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This specification covers all-metal, self-locking nuts, plate nuts, and gang channel nuts made of a carbon or low-alloy steel.

This specification covers all-metal, self-locking, prevailing-torque nuts, plate nuts, and gang channel nuts made of a carbon or low-alloy steel.

This SAE Standard provides performance and general design requirements and related test procedures for a combination tail and floodlamp for use on industrial wheeled equipment that may be operated on public roads.

No scope available.

This SAE Aerospace Recommended Practice (ARP) provides guidance to develop and assure validation and verification of IVHM systems used in autonomous aircraft, vehicles and driver assistance functions. IVHM covers a vehicle, monitoring and data processing functions inherent within its sub-systems, and the tools and processes used to manage and restore the vehicle’s health. The scope of this document is to address challenges and identify recommendations for the application of integrated vehicle health management (IVHM) specifically to intelligent systems performing tasks autonomously within the mobility sector. This document will focus on the core aspects of IVHM for autonomous vehicles that are common to both aerospace and automotive applications. It is anticipated that additional documents will be developed separately to cover aspects of this functionality that are unique to each application domain.

The scope of this document is to provide a guidance of the common contamination types and their concentrations in order to size FTIS components and characterize its performance on generic commercial aircraft.

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.

This information report is useful for personnel involved in the design, manufacturing, and/or use of digital fiber optic transmitters, receivers, and transceivers for aerospace applications

The purpose of this AIR is to provide a comprehensive description document that displays various examples of low pressure seals and wipers utilized within mechanical and electromechanical actuators. The document is intended as an overview for those specifying or designing actuators in order to compare existing solutions as reference for implementation.

The proposed AIR will detail power levels required for future electric aircraft applications and detail design considerations and use cases for megawatt and extreme fast charging for electric aircraft. The AIR will provide a mapping to other industry standard that may be have relevance as well as detail areas where technology gaps / future design considerations will need to be addressed.

A single depository for fiber optic and applied photonic definitions.

This Aerospace Informational Report (AIR) provides guidance on using environmental, electrochemical, and electrical resistance measurements to monitor environment spectra and corrosivity of service environments, focusing on parameters of interest, existing measurement platforms, deployment requirements, and data processing techniques. The sensors and monitoring systems provide discrete time-based records of 1) environmental parameters such as temperature, humidity, and contaminants; 2) measures of alloy corrosion in the sensor; and 3) protective coating performance in the sensor. These systems provide measurements of environmental parameters, sensor material corrosion rate, and sensor coating condition for use in assessing the risk of atmospheric corrosion of the structure.

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.

To detail the different epoxy types available for different aerospace applications which require different temperature ranges. Explain incoming/final inspection requirements and storage requirements. Examine the epoxy chemical make up with explanations of purpose in performance.

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 document provides guidance on key areas of system design to achieve high performance and high reliability for mission critical aerospace systems and platforms. The fundamental element of a reliable, functional aerospace fiber optic application is the system design. It is the system designers’ task to define the methods, components, installation and processes supporting the transmission of the optical signal through the platform, while providing a physical layer with the necessary performance, reliability, and readiness for the application.

This specification includes detailed requirements for a fiber optic cable splice compliant with AS5405.