ASTM F3116/F3116M-15
(Specification)Standard Specification for Design Loads and Conditions
Standard Specification for Design Loads and Conditions
ABSTRACT
This specification covers airworthiness requirements for the design loads and conditions of small airplanes, and is applicable to small airplanes as defined in the F44 terminology standard. The applicant for a design approval must seek individual guidance from their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements cover: flight loads including air, ground, and water loads; flight load factors; symmetrical and unsymmetrical flight conditions; limit maneuvering load factors; gust load factors; design fuel loads; rolling and yawing conditions; pressurized cabin loads; unsymmetrical loads due to engine failure; maneuvering loads for horizontal surfaces; and gust loads for horizontal surfaces. Also addressed in this specification are design airspeeds, engine mount loads, and flight control loads.
SCOPE
1.1 This specification addresses the airworthiness requirements for the design loads and conditions of small airplanes.
1.2 This specification is applicable to small airplanes as defined in the F44 terminology standard. Use of the term airplane is used throughout this specification and will mean “small airplane.”
1.3 The applicant for a design approval must seek individual guidance from their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Small Airplane Airworthiness Rules (hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links.
1.4 Units—Currently there is a mix of SI and Imperial units. In many locations, SI units have been included otherwise units are as they appear in Amendment 62 of 14 CFR Part 23. In a future revision values will be consistently stated in SI units followed by Imperial units in square brackets. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in non-conformance with the standard.
1.5 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.
General Information
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Standards Content (Sample)
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Designation:F3116/F3116M −15
Standard Specification for
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Design Loads and Conditions
ThisstandardisissuedunderthefixeddesignationF3116/F3116M;thenumberimmediatelyfollowingthedesignationindicatestheyear
of original adoption or, in the case 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.
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1. Scope 2.2 U.S. Code of Federal Regulations:
14 CFR Part 23 Airworthiness Standards: Normal, Utility,
1.1 This specification addresses the airworthiness require-
Aerobatic and Commuter Category Airplanes (Amend-
ments for the design loads and conditions of small airplanes.
ment 62)
1.2 This specification is applicable to small airplanes as
2.3 European Aviation Safety Agency Regulations:
defined in the F44 terminology standard. Use of the term
Certification Specifications for Normal, Utility, Aerobatic,
airplane is used throughout this specification and will mean
and Commuter CategoryAeroplanes (CS-23,Amendment
“small airplane.”
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1.3 Theapplicantforadesignapprovalmustseekindividual Certification Specifications for Very Light Aeroplanes (CS-
guidance from their respective CAA body concerning the use VLA, Amendment 1)
of this standard as part of a certification plan. For information
3. Terminology
on which CAA regulatory bodies have accepted this standard
(in whole or in part) as a means of compliance to their Small
3.1 A listing of terms, abbreviations, acronyms, and sym-
Airplane Airworthiness Rules (hereinafter referred to as “the bols related to aircraft covered byASTM Committees F37 and
Rules”), refer to ASTM F44 webpage (www.ASTM.org/
F44 airworthiness design standards can be found in Terminol-
COMMITTEE/F44.htm) which includes CAA website links. ogy F3060. Items listed below are more specific to this
standard.
1.4 Units—Currently there is a mix of SI and Imperial units.
In many locations, SI units have been included otherwise units 3.2 Definitions of Terms Specific to This Standard:
are as they appear in Amendment 62 of 14 CFR Part 23. In a 3.2.1 chordwise, n—directed, moving, or placed along the
future revision values will be consistently stated in SI units chord of an airfoil section.
followed by Imperial units in square brackets. The values
3.2.2 downwash, n—the downward deflection of an air-
stated in each system may not be exact equivalents; therefore,
stream by an aircraft wing.
each system shall be used independently of the other. Combin-
3.2.3 flight envelope, n—any combination of airspeed and
ing values from the two systems may result in non-
load factor on and within the boundaries of a flight envelope
conformance with the standard.
that represents the envelope of the flight loading conditions
1.5 This standard does not purport to address all of the
specified by the maneuvering and gust criteria.
safety concerns, if any, associated with its use. It is the
3.2.4 flight load factor, n—represents the ratio of the aero-
responsibility of the user of this standard to establish appro-
dynamic force component (acting normal to the assumed
priate safety and health practices and determine the applica-
longitudinal axis of the airplane) to the weight of the airplane.
bility of regulatory limitations prior to use.
A positive flight load factor is one in which the aerodynamic
force acts upward, with respect to the airplane.
2. Referenced Documents
3.2.5 propeller slipstream, n—the airstream pushed back by
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2.1 ASTM Standards:
a revolving aircraft propeller.
F3060 Terminology for Aircraft
3.2.6 spanwise, n—directed, moving, or placed along the
span of an airfoil.
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ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral 3.2.7 winglet, n—a nearly vertical airfoil at an airplane’s
Aviation Aircraft and is the direct responsibility of Subcommittee F44.30 on
wingtip.
Structures.
3.3 Acronyms:
Current edition approved May 1, 2015. Published July 2015. DOI: 10.1520/
F3116_F3116M-15.
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For referenced ASTM standards, visit the ASTM website, www.astm.org, or
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contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM AvailablefromU.S.GovernmentPrintingOfficeSuperintendentofDocuments,
Standards volume information, refer to the standard’s Document Summary page on 732 N. Capitol St., NW, Mail Stop: SDE, Washington, DC 20401, http://
the ASTM website. www.access.gpo.gov.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
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F3116/F3116M−15
3.3.1 MCP—maximum continuous power 4.3.3 Mutual influence of the aerodynamic surfaces must be
taken into account when determining flight loads.
3.4 Symbols:
4.4 Flight Envelope:
C = maximum airplane normal force coefficient
NA
4.4.1 General—Compliance with the st
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