Results
This SAE Aerospace Standard (AS) provides a standardized test procedure that can be used to evaluate material capability in a dynamic sealing application. This procedure will be utilized by applicable elastomer material specifications which are used for production of O-rings and other seals. This specification is applicable to the dynamic testing requirements for aerospace elastomer parts utilizing materials conforming to AMS7XXX series specifications, user specifications, or print on a Purchase Order (PO) that calls out this document for aerospace applications. This procedure is intended for testing NBR. Other elastomers may have different requirements which will require a separate procedure.
This SAE Aerospace Standard (AS) defines the requirements for loop-type clamps primarily intended for general clamping of tubing for aircraft hydraulic systems.
This specification covers a corrosion- and heat-resistant nickel alloy in the form of sheet, strip, and plate up to 1.000 inch (25.40 mm) in nominal thickness.
This specification covers an aircraft-quality, low-alloy steel in the form of sheet, strip, and plate.
This standard is intended to apply to portable compressed gaseous oxygen equipment. When properly configured, this equipment is used either for the administration of supplemental oxygen, first aid oxygen or smoke protection to one or more occupants of either private or commercial transport aircraft. This standard is applicable to the following types of portable oxygen equipment: a Continuous flow 1 Pre-set 2 Adjustable 3 Automatic b Demand flow 1 Straight-demand 2 Diluter-demand 3 Pressure-demand c Combination continuous flow and demand flow.
This specification covers a high-strength, corrosion-resistant alloy in the form of bar up to 1.75 inches (44.4 mm) in diameter (see 8.2).
This specification covers an aluminum alloy in the form of sheet and plate 0.020 to 6.000 inches (0.551 to 152.4 mm), inclusive, in thickness (see 8.6).
This SAE Aerospace Recommended Practice (ARP) covers a brief discussion of the icing problem in aircraft fuel systems and the different means that have been used to test for icing. Fuel preparation and icing test procedures for aircraft fuel systems and components are proposed herein as a recommended practice to be used for fixed wing and rotary-wing aircraft within their operational environment. This ARP mostly addresses aircraft fuel system level testing and provides a means to address the requirements of FAR 14 CFR § 23.951(c), § 25.951(c), § 27.951(c), and § 29.951(c). In the context of this ARP, the engine and the auxiliary power unit (APU) are not considered to be components of the aircraft fuel system. However, some of the methods described in this document can be applied to the engine, APU, and other aircraft (system or component level) icing tests. This revision does not completely address new developments in ice accretion and release resulting from internal flow in tubing
This specification covers a petroleum base material in the form of a liquid.
This SAE Aerospace Standard (AS) establishes the requirements for fluid fittings that combine both 24° cone flareless and 37° flared connections for use in all types of fluid systems.
This SAE Aerospace Standard (AS) establishes the requirements for bite type sleeves for use with 24° cone flareless fluid connection fittings per AS4444.
This specification covers a corrosion-resistant steel in the form of sheet, strip, and foil.
This SAE Recommended Practice provides standard dimensions for liquid fuel dispenser nozzle spouts and a system for differentiating between nozzles that dispense liquid fuel into vehicles with spark ignition (SI) engines and compression ignition (CI) engines for land vehicles. Current legal definitions only distinguish between “Unleaded Fuel” and “All Other Types of Fuel.” These definitions are no longer valid. This document establishes a new set of definitions that have practical application to current automobile liquid fuel inlets and liquid fuel dispenser nozzle spouts.
This specification covers the procurement of granular heat-treating salts suitable for use in the molten state.
This SAE Standard was developed to provide a method for indicating the direction of engine rotation and numbering of engine cylinders. The document is intended for use in designing new engines to eliminate the differences which presently exist in industry.
This part of SAE J514 covers general and dimensional specifications for NPTF pipe adapters and 30 degree NPSM adapter unions. These fittings are intended for general application in hydraulic systems on industrial equipment and commercial products. These fittings are capable of providing leak-proof, full-flow connections in hydraulic systems operating at working pressures as specified in Table 6. Since many factors influence the pressure at which a hydraulic system will or will not perform satisfactorily, the values shown in Table 6 should not be construed as a guaranteed minimum. For any application, it is recommended that sufficient testing be conducted and reviewed by both the user and fitting manufacturer to assure that performance levels will be safe and satisfactory.
This specification covers a corrosion and heat-resistant nickel alloy in the form of sheet, strip, and plate up to 1.000 inch (25.40 mm) in nominal thickness (see 8.7).
This SAE Aerospace Standard (AS) defines the requirements for loop type clamps primarily intended for general clamping of tubing for aircraft hydraulic systems.
This specification covers a high-strength, corrosion-resistant alloy in the form of bars up to 1.75 inches (44.4 mm) in diameter (see 8.2).
This specification covers an aircraft-quality, low-alloy steel in the form of sheet, strip, and plate.
This specification covers an iron-nickel alloy in the form of strip 0.020 to 0.1874 inch (0.51 to 4.760 mm), inclusive, in nominal thickness.
This specification covers an aluminum alloy in the form of plate 0.250 to 4.000 inches (6.35 to 101.60 mm), inclusive, in thickness (see 8.6).
This SAE Aerospace Standard (AS) establishes the requirements for 24° cone flareless fluid connection fittings and nuts and bite type flareless sleeves for use in aircraft fluid systems at an operating pressure of 5000 psi for the fittings and nuts and 3000 psi for the bite type sleeves.
This document recommends design and performance criteria for aircraft lighting systems used to illuminate flight deck controls, luminous visual displays used for transfer of information, and flight deck background and instrument surfaces that form the flight deck visual environment. This document is for aircraft, except for applications requiring night vision compatibility.
This specification covers grease for use within an aircraft. It also defines the quality control requirements to assure batch conformance and materials traceability and the procedures to manage and communicate changes in the grease formulation and brand. This specification invokes the Performance Review Institute (PRI) product qualification process. Requests for submittal information may be made to the PRI at the address in 2.2, referencing this specification. Products qualified to this specification are listed on a Qualified Products List (QPL) managed by the PRI. Additional tests and evaluations may be required by individual equipment builders before a grease is approved for use in their equipment. Approval and/or certification for use of a specific grease in aero and aero-derived marine and industrial applications is the responsibility of the individual equipment builder and/or governmental authorities and is not implied by compliance with or qualification to this specification.
This specification establishes the requirements for a waterborne, corrosion-inhibiting, chemical- and solvent-resistant, anodic electrodeposition epoxy primer capable of curing at 200 to 210 °F (93 to 99 °C).
This specification covers grease for use on aircraft wheel bearings. It also defines the quality control requirements to assure batch conformance and materials traceability and the procedures to manage and communicate changes in the grease formulation and brand. This specification invokes the Performance Review Institute (PRI) product qualification process. Requests for submittal information may be made to the PRI at the address in 2.2, referencing this specification. Products qualified to this specification are listed on a qualified products list (QPL) managed by the PRI. Additional tests and evaluations may be required by individual equipment builders before a grease is approved for use in their equipment. Approval and/or certification for use of a specific grease in aero and aero-derived marine and industrial applications is the responsibility of the individual equipment builder and/or governmental authorities and is not implied by compliance with or qualification to this
Current regulations (e.g., Title 14 of the United States Code of Federal Regulations, or 14 CFR) define design requirements for oxygen system provisions for protection of crewmembers and passengers following emergency events such as in-flight decompression. This aerospace information report (AIR) addresses the operational oxygen system requirements for a decompression incident that may occur at any point during a long-range flight, with an emphasis for a decompression at the equal time point (ETP). This AIR identifies fuel and oxygen management contingencies and presents possible solutions for the efficient, safe, and optimum fuel/oxygen flight continuation. Oxygen management is a critical concern for all aircraft, ranging from single-engine types operating above 10000 feet to complex, high-performance aircraft equipped with supplemental oxygen systems. Proper planning ensures compliance with regulations and supports pilot and passenger safety at higher altitudes. This document
The scope of this SAE performance standard is to provide a simple, practical, and broadly applicable test procedure for appraising luminous Illuminant A reflectance of reflecting safety glazing materials for road vehicles. This SAE performance standard, which provides a simple test procedure widely used in the optics field, may be used to measure the reflectivity which films applied to safety glazing materials for road vehicles may enhance. This test procedure applies to conditions where feasibility, rather than accuracy of measurement, is of prime importance. Measurements can be made outside laboratories in a quality control environment and in similar applications, when glazings, instead of small test specimens, have to be tested.
This specification establishes requirements for three types of corrosion-preventative coatings for protection of aircraft integral fuel tanks.
This SAE Standard encompasses connectors between two cables or between a cable and an electrical component and focuses on the connectors external to the electrical component. This document provides environmental test requirements and acceptance criteria for the application of connectors for direct current electrical systems of 60 V or less in the majority of heavy-duty applications typically used in off-highway machinery. Severe applications can require higher test levels or field-testing on the intended application.
This SAE Recommended Practice defines the minimum performance specifications for sensors used within anthropomorphic test devices (ATDs) when performing impact tests per SAE J211. It is intended that any agency proposing to conduct tests in accordance with SAE J211 shall be able to demonstrate that the transducers they use would meet the performance requirements specified in this document.
This specification establishes the engineering requirements for producing an anodic coating on titanium and titanium alloys and the properties of the coating.
This specification covers a corrosion-resistant steel in the form of sheet and strip.
The AMS1428 specification defines the technical requirements for Type II, III, and IV aircraft deicing/anti-icing fluids. These non-Newtonian thickened fluids are formulated to effectively remove frost, ice, and snow from aircraft surfaces while offering protection times longer than Type I fluids against refreezing or frozen contamination. The document outlines key performance criteria, such as freezing point, aerodynamic acceptance, and anti-icing performance, alongside environmental properties like biodegradability, aquatic toxicity, biochemical oxygen demand (BOD), and chemical oxygen demand (COD). Operational considerations, including storage stability, materials compatibility, exposure to dry air, dry-out exposure to cold dry air, successive dry-out and rehydration, and physical properties like pH, refraction, and rheological properties (viscosity) are also specified. Additionally, the specification details the required testing methods to evaluate these properties and sets forth
This document applies to the development of Plans for integrating and managing electronic components in equipment for the military and commercial aerospace markets, as well as other ADHP markets that wish to use this document. Examples of electronic components described in this document include resistors, capacitors, diodes, integrated circuits, hybrids, application specific integrated circuits, wound components, and relays. It is critical for the Plan owner to review and understand the design, materials, configuration control, and qualification methods of all “as-received” electronic components and their capabilities with respect to the application; and to identify risks and, where necessary, take additional action to mitigate the risks. The technical requirements are in Section 3 of this standard and the administrative requirements are in Section 4.
This SAE Recommended Practice was developed by SAE and the section “Standard Classification and Specification for Service Greases” cooperatively with ASTM and NLGI. It is intended to assist those concerned with the design of heavy-duty vehicle components and with the selection and marketing of greases for the lubrication of certain components on heavy-duty vehicles like trucks and buses. The information contained herein will be helpful in understanding the terms related to properties, designations, and service applications of heavy-duty vehicle greases.
This specification covers an aluminum alloy in the form of plate 0.750 to 1.500 inches, incl (19.05 to 38.10 mm, incl) in thickness (see 8.6).
This SAE Recommended Practice establishes the procedure for measuring the maximum exterior sound level of recreational motorboats while being operated under a variety of operating conditions. It is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances.
This SAE Standard is equivalent to ISO 362-1:2015 and specifies an engineering method for measuring the noise emitted by road vehicles of categories M and N under typical urban traffic conditions. It excludes vehicles of category L1, L2, L3, L4, and L5. The specifications are intended to reproduce the level of noise generated by the principal noise sources during normal driving in urban traffic. The method is designed to meet the requirements of simplicity as far as they are consistent with reproducibility of results under the operating conditions of the vehicle. The test method requires an acoustical environment that is obtained only in an extensive open space. Such conditions are usually provided for during: Measurements of vehicles for regulatory certification and/or type approval Measurements at the manufacturing stage Measurements at official testing stations Annex A provides background information on the use of this standard consistent with the intent.
This aerospace test standard establishes the requirements and procedures for evaluating and comparing the impulse fatigue performance of high pressure hydraulic fittings and tubing. This test method may be used to test similar fluid system components, if desired.
This specification covers a single-component, unfilled, heat-reactive, thermosetting, aromatic system which thermally cures to form a polyimide polymer structure.
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