ASTM_F_3114_-_15.pdf

Designation:F311415Standard Specification forStructures1This standard is issued under the fixed designation F3114;the number immediately following the designation indicates the year oforiginal adoption or,in the case of revision,the year of last revision.A number in parentheses indicates the year of last reapproval.Asuperscript epsilon()indicates an editorial change since the last revision or reapproval.1.Scope1.1 This specification addresses the structural requirementsthat apply to all portions of the airframe regardless ofcomponent,system,or structure.1.2 This specification was originally conceived for smallairplanes as defined in the F44 terminology standard but mayfind broader applicability.Use of the term aircraft throughoutthis specification is intended to allow the relevant CAA(s)toaccept this standard as a means of compliance as theydetermine it to be appropriate,whether for small airplanes orfor other types of aircraft.1.3 The applicant for a design approval must seek individualguidance from their respective CAA body concerning the useof this standard as part of a certification plan.For informationon which CAA regulatory bodies have accepted this standard(in whole or in part)as a means of compliance to their SmallAirplane Airworthiness Rules(hereinafter referred to as“theRules”),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 thesafety concerns,if any,associated with its use.It is theresponsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility of regulatory limitations prior to use.2.Referenced Documents2.1 ASTM Standards:2F3060 Terminology for AircraftF3061 Specification for Systems and Equipment in SmallAircraftF3083 Specification for Emergency Conditions,OccupantSafety and AccommodationsF3093 Specification for Aeroelasticity RequirementsF3115 Specification for Structural Durability for Small Air-planesF3116 Specification for Design Loads and Conditions3.Terminology3.1 See Terminology F3060 for more definitions and abbre-viations.4.Strength4.1 LoadsStrength requirements are specified in terms oflimit loads(the maximum loads to be expected in service)andultimate loads(limit loads multiplied by prescribed factors ofsafety).4.2 Factor of SafetyUnless otherwise provided,a factor ofsafety of 1.5 must be used.4.3 Strength and Deformation:4.3.1 The structure must be able to support limit loadswithout detrimental,permanent deformation.At any load up tolimit loads,the deformation may not interfere with safeoperation.4.3.2 The structure must be able to support ultimate loadswithout failure for at least three seconds,except local failuresor structural instabilities between limit and ultimate load areacceptable only if the structure can sustain the requiredultimate load for at least three seconds.However when proof ofstrength is shown by dynamic tests simulating actual loadconditions,the three second limit does not apply.4.4 Proof of Structure:4.4.1 Compliance with the strength and deformation re-quirements of 4.3 must be shown for each critical loadcondition.Structural analysis may be used only if the structureconforms to those for which experience has shown this methodto be reliable.In other cases,substantiating load tests must bemade.Dynamic tests,including structural flight tests,areacceptable if the design load conditions have been simulated.4.4.2 Certain parts of the structure must be tested asspecified.4.5 Vibration and BuffetingThere must be no vibration orbuffeting severe enough to result in structural damage,andeach part of the airplane must be free from excessive vibration,under any appropriate speed and power conditions up toVD/MD,or VDF/MDFfor turbojets.1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.30 onStructures.Current edition approved Nov.1,2015.Published December 2015.DOI:10.1520/F3114-15.2For referenced ASTM standards,visit the ASTM website,www.astm.org,orcontact ASTM Customer Service at serviceastm.org.For Annual Book of ASTMStandards volume information,refer to the standards Document Summary page onthe ASTM website.Copyright ASTM International,100 Barr Harbor Drive,PO Box C700,West Conshohocken,PA 19428-2959.United States1 4.6 Canard or Tandem Wing Configurations:4.6.1 The forward structure of a canard or tandem wingconfiguration must:4.6.1.1 Meet all requirements of this standard,Specifica-tions F3116,F3093,F3083,and F3115 applicable to a wing;and4.6.1.2 Must meet all requirements applicable to the func-tion performed by these surfaces.4.7 Windshields and Windows:4.7.1 The internal panels of windshields and windows mustbe constructed of a nonsplintering material,such as but notlimited to:4.7.1.1 Nonsplintering safety glass;or4.7.1.2 Synthetic resins.4.7.2 The design of windshields,windows,and canopies inpressurized airplanes