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This document provides background information, rationale, and data (both physical testing and computer simulations) used in defining the component test methods and similarity criteria described in SAE Aerospace Recommended Practice (ARP) 6330. ARP6330 defines multiple test methods used to assess the effect of seat back mounted IFE monitor changes on blunt trauma to the head and post-impact sharp edge generation. The data generated is based on seat and IFE components installed on type A-T (transport airplane) certified aircraft. While not within the scope of ARP6330, generated test data for the possible future development of surrogate target evaluation methods is also included
Aircraft Seat Committee
This SAE Aerospace Recommended Practice (ARP) provides recommendations for: The audit process in general A list of specific areas of attention to be audited Maintaining the test facility in such a manner that it meets audit requirements
EG-1E Gas Turbine Test Facilities and Equipment
This document outlines the engineering evaluation appropriate for modifying or replacing components of a previously certified seat when the certification process is based on qualification to the requirements of AS8049, which includes dynamic testing. The engineering evaluation presented in this document may be used to determine if a modification (including replacement of a component) is a minor change with respect to meeting the dynamic testing requirements described in AS8049. Whenever a modification is considered, the ability to meet all requirements of the applicable Federal Aviation Regulation (FAR) must be verified. For example, this would include the capability to meet requirements such as flammability and flotation. Analysis and/or test data supporting the ability of the new materials and/or configuration to meet the applicable requirements must be submitted with the change documentation. This document addresses the evaluation of seat pan cushions, secondary components, and
Aircraft Seat Committee
The specific performance requirements preceding each test in Section 9 have been written to define certain characteristics of the machine. Conformance with the tests constitutes what is considered minimum proof that the machine will meet these requirements. The test procedures will not prove conformance with all requirements over the full range of all variables, neither will they measure nor define the exact reasons for nonconformance in a given test. Failure of a machine to conform may be due to shortcomings in specific components or to more general reasons such as lack of ruggedness, improper leveling or anchoring to the floor, etc
EG-1A Balancing Committee
This SAE Aerospace Recommended Practice (ARP) contains methods used to measure the optical performance of airborne binocular Head Up Displays (HUDs). This document covers methods for conformal and non-conformal HUD systems that are intended for use in the cockpit by the pilot or copilot. The focus of this document is on displays that generate the HUD information using a cathode ray tube (CRT), however, the majority of the methods can be applied to other display technologies. These measurement methods are provided for testing to the requirements of AS8055. This document does not address measurement methods for sensor imaging systems, or displays worn by the pilot (goggles, helmet mounted displays
A-4HUD Head-up Display Subcommittee
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
Procedure for obtaining the corrected heat-rating values (indicated mean effective pressure, IMEP) of spark plugs rated in the SAE 17.6 cubic inch rating engine (SAE AS840
E-30 Propulsion Ignition Systems Committee
This specification relates to Synchros, 60 and 400 Hz. It is not complete in itself, but shall be used in conjunction with MIL-DTL-81963, in which the latter shall be recognized as forming an inherent part of this specification. This standard requires a Qualified Products List (see 6.4
AE-7A Generators and Controls Motors and Magnetic Devices
This guide is intended to promote safe designs, operations and maintenance on aircraft and ground support oxygen systems. This is also a summary of some work by the ASTM G 4 Committee related to oxygen fire investigations and design concerns to reduce the risk of an oxygen fire. There have been many recent technological advances and additional test data is available for evaluating and controlling combustion hazards in oxygen equipment. Standards that use this new information are rapidly evolving. A guide is needed to assist organizations and persons not completely familiar with this process to provide oxygen systems with minimum risks of combustion. This guide does not necessarily address all the detailed issues and provide all data that will be needed. For a complete analysis, supplemental publications need to be consulted. This guide does discuss the basics of oxygen systems fire hazards. The hazard analysis process is discussed and a simple example to explain this process. Also
A-10 Aircraft Oxygen Equipment Committee
Groove designs presented herein are applicable for use with machined or formed metal seals which are similar in configuration to those shown in figure 3, which operate under internal pressure or in vacuum service and which have been specifically qualified or recommended by the purchaser or the manufacturer for use with this AIR. They are also applicable for use with metal o-rings (e.g., MS9142, MS202 thru MS9205) where interchangeability with machined or formed metal seals is desired. For metal o-ring groove designs where inter-changeability is not a requirement refer to ARP 674
E-25 General Standards for Aerospace and Propulsion Systems
This SAE Aerospace Standard (AS) shall be used in conjunction with AMS4946 to provide requirements for qualification testing and for qualified products listing (QPL) and qualified manufacturer listing (QML) for Ti-3Al-2.5V cold worked and stress relieved hydraulic system tubing. The basic tubing shall comply with the requirements of AMS4946
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This specification covers manual pressure-generating brake control units as defined by Specification MIL-H-5440
A-6C5 Components Committee
E-25 General Standards for Aerospace and Propulsion Systems
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
The Aircraft Engine Starting and Auxiliary Power System Glossary presents definitions of terms commonly encountered and associated with aircraft engine starting and auxiliary power systems. Terms have been arranged alphabetically
AE-6 Starting Systems and Auxiliary Power Committee
The purpose of this document is to give the reader an overview of the document package which makes up AIR825, Introduction to Oxygen Equipment for Aircraft, and a basic overview (see Section 4) of the operational concerns driven by human physiology during altitude exposure
A-10 Aircraft Oxygen Equipment Committee
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This SAE Aerospace Recommended Practice (ARP) covers all types of ground support equipment required to support civil transport aircraft
AGE-3 Aircraft Ground Support Equipment Committee
AE-7A Generators and Controls Motors and Magnetic Devices
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This SAE Aerospace Standard (AS) documents a common understanding of terms, compliance issues, and occupant injury criteria to facilitate the design and certification of oblique facing passenger seat installations specific to Part 25 aircraft. The applicability of the criteria listed in this current release is limited to seats with an occupant facing direction greater than 18° and no greater than 45° relative to the aircraft longitudinal axis. Seats installed at angles greater than 30° relative to the aircraft longitudinal axis must have an energy absorbing rest or shoulder harness and must satisfy the criteria listed in Table 2. Later revisions are intended to provide criteria for other facing directions. Performance criteria for forward and aft facing seats are provided in AS8049 and for side facing seats in AS8049/1. This document contains the same content as superseded ARP6316 with additional information included to align this Aerospace Standard with AS8049/1 regarding the use of
Aircraft Seat Committee
This procurement specification covers rivets fabricated from an aluminum alloy designated as 1100-H14, strain hardened
E-25 General Standards for Aerospace and Propulsion Systems
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