ASTM F3115/F3115M-23 PDF
Standard Specification for Structural Durability for Small Aeroplanes
Standard Specification for Structural Durability for Small Aeroplanes
- Статус документа:
- Действующий
- Формат:
- Электронный (PDF)
- Количество страниц:
- 6
- Дата публикации:
- 1 января 2023 г.
- Издание:
- F3115/F3115M
- ICS:
- 49.020
ABSTRACT This specification is concerned with the airworthiness requirements related to structural durability for the design of small airplanes. The applicant for a design approval must seek individual guidance from their respective civil aviation authority (CAA) body regarding the use of this specification as part of a certification plan. This specification covers metallic structures such as pressurized cabin structures and wing, empennage, and associated structures that must be able to withstand the repeated loads of variable magnitude expected in service. These structures, as well as composite and bonded structures, must also conform to specified requirements for fatigue strength, fail safe strength, damage tolerance, and residual strength. SCOPE 1.1 This specification addresses the airworthiness requirements related to structural durability for the design of small aeroplanes. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Levels 1 through 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 (CAAs), including the guidance noted in Appendix X2, Guidance Material) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this specification (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm). Annex A1 maps the Means of Compliance of the ASTM standards to EASA CS-23, amendment 5, or later, and FAA 14 CFR 23, amendment 64, or later, Structural Durability requirements of 23.2240. 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.
Abstract
Overview
ASTM F3115/F3115M-23: Standard Specification for Structural Durability for Small Aeroplanes sets forth airworthiness requirements related to structural durability in the design of small airplanes. Developed through the consensus of global experts in general aviation, this specification provides criteria for ensuring the structural integrity and safety of small aircraft, particularly in Levels 1 through 4 Normal Category aeroplanes. The standard covers both metallic and composite structures and addresses critical aspects such as fatigue strength, fail safe strength, damage tolerance, and residual strength. Its application is recognized by various civil aviation authorities, including alignment to EASA CS-23 and FAA 14 CFR 23 standards.
Key Topics
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Structural Durability Requirements: The specification details the factors necessary to ensure that aircraft structures can withstand repeated service loads throughout their operational life without failure.
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Fatigue and Damage Tolerance: Key provisions require that both metallic and composite aircraft structures undergo rigorous analysis and testing to demonstrate resistance to fatigue, maintain fail safe integrity, and demonstrate damage tolerance.
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Residual Strength: Criteria ensure that even after sustaining detectable damage from fatigue, corrosion, or impact, structures possess sufficient residual strength to prevent catastrophic failure before maintenance can occur.
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Evaluation Methods:
- Fatigue strength evaluation via testing or analysis supported by test data.
- Fail safe strength evaluation to prevent loss of strength following failure of a principal element.
- Damage tolerance evaluation to demonstrate structure retains required strength after certain levels of damage.
-
Inspection and Maintenance Intervals: The standard incorporates guidance on defining inspection intervals and maintenance procedures necessary for continued airworthiness, tailored to analytical results and operational profiles.
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Composite and Bonded Structures: Additional requirements address the unique behavior and manufacturing considerations of composite materials, including joint integrity and long-term durability.
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Alignment with Regulatory Requirements: The specification includes annexes that map requirements directly to FAA (14 CFR 23.2240) and EASA (CS-23) regulations.
Applications
Practical applications of ASTM F3115/F3115M-23 include:
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Aircraft Type Certification: Designers and manufacturers use this standard as a means of compliance within the certification planning for small aeroplanes, ensuring their products meet global airworthiness requirements.
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Structural Engineering and Design: Aircraft structural engineers utilize the standard’s methodology to optimize airframe designs for durability, safety, and maintenance.
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Maintenance Planning: Operators and maintenance organizations reference the inspection intervals and durability requirements to establish effective maintenance schedules for continued airworthiness.
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Regulatory Submittals: Entities aiming to gain approval for new aircraft designs submit compliance to this standard as part of their certification documentation to civil aviation authorities.
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Safety Enhancements: The standard is essential for minimizing risks of catastrophic structural failure, contributing to higher safety and performance of both legacy and new small aircraft.
Related Standards
ASTM F3115/F3115M-23 is closely related to the following standards and regulations:
- ASTM F3060: Terminology for Aircraft
- ASTM F3066/F3066M: Aircraft Powerplant Installation Hazard Mitigation
- ASTM F3116/F3116M: Specification for Design Loads and Conditions
- ASTM F3174/F3174M: Specification for Establishing Operating Limitations and Information for Aeroplanes
- ASTM F3380: Practice for Structural Compliance of Very Light Aeroplanes
- FAA: 14 CFR 23, Amendment 64 - Airworthiness Standards: Normal Category Airplanes
- EASA: CS-23, Amendment 5 - Certification Specifications for Normal Category Aeroplanes
Keywords: small aeroplane, structural durability, airworthiness, fatigue strength, damage tolerance, fail safe, composite structure, metallic structure, continued airworthiness, ASTM F3115/F3115M-23.
Технические детали
- Технический комитет
- F44 - General Aviation Aircraft
- SKU
- ASTM F3115/F3115M-23
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