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2017-02-25
WIP Standard
AS4681C
Scope is unavailable.
2017-02-16
WIP Standard
AS4694C
Propose revision to add conductive high purity aluminum coating per MIL-DTL-83488 for aluminum alloy fittings. The W code aluminum parts with new finish will be distinguished by new finish code V at the end of part number.
2017-02-16
WIP Standard
AS4664D
Propose revision to add conductive high purity aluminum coating per MIL-DTL-83488 for aluminum alloy fittings. The W code aluminum parts with new finish will be distinguished by new finish code V at the end of part number.
2017-02-16
WIP Standard
AS4808C
SCOPE IS UNAVAILABLE.
2017-02-16
WIP Standard
6533
Fitting will be based on AS4224 except it will specify AS85720 only (5,000 PSI). Related project G3B16-08 will remove "dual" qualification requirements from AS4224 by removing AS85720 and leaving AS85421.
2017-02-16
WIP Standard
6536
Fitting will be based on AS4808 except it will specify AS85720 only (5,000 PSI). Related project G3B16-08 will remove "dual" qualification requirements from AS4808 by removing AS85720 and leaving AS85421.
2017-02-16
WIP Standard
6534
Fitting will be based on AS4807 except it will specify AS85720 only (5,000 PSI). Related project G3B16-08 will remove "dual" qualification requirements from AS4807 by removing AS85720 and leaving AS85421.
2017-02-16
WIP Standard
AS6529
Fitting will be based on AS4220 except it will specify AS85720 only (5,000 PSI). Related project G3B16-08 will remove "dual" qualification requirements from AS4220 by removing AS85720 and leaving AS85421.
2017-02-16
WIP Standard
AS6528
Fitting will be based on AS4210 except it will specify AS85720 only (5,000 PSI). Related project G3B16-08 will remove "dual" qualification requirements from AS4210 by removing AS85720 and leaving AS85421.
2017-02-16
WIP Standard
AS6531
Fitting will be based on AS4221 except it will specify AS85720 only (5,000 PSI). Related project G3B16-08 will remove "dual" qualification requirements from AS4221 by removing AS85720 and leaving AS85421
2017-02-16
WIP Standard
AS6530
Fitting will be based on AS4211 except it will specify AS85720 only (5,000 PSI). Related project G3B16-08 will remove "dual" qualification requirements from AS4211 by removing AS85720 and leaving AS85421.
2017-02-16
WIP Standard
AS6532
Fitting will be based on AS4222 except it will specify AS85720 only (5,000 PSI). Related project G3B16-08 will remove "dual" qualification requirements from AS4222 by removing AS85720 and leaving AS85421.
2017-02-16
WIP Standard
AS6535
Fitting will be based on AS4809 except it will specify AS85720 only (5,000 PSI). Related project G3B16-08 will remove "dual" qualification requirements from AS4809 by removing AS85720 and leaving AS85421.
CURRENT
2017-02-15
Standard
AS6495A
SCOPE IS UNAVAILABLE.
2017-01-24
WIP Standard
AIR7999
This SAE Aerospace Information Report (AIR) presents metrics for assessing the performance of diagnostic and prognostic algorithms applied to Engine Health Management (EHM) functions. This document consolidates and expands upon the metric information previously contained in AIR4985 and AIR5909. The emphasis is entirely on metrics and as such is intended to provide an extension and complement to such documents as ARP4176, which provides insight into how to create a cost benefit analysis to determine the justification for implementing an EHM system.
2017-01-10
WIP Standard
ARP1897A
This document is prepared as an aid in the selection of clamping devices and their use in aerospace equipment for the installation and support of tubing and wiring.
2017-01-10
Technical Paper
2017-26-0130
Hemant P. Urdhwareshe
Abstract In the recent times, there have been number of cases of failure to pass the COP tests. When a vehicle fails a COP test, it is very embarrassing and expensive for the manufacturer as there is a loss of faith by the society and consumers. It is also painful for the certification agency as well as government. In this context, it is important to quantify and minimize the risk associated with these tests for manufacturers as well as certification agencies. The sampling plan specified in MoRTH / CMVR / TAP-115 is designed to quickly pass vehicles which have very low emissions and quickly reject (fail) vehicles having higher emissions compared to the specified limit. These sampling plans can be classified under Probability Ratio Sequential Tests (PRST).
2017-01-10
Technical Paper
2017-26-0336
Ganesh Liladhar Yewale, Abhishek Tapkire, D Radhakrishna, Popat Shejwal, Kaushal Singh, Gaurav Panchal
Abstract VRDE has developed Wankel type rotary engine to achieve high power output & fuel efficiency for indigenization programme of UAVs. This engine is meeting all performance parameters needed for intended aerial vehicle. This paper describes the testing methodology followed by development engineers to prove the endurance and reliability of UAV engine for airworthiness certification. This paper gives the brief about testing carried out on the Wankel engine, failures faced during endurance testing and their rectification to enhance the life of the engine to achieve hundred test cycle mark. This paper also briefs about the test set up, endurance test cycles simulating the practical operating conditions.
2017-01-09
WIP Standard
AS5117A
No scope available.
2017-01-05
WIP Standard
AIR7521
This document summarizes a number of guidance values and measured values in published literature for Substances listed in ARP4418.
2016-12-21
WIP Standard
ARP6915
This Aerospace Recommended Practice (ARP) offers best practice regarding the implementation of IVHM systems taking into account Human Factors, both the vehicle crew and the maintenance staff. The document will include considerations regarding both military and civil fixed wing aircraft. Safety implications will also be addressed.
CURRENT
2016-11-29
Standard
AIR1873A
This Aerospace Information Report (AIR) describes a Limited Engine Monitoring System that can be used by the flight crew or the maintenance staff, or both, to monitor the health of gas turbine engines in aircraft. This AIR considers monitoring of gas path performance and mechanical parameters, and systems such as low cycle fatigue counters and engine history recorders. It also considers typical measurement system accuracies and their impact. This AIR is intended as a technical guide. It is not intended to be used as a legal document or standard. AIR 1873 supplements ARP 1587, Aircraft Gas Turbine Engine Monitoring System Guide.
2016-10-26
WIP Standard
AS6449C
This document establishes the requirements for a dry film lubricant AS6449 lubricant for use on breathing oxygen system and potable water system components, for a temperature range of -90 to +300 °F. This document also establishes the Non-Destructive Test (NDT) procedures and criteria for coated production parts. This document requires qualified products and product applicators.
CURRENT
2016-10-21
Standard
ARP1619B
This SAE Aerospace Recommended Practice (ARP) defines recommended planning and substantiation procedures and associated reviewing and approval processes to confirm that proposed changes do not compromise the demonstrated safety of the originally certified aircraft, and performance and aircraft compatibility are appropriately addressed in aircraft documentation. Successful demonstration also requires that failure modes be identified and mitigation provided for each. These procedures apply to modifications made by the original component or assembly supplier as well as approval of an alternate supplier.
2016-10-03
WIP Standard
AS6462B
This set of criteria shall be utilized by accredited Certification Bodies (CBs) to establish compliance, and grant certification to AS5553A, Aerospace Standard; Counterfeit Electronic Parts; Avoidance, Detection, Mitigation, and Disposition.
2016-09-27
Journal Article
2016-01-8018
Houshun Zhang, L. James Sanchez, Matthew Spears, Jayant Sarlashkar, Dennis Robertson, Michael Ross
Abstract In June of 2015, the Environmental Protection Agency and the National Highway Traffic Safety Administration issued a Notice of Proposed Rulemaking to further reduce greenhouse gas emissions and improve the fuel efficiency of medium- and heavy-duty vehicles. The agencies proposed that vehicle manufacturers would certify vehicles to the standards by using the agencies’ Greenhouse Gas Emission Model (GEM). The agencies also proposed a steady-state engine test procedure for generating GEM inputs to represent the vehicle’s engine performance. In the proposal the agencies also requested comment on an alternative engine test procedure, the details of which were published in two separate 2015 SAE Technical Papers [1, 2]. As an alternative to the proposed steady-state engine test procedure, these papers presented a cycle-average test procedure.
2016-09-27
Journal Article
2016-01-8017
Eric Wood, Adam Duran, Kenneth Kelly
Abstract In collaboration with the U.S. Environmental Protection Agency and the U.S. Department of Energy, the National Renewable Energy Laboratory has conducted a national analysis of road grade characteristics experienced by U.S. medium- and heavy-duty trucks on controlled access highways. These characteristics have been developed using TomTom’s commercially available street map and road grade database. Using the TomTom national road grade database, national statistics on road grade and hill distances were generated for the U.S. network of controlled access highways. These statistical distributions were then weighted using data provided by the U.S. Environmental Protection Agency for activity of medium- and heavy-duty trucks on controlled access highways. The national activity-weighted road grade and hill distance distributions were then used as targets for development of a handful of sample grade profiles potentially to be used in the U.S.
2016-09-20
Technical Paper
2016-01-2047
K. Suresh, Rajkumar Dhande, Udupi Ananthakrishna Acharya
Abstract Reducing the amount of physical testing is of importance in the aeronautical industry, where each physical test represents a significant cost. Apart from the cost aspect, it may also be difficult or hazardous to carry out physical testing. Specific to the aeronautic industry are also the relatively long development cycles, implying long periods of uncertainty during product development. In any industry a common viewpoint is that of verification, validation, and uncertainty quantification using simulation models are critical activities for a successful development of a product. In Aeronautical application, the design of store's structural equipments needs to be certified in accordance with MIL-T-7743F [1]. This paper focuses on a case study for shock analysis, whereby an attempt has been made to reduce the cost of certification by way of replacing the actual physical testing by a reliable high fidelity FE simulation.
2016-09-20
Technical Paper
2016-01-2039
Prashant S. Vadgaonkar, Ullas Janardhan
Avionics industry is moving towards fly-by wire aircrafts with less reliance on mechanical systems leading to increase in the complexity of in-flight hardware elements. RTCA/DO-254 and EUROCAE ED-80 plays a vital role in the design assurance of airborne electronic hardware. RTCA/ DO-254 and EUROCAE ED-80 are the industry standards for Design Assurance Guidance for Airborne Electronic Hardware. The two different agencies FAA and EU regulate and apply this design assurance guidance to the regulatory law in CFR and EASA CS respectively. This paper discusses the need for DO-254 /ED-80 certification in Aerospace industry, the advantages and benefits to the avionics manufacturers. The paper presents the study made on similarities and differences between DO-254/ED-80.
2016-09-20
Technical Paper
2016-01-2044
Jeffrey J. Joyce, Scott Beecher, Laurent Fabre, Ramesh Rajagopalan
Abstract Over the past few decades, advanced methods have been developed for the analysis of digital systems using mathematical reasoning, i.e., formal logic. These methods are supported by sophisticated software tools that can be used to perform analysis far beyond what is practically achievable using “paper and pencil” analysis. In December 2011, RTCA published RTCA DO-178C [1] along with a set of technical supplements including RTCA DO-333 [2] which provides guidance on the use of formal methods towards the certification of airborne software. Such methods have the potential to reduce the cost of verification by using formal analysis instead of conventional test-based methods to produce a portion of the verification evidence required for certification.
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