电子推进控制系统/飞机接口控制文件

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.Cross Reference: EASAAMC20-1