In the Aerospace Industry there is a growing focus on Defect Prevention to ensure that quality goals are met. Process Failure Mode & Effects Analysis (PFMEA) and Control Plan activities described in AS13004 are recognized as being one of the most effective, on the journey to Zero Defects. This two-day course is designed to explain the core tools of Process Flow Diagrams, Process Failure Mode & Effects Analysis (PFMEA) and Control Plans as described in AS13004. It will show the links to other quality tools such as Design FMEA, Characteristics Matrix and Measurement Systems Analysis (MSA).
Certifying an aircraft, part or appliance can be challenging while navigating the maze of Federal Aviation Administration (FAA) procedures, rules, policies and guidelines. This course will help you to the understand the FAA organizational structure, it"s policies, guidelines and requirements leading to Type and Supplemental Type airworthiness approvals, and provide you with a competitive edge and potential reduction in time in obtaining an FAA approval.
The international standards D-326A (U.S.) and ED-202A (Europe) titled "Airworthiness Security Process Specification" are the cornerstones of the "DO-326/ED-202 Set" and they are the only Acceptable Means of Compliance (AMC) by FAA & EASA for aviation cyber-security airworthiness certification, as of 2019.
Hybrid-electric gas turbine generators are considered a promising technology for more efficient and sustainable air transportation. The Ohio State University is leading the NASA University Leadership Initiative (ULI) Electric Propulsion: Challenges and Opportunities, focused on the design and demonstration of advanced components and systems to enable high-efficiency hybrid turboelectric powertrains in regional aircraft to be deployed in 2030. Within this large effort, the team is optimizing the design of the battery energy storage system (ESS) and, concurrently, developing a supervisory energy management strategy for the hybrid system to reduce fuel burn while mitigating the impact on the ESS life. In this paper, an energy-based model was developed to predict the performance of a battery-hybrid turboelectric distributed-propulsion (BHTeDP) regional jet.
Ice accretion poses a major problem for civilian and military aircraft and rotorcraft, severely jeopardizing the safety and survivability of the vehicle. The development of analytical and empirical ice tools to understand the ice accretion process is crucial. Existing methodologies, such as the Messinger model employed by LEWICE, are able to predict ice shapes and growth on lifting surfaces such as wings and rotors relatively well. Extension of these methodologies to more complex configurations is needed. The methodology must be reasonably modular so that one can leverage future developments in computational fluid dynamics, structured and unstructured grid generation, and ice accretion models. Towards this goal, the following modular approach has been developed. 1. Do the unstructured grid based flow analysis. Save the grid and flow field in a standard format such as Plot3D or VGrid. 2. Compute the water particle transport using either the Lagrangian approach or an Eulerian approach.
A head gasket is a component that sits between the engine block/liner and cylinder head(s) in an internal combustion engine. Its purpose is to seal high pressure combustion gasses in the cylinders, seal coolant and engine oil transfer ports between the block and head and to ensure no leakage of gasses or fluids out of the block to head joint; as such, it is the most critical sealing application in an engine. In general practice, the load deflection(L/D) characteristic is generated by the gasket manufacturer for edge molded or composite gasket types. In the case of a solid-sheet metallic gasket, where the gasket is expected to undergo local yielding to provide adequate conformance and sealing, supplier is usually not able to provide the required L/D curve due to difficulties experimentally separating the large loads and small displacements from the elastic loads and deflections of the experimental apparatus.
Mars has been the topic of colonization and discovery for the last few decades but there have been hindrances in implementing the mission. This focus on Mars colonization has only deepened after the discovery of water on its surface. The discovery of water on Mars has led researchers to believe that its sustainability of life is higher than any other uncolonized planet. Although, life can survive on Mars, it is highly unethical to send communities to Mars without acknowledging the risks, especially those concerning the well being of humans. The risks of living on Mars are slowly unraveling through extensive research, but it is evident that certain health care measures must be taken in order to prevent potentially fatal conditions. One of the biggest problems is health concerns that astronauts face after returning from Mars. Health problems in space have been increasingly difficult to deal with because of the lasting circumstances that astronauts suffer upon returning back to Earth.
The avionics hardware industry world-wide is now commonly required to follow DO-254 Design Assurance Guidance for Airborne Electronic Hardware for literally all phases of development: Safety, Requirements, Design, Logic Implementation, V&V, Quality Assurance, etc. The DO-254 standard is a companion to the software DO-178B standard; however, there are many differences between hardware and software which must be understood. This basic course introduces the intent of the DO-254 standard for commercial avionics hardware development.
This document provides informational background, rationale and a technical case to allow consideration of the removal of the magnesium alloy restriction in aircraft seat construction as contained in AS8049B. The foundation of this argument is flammability characterization work performed by the FAA at the William J. Hughes Technical Center (FAATC), Fire Safety Branch in Atlantic City, New Jersey, USA. The rationale and detailed testing results are presented along with flammability reports that have concluded that the use of specific types of magnesium alloys in aircraft seat construction does not increase the hazard level potential in the passenger cabin in a post-crash fire scenario. Further, the FAA has developed a lab scale test method, reference DOT/FAA/TC-13/52, to be used as a certification test, or method of compliance (MOC) to allow acceptability of the use of magnesium in the governing TSO-C127 and TSO-C39C.
This specification covers the requirements for aircraft, hydraulic, self-sealing, quick disconnect couplings, for use in Type II hydraulic systems (-65 to +275 °F temperature range) as defined by AS5440.
This AIR would examine the applicability of ARP 4754 and ARP 4761 to UAS and would identify the shortcomings in both recommended practices with regards to the specific technical aspects needed for UAS development.
This SAE Aerospace Standard (AS) establishes the aerodynamic flow-off requirements and test procedures for AMS1424 Type I and AMS1428 Type II, III and IV fluids used to deice and/or anti-ice aircraft. The objective of this standard is to ensure acceptable aerodynamic characteristics of the deicing/anti-icing fluids as they flow off of aircraft lifting and control surfaces during the takeoff ground acceleration and climb. Aerodynamic acceptance of an aircraft ground deicing/anti-icing fluid is based upon the fluid’s boundary layer displacement thickness (BLDT) on a flat plate, measured after experiencing the free stream velocity time history of a representative aircraft takeoff. Acceptability of the fluid is determined by comparing BLDT measurements of the candidate fluid with a datum established from the values of a reference fluid BLDT and the BLDT over the dry (clean) test plate.
This SAE Aerospace Recommended Practice (ARP) covers requirements for a rotary plow with carrier vehicle primarily used to cast heavy concentrations of snow away from airport operational areas such as runways and taxiways. The term carrier vehicle represents the various self-propelled prime movers that provide the power necessary to move snow and ice control equipment during winter operations.