicant An applicant intending to propose this information as Means of Compliance for a design approval must seek
individual guidance from their respective CAA body oversight authority (for example, published guidance from applicable CAAs,
including the guidance noted in Appendix X2) concerning the use of this standard as part of a certification plan. acceptable use
and application thereof. For information on which CAA regulatory bodies oversight authorities have accepted this standard (in
whole or in part) as a means of compliance to their Small Airplane Airworthiness Rules (hereinafter referred to as an acceptable
Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/
COMMITTEE/F44.htm) which includes CAA website links.(www.astm.org/COMMITTEE/F44.htm).
1.3 TheUnits values stated – This document may present information in either SI units or inch-pound units are to be regarded
separately as standard. The units, English Engineering units, or both; the values stated in each system aremay not necessarily exact
equivalents; therefore, to ensure conformance with the standard, each be exact equivalents. Each system shall be used
independently of the other, andother; combining values from the two systems shall not be combined.may result in nonconformance
with the 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 safety, health, and healthenvironmental 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
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2.1 ASTM Standards:
F3060 Terminology for Aircraft
F3174 Specification for Establishing Operating Limitations and Information for Aeroplanes
F3380 Practice for Structural Compliance of Very Light Aeroplanes
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2.2 Federal Aviation Regulations:
14 CFR Part 23 Amendment 62, §§ 23.571 through 23.575, 23.627
2.3 EASA Requirements:
CS 23, §§ 23.571 through 23.575
CS-VLA
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This specification is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsibility of Subcommittee F44.30 on Structures.
Current edition approved June 1, 2015Nov. 1, 2019. Published September 2015December 2019. Originally approved in 2015. Last previous edition approved in 2015 as
F3115/F3115M-15. DOI: 10.1520/F3115_F3115M-15.10.1520/F3115_F3115M-19.
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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.
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