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This SAE Aerospace Recommended Practice (ARP) provides guidance and interpretation on how to apply the objectives and activities in ARP4754A, “Guidelines for Development of Civil Aircraft and Systems”, to propulsion systems with electronic engine control. As the ARP4754A was developed and written more generally at the aircraft level, guidance will be provided to allocate ARP4754A objectives and activities to each side of the aircraft/engine interface. Using this guidance, certification applicants (aircraft and engine manufacturers) will be able to make proposals to coordinate their activities with their respective authority based on this allocation with the objective of distributing efficiently the compliance demonstration efforts between engine and aircraft certification and of avoiding unnecessary duplication of work.

The E-36 committee is requested to develop a standard or recommended practice for Control System Fault Accommodation to provide guidance on the fault detection and accommodation strategies and robust validation toward certification to FAA Control System regulation 33.28. FAA has written an issue paper on this outlining the risks and vulnerabilities in fault detection/ accommodation based on industry/agency experience over many years; and suggested means of compliance in terms of tests, analyses, simulations. The E-36 is requested to factor in the issue paper and build on the guidance content into an SAE document for reference by the industry. In this endeavor, it is recommended that the SAE standard/ARP consider conventional gas turbine controls as well as emerging architectures such Hybrid and Electric Propulsion Systems.

The purpose of this SAE Aerospace Information Report (AIR) is to provide guidance for aircraft engine and propeller systems (hereafter referred to as propulsion systems) certification for cybersecurity. Compliance for cybersecurity requires that the engine control, propeller control, monitoring system, and all auxiliary equipment systems and networks associated with the propulsion system (such as nacelle systems, overspeed governors, and thrust reversers) be protected from intentional unauthorized electronic interactions (IUEI) that may result in an adverse effect on the safety of the propulsion system or the airplane. This involves identification of security risks, their mitigation, verification of protections, and their maintenance in service. This document is intended to serve as suitable guidance for propulsion system manufacturers and applicants for propulsion system type certification.

The purpose of this document is to provide reference material for establishing compatibility of electronic gas turbine engine control systems and associated components with the electromagnetic environment and achieving compliance with associated airworthiness requirements.

This report lists documents that aid and govern the design, development, and utilization of aerospace electronic engine control systems. The report lists the military and industry specifications and standards that are commonly used in electronic engine control system design. However, this list is not necessarily complete. The specifications and standards section has been divided into two parts; a master list arranged numerically and a categorized list that provides a functional breakdown and cross-reference of these documents. Current revisions for standards and specifications are not listed. For details of current revisions of many documents, including notices, amendments, and supplements, refer to the Department of Defense Index of Specifications and Standards (DODISS).

The purpose of this document is to provide reference material for establishing compatibility of electronic gas turbine engine control systems and associated components with the electromagnetic environment and achieving compliance with associated airworthiness requirements.

The purpose of this document is to provide reference material for establishing compatibility of electronic gas turbine engine control systems and associated components with the electromagnetic environment and achieving compliance with associated airworthiness requirements.

This document is intended for use by manufacturers of aircraft, engines and Electronic Engine Controls [EECs] as a component change process and evaluation guideline. Its purpose is to provide an effective means of managing the modification of electronic hardware. The process defined in this document is based upon: an understanding of the electronic component market evolution, e.g., obsolescence; lessons learned from the effects caused by the introduction of electrical component changes in a service fleet environment; industry best practice; and an understanding of the applicable regulations.

This report lists documents that aid and govern the design, development, certification, and utilization of aerospace electronic engine control systems. The report lists the military and industry specifications and standards that are commonly used in electronic engine control system design. Also included are Airworthiness Authority documents and requirements associated with certification. However, these lists are not necessarily complete. The specifications and standards section has been divided into two parts: a master list, and a categorized list that provides a functional breakdown and cross-reference of these documents. For specifications and standards, the issue available during the latest revision to this document is listed. Details of current revisions for many documents are available in the Department of Defense Index of Specifications and Standards (DODISS). It should be noted that not all of these documents are referenced or even recognized by all certification authorities.

This report lists documents that aid and govern the design, development, and utilization of aerospace electronic engine control systems. The report lists the military and industry specifications and standards that are commonly used in electronic engine control system design. However, this list is not necessarily complete. The specifications and standards section has been divided into two parts; a master list arranged numerically and a categorized list that provides a functional breakdown and cross-reference of these documents. For specifications and standards, the issue available during the latest revision to this document is listed. Details of current revisions for many documents are available in the Department of Defense Index of Specifications and Standards (DODISS).

This report lists documents that aid and govern the design, development, certification and utilization of aerospace electronic engine control systems. The report lists the military and industry specifications and standards that are commonly used in electronic engine control system design. Also included are Airworthiness Authority documents and requirements associated with certification. However, these lists are not necessarily complete. The specifications and standards section has been divided into two parts; a master list arranged numerically and a categorized list that provides a functional breakdown and cross-reference of these documents. For specifications and standards, the issue available during the latest revision to this document is listed. Details of current revisions for many documents are available in the Department of Defense Index of Specifications and Standards (DODISS).

This SAE Aerospace Information Report (AIR) provides guidelines to document the functional and physical interface requirements for the electrical systems (including an EPCS and its components) between a given propulsion system and the aircraft on which the system is installed and the functionality pertinent to each interface. The scope includes civilian aircraft powered by turbofan, turboprop, and turboshaft engines equipped with electronic engine controls.

This SAE Aerospace Information Report (AIR) provides technical information regarding Engine Control Systems Interdependencies strategies and/or functions. This concerns aircraft with multiple power sources: at least two engines, whatever the nature of the power source is (electrical motor or gas turbine engine). Within this document the aircraft stands for fixed-wing aircraft as well as rotorcraft. The term EECS or FADEC is used for the engine electronic control system, whereas the term EEC is used for the electronic unit itself. The scope includes civilian aircraft powered by turbofan, turboprop, turboshaft and electrical engines equipped with electronic engine controls. Military aircraft is taken into consideration, however restricted topics that change the operational behaviors are not discussed.

This paper presents guidelines for development of a procedure for external software loading of an electronic engine control (EEC) for a commercial application, on-wing or in a qualified service shop. This paper makes the following assumptions: a The EEC is designed to accept external software loading. b The EEC is certified as part of an engine. c The support equipment is qualified in accordance with procedures set forth by the engine (and aircraft, if necessary) certifying authority if the EEC cannot detect an integrity violation of the loaded program. d The software to be loaded has been approved by the engine and aircraft certifying authorities. e One or more configurations of EEC hardware has been identified for each version of software which is to be loaded in the EEC. It is appropriate to use these guidelines in the initial development phase, although the certification issues would not be applicable.

This paper presents guidelines for development of a procedure for external software loading of an electronic engine control(EEC)for a commercial application, on-wing or in a qualified service shop. This paper makes the following assumptions: a. The EEC is designed to accept external software loading. b. The EEC is certified as part of an engine. c. The support equipment is qualified in accordance with procedures set forth by the engine (and aircraft, if necessary) certifying authority if the EEC cannot detect an integrity violation of the loaded program. The software to be loaded has been approved by the engine and aircraft certifying authorities. One or more configurations of EEC hardware has been identified for each version of software which is to be loaded in the EEC. It is appropriate to use these guidelines in the initial development phase, although the certification issues would not be applicable.

This SAE Aerospace Recommended Practice (ARP) provides guidance for substantiating the airworthiness of aircraft engine components. Generally these components are associated with the engine control system, the system or systems that allow the engine to provide thrust or power as demanded by the pilot of the aircraft while also ensuring the engine operates within acceptable operating limits. But these components may also include hardware and systems associated with engine lubrication, engine or aircraft hydraulic or electrical systems, aircraft environmental control systems, thrust reverser control, or similar aircraft or engine propulsion system functions. This paper develops the concept of using a 26 item matrix of environmental conditions for evaluating aircraft engine component airworthiness. This approach is compatible with current practices used in the industry and has been accepted by engine certification authorities as part of engine certification programs.

This SAE Aerospace Recommended Practice (ARP) provides guidance for substantiating the airworthiness of aircraft engine components. Generally these components are associated with the engine control system, the system or systems that allow the engine to provide thrust or power as demanded by the pilot of the aircraft while also ensuring the engine operates within acceptable operating limits. But these components may also include hardware and systems associated with engine lubrication, engine or aircraft hydraulic or electrical systems, aircraft environmental control systems, thrust reverser control, or similar aircraft or engine propulsion system functions. This paper develops the concept of using a 26 item matrix of environmental conditions for evaluating aircraft engine component airworthiness. This approach is compatible with current practices used in the industry and has been accepted by engine certification authorities as part of engine certification programs.

This SAE Aerospace Recommended Practice (ARP) provides guidance for substantiating the airworthiness of aircraft engine components. Generally these components are associated with the engine control system, the system or systems that allow the engine to provide thrust or power as demanded by the pilot of the aircraft while also ensuring the engine operates within acceptable operating limits. But these components may also include hardware and systems associated with engine lubrication, engine or aircraft hydraulic or electrical systems, aircraft environmental control systems, thrust reverser control, or similar aircraft or engine propulsion system functions. This paper develops the concept of using a 26 item matrix of environmental conditions for evaluating aircraft engine component airworthiness. This approach is compatible with current practices used in the industry and has been accepted by engine certification authorities as part of engine certification programs.

This document establishes guidelines for a Reliability Assessment Plan (herein also called the Plan), in which Electronic Engine Control manufacturers document their controlled, repeatable processes for assessing reliability of their products. Each Electronic Engine Control manufacturer (the Plan owner) prepares a Plan, which is unique to the Plan owner. This document describes processes that are intended for use in assessing the reliability of Electronic Engine Controls, or subassemblies thereof. The results of such assessments are intended for use as inputs to safety analyses, certification analyses, equipment design decisions, system architecture selection and business decisions such as warranties or maintenance cost guarantees.

This SAE Aerospace Recommended Practice (ARP) provides methodologies and approaches which have been used for conducting and documenting the analyses associated with the application of Time Limited Dispatch (TLD) to the thrust control reliability of Full Authority Digital Engine Control (FADEC) systems. The TLD concept is one wherein a fault-tolerant system is allowed to operate for a predetermined length of time with faults present in the redundant elements of the system, before repairs are required. This document includes the background of the development of TLD, the structure of TLD that was developed and implemented on present generation commercial transports, and the analysis methods used to validate the application of TLD on present day FADEC equipped aircraft.