1、Designation: F2244 14Standard 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
2、 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
3、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 thesaf
4、ety 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 Contin
5、uedAirworthiness 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 ofMain
6、tenance 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) attake
7、off.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 i
8、n 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 displac
9、ement 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
10、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.
11、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
12、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
13、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 shal
14、l 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 approve
15、d 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 In
16、ternational, 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) t
17、otal 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 for flar
18、e.(1) Demonstrate a smooth transition between all flightconditions shall be possible without excessive pilot skills norexceeding pilot forces of 59.1 kg (130 lb) for the rudder petal,9.1 kg (20 lb) prolonged application.(2) LandingIt must be shown that in the event of anengine or propeller failure t
19、hat a safe descent and landing canbe made. It must be shown that a pilot of normal skill canachieve landing sink rates of no more than 2.4 m/s (8 ft/s).4.1.2.4 Reference ParametersReference velocity param-eters V(S1) and V(H) are to be calculated as follows:VS1! 5 square root W*391/S!VH! 5 2*VS1! 5
20、square root4*W*391/S!where:V = mph,W = lbs, andS =ft2.4.1.3 Stability and Control:4.1.3.1 Longitudinal StabilityLongitudinal stability of theaircraft will be demonstrated by performing two minutes offlight without control input for three conditions. In each case,the aircraft must not enter into dang
21、erous or unusual attitudes.Test must be conducted at maximum gross weight, withminimum of in-flight turbulence.4.1.3.2 The three conditions are:(1) Maximum power setting climb,(2) Zero power descent, and(3) Cruise setting power level flight.4.1.3.3 Lateral and Directional Stability:(1) Lateral stabi
22、lity will be demonstrated by maintainingthe controls in a neutral position, which will initially give anunaccelerated level flight condition. The aircraft must not enterinto a dangerous attitude during the 2 min that the flightcontrols are fixed. Test must be conducted at maximum takeoffweight, with
23、 minimum of in-flight turbulence(2) Directional stability will be demonstrated by a separateand full deflection of each directional flight control for threefull turns of 360 without the aircraft entering any dangerousflight attitude during the maneuver. Test must be conducted atminimum flight weight
24、, with minimum of in-flight turbulence.The demonstrated turn rate shall not be less than 12/s (30 s fora 360 turn) in either direction.4.1.3.4 Parachute Re-InflationChute re-inflation may beconducted detached from the cage, or on a suitable testapparatus.(1) Ground Roll Chute CollapseThe chute manuf
25、acturershall demonstrate techniques that recover tip and wing collapseconditions as documented in the Aircraft Operating Instruc-tions.(2) In-Flight CollapseAt least one type of in-flight chutecollapse and recovery shall be demonstrated.5. Structure5.1 LoadsUnless otherwise specified, all requiremen
26、ts arespecified in terms of limit load.5.1.1 Ultimate loads are limit loads multiplied by the factorof safety defined below.5.1.1.1 Loads shall be redistributed if the deformationsaffect them significantly.5.1.2 Factors of SafetyThe factor of safety is 1.5, exceptas shown in the following:5.1.2.1 3.
27、0 on castings,5.1.2.2 1.8 on fittings,5.1.2.3 6.67 on control surface hinges,5.1.2.4 3.3 on push-pull control systems, and5.1.2.5 2.0 on cable control systems.5.1.3 Strength and Deformation:5.1.3.1 The structure must be able to support limit loadswithout permanent deformation of the structure.5.1.3.
28、2 The structure must be shown by analysis, test oranalysis supported by test, to be able to withstand ultimateloads without failure.5.1.3.3 The structure shall be able to withstand ultimateloads for 3 s without failure when proof is by static test. Whendynamic tests are used to demonstrate strength,
29、 the three-second requirement does not apply. Local failures or structuralinstabilities between limit load and ultimate load are acceptableif the structure can sustain the required ultimate load for threeseconds.5.2 Proof of StructureEach critical load requirement shallbe investigated either by cons
30、ervative analysis or tests, or acombination of both.5.2.1 Proof of Strength-WingsTest the wing design for apowered parachute aircraft to verify the critical ultimate loads.The wing designer shall provide the wing and risers designload capability to the point of attachment of the risers. Thewing desi
31、gner shall provide the factor of safety demonstratedin wing and riser tests to the fuselage designer.NOTE 1Advisory informationWing designer information providedto the fuselage designer shall be known as “pass-through” information.5.2.2 Load Factor:5.2.2.1 Positiven = 2.25 (comprised of a 1.5 maneuv
32、eringload multiplied by a 1.5 gust load factor). The maneuveringload must be increased for any conditions for which thefollowing equation indicates a g loading higher than 1.5 gs.The calculated g load shall then be used as the maneuveringload. Maneuvering Load Factor: N = 1/cos(B), where B=arctan (R
33、T V/1255), where RT is turning rate in degrees persecond, and V is true airspeed in mph. For example, V =26mph, RT = 60/s (360 turn in 6 s), N =1.595. N 1.5 and themaneuvering load factor rises to 1.595. As a result, the limitload is 1.5 1.595 = 2.393 gs. See Fig. 1 for a reference graph.5.2.2.2 Neg
34、ativen =0.5.2.3 Fuselage LoadsThe airframe must be capable ofsupporting all lifting forces created by the parachute, anypropulsive device, systems, persons, and landing loads.F2244 1425.2.4 Control Surface LoadsControl surface loads on apowered parachute are related through the turn lines and shallb
35、e evaluated at loads defined in flight tests of the wing by thewing manufacturer.5.2.5 Ground Gust ConditionsA powered parachute wingis not inflated for normal ground conditions. As a result,classical ground gust load concerns do not exist. Rolling gustloads for takeoff or landing are considered as
36、part of thelanding ground load conditions.5.2.6 Control System and Supporting StructureThe con-trol system structure shall be designed to withstand maximumforces and in the case of dual controls the relevant system shallbe designed for the pilots operating in opposition, if greaterthan the control s
37、ystem forces.5.2.7 Ground Load ConditionsDesign features shall limitthe landing sink rate to less than, or equal to, 3 m/s (10 ft/s).Testing by drop test will use a drop height to achievea3m/s(10 ft/s) drop rate in a nose high simulation of flare. This willbe a “dead drop” test at maximum takeoff we
38、ight.5.2.8 Nose Wheel ConditionsA 2.25 times maximumloaded static load vertical in each case with 1.8 times maxi-mum static load applied at the axle acting aft, or 0.9 timesmaximum static load at the axle acting forward, or 1.57 timesmaximum static load acting at the surface as a side load. Wheremax
39、imum static load is the vertical load on the nose wheel atmaximum takeoff weight and the related forward most CG.5.2.9 Emergency Landing ConditionsDesign structure toprotect each occupant from serious injury when the aircraftexperiences three independent ultimate load conditions: 1.5-gsupward; 6-gs
40、forward; 3-gs sideward. Test articles that holdthis load for more than 3 s are considered to have passed.NOTE 2Advisory Information(1) Occupants restrained by availablesafety harnesses. (2) Consider all items of mass behind, above, below, andlateral to the occupants (engine, baggage, fuel, ballast,
41、and so forth). (3)The design must have design features to protect an occupant or occupantsin the event of a turnover.6. Design and Construction6.1 GeneralThe integrity of any novel or unusual designfeature having an important bearing on safety shall be estab-lished by a test.6.2 Materials and Workma
42、nshipMaterials shall be suit-able and durable for the intended use and design values(strength) must be chosen so that structural under strengthbecause of material variations is unlikely as shown by test,analysis, service history or manufacturer certification.6.2.1 Fabrication Methods:6.2.1.1 Workman
43、ship of manufactured parts, assemblies,and aircraft shall be of high standard.6.2.1.2 Methods of fabrication shall produce consistentlysound structures.6.2.1.3 Process specifications shall be followed where re-quired.6.2.2 Protection of StructureProtection of the structureagainst weathering, corrosi
44、on, and abrasion, as well as suitableventilation and drainage shall be provided.6.2.3 AccessibilityAccessibility for principal structuraland control system inspection, adjustment, maintenance, andrepair shall be provided.6.2.4 Control Systems-Operation TestsIt must be shownby functional test that th
45、e control system is free from jamming,excessive friction, or excessive deflection when the maximumpilot forces are applied from the cockpit.6.2.5 Pilot CompartmentPilot comfort, good visibility(instruments, placards and outside), accessibility, exit, andability to reach all controls for smooth and p
46、ositive operationshall be provided.FIG. 1 Reference GraphF2244 1437. Power Plant7.1 The power plant installation shall be easily accessiblefor inspection and maintenance.7.2 EngineA FAA type certificate is not required for apowered parachute aircraft engine. Engine installation andtesting shall demo
47、nstrate operation and reliability consistentwith industry-accepted practices.NOTE 3Advisory InformationPowered parachutes are light lowspeed aircraft with excellent short field landing capabilities. The craft arenot intended for flight in airspace in which safety depends on continuedengine operation
48、. The engine is not considered to be a safety-of-flightcomponent.7.3 Fuel Tank TestsThe fuel tank shall be pressure testedto 24.1 kPa (3.5 psi) (2.4 m (8 ft) of water column) andinstalled to withstand prescribed load factors.7.4 Fuel Tank VentsA fuel tank vent that does not siphonin flight shall be
49、provided. The fuel vent system does notsiphon in the event of roll over.7.5 Fuel Strainer or FilterA replaceable fuel filter, acces-sible for drainage and cleaning, or both, shall be included in thesystem.8. Equipment8.1 InstrumentsAn airspeed indicator is not a requiredinstrument. Required instruments include:8.1.1 A fuel quantity indicator,8.1.2 An engine kill switch, and8.1.3 Engine instruments identified as necessary by theengine designer or manufacturer.NOTE 4Advisory Information(1) Powered parachute aircraft a
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