ASTM_F_3066_-_F_3066M_-_15.pdf

Designation:F3066/F3066M15Standard Specification forPowerplant Systems Specific Hazard Mitigation1This standard is issued under the fixed designation F3066/F3066M;the number immediately following the designation indicates the yearof original adoption 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 covers minimum requirements forhazard mitigation in propulsion systems installed on smallaeroplanes.1.2 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 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.1.3 UnitsThe values stated are SI units followed byimperial units in brackets.The values stated in each systemmay not be exact equivalents;therefore,each system shall beused independently of the other.Combining values from thetwo 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 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 AircraftF3061 Specification for Systems and Equipment in SmallAircraftF3062/F3062M Specification for Installation of PowerplantSystems2.2 Federal Aviation Regulations:314 CFR Part 23 Amendment 623.Terminology3.1 See Terminology F3060 for definitions and abbrevia-tions.4.Engines4.1 For Turbine Engine Installations:4.1.1 Design precautions must be taken to minimize thehazards to the aeroplane in the event of an engine rotor failureor of a fire originating inside the engine which burns throughthe engine case.4.1.2 The powerplant systems associated with engine con-trol devices,systems,and instrumentation must be designed togive reasonable assurance that those operating limitations thatadversely affect turbine rotor structural integrity will not beexceeded in service.4.1.3 For turbine engines installations embedded in thefuselage behind the cabin,the effects of a fan exiting forwardof the inlet case(fan disconnect)must be addressed,thepassengers must be protected,and the aeroplane must becontrollable to allow for continued safe flight and landing.4.2 Engine IsolationThe powerplants must be arrangedand isolated from each other to allow operation,in at least oneconfiguration,so that the failure or malfunction of any engine,or the failure or malfunction(including destruction by fire inthe engine compartment)of any system that can affect anengine(other than a fuel tank if only one fuel tank is installed),will not:4.2.1 Prevent the continued safe operation of the remainingengines;or4.2.2 Require immediate action by any crewmember forcontinued safe operation of the remaining engines.5.Powerplant Ice Protection5.1 Induction System Icing Protection: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 August 2015.DOI:10.1520/F3066_F3066M-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.3Available from U.S.Government Printing Office Superintendent of Documents,732 N.Capitol St.,NW,Mail Stop:SDE,Washington,DC 20401,http:/www.access.gpo.gov.Copyright ASTM International,100 Barr Harbor Drive,PO Box C700,West Conshohocken,PA 19428-2959.United States1 5.1.1 Reciprocating engines.Each reciprocating engine airinduction system must have means to prevent and eliminateicing.Unless this is done by other means,it must be shownthat,in air free of visible moisture at a temperature of 1C30F.5.1.2 Each aeroplane with sea level engines using conven-tional venturi carburetors has a preheater that can provide aheat rise of 50C 90F.with the engines at 75%of maximumcontinuous power.5.1.3 Each aeroplane with altitude engines using conven-tional venturi carburetors has a preheater that can provide aheat rise of 67C 120F.with the engines at 75%ofmaximum continuous power.5.1.4 Each aeroplane with altitude engines using fuel me-tering device(carburetor)tending to prevent icing has apreheater that,with the engines at 60%of maximum continu-ous power,can provide a heat rise of:5.1.4.1 56C 100F,or5.1.4.2 22C 40F,if a fluid deicing system meeting thecarburetor deici