1、Designation: F3061/F3061M 17Standard Specification forSystems and Equipment in Small Aircraft1This standard is issued under the fixed designation F3061/F3061M; the number immediately following the designation indicates the yearof original adoption or, in the case of revision, the year of last revisi
2、on. 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 thesystems and equipment aspects of airworthiness and design for“small” air
3、craft.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 toth
4、eir 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 The values stated in either SI units or inch-pound unitsare to be regarded separately as standard. The values stated ine
5、ach system may not be exact equivalents; therefore, eachsystem shall be used independently of the other. Combiningvalues from the two systems may result in non-conformancewith the standard.1.4 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is
6、 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 Following is a list of external standards referencedthroughout this specification; the earliest rev
7、ision acceptablefor use is indicated. 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 Aircra
8、ftF3082/F3082M Specification for Flight for GeneralAviationAeroplanesF3083/F3083M Specification for Emergency Conditions,Occupant Safety and AccommodationsF3116/F3116M Specification for Design Loads and Condi-tionsF3117 Specification for Crew Interface in AircraftF3227/F3227M Specification for Envir
9、onmental Systems inSmall AircraftF3228 Specification for Flight Data and Voice Recording inSmall AircraftF3230 Practice for Safety Assessments of Systems andEquipment in Small AircraftF3231/F3231M Specification for Electrical Systems inSmall AircraftF3232/F3232M Specification for Flight Controls in
10、SmallAircraftF3233/F3233M Specification for Instrumentation in SmallAircraftF3234/F3234M Specification for Exterior Lighting in SmallAircraftF3236 Specification for High Intensity Radiated Field(HIRF) Protection in Small Aircraft2.3 Other Standards:FAA-S-8081-14B, Change 5 Private Pilot Practical Te
11、stStandards for AirplaneRTCA/DO-178, Rev B Software Considerations in AirborneSystems and Equipment CertificationRTCA/DO-254 Design Assurance Guidance for AirborneElectronic Hardware2.4 SAE Standards:3SAE ARP4754, Rev A Guidelines for Development of CivilAircraft Systems3. Terminology3.1 Terminology
12、 specific to this standard is provided below.For general terminology, refer to Terminology F3060.3.2 Definitions of Terms Specific to This Standard:1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.50 o
13、nSystems and Equipment.Current edition approved Feb. 15, 2017. Published March 2017. Originallyapproved in 2015. Last previous edition approved in 2016 as F3061/F3061M 16b.DOI: 10.1520/F3061_F3061M-17.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Servi
14、ce 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.org.Copyright ASTM International, 100 Barr Harbor Drive, PO Bo
15、x 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 International Standards, Guides and Recommendations issued by t
16、he World Trade Organization Technical Barriers to Trade (TBT) Committee.13.2.1 aircraft type code, nan Aircraft Type Code (ATC) isdefined by considering both the technical considerations re-garding the design of the aircraft and the airworthiness levelestablished based upon risk-based criteria. An A
17、TC is ex-pressed as an alphanumeric character string as illustrated inFig. 1. An explanation of each character in the string isprovided below.3.2.1.1 DiscussionThe first character in the Aircraft TypeCode indicates the risk-based airworthiness level of the air-craft.(1) A “1” indicates an airworthin
18、ess level corresponding toLevel 1; this corresponds to seating for one or fewer passengers(excluding crew).(2) A “2” indicates an airworthiness level corresponding toLevel 2; this corresponds to seating for two or more passengersbut no more than six (excluding crew).(3) A “3” indicates an airworthin
19、ess level corresponding toLevel 3; this corresponds to seating for seven or morepassengers but no more than nine (excluding crew).(4) A “4” indicates an airworthiness level corresponding toLevel 4; this corresponds to seating for ten or more passengersbut no more than nineteen (excluding crew).3.2.1
20、.2 DiscussionThe second character in the AircraftType Code indicates the number of engines employed on theaircraft.(1) An “S” indicates a single-engine aircraft.(2) An “M” indicates a multiengine aircraft.3.2.1.3 DiscussionThe third character in theAircraft TypeCode indicates the type of engine(s) e
21、mployed on the aircraft.(1) An “R” indicates use of a reciprocating engine.(2) A “T” indicates use of a turbine engine.3.2.1.4 DiscussionThe fourth character in the AircraftType Code indicates the stall speed of the aircraft.(1) An “L” indicates a stall speed less than or equal to 83km/h 45 knots.(2
22、) An “M” indicates a stall speed greater than 83 km/h 45knots but less than or equal to 113 km/h 61 knots.(3) An “H” indicates a stall speed greater than 113 km/h61 knots.3.2.1.5 DiscussionThe fifth character in the Aircraft TypeCode indicates the cruise speed of the aircraft.(1) An “L” indicates a
23、cruise speed less than or equal to463 km/h 250 knots (or Mach 0.6).(2) An “H” indicates a cruise speed greater than 463 km/h250 knots (or Mach 0.6).3.2.1.6 DiscussionThe sixth character in theAircraft TypeCode indicates the allowed meteorological conditions of theaircraft.(1) A “D” indicates an airc
24、raft limited to Day VFR condi-tions only.(2) An “N” indicates an aircraft limited to Day or NightVFR conditions only.(3) A “I” indicates an aircraft certified for IFR operations.3.2.1.7 DiscussionThe seventh character in the AircraftType Code indicates the maximum operational altitude of theaircraft
25、.(1) An “L” indicates an aircraft with a maximum opera-tional altitude equal to or less than 7620 m 25 000 ft.(2) An “H” indicates an aircraft with a maximum opera-tional altitude greater than 7620 m 25 000 ft.3.2.1.8 DiscussionThe eighth character in the AircraftType Code indicates the allowed flig
26、ht maneuvers for theaircraft.(1) An “N” indicates an aircraft that is limited to non-aerobatic maneuvers.(2) An “A” indicates an aircraft that is certified for aero-batic maneuvers.3.2.2 continued safe flight and landing, ncontinued safeflight and landing is defined as the capability for continuedco
27、ntrolled flight and landing, possibly using emergencyprocedures, but without requiring pilot skill beyond thatneeded to pass the Private Pilot Practical Test Standard forAirplane (refer to FAA-S-8081-14B), or requiring pilot forcesbeyond those defined in Specification F3082/F3082M. Landingmay occur
28、either at an airport or at an emergency landinglocation consistent with established emergency procedures.Some aircraft damage may be realized, either during flight orupon landing.3.2.3 development assurance level, na development assur-ance level is an indication of the level of those planned andsyst
29、ematic actions used to substantiate, to an adequate level ofFIG. 1 Illustration of Aircraft Type CodeF3061/F3061M 172confidence, that errors in requirements, design, and implemen-tation have been identified and corrected such that the systemsatisfies the applicable certification basis.3.2.4 primary
30、function, na primary function is a functionthat is installed to comply with applicable requirements for arequired function and that provides the most pertinent controlsor information instantly and directly to the pilot.3.2.5 primary system, na primary system is a system thatprovides a primary functi
31、on.3.2.6 secondary system, na secondary system is a redun-dancy system that provides the same function as the primarysystem.3.2.7 unsafe system operating condition, nan unsafe sys-tem operating condition is any system operating conditionwhich, if not detected and properly accommodated by crewaction,
32、 would significantly contribute to or cause one or moreserious injuries.4. Basic InformationNOTE 1Table 1 provides correlation between various Aircraft TypeCodes and the individual requirements contained within this section; referto 3.2.1. For each subsection, an indicator can be found under each AT
33、Ccharacter field; three indicators are used:An empty cell()inal applicable ATC character field columnsindicates that an aircraft must meet the requirements of that subsection.A white circle () in multiple columns indicates that the requirementsof that subsection are not applicable to an aircraft onl
34、y if all such ATCcharacter fields are applicable.A mark-out () in any of the applicable ATC character field columnsindicates that the requirements of that subsection are not applicable to anaircraft if that ATC character field is applicable.ExampleAn aircraft with anATC of 1SRLLDLN is being consider
35、ed.Since all applicable columns are empty for 4.1.1, that subsection isapplicable to the aircraft. Since the “1” airworthiness level column, the“L” stall speed column, and the “D” meteorological column for 4.1.6 allcontain white circles, then that subsection is not applicable; however, foran aircraf
36、t with an ATC of 1SRMLDLN, 4.1.6 would be applicable sincethe “M” stall speed column does not contain a white circle. Subsection4.2.1.1 would also not be applicable to the second aircraft, since itcontains an in the “M” stall speed column.NOTE 2The requirements of this chapter are applicable to all
37、systemsand equipment installed in the aircraft. These requirements are in additionto and do not supersede any additional system specific requirementsidentified elsewhere in these design standards or contained in the rules ofthe governing civil aviation authority.4.1 Function and Installation:4.1.1 E
38、ach item of installed equipment must be of a kindand design appropriate to its intended function.4.1.2 Each item of installed equipment must be marked in away that makes it clear to an installer the equipmentsidentification, function, or operating limitations, or any appli-cable combination of these
39、 factors. It is acceptable to referenceequipment installation manuals for function or limitationinformation.4.1.3 Each item of installed equipment must be installedaccording to limitations specified for that equipment.4.1.4 Each item of installed equipment must function prop-erly when installed.4.1.
40、5 The aircraft systems and equipment required for typecertification or by operating rules must be designed andinstalled so that they perform as intended under the aircraftoperating and environmental conditions.NOTE 3The intent of this requirement is to provide assurance that therequired systems and
41、equipment will function as intended in the expectedoperating and environmental conditions. It is recognized that randomfailures will occur throughout the aircraft life and that the failed devicemay no longer “perform as intended”. The acceptability of such failures orcombination of failures and thei
42、r associated risks are addressed under therequirements of 4.2.4.1.6 All aircraft systems and equipment must be designedand installed so that they do not adversely affect the safety ofthe aircraft or its occupants.TABLE 1 ATC Compliance Matrix, Section 4SectionAirworthiness LevelNumber ofEnginesType
43、ofEngine(s)Stall SpeedCruiseSpeedMeteorologicalConditionsAltitude Maneuvers1234SMRTLMHLHDNILHNA44.14.1.14.1.24.1.34.1.44.1.54.1.6 CCC4.1.74.1.84.1.8.14.1.8.24.24.2.14.2.1.1 4.2.1.2 CCC4.2.1.34.2.1.44.2.24.2.34.2.3.14.2.4 CC4.2.4.14.2.4.2F3061/F3061M 1734.1.7 All aircraft systems and equipment must b
44、e designedand installed so that they do not adversely affect the properfunctioning of those systems or equipment, or both, covered by4.1.5.4.1.8 Those systems and equipment not required for typecertification or by operating rules are not required to performtheir intended function under all aircraft
45、operating and envi-ronmental conditions, provided that the resultant failure con-ditions are classified as “Negligible Failure Condition” in theassessment conducted per 4.2.1; refer to Practice F3230.4.1.8.1 Non-required systems and equipment with failureconditions classified more severe than “Negli
46、gible FailureCondition” are not required to perform their intended functionunder all aircraft operating and environmental conditions,provided the failure is appropriately annunciated to the crew.4.1.8.2 When addressing the requirements of 4.2,ifanycredit is taken for the installation, or any aspect,
47、 of thesenon-required systems, the portion of the system for whichcredit is taken must comply with 4.1.4.4.2 System Safety Requirements:4.2.1 An assessment of the aircraft and system functionsmust be performed to identify and classify the various FailureConditions associated with each function; refe
48、r to PracticeF3230.4.2.1.1 The equipment, systems, and installations must bedesigned to minimize hazards to the aircraft in the event of aprobable malfunction or failure; refer to Practice F3230.4.2.1.2 The aircraft systems and associated components,considered separately and in relation to other sys
49、tems, must bedesigned and installed so that each Catastrophic Failure Con-dition is “extremely improbable”; refer to Practice F3230.4.2.1.3 The aircraft systems and associated components,considered separately and in relation to other systems, must bedesigned and installed so that each Hazardous Failure Condi-tion is “extremely remote”; refer to Practice F3230.4.2.1.4 The aircraft systems and associated components,considered separately and in relation to other systems, must bedesigned and installed so that each Ma
