ASTM_F_3063_-_F_3063M_-_15.pdf

Designation:F3063/F3063M15Standard Specification forDesign and Integration of Fuel/Energy Storage and DeliverySystem Installations for Aeroplanes1This standard is issued under the fixed designation F3063/F3063M;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 for thedesign and integration of Fuel/Energy Storage and Deliverysystem installations for aeroplanes.1.2 This specification is applicable to aeroplanes as definedin the 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 acceptedthis standard(in whole or in part)as a means of compliance totheirAeroplaneAirworthiness regulations(Hereinafter referredtoas“theRules”),refertoASTMF44webpage(www.ASTM.org/COMITTEE/F44.htm)which includes CAAwebsite links.1.4 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.1.5 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 AircraftF3083/F3083M Specification for Emergency Conditions,Occupant Safety,and AccommodationsF3116/F3116M Specification for Design Loads and Condi-tions2.2 Other Standard:US 14 CFR Part 23 Airworthiness Standards:Normal,Utility,Aerobatic and Commuter Category Airplanes(Amendment 62)33.Terminology3.1 The following are a selection of relevant terms.SeeTerminology F3060 for more definitions and abbreviations.3.2 Definitions:3.2.1 main pump,na pump that supplies sufficient fuel tosustain the engine during normal operations.3.2.2 emergency pump,na pump that can sustain engineoperation at full power in the event the main pump fails.3.2.3 auxiliary pump,na pump that can provide some fuelflow during emergency operations but not enough to sustainengine operation at full power.Its function is to aid in primingthe engine and suppressing fuel vapors.3.3 Abbreviations:3.3.1 cccubic centimeter3.3.2 CFRCode of Federal Regulations3.3.3 RPMrotation per minute4.Fuel System4.1 General:4.1.1 Each fuel system must be constructed and arranged toensure fuel flow at a rate and pressure established for properengine and auxiliary power unit functioning under each likelyoperating condition,including any maneuver for which certi-fication is requested and during which the engine or auxiliarypower unit is permitted to be in operation.4.1.2 Each fuel system for a turbine engine and compressionignition engine must be capable of sustained operationthroughout its flow and pressure range with fuel initiallysaturated with water at 27C 80F and having 0.75 cc of freewater per 3.8 L1 US-gal added and cooled to the most criticalcondition for icing likely to be encountered in operation.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 June 1,2015.Published August 2015.DOI:10.1520/F3063_F3063M-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 4.1.3 Each fuel system for a turbine engine powered aero-plane must meet the applicable fuel venting requirements of 14CFR part 34 for the US or the applicable fuel ventingrequirements as contained in the rules specified by the appli-cants local civil aviation authority.4.1.4 Each fuel system must be arranged so that:4.1.4.1 No fuel pump can draw fuel from more than onetank at a time;or4.1.4.2 There are means to prevent introducing air into thesystem.4.1.5 Fuel system components in an engine nacelle or in thefuselage must be protected from damage which could result inspillage of enough fuel to constitute a fire hazard as a result ofa wheels-up landing on a paved runway.4.1.6 Each check valve must be constructed,or otherwiseinco