ASTM F3093/F3093M-20

Standard Specification for Aeroelasticity Requirements

SCOPE
1.1 This specification covers the aeroelasticity requirements of the aeroplane. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Level 1, 2, 3, and 4 Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this document are: 2. Referenced Documents, 3. Terminology, 4. Flutter.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This document may present information in either SI units, English Engineering units, or both. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
1.4 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, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.5 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.

General Information

• Status: Historical
• Publication Date: 29-Feb-2020
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: F44 - General Aviation Aircraft
• Drafting Committee: F44.30 - Structures

Standards Content (Sample)

NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Contact ASTM International (www.astm.org) for the latest information
Designation: F3093/F3093M −20
Standard Specification for
1
Aeroelasticity Requirements
This standard is issued under the fixed designation F3093/F3093M; 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 2. Referenced Documents
2
1.1 This specification covers the aeroelasticity requirements 2.1 ASTM Standards:
of the aeroplane. The material was developed through open F3061/F3061M Specification for Systems and Equipment in
consensus of international experts in general aviation. This Small Aircraft
information was created by focusing on Level 1, 2, 3, and 4 F3115/F3115M Specification for Structural Durability for
Normal Category aeroplanes. The content may be more Small Aeroplanes
broadly applicable; it is the responsibility of the Applicant to F3120/F3120M Specification for Ice Protection for General
substantiate broader applicability as a specific means of com- Aviation Aircraft
3
pliance. The topics covered within this document are: 2. 2.2 Federal Aviation Administration (FAA) Document:
Referenced Documents, 3. Terminology, 4. Flutter. Airframe and Equipment Engineering Report No. 45 (as
corrected) “Simplified Flutter Prevention Criteria” 1955
1.2 An applicant intending to propose this information as
Means of Compliance for a design approval must seek guid-
3. Terminology
ance from their respective oversight authority (for example,
3.1 Definitions:
published guidance from applicable CAAs) concerning the
3.1.1 GVT—ground vibration testing
acceptable use and application thereof. For information on
which oversight authorities have accepted this standard (in 3.1.2 V-n—velocity versus load factor
whole or in part) as an acceptable Means of Compliance to
4. Flutter
their regulatory requirements (hereinafter “the Rules”), refer to
the ASTM Committee F44 web page (www.astm.org/ 4.1 It must be shown by the methods in 4.2, and either 4.3
COMMITTEE/F44.htm). or 4.4, that the aeroplane is free from flutter, control reversal,
and divergence for any condition of operation within the limit
1.3 Units—Thisdocumentmaypresentinformationineither
V-n envelope and at all speeds up to the speed specified for the
SI units, English Engineering units, or both. The values stated
selected method. In addition:
in each system are not necessarily exact equivalents; therefore,
4.1.1 Adequate tolerances must be established for quantities
to ensure conformance with the standard, each system shall be
which affect flutter, including speed, damping, mass balance,
used independently of the other, and values from the two
and control system stiffness; and
systems shall not be combined.
4.1.2 The natural frequencies of main structural components
1.4 This standard does not purport to address all of the
must be determined by vibration tests or other approved
safety concerns, if any, associated with its use. It is the
methods. This determination is not required for Level 1
responsibility of the user of this standard to establish appro-
aeroplanes with V up to 260 kph [140 knots] CAS and
D
priate safety, health, and environmental practices and deter-
maximum gross weight up to 750 kg [1650 lbm].
mine the applicability of regulatory limitations prior to use.
4.2 Flight flutter tests must be made to show that the
1.5 This international standard was developed in accor-
aeroplane is free from flutter, control reversal, and divergence,
dance with internationally recognized principles on standard-
and to show that:
ization established in the Decision on Principles for the
4.2.1 Proper and adequate attempts to induce flutter have
Development of International Standards, Guides and Recom-
been made within the speed range up to V /M (or V /M
D D DF DF
mendations issued by the World Trade Organization Technical
for jets);
Barriers to Trade (TBT) Committee.
1 2
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral For referenced ASTM standards, visit the ASTM website, www.astm.org, or
Aviation Aircraft and is the direct responsibility of Subcommittee F44.30 on contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
Structures. Standards volume information, refer to the standard’s Document Summary page on
Current edition approved March 1, 2020. Published March 2020. Originally the ASTM website.
3
approved in 2015. Last previous edition approved in 2019 as F3093/F3093M–19. Available from Federal Aviation Administration (FAA), 800 Independence
DOI: 10.1520/F3093_F3093M–20. Ave., SW, Washington, DC 20591, http://www.faa.gov.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United St
...

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. Because
it may not be technically possible to adequately depict all changes accurately, ASTM recommends that users consult prior editions as appropriate. In all cases only the current version
of the standard as published by ASTM is to be considered the official document.
Designation: F3093/F3093M − 19 F3093/F3093M − 20
Standard Specification for
1
Aeroelasticity Requirements
This standard is issued under the fixed designation F3093/F3093M; 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
1.1 This specification covers the aeroelasticity requirements of the aeroplane. The material was developed through open
consensus of international experts in general aviation. This information was created by focusing on Level 1, 2, 3, and 4 Normal
Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader
applicability as a specific means of compliance. The topics covered within this document are: 2. Referenced Documents, 3.
Terminology, 4. Flutter.
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from
their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and
application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an
acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web
page (www.astm.org/COMMITTEE/F44.htm).
1.3 Units—This document may present information in either SI units, English Engineering units, or both. The values stated in
each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used
independently of the other, and values from the two systems shall not be combined.
1.4 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, health, and environmental practices and determine the applicability of
regulatory limitations prior to use.
1.5 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.
2. Referenced Documents
2
2.1 ASTM Standards:
F3061/F3061M Specification for Systems and Equipment in Small Aircraft
F3065/F3065M Specification for Aircraft Propeller System Installation
F3115/F3115M Specification for Structural Durability for Small Aeroplanes
F3120/F3120M Specification for Ice Protection for General Aviation Aircraft
3
2.2 Federal Aviation Administration (FAA) Document:
Airframe and Equipment Engineering Report No. 45 (as corrected) “Simplified Flutter Prevention Criteria” 1955
4
2.3 Federal Aviation Regulations:
14 CFR 23 Amendment 62
3. Terminology
3.1 Definitions:
3.1.1 GVT—ground vibration testing
3.1.2 V-n—velocity versus load factor
1
This specification is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsibility of Subcommittee F44.30 on Structures.
Current edition approved Feb. 15, 2019March 1, 2020. Published March 2019March 2020. Originally approved in 2015. Last previous edition approved in 20152019 as
F3093/F3093M–15.–19. DOI: 10.1520/F3093_F3093M–19.10.1520/F3093_F3093M–20.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM Standards
volume information, refer to the standard’s Document Summary page on the ASTM website.
3
Available from Federal Aviation Administration (FAA), 800 Independence Ave., SW, Washington, DC 20591, http://www.faa.gov.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

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F3093/F3093M − 20
4. Flutter
4.1 It must be shown by the methods in 4.2, and either 4.3 or 4.4, that the aeroplane is free from flutter, control reversal, and
divergence for any condition of operation within the limit V-n envelope and at all speeds up to the speed specified for the selected
method. In addition:
4.1.1 Adequate tolerances must be established for quantities which affect flutter, including speed, damping, mass balance, and
cont
...