Results
This SAE Aerospace Information Report (AIR) discusses past and present approaches for monitoring the landing gear structure and shock absorber (servicing), opportunities for corrosion detection, methods for transient overload detection, techniques for measuring the forces seen by the landing gear structure, and methods for determining the fatigue state of the landing gear structure. Landing gear tire condition and tire pressure monitoring are detailed in ARP6225, AIR4830, and ARP6137, respectively. Aircraft Brake Temperature Monitoring Systems (BTMS) are detailed in AS1145.
This test method provides a procedure for measuring no-load rotational breakaway torque of self-lubricating spherical bearings.
This SAE Recommended Practice describes common definitions and operational elements of Event Data Recorders. The SAE J1698 series of documents consists of the following: SAE J1698-1 - Event Data Recorder - Output Data Definition: Provides common data output formats and definitions for a variety of data elements that may be useful for analyzing vehicle crash and crash-like events that meet specified trigger criteria. SAE J1698-2 - Event Data Recorder - Retrieval Tool Protocol: Utilizes existing industry standards to identify a common physical interface and define the protocols necessary to retrieve records stored by light duty vehicle Event Data Recorders (EDRs). SAE J1698-3 - Event Data Recorder - Compliance Assessment: Defines procedures that may be used to validate that relevant EDR output records conform with the reporting requirements specified in Part 563, Table 1 during the course of FMVSS-208, FMVSS-214, and other applicable vehicle level crash testing.
This specification covers continuous, multiple-strand, roving of Type "S-2" glass impregnated with a heat-curable epoxy resin matrix and processed to a "B" stage condition.
This specification covers a silicone (MQ/VMQ) elastomer that can be used to manufacture product in the form of sheet, strip, tubing, extrusions, and molded shapes. This specification should not be used for molded rings, compression seals, O-ring cord, and molded in place gaskets for aeronautical and aerospace applications without complete consideration of the end use prior to the selection of this material.
This SAE Recommended Practice establishes dimensions and tolerances for the interface between inboard mounted disc brake rotors and disc wheel hubs. This document is intended for inboard mounted disc brake rotors and disc wheel hubs for Class 5, 6, 7, and 8 commercial vehicles. Special and less-common applications are not covered.
This procurement specification covers the requirements for metal tube support clamps comprising of two spring clips made of corrosion and heat resistant steel and the associated PTFE single split cushion that supports the tube. See Figure 1.
The landing gear system is a major and safety critical airframe system that needs to be integrated efficiently to meet the overall aircraft program goals of minimizing the penalties of weight, cost, dispatch reliability and maintenance. As the landing gear system business develops and large-scale teaming arrangements and acquisitions become increasingly common, it may be desirable in some instances to procure an Integrated Landing Gear System. This document provides guidelines and useful references for developing an integrated landing gear system for an aircraft. The document structure is divided into four sections: Landing Gear System Configuration Requirements (Section 3) Landing Gear System Functional Requirements (Section 4) Landing Gear System Integrity Requirements (Section 5) Landing Gear System Program Requirements (Section 6) The landing gear system encompasses all landing gear structural and subsystem elements. Structural elements include shock struts, truck beams, torsion
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 purpose of this SAE Aerospace Recommended Practice (ARP) is to provide recommendations which will lead to the standardization of interior door design and operation in all transport aircraft. Interior doors are broadly classified into two main categories which include egress path doors and non-egress path doors. The scope of this ARP does not include crew rest doors, secondary barriers to the flight deck, or doors incorporated in furniture surrounding passenger seats as defined in AS6960.
This specification covers one grade of polytetrafluoroethylene resin in the form of film.
This SAE Aerospace Information Report (AIR) provides a methodology for performing a statistical assessment of gas-turbine-engine stability-margin usage. Consideration is given to vehicle usage, fleet size, and environment to provide insight into the probability of encountering an in-service engine stall event. Current industry practices, such as ARP1420, supplemented by AIR1419, and engine thermodynamic models, are used to determine and quantify the contribution of individual stability threats. The statistical technique adopted by the S-16 committee for performing a statistical stability assessment is the Monte Carlo method (see Applicable References 1 and 2). While other techniques may be suitable, their application is beyond the scope of this document. The intent of the document is to present a methodology and process to construct a statistical-stability-assessment model for use on a specific system and its mission or application.
This SAE Aerospace Standard (AS) establishes the surface pretreatment, temperature, and baking time required to cure AS5272 lubricant when it is applied over the surfaces of manufactured parts of various metals.
This specification covers an aluminum alloy in the form of rolled or cold-finished bars, rods, wire, and flash-welded rings and of stock for flash-welded rings.
This document describes guidelines, methods, and tools used to perform the ongoing safety assessment process for transport airplanes in commercial service (hereafter, termed “airplane”). The process described herein is intended to support an overall safety management program. It is associated with showing compliance with the regulations, and also with assuring a company that it meets its own internal standards. The methods identify a systematic means, but not the only means, to assess ongoing safety. While economic decision-making is an integral part of the safety management process, this document addresses only the ongoing safety assessment process. To put it succinctly, this document addresses the “Is it safe?” part of safety management; it does not address the “How much does it cost?” part of the safety management. This document also does not address any specific organizational structures for accomplishing the safety assessment process. While the nature of the organizational
This test plan defines the requirements of data bus components which comply with the requirements of MIL-STD-1553B, Digital Time Division Command/Response Multiplex Data Bus.
This SAE Standard specifies the essential interface dimensions, the installation dimensions, and the operating requirements for hydraulic couplers employed to transmit hydraulic power from agricultural tractors to agricultural implements and farmstead equipment as defined in SAE J1150.
This SAE Recommended Practice establishes a uniform procedure for the level road test of the brake systems of new light-duty trucks and new multipurpose passenger vehicles1 up to and including 2700 kg (6000 lb) GVW and all classes of new passenger cars.
This specification covers an ethylene propylene (EPDM) rubber in the form of sheet, strip, tubing, extrusions, and molded shapes.
This specification covers an aluminum alloy procured in the form of sheet 0.078 to 0.197 inch (2.00 to 5.00 mm), inclusive, in nominal thickness, Alclad on both sides (see 8.5).
This specification establishes the requirements for a probe type self-sealing, self-aligning, non-locking coupling intended for aerospace hydraulic and cooling systems.
The test procedures and performance criteria are directed to operation and parking of agricultural tractors equipped with braking system(s) and having a maximum design speed exceeding 6 km/h. Combinations of agricultural towing machines equipped with braking systems and towed agricultural machines without braking systems are included in this SAE Standard.
CLARA identifies four functions: Data Space Generator, Truth Data Generator, Coefficient Generator, and Reconstructor. Together these four functions standardize the solution to the LAR problem. This ICD defines the logical interfaces of the four functions.
This SAE Standard applies to refrigerant identification equipment used for identifying an acceptable level of R-1234yf purity in a refrigerant tank or vehicle MAC system labeled as containing R-1234yf, and not misidentify other refrigerants, per 5.7.
This SAE Standard describes head position contours and procedures for locating the contours in a vehicle. Head position contours are useful in establishing accommodation requirements for head space and are required for several measures defined in SAE J1100. Separate contours are defined depending on occupant seat location and the desired percentage (95 and 99) of occupant accommodation. This document is primarily focused on application to Class A vehicles (see SAE J1100), which include most personal-use vehicles (passenger cars, sport utility vehicles, pick-up trucks). A procedure for use in Class B vehicles can be found in Appendix B.
This specification covers a premium aircraft-quality alloy steel in the form of bars, forgings, and forging stock.
THIS STANDARD ESTABLISHES THE DIMENSIONAL AND VISUAL QUALITY REQUIREMENTS, LOT REQUIREMENTS, AND PACKAGING AND LABELING REQUIREMENTS FOR O-RINGS MOLDED FROM AMS7270 (MATERIAL NAME) RUBBER. IT SHALL BE USED FOR PROCUREMENT PURPOSES.
This document outlines the most common repairs used on landing gear components. It is not the intention of this AIR to replace overhaul/component maintenance or technical order manuals, but it can serve as a guide into their preparation. Refer to the applicable component drawings and specifications for surface finish, thickness, and repair processing requirements. This document may also be used as a guide to develop an MRB (Material Review Board) plan. The repairs in this document apply to components made of metallic alloys. These repairs are intended for new manufactured components and overhauled components, including original equipment manufacturer (OEM)/depot and in-service repairs. The extent of repair allowed for new components as opposed to in-service components is left to the cognizant engineering authorities. Reference could be made to this document when justifying repairs on landing gears. For repairs outside the scope of this document, a detailed justification is necessary
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