ASTM F3619-22

This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the
Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
Designation: F3619 −22
Standard Specification for
Aeroelasticity Requirements for a Light Sport Airplane
This standard is issued under the fixed designation F3619; the number immediately following the designation indicates the year 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.
1. Scope AC 23.629 Means of Compliance withTitle 14 CFR, Part 23
Amdt. 63, § 23.629, Flutter
1.1 This specification addresses the aeroelasticity require-
ments of the airplane and is applicable to the design of a light
3. Terminology
sport aircraft/airplane as defined by regulations.
3.1 Abbreviations:
1.2 This specification shall apply to airplanes with V
H
3.1.1 CAS—calibrated airspeed (m/s, knots)
greater than 62 m/s (120 KCAS) and with V less than or
NE
3.1.2 EAS—equivalent airspeed (m/s, knots)
equalto129 m⁄s(250 KCAS).Thecontentofthisspecification
3.1.3 EFIS—electronic flight information system
may be more broadly applicable. It is the responsibility of the
applicant to substantiate broader applicability as a specific
3.1.4 GVT—ground vibration testing
means of compliance.
3.1.5 TAS—true airspeed (m/s, knots)
1.3 Units—The values given in this standard are in SI units
3.1.6 V—airspeed (m/s, knots)
and are to be regarded as standard. The values given in
3.1.7 V —design diving speed
D
parentheses are mathematical conversions to inch-pound (or
3.1.8 V —demonstrated flight diving speed
other) units that are provided for information only and are not
DF
considered standard. The values stated in each system may not
3.1.9 V —maximum speed in level flight with maximum
H
be exact equivalents. Where it may not be clear, some
continuous power (corrected for sea level standard conditions)
equations provide the units of the result directly following the
3.1.10 V —never exceed speed.
NE
equation. It is also noted that the internationally accepted units
3.1.11 V —stalling speed or minimum steady flight speed
S0
for altitude and airspeed are feet and knots, respectively. This
at which the aircraft is controllable in the landing configura-
is the only exception to standard SI units.
tion.
1.4 This standard does not purport to address all of the
safety concerns, if any, associated with its use. It is the
4. Flutter
responsibility of the user of this standard to establish appro-
4.1 It must be shown by the methods in 4.2, and either 4.3
priate safety, health, and environmental practices and deter-
or4.4,thattheairplaneisfreefromflutter,controlreversal,and
mine the applicability of regulatory limitations prior to use.
divergence for any condition of operation for all speeds from
1.5 This international standard was developed in accor-
V up to the speed specified for the selected method. In
S0
dance with internationally recognized principles on standard-
addition:
ization established in the Decision on Principles for the
NOTE 1—Reference AC 23.629 and Aeroelastic Flutter Prevention in
Development of International Standards, Guides and Recom-
Gliders and Small Aircraft for additional guidance on flutter evaluation.
mendations issued by the World Trade Organization Technical
Barriers to Trade (TBT) Committee. 4.1.1 Adequate tolerances of at least 0.8 to 1.2 must be
established for quantities that affect flutter, including speed,
2. Referenced Documents
damping, mass balance, and control system stiffness.
4.1.2 Thenaturalfrequenciesofmainstructuralcomponents
2.1 FAA Documents:
Airframe and Equipment Engineering Report No. 45 (as must be determined by vibration tests or other approved
corrected) Simplified Flutter Prevention Criteria methods. This determination is not required for airplanes with
V up to 72 m⁄s (140 KCAS).
D
4.1.3 The requirements of this specification must also be
This specification is under the jurisdiction of ASTM Committee F37 on Light
met with zero fuel in the wings.
SportAircraft and is the direct responsibility of Subcommittee F37.20 on Airplane.
Current edition approved Dec. 1, 2022. Published February 2023. DOI: 10.1520/
F3619-22.
2 3
Available from Federal Aviation Administration (FAA), 800 Independence Stender, W., Kießling, F., Aeroelastic Flutter Prevention in Gliders and Small
Ave., SW, Washington, DC 20591, http://www.faa.gov. Aircraft, Wiss. Berichtswesen der DLR, Köln, 1990.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
F3619 − 22
4.2 Flight Fl
...