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Rubber, Fluorocarbon Elastomer (FKM), 70 to 80 Hardness, Low Temperature Sealing Tg -22°F (-30°C), For Elastomeric Shapes or Parts in Gas Turbine Engine Oil, Fuel and Hydraulic SystemsAMS3384A (Current)12/09/2025
This specification covers a high temperature, compression set and fluid resistant fluorocarbon (FKM) rubber in the form of sheet, strip, tubing, extrusions, and molded shapes for aeronautical and aerospace applications.
AMS CE Elastomers Committee
Hard Anodic Coating of Magnesium AlloysAMS2466D (Current)12/09/2025
This specification covers the requirements for a hard anodic coating on magnesium alloys.
AMS B Finishes Processes and Fluids Committee
Tolerances Titanium and Titanium Alloy Extruded Bars, Rods, and Shapes AMS2245D (Current)12/09/2025
This specification covers established manufacturing tolerances applicable to titanium and titanium alloy extruded bars, rods, and shapes. These tolerances apply to all conditions, unless otherwise noted. The term "excl" applies only to the higher figure of the specified range.
AMS G Titanium and Refractory Metals Committee
Trace Element Control, Nickel Alloy CastingsAMS2280E (Current)12/09/2025
<p>This specification establishes testing methods and maximum permissible limits for trace elements in nickel alloy castings.</p>
AMS F Corrosion Heat Resistant Alloys Committee
Aluminum Alloy Castings, Permanent Mold, 5.0Si - 1.2Cu - 0.5Mg (355.0-T71), Solution Heat Treated and OveragedAMS4280K (Current)12/09/2025
This specification covers an aluminum alloy in the form of permanent mold castings.
AMS D Nonferrous Alloys Committee
Aluminum Alloy, Investment Castings, 7.0Si - 0.32Mg (356.0-T6), Solution and Precipitation Heat TreatedAMS4260H (Current)12/09/2025
This specification covers an aluminum alloy in the form of castings.
AMS D Nonferrous Alloys Committee
Aluminum Alloy Castings, 7.0Si - 0.55Mg - 0.12Ti (F357.0-T6), Solution and Precipitation Heat TreatedAMS4289A (Current)12/09/2025
This specification covers an aluminum alloy in the form of castings.
AMS D Nonferrous Alloys Committee
Aluminum Alloy Castings, Permanent Mold, 5.0Si - 1.2Cu - 0.50Mg (355.0-T6), Solution and Precipitation Heat TreatedAMS4281H (Current)12/09/2025
This specification covers an aluminum alloy in the form of permanent mold castings.
AMS D Nonferrous Alloys Committee
Aluminum Alloy, Castings 4.7Cu - 0.60Ag - 0.35Mn - 0.25Mg - 0.25Ti (B201.0-T7) Solution Heat Treated and Overaged AMS4242D (Current)12/09/2025
This specification covers an aluminum alloy in the form of castings.
AMS D Nonferrous Alloys Committee
Aluminum Alloy, Castings 4.5Cu - 0.70Ag - 0.30Mn - 0.25Mg - 0.25Ti (A201.0-T4) Solution Heat Treated and Naturally Aged AMS4223F (Current)12/09/2025
This specification covers an aluminum alloy in the form of castings.
AMS D Nonferrous Alloys Committee
Aluminum Alloy Castings, High Strength 4.5Cu - 0.70Ag - 0.30Mn - 0.25Mg - 0.25Ti (A201.0-T7) Solution Heat Treated and Overaged AMS4229H (Current)12/09/2025
This specification covers an aluminum alloy in the form of sand, permanent mold, and composite mold castings.
AMS D Nonferrous Alloys Committee
Cloths, Cleaning, For Aircraft Primary and Secondary Structural SurfacesAMS3819E (Current)12/09/2025
This specification covers woven, nonwoven, and knit absorbent materials supplied either as dry cloths or presaturated cloths for solvent cleaning process applications.
AMS G9 Aerospace Sealing Committee
Aircraft Electrical Voltage Level DefinitionsAIR7502A (Current)12/09/2025
The scope of this report will document the various voltage levels and provide a rational for each level as discussed and agreed to in the AE-7 committee.
AE-7C Systems
Steel, Corrosion Resistant, Sheet, Strip, and Foil, 19Cr - 9.5Ni (304), Cold Rolled, 125 ksi (862 MPa) Tensile StrengthAMS5501G (Current)12/08/2025
This specification covers a corrosion-resistant steel in the form of sheet, strip, and foil 0.005 inch (0.13 mm) and over in nominal thickness (see 8.4).
AMS F Corrosion Heat Resistant Alloys Committee
J1939 Digital AnnexJ1939DA_201402 (Current)12/08/2025
The J1939 Digital Annex The J1939 Digital Annex, introduced in August 2013, offers key J1939 technical data in an Electronic Spreadsheet that can be easily searched, sorted, and adapted to other formats. J1939DA contains all of the SPNs (parameters), PGNs (messages), and other J1939 data previously published in the SAE J1939 top level document. J1939DA also contains all of the SLOTs, Manufacturer ID Codes, NAME Functions, and Preferred Addresses previously published in the SAE J1939 top level and the J1939-71 document. J1939DA contains the complete technical details for all of the SPNs and PGNs previously published in the SAE J1939-71 document. For all other SPNs and PGNs which are published in a document other than SAE J1939-71, J1939DA lists only basic details along with a reference to the document that contains the complete technical details. J1939DA replaces, and expands upon, the 1939 Companion Spreadsheet (CS1939), which was last published through November 2012. The data fields
Truck Bus Control and Communications Network Committee
Hard Anodic Coating on Aluminum and Aluminum AlloysAMS2469J (Current)12/08/2025
This specification establishes the requirements for a hard anodic coating on aluminum and aluminum alloys.
AMS B Finishes Processes and Fluids Committee
HELICOPTER TURBOSHAFT ENGINE IDLE POWER SCHEDULINGAIR4121 (Current)11/26/2025
The purpose of this AIR (Aerospace Information Report) is to provide aircraft and engine designers with a better understanding of helicopter turboshaft engine idle power characteristics and objectives to be considered in the design process. Idle is the lowest steady state power setting. At this setting, the engine typically does not produce enough power to obtain governed output shaft speed (i.e. the shaft speed is determined by the load imposed by the aircraft). In the aircraft, the engine is typically stabilized at this power setting after starting, prior to taxi and for some period of time after rotor shutdown for cool down prior to engine shutoff. Traditionally, the aircraft designer wants idle power scheduled as low as possible and of course, does not want any resulting aircraft operational difficulties such as overcoming the rotor brake. The engine designer, however, desires a higher scheduled power because of the reduced probability of engine operational problems. The attributes
S-12 Powered Lift Propulsion Committee
Tool, Stripper, Electrical Insulation, General Specification ForAS5768A (Current)11/26/2025
This specification covers design requirements, performance requirements, and methods of procurement for tools and associated accessories used to strip aerospace vehicle electrical wire and cable. Aerospace vehicle electrical wire has stranded conductors with protective plating and specialized insulation. Poor quality wire strippers or mismatched blades can compromise the performance of wiring.
AE-8C2 Terminating Devices and Tooling Committee
Arc Damage Assessment of Arc Plume and Physical DamageAIR6982 (Current)11/26/2025
Describes the relative measurement of assessing the damage zone of arc plasma to determine appropriate separation/segregation requirements between a wire harness and nearby components
AE-8A Elec Wiring and Fiber Optic Interconnect Sys Install
Aircraft and Aircraft Engine Fuel Pump Low Lubricity Fluid Endurance TestARP1797B (Current)11/26/2025
This procedure is intended to apply to fuel pumps. This procedure will be defined in terms of recommended test fluid, test setup, test conditions, and test method. This procedure may be used for other fuel system components, by testing in conjunction with the pump, which normally supplies the component inlet flow, or a substitute test pump of similar capacity. This procedure may be used, with variations in test conditions and test fluid for performing pump evaluation tests. Tests at progressively increasing pump speeds and pressures will provide design limitation data. Alternate test periods on a test pump and another pump, of a design for which actual service durability is known, will provide useful comparison data.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
Measurement of Exterior Noise Produced by Aircraft Auxiliary Power Units (APUs) and Associated Aircraft Systems During Ground OperationARP1307C (Current)11/26/2025
Test procedures are described for measuring noise at specific receiver locations (passenger and cargo doors, and servicing positions) and for conducting general noise surveys around aircraft. Procedures are also described for measuring noise level and directivity at noise source locations to facilitate the understanding and interpretation of the data. Requirements are identified with respect to instrumentation; acoustic and atmospheric environment; data acquisition, reduction and presentation, and such other information as is needed for reporting the results. This document makes no provision for predicting APU or component noise from basic engine characteristics or design parameters, nor for measuring noise of more than one aircraft operating at the same time. No attempt is made to suggest acceptable levels of noise or suitable subjective criteria for judging acceptability. ICAO Annex 16 Volume I Attachment C provides guidance on recommended maximum noise levels.
A-21 Aircraft Noise Measurement Aviation Emission Modeling
Nitrogen Absorption/Desorption (Gas Dissolution) in Aircraft Shock AbsorbersAIR6942 (Current)11/26/2025
This document outlines the current state of the art in the understanding of gas in solution in shock absorber oils in unseperated shock absorbers. A literature review, overview of Henry's law, Henry's law coefficients for known gas and oil couples, in-service operational problems, lessons learned, and potential future work will be discussed in the document.
A-5B Gears, Struts and Couplings CommitteeNEW
Composite Secondary and Tertiary Structure for Landing Gear AIR6827 (Current)11/26/2025
This document will contain guidance and considerations for the use of composite materials on non-primary structure for landing gear systems. Content to include design considerations, conditions and applications where composites are feasible/beneficial, high-level descriptions of various manufacturing processes, and certification/validation considerations.
A-5B Gears, Struts and Couplings CommitteeNEW
Development and Qualification of Composite Landing GearsAIR5552A (Current)11/26/2025
This information report provides general guidance for the design considerations, qualification in endurance, strength and fatigue of landing gear using composite components as principle structural elements. The information discussed herein includes the development and evaluation of design data considering: the potential for imbedded manufacturing defects, manufacturing process variations, the component operating environment, potential damage threats in service, rework and overhaul, and inspection processes. This AIR mainly discusses the use of thick composites for landing gear structural components. Considerations and recommendations provided in this AIR may therefore differ greatly from considerations and recommendations found in widely accepted composite design references such as CMH-17 and Advisory Circulars such as AC 20-107(B).
A-5B Gears, Struts and Couplings CommitteeNEW
LED Landing, Taxiing, Runway Turnoff, and Recognition LightsARP6402B (Current)11/26/2025
This document includes recommendations of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a. Single engine personal and/or liaison type b. Light twin engine c. Large multiengine propeller d. Large multiengine turbojet e. Military high performance fighter and attack f. Helicopter which are subject to the following CFR Parts certification: Part 23 – Airworthiness Standards: Normal, Utility, Acrobatic and Commuter Aircrafts Part 25 – Airworthiness Standards: Transport Category Aircrafts Part 27 – Airworthiness Standards: Normal Category Rotorcraft Part 29 – Airworthiness Standards: Transport Category Rotorcraft
A-20B Exterior Lighting Committee
Environment Spectra and Corrosivity Monitoring Using Electrochemical and Electrical Resistance SensorsAIR6970 (Current)11/26/2025
This Aerospace Informational Report (AIR) provides guidance on using environmental, electrochemical, and electrical resistance measurements to monitor environment spectra and corrosivity of service environments, focusing on parameters of interest, existing measurement platforms, deployment requirements, and data processing techniques. The sensors and monitoring systems provide discrete time-based records of 1) environmental parameters such as temperature, humidity, and contaminants; 2) measures of alloy corrosion in the sensor; and 3) protective coating performance in the sensor. These systems provide measurements of environmental parameters, sensor material corrosion rate, and sensor coating condition for use in assessing the risk of atmospheric corrosion of the structure. Time-based records of environment spectra and corrosivity can help determine the likelihood of corrosion to assess the risk of corrosion damage of the host structure for managed assets, aiding in establishing
HM-1 Integrated Vehicle Health Management Committee
Hose Assembly, Polytetrafluoroethylene, Cres Reinforced, 400 °F, 3000 psi, Lightweight, Beam Seal, Straight to 90°AS1911D (Current)11/26/2025
No scope available
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
Hose Assemblies, Installed, Visual Inspection Guide ForARP1658C (Current)11/26/2025
This SAE Aerospae Recommended Practice (ARP) covers visible surface defects on aerospace hose assemblies which have been installed and are functioning within a working environment at the time of visual inspection. This document is intended to help those who are conducting periodic visual inspections of hose assemblies used in aerospace systems and ground servicing equipment to determine time for replacement by condition of hose assemblies at time of inspection. This practice is intended to augment existing procedures for replacement of hose assemblies based on service time. A constant surveillance of all hose assemblies for visible wear, defects, and/or damage shall be routine at all times of maintenance. When wear, defects, or damage to installed hose assemblies is detected, the hose assemblies shall be tagged or replaced in accordace with Section 4 of this document.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
Observers for Laser Safety in the Navigable AirspaceARP5535B (Current)11/26/2025
This document applies to safety observers or spotters involved with the use of outdoor laser systems. It may be used in conjunction with SAE Aerospace Standard (AS4970) “Human Factors Considerations for Outdoor Laser Operations in the Navigable Airspace.” Additional control measures may be applicable and are listed in ANSI Z136.6.
G10T Laser Safety Hazards Committee
Aviation Lubricant Tribology Evaluator (ALTE) Method to Determine the Lubricating Quality of Gas Turbine LubricantsARP6255A (Current)11/26/2025
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.
E-34 Propulsion Lubricants Committee
Test Method for the Determination of Total Acidity in Polyol Ester and Diester Gas Turbine Lubricants by Automatic Potentiometric TitrationARP5088C (Current)11/26/2025
The test method describes the procedure for determination of the total acid number of new and degraded polyol ester and diester based gas turbine lubricants by potentiometric titration technique. The method was validated to cover an acidity range 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 lubricant.
E-34 Propulsion Lubricants Committee
Gas Turbine Engine Lubricant Specifications: Current Technical Review and Future DirectionAIR6056A (Current)11/26/2025
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
A Review of Literature on the Relationship Between Gas Turbine Engine Lubricants and Aircraft Cabin Air QualityAIR5784A (Current)11/26/2025
There has been a recent upsurge in interest from the media concerning the quality of the environment within aircraft cabins and cockpits especially in the commercial world. This has included (although by no means been limited to) the air quality, with particular reference to the alleged effects of contamination from the aircraft turbine lubricant. Possible exposure to 'organophosphates' (OPs) from the oil has raised special concerns from cabin crew. Such is the concern that government organisations around the world, including Australia, USA and UK, have set up committees to investigate the cabin air quality issue. Concern was also voiced in the aviation lubricants world at the way in which OP additives in turbine lubricants were being blamed in some reports for the symptoms being experienced by air crew and passengers. SAE Committee E-34 therefore decided that it should gather as much available information on the subject as possible. This would then enable E-34 to participate in
E-34 Propulsion Lubricants Committee
Aircraft Lightning Test MethodsARP5416B (Current)11/26/2025
This document is one of a set covering the whole spectrum of aircraft interaction with lightning. This document is intended to describe how to conduct lightning direct effects tests and indirect system upset effects tests. Indirect effects upset and damage tolerance tests for individual equipment items are addressed in DO-160/ED-14. Documents relating to other aspects of the certification process, including definition of the lightning environment, zoning, and indirect effects certification are listed in Section 2. This document presents test techniques for simulated lightning testing of aircraft and the associated systems. This document does not include design criteria nor does it specify which items should or should not be tested. Acceptable levels of damage and/or pass/fail criteria for the qualification tests must be approved by the cognizant certification authority for each particular case. When lightning tests are a part of a certification plan, the test methods described herein
AE-2 Lightning Committee
Fuel Flowmeters and IndicatorsAS407E (Current)11/26/2025
To specify minimum requirements for Fuel Flowmeters for use primarily in reciprocating engine powered civil transport aircraft, the operation of which may subject the instruments to the environmental conditions specified in Section 3.3. This Aeronautical Standard covers two basic types of instruments, or combinations thereof, intended for use in indicating fuel consumption of aircraft engines as follows: TYPE I - Measure rate of flow of fuel used. TYPE II - Totalize amount of fuel consumed or remaining.
AS407 Fuel Flowmeters
Artificial Intelligence in Aeronautical Systems: TaxonomyAIR6987 (Current)11/26/2025
Establish a comprehensive taxonomy of Artificial Intelligence in aviation
G-34, Artificial Intelligence in Aviation
Performance based packaging standard for lithium batteries as cargo on aircraftAS6413 (Current)11/26/2025
This standard is intended to demonstrate and document the control of the potential hazards from lithium cells or batteries (UN 3090 and 3480) when transported as cargo on aircraft. [still need to identify if we are addressing global (external fire) or local (battery internal failures)] This standard addresses the need to control the hazards which might arise from a failure from an individual cell by containing the hazards within the package. This specific hazards addressed within this standard are: • Uncontrolled fire • Rapid overpressure pulse within compartment
G-27 Lithium Battery Packaging Performance
Recommendations and Background Material for Battery Package TestingAIR6840 (Current)11/26/2025
AS 6413 and slash sheets /1 & /2 hold the main information for testing of battery packaging. This document holds further information and expansion of philosophy, clarification etc. surrounding the testing and industry needs.
G-27 Lithium Battery Packaging Performance
Counterfeit Materiel; Assuring Acquisition of Authentic and Conforming Materiel - BearingsAS6834 (Current)11/26/2025
This document standardizes requirements for bearings: (a) supply chain management, procurement, inspection, parts management, and test/evaluation to assure the authenticity of bearings being acquired/used, and (b) response strategies when suspect or confirmed counterfeit bearings are discovered. Though developed primarily for critical application bearings, the document also may be applicable, at the discretion of the user, to other bearings with similar characteristics and applications. The bearings slash sheet is not intended to replace, conflict with, or duplicate requirements in quality system or AMS series material specs but rather to augment them with regards to counterfeit prevention and risk mitigation.
G-21 Counterfeit Materiel Committee
Guidelines for Engine Component TestsARP5757B (Current)11/26/2025
This SAE Aerospace Recommended Practice (ARP) provides guidance for substantiating the airworthiness of aircraft engine components. Generally these components are associated with the engine control system, the system or systems that allow the engine to provide thrust or power as demanded by the pilot of the aircraft while also ensuring the engine operates within acceptable operating limits. But these components may also include hardware and systems associated with engine lubrication, engine or aircraft hydraulic or electrical systems, aircraft environmental control systems, thrust reverser control, or similar aircraft or engine propulsion system functions. This paper develops the concept of using a 26 item matrix of environmental conditions for evaluating aircraft engine component airworthiness. This approach is compatible with current practices used in the industry and has been accepted by engine certification authorities as part of engine certification programs.
E-36 Electronic Engine Controls Committee
Guidelines for the Integration of Electronic Engine Control Systems for Transport Category (Part 25) and General Aviation (Part 23) AircraftAIR5924B (Current)11/26/2025
This SAE Aerospace Information Report (AIR) provides methodologies and approaches that have been used to install and integrate full-authority-digital-engine-control (FADEC) systems on transport category aircraft. Although most of the information provided is based on turbofan engines installed on large commercial transports, many of the issues raised are equally applicable to corporate, general aviation, regional and commuter aircraft, and to military installations, particularly when commercial aircraft are employed by military users. The word “engine” is used to designate the aircraft propulsion system. The engine station designations used in this report are shown in Figure 1. Most of the material concerns an Electronic Engine Control (EEC) with its associated software, and its functional integration with the aircraft. However, the report also addresses the physical environment associated with the EEC and its associated wiring and sensors. Since most of today’s transport category
E-36 Electronic Engine Controls Committee
Standardized composite training programAIR6671 (Current)11/26/2025
SAE CACRC has produced several standards, each representing the best-practice, recommended minimum training syllabus for the aforementioned target groups. The purpose of this document is to promote the use of these SAE standards, particularly for developing training programs for employee training, qualification in airlines and maintenance organizations, and as reference in regulatory guidance material. It summarizes, as a quick reference, the content of each training document and its relation to and interaction with other training documents. Thereby it allows users to select the appropriate training documents and syllabi to establish a comprehensive, sequential training program build-up customized to the specific needs of the aforementioned functions (see figure). This document does not intend to introduce new training content/syllabus.
AMS CACRC Commercial Aircraft Composite Repair Committee
Guidelines for Repair Process Evaluation of Fiber Reinforced Composite Bonded StructureAIR6292 (Current)11/26/2025
The SAE Aerospace Information Report (AIR) is intended to be used as a process verification guide for evaluating implementation of key factors in bonded repair of fiber reinforced composite structure in a repair shop environment. The guide will be used in conjunction with a regulatory approved and substantiated repair, and is intended to promote consistency and reliability.
AMS CACRC Commercial Aircraft Composite Repair Committee
Guidelines for Repair Process Evaluation of Aluminum Bonded StructureAIR6291A (Current)11/26/2025
This SAE Aerospace Information Report (AIR) is intended to be used as a process verification guide for evaluating implementation of key factors in repair of metal bond parts or assemblies in a repair shop environment. This guide is to be used in conjunction with a regulatory approved and substantiated repair, and is intended to promote consistency and reliability.
AMS CACRC Commercial Aircraft Composite Repair Committee
Water Spray and High Humidity Endurance Test Methods for AMS1424 and AMS1428 Aircraft Deicing/Anti-Icing FluidsAS5901E (Current)11/26/2025
This document establishes the minimum requirements for an environmental test chamber, and test procedures to carry out anti-icing performance tests according to the current materials specification for aircraft deicing/anti-icing fluids. The primary purpose for such a test method is to determine the anti icing endurance under controlled laboratory conditions of AMS1424 Type I and AMS1428 Type II, III, and IV fluids.
G-12ADF Aircraft Deicing Fluids
Aerospace - Test Methodology for Electrohydrostatic ActuatorsARP5879A (Current)11/26/2025
This document provides an overview of the tests and issues related to testing that are unique to Electrohydrostatic Actuators (EHAs). An EHA incorporates a linear or rotary hydraulic actuator and a variable speed, reversible electric servomotor driving a fixed displacement hydraulic pump for actuator control, and associated power drive electronics. The tests and issues documented are not necessarily all-inclusive. This document discusses both, the tests applicable to EHAs and the test methodologies to accomplish the test objectives. This document also lists tests that are not unique to EHAs, but are still applicable to EHAs. In these instances a discussion of such tests is not contained in this document, and as applicable, the reader may reference ARP1281 (Actuators: Aircraft Flight Controls, Power Operated, Hydraulic, General Specification For), which addresses test issues applicable to electrohydraulic flight control servoactuators. In the discussion of the tests and test
A-6B2 Electrohydrostatic Actuation Committee
Electrohydrostatic Actuation Applications on Aircraft ProgramsAIR6353 (Current)11/26/2025
This document will maintain a listing of all current and new EHA/EBHA aircraft applications, including parameters such as power, force, rate, etc, as is permissible for public offering.
A-6B2 Electrohydrostatic Actuation Committee
Guidelines for Specifying LVDTs and RVDTsARP5554 (Current)11/26/2025
As per Committee/Henry E. Harschburger recommendations
A-6B1 Hydraulic Servo Actuation Committee
Aerospace - Lightning Effects on Hydraulic Transport Elements on AircraftAIR6185A (Current)11/26/2025
<p>This SAE Aerospace Information Report (AIR) describes hydraulic system design and installation to minimize the effects of lightning, especially when the aircraft structure is composite. Techniques for effective electrical bonding, hydraulic system lightning protection, and lightning protection verification techniques are discussed.</p>
My new committee for commercial aircrafts
Bearing, Sleeve, Flanged, Self-Lubricating -65 to +250 °FAS21241A (Current)11/26/2025
Scope unavailable.
ACBG Plain Bearing Committee
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