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ASTM F3498-21

(Practice)

Standard Practice for Developing Simplified Fatigue Load Spectra

Standard Practice for Developing Simplified Fatigue Load Spectra

SIGNIFICANCE AND USE
4.1 This standard practice provides one means for determining fatigue load spectra for aeroplane durability assessments. This information can be used in conjunction with Specification F3115/F3115M, Section 5, Load Considerations.  
4.1.1 Users of this practice may propose alternate spectra, subject to the approval of their CAA.  
4.2 The methods are applicable to the durability evaluation of wings of small aeroplanes. Additional calculation (such as methods noted in ACE-100-01) are needed to properly develop load spectra for fatigue evaluation of empennage and/or configurations with canards (or forward wings) and/or winglets (or tip fins), fuselage, and potentially other components, with approval from appropriate regulatory agency.  
4.3 Much of the material presented herein is directly taken from AC 23-13A. The FAA developed the flight load spectra, presented herein, based on a statistical analysis of the data presented in DOT/FAA/CT-91/20. The ground load spectra are directly from AFS-120-73-2.  
4.4 The flight load spectra, presented in Section 7, includes an adjustment (1.5 standard deviations) to the average measured load frequency. The adjustment accounts for the variability in the loading spectra experienced by individual aeroplanes, as well as across aeroplane types. The magnitude of the adjustment was selected to maintain the probability that a component will reach its safe-life without a detectable fatigue crack established by scatter factor (see paragraph 2–15 of AC 23-13A).
SCOPE
1.1 This practice provides data to develop simplified loading spectra that can be used to perform structural durability analysis for aeroplanes, specifically for wings of small aeroplanes. The material was developed through open consensus of international experts in general aviation. The 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.  
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 civil aviation authorities, or CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (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 The values stated in inch-pound units are to be regarded as standard. No other units of measurement are included in this standard.  
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
Published
Publication Date
31-Dec-2020
ICS
49.035 - Components for aerospace construction
Technical Committee
F44 - General Aviation Aircraft
Drafting Committee
F44.30 - Structures
Current Stage
Ref Project

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ASTM F3498-21 - Standard Practice for Developing Simplified Fatigue Load Spectra
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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: F3498 −21
Standard Practice for
1
Developing Simplified Fatigue Load Spectra
This standard is issued under the fixed designation F3498; 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 practice provides data to develop simplified load- 2.1 ASTM Standards:
ing spectra that can be used to perform structural durability E1049 Practices for Cycle Counting in Fatigue Analysis
analysis for aeroplanes, specifically for wings of small aero- F3060 Terminology for Aircraft
planes.The material was developed through open consensus of F3115/F3115M Specification for Structural Durability for
international experts in general aviation. The information was Small Aeroplanes
3
created by focusing on Level 1, 2, 3, and 4 Normal Category
2.2 EASA Standard:
aeroplanes. The content may be more broadly applicable; it is
CS-23 Normal, Utility,Aerobatic and CommuterAeroplanes
the responsibility of the applicant to substantiate broader
2.3 FAA Documents:
applicability as a specific means of compliance.
14 CFR 23 Airworthiness Standards: Normal, Utility,
4
Acrobatic, and Commuter Category Airplanes
1.2 An applicant intending to propose this information as
AC 23-13A Fatigue, Fail-Safe, and Damage Tolerance
Means of Compliance for a design approval must seek guid-
Evaluation of Metallic Structure for Normal, Utility,
ance from their respective oversight authority (for example,
5
Acrobatic, and Commuter Category Airplanes
published guidance from applicable civil aviation authorities,
ACE-100-01 Fatigue Evaluation of Empennage, Forward
or CAAs) concerning the acceptable use and application
6
Wing and Winglets/Tips Fins on Part 23 Airplanes
thereof. For information on which oversight authorities have
Report No. AFS-120-73-2 Fatigue Evaluation of Wing and
accepted this standard (whole or in part) as an acceptable
7
Associated Structure on Small Airplanes
Means of Compliance to their regulatory requirements (here-
DOT/FAA/AR-96/46 User’s Guide for FAR23 Loads Pro-
inafter “the Rules”), refer to the ASTM Committee F44 web
6
gram
page (www.astm.org/COMMITTEE/F44.htm).
DOT/FAA/CT-91/20 General Aviation Aircraft – Normal
1.3 The values stated in inch-pound units are to be regarded
6
Acceleration Data Analysis and Collection Project
as standard. No other units of measurement are included in this
standard.
3. Terminology
1.4 This standard does not purport to address all of the
3.1 The following are a selection of terms relevant to this
safety concerns, if any, associated with its use. It is the
practice. See Terminology F3060 for more definitions and
responsibility of the user of this standard to establish appro-
abbreviations.
priate safety, health, and environmental practices and deter-
mine the applicability of regulatory limitations prior to use.
1.5 This international standard was developed in accor-
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
dance with internationally recognized principles on standard-
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
Standards volume information, refer to the standard’s Document Summary page on
ization established in the Decision on Principles for the
the ASTM website.
Development of International Standards, Guides and Recom-
3
Available from European Aviation Safety Agency (EASA), Konrad-Adenauer-
mendations issued by the World Trade Organization Technical
Ufer 3, D-50668 Cologne, Germany, https://www.easa.europa.eu/.
4
Barriers to Trade (TBT) Committee. Available from Federal Aviation Administration (FAA), 800 Independence
Ave., SW, Washington, DC 20591, http://www.faa.gov.
5
Available from U.S. Government Publishing Office (GPO), 732 N. Capitol St.,
1
This practice is under the jurisdiction of ASTM Committee F44 on General NW, Washington, DC 20401, http://www.gpo.gov.
6
Aviation Aircraft and is the direct responsibility of Subcommittee F44.30 on Available from National Technical Information Service (NTIS), 5301 Shawnee
Structures. Rd., Alexandria, VA 22312, http://www.ntis.gov.
7
Current edition approved Jan. 1, 2021. Published February 2021. DOI: 10.1520/ Available from Clearinghouse for Federal Scientific andTechnical Information,
F3498-21. Springfield, VA 22151.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

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SIGNIFICANCE AND USE
5.1 Transparent parts, such as aircraft windshields, canopies, cabin windows, and visors, shall be measured for compliance with optical distortion specifications using this test method. This test method is suitable for assessing optical distortion of transparent parts as it relates to the visual perception of distortion. It is not suitable for assessing distortion as it relates to pure angular deviation of light as it passes through the part. Either Test Method F801 or Practice F733 is appropriate and shall be used for this latter application. This test method is not recommended for raw material.
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SIGNIFICANCE AND USE
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ABSTRACT
This test method covers the determination of non-volatile matter, that is, residue on evaporation, in solvent extract from aerospace components, using a rotary flash evaporator. The summary of the test method, the apparatus for testing, reagents and materials for testing, and procedure for testing are all presented in details.
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ASTM
ASTM A370-23(Test Method)
Standard Test Methods and Definitions for Mechanical Testing of Steel Products

SIGNIFICANCE AND USE
4.1 The primary use of these test methods is testing to determine the specified mechanical properties of steel, stainless steel, and related alloy products for the evaluation of conformance of such products to a material specification under the jurisdiction of ASTM Committee A01 and its subcommittees as designated by a purchaser in a purchase order or contract.  
4.1.1 These test methods may be and are used by other ASTM Committees and other standards writing bodies for the purpose of conformance testing.  
4.1.2 The material condition at the time of testing, sampling frequency, specimen location and orientation, reporting requirements, and other test parameters are contained in the pertinent material specification or in a general requirement specification for the particular product form.  
4.1.3 Some material specifications require the use of additional test methods not described herein; in such cases, the required test method is described in that material specification or by reference to another appropriate test method standard.  
4.2 These test methods are also suitable to be used for testing of steel, stainless steel and related alloy materials for other purposes, such as incoming material acceptance testing by the purchaser or evaluation of components after service exposure.  
4.2.1 As with any mechanical testing, deviations from either specification limits or expected as-manufactured properties can occur for valid reasons besides deficiency of the original as-fabricated product. These reasons include, but are not limited to: subsequent service degradation from environmental exposure (for example, temperature, corrosion); static or cyclic service stress effects, mechanically-induced damage, material inhomogeneity, anisotropic structure, natural aging of select alloys, further processing not included in the specification, sampling limitations, and measuring equipment calibration uncertainty. There is statistical variation in all aspects of mechanical testin...
SCOPE
1.1 These test methods2 cover procedures and definitions for the mechanical testing of steels, stainless steels, and related alloys. The various mechanical tests herein described are used to determine properties required in the product specifications. Variations in testing methods are to be avoided, and standard methods of testing are to be followed to obtain reproducible and comparable results. In those cases in which the testing requirements for certain products are unique or at variance with these general procedures, the product specification testing requirements shall control.  
1.2 The following mechanical tests are described:    
Sections  
Tension  
7 to 14  
Bend  
15  
Hardness  
16  
Brinell  
17  
Rockwell  
18  
Portable  
19  
Impact  
20 to 30  
Keywords  
32  
1.3 Annexes covering details peculiar to certain products are appended to these test methods as follows:    
Annex  
Bar Products  
Annex A1  
Tubular Products  
Annex A2  
Fasteners  
Annex A3  
Round Wire Products  
Annex A4  
Significance of Notched-Bar Impact Testing  
Annex A5  
Converting Percentage Elongation of Round Specimens to
Equivalents for Flat Specimens  
Annex A6    
Testing Multi-Wire Strand  
Annex A7  
Rounding of Test Data  
Annex A8  
Methods for Testing Steel Reinforcing Bars  
Annex A9  
Procedure for Use and Control of Heat-cycle Simulation  
Annex A10  
1.4 The values stated in inch-pound units are to be regarded as standard. The values given in parentheses are mathematical conversions to SI units that are provided for information only and are not considered standard.  
1.5 When these test methods are referenced in a metric product specification, the yield and tensile values may be determined in inch-pound (ksi) units then converted into SI (MPa) units. The elongation determined in inch-pound gauge lengths of 2 in. or 8 in. may be report...

  • Standard
    51 pages
    English language
    sale 15% off
  • Standard
    51 pages
    English language
    sale 15% off