1、Designation: F3062/F3062M 16Standard Specification forInstallation of Powerplant Systems1This standard is issued under the fixed designation F3062/F3062M; the number immediately following the designation indicates the yearof original adoption or, in the case of revision, the year of last revision. A
2、 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 theinstallation and integration of powerplant system units.1.2 This specification i
3、s applicable to small aeroplanes asdefined in the F44 terminology standard. Use of the termairplane is used throughout this specification and will mean“small airplane.”1.3 The applicant for a design approval must seek theindividual guidance to their respective CAA body concerningthe use of this stan
4、dard 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 the ASTM F44 webpage(www.ASTM.org/COMITTEE/
5、F44.htm) which includes CAAwebsite links.1.4 References within this standard normally refer to docu-ments in United States legal system. Appendix X1 crossreferences documents in the legal system of other countries ofcorresponding content.1.5 UnitsThe values stated are SI units followed byimperial un
6、its 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.1.6 This standard does not purport to address all of thesafety concerns,
7、 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:2F2339 Practice for Design and Manufacture of
8、 Reciprocat-ing Spark Ignition Engines for Light Sport AircraftF2506 Specification for Design and Testing of Light SportAircraft PropellersF2538 Practice for Design and Manufacture of Reciprocat-ing Compression Ignition Engines for Light Sport AircraftF2840 Practice for Design and Manufacture of Ele
9、ctricPropulsion Units for Light Sport AircraftF3060 Terminology for AircraftF3066/F3066M Specification for Powerplant Systems Spe-cific Hazard Mitigation2.2 Code of Federal Regulations (CFR):314 CFR part 33 Airworthiness Standards: Aircraft Engines14 CFR part 35 Airworthiness Standards: Propellers14
10、 CFR part 34 Fuel Venting and Exhaust Emission Require-ments for Turbine Powered Airplanes2.3 Federal Aviation Administration (FAA) Publications:4AC 23-8C Flight Test Guide for certification of part 23airplanesCAR 13 Aircraft Engines AirworthinessTSO C77 Technical Standard Order Gas Turbine Auxil-li
11、ary Power Units2.4 JAA Documents:5JAR-E EnginesJAR-P PropellersJAR-22 Gliders and Powered Gliders2.5 EASA Documents:6CS-22 Certification Specifications for Gliders and PoweredGlidersCS-E Certification Specifications for Engines1This specification is under the jurisdiction ofASTM Committee F44 on Gen
12、eralAviation Aircraft and is the direct responsibility of Subcommittee F44.40 onPowerplant.Current edition approved Sept. 1, 2016. Published September 2016. Originallyapproved in 2015. Last previous edition approved in 2015 as F3062/F3062M 15.DOI: 10.1520/F3062_F3062M-16.2For referenced ASTM standar
13、ds, 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. Capito
14、l St., NW, Mail Stop: SDE, Washington, DC 20401, www.access-.gpo.gov.4Available from Federal Aviation Administration (FAA), 800 IndependenceAve., SW, Washington, DC 20591, www.faa.gov.5Available from Global Engineering Documents, 15 Inverness Way, EastEnglewood, CO 80112-5704, .6Available from EASA
15、European Aviation Safety Agency, Postfach 10 12 53.D-50452 Koeln, Germany, easa.europa.eu.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States1CS-P Certification Specifications for PropellersCS-APU Certification Specifications for Auxiliar
16、y PowerUnits3. Terminology3.1 The following are a selection of relevant terms. SeeTerminology F3060 for more definitions and abbreviations.3.2 Definitions:3.2.1 powerplant, nall units and components necessaryfor propelling the aircraft or for providing auxiliary power forthe aircraft (APU).3.2.2 pow
17、erplant installation, nthe installation of an en-gine or auxiliary power unit including all components that arenecessary for propulsion or for providing auxiliary power(APU) and affects the safety of the major propulsive units.3.2.3 reciprocating engine, nengines with the characteris-tics of a non-c
18、ontinuous flow piston engines.3.2.3.1 DiscussionFor the purpose of this standard theterm reciprocating engine does include rotary piston enginedue to the similar characteristics.3.2.4 supercharger, nan air compressor that increases thepressure of air supplied to an engine.3.2.4.1 DiscussionFor the p
19、urpose of this standard theterm supercharger refers to both mechanical and turbine drivensuperchargers.3.2.5 turbocharger, na supercharger driven by a turbine inthe exhaust gas stream, short form of turbo supercharger.3.2.6 turbine engines, nturbopropeller, turbojet and turbo-fan engines.3.3 Abbrevi
20、ations:3.3.1 APUAuxilliary Power Unit4. General4.1 Engines and APU:4.1.1 Each engine must either:4.1.1.1 Meet the technical requirements of 14 CFR Part 33,or4.1.1.2 If accepted by the authority, meet the technicalrequirements of CS-22 Subpart H.4.1.2 Each APU must meet the technical requirements ofT
21、SO C77.4.1.3 Each turbine engine must meet the applicable require-ments of 14 CFR Part 34.4.2 Powerplant Installation:4.2.1 The powerplant installation must comply with theinstallation instructions of:(1) the engine,(2) the propeller, if applicable,(3) the APU, if applicable.4.2.2 Each powerplant in
22、stallation must be constructed andarranged to ensure safe operation to the maximum altitude forwhich approval is requested.4.2.3 Each turbine engine installation must be constructedand arranged to result in carcass vibration characteristics thatdo not exceed those established by the engine manufactu
23、rer.4.2.4 Each powerplant installation must be constructed andarranged to be accessible for necessary inspections and main-tenance.4.2.4.1 Engine cowls and nacelles must be easily removableor openable by the pilot to provide adequate access to andexposure of the engine compartment for preflight chec
24、ks.5. Air Induction System5.1 General:5.1.1 The air induction system for each engine and auxiliarypower unit and their accessories must supply the air requiredby that engine and auxiliary power unit and their accessoriesunder the operating conditions for which certification is re-quested.5.2 Inducti
25、on Systems of Reciprocating Engine PoweredAeroplanes:5.2.1 Each engine installation must have at least two sepa-rate air intake sources.5.2.2 Primary air intakes may open within the cowling ifthat part of the cowling is isolated from the engine accessorysection by a fire-resistant diaphragm or if th
26、ere are means toprevent the emergence of backfire flames.5.2.3 Each alternate air intake must be located in a shelteredposition and may not open within the cowling if the emergenceof backfire flames will result in a hazard.5.2.4 The supplying of air to the engine through the alter-nate air intake sy
27、stem may not result in a loss of excessivepower in addition to the power loss due to the rise in airtemperature.5.2.5 Each automatic alternate air door must have an over-ride means accessible to the flight crew.5.2.6 Each automatic alternate air door must have a meansto indicate to the flight crew w
28、hen it is not closed.5.3 Induction Systems of Turbine Engine Powered Aero-planes:5.3.1 There must be means to prevent quantities of fuelleakage or overflow from drains, vents, or other components offlammable fluid systems from entering the engine intakesystem that would cause the engine to exceed it
29、s operationallimitations, cause a significant loss of power, or otherwisecause the engine to operate in an unsafe condition.5.3.2 The airplane must be designed to prevent water orslush on the runway, taxiway, or other airport operatingsurfaces from being directed into the engine or auxiliary powerun
30、it air intake ducts in quantities that would cause the engineto exceed its operational limitations, cause a significant loss ofpower, or otherwise cause the engine to operate in an unsafecondition.5.3.3 The air intake ducts must be located or protected so asto minimize the hazard of ingestion of for
31、eign matter duringtakeoff, landing, and taxiing.5.3.4 Each turbine engine installation must be constructedand arranged to ensure that the capability of the installedengine to withstand the ingestion of rain, hail, ice, and birdsinto the engine inlet is not less than the capability establishedfor the
32、 engine itself under Specification F3066/F3066M.5.4 Induction System Ducts:F3062/F3062M 1625.4.1 Each induction system duct must have a drain toprevent the accumulation of fuel or moisture in the normalground and flight attitudes. No drain may discharge where itwill cause a fire hazard.5.4.2 Each du
33、ct connected to components between whichrelative motion could exist must have means for flexibility.5.4.3 Each flexible induction system duct must be capableof withstanding the effects of temperature extremes, fuel, oil,water, and solvents to which it is expected to be exposed inservice and maintena
34、nce without hazardous deterioration ordelamination.5.4.4 For reciprocating engine installations, each inductionsystem duct must be:5.4.4.1 Strong enough to prevent induction system failuresresulting from normal backfire conditions; and5.4.4.2 Fire resistant in any compartment for which a fireextingu
35、ishing system is required.5.4.5 Each inlet system duct for an auxiliary power unitmust be:5.4.5.1 Fireproof within the auxiliary power unit compart-ment;5.4.5.2 Fireproof for a sufficient distance upstream of theauxiliary power unit compartment to prevent hot gas reverseflow from burning through the
36、 duct and entering any othercompartment of the airplane in which a hazard would becreated by the entry of the hot gases;5.4.5.3 Constructed of materials suitable to the environmen-tal conditions expected in service, except in those areasrequiring fireproof or fire resistant materials; and5.4.5.4 Con
37、structed of materials that will not absorb or traphazardous quantities of flammable fluids that could be ignitedby a surge or reverse-flow condition.5.4.6 Induction system ducts that supply air to a cabinpressurization system must be suitably constructed of materialthat will not produce hazardous qu
38、antities of toxic gases orisolated to prevent hazardous quantities of toxic gases fromentering the cabin during a powerplant fire.5.5 Induction System Screens:5.5.1 Each screen must be upstream of the carburetor or fuelinjection system.5.5.2 No screen may be in any part of the induction systemthat i
39、s the only passage through which air can reach the engine,unless the available heat rise is at least 56C 100F; and thescreen can be deiced by heated air.5.5.3 No screen may be deiced by alcohol alone.5.5.4 It must be impossible for fuel to strike any screen.5.6 Induction System Filters:5.6.1 If an a
40、ir filter is used to protect the engine againstforeign material particles in the induction air supply:5.6.1.1 Each air filter must be capable of withstanding theeffects of temperature extremes, rain, fuel, oil, and solvents towhich it is expected to be exposed in service and maintenance;and5.6.1.2 E
41、ach air filter shall have a design feature to preventmaterial separated from the filter media from interfering withproper fuel metering operation.6. Powerplant Exhuast System6.1 General:6.1.1 Each exhaust system must ensure safe disposal ofexhaust gases without fire hazard or carbon monoxide contami
42、-nation in any personnel compartment.6.1.2 Each exhaust system part with a surface hot enough toignite flammable fluids or vapors must be located or shieldedso that leakage from any system carrying flammable fluids orvapors will not result in a fire caused by impingement of thefluids or vapors on an
43、y part of the exhaust system includingshields for the exhaust system.6.1.3 Each exhaust system must be separated by fireproofshields from adjacent flammable parts of the airplane that areoutside of the engine and auxiliary power unit compartments.6.1.4 No exhaust gases may discharge dangerously near
44、 anyfuel or oil system drain.6.1.5 For aeroplanes certified for night operation no exhaustgases may be discharged where they will cause a glareseriously affecting pilot vision at night.6.1.6 Each exhaust system component must be ventilated toprevent points of excessively high temperature.6.1.7 If si
45、gnificant traps exist, each turbine engine andauxiliary power unit exhaust system must have drains discharg-ing clear of the airplane, in any normal ground and flightattitude, to prevent fuel accumulation after the failure of anattempted engine or auxiliary power unit start.6.1.8 Each exhaust heat e
46、xchanger must incorporate meansto prevent blockage of the exhaust port after any internal heatexchanger failure.6.2 Exhaust System Construction:6.2.1 Each exhaust system must be fireproof and corrosion-resistant, and must have means to prevent failure due toexpansion by operating temperatures.6.2.2
47、The suitability and durability of materials used for anyexhaust part must:6.2.2.1 Be established by experience or tests;6.2.2.2 Meet approved specifications that ensure their hav-ing the strength and other properties assumed in the designdata; and6.2.2.3 Take into account the effects of environmenta
48、lconditions, such as temperature and humidity, expected inservice.6.2.3 Each exhaust system must be supported to withstandthe vibration and inertia loads to which it may be subjected inoperation.6.2.4 Parts of the system connected to components betweenwhich relative motion could exist must have mean
49、s forflexibility.6.3 Exhaust Heat Exchangers:6.3.1 Each exhaust heat exchanger must be constructed andinstalled to withstand the vibration, inertia, and other loads thatit may be subjected to in normal operation.6.3.2 Each exchanger must be suitable for continued opera-tion at high temperatures and resistant to corrosion fromexhaust gases.6.3.3 There must be means for inspection of critical parts ofeach exchanger.F3062/F3062M 1636.3.4 Each exchanger must have cooling provisions wher-ever it is subject to contact with exhaust gases.6.3.5 Each heat exch
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