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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 established manufacturing tolerances applicable to sheet, strip, and plate of corrosion and heat resistant steels, iron alloys, titanium, and titanium alloys 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 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 an aircraft-quality, low-alloy, heat-resistant steel in the form of bars, forgings, mechanical tubing, and forging stock procured in SI (metric) units. AMS 6304 is the inch/pound version of this MAM. These products have been used typically for parts, such as shafts, and fasteners, for service up to 540 degrees C, but usage is not limited to such applications
AMS E Carbon and Low Alloy Steels Committee
This specification covers an aluminum alloy in the form of die forgings and forging stock ordered to metric (SI) units. Primarily for parts requiring good resistance to stress-corrosion cracking but with lower strength than AMS-4139
AMS D Nonferrous Alloys Committee
This specification covers established metric manufacturing tolerances applicable to bars, rods, and wire of nickel, nickel alloys, and cobalt alloys 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 a specified range
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers established metric manufacturing tolerances applicable to corrosion and heat resistant steel, iron alloy, titanium, and titanium alloy bars and wire 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 F Corrosion and Heat Resistant Alloys 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 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 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
This specification covers an aluminum alloy in the form of hand forgings procured to metric dimensions. AMS 4323 is the inch/pound version of this MAM. These forgings have been used typically for parts requiring a high level of mechanical properties and good resistance to stress-corrosion cracking, but usage is not limited to such applications
AMS D Nonferrous 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 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
This SAE Recommended Practice establishes the instrumentation and procedure to be used in measuring the maximum exterior sound level for engine powered equipment under 14.7 kW (20 bhp). It is intended to include equipment such as lawn mowers, snow blowers, tillers, etc. It is not intended to include equipment designed primarily for operation on highways or within factories and buildings, or vehicles such as motorcycles, snowmobiles, and pleasure motor boats that are covered by other SAE Standards or Recommended Practices. This SAE Recommended Practice may also be used when measuring the maximum exterior sound level on similar equipment powered by electricity or other power sources
This document is intended for use during audits to the requirements of AS5553C. It may be used by all contracting organizations that procure EEE parts, whether such parts are procured directly or integrated into electronic assemblies or equipment as guidance for evaluating compliance to AS5553C
G-19 Counterfeit Electronic Parts Committee
This SAE Aerospace Information Report (AIR) was written because of the growing interest in aircraft installed outdoor engine testing by the Federal Aviation Administration, airlines, charter/commercial operators, cargo carriers, engine manufacturers and overhaul and repair stations. This document was developed by a broad cross section of personnel from the aviation industry and government agencies and includes information obtained from a survey of a variety of operators of fixed and rotary wing aircraft and research of aircraft and engine maintenance manuals
EG-1E Gas Turbine Test Facilities and Equipment
This document examines the most important considerations relative to the use of proximity sensing systems for applications on aircraft landing gear. In general, the information included are applicable to other demanding aircraft sensor installations where the environment is equally severe
A-5B Gears, Struts and Couplings Committee
This SAE Aerospace Recommended Practice (ARP) identifies and defines methods of compliance with power available and inlet distortion requirements for rotorcraft with inlet barrier filter (IBF) installations. The material developed herein is intended to provide industry-recommended methods of compliance with civil airworthiness regulations. It is intended to serve as a basis for new or revised FAA advisory material describing acceptable methods for determining power assurance, establishing power available, and for substantiating acceptable engine inlet distortion for IBF installations. The ARP does not address other types of inlet protection systems such as inertial separator, electrostatic precipitators, or foreign object debris (FOD) screens. It is agreed to treat dust, ice, salt, water, and snow as contaminants to the IBF for the purpose of establishing power available and assessing inlet distortion, but any other effects of ice and snow on inlet airworthiness are outside the scope
S-12 Powered Lift Propulsion Committee
The purpose of this SAE Aerospace Information Report (AIR) is to disseminate qualitative information regarding foreign object debris (FOD) damage to the gas path of rotorcraft gas turbine engines and to discuss methods of FOD prevention. Although turbine-powered fixed-wing aircraft are also subject to FOD, the unique ability of the rotorcraft to hover above, takeoff from, and land on unprepared surfaces creates a special need for a separate treatment of this subject
S-12 Powered Lift Propulsion Committee
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
A-5B Gears, Struts and Couplings Committee
This SAE Aerospace Information Report (AIR) provides a description of a screening method for use in the field for verifying an AMS 1428 anti-icing fluid is above its minimum low shear viscosity as published with holdover time guidelines. The test will determine if the fluid is (a) satisfactory, (b) unsatisfactory, or (c) borderline needing more advanced viscometry testing. Other field tests may be required to determine if an anti-icing fluid is useable, such as refractive index, appearance or other tests as may be recommended by the fluid manufacturer
G-12ADF Aircraft Deicing Fluids
The purposeful integration of existing and emerging technologies into CM practice will enable collaboration with supporting systems and provide stakeholders access to authoritative and trusted data in a timely fashion at their desktop to help drive educated decision making. This lays to rest the misguided myth that CM and supporting systems operate at cross-purposes. What does it mean to have CM in a world of new initiatives and 2-week sprints (i.e., time-boxed work periods), multiple increments producing Minimum Viable Products (MVP) and synchronized with Model Based Systems Engineering (MBSE) while being digitally transformed? MBSE initiatives drive the jump from “2D” data to “3D” data, thereby becoming a Model-Centric practice. Products now enable technology to push the product lifecycle management process to new levels of efficiency and confidence. This mindset is evidenced by five major functions of CM, as discussed below, and described in EIA-649C
G-33 Configuration Management
The scope of this ARP is to define methods of determining wire lengths and minimum insertion depths of thrust wires used for retaining components together
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
For tube fitting standards with reduction/expansion, to provide precautions against the use of large changes in tube size
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This SAE Recommended Practice establishes a test procedure for measuring pneumatic system differentials and time relationships for 125 psig (862 kPa) nominal air pressure brake systems
Truck and Bus Brake Systems Committee
This document covers all metal, castellated, self-locking nuts made from alloy steel of the types identified under the Unified Numbering System as UNS G41300 and UNS G43400
E-25 General Standards for Aerospace and Propulsion Systems
This specification establishes the requirements for various types and colors of electrical insulating sleeving that will shrink to a predetermined size upon the application of heat. This specification includes provisions for demonstrating compliance with qualification requirements (see Section 4 and 7.3), in process inspection, and statistical process control inspections (see 4.4). The continuous operating temperature ranges for the sleeving classes covered by this specification are from -112 to +482 °F (-80 to +250 °C). The continuous operating temperature range for each sleeving class is given in the applicable detail specification
AE-8D Wire and Cable Committee
This document covers minimum performance standards for protective equipment used on the flight deck during rapid decompression (5 to 30 seconds) up to a maximum pressure altitude of 45000 feet. Equipment with the capability to adequately protect flight deck crew from hypoxia up to FL450 is anticipated to provide sufficient protection at lower altitudes
A-10 Aircraft Oxygen Equipment Committee
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
This Information Report establishes the following minimum per formance levels in the operator’s environment
HFTC6, Operator Accommodation
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