Search
Advanced Search
of the following are true

Results

Items (206,871)
This document provides general and specific design guidance for the development of software data loading equipment for all types of aircraft. The primary purpose of data load is to upload loadable software parts to airborne computers. A secondary function of data load is downloading data from airborne computers. Software data load functionality generally falls into the following categories: Portable Data Loader (PDL) for loading equipment on the ground or carried onto aircraft to perform onboard loading. Airborne Data Loader (ADL) for installation on aircraft to perform onboard loading. Data Load Function (DLF) is software that performs the data loading. This document defines data loaders designed to load avionics equipment over a high-speed interface using an Ethernet network protocol. This document defines media interfaces and protocol requirements specific to all data load functions, whether portable or airborne. This document also describes the desired capabilities of data loading
Airlines Electronic Engineering CommitteeAvionics Maintenance CommitteeFlight Simulator Engineering and Maintenance Committee
This document is intended to supplement the SAE J1939 documents by offering the SAE J1939 information in a form that can be sorted and search for easier use
Truck Bus Control and Communications Network Committee
The purpose of this SAE Aerospace Information Report (AIR) is to provide guidance for aircraft engine and propeller systems (hereafter referred to as propulsion systems) certification for cybersecurity. Compliance for cybersecurity requires that the engine control, propeller control, monitoring system, and all auxiliary equipment systems and networks associated with the propulsion system (such as nacelle systems, overspeed governors, and thrust reversers) be protected from intentional unauthorized electronic interactions (IUEI) that may result in an adverse effect on the safety of the propulsion system or the airplane. This involves identification of security risks, their mitigation, verification of protections, and their maintenance in service. This document is intended to serve as suitable guidance for propulsion system manufacturers and applicants for propulsion system type certification. It is also intended to provide guidance for subsequent propulsion system integration into
E-36 Electronic Engine Controls Committee
The aviation, space, and defense industries rely on the development and manufacture of complex products comprised of multiple systems, subsystems, and components each designed by individual designers (design activities) at various levels within the supply chain. Each design or manufacturing activity controls various aspects of the configuration and specifications related to the product. When a change to design or process is requested or required, the change is typically required to be evaluated against the impacts to the entire system. Proposed changes to design data/information that the design activity identifies to be minor and have no effect on the product requirements or specifications, have the potential to be implemented and approved, where authorized to do so, but requires notification. Changes that affect customer mandated requirements or specifications shall be approved prior to implementation. In many cases, the design activity is not conducted by the DAH or design authority
G-14 Americas Aerospace Quality Standards Committee (AAQSC)
This SAE Aerospace Recommended Practice (ARP) addresses the general procedure for the best practices for minimizing uncertainty when calibrating thermal conductivity and cold cathode vacuum gauges, which includes the vacuum sensor(s) and accompanying electronics necessary for a pressure measurement to be made. It also includes the best practices for an in-process verification where limitations make it impossible to follow the best practices for minimizing uncertainty. Verifying the accuracy and operation of vacuum gauges is critical to ensure the maintenance of processes while under vacuum
AMS B Finishes Processes and Fluids Committee
This specification covers a corrosion-resistant steel in the form of sheet, strip, and plate 0.005 to 1.000 inches (0.13 to 25.40 mm) in nominal thickness in the solution heat-treated condition
AMS F Corrosion and Heat Resistant Alloys Committee
AS8049A currently requires adjustable features on aircraft seats to be designed so they can be returned to the positions required for taxi, takeoff and landing by the occupant without the release of the occupant restraints. This ARD will demonstrate Aviation Industry support for revisions to TSO-C39c and TSO-C127a to allow Technical Standard Order (TSO) approval of aircraft seat products designed with adjustable features that require the release of occupant restraints to return the feature to the taxi, takeoff and landing position
null, null
The high-temperature deposition test (HTDT) method is designed to evaluate the deposition and degradation characteristics of turbine lubricants when stressed under mixed-phase flow conditions found in certain parts of aviation gas turbine engines. This method is applicable to lubricants that form deposits in the range of 0.1 to 100 mg during the course of a test
E-34 Propulsion Lubricants Committee
To present methods which, according to the consensus of the aviation propulsion community represented by SAE Committee E-34, allow the continued assessment of load carrying capacity of current chemistry products during periods of limited or nonavailability of previously used standardized methods
E-34 Propulsion Lubricants Committee
This specification covers manufacturing tolerances applicable to seamless and welded tubing of corrosion and heat resistant steel ordered to metric dimension. These tolerances apply to all conditions and are based on individual measurements, unless otherwise noted. Tubing may be specified by two dimensions only (OD and wall thickness, ID and wall thickness, or OD and ID
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers steel cleanliness requirements in metric SI units for special aircraft-quality ferromagnetic steels, other than hardenable corrosion resistant steels, by magnetic particle inspection methods
AMS E Carbon and Low Alloy Steels Committee
Over the past two and one-half decades several metal clad fibers and fabrics have been developed to provide aerospace vehicle designers with a conductive, lighter weight alternative to coated copper, coated stainless steel and steel wire used for cable and wire shielding and harness overbraids on electrical cables. Several of these candidates have been unable to provide the strength or thermal stability necessary for the aerospace environment. However, several polymer-based products have shown remarkable resistance to the rigorous environment of aerospace vehicles. Concurrent with these fiber developments, there have been changes in the structures of aerospace vehicles involving greater use of nonmetallic outer surfaces. This has resulted in a need for increased shielding of electrical cables which adds substantial weight to the vehicle. Thus, a lighter weight shielding material has become more critical to meet the performance requirements of the vehicle. This report covers the
AE-8D Wire and Cable Committee
This specification covers the engineering requirements for electrodeposition of silver on other metals, usually with a nickel strike between the basis metal and the silver, and the properties of the deposit. AMS 2410 is the inch/pound version of this MAM. This processes has been used typically to provide a bearing surface and to prevent galling or seizing of surfaces of parts made of corrosion-resistant steels and alloys and of parts made of other metals not deleteriously affected by high-temperature baking, but usage is not limited to such applications
AMS B Finishes Processes and Fluids Committee
This specification provides requirements and procedures for hydraulic-pressure leak testing of parts
AMS B Finishes Processes and Fluids Committee
This specification provides requirements and procedures for hydraulic-pressure leak testing of parts. AMS 2625 is the inch/pound version of this MAM
AMS B Finishes Processes and Fluids Committee
This specification covers cotter pins made to metric dimensions from a corrosion and heat resistant steel
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers established metric manufacturing tolerances applicable to aluminum alloy drawn tubing ordered to metric dimensions. These tolerances apply to all conditions, unless otherwise noted. The term "excl" applies only to the higher figure of the specified range
AMS D Nonferrous Alloys Committee
This specification covers established metric manufacturing tolerances applicable to copper and copper alloy seamless tubing ordered to metric (SI) dimensions. These tolerances apply to all conditions, unless otherwise noted. The term "exclusive" is used to apply only to the higher figure of a specified range
AMS D Nonferrous Alloys Committee
This specification covers established metric manufacturing tolerances applicable to bars and rods of copper and copper alloys ordered to metric dimensions. These tolerances apply to all conditions, unless otherwise noted. The term "exclusive" is used to apply only to the higher figure of a specified range
AMS D Nonferrous Alloys Committee
This specification covers established metric manufacturing tolerances applicable to copper and copper alloy sheet, strip, and plate ordered to metric dimensions. These tolerances apply to all conditions, unless otherwise noted
AMS D Nonferrous Alloys Committee
This specification covers a nickel alloy in the form of wire, rod, strip, foil, and powder and a viscous mixture (paste) of the powder in a suitable binder and procured in metric units. AMS 4778 is the inch/pound version of this MAM. This filler metal has been used typically for joining corrosion and heat resistant steels and alloys requiring corrosion and oxidation resistant joints with good strength at elevated temperatures, but usage is not limited to such applications. Also may be used as a corrosion and oxidation resistant hard coating
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers an aluminum alloy in the form of hand forgings and rolled rings procured to metric (SI) dimensions. These products have been used typically for complex shaped parts requiring moderate strength and good forgeability of the alloy and where stability is required during machining, but usage is not limited to such applications. Corrosion resistance of this alloy is superior to that of aluminum alloys having copper as the principal alloying element
AMS D Nonferrous 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 5599, specified in inch/pound version of this MAM. These products have been used typically for parts requiring corrosion and oxidation resistance up to 1095 degrees C, particularly where such parts may require welding during fabrication, but usage is not limited to such applications
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock procured in SI (Metric) units. AMS 6415 is the inch/pound version of this MAM. These products have been used typically for parts, 90 millimeters and under in nominal thickness at time of heat treatment, requiring a through-hardening steel capable of developing a minimum hardness of 40 HRC when properly hardened and tempered and also for parts of greater thickness but requiring proportionately lower hardness, but usage is not limited to such applications. Certain design and processing procedures may cause these products to become susceptible to stress-corrosion cracking after heat treatment; ARP 1110 recommends practices to minimize such conditions
AMS E Carbon and Low Alloy Steels Committee
This specification covers an aluminum alloy in the form of sheet procured in metric units. Primarily for parts requiring a high degree of formability (superplasticity) and response to heat treatment
AMS D Nonferrous Alloys Committee
This SAE Systems Management Standard specifies the Habitability processes throughout planning, design, development, test, production, use and disposal of a system. Depending on contract phase and/or complexity of the program, tailoring of this standard may be applied. Appendix C provides guidance on tailoring standard requirements to fit the various DoD acquisition pathways. The primary goals of a contractor Habitability program include: Ensuring that the system design complies with the customer Habitability requirements and that discrepancies are reported to management and the customer. Identifying, coordinating, tracking, prioritizing, and resolving Habitability risks and issues and ensuring that they are: ◦ Reflected in the contractor proposal, budgets, and plans. ◦ Raised at design, management, and program reviews. ◦ Debated in working group meetings. ◦ Coordinated with Training, logistics, and the other HSI disciplines. ◦ Included appropriately in documentation and deliverable
G-45 Human Systems Integration
This specification establishes the requirements for a hard anodic coating on aluminum and aluminum alloys
AMS B Finishes Processes and Fluids Committee
This specification covers steel cleanliness requirements in SI (Metric) units for aircraft-quality, ferromagnetic, hardenable, corrosion-resistant steels as determined by magnetic particle inspection methods. This specification contains sampling, specimen preparation, and inspection procedures and cleanliness rating criteria
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers a water resistant lubricant in the form of grease procured in metric units
AMS M Aerospace Greases 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 5598 is the inch/pound version of this MAM
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers established metric manufacturing tolerances applicable to low-alloy steel bars ordered to metric dimensions. These tolerances apply to all conditions, unless otherwise noted. The term 'exclusive' is used to apply to the higher figure of the specified range
AMS E Carbon and Low Alloy Steels Committee
This specification covers procedures for identifying carbon and low-alloy steels, corrosion- and heat-resistant steels and alloys, maraging and other highly alloyed steels, and iron alloy sheet, strip, and plate, and aircraft tubing
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers steel cleanliness requirements in metric (SI) units for premium 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 provides requirements and procedures for air-pressure leak testing of parts
AMS B Finishes Processes and Fluids Committee
This specification covers established metric manufacturing tolerances applicable to low-alloy steel sheet, strip, and plate ordered to metric dimensions. These tolerances apply to all conditions unless otherwise noted. The term 'excl' is used to apply only to the higher figure of the specified range
AMS E Carbon and Low Alloy Steels Committee
This specification covers a corrosion and heat resistant steel in the form of welding wire. AMS 5822 is the inch/pound version of this MAM. This product has been used typically as bare filler metal for gas-metal-arc or gas-tungsten-arc welding of steels of similar composition, but usage is not limited to such applications
AMS F Corrosion and Heat Resistant Alloys Committee
The intent is to provide a reference which explains the types of possible changes to AS5780 products and provide appropriate context to the QPG. All product change requests to the QPG will be evaluated on their merits recognizing the content of this AIR is guidance only
E-34 Propulsion Lubricants Committee
This method is designed to evaluate the coking propensity of synthetic ester-based aviation lubricants under single phase flow conditions found in certain parts of gas turbine engines, for instance in bearing feed tubes. This method is applicable to lubricants with a coking propensity, as determined by this method, falling in the range 0.01 to 5.00 mg
E-34 Propulsion Lubricants Committee
Employing ‘ball-on-cylinder’ philosophy, a non-rotating steel ball is held in a vertically mounted chuck and using an applied load is forced against an axially mounted steel cylinder. The test cylinder is rotated at a fixed speed while being partially immersed in a lubricant reservoir. This maintains the cylinder in a wet condition and continuously transports a lubricating film of test fluid to the ball and cylinder interface. The diameter of the wear scar generated on the test ball is used as a measure of the fluid’s lubricating properties. The apparatus can be used, by adjusting the operating conditions, to reproduce two different wear mechanisms; mild and severe wear, the ALTE therefore has the ability to assess a lubricant’s performance in that regard. These mechanisms are described below
E-34 Propulsion Lubricants Committee
The lubricant performance capability for aero propulsion drive systems is derived from the physical properties of the oil and the chemical attributes associated with the oil formulation. All properties, such as viscosity, pressure-viscosity coefficient and full-film traction coefficient are inherent properties of the lubricating fluid. Chemical attributes are critical for the formation of protective boundary lubricating films on the surfaces to prevent wear and scuffing. To assure performance and to provide needed information for engineering design, test methodologies for at least five oil properties or attributes are being addressed: (1) pressure-viscosity coefficient, (2) full-film traction coefficient, (3) scuffing resistance, (4) wear resistance, and (5) micropitting propensity. While viscosity versus temperature data are readily available, the above five properties or attributes must be measured under relevant conditions for aero propulsion hardware systems. This document (ARP6156
E-34 Propulsion Lubricants Committee
This method is intended to evaluate the thermal and oxidative stability of synthetic, ester-based aviation lubricants under defined conditions of time and temperature. This method is applicable to lubricants meeting the compositional and performance requirements of AS5780
null, null
The lubricant performance capability for aero propulsion drive systems is derived from the physical properties of the oil and performance attributes associated with the chemical properties of the oil. Physical properties, such as viscosity, pressure-viscosity coefficient and full-film traction coefficient are inherent properties of the lubricating fluid. Chemical attributes are critical for the formation of protective boundary lubricating films on the surfaces to prevent wear and scuffing. These attributes are also associated with surface initiated fatigue (micropitting). To assure performance and to provide required information for engineering design, methodology for at least five oil properties are being studied: (1) pressure-viscosity coefficient, (2) full-film traction coefficient, (3) scuffing resistance, (4) wear resistance, and (5) micropitting propensity. The pressure-viscosity coefficient can be measured either directly by assessing viscosity as a function of pressure using
E-34 Propulsion Lubricants Committee
This AIR describes the current scientific and engineering principles of gas turbine lubricant performance testing per AS5780 and identifies gaps in our understanding of the technology to help the continuous improvement of this specification
E-34 Propulsion Lubricants Committee
This specification covers a neopentyl polyol ester fluid (see 8.2) with AS5780 HPC or MIL-PRF-23699 HTS Class performance
E-34 Propulsion Lubricants Committee
The test method describes the procedure for determination of the total acid number (TAN) of new and degraded polyol ester and diester-based gas turbine lubricants by the potentiometric titration technique. The method was validated to cover an acidity range of 0.05 to 6.0 mg KOH g-1. The method may also be suitable for the determination of acidities outside of this range and for other classes of lubricants
E-34 Propulsion Lubricants Committee
Items per page:
1 – 50 of 206871