ASTM F2506-2007 Standard Specification for Design and Testing of Fixed-Pitch or Ground Adjustable Light Sport Aircraft Propellers《固定螺距或地面可调整轻型运动飞机螺旋桨设计和测试用标准规范》.pdf

《ASTM F2506-2007 Standard Specification for Design and Testing of Fixed-Pitch or Ground Adjustable Light Sport Aircraft Propellers《固定螺距或地面可调整轻型运动飞机螺旋桨设计和测试用标准规范》.pdf》由会员分享，可在线阅读，更多相关《ASTM F2506-2007 Standard Specification for Design and Testing of Fixed-Pitch or Ground Adjustable Light Sport Aircraft Propellers《固定螺距或地面可调整轻型运动飞机螺旋桨设计和测试用标准规范》.pdf（4页珍藏版）》请在麦多课文档分享上搜索。

1、Designation: F 2506 07Standard Specification forDesign and Testing of Fixed-Pitch or Ground AdjustableLight Sport Aircraft Propellers1This standard is issued under the fixed designation F 2506; the number immediately following the designation indicates the year oforiginal adoption or, in the case of

2、 revision, the year of last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon (e) indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification covers the establishment of the mini-mum requirements for the design, testi

3、ng, and quality assur-ance of fixed-pitch or ground adjustable propellers for lightsport aircraft. These propellers are used on light aircraft, andcould be used with engines conforming to Practice F 2339.1.2 This specification is intended for use by manufacturersof propellers for light sport aircraf

4、t.1.3 This specification does not address the airframe instal-lation requirements for propellers.1.4 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

5、practices and to determine theapplicability of regulatory limitations prior to use.2. Referenced Documents2.1 ASTM Standards:2F 2339 Practice for Design and Manufacture of Reciprocat-ing Spark Ignition Engines for Light Sport Aircraft3. Terminology3.1 Definitions:3.1.1 blade, nthe aerodynamic portio

6、n of a propellerwhich is rotated through and acts on the air.3.1.2 blade root, nthe portion of the blade that interfaceswith the hub and provides retention.3.1.3 fixed pitch propeller, na propeller with no capacityfor pitch setting adjustment.3.1.4 ground adjustable propeller, na propeller whosepitc

7、h setting is adjustable only when the aircraft is on theground and the propeller is not rotating.3.1.5 hub, nany device that retains the blades of apropeller assembly.3.1.6 pitch setting, nthe propeller blade setting as deter-mined by the blade angle measured in a manner, and at aradius, specified b

8、y the instruction manual for the propeller.3.1.7 propeller, na device for propelling an aircraft thathas blades on an engine-driven shaft and that, when rotated,produces by its action on the air, a thrust approximatelyperpendicular to its plane of rotation.4. General4.1 Each manufacturer who claims

9、compliance to this speci-fication must be able to show compliance with the applicablerequirements of this specification.4.2 Manufacturers must prepare and make available a list ofacceptable engine-propeller combinations.4.3 Manufacturers must prepare and make available anoperating manual or manuals

10、containing, at minimum, thefollowing information:4.3.1 An overall description of the propeller and its features.4.3.2 The mass moment of inertia of the propeller about itsrotational axis.4.3.3 Instructions for installation of the propeller.4.3.4 Instructions for operation of the propeller.4.3.5 The

11、maximum allowable engine power and rotationalspeed and any other propeller operating limitations foundnecessary by the manufacturer for the safe operation of thepropeller.4.3.6 For ground adjustable propellers, instructions for pitchadjustment and the minimum and maximum pitch settingsallowed during

12、 operation.4.3.7 Instructions for removal of the propeller.4.4 Each manufacturer must prepare and make available amaintenance manual. The maintenance manual is intended toprovide for continued safe and proper operation of the propel-ler throughout its life cycle and contains, at minimum, thefollowin

13、g content:4.4.1 A maintenance schedule that provides the recom-mended periods at which the propeller should be cleaned,adjusted, inspected, and tested.4.4.2 The applicable damage and wear allowances.1This specification is under the jurisdiction of ASTM Committee F37 on LightSport Aircraft and is the

14、 direct responsibility of Subcommittee F37.70 on CrossCutting.Current edition approved Jan. 1, 2007. Published February 2007.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume information,

15、refer to the standards Document Summary page onthe ASTM website.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.4.4.3 Any applicable maintenance and overhaul instruc-tions, which include the following:4.4.3.1 A list of tools needed.4

16、.4.3.2 Skills or training required for personnel performingthe work.4.4.3.3 Inspections required.4.4.3.4 Details of repair and overhaul sequence and meth-ods.4.4.3.5 Applicable testing requirements.4.4.4 If a manufacturer deems it necessary to set mandatoryreplacement intervals of propellers or prop

17、eller components,the details of this requirement shall be stated in a separate,clearly distinguishable section entitled Life Limitations.5. Design and Construction5.1 Design FeaturesThe propeller may not have designfeatures that have been shown to be hazardous or unreliableunless the suitability of

18、each questionable design detail or partcan be established by tests.5.2 MaterialsThe suitability and durability of materialsused in the propeller must:5.2.1 be established on the basis of in-service experience ortests; and5.2.2 conform to documented specifications that ensure thatstrength and other m

19、aterial properties consistently meet orexceed those used in the initial design and qualification testing.5.3 DurabilityEach part of the propeller must be designedand constructed with consideration of likely in-service damageand wear. The propeller must be able to operate normallybetween inspection a

20、nd overhaul periods at the maximumdamage and wear limits published in the maintenance manual.5.4 Ground-Adjustable PropellersThe adjustment systemof a ground-adjustable propeller must be designed such that nosingle failure or malfunction in that system during normal oremergency operation will result

21、 in unacceptable changes inpropeller blade pitch setting. Failure of structural elementsneed not be considered if the occurrence of such a failure isexpected to be extremely remote.5.5 Propeller Strength and EndurancePropellers must beshown to have satisfactory endurance as well as stresses that don

22、ot exceed values shown to be safe for continuous operation inaccordance with the applicable requirements of Section 6, Testsand Inspections.6. Tests and Inspections6.1 General:6.1.1 Each manufacturer must be able to show that thepropeller concerned can complete the applicable tests andinspections of

23、 this section without evidence of failure ormalfunction.6.1.2 The minimum applicable testing and inspection re-quirements are outlined in Table 1 according to propellermaterial type.6.2 Strength Testing:6.2.1 All PropellersThe entire propeller assembly must betested for1hatarotational speed that pro

24、duces a constantcentrifugal load equal to twice that which would occur atmaximum rated rotational speed (as published in the operatingmanual). For the purpose of this requirement, an overspeed testat least 1.41 times the maximum rated rotational speed or astatic pull test are acceptable means of com

25、pliance. If a staticpull test is used, the required load for each blade must becarried by at least the inner one-half of its span.6.2.2 On propellers with detachable blades, the blade rootand blade retention system must be statically tested for1hata load level equal to four times the centrifugal loa

26、d that wouldbe generated by the blade weight at maximum rated rotationalspeed.6.3 Stress Measurement, Fatigue Strength, and FatigueAnalysis:6.3.1 The magnitude of the propeller vibration stresses,including any stress peaks and resonant conditions, throughoutthe operational envelope of the propeller

27、shall be determinedby direct measurement of stresses on a representative engine.6.3.2 A full-scale fatigue test shall be performed to deter-mine a fatigue allowable of the blade retention system.6.3.3 Through testing or analysis, the fatigue allowable forthe mid-blade and tip regions of the propelle

28、r blade shall bedetermined. This testing shall also account for normal in-service damage and wear.6.3.4 Using the measured stresses and root, mid-blade, andtip fatigue allowables, a fatigue assessment shall be conductedto show that failure of the propeller will not occur between thedeclared propelle

29、r inspection intervals when using the declaredinspection techniques.6.4 Endurance Testing:6.4.1 The propeller shall undergo an endurance test on theintended engine, or a vibrationally representative engine that iscapable of providing the maximum rated power at the maxi-mum rated propeller rotational

30、 speed and diameter. The pro-peller pitch may be adjusted as necessary to achieve maximumrated takeoff power at maximum rated takeoff RPM. Propellerpitch need not be readjusted for the remainder of the test unlessnecessary to avoid declared operational speed placards. Thetest shall be conducted acco

31、rding to the schedule, and in theorder, shown in Fig. 1.6.4.2 During the test, it is acceptable to stop the test asneeded, but the test should be restarted and continued from thepoint in the test schedule where it was stopped.6.5 Teardown Inspection:6.5.1 After completion of each test prescribed in

32、Section 5of this specification, the propeller must be completely disas-sembled and a detailed inspection must be made of thepropeller parts for cracks, wear, distortion, and any otherunusual conditions.6.5.2 Any unsatisfactory findings during the teardown in-spection must be resolved through design

33、changes and addi-tional testing as necessary to establish the compliance of thepropeller to this specification.TABLE 1 Applicable Section 6 Paragraphs for Testing andInspection RequirementsPropeller BladeMaterial TypeStrength/FatigueTestingEndurance Testing Inspection/MaintenanceWood 6.2Composite 6.

34、2 or 6.3 6.4 6.5 and 6.6Metal 6.2 or 6.3F25060726.6 Propeller Adjustments and Parts ReplacementsThemanufacturer may service and make repairs to the propellerduring the tests. Any service or repairs completed must beallowed by the maintenance manual. If repairs or replacementof parts that are beyond

35、the scope of the maintenance manualare found necessary during the tests or in the teardowninspection, the parts in question must be subjected to additionaltesting or design changes, or both, as necessary to establish thecompliance of the propeller to this specification.7. Identification Marking7.1 E

36、ach manufacturer of a propeller, propeller blade, orpropeller hub shall identify each by means of a plate, stamping,engraving, etching, or other method of permanent identifica-tion.7.2 The identification shall be placed on a non-criticalsurface that will not likely be defaced or removed duringnormal

37、 service or lost or destroyed in an accident.7.3 The identification marking(s) shall contain the followinginformation. Propeller diameter, pitch (for fixed-pitch propel-lers), and manufacturers identification must be obvious fromthe marking(s). The other required information can be encodedor abbrevi

38、ated as necessary to limit the space required for themarking(s):7.3.1 Manufacturers identification.7.3.2 Propeller model designation.7.3.3 Propeller serial number.7.3.4 Part number (or equivalent).7.3.5 Propeller diameter.7.3.6 Propeller pitch (for fixed-pitch propellers).8. Design Control8.1 The de

39、sign of a propeller consists of at least thefollowing:8.1.1 The drawings and specifications, and a listing of thosedrawings and specifications necessary to define the configura-tion and the design features of the propeller shown to complywith this specification.8.1.2 Information on dimensions, mater

40、ials, and processesnecessary to define the structural strength of the propeller.8.1.3 Any other data necessary to allow, by comparison, thedetermination that later propellers of the same or similar designmeet the requirements of this specification.9. Quality Assurance9.1 The propeller manufacturer s

41、hall have a quality assur-ance system that ensures manufactured propellers maintainconformity to the established design.10. Keywords10.1 light sport aircraft; propellerFIG. 1 Propeller Endurance Test ScheduleF2506073ASTM International takes no position respecting the validity of any patent rights as

42、serted 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 standard is subject to revision at any time

43、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 International Headquarters. Your comments will rec

44、eive 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 below.This standard is copyrighted by ASTM Int

45、ernational, 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).F2506074