1、Designation: F3082/F3082M 16Standard Specification forFlight for General Aviation Aeroplanes1This standard is issued under the fixed designation F3082/F3082M; the number immediately following the designation indicates the yearof original adoption or, in the case of revision, the year of last revisio
2、n. 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 establishes the airworthiness designstandards associated with aeroplane flight.1.2 The applicant for a design a
3、pproval shall seek theindividual guidance of their respective civil aviation authority(CAA) body concerning the use of this specification as part ofa certification plan. For information on which CAA regulatorybodies have accepted this specification (in whole or in part) asa means of compliance to th
4、eir small aircraft airworthinessregulations (hereinafter referred to as “the Rules”), refer toASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm), which includes CAA website links.1.3 UnitsThe values stated in either SI units or inch-pound units are to be regarded separately as standard. The
5、values stated in each system may not be exact equivalents;therefore, each system shall be used independently of the other.Combining values from the two systems may result in non-conformance with the standard.1.4 This standard does not purport to address all of thesafety concerns, if any, associated
6、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 AircraftF3063/F3063M Specification for Des
7、ign and Integration ofFuel/Energy Storage and Delivery System Installations forAeroplanesF3174/F3174M Specification for Establishing OperatingLimitations and Information for Aeroplanes3. Terminology3.1 See Terminology F3060 for definitions and abbrevia-tions.4. General4.1 Proof of Compliance:4.1.1 E
8、ach criterion of this specification shall be met at eachappropriate combination of weight and center of gravity withinthe range of loading conditions for which certification isrequested. This shall be shown by:4.1.1.1 Tests upon an aeroplane of the type for whichcertification is requested or by calc
9、ulations based on, and equalin accuracy to, the results of testing.4.1.1.2 Systematic investigation of each probable combina-tion of weight and center of gravity, if compliance cannot bereasonably inferred from combinations investigated.4.1.2 The general tolerances in Table 1 are allowed duringfligh
10、t testing. However, greater tolerances may be allowed inparticular tests, if properly justified.4.2 Load Distribution Limits:4.2.1 Ranges of weights and centers of gravity within whichthe aeroplane may be safely operated shall be established. If aweight and center of gravity combination is allowable
11、 onlywithin certain lateral load distribution limits that could beinadvertently exceeded, these limits shall be established for thecorresponding weight and center of gravity combinations.4.2.2 The load distribution limits shall not exceed any of thefollowing:(1) The selected limits,(2) The limits at
12、 which the structure is proven, or(3) The limits at which compliance with each applicableflight requirement is shown.4.3 Weight Limits:4.3.1 Maximum WeightThe maximum weight is the high-est weight at which compliance with each applicable require-ment (other than those complied with at the design lan
13、dingweight) is shown. The maximum weight shall be established sothat it is:4.3.1.1 Not more than the least of:(1) The highest weight selected by the applicant;(2) The design maximum weight, which is the highestweight at which compliance with each applicable structuralloading condition (other than th
14、ose complied with at the designlanding weight) is shown;(3) The highest weight at which compliance with eachapplicable flight requirement is shown.4.3.1.2 Not less than the weight with:1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct re
15、sponsibility of Subcommittee F44.20 on Flight.Current edition approved Feb. 1, 2016. Published March 2016. DOI: 10.1520/F3082_F3082M-16.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume in
16、formation, 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) Each seat occupied, assuming a weight of 77 kg 170lb for each occupant or 86 kg 190 lb for Level 1 aeroplan
17、eswith a stall speed of 45 kts or lower and for aeroplanesapproved for aerobatics except that seats other than pilot seatsmay be placarded for a lesser weight, and(a) Oil at full capacity,(b) At least enough fuel for maximum continuous poweroperation of at least 30 min for day-VFR approved aeroplane
18、sand at least 45 min for night-VFR and IFR approved aero-planes or for Level 1 aeroplanes with a stall speed of 45 kts orless enough fuel for1hofoperation at maximum continuouspower, or(2) The required minimum crew and fuel and oil to fullcapacity.4.3.2 Minimum WeightThe minimum weight (the lowestwe
19、ight at which compliance with each applicable requirementis shown) shall be established so that it is not more than thesum of:4.3.2.1 The empty weight determined under 4.4,4.3.2.2 The weight of the required minimum crew (assum-ing a weight of 77 kg 170 lb for each crewmember), or forLevel 1 aeroplan
20、es with a stall speed of 45 kts or less a weightof 55 kg 120 lb.4.3.2.3 For turbojet powered aeroplanes, 5 % of the totalfuel capacity of that particular fuel tank arrangement underinvestigation.4.3.2.4 For other aeroplanes, the weight of the fuel neces-sary for 30 min of operation at maximum contin
21、uous power.4.4 Empty Weight and Corresponding Center of Gravity:4.4.1 The empty weight and corresponding center of gravityshall be determined by weighing the aeroplane with:4.4.1.1 Fixed ballast,4.4.1.2 Unusable fuel determined under SpecificationF3063/F3063M,4.4.1.3 Full operating fluids including:
22、(1) Oil,(2) Hydraulic fluid,(3) Other fluids required for normal operation of aeroplanesystems, except potable water, lavatory precharge water, andwater intended for injection in the engines.4.4.2 The condition of the aeroplane at the time of deter-mining empty weight shall be one that is well defin
23、ed and canbe easily repeated.4.5 Removable BallastRemovable ballast may be used inshowing compliance with the flight requirements if:4.5.1 The place for carrying ballast is properly designed andinstalled and is marked under Specification F3174/F3174M.4.5.2 Instructions are included in the aeroplane
24、flightmanual, approved manual material, or markings and placardsfor the proper placement of the removable ballast under eachloading condition for which removable ballast is necessary.5. Keywords5.1 aircraft; airworthiness; design; flight; general aviation;operational limitations; performanceASTM Int
25、ernational takes no position respecting the validity of any patent rights asserted in connection with any item mentionedin this standard. Users of this standard are expressly advised that determination of the validity of any such patent rights, and the riskof infringement of such rights, are entirel
26、y their own responsibility.This standard is subject to revision at any time by the responsible technical committee and must be reviewed every five years andif not revised, either reapproved or withdrawn. Your comments are invited either for revision of this standard or for additional standardsand sh
27、ould be addressed to ASTM International Headquarters. Your comments will receive careful consideration at a meeting of theresponsible technical committee, which you may attend. If you feel that your comments have not received a fair hearing you shouldmake your views known to the ASTM Committee on St
28、andards, at the address shown below.This standard is copyrighted by ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959,United States. Individual reprints (single or multiple copies) of this standard may be obtained by contacting ASTM at the aboveaddress or at 61
29、0-832-9585 (phone), 610-832-9555 (fax), or serviceastm.org (e-mail); or through the ASTM website(www.astm.org). Permission rights to photocopy the standard may also be secured from the Copyright Clearance Center, 222Rosewood Drive, Danvers, MA 01923, Tel: (978) 646-2600; http:/ 1 General TolerancesItem ToleranceWeight +5 %, -10 %Critical items affected by weight +5 %, -1 %C.G. 7 % total travelF3082/F3082M 162
