ASTM_F_3083_-_F_3083M_-_15.pdf

Designation:F3083/F3083M15Standard Specification forEmergency Conditions,Occupant Safety andAccommodations1This standard is issued under the fixed designation F3083/F3083M;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 emergency conditions,oc-cupant safety and accommodations for occupants and cargo.1.2 The applicant for a design approval must seek theindividual guidance of their respective CAA body concerningthe use of this standard as part of a certification plan.Forinformation on which CAA regulatory bodies have acceptedthis standard(in whole or in part)as a means of compliance totheir airworthiness regulations(Hereinafter referred to as“theRules”),refer to ASTM F44 webpage(www.ASTM.org/COMITTEE/F44.htm)which includes CAA website links.1.3 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.1.4 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 Aircraft2.2 U.S.Code of Federal Regulations:314 CFR Part 23 Airworthiness Standards:Normal,Utility,Aerobatic and Commuter Category Airplanes49 CFR Part 572 Anthropomorphic Test Devices(Subpart B)2.3 European Aviation Safety Agency Regulations:4CS-23 Certification Specifications for Normal,Utility,Aerobatic,and Commuter Category Aeroplanes(Amend-ment 3)CS-VLA Certifications Specifications for Very Light Aero-planes(Amendment 1)2.4 Other Standard:PH1.25 Standard Specification for Safety Photographic Film3.Terminology3.1 See Terminology F3060 for definitions of terms used inthis standard.3.2 Abbreviations:3.2.1 gppeak deceleration for seat/restraint system test3.2.2 HIChead injury criteria3.2.3 trrise time to the peak deceleration,gp4.Emergency Landing Conditions4.1 General:4.1.1 The airplane,although it may be damaged in emer-gency landing conditions,must be designed as prescribed inthis section to protect each occupant under those conditions.4.1.2 The structure must be designed to give each occupantevery reasonable chance of escaping serious injury when:4.1.2.1 Proper use is made of the seats,safety belts,andshoulder harnesses provided for in the design.4.1.2.2 The occupant experiences the static inertia loadscorresponding to the following ultimate load factors:(1)Upward,3.0 g,or 4.5 g for airplanes approved foraerobatics;(2)Forward,9.0 g;(3)Sideward,1.5 g;and(4)Downward,6.0 g when certification to the emergencyexit provisions of 5.6.4.4 is requested.4.1.2.3 The items of mass within the cabin,that could injurean occupant,experience the static inertia loads correspondingto the following ultimate load factors:(1)For Level 1 aircraft with a VS0not more than 83 km/h45 kts: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 June 1,2015.Published September 2015.DOI:10.1520/F3083_F3083M-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 the U.S.Government Printing Office at www.ecfr.gov.4Available from the European Aviation Safety Agency at www.easa.europa.eu.Copyright ASTM International,100 Barr Harbor Drive,PO Box C700,West Conshohocken,PA 19428-2959.United States1(a)Upward,3.0 g;(b)Forward,9.0 g;and(c)Sideward,1.5 g.(2)For all other aircraft:(a)Upward,3.0 g;(b)Forward,18.0 g;and(c)Sideward,4.5 g.4.1.3 Each airplane with retractable landing gear must bedesigned to protect each occupant in a landing:4.1.3.1 With the wheels retracted;4.1.3.2 With moderate descent velocity;and4.1.3.3 Assuming,in the absence of a more rational analy-sis:(1)A downward ultimate inertia force of 3 g;and(2)A coefficient of friction of 0.5 at the ground.4.1.4 Unless it is established that a turnover is unlikelyduring an emergency landing,the structure must be designed toprotect the occupants in a complete turnover.For determiningthe loads to be applied to the inverted airplane after a turnover,in the absence of a more rational analysis,an upward ultimateinertia load factor of 3.0 g and a coefficient of friction with theground of 0.5 must be used.4.1