1、Designation: F3310 18Standard Specification forNon-Essential Ice Detectors for Aircraft1This standard is issued under the fixed designation F3310; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of last revision. A number
2、in parentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification covers international standards fornon-essential ice detection system aspects of airworthiness anddesign for aeroplanes.1.2
3、The term “aeroplane” is utilized in this specification asit was originally conceived for normal category fixed wingaircraft with a certified maximum takeoff weight (MTOW) of19 000 lb or less and a passenger seating configuration up to 19as defined in the Rules. However, these standards may be morebr
4、oadly applicable and their usage should not be unnecessarilylimited.1.3 The applicant for a design approval must seek theindividual guidance of their respective CAA body concerningthe use of this specification as part of a certification plan. Forinformation on which CAA regulatory bodies have accept
5、edthis specification (in whole or in part) as a means of compli-ance to their Small Aircraft Airworthiness regulations (herein-after referred to as “the Rules”), refer to ASTM F44 webpage(www.ASTM.org/COMMITTEE/F44.htm) which includesCAA website links. It is the responsibility of the Applicant toval
6、idate any applicability beyond that identified in this speci-fication and request acceptance from the applicable CAA.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-priat
7、e safety, health, and environmental practices and deter-mine the applicability of regulatory limitations prior to use.1.5 This international standard was developed in accor-dance with internationally recognized principles on standard-ization established in the Decision on Principles for theDevelopme
8、nt of International Standards, Guides and Recom-mendations issued by the World Trade Organization TechnicalBarriers to Trade (TBT) Committee.2. Referenced Documents2.1 Following is a list of external standards referencedthroughout this specification; the earliest revision acceptablefor use is indica
9、ted. In all cases later document revisions areacceptable if shown to be equivalent to the listed revision, or ifotherwise formally accepted by the governing civil aviationauthority; earlier revisions are not acceptable.2.2 ASTM Standards:2F3060 Terminology for AircraftF3061/F3061M Specification for
10、Systems and Equipment inSmall AircraftF3120/F3120M Specification for Ice Protection for GeneralAviation Aircraft2.3 Other Standards:SAEAS 5498 Issued 2001-10 Minimum Operational Perfor-mance Specification for Inflight Icing Detection System3EUROCAE ED-103A Minimum Operational PerformanceSpecificatio
11、n for Inflight Icing Detection Systems4RTCA DO-160E Environmental Conditions and Test Proce-dures for Airborne Equipment53. Terminology3.1 Refer to Terminology F3060.3.2 Definitions:3.2.1 FIDSflight icing detection system.3.2.2 LWCliquid water content.3.2.3 non-essential ice detectoran active or pas
12、sive icedetector that does not receive certification credit for itsinstallation.4. Applicability4.1 Aircraft Level/CategoryThe installation of a non-essential ice detector is limited to level 1, 2, 3 and 4Aeroplanesdefined in Specification F3061/F3061M and normal, utility,acrobatic, or commuter cate
13、gory Aeroplanes.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 April 1, 2018. Published April 2018. DOI: 10.1520/F3310-18.2For referenced ASTM standards, visit t
14、he 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 SAE International (SAE), 400 Commonwealth Dr., Warrendale,PA 15096, http:/www.sae.or
15、g.4Available from The European Organisation for Civil Aviation Equipment(EUROCAE), 9-23 rue Paul Lafargue, “Le Triangle” building, 93200 Saint-Denis,France, https:/.5Available from Radio Technical Commission for Aeronautics (RTCA), 115018th NW, Suite 910, Washington, DC 20036, https:/www.rtca.org.Co
16、pyright 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 principles on standardization established in the Decision on Principles for theDevelopment of Interna
17、tional Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.14.2 Existing Ice Detection SystemThe installation of aNon-essential ice detector as a replacement for or modificationto an existing Primary or Advisory ice detection syste
18、m isprohibited.4.3 Aircraft Certification BasisThe aircraft icing certifi-cation basis determines which portions of this specification areapplicable for a specific project. The requirements are definedin Table 1.5. General Requirements5.1 Product IdentificationOne of the major components ofa non-ess
19、ential ice detector system shall also be labeled withthe following information:5.1.1 Serial Number, and5.1.2 Manufacturers Name.5.2 Operating ConditionsThe ice detection system manu-facturer shall specify the following limitations for properfunction:5.2.1 Voltage operating range (min/max), if applic
20、able,5.2.2 Electrical load specifications, if applicable,5.2.3 Restrictions regarding the use and application ofdeicing fluids with the system, if applicable.5.2.4 Aircraft operating range and restrictions regarding:Speed, Temperature, altitude.5.2.5 Environmental icing conditions and restrictions r
21、e-garding: Specification F3120/F3120MAtmospheric Icing Con-ditions section.5.3 Installation ManualThe manufacturer of the non-essential ice detection system shall provide an installationmanual that specifies the following information so that aninstaller can determine appropriate use for an aircraft
22、installa-tion:5.3.1 A full description of the intended function(s) of thesystem including the possible restrictions / limitations, refer-encing the FIDS FUNCTIONS defined within SAEAS 5498 orEUROCAE ED-103A Section 3.5.3.2 An explicit compliance statement to this specification,5.3.3 The operation li
23、mitations (including the items in 5.2,Operating Conditions),5.3.4 The environmental conditions (including items inSection 7, Environmental Requirements),5.3.5 Installation and calibration instructions required forproper operation of all intended functions of the system,5.3.6 Instructions for Continu
24、ed AirworthinessThe manu-facturer of the Non-Essential ice detection system shall providecontinued airworthiness procedures necessary to ensure safeand accurate operation (calibration, alignment to aircraft,maintenance, etc.).5.3.7 A notice advising the installer that the icing indicationmust be pla
25、ced within the pilots viewing area, but cannotobstruct the pilots view.5.3.8 Installation location of markings and placards must beprovided.5.4 Users ManualThe manufacturer of the non-essentialice detection system shall provide a users manual that speci-fies:5.4.1 The functional operation of the sys
26、tem (includingitems in Section 6, Functional Requirements).5.5 It is permissible that the Installation and User Manual beone document, so long as it clearly delineates the two sections.6. Functional Requirements6.1 Intended Function:6.1.1 The intended function(s) shall be specified, referenc-ing the
27、 FIDS FUNCTIONS defined within SAE AS 5498 orEUROCAE ED-103 Section 3, highlighting the possible de-viations and adaptations made for the user.6.1.2 The intended function shall be consistent with anyexisting AFM Limitations and Procedures.6.2 Performance:6.2.1 Compliance of the function(s) specified
28、 in 6.1.1 shallbe demonstrated (taking into account declared deviations andadaptations) through test conditions of SAE AS 5498 orEUROCAE ED-103, “Minimum Operational PerformanceSpecification for Inflight Icing Detection Systems.”6.2.1.1 These characteristics shall be verified by test of afunctionall
29、y equivalent system.6.2.1.2 This test need not be representative of any particularaircraft installation and may be done in a wind tunnel, on anaircraft, or other testing method.6.3 Accessibility of ControlsAdjustments not normallymade during flight (for example, setup, calibration, etc.) shallnot be
30、 accessible from the top-level user interface (that is, theremust be a menu or special entry that requires a deliberate actionto enter setup mode).6.4 SoftwareIf the system uses software, it shall functionas described in the systems user manual. The softwareconfiguration shall be controlled by the m
31、anufacturer.6.4.1 If the device can have field loadable software, therevision shall reside on, or in, the product such that a user canview it.7. Environmental Requirements7.1 The system shall meet the following parameters speci-fied by the manufacturer:NOTE 1Only the environmental and electrical req
32、uirements explicitlycalled out in this specification are required for non-essential ice detectors.7.1.1 Operating Temperature RangeThe temperaturerange throughout which the system functions as intended.TABLE 1 Aircraft Icing Certification BasisAirplaneClassificationIcing Certification Basis Sections
33、 RequiredA Aircraft not approved foroperation in icing conditionsAll except 8.2.3, 10.3B Aircraft approved for operationin icing conditions by virtue ofice protection equipment as partof the minimum requiredequipment listAll except 8.2.3, 10.3C Aircraft certified for flight in theicing conditions de
34、fined in 11.1and 11.2 Specification F3120/F3120MAllF3310 1827.1.1.1 The performance levels in RTCA DO-160E, Section4.0, Category appropriate for the installation, for temperatureand altitude are one means to meet the requirements above.7.1.2 Storage/Survival Temperature RangeThe tempera-ture range t
35、hroughout which the system is exposed and notpermanently damaged.7.1.2.1 The performance levels in RTCA DO-160E, Section4.0, Category appropriate for the installation, for temperatureand altitude are one means to meet the requirements above.7.1.3 Operating Humidity RangeThe humidity range atstandard
36、 temperature and pressure throughout which the sys-tem functions as intended.7.1.3.1 The performance levels in RTCA DO-160E, Section6.0, Category A, for humidity is one means to meet therequirements above.7.1.4 Operating Altitude RangeThe altitude rangethroughout which the system functions as intend
37、ed.7.1.4.1 The performance levels in RTCA DO-160E, Section4.0, Category appropriate for the installation, for temperatureand altitude is one means to meet the requirements above.7.1.5 Operating Airspeed RangeThe airspeed rangethroughout which the system functions as intended.7.1.6 WaterproofnessThe
38、precipitation conditions forwhich the system functions as intended in accordance to thelimitations defined in Section 5.7.1.6.1 The performance levels in RTCA DO-160E, Section10.0, Category R, for waterproofness is one means to meet therequirements above.NOTE 2See 7.4.7.2 VibrationThe system shall n
39、ot be permanently dam-aged by vibration it is expected to be exposed to based on theaircraft installation.7.2.1 The performance levels in RTCA DO-160E, Section8.0, Category S, Curve C, for vibration is one means to meetthe requirements above.7.3 IcingThe system shall not be permanently damagedwhen i
40、cing occurs on system components that are designed tobe exposed to environments external to the aircraft.7.4 Deicing FluidsIf deicing fluids are permitted by theairplane manufacturer, compliance to 7.4.1 7.4.3 shall beshown.7.4.1 The system shall comply with the fluid susceptibilityrequirements in R
41、TCA DO-160E, Section 11.0, Category F, fora representative Type I or III fluid and a representative Type IIor IV fluid as approved by the airplane manufacturer.7.4.2 Unless the Users Manual prohibits the spraying ofdeicing or anti-icing fluid directly on the ice detectionsensor(s), the system shall
42、comply with the waterproofnessrequirements in RTCA DO-160E, Section 10.0, Category S.7.4.3 Unless the Users Manual requires cleaning of the icedetector after flights which applied a ground icing fluid, residueof Type II or IV fluid, if approved by the airplane manufacturer,shall be shown not to affe
43、ct ice detection performance.7.5 Emissions of RF EnergyThe system shall not ad-versely affect simultaneous operation of essential aircraftequipment, under operating conditions at any frequencies usedon aircraft.7.5.1 The performance levels in RTCA DO-160E, Section21.0, Category M, for conducted and
44、radiated RF emissions isone means to meet the requirements above.7.6 Electrical Power InputIf the system uses electricalpower from the aircraft, it shall function throughout the normalin-flight voltage operating range as provided by the aircraft.8. Installation Requirements8.1 The ice detection sens
45、or shall be located such that thelocal LWC at the sensor is comparable to freestream bymeeting one of the requirements of 8.1.1 8.1.3.8.1.1 For airplane classificationsAand B (see Table 1), withice detectors mounted on the lower surface of the wing withinthe first 25 % chord and where the sensing re
46、gion is located atleast one inch from the surface of the airfoil, no analysis isrequired.8.1.2 For airplane classifications A or B mounted in alocation other than that described in 8.1.1, an impingementanalysis shall be accomplished using a drop size of 15 and 40m and a typical holding angle of atta
47、ck and true airspeed withflaps retracted.8.1.3 For airplane classification C an impingement analysisshall be accomplished using drop sizes of 15 and 40 m andexpected operating angles of attack and true airspeed, for flapsretracted and approach flaps.8.2 Sensor Location:8.2.1 The sensor location shal
48、l consider effects induced byaircraft geometry and other upstream aircraft systems orcomponents.8.2.1.1 The location of the sensor shall take into consider-ation effects of propeller slipstream.8.2.1.2 The location of the sensor shall take into consider-ation effects of nearby heat producing systems
49、.8.2.1.3 The location shall consider local aerodynamic heat-ing effects.8.2.2 The sensor location shall not introduce a disturbancethat will interfere with downstream systems or componentssuch as air data probes or have an appreciable effect on aircraftaerodynamics.8.2.3 The selected location where the sensor is installedshall not introduce an ice shed hazard to downstream structureor propulsion systems.8.2.4 The sensor shall not reach a temperature duringdeicing that is hazardous to surrounding materials/structure/flammable fl
