ASTM F3115/F3115M-23

Standard Specification for Structural Durability for Small Aeroplanes

ABSTRACT
This specification is concerned with the airworthiness requirements related to structural durability for the design of small airplanes. The applicant for a design approval must seek individual guidance from their respective civil aviation authority (CAA) body regarding the use of this specification as part of a certification plan.
This specification covers metallic structures such as pressurized cabin structures and wing, empennage, and associated structures that must be able to withstand the repeated loads of variable magnitude expected in service. These structures, as well as composite and bonded structures, must also conform to specified requirements for fatigue strength, fail safe strength, damage tolerance, and residual strength.
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 specification (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm). Annex A1 maps the Means of Compliance of the ASTM standards to EASA CS-23, amendment 5, or later, and FAA 14 CFR 23, amendment 64, or later, Structural Durability requirements of 23.2240.  
1.3 Units—This document may present information in either SI units, English Engineering units, or both; the values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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.

General Information

• Status: Published
• Publication Date: 31-Dec-2022
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: F44 - General Aviation Aircraft
• Drafting Committee: F44.30 - Structures

Standards Content (Sample)

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.
Designation:F3115/F3115M −23
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 ization established in the Decision on Principles for the
Development of International Standards, Guides and Recom-
1.1 This specification addresses the airworthiness require-
mendations issued by the World Trade Organization Technical
ments related to structural durability for the design of small
Barriers to Trade (TBT) Committee.
aeroplanes. The material was developed through open consen-
sus of international experts in general aviation. This informa-
2. Referenced Documents
tion was created by focusing on Levels 1 through 4 Normal
2
2.1 ASTM Standards:
Category aeroplanes. The content may be more broadly appli-
cable; it is the responsibility of the applicant to substantiate F3060 Terminology for Aircraft
F3066/F3066M Specification forAircraft Powerplant Instal-
broader applicability as a specific means of compliance.
lation Hazard Mitigation
1.2 An applicant intending to propose this information as
F3116/F3116M Specification for Design Loads and Condi-
Means of Compliance for a design approval must seek guid-
tions
ance from their respective oversight authority (for example,
F3174/F3174M Specification for Establishing Operating
published guidance from applicable Civil Aviation Authorities
Limitations and Information for Aeroplanes
(CAAs), including the guidance noted in Appendix X2, Guid-
F3380 Practice for Structural Compliance of Very Light
ance Material) concerning the acceptable use and application
Aeroplanes
thereof. For information on which oversight authorities have
3
2.2 EASA Standard:
accepted this specification (in whole or in part) as an accept-
CS-23, Amendment 5 Certification Specifications for Nor-
able Means of Compliance to their regulatory requirements
mal Category Aeroplanes
(hereinafter referred to as “the Rules”), refer to ASTM Com-
4
mittee F44 webpage (www.astm.org/COMMITTEE/F44.htm).
2.3 FAA Standard:
Annex A1 maps the Means of Compliance of the ASTM
14 CFR 23, Amendment 64 Airworthiness Standards: Nor-
standards to EASACS-23, amendment 5, or later, and FAA14
mal Category Airplanes
CFR 23, amendment 64, or later, Structural Durability require-
ments of 23.2240.
3. Terminology
1.3 Units—Thisdocumentmaypresentinformationineither
3.1 The following are a selection of relevant terms. See
SI units, English Engineering units, or both; the values stated
Terminology F3060 for more definitions and abbreviations.
in each system are not necessarily exact equivalents; therefore,
3.2 Definitions:
to ensure conformance with the standard, each system shall be
3.2.1 catastrophic loss or catasrophic failure—failure con-
used independently of the other, and values from the two
dition that is expected to result in fatalities of the occupants,
systems shall not be combined.
normally with the loss of the aeroplane.
1.4 This standard does not purport to address all of the
3.2.2 damage tolerance—the attribute of the structure that
safety concerns, if any, associated with its use. It is the
permits it to retain its required residual strength for a period of
responsibility of the user of this standard to establish appro-
use after the structure has sustained a given level of fatigue,
priate safety, health, and environmental practices and deter-
corrosion, accidental, or discrete source damage.
mine the applicability of regulatory limitations prior to use.
1.5 This international standard was developed in accor-
dance with internationally recognized principles on standard-
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
1
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral Standards volume information, refer to the standard’s Document Summary page on
Aviation Aircraft and is the direct responsibility of Subcommittee F44.30 on the ASTM website.
3
Structures. Available from European Aviation Safety Agency (EASA), Postfach 10 12 53,
Current edition approved Jan. 1, 2023. Published January 2023. Originally D-50452 Cologne, Germany, http://easa.europa.eu
4
approved in 2015. Last previous edition approved in 2022 as F3115/F3115M-22. Available from Federal Aviation Administration (FAA), 800 Independence
DOI: 10.1520/F3115_F3115M-2
...

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 − 22 F3115/F3115M − 23
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
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 specification (in whole or in part) as an acceptable Means of Compliance to their
regulatory requirements (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/
COMMITTEE/F44.htm). Appendix X3Annex A1 maps the Means of Compliance of the ASTM standards to EASA CS-23,
amendment 5, or later, and FAA 14 CFR 23, amendment 64, or later, Structural Durability requirements of 23.2240.
1.3 Units—This document may present information in either SI units, English Engineering units, or both; the values stated in each
system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used
independently of the other, and values from the two systems shall not be combined.
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
2.1 ASTM Standards:
F3060 Terminology for Aircraft
F3066/F3066M Specification for Aircraft Powerplant Installation Hazard Mitigation
F3116/F3116M Specification for Design Loads and Conditions
F3174/F3174M Specification for Establishing Operating Limitations and Information for Aeroplanes
F3380 Practice for Structural Compliance of Very Light Aeroplanes
1
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 Aug. 1, 2022Jan. 1, 2023. Published August 2022January 2023. Originally approved in 2015. Last previous edition approved in 20202022 as
F3115/F3115M-20.-22. DOI: 10.1520/F3115_F3115M-22.10.1520/F3115_F3115M-23.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM Standards
volume information, refer to the standard’s Document Summary page on the ASTM website.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

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F3115/F3115M − 23
3
2.2 EASA Standard:
CS-23, Amendment 5 Certification Specifications for Normal Category Aeroplanes
4
2.3 FAA Standard:
14 CFR 23, Amendment 64 Airworthiness Standards: Normal Category Airplanes
3. Terminology
3.1 The following are a selection of relevant terms. See Terminology F3060 for more definitions and abbreviations.
3.2 Definitions:
3.2.1 catastrophic loss or catasrophic failure—failure condition that is expected to result in fatalities of the occupants, normally
with the loss of the aeroplane.
3.2.2 damage tolerance—the attribute of the struct
...