1、Designation:F3065/F3065M15Standard Specification forInstallation and Integration of Propeller Systems1This standard is issued under the fixed designation F3065/F3065M;the number immediately following the designation indicates the yearof original adoption or,in the case of revision,the year of last r
2、evision.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 addresses the airworthiness require-ments for the installation and integration of propeller systems.1.2 This
3、specification is applicable to aeroplanes as definedin F44 terminology standard.1.3 The applicant for a design approval must seek theindividual guidance to their respective CAA body concerningthe use of this standard as part of a certification plan.Forinformation on which CAA regulatory bodies have
4、acceptedthis standard(in whole or in part)as a means of compliance totheir Small Aircraft Airworthiness regulations(Hereinafterreferred to as“the Rules”),refer to ASTM F44 webpage(www.ASTM.org/COMITTEE/F44.htm)which includes CAAwebsite links.1.4 UnitsThe values stated are SI units followed byImperia
5、l units in square brackets.The values stated in eachsystem may not be exact equivalents;therefore,each systemshall be used independently of the other.Combining valuesfrom the two systems may result in non-conformance with thestandard.1.5 This standard does not purport to address all of thesafety con
6、cerns,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 limitations prior to use.2.Referenced Documents2.1 ASTM Standards:2F3060 Terminology for Aircraft3.Terminolog
7、y3.1 See Terminology F3060.4.Propeller Installation Aspects4.1 PropellerGeneral:4.1.1 Each propeller must:4.1.1.1 Have a type certificate,or4.1.1.2 Meet the requirements acceptable to the certifyingaviation authority for inclusion in the approved aeroplane.4.1.2 Engine power and propeller shaft rota
8、tional speed maynot exceed the limits for which the propeller is certificated orapproved.4.2 Feathering PropellersEach featherable propeller musthave a means to un-feather in flight.4.3 Variable-Pitch PropellersThe propeller blade pitchcontrol system must meet the following requirements:4.3.1 No sin
9、gle failure or malfunction in the propellersystem will result in unintended travel of the propeller bladesto a position below the in-flight low-pitch position.Failure ofstructural elements need not be considered if the occurrence ofsuch a failure is shown to be extremely remote.4.3.2 For propellers
10、incorporating a method to select bladepitch below the in-flight low pitch position,provisions must bemade to sense and indicate to the flight crew that the propellerblades are below that position by a defined amount.Themethod for sensing and indicating the propeller blade pitchposition must be such
11、that its failure does not affect the controlof the propeller.4.3.3 The propeller control system,operating in normal andalternative operating modes and in transition between operat-ing modes,performs the defined functions throughout thedeclared operating conditions and flight envelope.4.3.4 The prope
12、ller control system functionality is notadversely affected by the declared environmental conditions,including temperature,electromagnetic interference(EMI),high intensity radiated fields(HIRF)and lightning.4.3.5 A method is provided to indicate that an operatingmode change has occurred if flight cre
13、w action is required.4.3.6 No single failure or malfunction of electrical orelectronic components in the control system results in ahazardous propeller effect.4.3.7 Failures or malfunctions directly affecting the propel-ler control system in a typical airplane,such as structuralfailures of attachmen
14、ts to the control,fire,or overheat,do notlead to a hazardous propeller effect.1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.40 onPowerplant.Current edition approved May 1,2015.Published June 2015.DO
15、I:10.1520/F3065-15.2For 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 International,100 Barr Harbor Dr
16、ive,PO Box C700,West Conshohocken,PA 19428-2959.United States1 4.3.8 The loss of normal propeller pitch control does notcause a hazardous propeller effect under the intended operatingconditions.4.3.9 The failure or corruption of data or signals sharedacross propellers does not cause a hazardous propeller effect.4.3.10 Electronic propeller control system imbedded soft-ware must be designed and implemented by a method approvedby the Civil Aviation Authority that is consistent with thecriticality o
