ASTM_F_3093_-_F_3093M_-_15.pdf

Designation:F3093/F3093M15Standard Specification forAeroelasticity Requirements1This standard is issued under the fixed designation F3093/F3093M;the number immediately following the designation indicates the yearof 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.Scope1.1 This specification addresses the aeroelasticity require-ments of the airplane.1.2 The values stated in either SI units or inch-pound unitsare to be regarded separately as standard.The values stated ineach system may not be exact equivalents;therefore,eachsystem shall be used independently of the other.Combiningvalues from the two systems may result in non-conformancewith the standard.1.3 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:2F3061 Specification for Systems and Equipment in SmallAircraftF3065/F3065M Specification for Installation and Integrationof Propeller SystemsF3115 Specification for Structural Durability for Small Air-planes2.2 Federal Aviation Administration(FAA)Document:3Airframe and Equipment Engineering Report No.45(ascorrected)“Simplified Flutter Prevention Criteria”19552.3 Federal Aviation Regulations:414 CFR 23 Amendment 623.Terminology3.1 Definitions:3.1.1 GVTground vibration testing3.1.2 V-nvelocity versus load factor4.Flutter4.1 It must be shown by the methods in 4.2,and either 4.3or 4.4,that the airplane is free from flutter,control reversal,anddivergence for any condition of operation within the limit V-nenvelope and at all speeds up to the speed specified for theselected method.In addition:4.1.1 Adequate tolerances must be established for quantitieswhich affect flutter,including speed,damping,mass balance,and control system stiffness;and4.1.2 The natural frequencies of main structural componentsmust be determined by vibration tests or other approvedmethods.This determination is not required for Level 1airplanes with VDup to 260 kph 140 knots CAS andmaximum gross weight up to 750 kg 1650 lbm.4.2 Flight flutter tests must be made to show that theairplane is free from flutter,control reversal,and divergence,and to show that:4.2.1 Proper and adequate attempts to induce flutter havebeen made within the speed range up to VD/MD(or VDF/MDFfor jets);4.2.2 The vibratory response of the structure during the testindicates freedom from flutter;4.2.3 A proper margin of damping exists at VD/MD(orVDF/MDFfor jets);and4.2.4 As VD/MD(or VDF/MDFfor jets)is approached,thereis no large or rapid reduction in damping.4.3 Any rational analysis used to predict freedom fromflutter,control reversal,and divergence must cover all speedsup to 1.2 VD/1.2 MD,limited to Mach 1.0 for subsonicairplanes.4.4 Compliance with rigidity and mass balance criteriadefined in pages 4-12 of FAAs Airframe and EquipmentEngineering Report No.45 may be accomplished to show thatthe airplane is free from flutter,control reversal,or divergenceif:4.4.1 VD/MDfor the airplane is less than 480 kph 260knots(EAS)and less than Mach 0.5,1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.30 onStructures.Current edition approved May 1,2015.Published August 2015.DOI:10.1520/F3093_F3093M-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.3Available from Federal Aviation Administration(FAA),800 IndependenceAve.,SW,Washington,DC 20591,http:/www.faa.gov.Available from U.S.Gov-ernment Printing Office Superintendent of Documents,732 N.Capitol St.,NW,MailStop:SDE,Washington,DC 20401,http:/www.access.gpo.gov.4Available from U.S.Government Printing Office Superintendent of Documents,732 N.Capitol St.,NW,Mail Stop:SDE,Washington,DC 20401,http:/www.access.gpo.gov.Copyright ASTM International,100 Barr Harbor Drive,PO Box C700,West Conshohocken,PA 19428-2959.United States1 4.4.2 The wing and aileron flutter prevention criteria,asrepresented by the wing torsional stiffness and aileron balancecriteria,are limited in use to airplanes without large massconcentrations(such as engines,floats,or fuel tanks in outerwing panels)along the wing span,and4.4.3 The airplane does not have a T-tail or other unconven-tional tail configurations,does not have unusual mass distribu-tions or other unconventional design features that affect theapplicability of the criteria,and has fixed-fin and fixed-stabilizer surfaces.4.5 For turbopropeller-powered airplanes,the dynamicevaluation must includ