1、Designation: F3174/F3174M 15F3174/F3174M 18Standard Specification forEstablishing Operating Limitations and Information forAeroplanes1This standard is issued under the fixed designation F3174/F3174M; the number immediately following the designation indicates the yearof original adoption or, in the c
2、ase of revision, the year 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 establishes the airworthiness design requirements associated with the
3、establishment of operatinglimitations and information for the operation of aeroplanes. It covers the needcovers airworthiness requirements for establishinggeneral limitations and information to be contained in the aeroplane flight manual. This specification specifies what informationshall be provide
4、d and does not state how such information shall be presented unless this is necessary for the clarity of the purposeof the specification. Refer to Specification F3117 for means and methods of presentation. The material was developed through openconsensus of international experts in general aviation.
5、 This information was created by focusing on Level 1, 2, 3, and 4 NormalCategory aeroplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broaderapplicability as a specific means of compliance. The topics covered within this specification are:
6、 Limitations for Airspeed, Weightand Center of Gravity, Auxiliary Power Units, Minimum Flight Crew, Maximum Passenger Seating Configuration, Kinds ofOperation, and Maximum Operating Altitude.1.2 The applicant An applicant intending to propose this information as Means of Compliance for a design appr
7、oval shallmustseek the individual guidance offrom their respective civil aviation authority (CAA) body concerning the use of this specificationas part of a certification plan.oversight authority (for example, published guidance from applicable CAAs) concerning theacceptable use and application there
8、of. For information on which CAA regulatory bodies oversight authorities have accepted thisspecification (in whole or in part) as a means of compliance to their small aeroplane airworthiness regulations (hereinafter referredto as an acceptable Means of Compliance to their regulatory requirements (he
9、reinafter “the Rules”), refer to theASTM CommitteeF44 webpage (www.ASTM.org/COMITTEE/F44.htm), which includes CAA website links.web page (www.astm.org/COMMITTEE/F44.htm).1.3 This specification is applicable to small aeroplanes.1.3 UnitsThe values stated This specification may present information in
10、either SI units or inch-pound units are to be regardedseparately as standard. The units, English Engineering units, or both; the values stated in each system may not be exact equivalents;therefore, each equivalents. Each system shall be used independently of the other. Combiningother; combining valu
11、es from the twosystems may result in non-conformancenonconformance with the standard.1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibilityof the user of this standard to establish appropriate safety safety, health, and hea
12、lthenvironmental practices and determine theapplicability of regulatory limitations prior to use.1.5 This international standard was developed in accordance with internationally recognized principles on standardizationestablished in the Decision on Principles for the Development of International Sta
13、ndards, Guides and Recommendations issuedby the World Trade Organization Technical Barriers to Trade (TBT) Committee.2. Referenced Documents2.1 ASTM Standards:2F3060 Terminology for AircraftF3082 Specification for Weights and Centers of Gravity of AircraftF3114 Specification for Structures1 This spe
14、cification is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsibility of Subcommittee F44.20 on Flight.Current edition approved Dec. 1, 2015May 1, 2018. Published January 2016May 2018. Originally approved in 2015. Last previous edition approved in 2
15、015 asF3174/F3174M 15. DOI: 10.1520/F3174_F3174M-15.10.1520/F3174_F3174M-18.2 For referencedASTM standards, visit theASTM website, www.astm.org, or contactASTM Customer Service at serviceastm.org. For Annual Book of ASTM Standardsvolume information, refer to the standards Document Summary page on th
16、e 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 technically possible to adequately depict all changes accurately, ASTM recommends that users co
17、nsult 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 Box C700, West Conshohocken, PA 19428-2959. United States1F3116F3116/F3116M Specification f
18、or Design Loads and ConditionsF3117 Specification for Crew Interface in AircraftF3173F3173/F3173M Specification for Aircraft Handling Characteristics of Aeroplanes2.2 European Aviation Safety Agency Regulations:3CS-23 Certification Specifications for Normal, Utility, Aerobatic, and Commuter Category
19、 Aeroplanes (Amendment 3)CS-VLA Certification Specifications for Very Light Aeroplanes (Amendment 1)2.3 U.S. Code of Federal Regulations:414 CFR Part 23 Airworthiness Standards: Normal, Utility, Aerobatic and Commuter Category Airplanes (Amendment 62)3. Terminology3.1 See Terminology F3060 for defin
20、itions and abbreviations.4. Establishing Operating Limitations and Information4.1 GeneralEach applicable operating limitation specified in 4.2 4.84.11 and other limitations and information necessary forsafe operation shall be established.4.1.1 The operating limitations and other information necessar
21、y for safe operation shall be made available to the crewmembersas prescribed in Specification F3117.4.2 Airspeed Limitations:4.2.1 The never-exceed speed, VNE, shall be established as an operating limitation and shall be so that it is:4.2.1.1 Not less than 0.9 times the minimum value of VD allowed u
22、nder Specification F3116F3116/F3116M, and4.2.1.2 Not more than the lesser of:(1) 0.9 VD established under Specification F3116F3116/F3116M, or(2) 0.9 times the maximum speed shown under Specification F3173F3173/F3173M, Section 8.Vibration and Buffering.4.2.2 The maximum structural cruising speed, VNO
23、, shall be such that Vestablished as anCmin Voperating limitationNO VandshallC, with V be soCmin and Vthat itC established as under Specification is:F3116.4.2.2.1 Not less than the minimum value of VC allowed under Specification F3116/F3116M, and4.2.2.2 Not more than the lesser of:(1) VC established
24、 under Specification F3116/F3116M, or(2) 0.89 VNE established under 4.2.1.4.2.3 Subsections 4.2.1 and 4.2.2 do not apply when to turbine aeroplanes or to aeroplanes for which a VD/MD is establishedunder Specification F3116F3116/F3116M. For those aeroplanes:(1) Amaximum operating limit speed (VMO/ MM
25、O airspeed or Mach number, whichever is critical at a particular altitude) shallbe established as a speed that mayshall not be deliberately exceeded in any regime of flight (climb, cruise, or descent) unless ahigher speed is authorized for flight test or pilot training operations.(2) The value, VMO/
26、MMO, shall be established so that it is not greater than the design cruising speed, VC/MC, and so that itis sufficiently below VD/MD, or VDF/MDF, for jets, and the maximum speed shown under Specification F3173F3173/F3173M,Section 8 Vibration and Buffeting, to make it highly improbable that the latte
27、r speeds will be inadvertently exceeded in operations.(3) The speed margin between VMO/MMO and VD/MD, or VDF/MDF, may for jets, shall not be less than that determined underSpecification F3116F3116/F3116M, subsection 5.1.2 Design Dive Speed, or the speed margin found necessary in the flight testscond
28、ucted under Specification F3173F3173/F3173M, subsection 9.1.speed increase and recovery characteristics.4.2.4 The maximum operating maneuvering speed, VO, shall be established as an operating limitation and is a selected speedthat is not greater than Vs=n established in Specification F3116/F3116M, D
29、esign Maneuvering Speed.4.2.5 The flap extended speed, VFE, shall be established as an operating limitation and shall be so that it is:4.2.5.1 Not less than the minimum value of VF allowed in Specification F3116/F3116M, High Lift Devices, and4.2.5.2 Not more than VF established under Specification F
30、3116/F3116M, High Lift Devices.4.2.5.3 Additional combinations of flap setting, airspeed, and engine power may be established if the structure has been provenfor the corresponding design conditions.4.2.6 The minimum control speed, VMC, determined under Specification F3173/F3173M shall be established
31、 as an operatinglimitation.4.3 Operating Maneuvering SpeedThe maximum operating maneuvering speed, VO, shall be established as an operatinglimitation. The value, VO, is a selected speed that is not greater than VA established in Specification F3116.4.4 Flap Extended Speed:4.4.1 The flap extended spe
32、ed, VFE, shall be established so that it is:4.4.1.1 Not less than the minimum value of VF allowed in Specification F3116, subsection 4.8.2, and4.4.1.2 Not more than VF established under Specification F3116, subsections 4.8.1, 4.8.3, and 4.8.4.4.4.2 Additional combinations of flap setting, airspeed,
33、and engine power may be established if the structure has been provenfor the corresponding design conditions.F3174/F3174M 1824.5 Minimum Control SpeedThe minimum control speed, VMC, determined under Specification F3173, subsection 3.5, shallbe established as an operating limitation.4.3 Weight and Cen
34、ter of GravityThe weight and center of gravity limitations determined under 23.23Specification F3082,Load Distribution Limits, shall be established as operating limitations.4.4 Auxiliary Power Unit LimitationsIf an auxiliary power unit is installed, the limitations established for the auxiliary powe
35、runit shall be specified in the operating limitations for the aeroplane.4.5 Minimum Flight CrewThe minimum flight crew shall be established as an operating limitation and shall be so that it issufficient for safe operation considering:4.5.1 The workload on individual crewmembers,4.5.2 The accessibil
36、ity and ease of operation of necessary controls by the appropriate crewmember, and4.5.3 The kinds of operation authorized under 4.7.4.5.4 In addition, for Level 4 aeroplanes, each crewmember workload determination shall consider the following:(1) Flight path control,(2) Collision avoidance,(3) Navig
37、ation,(4) Communications,(5) Operation and monitoring of all essential aeroplane systems,(6) Command decisions, and(7) The accessibility and ease of operation of necessary controls by the appropriate crewmember during all normal andemergency operations when at the crewmember flight station.4.8.3 The
38、 accessibility and ease of operation of necessary controls by the appropriate crewmember, and4.8.4 The kinds of operation authorized under 4.10.4.6 Maximum Passenger Seating ConfigurationThe maximum passenger seating configuration shall be established.estab-lished as an operating limitation.4.7 Kind
39、s of OperationThe kinds of operation authorized (for example, VFR, IFR, day or night) and the meteorologicalconditions (for example, icing) to which the operation of the aeroplane is limited or from which it is prohibited shall be establishedas operating limitations and shall be appropriate to the i
40、nstalled equipment.4.8 Maximum Operating Altitude:4.8.1 The maximum altitude up to which operation is allowed, as limited by flight, structural, powerplant, functional orequipment characteristics, shall be established.established as an operating limitation.4.8.2 A For pressurized aeroplanes, a maxim
41、um operating altitude limitation of not more than 7620 m 25 000 ft shall beestablished for pressurized aeroplanes unless compliance with Specification F3114, subsection 4.7.4 Windshields and Windows foroperation above this altitude is shown.5. Keywords5.1 aeroplane; aeroplane flight manual; airworth
42、iness design requirementAPPENDIXES(Nonmandatory Information)X1. REMOVED WITH F3174/F3174M 18F3174/F3174M 183APPENDIX(Nonmandatory Information)X2. DIFFERENCES FROM PART/CS 23 AND CS-VLACHANGE HISTORYX2.1 Change History from F3174/F3174M 15 to 18X2.1 In Table X1.1, the changes are listed to Part 23 Am
43、dt 62, CS 23Amdt. 1 and CS-VLA 226 Amdt. 1 language and new requirements with rationale for the differences.X2.1.1 Reason for RevisionAlignment with 14 CFR Part 23, Amendment 64 and EASA CS 23 Amdt. 5, Update of referencesand simplification of language.X2.1.2 Detailed Changes:X2.1.2.1 Section 1.1 th
44、rough 1.3: Update to match F44 Standards Editorial Guide 2017-02.X2.1.2.2 Section 2.1: New reference for F3082 added. Update of titles.X2.1.2.3 Sections 2.2 and 2.3: Removed, since no longer referenced in Section 3 and onwards.X2.1.2.4 Section 4.1: Update to match new numbering structure.X2.1.2.5 Se
45、ction 4.2.1: Clarification that VNE shall be established as an operating limitation.X2.1.2.6 Section 4.2.1.2(2): Reference changed from section number to title.X2.1.2.7 Section 4.2.2: Clarification that VNO shall be established as an operating limitation and reverted back to 14 CFR Part 23,Amendment
46、 62 language (non simplified) for easier acceptance of first set of consensus standards by CAAs.X2.1.2.8 Section 4.2.3: Applicability to turbine aeroplanes or to aeroplanes for which VD/MD is established re-introduced,reverted back to 14 CFR Part 23,Amendment 62 language (non simplified) for easier
47、acceptance of first set of consensus standardsby CAAs.X2.1.2.9 Section 4.2.3(1): “may” replaced with “shall” in accordance with F44 Editorial Guide.X2.1.2.10 Section 4.2.3(2): Reference changed from section number to title. Term “VDF/MDF for jets” re-introduced (nonsimplified language) for easier ac
48、ceptance of first set of consensus standards by CAAs.X2.1.2.11 Section 4.2.3(3): Reference changed from section number to title. Term “VDF/MDF for jets” re-introduced (nonsimplified language) for easier acceptance of first set of consensus standards by CAAs. “May” replaced with “shall” in accordance
49、with F44 Editorial Guide.X2.1.2.12 Section 4.2.4: Operating Maneuvering Speed (former Section 4.3) moved under Section 4.2Airspeed Limitations. Titleof subsection removed, because of redundant language. Reverted back from Vs=n to match 14 CFR Part 23, Amendment 62/CS23, Amendment 4 language (non simplified) for easier acceptance of first set of consensus standards by CAAs.X2.1.2.13 Section 4.2.5: Flap Extended Speed (former Section 4.4) moved under section 4.2 Airspeed Limitations. Title ofsubsection removed, because of redundant language.X2.1.2.14 Sectio
