1.1 本规程为结构有限元模型（FEM）的验证和验证提供了指导，该模型用于支持符合民航局（CAA）法规的证明。这包括内部载荷、位移、应变、应力、稳定性和屈曲后载荷的FEM预测。 1.2 本规程适用于认证最大起飞重量为19的普通类飞机 000 磅（8618公斤）或以下，乘客座位配置最多可达19个。在本规范中使用“飞机”一词是为了让相关民航局在其确定合适的情况下接受该做法，将其作为其他飞机的合规手段。 1.3 FEM软件的代码验证不包括在本规程的范围内。然而，预计用于支持合规性展示的软件开发商已经应用了适当的软件质量保证和数字算法验证过程，包括基准案例，以验证解决方案的准确性和一致性。应记录和记录这些活动的证据，并应申请人和民航局的要求提供这些证据。 1.4 设计批准申请人应在使用CAA来支持合规性证明之前，验证CAA对该实践的接受程度。 有关民航局监管机构已接受本做法（全部或部分）作为符合适航标准的手段的信息:普通类飞机（以下简称“规则”），请参阅ASTM F44网页（www.ASTM.org/COMMITTEE/F44.htm），其中包括民航局网站链接。 1.5 以英寸磅为单位的数值应视为标准。括号中给出的值是国际单位制的数学转换，仅供参考，不被视为标准。 1.6 本标准并非旨在解决与其使用相关的所有安全问题（如有）。 本标准的使用者有责任在使用前制定适当的安全、健康和环境实践，并确定监管限制的适用性。 1.7 本国际标准是根据世界贸易组织技术性贸易壁垒委员会发布的《关于制定国际标准、指南和建议的原则的决定》中确立的国际公认的标准化原则制定的。 ====意义和用途====== 4.1 本规程为结构FEM的验证和验证提供了指导，用于支持符合CAA法规的证明。 4.2 此做法是规范的配套规范 第3114页 .

1.1 This practice provides guidance for verification and validation of structural finite element models (FEMs) that are used to support showings of compliance with Civil Aviation Authority (CAA) regulations. This encompasses FEM predictions of internal loads, displacements, strains, stresses, stability, and post-buckling loads. 1.2 This practice applies to normal category aeroplanes with a certified maximum take-off weight of 19 000 lb (8618 kg) or less and a passenger seating configuration of up to 19. Use of the term aircraft throughout this specification is intended to allow the relevant CAA(s) to accept this practice as a means of compliance for other aircraft as they determine appropriate. 1.3 Code verification for FEM software is not included in the scope of this practice. It is expected, however, that the developer of software that is used to support showings of compliance has applied appropriate software quality assurance and numerical algorithm verification processes, including benchmark cases, to verify the accuracy and consistency of the solutions. Evidence of these activities should be recorded and documented and made available to the applicant and CAA upon request. 1.4 The applicant for a design approval should verify CAA acceptance of this practice before using it to support showings of compliance. For information on which CAA regulatory bodies have accepted this practice (in whole or in part) as a means of compliance to airworthiness standards: normal category aeroplanes (hereinafter referred to as “the Rules”), refer to the ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm), which includes CAA website links. 1.5 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. 1.6 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. 1.7 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. ====== Significance And Use ====== 4.1 This practice provides guidance for verification and validation of structural FEMs that are used to support showings of compliance with CAA regulations. 4.2 This practice is a companion to Specification F3114 .