Results
This document describes a process for use by ADHP integrators of EEE parts and sub-assemblies (items) that have been targeted for other applications2. This document does not describe specific tests to be conducted, sample sizes to be used, nor results to be obtained; instead, it describes a process to define and accomplish application-specific qualification; that provides confidence to both the ADHP integrators, and the integrators’ customers, that the item will performs its function(s) reliably in the ADHP application.
This SAE Aerospace Standard (AS) prescribes requirements for the various types of nozzles that are used for the refueling and defueling of aircraft fitted with pressure fuel servicing systems. It is to be used as a replacement for MIL-N-5877, MS29520 and for all commercial applications.
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.
The purpose of this document is to establish the requirements for Real-Time Communication Protocols (RTCP). Systems for real-time applications are characterized by the presence of hard deadlines where failure to meet a deadline must be considered a system fault. These requirements have been driven predominantly, but not exclusively, by aerospace type military platforms and commercial aircraft, but are generally applicable to any distributed, real-time, control systems. These requirements are primarily targeted for the Transport and Network Layers of peer to peer protocols, as referenced in the Open System Interconnect Reference Model (2.2.1 and 2.2.2), developed by the International Standards Organization (ISO). These requirements are intended to complement SAE AS4074 (2.1.1) and AS4075 (2.1.2), and future SAE communications standards. Although information transfer objectives herein concentrate primarily on digital data flow attributes, efforts have been made such as not to preclude
This SAE Aerospace Recommended Practice (ARP) provides guidance for substantiating the airworthiness of aircraft engine components. Generally these components are associated with the engine control system, the system or systems that allow the engine to provide thrust or power as demanded by the pilot of the aircraft while also ensuring the engine operates within acceptable operating limits. But these components may also include hardware and systems associated with engine lubrication, engine or aircraft hydraulic or electrical systems, aircraft environmental control systems, thrust reverser control, or similar aircraft or engine propulsion system functions. This paper develops the concept of using a 26 item matrix of environmental conditions for evaluating aircraft engine component airworthiness. This approach is compatible with current practices used in the industry and has been accepted by engine certification authorities as part of engine certification programs.
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 (10340 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.
This Aerospace Information Report (AIR) has been prepared by the Systems Applications and Requirements Subcommittee of SAE Committee AS-2. It is intended to provide guidance primarily, but not exclusively, for specifiers and designers of data communication systems for real time military avionics applications within a platform. The subject of high speed data transmission is addressed from two standpoints: (1) the influence of developments in technology on avionics architectures as a whole and (2) the way in which specific problems, such as video, voice, closed loop control, and security may be handled. While the material has been prepared against a background of experience within SAE AS-2 relating to the development of a family of high speed interconnect standards, reference to specific standards and interconnect systems is minimized. It should be noted, however, that many of the concepts described require interconnect systems with advanced operational and performance characteristics
This specification covers minimum requirements for brake temperature monitoring equipment whenever used on any type and model of civil aircraft. It shall be the responsibility of the purchaser to determine the compatibility of these requirements with the application aircraft and to specify requirements in excess of these minimums as necessary.
This metric SAE Aerospace Information Report (AIR) details a ball-on-cylinder (BOC) test device and specifies a method of rating the relative lubricity of aviation turbine fuel samples. The BOC produces a wear scar on a stationary steel ball by forcing it with a fixed load against a fuel wetted steel test ring in a controlled atmosphere. The test ring is rotated at a fixed speed so its surface is wetted by a momentary exposure to the fluid under test. The size of the wear scar is a measure of the test fluid lubricity and provides a basis for predicting friction or wear problems.
This AIR provides guidance to the EMI test facility on how to check performance of the following types of EMI test equipment: Current probe Line Impedance Stabilization Network (LISN) Directional coupler Attenuator Cable loss Low noise preamplifier Rod antenna base Passive antennas All performance checks can be performed without software. A computer may be required to generate an electronic or hard copy of data. This is not to say that custom software might not be helpful; just that the procedures documented herein specifically eschew the necessity of automated operation.
Applications include specifications, reports, ratings, texts etc., where fluid leakage rates are treated.
Items per page:
50
1 – 50 of 211952