1、Designation: F3061/F3061M 16bF3061/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 yea
2、r of last 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 international standards for the systems and equipment aspects of airworthiness and desi
3、gn for“small” aircraft.1.2 The applicant for a design approval must seek the individual guidance of their respective CAA body concerning the use ofthis standard as part of a certification plan. For information on which CAAregulatory bodies have accepted this standard (in wholeor in part) as a means
4、of compliance to their SmallAircraftAirworthiness regulations (hereinafter referred to as “the Rules”), referto ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links.1.3 The values stated in either SI units or inch-pound units are to be regarded separately as standard. T
5、he values stated in eachsystem may not be exact equivalents; therefore, each system shall be used 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 the safety concerns, if any, associa
6、ted with its use. It is the responsibilityof the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatorylimitations prior to use.2. Referenced Documents2.1 Following is a list of external standards referenced throughout this document;s
7、pecification; the earliest revision acceptablefor use is indicated. In all cases later document revisions are acceptable if shown to be equivalent to the listed revision, or ifotherwise formally accepted by the governing civil aviation authority; earlier revisions are not acceptable.2.2 ASTM Standar
8、ds:2F3060 Terminology for AircraftF3066/F3066MF3082/F3082M Specification for Powerplant Systems Specific Hazard MitigationFlight for General AviationAeroplanesF3083/F3083M Specification for Emergency Conditions, Occupant Safety and AccommodationsF3116/F3116M Specification for Design Loads and Condit
9、ionsF3117 Specification for Crew Interface in AircraftF3227/F3227M Specification for Environmental Systems in Small AircraftF3228 Specification for Flight Data and Voice Recording in Small AircraftF3230 Practice for Safety Assessments of Systems and Equipment in Small AircraftF3231/F3231M Specificat
10、ion for Electrical Systems in Small AircraftF3232/F3232M Specification for Flight Controls in Small AircraftF3233/F3233M Specification for Instrumentation in Small AircraftF3234/F3234M Specification for Exterior Lighting in Small AircraftF3236 Specification for High Intensity Radiated Field (HIRF) P
11、rotection in Small Aircraft2.3 Other Standards:14 CFR Part 23 Amendment 62 Airworthiness Standards: Normal, Utility, Acrobatic, and Commuter Category AirplanesEUROCAE ED-107, Rev A Guide to Certification of Aircraft in a High-Intensity Radiated Field (HIRF) EnvironmentFAA-S-8081-14B, Change 5 Privat
12、e Pilot Practical Test Standards for Airplane1 This specification is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsibility of Subcommittee F44.50 on Systemsand Equipment.Current edition approved Dec. 1, 2016Feb. 15, 2017. Published January 2017Mar
13、ch 2017. Originally approved in 2015. Last previous edition approved in 2016 asF3061/F3061M 16a.F3061/F3061M 16b. DOI: 10.1520/F3061_F3061M-16B.10.1520/F3061_F3061M-17.2 For referencedASTM standards, visit theASTM website, www.astm.org, or contactASTM Customer Service at serviceastm.org. For Annual
14、Book of ASTM Standardsvolume information, refer to the standards Document Summary page on the ASTM website.This document is not an ASTM standard and is intended only to provide the user of an ASTM standard an indication of what changes have been made to the previous version. Becauseit may not be tec
15、hnically possible to adequately depict all changes accurately, ASTM recommends that users consult prior editions as appropriate. In all cases only the current versionof the standard as published by ASTM is to be considered the official document.Copyright ASTM International, 100 Barr Harbor Drive, PO
16、 Box C700, West Conshohocken, PA 19428-2959. United States1RTCA/DO-178, Rev B Software Considerations in Airborne Systems and Equipment CertificationRTCA/DO-254 Design Assurance Guidance for Airborne Electronic HardwareRTCA/DO-335 Guidance for Installation of Automatic Flight Guidance and Control Sy
17、stems (AFGCS) for Part 23 Airplanes2.4 SAE Standards:3SAE AIR825/4, Rev A Chemical Oxygen SystemsSAE ARP4754, Rev A Guidelines for Development of Civil Aircraft SystemsSAE ARP4761 Guidelines and Methods for Conducting the Safety Assessment Process on Civil Airborne Systems andEquipmentSAE ARP5583, R
18、ev A Guide to Certification of Aircraft in a High-Intensity Radiated Field (HIRF) EnvironmentSAE AS8017, Rev A Minimum Performance Standard for Anticollision Light SystemsSAE AS8037, Rev Minimum Performance Standard for Aircraft Position Lights3. Terminology3.1 Terminology specific to this standard
19、is provided below. For general terminology, refer to the Terminology standardF3060referenced in Section 2.3.2 Definitions of Terms Specific to This Standard:3.2.1 aircraft type code, nan Aircraft Type Code (ATC) is defined by considering both the technical considerations regardingthe design of the a
20、ircraft and the airworthiness level established based upon risk-based criteria. An ATC is expressed as analphanumeric character string as illustrated in Fig. 1. An explanation of each character in the string is provided below.3.2.1.1 DiscussionThe first character in the Aircraft Type Code indicates
21、the risk-based airworthiness level of the aircraft.(1) A “1” indicates an airworthiness level corresponding to Level 1; this corresponds to seating for one or fewer passengers(excluding crew).(2) A“2” indicates an airworthiness level corresponding to Level 2; this corresponds to seating for two or m
22、ore passengers butno more than six (excluding crew).(3) A “3” indicates an airworthiness level corresponding to Level 3; this corresponds to seating for seven or more passengersbut no more than nine (excluding crew).(4) A “4” indicates an airworthiness level corresponding to Level 4; this correspond
23、s to seating for ten or more passengers butno more than nineteen (excluding crew).3.2.1.2 DiscussionThe second character in the Aircraft Type Code indicates the number of engines employed on the aircraft.(1) An “S” indicates a single-engine aircraft.(2) An “M” indicates a multiengine aircraft.3 Avai
24、lable from SAE International (SAE), 400 Commonwealth Dr., Warrendale, PA 15096, http:/www.sae.org.FIG. 1 Illustration of Aircraft Type CodeF3061/F3061M 1723.2.1.3 DiscussionThe third character in the Aircraft Type Code indicates the type of engine(s) employed on the aircraft.(1) An “R” indicates use
25、 of a reciprocating engine.(2) A “T” indicates use of a turbine engine.3.2.1.4 DiscussionThe fourth character in the Aircraft Type Code indicates the stall speed of the aircraft.(1) An “L” indicates a stall speed less than or equal to 83 km/h 45 knots.(2) An “M” indicates a stall speed greater than
26、83 km/h 45 knots but less than or equal to 113 km/h 61 knots.(3) An “H” indicates a stall speed greater than 113 km/h 61 knots.3.2.1.5 DiscussionThe fifth character in the Aircraft Type Code indicates the cruise speed of the aircraft.(1) An “L” indicates a cruise speed less than or equal to 463 km/h
27、 250 knots (or Mach 0.6).(2) An “H” indicates a cruise speed greater than 463 km/h 250 knots (or Mach 0.6).3.2.1.6 DiscussionThe sixth character in the Aircraft Type Code indicates the allowed meteorological conditions of the aircraft.(1) A “D” indicates an aircraft limited to Day VFR conditions onl
28、y.(2) An “N” indicates an aircraft limited to Day or Night VFR conditions only.(3) A “I” indicates an aircraft certified for IFR operations.3.2.1.7 DiscussionThe seventh character in the Aircraft Type Code indicates the maximum operational altitude of the aircraft.(1) An “L” indicates an aircraft wi
29、th a maximum operational altitude equal to or less than 7620 m 25 000 ft.(2) An “H” indicates an aircraft with a maximum operational altitude greater than 7620 m 25 000 ft.3.2.1.8 DiscussionThe eighth character in the Aircraft Type Code indicates the allowed flight maneuvers for the aircraft.(1) An
30、“N” indicates an aircraft that is limited to non-aerobatic maneuvers.(2) An “A” indicates an aircraft that is certified for aerobatic maneuvers.3.2.2 BTPS, nBTPS stands for “Body Temperature and Pressure, Saturated.” This is defined to be a temperature of 37C anda pressure equal to the ambient press
31、ure to which the body is exposed minus 6.27 kPa 47 mmHg; this is the tracheal pressuredisplaced by water vapor pressure when the breathed air becomes saturated with water vapor at 37C.3.2.3 catastrophic failure condition, na catastrophic failure condition is one that would result in multiple fatalit
32、ies of theoccupants, or incapacitation or fatal injury to a flight crew member, normally with the loss of the aircraft.3.2.4 chemical oxygen generator, na chemical oxygen generator is defined as a device which produces oxygen by chemicalreaction; for more detailed information, refer to SAE AIR 825/4
33、.3.2.5 complex system, nA complex system is a system whose operation, failure modes, or failure effects are difficult tocomprehend without the aid of analytical methods or structured assessment methods, such as Failure Modes and Effects Analysis(FMEA) or Fault Tree Analysis (FTA). Increased system c
34、omplexity is often caused by such items as sophisticated componentsand multiple interrelationships.3.2.2 continued safe flight and landing, ncontinued safe flight and landing is defined as the capability for continued controlledflight and landing, possibly using emergency procedures, but without req
35、uiring pilot skill beyond that needed to pass the PrivatePilot Practical Test Standard for Airplane (refer to FAA-S-8081-14B), or requiring pilot forces beyond those defined in14Specification F3082/F3082MCFR 23.143. . Landing may occur either at an airport or at an emergency landing locationconsiste
36、nt with established emergency procedures. Some aircraft damage may be realized, either during flight or upon landing.F3061/F3061M 1733.2.7 conventional system, na conventional system is a system whose function, the technological means to implement itsfunction, and its intended usage are all the same
37、 as, or closely similar to, that of previously approved systems that are commonlyused.3.2.8 design appraisal, na design appraisal is a qualitative appraisal of the integrity and safety of the system design. Aneffective appraisal requires experienced judgment.3.2.3 development assurance level, na dev
38、elopment assurance level is an indication of the level of those planned andsystematic actions used to substantiate, to an adequate level of confidence, that errors in requirements, design, and implementationhave been identified and corrected such that the system satisfies the applicable certificatio
39、n basis.3.2.10 extremely improbable, nextremely improbable means that an event is considered so unlikely that it is not anticipatedto occur during the entire operational life of all aircraft of one type.3.2.11 extremely remote, nextremely remote means that an event is not anticipated to occur to eac
40、h aircraft during its totallife, but may occur a few times when considering the total operational life of all aircraft of the type.3.2.12 failure condition, na failure condition is a condition having an effect on the aircraft or its occupants or both, eitherdirect or consequential, which is caused o
41、r contributed to by one or more failures or errors. The severity of a failure condition maybe affected by flight phase, relevant adverse operational or environmental conditions, or other external events, or combinationsthereof.3.2.13 hazardous failure condition, na hazardous failure condition is one
42、 that would reduce the capability of the aircraft orthe ability of the crew to cope with adverse operating conditions to the extent that there would be: a large reduction in safetymargins or functional capabilities; physical distress or excessive workload such that the flight crew cannot be relied u
43、pon toperform their tasks accurately or completely; or, serious or fatal injuries to a relatively small number of persons other than the flightcrew.3.2.14 high speed, nan aircrafts performance level is considered High Speed if VNE or VNO is greater than 463 km/h 250knots, or MMO is greater than M0.6
44、.3.2.15 installation appraisal, nan installation appraisal is a qualitative appraisal of the integrity and safety of the installation.Any deviations from normal industry-accepted installation practices should be evaluated.3.2.16 instrument, nthe term instrument includes devices that are physically c
45、ontained in one unit or component, and devicesthat are composed of two or more physically separate units or components connected together (such as a remote indicatinggyroscopic direction indicator that includes a magnetic sensing element, a gyroscopic unit, an amplifier, and an indicator connectedto
46、gether).3.2.17 low speed, nan aircrafts performance level is considered low speed if VNE or VNO is less than or equal to 463 km/h250 knots, or MMO is less than or equal to M0.6.3.2.18 major failure condition, na major failure condition is one that would reduce the capability of the aircraft or the a
47、bilityof the flight crew to cope with adverse operating conditions to the extent that there would be: a significant reduction in safetymargins or functional capabilities; a significant increase in flight crew workload or in conditions impairing the efficiency of theflight crew; discomfort to the fli
48、ght crew; or, physical distress to passengers or cabin crew, possibly including injuries.3.2.19 minor failure condition, na minor failure condition is one that would not significantly reduce aircraft safety, and whichinvolves crew actions that are well within their capabilities. Minor Failure Condit
49、ions may include: a slight reduction in safetymargins or functional capabilities; a slight increase in crew workload, such as routine flight plan changes; or, some physicaldiscomfort to passengers or cabin crew.3.2.20 negligible failure condition, na negligible failure condition is one that would have no procedural or operational effecton the flight crew as documented in the Airplane Flight Manual, or on the operation or capabilities of the aircraft; however, theevent may result in an inconvenience to aircraft occupan
