ASTM F3082 F3082M-2017 Standard Specification for Weights and Centers of Gravity of Aircraft《飞机重量和重心的标准规格》.pdf

1、Designation: F3082/F3082M 16F3082/F3082M 17Standard Specification forFlight for General Aviation AeroplanesWeights and Centersof Gravity of Aircraft1This standard is issued under the fixed designation F3082/F3082M; the number immediately following the designation indicates the yearof original adopti

2、on 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 establishes the airworthiness design standards associat

3、ed with aeroplane flight.weight and center ofgravity.1.2 The term “aeroplane” is utilized in this specification as it was originally conceived for normal category fixed wing aircraftwith a maximum certificated weight of 19 000 lb or less and a passenger seating configuration up to 19 as defined in t

4、he Rules.However, these standards may be more broadly applicable and their usage should not be unnecessarily limited.1.3 The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA)body concerning the use of this specification as part of a

5、 certification plan. For information on which CAA regulatory bodies haveaccepted this specification (in whole or in part) as a means of compliance to their small aircraft airworthiness regulations(hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F4

6、4.htm), whichincludes CAA website links.1.4 UnitsThe values stated in either SI units or inch-pound units are to be regarded separately as standard. The values statedin each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining valuesfrom the

7、 two systems may result in non-conformance with the standard.1.5 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibilityof the user of this standard to establish appropriate safety safety, health, and healthenvironmental practic

8、es and determine theapplicability of regulatory limitations prior to use.1.6 This international standard was developed in accordance with internationally recognized principles on standardizationestablished in the Decision on Principles for the Development of International Standards, Guides and Recom

9、mendations issuedby the World Trade Organization Technical Barriers to Trade (TBT) Committee.2. Referenced Documents2.1 ASTM Standards:2F3060 Terminology for AircraftF3061 Specification for Systems and Equipment in Small AircraftF3063/F3063M Specification for Design and Integration of Fuel/Energy St

10、orage and Delivery System Installations forAeroplanesF3174/F3174M Specification for Establishing Operating Limitations and Information for AeroplanesF3120 Specification for Ice Protection for General Aviation Aircraft3. Terminology3.1 See Terminology F3060 for definitions and abbreviations.4. Genera

11、l4.1 Proof of Compliance: Weight and Center of GravityThe applicant must determine limits for weights and centers of gravitythat provide for the safe operation of the airplane.1 This specification is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsi

12、bility of Subcommittee F44.20 on Flight.Current edition approved Feb. 1, 2016Oct. 15, 2017. Published March 2016November 2017. Originally approved in 2016. Last previous edition approved in 2016 asF3082/F3082M 16. DOI: 10.1520/F3082_F3082M-16.10.1520/F3082_F3082M-17.2 For referencedASTM standards, v

13、isit theASTM website, www.astm.org, or contactASTM Customer Service at serviceastm.org. For Annual Book of ASTM Standardsvolume information, refer to the standards Document Summary page on the ASTM website.This document is not an ASTM standard and is intended only to provide the user of an ASTM stan

14、dard an indication of what changes have been made to the previous version. Becauseit may not be technically possible to adequately depict all changes accurately, ASTM recommends that users consult prior editions as appropriate. In all cases only the current versionof the standard as published by AST

15、M is to be considered the official document.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States14.1.1 Each criterion of this specification of the Flight Standards shall be met at each appropriate combination criticalcombinations of weight

16、 and center of gravity within the range of loading conditions for which certification is requested. This shallbe shown by:4.1.1.1 Tests upon an aeroplane of the type for which certification is requested or by calculations based on, and equal inaccuracy to, the results of testing.testing, and4.1.1.2

17、Systematic investigation of each probable combination 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 during flight testing. However, greater tolerances may be allowed inparticular tests, i

18、f properly justified.4.2 Load Distribution Limits:4.2.1 Ranges of weights and centers of gravity within which the aeroplane may be safely operated shall be established. If aweight and center of gravity combination is allowable only within certain lateral load distribution limits that could be inadve

19、rtentlyexceeded, these limits shall be established for the corresponding weight and center of gravity combinations.4.2.2 The load distribution limits shall not exceed any of the following:(1) The selected limits,(2) The limits at which the structure is proven, or(3) The limits at which compliance wi

20、th each applicable flight requirement is shown.4.3 Weight Limits:4.3.1 Maximum WeightThe maximum weight is the highest weight at which compliance with each applicable requirement(other than those complied with at the design landing weight) is shown. The maximum weight shall be established so that it

21、 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 highest weight at which compliance with each applicable structural loadingcondition (other than those complied with at the design landing weight) is shown;(3) The highe

22、st weight at which compliance with each applicable flight requirement is shown.shown, and4.3.1.2 Not less than the weight with:(1) Each seat occupied, assuming a weight of 77 kg 170 lb for each occupant or 86 kg 190 lb for Level 1 aeroplanes witha stall speed of 45 kts or lower and for aeroplanes ap

23、proved for aerobatics except that seats other than pilot seats may be placardedfor a lesser weight, and(a) Oil at full capacity,(b) At least enough fuel for maximum continuous power operation of at least 30 min for day-VFR approved aeroplanes andat least 45 min for night-VFR and IFR approved aeropla

24、nes or for Level 1 aeroplanes with a stall speed of 45 kts or less enoughfuel for 1 h of operation at maximum continuous power, or(2) The required minimum crew, and fuel and oil to full capacity.4.3.2 Minimum WeightThe minimum weight (the lowest weight at which compliance with each applicable requir

25、ement isshown) shall be established so that it is not more than the sum of:4.3.2.1 The empty weight determined under 4.4,4.3.2.2 The weight of the required minimum crew (assuming a weight of 77 kg 170 lb for each crewmember), or for Level1 aeroplanes with a stall speed of 45 kts or less a weight of

26、55 kg 120 lb.lb, and4.3.2.3 For turbojet powered aeroplanes, 5 % of the total fuel capacity of that particular fuel tank arrangement underinvestigation.4.3.2.4 For other aeroplanes, the weight of the fuel necessary for 30 min of operation at maximum continuous power.4.4 Empty Weight and Correspondin

27、g Center of Gravity:4.4.1 The empty weight and corresponding center of gravity shall be determined by weighing the aeroplane with:4.4.1.1 Fixed ballast,4.4.1.2 Unusable fuel determined under Specification F3063/F3063M, and4.4.1.3 Full operating fluids including:(1) Oil,(2) Hydraulic fluid, andTABLE

28、1 General TolerancesItem ToleranceWeight +5 %, -10 %Weight +5 %, 10 %Critical items affected by weight +5 %, -1 %Critical items affected by weight +5 %, 1 %C.G. 7 % total travelF3082/F3082M 172(3) Other fluids required for normal operation of aeroplane systems, except potable water, lavatory prechar

29、ge water, and waterintended for injection in the engines.4.4.2 The condition of the aeroplane at the time of determining empty weight shall be one that is well defined and can be easilyrepeated.4.5 Removable BallastRemovable ballast may be used in showing compliance with the flight requirements if:4

30、.5.1 The place for carrying ballast is properly designed and installed and is marked under Specification easily accessible toenable, during pre-flight inspection, that the ballast is properly installed.F3174/F3174M.4.5.2 Instructions are included in the aeroplane flight manual, approved manual mater

31、ial, or markings and placards for theproper placement of the removable ballast under each loading condition for which removable ballast is necessary.5. Keywords5.1 aircraft; airworthiness; design; flight; general aviation; operational limitations; performanceASTM International takes no position resp

32、ecting 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 entirely their own responsibility.This s

33、tandard 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 should be addressed to ASTM Internat

34、ional 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 Standards, at the address shown belo

35、w.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 610-832-9585 (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:/ 173