1.1 本规范提供了对飞机系统和设备进行系统级验证的过程。它提供了一种符合性方法，可用于具有传统开发保证方法未解决的软件和机载电子硬件（AEH）的系统和设备。 1.2 该过程可用于证明符合要求证明功能按预期实施的法规，包括解决软件故障条件和飞机系统和设备AEH方面的安全缓解措施。 1.3 虽然本规范的制定考虑到了安装在飞机认证等级1和2（或根据咨询通告（AC）23.1309-1的I和II级）正常类别飞机上的系统和设备，但其内容可能更广泛适用。 申请人有责任证明其作为具体合规手段的更广泛适用性，并获得适用民航局（CAA）的同意。 1.4 使用本规范时，适用于飞机的管理系统安全要求的法规仍然适用。为了遵守这些规定，除了本规范中规定的验证过程外，可能还需要额外的架构缓解措施，如冗余、独立性、分离、系统监视器等。 1.5 本规范预期的系统级验证活动随着适用于功能或受功能影响的故障条件的严重性增加而增加。这些具有危险和灾难性故障条件的功能通过该过程接受额外活动，以提供详细的审查。 对于普通类飞机，请参阅实践 F3309 实践 F3230 ，或AC 23.1309-1，以获取有关系统故障条件识别和分类的更多信息。应在项目早期讨论适用CAA人员或其指定人员参与该系统验证过程。 1.6 该验证过程特别涉及系统功能的定义、识别和验证。根据本规范进行的过程可能无法满足所有适用的外部要求；可能需要系统开发人员、集成商或安装人员进行额外审查，以满足特定要求或飞机的指定任务，或两者兼而有之。 1.7 以英寸-磅为单位的数值应视为标准值。本标准不包括其他计量单位。 1.8 本标准并非旨在解决与其使用相关的所有安全问题（如有）。本标准的用户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。 1.9 本国际标准是根据世界贸易组织技术性贸易壁垒（TBT）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》中确立的国际公认标准化原则制定的。

1.1 This specification provides a process for performing system level verification of aircraft systems and equipment. It provides a means of compliance that can be used for systems and equipment with software and Airborne Electronic Hardware (AEH) that have not been addressed by traditional development assurance methods. 1.2 This process can be used to show compliance to regulations that require a demonstration that functionality was implemented as intended, including safety mitigations that address failure conditions for software and AEH aspects for aircraft systems and equipment. 1.3 While this specification was developed with systems and equipment installed on aircraft certification level 1 and 2 (or class I and II in accordance with Advisory Circular (AC) 23.1309-1) normal category aeroplanes in mind, the content may be more broadly applicable. It is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance and obtain concurrence for its use from the applicable Civil Aviation Authority (CAA). 1.4 When using this specification, regulations that govern system safety requirements applicable to the aircraft still apply. In complying with those regulations, additional architectural mitigations such as redundancy, independence, separation, system monitors, etc., may be required in addition to the verification process specified in this specification. 1.5 The system level verification activities expected by this specification increase as the severity of the failure conditions applicable to or affected by the function increase. Those functions, which have hazardous and catastrophic failure conditions, receive additional activities through this process to provide detailed scrutiny. For normal category aircraft, refer to Practice F3309 , Practice F3230 , or AC 23.1309-1 for more information on the identification and classification of system failure conditions. Involvement of the applicable CAA personnel or their designees in this system verification process should be discussed early in the project. 1.6 This verification process specifically addresses definition, identification, and verification of system functions. Processes conducted under this specification may not satisfy all applicable external requirements; additional review on the part of the system developer, integrator, or installer may be required to meet specific requirements or the specified mission of the aircraft, or both. 1.7 The values stated in inch-pound units are to be regarded as standard. No other units of measurement are included in this standard. 1.8 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. 1.9 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.