1、Designation: F3063/F3063M 18aStandard Specification forAircraft Fuel and Energy Storage and Delivery1This 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
2、 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 ins
3、tallations 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. Forinformat
4、ion on which CAA regulatory bodies have acceptedthis standard (in whole or in part) as a means of compliance totheirAeroplaneAirworthiness regulations (Hereinafter referredto as “the Rules”), refer to ASTM F44 webpage(www.ASTM.org/COMITTEE/F44.htm) which includes CAAwebsite links.1.4 UnitsThe values
5、 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 pu
6、rport 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, health, and environmental practices and deter-mine the applicability of regulatory limitations prior to use.1.6 This international stand
7、ard was developed in accor-dance with internationally recognized principles on standard-ization established in the Decision on Principles for theDevelopment of International Standards, Guides and Recom-mendations issued by the World Trade Organization TechnicalBarriers to Trade (TBT) Committee.2. Re
8、ferenced Documents2.1 ASTM Standards:2F3060 Terminology for AircraftF3083/F3083M Specification for Emergency Conditions,Occupant Safety, and AccommodationsF3116/F3116M Specification for Design Loads and Condi-tionsF3117 Specification for Crew Interface in AircraftF3179/F3179M Specification for Perfo
9、rmance of Aircraft2.2 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
10、 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 n
11、ot 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 centimetre3.3.2 CFRCode of Federal Regulations3.3.3 RPMrotation per minute4. Fuel System4.1 General:1This specification is under the jurisdictio
12、n ofASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.40 onPowerplant.Current edition approved July 1, 2018. Published August 2018. Originallyapproved in 2015. Last previous edition approved in 2018 as F3063/F3063M 18.DOI: 10.1520/F3063_F3063M-18A.2F
13、or 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
14、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 StatesThis international standard was developed in accordance with internationally recognized
15、 principles on standardization established in the Decision on Principles for theDevelopment of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.14.1.1 Each fuel system must be constructed and arranged toensure fuel
16、 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
17、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
18、encountered in operation.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.
19、4 Each fuel system must be arranged so that it meets therequirement of 4.1.4.1 or 4.1.4.2.4.1.4.1 No fuel pump can draw fuel from more than onetank at a time.4.1.4.2 There are means to prevent introducing air into thesystem.4.1.5 Fuel system components in an engine nacelle or in thefuselage must be
20、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 otherwiseincorporate provisions, to preclude incorrect assembly orconnection of the valve.4.2 Independence
21、:4.2.1 Each fuel system for a multiengine aeroplane must bearranged so that, in at least one system configuration, thefailure of any one component will not result in the loss ofpower of more than one engine or require immediate action bythe pilot to prevent the loss of power of more than one engine.
22、4.2.2 If a single fuel tank (or series of fuel tanks intercon-nected to function as a single fuel tank) is used on amultiengine aeroplane, the provision of 4.2.2.1 through 4.2.2.4and 5.7.7 must be met.4.2.2.1 There shall be an independent tank outlet for eachengine.4.2.2.2 There shall be a shut-off
23、valve at each tank outlet.This shutoff valve may also serve as the fire wall shutoff valverequired if the line between the valve and the engine compart-ment does not contain more than 1 L 1 US qt of fuel (or anygreater amount shown to be safe) that can escape into theengine compartment.4.2.2.3 At le
24、ast two vents arranged to minimize the prob-ability of both vents becoming obstructed simultaneously mustbe provided.4.2.2.4 A fuel system in which those parts of the systemfrom each tank outlet to any engine are independent of eachpart of the system supplying fuel to any other engine must beprovide
25、d.4.3 Drains:4.3.1 There must be at least one drain to allow safe drainageof the entire fuel system with the aeroplane in its normalground attitude.4.3.2 Each drain installed for the purpose of draininghazardous quantities of water, as required by 5.6, must meet theprovision of 4.3.2.1 through 4.3.2
26、.2.4.3.2.1 Discharge clear of all parts of the aeroplane.4.3.2.2 Have a drain valve that meets 4.3.2.2(1) through (6).(1) That has manual or automatic means for positivelocking in the closed position.(2) That is readily accessible.(3) That can be easily opened and closed.(4) That is either located o
27、r protected to prevent fuelspillage in the event of a landing with landing gear retracted.(5) That allows the fuel to be caught for examination.(6) That can be observed for proper closing.5. Fuel Tanks5.1 General:5.1.1 Each fuel tank must be able to withstand, withoutfailure, the vibration, inertia,
28、 fluid, and structural loads that itmay be subjected to in operation.5.1.2 Each flexible fuel tank liner must be shown to besuitable for the particular application.5.1.3 The total usable capacity of the fuel tanks must beenough for at least 30 min of operation at maximum continuouspower.5.2 Installa
29、tion:5.2.1 Each fuel tank must be supported so that tank loads arenot concentrated.5.2.1.1 There must be pads, if necessary, to prevent chafingbetween each tank and its supports.5.2.1.2 Padding must be nonabsorbent or treated to preventthe absorption of fuel.5.2.1.3 If a flexible tank liner is used,
30、 it must be supportedso that it is not required to withstand fluid loads.5.2.1.4 Interior surfaces adjacent to the liner must besmooth and free from projections that could cause wear, unlessprovisions are made for protection of the liner at those points;or the construction of the liner itself provid
31、es such protection.5.2.1.5 A positive pressure must be maintained within thevapor space of each bladder cell under any condition ofoperation, except for a particular condition for which it isshown that a zero or negative pressure will not cause thebladder cell to collapse.5.2.1.6 Siphoning of fuel (
32、other than minor spillage) orcollapse of bladder fuel cells may not result from impropersecuring or loss of the fuel filler cap.5.2.2 Fuel tanks must be designed, located, and installed soas to retain fuel when subjected to the inertia loads resultingfrom the ultimate static load factors prescribed
33、in SpecificationF3083/F3083M; and under conditions likely to occur when theaeroplane lands on a paved runway at a normal landing speedunder the conditions specified in 5.2.2.1 through 5.2.2.3.5.2.2.1 The aeroplane is in a normal landing attitude and itslanding gear is retracted.5.2.2.2 The most crit
34、ical landing gear leg is collapsed andthe other landing gear legs are extended.F3063/F3063M 18a25.2.2.3 In showing compliance with 5.2.2.1 and 5.2.2.2, thetearing away of an engine mount must be considered unless allthe engines are installed above the wing or on the tail orfuselage of the aeroplane.
35、5.2.3 Each integral fuel tank must have adequate facilitiesfor interior inspection and repair.5.2.4 For Level 4 aeroplanes, fuel tanks within the fuselagecontour must be able to resist rupture and be in a protectedposition so that exposure of the tanks to scraping action withthe ground is unlikely.5
36、.3 Compartments:5.3.1 Each tank compartment must be ventilated anddrained to prevent the accumulation of flammable fluids orvapors.5.3.2 Each compartment adjacent to a tank that is an integralpart of the aeroplane structure must also be ventilated anddrained.5.4 Expansion Space:5.4.1 Each fuel tank
37、must have an expansion space of notless than2%ofthetank capacity, unless the tank ventdischarges clear of the aeroplane (in which case no expansionspace is required).5.4.2 It must be impossible to fill the expansion spaceinadvertently with the aeroplane in the normal ground attitude.5.5 Vents and Ca
38、rburetor Vapor Vents:5.5.1 Each fuel tank must be vented from the top part of theexpansion space.5.5.1.1 Each vent outlet must be located and constructed ina manner that minimizes the possibility of its being obstructedby ice or other foreign matter.5.5.1.2 Each vent must be constructed to prevent s
39、iphoningof fuel during normal operation.5.5.1.3 The venting capacity must allow the rapid relief ofexcessive differences of pressure between the interior andexterior of the tank.5.5.1.4 Airspaces of tanks with interconnected outlets mustbe interconnected.5.5.1.5 There may be no point in any vent lin
40、e wheremoisture can accumulate with the aeroplane in either theground or level flight attitudes, unless drainage is provided.Any drain valve installed must be accessible for drainage.5.5.1.6 No vent may terminate at a point where the dis-charge of fuel from the vent outlet will constitute a fire haz
41、ardor from which fumes may enter personnel compartments.5.5.1.7 Vents must be arranged to prevent the loss of fuel,except fuel discharged because of thermal expansion, when theaeroplane is parked in any direction on a ramp havinga1%slope.5.5.2 Each carburetor with vapor elimination connectionsand ea
42、ch fuel injection engine employing vapor return provi-sions must meet the conditions specified in 5.5.2.1 through5.5.2.2.5.5.2.1 Each vapor elimination connections and each vaporreturn provisions must have a separate vent line to lead vaporsback to the top of one of the fuel tanks.5.5.2.2 If there i
43、s more than one tank and it is necessary touse these tanks in a definite sequence for any reason, the vaporvent line must lead back to the fuel tank to be used first, unlessthe relative capacities of the tanks are such that return toanother tank is preferable.5.5.3 For aeroplanes approved for aeroba
44、tics, the require-ments in 5.5.3.1 through 5.5.3.2 must be prevented for eachacrobatic maneuver for which certification is requested.5.5.3.1 Excessive loss of fuel, including short periods ofinverted flight.5.5.3.2 Siphoning of fuel from the vent when normal flighthas been resumed.5.6 Sump:5.6.1 Eac
45、h fuel tank must have a drainable sump with aneffective capacity, in the normal ground and flight attitudes, of0.25 % of the tank capacity, or 0.24 L 116 US-gal, whicheveris greater.5.6.2 Each fuel tank must allow drainage of any hazardousquantity of water from any part of the tank to its sump with
46、theaeroplane in the normal ground attitude.5.6.3 Each reciprocating engine fuel system must have asump that meets the requirements of 5.6.3.1 through 5.6.3.3.5.6.3.1 Have a sediment bowl or chamber that is accessiblefor drainage.5.6.3.2 Have a capacity of 30 cm31 oz for every 75.7 L20 US-gal of fuel
47、 tank capacity.5.6.3.3 Each fuel tank outlet must be located so that, in thenormal flight attitude, water will drain from all parts of the tankexcept the sump to the sediment bowl or chamber.5.7 Filler Connection:5.7.1 Each fuel tank filler connection must be marked asprescribed in Specification F31
48、17.5.7.2 Fuel tank filler connections must be located outsidethe personnel compartment.5.7.3 Spilled fuel must be prevented from entering the fueltank compartment or any part of the aeroplane other than thetank itself.5.7.4 Each filler cap must provide a fuel-tight seal for themain filler opening. H
49、owever, there may be small openings inthe fuel tank cap for venting purposes or for the purpose ofallowing passage of a fuel gauge through the cap provided suchopenings comply with the requirements of 5.5.1.5.7.5 Each fuel filling point, except pressure fueling con-nection points, must have a provision for electrically bondingthe aeroplane to ground fueling equipment.5.7.6 Fuel filler openings should be designed to preclude theuse of fuels other than those approved for use.5.7.6.1 Fuel filler openings no larger than 60 mm 2.36 in.are appropriate for aeropla
