Results
This test method provides a procedure for measuring no-load rotational breakaway torque of self-lubricating spherical bearings.
This SAE Information Report establishes a uniform procedure for assuring the manufactured quality, installed utility, and performance of automotive remote steering controls other than those provided by the vehicle manufacturer (OEM). These products are intended to provide driving capability to persons with physical disabilities. The adaptive modifications seek to compensate for lost or reduced function in the extremities of the driver with a disability. Remote steering controls are designed to provide a steering input device alternative to the OEM steering wheel that either reduces the required input force, changes the required range of motion or changes the location of the steering control, or any combination of the above. These controls supplement by power, other than by the driver’s own muscular efforts, the force output of the driver with a disability. Because this is an Information Report, the numerical values for performance measurements presented in this report and in the
This SAE Aerospace Information Report (AIR) describes procedures for use in the field to determine if 115/200 Volt, 400 Hz aircraft external electrical power connectors are excessively worn, which may result in the inability of the external power plug to be retained, intermittent electrical performance, and arcing.
The primary objective of this recommended practice is to confirm that vehicles can communicate a minimum set of information in accordance with diagnostic test services specified in SAE J1979-2, or the equivalent ISO 14229-1:2013 (Ed. 2) and SAE J1979-3 documents. A successful result using the SAE J1699-5 Automotive Alliance for Innovation (AAI) software for OBD-II testing indicates that the main aspects of UDS communication have been examined, but it does not provide assurance of complete compliance with all aspects of SAE J1979-2 or SAE J1979-3. SAE J1699-5 tests run with a SAE J2534 device hardware and API that is not fully compliant will result in a test failure. This specification takes precedence over all conflicts in the documents cited in this section.
This SAE Information Report provides SAE’s recommendations for meeting the requirements for Real Emissions Assessment Logging (REAL) oxides of nitrogen (NOx) accuracy demonstration and for the implementation of REAL NOx binning requirements as defined in onboard diagnostics (OBD) regulations 13 CCR 1971.1 and 13 CCR 1968.2.
This specification covers a corrosion- and heat-resistant nickel alloy in the form of plate nominally 2.00 inches (50.8 mm) and under in thickness, inclusive.
This specification covers a corrosion- and heat-resistant cobalt alloy in the form of bars, forgings, flash-welded rings, and stock for forging or flash-welded rings.
This specification covers pure gold in the form of wire 0.005 to 0.040 inch (0.012 to 1.000 mm), inclusive, in nominal diameter and ribbon 0.002 to 0.051 inch (0.05 to 1.28 mm), inclusive, in nominal thickness (see 8.5).
This SAE Aerospace Standard (AS) contains landing gear strength and rigidity requirements which, in combination with other applicable specifications, define the structural design, analysis, test, and data requirements for fixed wing piloted airplanes. These requirements include, but are not limited to, the following: a General specifications: 1 The shock-absorption characteristics and strength of landing-gear units and the strength and rigidity of their control systems and of their carry-through structures. Requirements for wheels, tires, and brakes as they affect air vehicle ground loads are also included. 2 The strength of structures integral with the airplane provided for transmitting catapulting forces to the airplanes, and for engaging shipboard and shore-based arresting gear, and barricades. 3 The strength of anchor-line clamps, and the airplane strength for hoisting, jacking, towing, tie-down, and other ground- or deck-handling conditions. 4 Structural design, analysis, and test
This document establishes the requirements for screw-on type reattachable couplings for use in low temperature hose assemblies.
This Aerospace Recommended Practice (ARP) provides: Recommended methods for cleaning sample bottles, when used, and the solvents to be applied and how these solvents should be prepared. Recommendations for three measuring methods for determining the level of solid particle contamination of hydraulic fluids used in aerospace hydraulics. Recommendations for the selection of the sampling point, sampling method, and the sampling frequency.
This specification covers a high-temperature, electrical grade, polyimide resin adhesive in the form of film or paste.
This SAE Aerospace Information Report (AIR) provides design data reliability information relative to the long-term storage of gas containers or pressure vessels charged with nitrogen or helium at pressures ranging from 6000 to 12 000 psi. The gas containers are cylindrical, spherical, or toroidal in shape. Internal volumes range up to 1385 in3. Applications for this type cold gas actuation system include tactical missiles, guided projectiles, and smart bombs. A typical system is described.
This specification covers the specific requirements for 2014 aluminum alloy alclad plate and sheet; the general requirements are covered in AMS-QQ-A-250. The plate and sheet covered by this specification shall be an integral composite product consisting of a heat-treatable aluminum alloy (2014) core with thin layers of an aluminum alloy (6003) anodic to the core and of approximately equal thickness bonded to both surfaces.
This document applies to prognostics of aerospace propulsion systems. Its purpose is to define the meaning of prognostics in this context, explain their potential and limitations, and to provide guidelines for potential approaches for use in existing condition monitoring environments. This document also includes some examples. The current revision does not provide specific guidance on validation and verification, nor does it address implementation aspects such as computational capability or certification.
The purpose of this SAE Aerospace Standard (AS) is to standardize the basic design, performance, and testing requirements for “Cargo Stoppers” cargo tie-down accessories to be used in conjunction with approved restraint straps meeting AS5385C (TSO C-172) requirements.
This specification covers a manganese alloy in the form of powder, preforms, and a viscous mixture (paste) of the powder in a suitable binder.
This SAE Aerospace Standard (AS) specifies scarf-cut polytetrafluoroethylene (PTFE) retainers (backup rings) for use in static glands in accordance with AS5857. They are usually for use in hydraulic and pneumatic systems as anti-extrusion devices in conjunction with O-rings and other seals.
This document provides information to help the reader view maintainability in the context of an overall systems engineering effort. The guide defines maintainability, describes its relationship to other disciplines, addresses the basic elements common to sound maintainability programs, and describes the tasks and activities associated with those elements.
The primary objective of this document is to describe the systematic and random measurement uncertainties which may be expected when testing gas turbine engines in a range of different test facilities. The documentation covers a "traditional" method for estimating pretest uncertainties and a "new" method for computing and comparing posttest uncertainties. To determine these posttest uncertainties, data generated during the AGARD Uniform Engine Test Program (UETP) were analyzed and compared to the pretest estimates. The proposed procedure provides a mechanism for determining the expected accuracy of test results obtained from facilities which were not previously cross calibrated. Furthermore, the method can be used to assist in making cost-effective management decisions on the level of validation/cross calibration necessary when bringing a test facility on line. This document is also intended to act as a guide for improving uncertainty analyses in a broad spectrum of related industries
This report identifies the reasons for, and results associated with, the conduct of a flight simulation research project evaluating the effect of low powered laser beam illumination of pilot crewmembers operating in the navigable airspace. This evaluation was primarily concerned with the possible degradation of pilot performance when illuminated by a laser while operating in an airport terminal area where pilot workloads are normally at their maximum.
This specification covers aluminum alloy brazing sheet for use in brazed aluminum joints.
The primary purpose of the shipping closure is to protect the aircraft parts or system from damage and foreign material ingress/egress (e.g., dust, dirt or other contaminants) during transport and storage. Shipping closures are not airworthy items. Therefore, their usage is defined as preventative for the parts to be protected as opposed to operational. Military and commercial customer requirements for the prevention of damage or contamination to stored parts are generally limited to the generic instructions “all openings should be sufficiently covered to prevent the entrance of dust, dirt, moisture or other foreign contaminants”. This recommended practice outlines basic minimum parameters for suggested item construction and usage. Additionally, this recommended practice provides instruction on how to apply these closures to various openings.
The intent of this specification is for the procurement of the material listed on the QPL and, therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program shall refer to the Quality Assurance section of the base specification, AMS3961. All material qualification and equivalency data has been archived and is available for review upon request. Contact the CMH-17 Secretariat (www.cmh17.org) for additional information.
This document establishes the industry standard practices for marking standard elastomeric hose used in aircraft manufacture and repair.
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