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Unmanned aviation systems (UAS) acquired for US Navy for military roles are developed in the context of NAVAIR's rigorous and well-established policies, procedures and processes employed in the acquisition and development of manned aircraft. A key process is the preparation and approval of interim flight clearances (IFC) prior to flight test to ensure the aircraft is airworthy and thus safe to operate. Due to the perceived risks of UAS experimental flight test, the use of this process has been mandated for all Navy organizations, including use of commercially available UAS in research projects. This policy has proved to be a challenge, impeding and discouraging the use of UAS in research and experimental projects. Currently, the cost of compliance is unaffordable and IFC preparation and approval time are inconsistent with research cycle time expectations.

Within the aerospace industry there is a growing interest in evaluating and reducing the environmental impacts of products and related risks to business. Consequently, requests from governments, customers, manufacturers, and other interested stakeholders, for environmental information about aerospace products are becoming widespread. Presently, requests are inconsistent and this limits the ability of the aerospace industry to meet the informational needs of various stakeholders and reduce the environmental impacts of their products in a cost-effective manner. Energy consumption is a significant business cost, risk, and a simple proxy value for overall environmental impact. This paper presents the initial research carried out by an academic and industry consortium to develop standardised methods for calculating and reporting the embodied manufacturing energy content of aerospace products.

Industrial robots have been around since the 1960s and their introduction into the manufacturing industry has helped in automating otherwise repetitive and unsafe tasks, while also increasing the performance and productivity for the companies that adopted the technology. As the majority of industrial robotic arms are deployed in repetitive tasks, the pose accuracy is much less of a key driver for the majority of consumers (e.g. the automotive industry) than speed, payload, energy efficiency and unit cost. Consequently, manufacturers of industrial robots often quote repeatability as an indication of performance whilst the pose accuracy remains comparatively poor. Due to their lack in accuracy, robotic arms have seen slower adoption in the aerospace industry where high accuracy is of utmost importance. However if their accuracy could be improved, robots offer significant advantages, being comparatively inexpensive and more flexible than bespoke automation.

This SAE Metric Aerospace Standard (MA) provides dimensional, performance, testing and other requirements for high strength, thin wall, double head box and combination wrenches which possess an internal wrenching design so configured that, when mated with hexagon (6 point) fasteners, they shall transmit torque to the fastener without bearing on the apex of the fastener’s wrenching points. This standard provides additional requirements beyond ANSI B107.9 appropriate for aerospace use. Inclusion of dimensional data in this document is not intended to imply all of the products described therein are stock production sizes. Consumers are requested to consult with manufacturers concerning lists of stock production sizes.

This information is to aid the international air transport industry when considering the communication of safety information to sight-impaired passengers.

This information is to aid the international air transport industry when considering the communication of safety information to sight-impaired passengers.

This Handbook is intended to provide useful information on the application of AS5716A. It is for use by System Program Offices, aircraft prime contractors, avionics and store system designers, system integrators and equipment manufacturers and users. This Handbook was prepared to provide users of the standard of the rationale and principles considered during the development of the standard. It is anticipated that the handbook will serve to assist developers in introducing new technology to achieve compliance with the standard and the underlying principles of the standard. It is intended that the Handbook be used alongside the standard, as it does not contain significant extracts of the standard.

This Assessment Guide is applicable to any assessment technique that wishes to embrace the principles and concepts presented in the EIA-599 National Electronic Process Certification Standard.

The following is the history of SAE Committee A-10.

This SAE Aerospace Recommended Practice (ARP) covers the requirements for alternative coatings used in lieu of nickel-chromium plating and the surface finish requirements for aerospace hand tools. It is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances.

This SAE Aerospace Recommended Practice (ARP) covers the requirements for alternative coatings used in lieu of nickel-chromium plating and the surface finish requirements for aerospace hand tools. It is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances.

These recommendations cover the use of taper pins in taper pin terminal blocks, multi-contact electric connectors, and components designed to accept taper pins. Taper pins are intended to facilitate termination of a wire and are not to be employed as a quick-disconnect device. The mating portions of taper pins and taper pin receptacles shall be in accordance with Figure 1.

This ARP provides design guidelines based on currently available information for the impact safety design of the cabin occupant environment.

A life support system (LSS) is usually defined as a system that provides elements necessary for maintaining human life and health in the state required for performing a prescribed mission. The LSS, depending upon specific design requirements, will provide pressure, temperature, and composition of local atmosphere, food, and water. It may or may not collect, dispose, or reprocess wastes such as carbon dioxide, water vapor, urine, and feces. It can be seen from the preceding definition that LSS requirements may differ widely, depending on the mission specified, such as operation in Earth orbit or lunar mission. In all cases the time of operation is an important design factor. An LSS is sometimes briefly defined as a system providing atmospheric control and water, waste, and thermal management.