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The CDIF Family of Standards is primarily designed to be used as a description of a mechanism for transferring information between CASE tools. It facilitates a successful transfer when the authors of the importing and exporting tools have nothing in common except an agreement to conform to CDIF. The language that is defined for the Transfer Format also has applicability as a general language for Import/Export from repositories. The CDIF Integrated Meta-model defined for CASE also has applicability as the basis of standard definitions for use in repositories. The standards that form the complete family of CDIF Standards are documented in EIA/IS-106 CDIF - CASE Data Interchange Format - Overview. These standards cover the overall framework, the transfer format and the CDIF Integrated Meta-model. The diagram in Figure 1 depicts the various standards that comprise the CDIF Family of Standards. The shaded box depicts this Standard and its position in the CDIF Family of Standards.

The CDIF Family of Standards is primarily designed to be used as a description of a mechanism for transferring information between CASE tools. It facilitates a successful transfer when the authors of the importing and exporting tools have nothing in common except an agreement to conform to CDIF. The language that is defined for the Transfer Format also has applicability as a general language for Import/Export from repositories. The CDIF Integrated Meta-model defined for CASE also has applicability as the basis of standard definitions for use in repositories. The standards that form the complete family of CDIF Standards are documented in EIA/IS-106 CDIF - CASE Data Interchange Format - Overview. These standards cover the overall framework, the transfer format and the CDIF Integrated Meta-model. The diagram in Figure 1 depicts the various standards that comprise the CDIF Family of Standards. The shaded box depicts this Standard and its position in the CDIF Family of Standards.

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 development of future more-and full-electric aircraft concepts has significantly impacted aircraft electric power system (EPS) design. Finalizing the EPS architectures involves extensive modeling and simulation activities to ensure the required characteristics of the entire EPS prior to the physical implementation. Hence, the development of accurate, effective and computational time-saving simulation models is of great importance. Correspondingly, there is a need to establish an EPS-specific modeling and simulations common framework to ensure effective and accurate solutions to the problems addressed. The document continues a series of AE-7M documents specific for aircraft electrical systems aiming to establish such a framework (the series has started with AIR 6326 "Aircraft Electrical Power Systems. Modeling and Simulation. Definitions" issued in August, 2015).

This document addresses many of the issues and challenges related to obtaining high quality measurements at the designated Aerodynamic Interface Plane (AIP) necessary to characterize the flow field. The intent is to consolidate information needed to understand the requirements, and techniques for obtaining quality measurements, and provide lessons learned from previous test programs. This document applies to Ground (wind tunnel and engine test) and Flight testing for inlet recovery and distortion for air vehicles.

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.

This is an initial release of an Aerospace Information Report to provide methods for Engine Suppliers to follow to execute their in house performance models to generate datasets that are provided to airframe customers early in the conceptual design phase of an aircraft program. This AIR provides some general guidance for execution order and input settings to be used to execute the model.

This document will address techniques or methods that have been used within the industry to address the problem of engine stability margin accounting when combinations of distortion types exist in an aircraft installation. Its focus is combining temperature, planar wave, and swirl distortion with time-variant spatial total pressure distortion. Example methodologies will be presented along with example cases where co-existing distortions have been evaluated. It will also address the areas where the industries' knowledge base is lacking (experimental data or computational methods) and the future work that is needed for methodology development in these areas. This document is viewed to be updated every five years as more information (data either experimentally or analytically) becomes available.

Requirements for 3rd party powder distributors.

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.

This standard establishes the requirements for the manufacturing of a Finished Goods Feedstock from receipt of Raw Feedstock Lot for continuous fiber-reinforced materials. It does not establish implementation.

This slash sheet establishes the requirements for the manufacturing of a Finished Goods Feedstock from receipt of Raw Feedstock Lot. It does not establish implementation. The Finished Goods Feedstock detailed in this document is Carbon Fiber FR-ATM (T300 1K tow), a Type 1 Form 1 PACF50FR05 filament. Carbon Fiber FR-A cannot be used on its own and is intended to be used with Onyx FR-A

This specification will establish the minimum requirements for Laser Sintering feedstock to be used in conjunction with the Laser Sintering process specification for fabricating LS parts. The Laser Sintering part (with/without subsequent processing) may be used for, but not limited to, aerospace applications. This specification outlines the minimum technical and documentation requirements for Laser Sintering materials.

This specification establishes the requirements for the production of reliable, repeatable, reproducible aerospace parts by fused filament fabrication with continuous fiber reinforcement. This specification establishes the requirements to approve new machines, processes, and materials. Specifically, this specification covers the constituent material, the configuration of the machine, operating software, machine calibration, build parameters, and acceptance criteria and testing methodology required to create aerospace parts. This specification also defines the user’s responsibility for following the specified requirements.

This specification establishes the requirements for the production of reliable, repeatable, reproducible aerospace parts by fused filament fabrication with continuous fiber reinforcement. This specification establishes the requirements to approve new machines, processes, and materials. Specifically, this specification covers the constituent material, the configuration of the machine, operating software, machine calibration, build parameters, and acceptance criteria and testing methodology required to create aerospace parts. This specification also defines the user’s responsibility for following the specified requirements.

This specification will establish the critical controls and requirements for the production of reliable, repeatable, reproducible aerospace parts by Laser Sintering fabrication but is not limited to such application. This procedure will establish guidelines that users shall follow to approve new machines, processes, and materials. Specifically, this specification covers the configuration of the machine, operating software, machine calibration, machine and build parameters, and testing methodology required to create high performance aerospace parts. This specification also outlines the user’s responsibility for following the established guidelines and documentation requirements

This specification establishes the requirements for the manufacturing of a Finished Goods Feedstock from receipt of Raw Feedstock Lot. The Finished Goods Feedstock detailed in this document is Onyx FR-A, a Type 1 Form 1 PACF15FR15 filament.

This slash sheet is used in conjunction with the AM Polymer base specification AMS 7100 and provides the unique and specific process information for the Onyx FR-A processes using the Markforged X7 Machine