本SAE航空航天信息报告（AIR）提供了记录给定推进系统和安装该系统的飞机之间电气系统（包括电子发动机控制系统（EECS）及其组件）的功能和物理接口要求的指南。 接口控制文件（ICD）被认为是发动机安装手册的一个子集，考虑了机身制造商和发动机制造商之间的接口。虽然它可以与机身制造商和发动机制造商同时开发，但其格式和内容是发动机和飞机型号证书持有者之间使用认证指南达成的协议的结果。 在本文件中，以下定义改编自AC33.28-1和CS-定义: “发动机控制系统”是指作为发动机类型设计的一部分的任何系统或装置，其控制、限制或监测发动机运行并且是发动机持续适航所必需的。 “电子发动机控制系统”(EECS)是指其中使用电子器件提供主要功能的发动机控制系统。它包括控制发动机所必需的所有部件（即电气、电子、液压机械和气动），并且可以在需要时结合其他控制功能。 术语“EEC”用于指代电子发动机控制单元。术语“飞行器”与飞行器或旋翼飞行器的全局含义一起使用。 范围包括由活塞、涡轮风扇、涡轮螺旋桨和涡轮轴发动机提供动力并配备电子发动机控制装置的商用和通用航空飞机。它还可以适用于配备有电子控制装置的辅助动力单元(APU)。

This SAE Aerospace Information Report (AIR) provides guidelines to document the functional and physical interface requirements for the electrical systems (including an Electronic Engine Control System (EECS) and its components) between a given propulsion system and the aircraft on which the system is installed. The Interface Control Document (ICD) is considered to be a subset of the Engine Installation Manual, with interface considerations between the Airframer and Engine manufacturer. Although it can be developed concurrently with the Airframer and Engine manufacturer, its format and content result from an agreement between the Engine and Aircraft Type Certificate Holders, using the Certification Guidelines. Within this document, the following definitions are adapted from the AC33.28-1 and CS-Definitions: “Engine Control System” means any system or device which is part of the Engine Type design, which controls, limits, or monitors Engine operation and is necessary for continued airworthiness of the Engine. “Electronic Engine Control System” (EECS) means an Engine Control System in which the primary functions are provided using electronics. It includes all the components (i.e., electrical, electronic, hydro-mechanical and pneumatic) which are necessary for the control of the Engine and may incorporate other control functions where desired. The term “EEC” is used to refer to the Electronic Engine Control unit. The term “aircraft” is used with the global meaning of aircraft or rotorcraft. The scope includes commercial and general aviation aircraft powered by piston, turbofan, turboprop, and turboshaft engines equipped with electronic engine controls. It can also be applicable to an Auxiliary Power Unit (APU) equipped with an electronic control.