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2015-09-29
Journal Article
2015-01-2768
Houshun Zhang, James Sanchez, Matthew W. Spears
Abstract In 2015 the U.S. Environmental Protection Agency (EPA) and the U.S. Department of Transportation's National Highway Traffic Safety Administration (NHTSA) proposed a new steady-state engine dynamometer test procedure by which heavy-duty engine manufacturers would be required to create engine fuel rate versus engine speed and torque “maps”.[1] These maps would then be used within the agencies' Greenhouse Gas Emission Model (GEM)[2] for full vehicle certification to the agencies' proposed heavy-duty fuel efficiency and greenhouse gas (GHG) emissions standards. This paper presents an alternative to the agencies' proposal, where an engine is tested over the same duty cycles simulated in GEM. This paper explains how a range of vehicle configurations could be specified for GEM to generate engine duty cycles that would then be used for engine testing.
2015-09-15
Technical Paper
2015-01-2546
Sylvain Delrieu
Abstract To perform a complete aircraft certification plan, civil aviation test centres use specific flight test installations and ground test means. In this scope tests specialists operate ground test means which have a generic name Laboratory Tests Means (LTM) to validate aircraft functions. Today these functions are becoming more and more complex, moreover certification deadlines and tests campaign costs are becoming increasingly challenging and demand LTM use optimization. In this context current LTM development approach is no longer suitable to cover these new constraints. Currently LTMs start to be designed when testing strategy for a new aircraft is defined and design is quite specific. Drawbacks of such an approach are: tunnel effect for LTM development, no simple sharing of testing resources, LTM reuse is not easy, LTM upgrade requires re-engineering and many LTMs have to be maintained even if only partially used.
2015-09-15
Technical Paper
2015-01-2434
Tian Lirong, Mu Ming
Abstract: Chinese aviation industry is now making great efforts in developing civil aircraft, as a result, more opportunities for Chinese companies to be involved in these programs, but Chinese companies are lack of experience in this area, certification is one of the challenges for them,so they are expected to be more competitive in design and certification. ACTRI (Aeronautical Computing Technique Research Institute) is a airborne computer supplier in China, to be able to develop electronic equipment for civil aircraft, the company has being working on processes improvement including the system process based on ARP4754 since 2008. This paper describes the customized system process in Chinese context.
2015-09-15
Technical Paper
2015-01-2524
Srikanth Gampa
Abstract Multi core platforms offer high performance at low power and have been deemed as future of size, weight and power constrained applications like avionics safety critical applications. Multi core platforms are widely used in non-real time systems where the average case performance is desired like in consumer electronics, telecom domains. Despite these advantages, multi core platforms (hardware and software) pose significant certification challenges for safety critical applications and hence there has been limited usage in avionics and other safety critical applications. Many multicore platform solutions which can be certified to DO-254 & DO 178B Level A are commercially available. There is a need to evaluate these platforms w.r.t certification requirements before deploying them in the safety critical systems thereby reducing the program risks. This paper discusses the advantages of multi core platforms in terms of performance, power consumption and weight/size.
2015-08-24
Standard
AIR5396A
This SAE Aerospace Information Report (AIR) provides various graphical displays of atmospheric variables related to aircraft icing conditions in natural clouds. It is intended as a review of recent developments on the subject, and for stimulating thought on novel ways to arrange and use the available data. Included in this Report is FAR 25 (JAR 25) Appendix C, the established Aircraft Icing Atmospheric Characterization used for engineering design, development, testing and certification of civilian aircraft to fly in aircraft icing conditions.
2015-08-12
Standard
J3010_201508
The SAE J2530 provides performance, sampling, test procedures, and marking requirements for wheels intended for normal highway use on passenger cars, light trucks, and multipurpose passenger vehicle. This Recommended Practice (which is separate from SAE J2530) specifies the workflow of the Wheel Conformity Assessment Program. This program allows wheel manufacturers to register their product compliant to SAE J3010. The following items precede display of “SAE J3010” on any particular wheel design: a. Manufacturer registration All manufactures with the objective to pursue registration, shall complete the registration as an individual manufacturer via the registrar’s website http://wheeldb.registrar.domain. The registration includes company contact information, wheels produced, and company identification marks. b.
2015-08-11
WIP Standard
AS4468G
This SAE Aerospace Standard (AS) covers the requirements for a flexible, lightweight, low pressure, self-extinguishing, silicone hose assembly. The hose has a fully fluorinated fluoropolymer inner liner and is primarily intended for use in aircraft potable water systems.
2015-08-07
Standard
AS5562
This SAE Aerospace Standard (AS) establishes minimum ice and rain performance criteria for electrically-heated pitot and pitot-static probes intended for use on the following classes of fixed-wing aircraft and rotorcraft. The classes of fixed-wing aircraft are defined by aircraft flight envelopes and are shown in Figure 1. The flight envelopes generally fall into the classes as shown below: Class 1: Cruise altitude ≤ 23 000 feet Class 2: Cruise altitude ≤ 31 000 feet Class 3: Cruise altitude ≤ 42 000 feet Class 4: Cruise altitude > 42 000 feet Class R: Rotorcraft The user of this standard must evaluate the aircraft level installation requirements for the probe against the class definition criteria to ensure adequate coverage for the application. It may be necessary to step up in class or modify the test conditions in order to meet the applicable installation requirements. NOTE: Class 2 is divided into two subgroups identified as either Class 2a or Class 2b.
2015-08-06
Standard
AMS2755G
AMS2755F has been declared "STABILIZED" by AMS Committee B. This document will no longer be updated and may no longer represent standard industry practice. This document was stabilized because it contains mature technology that is not expected to change and thus no further revisions are anticipated. NOTE: Previously this document was cancelled. The last technical update of this document occurred in November, 1996. Users of this document should refer to the cognizant engineering organization for disposition of any issues with reports/certifications to this specification; including exceptions listed on the certification. In many cases, the purchaser may represent a sub tier supplier and not the cognizant engineering organization.
2015-07-20
WIP Standard
AS4108/1A
SCOPE IS UNAVAILABLE.
2015-07-20
WIP Standard
AS4108/3A
SCOPE IS UNAVAILABLE.
2015-07-20
WIP Standard
AS4108/2A
SCOPE IS UNAVAILABLE.
2015-06-15
Technical Paper
2015-01-2111
Marie-Laure Toulouse, Richard Lewis
Abstract The intent of this paper is to provide a general overview of the main engineering and test activities conducted in order to support A350XWB Ice and Rain Protection Systems certification. Several means of compliance have been used to demonstrate compliance with applicable Certification Basis (CS 25 at Amendment 8 + CS 25.795 at Amendment 9, FAR 25 up to Amendment 129) and Environmental protection requirements. The EASA Type Certificate for the A350XWB was received the 30th September 2014 after 7 years of development and verification that the design performs as required, with five A350XWB test aircraft accumulating more than 2600 flight test hours and over 600 flights. The flight tests were performed in dry air and measured natural icing conditions to demonstrate the performance of all ice and rain protection systems and to support the compliance demonstration with CS 25.1419 and CS25.21g.
2015-06-15
Technical Paper
2015-01-2128
Enrico Bellussi
Abstract This paper describes the AgustaWestland (AW) experience in the use of the results obtained with the HISS flight tests to support the civil ice clearance for rotorcraft. The use of the HISS, a US Army CH-47D Chinook fitted with a spray bar system providing a cloud where the helicopter can fly in icing conditions, allows stable and prolonged flight data, conditions extremely difficult to encounter during natural ice flights. The paper analyses the definition of the HISS test matrix, to optimize the points needed for system development and the points possibly usable during certification, in both normal and failure mode conditions. It is also shown how the HISS ice campaigns results can be assessed, and how they can be compared to the natural ice flights to validate them. Finally it is explained how the HISS results can be used, in addition to natural ice flights results, to support the certification.
2015-06-15
Technical Paper
2015-01-2144
James MacLeod, Michael Clarke, Doug Marsh
The Global Aerospace Centre for Icing and Environmental Research Inc. (GLACIER) facility is located in Thompson, Manitoba, Canada. This facility provides icing certification tests for large gas turbine engines, as well as performance, endurance and other gas turbine engine qualification testing. This globally unique outdoor engine test and certification facility was officially opened back in 2010. The prime purpose of this facility is for icing certification of aero gas turbines. As a generic engine test facility, it includes the infrastructure and test systems necessary for the installation of both current and future gas turbine engines. The GLACIER facility completed its commissioning in the winter of 2010/2011, and has now experienced five years of full icing seasons. Rolls-Royce and Pratt and Whitney have both successfully performed certification and engineering icing testing with 5 engines completing their icing certification.
2015-06-15
Technical Paper
2015-01-2105
Darren Glenn Jackson
Aircraft icing has been a focus of the aviation industry for many years. While regulations existed for the certification of aircraft and engine ice protection systems (IPS), no FAA or EASA regulations pertaining to certification of ice detection systems existed for much of this time. Interim policy on ice detection systems has been issued through the form of AC 20-73A as well as FAA Issue Papers and EASA Certification Review Items to deal mainly with Primary Ice Detection Systems. A few years ago, the FAA released an update to 14 CFR 25.1419 through Amendment 25-129 which provided the framework for the usage of ice detection systems on aircraft. As a result of the ATR-72 crash in Roselawn, Indiana due to Supercooled Large Droplets (SLD) along with the Air France Flight 447 accident and numerous engine flame-outs due to ice crystals, both the FAA and EASA have developed new regulations to address these concerns.
2015-06-12
Standard
AS9014A
These requirements are applicable to IAQG sector schemes when making use of ABs, CRBs and their auditors, for the assessment and certification/registration of supplier quality systems in accordance with the requirements of this document. The quality management system standard used by the CRB shall be 9100/9110/9120, as appropriate to the supplier's activities. It shall be applied to the supplier's complete Quality System that covers aerospace products. Sectors may use these requirements for other standards. IAQG members have committed to recognize the equivalence of certification/registration of a suppliers quality management system to either of the AS, EN or JISQ/SJAC standards. This AS provides the approval process for Auditor Authentication Bodies (AAB), training course providers, trainers and auditors who meet the requirements of AIR5493 and outlines the America's sector specific process to implement AS9104. This document is created to be in conformance with AS9104.
2015-06-01
WIP Standard
AS1708F
Scope is unavailable.
2015-05-20
WIP Standard
AS4130C
Scope is unavailable.
2015-05-20
WIP Standard
AS4136C
Scope is unavailable.
2015-05-20
WIP Standard
AS4134C
Scope is unavailable.
2015-04-28
WIP Standard
AIR6892
This SAE Aerospace Information Report (AIR) is applicable to rotorcraft structural health monitoring (SHM) applications, both commercial and military, where end users are seeking guidance on the definition, development, integration, qualification, and certification of SHM technologies to achieve enhanced safety and reduced maintenance burden based on the lessons learned from existing Health and Usage Monitoring Systems (HUMS). While guidance on SHM business case analysis would be useful to the community, such guidance is beyond the scope of this AIR. For the purpose of this document, SHM is defined as “the process of acquiring and analyzing data from on-board sensors to evaluate the health of a structure.” The suite of on-board sensors could include any presently installed aircraft sensors as well as new sensors to be defined in the future. Interrogation of the sensors could be done onboard during flight or using ground support equipment.
2015-03-12
WIP Standard
AS6323
AS PART STANDARD FOR AN EXTENDED UNION TO REPLACE A CUT OUT AS6117 UNION
2015-03-11
WIP Standard
AS6322
AS PART STANDARD FOR AN EXTENDED UNION TO REPLACE A CUT OUT AS5969 UNION.
2015-02-27
WIP Standard
AS6116A
This SAE Aerospace Standard (AS) establishes the requirements for externally swaged aluminum tube fittings on aluminum tubing with flareless separable fitting ends for use in hydraulic supply and return aerospace fluid systems including pneumatic, coolants, and fire extinguishers up to a maximum operating pressure of 1500 psig (10 340 kPa) and a maximum operating temperature range of -65 to +225 °F (-54 to +107 °C).

This specification covers a common aluminum fitting that may be used for a range of operating pressures up to 1500 psi with different tubing materials and tubing wall thicknesses, and is assembled with the same tooling in accordance with AS6124. Table 12 shows applicable aerospace fitting part number standard and tubing materials and operating pressures.

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