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Using STPA During Development and Safety Assessment of Civil Aircraft

2018-02-13
WIP
AIR6913
This AIR will provide a basic understanding of STPA and how it can be applied to development and safety assessment of civil aircraft. It will explain, by way of an example, the information needed to begin STPA, the expected STPA outputs, and the phases of aircraft development and safety assessment that can be supported by STPA.
Standard

FIBER OPTIC DESIGN GUIDELINES FOR AEROSPACE

2018-10-18
WIP
AIR8448
This document provides guidance on key areas of system design to achieve high performance and high reliability for mission critical aerospace systems and platforms. The fundamental element of a reliable, functional aerospace fiber optic application is the system design. It is the system designers’ task to define the methods, components, installation and processes supporting the transmission of the optical signal through the platform, while providing a physical layer with the necessary performance, reliability, and readiness for the application.
Standard

High Lift Systems Description

2008-10-25
WIP
AIR6016
The scope of the project is to develop a comprehensive description document that displays various examples of High Lift Systems of commercial and military aircraft. The main focus is on mechanical systems which may be actuated hydraulically or electrically. The document is intended as an overview for those specifying or designing High Lift Systems in order to compare existing solutions as reference for implementation in new aircraft programs.
Standard

Engine Electronics fire and overheat design guide

2010-03-09
WIP
AIR6108
This document scope covers all of the considerations relevant to the design of a fire and overheat protection scheme for an aerospace electronic control unit.. The focus is the engine electronic controller (EEC) typically used on civil aircraft applications and mounted on engine, but aspects are also applicable to condition monitoring units and units mounted off-engine. Content includes aplicable regulations, assumptions, additional constraints, installation, compliance strategies and compliance testing.
Standard

Landing Gear Systems - Endurance Scatter Factor

2010-08-16
WIP
AIR6452
This information report will provide the reader with the thought processes and rationales employed by OEM's and gear manufacturers when specifying the scatter factor to apply to landing gear system components for endurance qualification testing.
Standard

Using Aircraft Position Data to Estimate Aircraft Thrust

2007-02-26
WIP
AIR5766
This SAE Aerospace Information Report (AIR) provides information and methods for using aircraft position data to estimate aircraft thrust. The thrust estimated using this AIR is intended to be used to estimate aircraft noise level and aircraft air pollution and greenhouse gas emissions. The method of estimating aircraft noise level using aircraft thrust is provided in AIR 1845. Aircraft noise and emissions are generally estimated using models that are based on standard sets of aircraft profiles that include aircraft thrust, speed, and altitude along the flight path. Potential uses of this AIR are to provide an experimental method of determining the adequacy of a standard profile or to develop a flight specific profile. Flight specific profiles may be used to develop or revise standard profiles or to model noise or emissions on a flight-by-flight basis.
Standard

HELICOPTER TURBOSHAFT ENGINE IDLE POWER SCHEDULING

2018-08-09
WIP
AIR4121
The purpose of this AIR (Aerospace Information Report) is to provide aircraft and engine designers with a better understanding of helicopter turboshaft engine idle power characteristics and objectives to be considered in the design process. Idle is the lowest steady state power setting. At this setting, the engine typically does not produce enough power to obtain governed output shaft speed (i.e. the shaft speed is determined by the load imposed by the aircraft). In the aircraft, the engine is typically stabilized at this power setting after starting, prior to taxi and for some period of time after rotor shutdown for cool down prior to engine shutoff. Traditionally, the aircraft designer wants idle power scheduled as low as possible and of course, does not want any resulting aircraft operational difficulties such as overcoming the rotor brake. The engine designer, however, desires a higher scheduled power because of the reduced probability of engine operational problems.
Standard

Guidelines for Ethernet Physical Layer on Military and Aerospace Vehicle Applications

2017-08-01
WIP
ARP7208
This ARP establishes guidelines for the use of IEEE-802.3 as a data bus network in military and aerospace vehicles. It encompasses the data cable and its connections for a system utilizing 10Base-T, 100Base-T, 1000BASE-T and 10GBASE-T over copper medium dependent interfaces (MDI). This document contains extensions/restrictions to “off-the-shelf” IEEE-802.3 standards, and assumes that the reader already has a working knowledge of IEEE-802.3.
Standard

Recommended Design and Test Requirements for Quantity Measuring Hydraulic Fuses

2018-11-07
WIP
ARP8450
1. SCOPE This Aerospace Recommended Practice (ARP) provides recommendations for design and test requirements for quantity measuring hydraulic fuses. 1.1 Purpose The recommended requirements contained in this ARP are compiled for inclusion, as applicable, in a Procurement Specification for this type of hydraulic fuse. NOTES: 1. The recommended requirements in this ARP should be reviewed by the procuring activity and only those requirements that are applicable for a specific application should be incorporated in the Procurement Specification. 2.
Standard

Substantiation of Power Available and Inlet Distortion Compliance for Rotorcraft Inlet Barrier Filter Installations

2017-03-20
WIP
ARP6912
This Aerospace Recommended Practice (ARP) identifies and defines methods of compliance to power available and inlet distortion requirements for rotorcraft with Inlet Barrier Filter (IBF) installations. The advisory material developed therein may be used as acceptable methods of compliance for determining power assurance, establishing power available, and for substantiating acceptable engine inlet distortion for IBF installations. It is agreed to treat dust, ice, salt water & snow as contaminants to IBF for the purpose of establishing power available and distortion. Flight in known icing will be addressed in ARP6901.
Standard

Tests Recommended for Qualifying an Artificial Bird for Aircraft Certification Testing

2018-03-27
WIP
ARP6924
This document defines the Level 1 tests required for qualifying an artificial bird for certification testing of aircraft and aircraft engines. Level 1 refers to the lowest level of the test pyramid associated with the building block approach defined in the CMH-17 Composite Materials Handbook. The test pyramid consists of a sequence of 5 levels of testing, ranging from the most basic at the lowest level of the pyramid to the most complex at the apex. Typically the number of tests performed has an inverse relationship to the complexity of the tests. The building block approach is used for defining the tests required to qualify an artificial bird that would be accepted by regulatory agencies for certification testing of aircraft, including rotorcraft, fixed wing fuselages and engines, where bird strike testing is currently required. This document only describes the tests required for Level 1 of the test pyramid. Separate documents define the tests required at higher levels.
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