1、Designation: F3120/F3120M 15Standard Specification forIce Protection for General Aviation Aircraft1This standard is issued under the fixed designation F3120/F3120M; the number immediately following the designation indicates the yearof original adoption or, in the case of revision, the year of last r
2、evision. 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 international standards for iceprotection aspects of airworthiness and design for “generalaviation
3、” aircraft.1.2 The applicant for a design approval must seek theindividual guidance of 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
4、 totheir Small Aircraft Airworthiness regulations (hereinafterreferred to as “the Rules”), refer to ASTM F44 webpage(www.ASTM.org/COMMITTEE/F44.htm) which includesCAA website links.1.3 UnitsThe values are stated in units common to thefield of aircraft icing. Typically SI or inch-pound units areused,
5、 but in some cases this has resulted in the use of mixedunits due to the historical development of these values. In caseswhere values are given in one system with the other systemfollowing in brackets, the values stated in each system may notbe exact equivalents; therefore, each system shall be used
6、independently of the other. Combining values from the twosystems 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 this standard to establish appro-priate sa
7、fety 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 SmallAircraftF3066/F3066M Specification for Powerplant Systems Spe-cific Hazard
8、MitigationF3093/F3093M Specification for Aeroelasticity Require-ments2.2 Federal Standards:314 CFR Part 33 (Amdt 34) Airworthiness Standards:AircraftEngines14 CFR Part 23 (Amdt 62) Airworthiness Standards:Normal, Utility, Aerobatic, and Commuter Category Air-craft2.3 Other Standard:SAE AS5562 Ice an
9、d Rain Minimum Qualification Stan-dards for Pitot and Pitot-static Probes43. Terminology3.1 Refer to Terminology F3060 for definitions of terms inthis standard.3.2 Acronyms:3.2.1 ICTSice contaminated tailplane stall3.2.2 IPSice protection system3.2.3 SLDsupercooled large droplets3.2.4 TTO Probetotal
10、 temperature probe4. Applicability4.1 Operational RequirementsThe aircraft level of ap-proval determines which portions of this specification areapplicable for a specific project. The requirements are definedin Table 1.5. Crew External Visibility5.1 Windshields and WindowsFor aircraft approved forfl
11、ight in icing conditions, a means must be provided to preventor to clear accumulations of ice from the windshield on an areasufficiently large to provide the view specified in 23.775(f).This means must be designed to function in the icing condi-tions specified in Section 11 for which approval is sou
12、ght.1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.10 onGeneral.Current edition approved Dec. 1, 2015. Published January 2016. DOI: 10.1520/F3120_F3120M-15.2For referenced ASTM standards, visit the A
13、STM 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 ofDocuments, 732 N. Capitol St., NW, Was
14、hington, DC 20401-0001, http:/www.access.gpo.gov.4Available from SAE International (SAE), 400 Commonwealth Dr., Warrendale,PA 15096, http:/aerospace.sae.org.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States16. Ice Shedding6.1 Engine Inl
15、et Ice IngestionThe ingestion of ice into theengine inlet must be considered by taking into account iceaccumulation levels on the engine, inlet system, or airframecomponents for each turbine engine installation defined inaccordance with Specification F3066/F3066M as follows:6.1.1 For VFR only or VFR
16、 and IFR only aircraft, iceaccumulations representative of an inadvertent encounter andsubsequent exit from icing conditions specified in Sections11.1 and 11.2 must be considered, assuming a minimum of afive minute exposure at the critical, continuous maximum icingconditions of Section 11.1.6.1.2 Fo
17、r aircraft approved for flight in icing conditions, iceaccumulations must be representative of the icing conditions inSection 11 for which approval is sought. The ice accumulationsmust be consistent with the icing exposures used for assess-ment of the aircraft performance and flight characteristics
18、inAnnex A1.6.2 Propeller Ice SheddingThe formation and shedding ofhazardous ice accumulation levels must be considered for eachpropeller installation defined in accordance to SpecificationF3066/F3066M as follows:6.2.1 For aircraft with pusher propellers VFR only or VFRand IFR only aircraft, airframe
19、 ice accumulations of aninadvertent encounter and subsequent exit from icing condi-tions specified in Sections 11.1 and 11.2 must be considered,assuming a minimum of a five minute exposure at the critical,continuous maximum icing conditions of Section 11.1.6.2.2 For aircraft approved for flight in i
20、cing conditions,airframe ice accumulations must be representative of the icingconditions in Section 11 for which approval is sought. The iceaccumulations must be consistent with the icing exposuresused for assessment of the aircraft performance and flightcharacteristics in Annex A1.6.3 Airframe Ice
21、SheddingIce accumulation levels anddamage criteria that must be considered with respect toairframe ice shedding are as follows:6.3.1 For aircraft approved for flight in icing conditions,airframe ice accumulations must be representative of the icingconditions in Section 11 for which approval is sough
22、t. The iceaccumulations must be consistent with the icing exposuresused for assessment of the aircraft performance and flightcharacteristics in Annex A1.6.3.2 Any damage resulting from ice shedding:6.3.2.1 Must not significantly affect the airframes structuralintegrity.6.3.2.2 Must not degrade perfo
23、rmance and flight character-istics below levels required in 14 CFR Part 23 Amend 62referenced in Section 2.6.3.2.3 Be shown acceptable for continued in-service use.6.4 Ice Protection System Failure ConsiderationsHazardsassociated with the potential shedding of ice from normallyprotected surfaces tha
24、t can result in engine ingestion orsignificant airframe damage (beyond levels required to meet 14CFR Part 23 Amend 62 performance and flight characteristics)shall be mitigated through the safety analysis process asdefined in Specification F3061. Ice accumulations must berepresentative of the icing c
25、onditions in Section 11 for whichapproval is sought using exit scenarios as described in A2.3.Consideration of system failures after an unintentional encoun-ter outside of the approved icing conditions of Section 11 is notrequired.7. Engine Installation and Induction System IceProtection7.1 Propelle
26、rsFor aircraft approved for flight in icingconditions, propellers and other components of completeengine installations defined in accordance with SpecificationF3066/F3066M must meet the requirements of Section 7.1.1through 7.1.2.7.1.1 Ice accumulations must be representative of the icingconditions i
27、n Section 11 for which approval is sought. The iceaccumulations must be consistent with the icing exposuresused for assessment of the aircraft performance and flightcharacteristics in Annex A1.7.1.2 An analysis shall be provided that:7.1.2.1 Substantiates the chordwise and spanwise ice pro-tection c
28、overage.7.1.2.2 Substantiates the ice protection system thermal en-ergy rates or fluid rates.7.1.2.3 Calculates intercycle ice accretions for propellerdeice systems and shows resulting efficiency losses. The use ofFig. A1.1 or Fig. A1.2, as appropriate for the icing conditionbeing addressed, is also
29、 acceptable in place of the analysis.TABLE 1 Types of Aircraft Operational RequirementsOperational Requirements Required SectionsAircraft is approved for VFRoperationsSections 6.1.1, 6.2.1 and 10.Aircraft is approved for IFRoperationsSections 6.1.1, 6.2.1, 8.1, 8.2, 8.3and 10 considering the icingco
30、nditions specified in Sections11.1 and 11.2Aircraft is approved for flight inthe icing conditions of Sections11.1 and 11.2Sections 5, 6, 7, 8, and 9 (NoteAnnex A1 and Annex A2 arerequired by Section 9) consideringthe icing conditions specified inSections 11.1, 11.2 and A2.4.For Section 8, considerat
31、ion ofthe icing conditions of Section11.5 must be shownAircraft is approved for flight inthe icing conditions of Sections11.1 and 11.2 along with portionsof Section 11.4Sections 5, 6, 7, 8, and 9 (NoteAnnex A1 and Annex A2 arerequired by Section 9) consideringthe icing conditions specified inSection
32、s 11.1, 11.2 and theportions of 11.4 applicable to theconditions for which approval issoughtFor Section 8, consideration ofthe icing conditions of Section11.5 must be shownAircraft is approved for flight inthe icing conditions of Sections11.1 and 11.2 along with all ofSection 11.4Sections 5, 6, 7, 8
33、, and 9 (NoteAnnex A1 and Annex A2 arerequired by Section 9) consideringthe icing conditions specified inSections 11.1, 11.2 and 11.4.For Section 8, consideration ofthe icing conditions of Section11.5 must be shownF3120/F3120M 1527.2 Turbine Engines in FlightEach turbine engine and itsair inlet syst
34、em must operate throughout its flight power rangeas described in Specification F3066/F3066M:7.2.1 In the icing conditions specified in Section 11 forwhich approval is sought.7.2.2 In both falling and blowing snow conditions of Table2 within the limitations established for the airplane for suchoperat
35、ion.7.3 Turbine Engines on GroundEach turbine engine andits air inlet system must operate at idle on the ground asdescribed in Specification F3066/F3066M.7.3.1 In the rime and glaze icing conditions defined in Table3.7.3.2 For aircraft approved for operation in the icing con-ditions of Section 11.4,
36、 the large droplet condition as defined inTable 3 also applies.7.3.3 In both falling and blowing snow of Table 2 within thelimitations established for the airplane for such operation.8. Instrumentation Ice Protection8.1 If certification for instrument flight rules (IFR) or flightin icing conditions
37、is requested, each airspeed system musthave a heated pitot probe or an equivalent means of preventingmalfunction due to icing.8.1.1 The following icing conditions must be addressed:8.1.1.1 For IFR certified airplanes, the continuous maxi-mum and intermittent maximum icing conditions defined inSectio
38、ns 11.1 and 11.2.8.1.1.2 For flight into icing certified airplanes the icingconditions defined in Sections 11.1 through 11.4 for whichcertification is sought.8.1.1.3 In addition to the requirements of Sections 8.1.1.1and 8.1.1.2, for airplanes with VNEor VMO 250 KCAS (andMMO 0.6) and a maximum certi
39、fied altitude above 25 000 ft,the mixed phase and ice crystal conditions defined in Section11.5.8.1.2 Pitot probes which comply with SAE AS5562 meetthe requirements of Section 8.1.1.8.1.3 The following installation factors must be considered:8.1.3.1 It shall be shown that qualification tests of the
40、pitotprobe utilize a concentration factor that is equal to or exceedsthe concentration factor of the probe installed on the airplane.8.1.3.2 For flight into icing certified airplanes, in the icingconditions for which certification is sought, it must be shownthat any ice accretions on the airframe, f
41、orward of pitot probes,does not significantly affect airspeed indications.8.2 If a flight instrument pitot probe heating system isinstalled to meet the requirements specified in Section 8.1,analerting system must be provided to alert the flight crew whenthat pitot probe heating system is not operati
42、ng.8.2.1 The alert provided must conform to a “Caution” alertthat is in clear view of a flightcrew member.8.2.2 The alert required by 8.2 must be triggered in either ofthe following conditions:8.2.2.1 The pitot heating system is switched “off”; except asprovided in Sections 8.2.3 or 8.2.4.8.2.2.2 Th
43、e pitot heating system is switched “on” and anypitot probe heating element is inoperative.8.2.3 The alert may be inhibited automatically by systemdesign for the following conditions:8.2.3.1 Ground operations.8.2.3.2 In-flight at ambient temperature of +5C or greater.8.2.4 A placard or flight manual
44、procedure that prescribeswhen to operate the pitot heating system may be used in lieu of8.2.1 thru 8.2.3 if the airplane:8.2.4.1 Is not certified for flight in icing conditions,8.2.4.2 Does not have a service ceiling or maximum oper-ating altitude above 18 000 ft, and8.2.4.3 Is not certified as a le
45、vel 4 aircraft.8.3 If a static pressure system is necessary for the function-ing of instruments, systems, or devices on airplanes certifiedfor flight in instrument meteorological or icing conditions, eachstatic pressure port must be designed or located in such amanner that the correlation between ai
46、r pressure in the staticpressure system and true ambient atmospheric static pressure isnot altered when the aircraft encounters icing conditions ofSection 11. Protecting the static pressure port(s) from theeffects of ice accumulation, or utilizing an alternate source ofstatic pressure that is protec
47、ted from such effects may benecessary to comply with this requirement.8.3.1 If the reading of the altimeter, when on the alternatestatic pressure system, differs from the reading of the altimeterwhen on the primary static pressure system by more than 50 ft,a correction card for the alternate static
48、pressure system mustbe made available to the pilot.8.3.2 If an alternate source of static pressure is utilized, anindication orAFM procedure must be provided when switchingto the alternate static pressure source is required in flight.TABLE 2 Falling and Blowing Snow Criteria for Turbine AircraftEngi
49、nesParameter DescriptionSnow Condition A “wet, sticky snow” which accumulates onunheated exterior and interior surfacessubject to impingementConcentration 0.9 g/m3Liquid Water Equivalent orEquivalent to Rainfall of 2.5 mm/hr(Represents heavy snow with a visibility of14mile or less)Wind Velocity Greater than 15 knotsStatic Air Temperature 4C to 0C (25F to 32F)TABLE 3 Ground Icing Conditions for Turbine Aircraft EnginesConditionStatic AirTemperatureWaterConcentration(minimum)MeanEffectiveParticleDiameterDemonstrationRime icecondition0to15F(18 to 9C)Liquid
