1、Designation: F3063/F3063M 15F3063/F3063M 16Standard 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 o
2、riginal 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 the desig
3、n and integration of Fuel/Energy Storage and Delivery systeminstallations for aeroplanes.1.2 This specification is applicable to aeroplanes as defined in the F44 terminology standard.1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the
4、 use ofthis standard as part of a certification plan. For information on which CAAregulatory bodies have accepted this standard (in wholeor in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), referto ASTM F44 webpage (www.ASTM.org/
5、COMITTEE/F44.htm) which includes CAA website links.1.4 UnitsThe values stated are SI units followed by imperial units in brackets. The values stated in each system may not beexact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems mayr
6、esult in non-conformance with the standard.1.5 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibilityof the user of this standard to establish appropriate safety and health practices and determine the applicability of regulator
7、ylimitations 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 Conditions2.2 Other Standard:US 14 CFR Part 23 Airworthiness Stan
8、dards: Normal, Utility, Aerobatic and Commuter Category Airplanes (Amendment 62)33. Terminology3.1 The following are a selection of relevant terms. See Terminology F3060 for more definitions and abbreviations.3.2 Definitions:3.2.1 main pump, na pump that supplies sufficient fuel to sustain the engin
9、e during normal operations.3.2.2 emergency pump, na pump that can sustain engine operation at full power in the event the main pump fails.3.2.3 auxiliary pump, na pump that can provide some fuel flow during emergency operations but not enough to sustain engineoperation at full power. Its function is
10、 to aid in priming the engine and suppressing fuel vapors.3.3 Abbreviations:3.3.1 cccubic centimetercentimetre3.3.2 CFRCode of Federal Regulations1 This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviationAircraft and is the direct responsibility of Subcommittee F44.40 on
11、Powerplant.Current edition approved June 1, 2015Feb. 1, 2016. Published August 2015March 2016. Originally approved in 2015. Last previous edition approved in 2015 asF3063/F3063M 15. DOI: 10.1520/F3063_F3063M-15.10.1520/F3063_F3063M-16.2 For referencedASTM standards, visit theASTM website, www.astm.o
12、rg, or contactASTM Customer Service at serviceastm.org. For Annual Book of ASTM Standardsvolume information, refer to the standards Document Summary page on the ASTM website.3 Available from U.S. Government Printing Office Superintendent of Documents, 732 N. Capitol St., NW, Mail Stop: SDE, Washingt
13、on, DC 20401, http:/www.access.gpo.gov.This document is not an ASTM standard and is intended only to provide the user of an ASTM standard an indication of what changes have been made to the previous version. Becauseit may not be technically possible to adequately depict all changes accurately, ASTM
14、recommends that users consult prior editions as appropriate. In all cases only the current versionof the standard as published by ASTM is to be considered the official document.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States13.3.3 RPM
15、rotation per minute4. Fuel System4.1 General:4.1.1 Each fuel system must be constructed and arranged to ensure fuel flow at a rate and pressure established for proper engineand auxiliary power unit functioning under each likely operating condition, including any maneuver for which certification isre
16、quested and during which the engine or auxiliary power unit is permitted to be in operation.4.1.2 Each fuel system for a turbine engine and compression ignition engine must be capable of sustained operation throughoutits flow and pressure range with fuel initially saturated with water at 27C 80F and
17、 having 0.75 cc of free water per 3.8 L 1US-gal added and cooled to the most critical condition for icing likely to be encountered in operation.4.1.3 Each fuel system for a turbine engine powered aeroplane must meet the applicable fuel venting requirements of 14 CFRpart 34 for the US or the applicab
18、le fuel venting requirements as contained in the rules specified by the applicants local civilaviation 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 one tank at a time; or4.1.4.2 There are means to prevent introducing air into the system.
19、4.1.5 Fuel system components in an engine nacelle or in the fuselage must be protected from damage which could result inspillage of enough fuel to constitute a fire hazard as a result of a wheels-up landing on a paved runway.4.1.6 Each check valve must be constructed, or otherwise incorporate provis
20、ions, to preclude incorrect assembly or connectionof the valve.4.2 Independence:4.2.1 Each fuel system for a multiengine aeroplane must be arranged so that, in at least one system configuration, the failureof any one component will not result in the loss of power of more than one engine or require i
21、mmediate action by the pilot toprevent the loss of power of more than one engine.4.2.2 If a single fuel tank (or series of fuel tanks interconnected to function as a single fuel tank) is used on a multiengineaeroplane, the provision of 4.2.2.1 through 4.2.2.3 must be met.4.2.2.1 For each engine, pro
22、visions of 4.2.2.1(1) and (2) must be met:(1) Independent tank outlets.(2) A shut-off valve at each tank outlet. This shutoff valve may also serve as the fire wall shutoff valve required if the linebetween the valve and the engine compartment does not contain more than 1 L 1 US qt of fuel (or any gr
23、eater amount shownto be safe) that can escape into the engine compartment.4.2.2.2 At least two vents arranged to minimize the probability of both vents becoming obstructed simultaneously must beprovided.4.2.2.3 A fuel system in which those parts of the system from each tank outlet to any engine are
24、independent of each part ofthe system supplying fuel to any other engine must be provided.4.3 Drains:4.3.1 There must be at least one drain to allow safe drainage of the entire fuel system with the aeroplane in its normal groundattitude.4.3.2 Each drain installed for the purposes of draining the ent
25、ire fuel system or for the purposes of draining hazardous quantitiesof water must meet the provision of 4.3.2.1 through 4.3.2.2.4.3.2.1 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 positive locki
26、ng in the closed position.(2) That is readily accessible.(3) That can be easily opened and closed.(4) That is either located or protected to prevent fuel spillage 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
27、proper closing.5. Fuel Tanks5.1 General:5.1.1 Each fuel tank must be able to withstand, without failure, the vibration, inertia, fluid, and structural loads that it may besubjected to in operation.5.1.2 Each flexible fuel tank liner must be shown to be suitable for the particular application.5.1.3 T
28、he total usable capacity of the fuel tanks must be enough for at least 30 min of operation at maximum continuous power.5.2 Installation:5.2.1 Each fuel tank must be supported so that tank loads are not concentrated.5.2.1.1 There must be pads, if necessary, to prevent chafing between each tank and it
29、s supports.F3063/F3063M 1625.2.1.2 Padding must be nonabsorbent or treated to prevent the absorption of fuel.5.2.1.3 If a flexible tank liner is used, it must be supported so that it is not required to withstand fluid loads.5.2.1.4 Interior surfaces adjacent to the liner must be smooth and free from
30、 projections that could cause wear, unless provisionsare made for protection of the liner at those points; or the construction of the liner itself provides such protection.5.2.1.5 A positive pressure must be maintained within the vapor space of each bladder cell under any condition of operation,exce
31、pt for a particular condition for which it is shown that a zero or negative pressure will not cause the bladder cell to collapse.5.2.1.6 Siphoning of fuel (other than minor spillage) or collapse of bladder fuel cells may not result from improper securing orloss of the fuel filler cap.5.2.2 Fuel tank
32、s must be designed, located, and installed so as to retain fuel when subjected to the inertia loads resulting fromthe ultimate static load factors prescribed in Specification F3083/F3083M; and under conditions likely to occur when the aeroplanelands on a paved runway at a normal landing speed under
33、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 its landing gear is retracted.5.2.2.2 The most critical landing gear leg is collapsed and the other landing gear legs are extended.5.2.2.3 In showing compliance with 5.2.2.1 and 5.2.2.2, the
34、 tearing away of an engine mount must be considered unless all theengines are installed above the wing or on the tail or fuselage of the aeroplane.5.2.3 Each integral fuel tank must have adequate facilities for interior inspection and repair.5.2.4 For Level 4 aeroplanes, fuel tanks within the fusela
35、ge contour must be able to resist rupture and be in a protected positionso that exposure of the tanks to scraping action with the ground is unlikely.5.3 Compartments:5.3.1 Each tank compartment must be ventilated and drained to prevent the accumulation of flammable fluids or vapors.5.3.2 Each compar
36、tment adjacent to a tank that is an integral part of the aeroplane structure must also be ventilated and drained.5.4 Expansion Space:5.4.1 Each fuel tank must have an expansion space of not less than 2 % of the tank capacity, unless the tank vent dischargesclear of the aeroplane (in which case no ex
37、pansion space is required).5.4.2 It must be impossible to fill the expansion space inadvertently with the aeroplane in the normal ground attitude.5.5 Vents and Carburetor Vapor Vents:5.5.1 Each fuel tank must be vented from the top part of the expansion space.5.5.1.1 Each vent outlet must be located
38、 and constructed in a manner that minimizes the possibility of its being obstructed byice or other foreign matter.5.5.1.2 Each vent must be constructed to prevent siphoning of fuel during normal operation.5.5.1.3 The venting capacity must allow the rapid relief of excessive differences of pressure b
39、etween the interior and exteriorof the tank.5.5.1.4 Airspaces of tanks with interconnected outlets must be interconnected.5.5.1.5 There may be no point in any vent line where moisture can accumulate with the aeroplane in either the ground or levelflight attitudes, unless drainage is provided. Any dr
40、ain valve installed must be accessible for drainage.5.5.1.6 No vent may terminate at a point where the discharge of fuel from the vent outlet will constitute a fire hazard or fromwhich fumes may enter personnel compartments.5.5.1.7 Vents must be arranged to prevent the loss of fuel, except fuel disc
41、harged because of thermal expansion, when theaeroplane is parked in any direction on a ramp having a 1 % slope.5.5.2 Each carburetor with vapor elimination connections and each fuel injection engine employing vapor return provisionsmust meet the conditions specified in 5.5.2.1 through 5.5.2.2.5.5.2.
42、1 Each vapor elimination connections and each vapor return provisions must have a separate vent line to lead vapors backto the top of one of the fuel tanks.5.5.2.2 If there is more than one tank and it is necessary to use these tanks in a definite sequence for any reason, the vapor ventline must lea
43、d back to the fuel tank to be used first, unless the relative capacities of the tanks are such that return to another tankis preferable.5.5.3 For aeroplanes approved for aerobatics, the requirements in 5.5.3.1 through 5.5.3.2 must be prevented for each acrobaticmaneuver for which certification is re
44、quested.5.5.3.1 Excessive loss of fuel, including short periods of inverted flight.5.5.3.2 Siphoning of fuel from the vent when normal flight has been resumed.5.6 Sump:5.6.1 Each fuel tank must have a drainable sump with an effective capacity, in the normal ground and flight attitudes, of 0.25% of t
45、he tank capacity, or 0.24 L 116 US-gal, whichever is greater.5.6.2 Each fuel tank must allow drainage of any hazardous quantity of water from any part of the tank to its sump with theaeroplane in the normal ground attitude.5.6.3 Each reciprocating engine fuel system must have a sump that meets the r
46、equirements of 5.6.3.1 through 5.6.3.3.5.6.3.1 Have a sediment bowl or chamber that is accessible for drainage.F3063/F3063M 1635.6.3.2 Have a capacity of 30 cm3 1 oz for every 75.7 L 20 US-gal of fuel tank capacity.5.6.3.3 Each fuel tank outlet must be located so that, in the normal flight attitude,
47、 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 as prescribed in 14 CFR 23.1557(c).5.7.2 Fuel tank filler connections must be located outside the personnel compartment.5.7.3 Spille
48、d fuel must be prevented from entering the fuel tank compartment or any part of the aeroplane other than the tankitself.5.7.4 Each filler cap must provide a fuel-tight seal for the main filler opening. However, there may be small openings in the fueltank cap for venting purposes or for the purpose o
49、f allowing passage of a fuel gauge through the cap provided such openingscomply with the requirements of 5.5.1.5.7.5 Each fuel filling point, except pressure fueling connection points, must have a provision for electrically bonding theaeroplane to ground fueling equipment.5.7.6 Fuel filler openings should be designed to preclude the use 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 aeroplanes with engines requiring gasoline asthe only permissible fuel.5.7.6.2 Fuel filler opening
