ASTM_F_2244_-_14.pdf

Designation:F224414Standard Specification forDesign and Performance Requirements for PoweredParachute Aircraft1This standard is issued under the fixed designation F2244;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 The following requirements apply for the manufactureof powered parachute aircraft.This specification includesdesign and performance requirements for powered parachuteaircraft.1.2 This specification applies to powered parachute aircraftseeking civil aviation authority approval,in the form of flightcertificates,flight permits,or other like documentation.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 requirements prior to use.2.Referenced Documents2.1 ASTM Standards:2F2241 Specification for ContinuedAirworthiness System forPowered Parachute AircraftF2242 Specification for Production Acceptance Testing Sys-tem for Powered Parachute AircraftF2243 Specification for Required Product Information to beProvided with Powered Parachute AircraftF2483 Practice for Maintenance and the Development ofMaintenance Manuals for Light Sport AircraftF2563 Practice for Kit Assembly Instructions of AircraftIntended Primarily for RecreationF2972 Specification for Light Sport Aircraft ManufacturersQuality Assurance System3.Terminology3.1 Definitions:3.1.1 gross weight,ntotal aircraft system weight(s)attakeoff.3.1.2 maximum takeoff weight,ngross weight limit asdefined by the manufacturer,proven through compliance withthis specification and placarded on the aircraft as the not-to-exceed gross weight.3.1.3 powered parachute,naircraft comprised of a flexibleor semi-rigid wing connected to a fuselage in such a way thatthe wing is not in position for flight until the aircraft is inmotion.That aircraft has a fuselage with seats,engine,andwheels(or floats),such that the wing and engine cannot beflown without the wheels(or floats)and seat(s).Unique to thepowered parachute is the large displacement between thecenter of lift(high)and the center of gravity(low),which ispendulum effect.Pendulum effect limits angle of attackchanges,provides stall resistance and maintains flight stability.4.Flight4.1 Performance Requirements:4.1.1 Proof of ComplianceEach of the following require-ments shall be met at the maximum takeoff weight and mostcritical center of gravity(CG)position.To the extent that CGadjustment devices may be adjusted for flight,these compo-nents will be evaluated in the least favorable recommendedposition as it affects either performance or structural strength.4.1.2 General PerformanceAll performance requirementsapply in and shall be corrected to International Civil AviationOrganization(ICAO)defined standard atmosphere in still airconditions at sea level.Speeds shall be given in indicated(IAS)and calibrated(CAS)airspeeds in miles per hour(MPH).4.1.2.1 Wing PerformanceFor straight-ahead flight andturns in either direction during climb,cruise,descent,andlanding flare,it shall be shown that the limits of control inputare less than the wing stall limitations:(1)If a fixed wing trim is available;(2)If adjustable wing trim is available,it shall be tested toboth the most negative and most positive trim settings;and(3)If separate left wing and right wing trim devises areavailable,each shall be tested to both the maximum-left-andminimum-right trim settings and the minimum-left-and-maximum-right trim settings.4.1.2.2 ClimbThe following shall be measured:1This specification is under the jurisdiction of ASTM Committee F37 on LightSport Aircraft and is the direct responsibility of Subcommittee F37.30 on PowerParachute.Current edition approved Nov.1,2014.Published November 2014.Originallyapproved in 2003.Last previous edition approved in 2013 as F2244 13.DOI:10.1520/F2244-14.2For 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(1)Distance to clear a 15 m(50 ft)obstacle not to exceed213 m(700 ft)from point of liftoff.(2)LandingThe total landing distance over a 15 m(50 ft)obstacle shall be achieved within 183 m(600 ft)total distance.4.1.2.3 Controllability and ManeuverabilityThe aircraftshall be safely controllable and maneuverable during takeoff,climb,level flight(cruise),approach,and landing(power offand on)with primary controls of turn and throttle and thepossibility of combined turn displacement