Search
Advanced Search
of the following are true

Results

Items (207,264)
The technical architecture defined in this document outlines mandatory, emerging, and needed standards to provide interoperability at key interfaces in the aircraft/store system (including an associated NATO Network Enabled Capability environment), as required to support a future plug-and-play aircraft/store integration capability. These standards relate to services and protocols associated with the subject interfaces. Modeling standards to facilitate the Model Driven Architecture® (MDA®) approach to system definition and implementation are also included. Note that the status of referenced standards as reflected in this document is as of August 2007, and document users should check to see if there has been a subsequent change of status relative to applicable standards
AS-1B Aircraft Store Integration Committee
This specification covers steel cleanliness requirements in SI (metric) units for aircraft-quality ferromagnetic steels, other than hardenable corrosion-resistant steels, by magnetic particle inspection methods
AMS E Carbon and Low Alloy Steels Committee
This specification covers a corrosion and heat resistant nickel alloy in the form of bars, forgings, flash welded rings, and stock for forging, flash welded rings, or heading procured in SI (metric) units. AMS 5706 is the inch/pound version of this MAM. These products have been used typically for parts, such as fasteners, flanges, and rings, requiring high strength up to 815 degrees C and oxidation resistance up to 955 degrees C, particularly those parts which are formed or welded and then heat treated to develop required properties, but usage is not limited to such applications
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers a corrosion and heat resistant nickel alloy in the form of sheet, strip, and plate procured in SI (metric) units. AMS 5536 is the inch/pound version of this MAM. These products have been used typically for parts requiring oxidation resistance up to 1205 degrees C and relatively high strength up to 815 degrees C, but usage is not limited to such applications
AMS F Corrosion and Heat Resistant Alloys Committee
This Aerospace Standard covers two basic Stall Warning Systems, one measures air flow and pressure distribution on the airfoil and the other measures the angle of airflow with respect to an arbitrary reference line. Each type of system includes, as a minimum, a sensor and the means for activating a device which warns the pilot of an impending stall
A-4 Aircraft Instruments Committee
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This document presents minimum criteria for the design and installation of LED passenger reading light assemblies in commercial aircraft. The use of “shall” in this specification expresses provisions that are binding. Non-mandatory provisions use the term “should
A-20C Interior Lighting
The purpose of this SAE Aerospace Recommended Practice (ARP) is to provide the aerospace industry with recommendations concerning the minimization of stress corrosion cracking in wrought heat-treatable carbon and low alloy steels and in austenitic, precipitation hardenable, and martensitic corrosion-resistant steels and alloys. The detailed recommendations are based on laboratory and field experience and reflect those design practices and fabrication procedures which should avoid in-service stress corrosion cracking
AMS E Carbon and Low Alloy Steels Committee
The purpose of this document is to provide an introduction and overview of the ARINC 628 series of Specifications. ARINC 628 defines equipment and installation standards for cabin equipment, which is generally defined as communication and entertainment equipment designed for passenger use. Part 0 provides the concepts and overview of ARINC 628 and descriptions of each individual part. Appendix B is written in briefing chart format to facilitate the user in preparing quick-reaction overhead projection-type presentations. Supplement 3 represents a summary of recent changes to Parts 1 through 9 of ARINC Specification 628
Airlines Electronic Engineering Committee
The Advanced FMCS provides expanded functions beyond that defined in ARINC 702 to support the anticipated requirements for operation in the CNS/ATM operating environment. GNSS and RNP based navigation, air-to-ground data link for communications and surveillance, and the associated crew interface control/display definitions are included
Airlines Electronic Engineering Committee
This standard sets forth the desired interface characteristics of the data link service provider to the data link user. Provides data link users the information needed to develop applications and to encourage uniformity and standardization (to the extent possible) among various data link service providers. Contains general and specific guidance concerning the interfaces between the data link service providers and both the airborne and ground user
Airlines Electronic Engineering Committee
The reader of specifications sometimes needs help understanding the format of an AMS and reasoning behind certain usage of terms. The scope of this AIR is to explain the functions of the various sections of the specifications, why some of the terms in AMS specifications are used, and how the specification system works. After the introduction (Section 3 of this document), the topics are presented in the order they usually appear in specifications
Aerospace Materials Systems Group
This document describes a method for measuring forces during an impact between a soft or frangible projectile and a relatively rigid flat normal surface. The document describes the hardware and instrumentation required, as well as the processing and data reduction required to compute force. In this test, a projectile impacts one end of a long cylindrical bar with flat ends, called a Hopkinson bar. The impact occurs on the centerline of the bar in the axial direction. The diameter of the cylindrical bar is large compared to the lateral dimension of the projectile so that, during and after the impact, the projectile material moves radially or backward, rather than extruding around the perimeter of the impact surface. The bar is instrumented with strain gages at some distance from the impacted end to measure the longitudinal strain in the bar. The bar must be sufficiently long so that the duration of the impact is less than the time it takes for the transient stress wave generated by the
G-28 Simulants for Impact and Ingestion Testing Committee
This SAE Aerospace Standard (AS) specifies minimum operation performance requirements for helicopter hoists. This document covers criteria for hoist systems that are intended for use on helicopter platforms for a variety of missions, including but not limited to, search and rescue (SAR) operations, fire control/support, offshore windfarm maintenance, transferring harbor pilots, and power line maintenance. Helicopter hoist minimum performance characteristics are specified for standard and other environmental conditions for the purpose of product qualification. Compliance with this standard is not considered approval for installation on any aircraft
G-26 Helicopter Hoists
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This document is an annex to EIA Engineering Bulletin SSB-1, Guidelines for Using Plastic Encapsulated Microcircuits and Semiconductors in Military, Aerospace and Other Rugged Applications (the latest revision). This document provides reference information concerning acceleration factors commonly used by device manufacturers to model failure rates in conjunction with statistical reliability monitoring. These acceleration factors are frequently used by OEMs in conjunction with physics of failure reliability analysis to assess the suitability of plastic encapsulated microcircuits and semiconductors for specific end use applications
CE-12 Solid State Devices
This document provides an approach to the development of training topics for pilots of Unmanned Aircraft Systems (UAS) for use by operators, manufacturers, and regulators. The identification of training topics is based initially on Practical Test Standard (PTS) topics for manned aircraft pilots. The topics identified could be used for the construction of a PTS for UAS commercial pilot operations and a PTS for a UAS pilot instrument rating. The UAS commercial pilot rating would contain restrictions on the types of operations that could be flown that would be dependent on the type of UAS used. The UAS type would also influence the specific training topics that would be covered. This document is not intended to outline the requirements for other crewmembers, such as observers, payload operators, or ground personnel, nor does it distinguish between different levels of pilot authority or discuss the roles for pilot-in-command, supplemental pilot, or observer. The recommendations outlined in
G-10U Unmanned Aerospace Vehicle Committee
The purpose of this Standard is to support the development and improvement of systems engineering capability
G-47 Systems Engineering
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This SAE Information Report (AIR) provides descriptions of High Lift Systems of commercial and military aircraft. The main focus is on mechanical systems which may be actuated hydraulically or electrically
A-6B3 Electro-Mechanical Actuation Committee
This SAE Aerospace Information Report (AIR) provides guidance on the definition, development, integration, qualification/certification, and deployment of Structural Health Monitoring (SHM) technologies applied to commercial and military rotorcraft. Increased implementation of SHM is believed to have numerous potential benefits, including enhanced operational safety and reduced maintenance burden. The focus is on augmenting ARP6461 to address specific unique aspects of implementing SHM on rotorcraft without unnecessarily duplicating guidance already contained in the ARP that is generally applicable to both fixed-wing and rotary-wing aircraft. For the purpose of this document, SHM is defined as “the process of acquiring and analyzing data from on-board sensors in order to determine the health of a structure”. Note that this is irrespective of whether the on-board sensors are a permanent or temporary installation. On-board sensors could include any presently installed aircraft sensors as
Aerospace Industry Steering Committee on Structural Health
This document covers the general recommendations for Transverse Electromagnetic Mode (TEM) Transmission Lines intended for use in airborne systems (see 6.2.14). For U.S military applications, TEM Transmission Lines shall meet the requirements in accordance with MIL-T-81490. The follow index lists the recommended requirements and methods covered by the Aerospace Recommended Practice (ARP
AE-8A Elec Wiring and Fiber Optic Interconnect Sys Install
This specification covers an aluminum alloy in the form of sheet 0.040 to 0.249 inches (1.02 to 6.32 mm), inclusive, in nominal thickness (see 8.5
AMS D Nonferrous Alloys Committee
This SAE Aerospace Recommended Practice (ARP) provides design guidelines for aircraft mechanical control systems and components. Topics contained in this document include design requirements, system design and installation guidelines, and component design practices for primary flight controls, secondary flight controls, and utility controls
A-6A3 Flight Control and Vehicle Management Systems Cmt
This procurement specification covers aircraft-quality solid rivets and tubular end rivets made from a corrosion- and heat-resistant nickel alloy of the type identified under the Unified Numbering System as UNS N06002
E-25 General Standards for Aerospace and Propulsion Systems
This standard specifies the characteristics of the MJ profile metric series of screw threads, altered from ISO 68 M Profile, to include a mandatory controlled radius of 0.18042P to 0.15011P at the root of the external thread and with the minor diameter of both external and internal threads increased to provide a basic thread height of 0.5625H in order to accommodate the external thread maximum root radius. The following detailed requirements are included: a MJ basic profile and design profiles b Standard series of diameter-pitch combinations for nominal thread diameters from 1.6 to 200 mm c Standard thread classes and form tolerances d Formulae for thread dimensions and tolerances e Method of designating MJ threads f Inspection requirement g Tables for selected diameter-pitch combinations for aerospace screws, bolts, nuts, shaft and bearing retaining screw threads, and fluid fittings thread sizes h Tables for MJ screw threads limiting dimensions and tolerances i Symbols for MJ thread
E-25 General Standards for Aerospace and Propulsion Systems
This method is used for determining the compatibility of a candidate lubricant with specific reference lubricants. The reference lubricants to be used will typically be mandated by the owner of the product specification against which the candidate lubricant is being compared. This method is split into two procedures (Procedure A and Procedure B) with a summary of each procedure contained in Section 4
E-34 Propulsion Lubricants Committee
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This standard applies to the aerospace and defense industries and their supply chains
E-1 Environmental Committee
This specification covers the requirements for flexible shielded electrical conduit for aircraft installations
AE-8A Elec Wiring and Fiber Optic Interconnect Sys Install
The purpose of this standard is to provide uniform methods for defining, quantifying, and classifying the residual stress in metallic structural alloy products and finished parts. These stresses may exist within a single element, or they may be the result of a joining process. Such quantification and classification may be required when residual stresses within mill stock or preforms can impact further in-process distortion during machining or other processes, and when residual stresses within finished components can impact final mechanical properties and performance (especially strength, durability, and fracture performance
null, null
This is an initial release of a recommended practice for an interface to supplier simulations that utilize traditional inter-process communication (IPC) methods of shared memory and semaphore communications. These IPC methods are standard practice in the computer science world and allow for communication by separate processes running on a computer without any common runtime requirements. This allows things like 32-bit applications to talk with 64-bit applications, as well as any other compiler version or runtime library dependencies being required by the calling program to interface with the called model. This also allows the calling program and the called program to be run on separate CPUs to allow parallel execution of the called program as well as multiple instances of the called program to execute all on separate processors. Also, other third party applications would be able to interact with this common IPC interface allowing an interface where no compilation or integration of
S-15 Gas Turbine Perf Simulation Nomenclature and Interfaces
Items per page:
1 – 50 of 207264