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ARP4754B Clarification Notice to address typographical errors and clarify portions of the document to facilitate usage of the newly released ARP4754B.

This specification covers aircraft-quality, low-alloy steel in the form of round, seamless tubing.

This document covers the recommended practice for determining the acceptability of the dendrite arm spacing (DAS) of D357-T6 aluminum alloy castings required to have tensile strength not lower than 50 ksi (345 MPa).

This SAE Aerospace Recommended Practice (ARP) defines the performance criteria and validation for tire circumferential movement on the rim, in the laboratory, by a static test, as well as a performance assessment in service. This document is applicable to braked wheel positions using both bias ply and radial aircraft tires.

This procurement specification covers aircraft quality self-locking nuts for wrenching (hex, spline) and anchor (plate, gang channel, shank) types of nuts made from a corrosion and heat-resistant nickel-base alloy of the type identified under the Unified Numbering System as UNS N07001. Tension height nuts having overall length of threaded portion not less than 1.2 times the nominal thread diameter have 1210 MPa minimum tensile strength at room temperature. Shear height nuts having shorter threaded portion have 1100 MPa minimum tensile strength at room temperature. Maximum test temperature of parts is 730 °C.

This specification covers a titanium alloy in the form of welding wire (see 8.5).

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.

This procurement specification covers tubular, blind rivets fabricated from a corrosion resistant nickel-copper alloy of the type identified under the Unified Numbering System as UNS N04405, and of 52 ksi minimum shear strength for self-plugging style rivets.

This technical information report (IR) presents a methodology to evaluate battery pack liquid leak tightness attributes to be used in a production line to satisfy the functional requirement for IPX7, water ingress requirement, and no sustainable coolant leakage for coolant circuits. The Equivalent Channel Method is used as a suggested production leak tightness requirement for a given battery pack design that will correlate and assure that the battery pack meets or exceeds its functional requirement. Obtaining the specific geometry of the Equivalent Channel (EC) for a given battery pack is done analytically and empirically in consideration of the product design limitations. This document is a precursor to J3277-1, which will present the practices to qualify that product leak tightness is equal or better than the maximum allowed EC for that product using applicable and commercially available leak test technologies.

This procurement specification covers aircraft-quality solid rivets made from a corrosion resistant nickel-copper alloy of the type identified under the Unified Numbering System as UNS N04400 and of 46 ksi minimum shear strength.

This SAE Aerospace Standard (AS) sets forth criteria for the selection and verification processes to be followed in providing tires that will be suitable for intended use on civil aircraft. This document encompasses new and requalified radial and bias aircraft tires.

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.

This document describes a process that may be used to perform the ongoing safety assessment for (1) GAR aircraft and components (hereafter, aircraft), and (2) commercial operators of GAR aircraft. The process described herein is intended to support an overall safety management program. It is to help a company establish and meet its own internal standards. The process described herein identifies a systematic means, but not the only means, to assess continuing airworthiness.Ongoing safety management is an activity dedicated to assuring that risk is identified and properly eliminated or controlled. The safety management process includes both safety assessment and economic decision-making. While economic decision-making (factors related to scheduling, parts, and cost) is an integral part of the safety management process, this document addresses only the ongoing safety assessment process.

This SAE Aerospace Standard (AS) provides the general performance, design, installation, test, development, and quality assurance requirements for the flight control related functions of the Vehicle Management Systems (VMS) of military piloted aircraft. It also provides specification guidance for the flight control interfaces with other systems and subsystems of the aircraft.

This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.

This SAE Aerospace Information Report (AIR) provides the hydraulic and flight-control system designer with the various design options and techniques that are currently available to enhance the survivability of military aircraft. The AIR addresses the following major topics: a Design concepts and architecture (see 3.2, 3.5, and 3.6) b Design implementation (see 3.3, 3.6, and 3.7) c Means to control external leakage (see 3.4) d Component design (see 3.8)

Generate guidance and example(s) regarding Airworthiness Security inputs to the Aircraft/System Development Processes in ARP 4754B sections 4.2 thru 4.6, and section 6. Also, clarify any essential output(s) from the Aircraft/System Development Processes that the Airworthiness Security Process DO-326A requires as input(s).

This specification covers a nickel in the form of round wire and rectangular ribbon.

This specification covers a blend of tungsten carbide-cobalt aggregate, a nickel alloy, and a nickel aluminum aggregate in the form of powder.

This procurement specification covers split cotter pins with optional ends (see Figure 1), made from a corrosion resistant steel of the type identified under the Unified Numbering System as UNS S30200.