ASTM F3066 F3066M-2015 Standard Specification for Powerplant Systems Specific Hazard Mitigation《发动机系统特定危险缓解的标准规范》.pdf

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1、Designation: F3066/F3066M 15Standard 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

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 forhazard mitigation in propulsion systems installed on smallaeroplanes.1.2

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 totheir Small

4、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 equival

5、ents; 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

6、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 Specificatio

7、n 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

8、 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 thata

9、dversely 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 aerop

10、lane 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 destruc

11、tion 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

12、 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 Aug

13、ust 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. G

14、overnment 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 States15.1.1 Reciprocating engines. Each reciprocati

15、ng 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 ca

16、n 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 wi

17、th 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 deicing requirements of Sp

18、ecification F3062/F3062M is installed.5.1.5 Each single-engine aeroplane with a sea-level engineusing a carburetor tending to prevent icing has a shelteredalternate source of air with a preheat of not less than thatprovided by the engine cooling air downstream of the cylin-ders; and5.1.5.1 Each aero

19、plane with a sea level engine(s) using afuel metering device tending to prevent icing has a shelteredalternate source of air with a preheat (higher than ambient) ofnot less than 16C 60F with the engines at 75 % ofmaximum continuous power;5.1.6 Each twin-engined aeroplane with sea-level enginesusing

20、a carburetor tending to prevent icing has a preheater thatcan provide a heat rise (higher than ambient) of 50C 90Fwith the engines at 75 % of maximum continuous power.5.1.7 Each aeroplane with sea level or altitude engine(s)using fuel injection systems not having fuel metering compo-nents projecting

21、 into the airstream on which ice may form, andintroducing fuel into the air induction system downstream ofany components or other obstruction on which ice produced byfuel evaporation may form, has a sheltered alternate source ofair with a preheat of not less than 16C 60F with the enginesat 75 % of m

22、aximum continuous power.5.2 Turbine Engines:5.2.1 Each turbine engine and its air inlet system with allicing protection systems operating must:5.2.1.1 Operate throughout its flight power range, includingminimum descent idle speeds, in the icing and snow conditionsspecified in Appendix C of US 14 CFR

23、 Part 25, without theaccumulation of ice on engine, inlet system components, orairframe components that would do any of the following:(1) Adversely affect installed engine operation or cause asustained loss of power or thrust; or an unacceptable increasein gas path operating temperature; or an airfr

24、ame/engineincompatibility; or(2) Result in unacceptable temporary power or thrust lossor unacceptable engine damage of the engine (includingidling), without the accumulation of ice on engine or inletsystem components that would adversely affect engine opera-tion or cause a serious loss of power or t

25、hrust.5.2.2 (1) Under the icing conditions specified in 14 CFRPart 23 and (2) in snow, both falling and blowing, within thelimitations established for the aeroplane for such operation.5.2.3 Each turbine engine must idle for 30 min on theground, with the air bleed available for engine icing protectio

26、nat its critical condition, without adverse effect, (as specified in14 CFR Part 23) in an atmosphere that is (1) at a temperaturebetween 9 and 1C 15 and 30F and (2) has a liquid watercontent not less than 0.3 g/m3in the form of drops, having amean effective diameter not less than 20 m.5.2.3.1 Follow

27、ed by momentary operation at takeoff poweror thrust.5.2.3.2 During the 30 min of idle operation, the engine maybe run up periodically to a moderate power or thrust setting.5.3 For aeroplanes with reciprocating engines having super-chargers to pressurize the air before it enters the fuel meteringdevi

28、ce (carburetor), the heat rise in the air caused by thatsupercharging at any altitude may be utilized in determiningcompliance with 5.1.1 if the heat rise utilized is that which willbe available, automatically, for the applicable altitudes andoperating condition because of supercharging.5.4 Propelle

29、rs and other components of complete engineinstallations must be protected against the accumulation of ice(as specified in 14 CFR Part 23) as necessary to enablesatisfactory functioning without appreciable loss of thrustwhen operated in the icing conditions for which approval issought.5.5 All areas o

30、f the aeroplane forward of the pusher propel-ler that are likely to accumulate and shed ice into the propellerdisc during any operating condition must be suitably protectedto prevent ice formation (as defined in 14 CFR Part 23), or itmust be shown that any ice shed into the propeller disc will notcr

31、eate a hazardous condition.5.5.1 Propeller ice impact results compliance may be usedfor showing compliance.5.6 Each drain must be protected from hazardous ice accu-mulation under any operating condition.5.7 Engine Rain Hail Ice and Bird Ingestion:5.7.1 Each turbine engine installation must be constr

32、uctedand arranged to:5.7.1.1 Ensure that the capability of the installed engine towithstand the ingestion of rain, hail, ice, and birds into theengine inlet is not less than the capability established for theengine itself under 5.7.2.5.7.2 Each turbine engine and its installation must complywith one

33、 of the following:5.7.2.1 US 14 CFR Sections 33.76, 33.77 and 33.78 in effecton December 13, 2000, or as subsequently amended; or5.7.2.2 US 14 CFR Sections 33.77 and 33.78 in effect onApril 30, 1998, or as subsequently amended before December13; 2000; or5.7.2.3 US 14 CFR Section 33.77 in effect on O

34、ctober 31,1974, or as subsequently amended before April 30, 1998,unless that engines foreign object ingestion service history hasresulted in an unsafe condition; orF3066/F3066M 1525.7.2.4 Be shown to have a foreign object ingestion servicehistory in similar installation locations which has not resul

35、tedin any unsafe condition.6. Designated Fire Zones6.1 Designated Fire ZonesRegions include:6.1.1 For reciprocating engines:6.1.1.1 The power section;6.1.1.2 The accessory section;6.1.1.3 Any complete powerplant compartment in whichthere is no isolation between the power section and theaccessory sec

36、tion.6.1.2 For turbine engines:6.1.2.1 The compressor and accessory sections;6.1.2.2 The combustor, turbine and tailpipe sections thatcontain lines or components carrying flammable fluids orgases;6.1.2.3 Any complete powerplant compartment in whichthere is no isolation between compressor, accessory,

37、combustor, turbine, and tailpipe sections.6.1.3 Other types of aeroplane engines;6.1.4 Any auxiliary power unit compartment; and6.1.5 Any fuel-burning heater, and other combustion equip-ment installation described in 7.1.6.2 No fuel tanks may reside in a fire zone.6.2.1 There must be at least 13 mm

38、12 in. of clearancebetween the fuel tank and the firewall. No part of the enginenacelle skin that lies immediately behind a major air openingfrom the engine compartment may act as the wall of an integraltank.6.3 Each fuel/oil tank may be isolated from personnelcompartments by a fume-proof and fuel-p

39、roof enclosure that isvented and drained to the exterior of the aeroplane. Therequired enclosure must sustain any personnel compartmentpressurization loads without permanent deformation or failureunder the conditions defined in (US14 CFR 23.365 and23.843). A bladder-type fuel cell, if used, must hav

40、e a retainingshell at least equivalent to a metal fuel tank in structuralintegrity.7. Fire Protection7.1 Combustion Heater:7.1.1 Combustion Heater Fire RegionsThe followingcombustion heater fire regions must be protected from fire inaccordance with the applicable provisions of 11.6 and Sections8 and

41、 9:7.1.1.1 The region surrounding the heater, if this regioncontains any flammable fluid system components (excludingthe heater fuel system) that could, be damaged by heatermalfunctioning; or allow flammable fluids or vapors to reachthe heater in case of leakage.7.1.1.2 The region surrounding the he

42、ater, if the heater fuelsystem has fittings that, if they leaked, would allow fuel vaporto enter this region.7.1.1.3 The part of the ventilating air passage that surroundsthe combustion chamber.7.1.2 Ventilating Air DuctsEach ventilating air duct pass-ing through any fire region must be fireproof. I

43、n addition:7.1.2.1 Unless isolation is provided by fireproof valves orby equally effective means, the ventilating air duct downstreamof each heater must be fireproof for a distance great enough toensure that any fire originating in the heater can be containedin the duct; and7.1.2.2 Each part of any

44、ventilating duct passing throughany region having a flammable fluid system must be con-structed or isolated from that system so that the malfunctioningof any component of that system cannot introduce flammablefluids or vapors into the ventilating airstream.7.1.3 Combustion Air DuctsEach combustion a

45、ir ductmust be fireproof for a distance great enough to preventdamage from backfiring or reverse flame propagation. Inaddition:7.1.3.1 No combustion air duct may have a common open-ing with the ventilating airstream unless flames from backfiresor reverse burning cannot enter the ventilating airstrea

46、m underany operating condition, including reverse flow or malfunc-tioning of the heater or its associated components; and7.1.3.2 No combustion air duct may restrict the promptrelief of any backfire that, if so restricted, could cause heaterfailure.7.1.4 Provision must be made to heater controls whic

47、hprevent the hazardous accumulation of water or ice on or in anyheater control component, control system tubing, or safetycontrol.7.1.5 Heater Safety Controls:7.1.5.1 Each combustion heater must have the followingsafety controls including: Means independent of the compo-nents for the normal continuo

48、us control of air temperature,airflow, and fuel flow must be provided to automatically shutoff the ignition and fuel supply to that heater at a point remotefrom that heater when any of the following occurs:(1) The heater exchanger temperature exceeds safe limits.(2) The ventilating air temperature e

49、xceeds safe limits.(3) The combustion airflow becomes inadequate for safeoperation.(4) The ventilating airflow becomes inadequate for safeoperation.7.1.5.2 Means to warn the crew when any heater whose heatoutput is essential for safe operation has been shut off by theautomatic means prescribed in this subsection.7.1.5.3 The means for complying with 7.1.5.1 for anyindividual heater must be independent of components servingany other heater whose heat output is essential for safeoperations; and keep the heater off until restarted by the