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This activity is focused on more electric and all electric type power systems for air vehicles. The scope of which includes source, distribution and user contributions to electrical power quality, failure modes, coordination, system reliabilty and robustness, impacts of being flight critical and the gaps which exist in present standards and guidance documents.

AS 6413 and slash sheets /1 & /2 hold the main information for testing of battery packaging. This document holds further information and expansion of philosophy, clarification etc. surrounding the testing and industry needs.

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 SAE Aerospace Information Report is intended to provide advanced methods for wire selecting and sizing in aerospace application as a continuation of AIR6540, Fundamentals in Wire Selection and Sizing for Aerospace Applications. Also, it will provide valuable information for the electrical design engineer to verify the proper wire selection and validate a set of system design requirements which includes meeting environmental and installation constraints.

EPS stability is an essential property that defines EPS ability to provide secure operation under required range of operation scenario. Power system stability is defined as “the ability of an electric power system, for a given initial operating condition, to regain a state of operating equilibrium after being subjected to a physical disturbance, with most system variables bounded so that practically the entire system remains intact”. This is applicable for AC and DC systems and has to address steady state conditions, transient conditions as well as high power loads connection / disconnection on the network.

This standard is intended to demonstrate and document the control of the potential hazards from lithium cells or batteries (UN 3090 and 3480) when transported as cargo on aircraft. [still need to identify if we are addressing global (external fire) or local (battery internal failures)] This standard addresses the need to control the hazards which might arise from a failure from an individual cell by containing the hazards within the package. This specific hazards addressed within this standard are: • Uncontrolled fire • Rapid overpressure pulse within compartment

This category specification provides a minimum performance standard that may be used for mitigation means, in addition to the foundation specification (AS6413), to provide external fire thermal threat capability which supports the safe shipment of lithium batteries as cargo on aircraft. This slash sheet provides information and testing to assist or augment the performance of the packaging used for shipping of lithium batteries. If protective equipment and measures are used, the performance of the battery package under the challenge of external heat and fire may be improved and enhanced.  

This category specification provides a minimum performance standard that may be used for mitigation means, in addition to the foundation specification (AS6413), to provide external fire thermal threat capability which supports the safe shipment of lithium batteries as cargo on aircraft. This slash sheet provides information and testing to assist or augment the performance of the packaging used for shipping of lithium batteries. If protective equipment and measures are used, the performance of the battery package under the challenge of external heat and fire may be improved and enhanced.  

The need for developing this standard is driven by the quickly evolving field of electrified propulsion for aircraft. Industry is moving forward in development of a broad range of high voltage primary power systems. There is an immediate need to standardize power quality requirements for design, analysis, verification, and testing for these types of systems.

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.

Technical requirements especially related to the design and construction and the minimum performance requirements (including qualification test conditions) for PM motors and power converters (operated as VFDs) used as the prime mover for more-electric, hybrid-electric, and fully-electric aircraft propulsion systems.

This AIR intends to better document and tabulate electrical load dynamics that influence power source capacity, power quality and stabiltiy.

To determine the end-of-life criteria of electrical insulation materials and components and predict insulation life in high voltage aviation applications

To provide test guidelines, recommendations and referenced standards for insulation materials in a high energy system especially at high voltages (AC, DC and PWM) and at high altitudes, in the purpose of defining/measuring the effects of insulation ageing.

This SAE Aerospace Information Report (AIR) presents descriptions of several types of industrial and marine gas turbine engine starting systems.

This publication formalizes the applicable design concepts considered acceptable for "draw-through" cooling of electronic (avionic) equipment installed in subsonic and supersonic commercial jet transports. Methods other than draw-through cooling are covered in AIR 728A for high Mach number aircraft.