ASTM F3114-21
(Specification)Standard Specification for Structures
Standard Specification for Structures
ABSTRACT
This specification prescribes structural requirements that apply to all portions of the airframe regardless of component, system, or structure. The applicant for a design approval must seek individual guidance from their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The structural requirements described in this specification cover strength (loads, factor of safety, strength and deformation, proof of structure, vibration and buffeting, canard or tandem wing configurations, windshields and windows, landing gear, testing of wings and control surfaces, pressurization tests); mass and mass distribution (load distribution limits, leveling means; materials, processes, and methods of fabrication (materials and workmanship, fabrication methods, material strength properties and design values; and protection of structure (fasteners, accessibility provisions, fire protection of engine mounts, and other flight structure). Also addressed are special factors of safety, including casting factors, bearing factors, fitting factors, and configuration based factors.
SCOPE
1.1 This specification addresses the structural requirements that apply to all portions of the airframe regardless of component, system, or structure.
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.
1.3 The applicant for a design approval must seek individual guidance from their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Small Airplane Airworthiness Rules (hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links.
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
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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: F3114 −21
Standard Specification for
1
Structures
This standard is issued under the fixed designation F3114; 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 F3061/F3061M Specification for Systems and Equipment in
Small Aircraft
1.1 This specification addresses the structural requirements
F3083/F3083M Specification for Emergency Conditions,
that apply to all portions of the airframe regardless of
Occupant Safety and Accommodations
component, system, or structure.
F3093/F3093M Specification for Aeroelasticity Require-
1.2 This specification was originally conceived for small
ments
airplanes as defined in the F44 terminology standard but may
F3115/F3115M Specification for Structural Durability for
find broader applicability. Use of the term aircraft throughout
Small Aeroplanes
this specification is intended to allow the relevant CAA(s) to
F3116/F3116M Specification for Design Loads and Condi-
accept this standard as a means of compliance as they
tions
determine it to be appropriate, whether for small airplanes or
for other types of aircraft.
3. Terminology
1.3 Theapplicantforadesignapprovalmustseekindividual
3.1 See Terminology F3060 for more definitions and abbre-
guidance from their respective CAA body concerning the use
viations.
of this standard as part of a certification plan. For information
on which CAA regulatory bodies have accepted this standard
4. Strength
(in whole or in part) as a means of compliance to their Small
4.1 Loads—Strength requirements are specified in terms of
Airplane Airworthiness Rules (hereinafter referred to as “the
limit loads (the maximum loads to be expected in service) and
Rules”), refer to ASTM F44 webpage (www.ASTM.org/
ultimate loads (limit loads multiplied by prescribed factors of
COMMITTEE/F44.htm) which includes CAA website links.
safety).
1.4 This standard does not purport to address all of the
safety concerns, if any, associated with its use. It is the 4.2 Factor of Safety—Unless otherwise provided, a factor of
responsibility of the user of this standard to establish appro- safety of 1.5 must be used.
priate safety, health, and environmental practices and deter-
4.3 Strength and Deformation:
mine the applicability of regulatory limitations prior to use.
4.3.1 The structure must be able to support limit loads
1.5 This international standard was developed in accor-
without detrimental, permanent deformation.At any load up to
dance with internationally recognized principles on standard-
limit loads, the deformation may not interfere with safe
ization established in the Decision on Principles for the
operation.
Development of International Standards, Guides and Recom-
4.3.2 The structure must be able to support ultimate loads
mendations issued by the World Trade Organization Technical
without failure for at least three seconds, except local failures
Barriers to Trade (TBT) Committee.
or structural instabilities between limit and ultimate load are
acceptable only if the structure can sustain the required
2. Referenced Documents
2 ultimateloadforatleastthreeseconds.Howeverwhenproofof
2.1 ASTM Standards:
strength is shown by dynamic tests simulating actual load
F3060 Terminology for Aircraft
conditions, the three second limit does not apply.
1
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral 4.4 Proof of Structure:
Aviation Aircraft and is the direct responsibility of Subcommittee F44.30 on
4.4.1 Compliance with the strength and deformation re-
Structures.
quirements of 4.3 must be shown for each critical load
Current edition approved May 1, 2021. Published May 2021. Originally
condition. Structural analysis may be used only if the structure
approved in 2015. Last previous edition approved in 2019 as F3114–19. DOI:
10.1520/F3114-21.
conforms to those for which experience has shown this method
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
to be reliable. In other cases, substantiating load tests must be
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
made. Dynamic tests, including structural flight tests, are
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website. acceptable if the design load conditions have been simulated.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
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...
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: F3114 − 19 F3114 − 21
Standard Specification for
1
Structures
This standard is issued under the fixed designation F3114; 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 structural requirements that apply to all portions of the airframe regardless of component,
system, or structure.
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.
1.3 The applicant for a design approval must seek individual guidance from their respective CAA body concerning the use of this
standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole
or in part) as a means of compliance to their Small Airplane Airworthiness Rules (hereinafter referred to as “the Rules”), refer to
ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links.
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
F3061/F3061M Specification for Systems and Equipment in Small Aircraft
F3083/F3083M Specification for Emergency Conditions, Occupant Safety and Accommodations
F3093/F3093M Specification for Aeroelasticity Requirements
F3115/F3115M Specification for Structural Durability for Small Aeroplanes
F3116/F3116M Specification for Design Loads and Conditions
3. Terminology
3.1 See Terminology F3060 for more definitions and abbreviations.
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 Nov. 1, 2019May 1, 2021. Published December 2019May 2021. Originally approved in 2015. Last previous edition approved in 20152019 as
F3114–15.–19. DOI: 10.1520/F3114–19.10.1520/F3114-21.
2
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.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
---------------------- Page: 1 ----------------------
F3114 − 21
4. Strength
4.1 Loads—Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate
loads (limit loads multiplied by prescribed factors of safety).
4.2 Factor of Safety—Unless otherwise provided, a factor of safety of 1.5 must be used.
4.3 Strength and Deformation:
4.3.1 The structure must be able to support limit loads without detrimental, permanent deformation. At any load up to limit loads,
the deformation may not interfere with safe operation.
4.3.2 The structure must be able to support ultimate loads without failure for at least three seconds, except local failures or
structural instabilities between limit and ultimate load are acceptable only if the structure can sustain the required ultimate load
for at least three seconds. However when proof of strength is shown by dynamic tests simulating actual load conditions, the three
second limit does not apply.
4.4 Proof of Structure:
4.4.1 Compliance with the strength and deformation requirements of 4.3 must be shown for each critical load condition. Structural
analysis may be used only if the structure conforms to those for which experience h
...
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