1、Designation: F2352 14Standard Specification forDesign and Performance of Light Sport Gyroplane Aircraft1This standard is issued under the fixed designation F2352; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of last rev
2、ision. 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 covers the manufacture of gyroplanes.This specification includes design and performance require-ments for l
3、ight sport gyroplane aircraft.1.2 This specification applies to light gyroplane aircraftseeking civil aviation authority approval in the form of flightcertificates, flight permits, or other like documentation.1.3 A gyroplane for the purposes of this specification isdefined as a rotorcraft to be used
4、 for day VFR only, with rotorblades that are not engine-driven in flight and are supported inflight by the reaction of the air on a single rotor that rotatesfreely on a substantially vertical axis when the aircraft is inhorizontal flight.1.4 These requirements apply to light gyroplanes of ortho-dox
5、design.Aircraft having the following basic features will beso regarded:1.4.1 Rotors of either fixed collective pitch or collectivepitch control that are not adjustable in flight,1.4.2 Single engine with fixed or ground adjustable pitchpropeller,1.4.3 No more than two occupant seats, and1.4.4 Amaximu
6、m gross weight (MGW) of 725 kg (1600 lb)or less.1.5 Where it can be shown that a particular feature is similarin all significant respects to a feature that has historicallydemonstrated compliance with this specification and can beconsidered a separate entity in terms of its operation, thatfeature sh
7、all be deemed to be applicable and in compliancewith this specification.1.6 Where these requirements are inappropriate to particulardesign and construction features, it will be necessary to submitan appropriate amendment of this specification to ASTMCommittee F37 on Light Sport Aircraft for consider
8、ation andapproval.1.7 The values in SI units are to be regarded as the standard.The values in parentheses are for information only.1.8 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 establi
9、sh appro-priate safety and health practices and determine the applica-bility of regulatory limitations prior to use.1.9 Table of Contents:SectionScope 1Table of Contents 1.9Referenced Documents 2Terminology 3Definitions 3.1Acronyms 3.2Flight 4General 4.1Performance 4.2Controllability and Maneuverabi
10、lity 4.3Longitudinal Lateral and Directional Control 4.4Stability 4.5Ground-Handling Characteristics 4.6Miscellaneous Flight Requirements 4.7Structure 5General 5.1Flight Loads 5.2Engine Torque 5.3Control System Loads 5.4Stabilizing and Control Surfaces 5.5Ground Loads 5.6Main Component Requirements
11、5.7Emergency Landing Conditions 5.8Other Loads 5.9Design and Construction 6General 6.1Materials 6.2Fabrication Methods 6.3Locking of Connections 6.4Protection of Structure 6.5Inspection 6.6Provisions for Rigging and Derigging 6.7Material Strength Properties and Design Values 6.8Fatigue Strength 6.9S
12、pecial Factors of Safety 6.10Bearing Factors 6.10.2Fitting Factors 6.10.3Cable Factor 6.10.4Rotor Components Factor 6.10.5Flutter Prevention and Structural Stiffness 6.11Control Surfaces and Rotors 6.12Control Surface Installations (Other Than RotorBlades)6.13Control Surface Hinges (Other Than Rotor
13、 Blades) 6.14Rotor Mass Balance 6.15Rotor Blade Clearance 6.161This specification is under the jurisdiction of ASTM Committee F37 on LightSport Aircraft and is the direct responsibility of Subcommittee F37.50 on Gyro-plane.Current edition approved Nov. 1, 2014. Published November 2014. Originallyapp
14、roved in 2004. Last previous edition approved in 2011 as F2352 11. DOI:10.1520/F2352-14.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States1SectionRotor Head Bearings 6.17Control Systems 6.18Cockpit Design 6.19Powerplant 7General 7.1Engin
15、e 7.2Engine and Propeller Compatibility 7.3Rotor Spin-Up and Brake Systems 7.4Powerplant and Rotor System Compatibility 7.5Propeller Clearance 7.6Fuel System 7.7Oil System 7.8Cooling 7.9Induction System 7.10Exhaust System 7.11Powerplant Controls and Accessories 7.12Cowling and Nacelle 7.13Equipment
16、8General 8.1InstrumentsInstallation 8.2Electrical Systems and Equipment 8.3Miscellaneous Equipment 8.4Operating Limitations and Information 9General 9.1Airspeed Limitations 9.2Weight and Balance 9.3Powerplant and Propeller Limitations 9.4Pilot Operating Handbook, POH 9.5Maintenance Manual 9.6Marking
17、s and Placards 9.7Propellers 10Design and Construction 10.1Keywords 122. Referenced Documents2.1 ASTM Standards:2F2339 Practice for Design and Manufacture of Reciprocat-ing Spark Ignition Engines for Light Sport AircraftF2483 Practice for Maintenance and the Development ofMaintenance Manuals for Lig
18、ht Sport AircraftF2972 Specification for Light Sport Aircraft ManufacturersQuality Assurance System2.2 CAA Standard:3CAP 643 British Light Gyroplane AirworthinessRequirements, Section T2.3 Federal Aviation Regulations:4FAR-33 Airworthiness Standards: Aircraft Engines2.4 Joint Aviation Regulations:5C
19、S-E EASA Certification StandardEnginesCS-22 EASA Certification StandardSailplanes and Pow-ered SailplanesJAR-E Joint Aviation Requirements for EnginesJAR-22 Sailplanes and Powered Sailplanes3. Terminology3.1 Definitions:3.1.1 factor of safety, nmultiplier of limit load to deter-mine design ultimate
20、load.3.1.2 fire proof, adjcapable of withstanding for a period ofat least 15 min the application of heat by the standard flame.3.1.3 fire resistant, adjcapable of withstanding for aperiod of at least 5 min of heat by standard flame.3.1.4 limit load, nmaximum expected static load on acomponent.3.1.5
21、power off, nfor testing purposes, engine at idle.3.1.6 primary structure, nthose parts of the structure thefailure of which would endanger the gyroplane.3.1.7 ultimate load, nlimit load multiplied by the factor ofsafety.3.2 Acronyms:3.2.1 ASTMAmerican Society for Testing and Materials3.2.2 CAScalibr
22、ated airspeed3.2.3 CGcenter of gravity3.2.4 CNnormal force coefficient3.2.5 IASindicated airspeed3.2.6 ICAOInternational Aviation Organization3.2.7 LSAlight sport aircraft3.2.8 MGWmaximum gross weight3.2.9 MPRSminimum power required airspeed3.2.10 POHPilot Operating Handbook3.2.11 VFRVisual Flight R
23、ules3.2.12 VHstraight and level airspeed at full power3.2.13 VMINminimum controllable level flight airspeed,IAS3.2.14 VNEnever exceed airspeed, IAS3.2.15 VYbest rate of climb airspeed, IAS4. Flight4.1 General:4.1.1 Conditions of Compliance:4.1.1.1 Unless otherwise specified, each requirement of this
24、section must be met for the most adverse combinations ofweight and balance loading conditions within which thegyroplane will be operated.4.1.1.2 Unless otherwise stipulated, performance require-ments are at standard atmospheric conditions (15C (59F)and sea level pressure altitude).4.1.1.3 Each requi
25、rement of this section must be met for allconfigurations at which the gyroplane will be operated exceptas otherwise stated. (If, for example, a gyroplane is equippedwith a canopy or doors and it is intended that the gyroplanemay be operated with the canopy or doors removed, then thegyroplane must me
26、et the requirements both with and withoutthe canopy or doors installed.)4.1.2 Load Distribution LimitsA method must be speci-fied to determine the range of weight and balance of the pilot,passenger, and fuel (and ballast if required) that ensuressatisfactory control and safety margins. The range of
27、balance is2For 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 Civil Aviation Authority (CAA), htt
28、p:/www.caa.co.uk/.4Available from Federal Aviation Administration, 800 Independence Ave., SW,Washington, DC 20591.5Available from Global Engineering Documents, 15 Inverness Way, EastEnglewood, CO 80112-5704F2352 142normally determined by a “hang test” with specified angularlimits between a fixed air
29、frame component and a horizontalreference.NOTE 1The method of determination of proper weight and balancemust be specified in the POH.4.1.3 Weight LimitsThe MGW, which is the highestweight that complies with each applicable structural loadingcondition and each applicable flight requirement, must bees
30、tablished. The MGW must be specified in the POH.4.1.4 Empty Weight:4.1.4.1 The design empty weight shall be specified by themanufacturer.NOTE 2The design empty weight must be included in the POH.4.1.4.2 The actual empty weight shall be established byweighing the gyroplane with fixed ballast, require
31、d minimumequipment, and unusable fuel and, where appropriate, maxi-mum oil, engine coolant, and hydraulic fluid, and excludingusable fuel, weight of occupant(s), and other readily removableitems of load.4.1.4.3 The condition of the gyroplane at the time ofdetermining actual empty weight must be one
32、that is welldefined and easily repeated.4.1.5 Removable BallastRemovable ballast may be usedin compliance with the flight requirements of this section.4.1.6 Rotor Speed Limits:4.1.6.1 At the critical combinations of weight, altitude, andairspeed, the rotor speed must be stable and remain within thee
33、stablished safe range that would permit any expected maneu-ver to be performed safely. The established safe rotor speedrange must be identified in the POH.The established safe rangemust be established by the rotor blade manufacture or accept-able history of safe operation.4.1.6.2 The established saf
34、e range must be speed in consid-eration of spanwise and chordwise flexure cycles on the rotorat the worst combination of load and rotor speed, and rotorstiffness that assures the in-plane vibration natural frequency ishigher than the maximum rotor RPM by a minimum factor of1.2.4.1.6.3 Compliance may
35、 also be established by use ofacceptable aircraft manufacturing practices, correct use ofmaterials of known design strength and fatigue properties, andperformance testing at the extremes of the established saferange rotor speed.4.2 Performance:4.2.1 GeneralThe performance in accordance with Sec-tion
36、 4 applies:4.2.1.1 With normal piloting skill under average conditions;4.2.1.2 In and shall be corrected to International CivilAviation Organization (ICAO) defined standard atmosphere instill air conditions at sea level;4.2.1.3 Speeds shall be given in indicated (IAS) and cali-brated (CAS) airspeeds
37、;4.2.1.4 At the most critical weight and CG combination;4.2.1.5 At the most unfavorable center of gravity for eachcondition; and4.2.1.6 Using engine power not in excess of the maximumdeclared for the engine type and without exceeding power plantand propeller limitations in accordance with 9.4.4.2.2
38、TakeoffThe distance(s) required from rest, to takeoffand climb to 15 m (50 ft) above the takeoff surface, with zerowind, with normally accepted flight technique(s) must beestablished (with and without pre-rotator if it is intended thatthe gyroplane is to be operated both ways).NOTE 3These establishe
39、d takeoff distances must be identified in thePOH.4.2.3 ClimbThe time for climb from leaving the groundup to 300 m (1000 ft) above the field must be established andmust be less than 4 min.NOTE 4The established climb must be identified in the POH.4.2.4 Glide:4.2.4.1 The minimum achievable power off ra
40、te of descentand the associated airspeed must be established by test at themaximum gross weight with the gyroplane trimmed at theminimum rate of descent airspeed.NOTE 5The minimum power off rate of descent must be identified inthe POH.4.2.4.2 The maximum achievable power off glide ratio mustbe estab
41、lished by test at maximum gross weight with thegyroplane trimmed at the best glide ratio airspeed.NOTE 6The best glide ratio airspeed must be identified in the POH.4.2.5 Never Exceed Airspeed (VNE)The maximum safeoperating airspeed, considering the controllability,maneuverability, and stability requ
42、irements (4.3.1 4.5.7)must be established. This airspeed must be established for theworst-case power condition between idle and full power.NOTE 7The established VNEmust be identified in the POH.4.2.6 Minimum Controllable Airspeed for Level Flight,VMINThe minimum speed for level flight at maximum tak
43、eoffpower must be established.NOTE 8The established VMINmust be identified in the POH.4.2.7 Best Rate of Climb Airspeed (VY)The airspeed atwhich the maximum rate of climb is achieved must beestablished.NOTE 9The established VYmust be identified in the POH.4.2.8 Minimum Power Required Airspeed (MPRS)
44、Theairspeed at which minimum power is required for steady levelflight must be established.NOTE 10The established MPRS must be identified in the POH.4.2.9 Landing DistanceThe distance required to land andcome to rest from a point 15 m (50 ft) above the landingsurface, with zero wind, must be establis
45、hed. The approachairspeed to achieve this performance must be established.NOTE 11This landing distance and the approach speed to achieve thislanding distance must be identified in the POH.4.2.10 Maximum Operating AltitudeThe maximum safeoperating altitude considering the controllability,maneuverabil
46、ity, and stability requirements (4.3.1 4.5.7)F2352 143must be established, except that demonstrating safe operatingpressure altitudes in excess of 3000 m (10 000 ft) is notrequired.NOTE 12The maximum operating altitude must be identified in thePOH.4.2.11 Height/Velocity EnvelopeThe combinations ofhe
47、ight and forward airspeed from which a safe landing cannotbe made following engine failure must be established as alimiting height-speed envelope (graph).NOTE 13The height-speed envelope graph must be included in thePOH.4.3 Controllability and Maneuverability:4.3.1 GeneralThe gyroplane must be safel
48、y controllableand maneuverable with sufficient margin of control movementand blade freedom to correct for atmospheric turbulence andpermit control of the attitude of the gyroplane at all powersettings at the critical weight and balance at sea level and at themaximum operating altitude:4.3.1.1 During
49、 steady flight at all operable airspeeds up toVNE,4.3.1.2 During airspeed changes,4.3.1.3 During changes of engine power (including rapid orsudden application or loss of engine power), and4.3.1.4 During any maneuver appropriate to the type, in-cluding:(1) Takeoff,(2) Climb,(3) Turning flight,(4) Descent (power on and off), including vertical andspiral descents,(5) Landing (power on and off),(6) Recovery to full power climbing flight from an abortedlanding, and(7) Dynamic maneuvers including steep turns, straightpullouts,
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