ASTM F3114-15
(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 and health practices and determine the applicability of regulatory limitations prior to use.
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Standards Content (Sample)
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Designation:F3114 −15
Standard Specification for
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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 F3115 Specification for Structural Durability for Small Air-
planes
1.1 This specification addresses the structural requirements
F3116 Specification for Design Loads and Conditions
that apply to all portions of the airframe regardless of
component, system, or structure.
3. Terminology
1.2 This specification was originally conceived for small
3.1 See Terminology F3060 for more definitions and abbre-
airplanes as defined in the F44 terminology standard but may
viations.
find broader applicability. Use of the term aircraft throughout
this specification is intended to allow the relevant CAA(s) to
4. Strength
accept this standard as a means of compliance as they
determine it to be appropriate, whether for small airplanes or
4.1 Loads—Strength requirements are specified in terms of
for other types of aircraft.
limit loads (the maximum loads to be expected in service) and
ultimate loads (limit loads multiplied by prescribed factors of
1.3 Theapplicantforadesignapprovalmustseekindividual
safety).
guidance from their respective CAA body concerning the use
of this standard as part of a certification plan. For information
4.2 Factor of Safety—Unless otherwise provided, a factor of
on which CAA regulatory bodies have accepted this standard
safety of 1.5 must be used.
(in whole or in part) as a means of compliance to their Small
4.3 Strength and Deformation:
Airplane Airworthiness Rules (hereinafter referred to as “the
4.3.1 The structure must be able to support limit loads
Rules”), refer to ASTM F44 webpage (www.ASTM.org/
without detrimental, permanent deformation.At any load up to
COMMITTEE/F44.htm) which includes CAA website links.
limit loads, the deformation may not interfere with safe
1.4 This standard does not purport to address all of the
operation.
safety concerns, if any, associated with its use. It is the
4.3.2 The structure must be able to support ultimate loads
responsibility of the user of this standard to establish appro-
without failure for at least three seconds, except local failures
priate safety and health practices and determine the applica-
or structural instabilities between limit and ultimate load are
bility of regulatory limitations prior to use.
acceptable only if the structure can sustain the required
ultimateloadforatleastthreeseconds.Howeverwhenproofof
2. Referenced Documents
strength is shown by dynamic tests simulating actual load
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conditions, the three second limit does not apply.
2.1 ASTM Standards:
F3060 Terminology for Aircraft
4.4 Proof of Structure:
F3061 Specification for Systems and Equipment in Small
4.4.1 Compliance with the strength and deformation re-
Aircraft
quirements of 4.3 must be shown for each critical load
F3083 Specification for Emergency Conditions, Occupant
condition. Structural analysis may be used only if the structure
Safety and Accommodations
conforms to those for which experience has shown this method
F3093 Specification for Aeroelasticity Requirements
to be reliable. In other cases, substantiating load tests must be
made. Dynamic tests, including structural flight tests, are
acceptable if the design load conditions have been simulated.
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4.4.2 Certain parts of the structure must be tested as
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
Aviation Aircraft and is the direct responsibility of Subcommittee F44.30 on
specified.
Structures.
4.5 Vibration and Buffeting—There must be no vibration or
Current edition approved Nov. 1, 2015. Published December 2015. DOI:
10.1520/F3114-15.
buffeting severe enough to result in structural damage, and
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For referenced ASTM standards, visit the ASTM website, www.astm.org, or
each part of the airplane must be free from excessive vibration,
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
under any appropriate speed and power conditions up to
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website. V /M ,orV /M for turbojets.
D D DF DF
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F3114−15
4.6 Canard or Tandem Wing Configurations: 4.8.1.2 Compliance with the provisions of this section may
4.6.1 The forward structure of a canard or tandem wing be shown by analysis or tests, or both.
configuration must:
4.9 Testing—The suitability of each questionable d
...
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