本SAE航空航天推荐规程（ARP）为飞机和 系统 ，考虑到飞机 功能 和操作环境。它提供了确保 安全 整体飞机设计，表明符合法规，并协助公司制定和满足自己的内部标准。这些做法包括 验证 的 要求 和 验证 安全的设计实施， 认证 ，和产品 保证 . The 指导原则 本文件是在美国的背景下开发的。联邦法规（14 CFR）第25部分第14篇和欧盟航空安全局（EASA）认证规范（CS）CS-25。它们可能适用于其他法规，如14 CFR第23、27、29、33和35部分以及CS-23、CS-27、CS-29、CS-E和CS-P。 本文件涉及飞机和实现飞机和系统功能的系统的开发周期。它不包括以下主题和参考文献的详细信息: 软件 发展；参见RTCA DO-178C/EUROCAE ED-12C。 电子的 硬件 发展；参见RTCA DO-254/EUROCAE ED-80。 集成模块化航空电子设备开发；参见RTCA DO-297/EUROCAE ED-124。 适航安全 过程 ;参见RTCA DO-326A/EUROCAE ED-202A。 安全 评估 过程；参见ARP4761A/EUROCAE ED-135。 ARP5150A和ARP5151A或其他文件（如 指导 当适用法规要求时，EASA第21部分（GM21）的材料。在本文件中，凡提及ARP5150A/ARP5151A，读者应理解这也意味着EASA第21部分（GM21）。主最低设备清单（MMEL）或配置偏差清单（CDL）开发；请参阅适用的法规指南 认证机构 . 飞机结构和空气动力学发展。 图1 概述了各种开发文档之间的关系，这些文档为安全评估、电子硬件和软件生命周期过程以及本文所述的系统开发过程提供了指南。

This SAE Aerospace Recommended Practice (ARP) provides recommendations for the development of aircraft and systems , taking into account aircraft functions and operating environment. It provides practices for ensuring the safety of the overall aircraft design, showing compliance with regulations, and assisting a company in developing and meeting its own internal standards. These practices include validation of requirements and verification of the design implementation for safety, certification , and product assurance . The guidelines in this document were developed in the context of U.S. Title 14 Code of Federal Regulations (14 CFR) Part 25 and European Union Aviation Safety Agency (EASA) Certification Specification (CS) CS-25. They may be applicable in the context of other regulations, such as 14 CFR Parts 23, 27, 29, 33, and 35, and CS-23, CS-27, CS-29, CS-E, and CS-P. This document addresses the development cycle for aircraft and systems that implement aircraft and system functions. It does not include detailed information on the following subjects and references: Software development; refer to RTCA DO-178C/EUROCAE ED-12C. Electronic hardware development; refer to RTCA DO-254/EUROCAE ED-80. Integrated modular avionics development; refer to RTCA DO-297/EUROCAE ED-124. Airworthiness security process ; refer to RTCA DO-326A/EUROCAE ED-202A. Safety assessment processes; refer to ARP4761A/EUROCAE ED-135. A process for accomplishing in-service safety assessment is described in ARP5150A and ARP5151A or in other documents such as the guidance material of EASA Part 21 (GM21) when required by applicable regulation. In this document, wherever references to ARP5150A/ARP5151A are made, the reader should understand this also implies EASA Part 21 (GM21). Master Minimum Equipment List (MMEL) or Configuration Deviation List (CDL) development; refer to applicable regulatory guidance from the applicable Certification Authority . Aircraft structure and aerodynamics development. Figure 1 outlines the relationships between the various development documents, which provide guidelines for safety assessment, electronic hardware and software life cycle processes, and the system development process described herein.