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Viewing 91 to 120 of 45192
2017-11-10
WIP Standard
J2717
This SAE Recommended Practice describes a trio of test methods which determine basic tire size (geometry), mass, and moments of inertia. The methods apply to any tire so long as the equipment is properly scaled to conduct the measurements for the intended test tire. The data are suitable for determining parameters for road load models and for comparative evaluations of the measured properties in research and development. NOTE: Herein, road load models are models for predicting forces applied to the vehicle spindles during operation over irregular surfaces paved or unpaved. Within the context of this Recommended Practice, forces applied to the surface on which the tire is operating are not considered.
2017-11-10
WIP Standard
AMS6568/3
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness.
2017-11-10
WIP Standard
AMS6568/2
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness.
2017-11-10
WIP Standard
AMS6568/1
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness. This is the base specification and it will have three slash/detail specs.
2017-11-10
WIP Standard
AMS6566/1
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness. This is the base specification and it will have one slash/detail specs.
2017-11-09
WIP Standard
AIR5771A

This report covers engine tests performed in Altitude Test Facilities (ATFs) with the primary purpose of determining steady state thrust at simulated altitude flight conditions as part of the in-flight thrust determination process. As such it is complementary to AIR1703 and AIR5450, published by the SAE E-33 Technical Committee. The gross thrust determined using such tests may be used to generate other thrust-related parameters that are frequently applied in the assessment of propulsion system performance. For example: net thrust, specific thrust, and exhaust nozzle coefficients.

The report provides a general description of ATFs including all the major features. These are:

  • Test cell air supply system. This controls the inlet pressure and includes flow straightening, humidity and temperature conditioning.
  • Air inlet duct and slip joint. Note that the report only covers the case where the inlet duct is connected to the engine, not free jet testing.
2017-11-09
WIP Standard
ARP7204
This SAE Aerospace Recommended Practice (ARP) provides guidelines for the application of polymeric bearings/wear rings for linear actuation systems. Design considerations are included for recommended fit and function in conjunction with material selection and load bearing capability.
2017-11-09
WIP Standard
AIR1490C
Since the ULD device containing textiles should have a predictable service life, there should be data available so that predictions can be made. This document compiles available information on textiles of the types used in air cargo ULD devices and reviews the degradation characteristics of each. Textiles are used primarily in cargo restraint nets on air cargo pallets and nonstructural containers, restraint nets installed in cargo aircraft, and similar applications.
CURRENT
2017-11-09
Standard
AMS2451/12A
This specification covers the engineering requirements and process for brush plating of tin by electrodeposition. It shall be used, in conjunction with AMS2451, for general purpose tin deposits.
CURRENT
2017-11-09
Standard
AMS2451/13A
This specification covers the engineering requirements and process for brush plating of silver by electrodeposition. It shall be used, in conjunction with AMS2451, for silver deposits.
CURRENT
2017-11-09
Standard
AMS5442B
This specification covers a corrosion and heat-resistant nickel alloy in the form of bars, forgings, and flash welded rings up to 5.0 inches (127mm) in least nominal cross-sectional dimension having a cross-sectional area not greater than 50 in2 (323 cm2), and stock of any size for forging or flash welded rings (see 8.5).
CURRENT
2017-11-09
Standard
ARP594F
The requirements presented in this document address the key considerations for thermal safety in aircraft fuel pump design. Document sections focus on understanding safety relative to an electrically motor driven fuel pump assembly acting as an ignition source for explosive fuel vapors within the airplane tank.
CURRENT
2017-11-09
Standard
ARP991C
This document recommends design objectives for navigation, position, and anticollisionlight systems for visual detection and collision avoidance between airplanes in flight and on the ground. Customers for new airplanes or lighting components, and designers or manufacturers may take advantage of this document in specifying the initial requirements that, in most cases, significantly exceed the applicable minimum intensities as shown in the Federal Aviation Regulations as well provide better stability, longer life and lower operating costs.
CURRENT
2017-11-09
Standard
AS81582C
This specification covers environment-resisting, quick disconnect, EMI/RFI shielded and non-shielded umbilical, electric connectors and adapter assemblies with removable crimp or nonremovable solder-type contacts and accessories. Connectors are rated for operation from -55 °C (-67 °F) to 200 °C (392 °F). Adapter assemblies are rated for operation from -55 °C (-67 °F) to 125 °C (257 °F). The upper temperature is the maximum internal hot spot temperature resulting from any combination of electrical load and ambient temperature.
CURRENT
2017-11-09
Standard
AS6009A
This document defines a set of standard application layer interfaces called JAUS Mobility Services. JAUS Services provide the means for software entities in an unmanned system or system of unmanned systems to communicate and coordinate their activities. The Mobility Services represent the vehicle platform-independent capabilities commonly found across all domains and types of unmanned systems (referred to as UxVs). At present, over 15 services are defined in this document many of which were updated in this revision to support Unmanned Underwater Vehicles (UUVs). Some examples include:
2017-11-09
WIP Standard
AMS6562/2
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the second detail spec.
2017-11-09
WIP Standard
AMS6562/1
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the first slash/detail spec.
2017-11-09
WIP Standard
AMS6562/3
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the third detail spec.
CURRENT
2017-11-09
Standard
ARP9107A
Limited to the commercial aerospace industry where a request is made for a PO to have Direct Delivery Authorization (DDA), which includes an Appropriate Arrangement (AA) between the PO and the Design Organization (DO). In this process the DO is responsible for ensuring the continuous updating of design and airworthiness data to the PO, whilst the PO is responsible for assurance that the manufactured article conforms to approved design and airworthiness data. The PO is responsible to provide airworthiness release documentation.
CURRENT
2017-11-09
Standard
AMS5596M
This specification covers a corrosion and heat-resistant nickel alloy in the form of sheet, strip, foil, and plate 1.00 inch (25.4 mm) and under in thickness (see 8.5).
2017-11-08
WIP Standard
MA3374D
This document covers metric bolts and screws made from a corrosion and heat resistant, age hardenable iron base alloy of the type identified under the Unified Numbering System as UNS S66286. The following specification designations and their properties are covered: MA3374 900 MPa minimum ultimate tensile strength at room temperature; 480 MPa stress-rupture strength at 650 °C and MA3374-1 900 MPa minimum ultimate tensile strength at room temperature; 590 MPa minimum ultimate shear strength at room temperature.

Primarily for aerospace propulsion system applications where a combination of fatigue strength, tensile strength, stress-rupture strength and resistance to relaxation at elevated temperatures is required.

CURRENT
2017-11-08
Standard
AMS4403A
This specification covers an aluminum alloy in the form of die forgings 1.000 to 12.000 inches inclusive (25 to 305 mm) in nominal thickness at the time of heat treatment and of forging stock (see 8.4).
CURRENT
2017-11-08
Standard
AMS6516B
This specification covers a premium aircraft quality alloy steel in the form of bars and forgings 189 in2 (1219 cm2) and under in cross-sectional area and forging stock of any size.
CURRENT
2017-11-08
Standard
J2854_201711
The CRABI dummy was developed to evaluate small child restraint systems in automotive crash environments, in all directions of impact, with or without air bag interaction Basic anthropometry for this test device was taken from the University of Michigan Transportation Research Institute Report 85-23. Weight distribution and scaling methods for the infant were approved by the Society of Automotive (SAE) Infant Dummy Task Group. The dummy weighs 17.2 pounds and has a 26.4 inches standing or 17.3 inches sitting height. The Hybrid Ill-like neck and lumbar spine are laterally notched to reduce lateral stiffness The shoulders have flesh support for durability and human-like performance in areas where seatbelt webbing may be placed. In addition, rubber elements are used in each joint to improve biofidelity and to give the CRABI infant-like range of motion. The CRABI Six-Month-Old design meets all the SAE Infant Dummy Task Group anthropometry, biomechanical and instrumentation requirements.
CURRENT
2017-11-08
Standard
J1701M_201711
This SAE Information Report is provided as an advisory guide. Individual application discretion is recommended. The content has been presented as accurately as possible, but responsibility for its application lies with the user. The document covers a number of the variables in the torque-tension relationship: friction, materials, temperature, humidity, fastener and mating part finishes, surfaces, and the kind of tightening tools or equipment used.
Viewing 91 to 120 of 45192