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The turbine-engine-inlet flow distortion descriptors summarized in this document apply to the effects of inlet total-pressure, planar-wave, and total-temperature distortions. Guidelines on stability margin, destabilizing influences, types and purposes of inlet data, AIP definition, and data acquisition and handling are summarized from AIR5866, AIR5867, ARP1420, and AIR1419. The degree to which these recommendations are applied to a specific program should be consistent with the complexity of the inlet/engine integration. Total-pressure distortion is often the predominant destabilizing element that is encountered and is often the only type of distortion to be considered, i.e, not all types of distortion need to be considered for all vehicles.

This User Guide describes the content of the Rational Software Architect (RSA) version of the UCS Architectural Model and how to use this model within the RSA modeling tool environment. The purpose of the RSA version of the UCS Architectural Interface ICD model is to provide a model for Rational Software Architect (RSA) users, derived from the Enterprise Architect (EA) ICD model (AIR6515). The AIR6515 EA Model, and by derivation, the AIR6516 RSA Model, have been validated to contain the same content as the AS6518 model for: all UCS ICD interfaces all UCS ICD messages all UCS ICD data directly or indirectly referenced by ICD messages and interfaces the Domain Participant, Information, Service and Non-Functional Properties Models

• AIRBAG COMPONENT MINIMUM PERFORMANCE REQUIREMENTS • AIRBAG INSTALLATION PERFORMANCE REQUIREMENT Current revision will only contain Part 25 and lapbelt installed airbags. Future revisions will expand to include Structural airbags, 3-point restraint airbag, pre-tensioner etc.

This white paper is an examination of the increasing rate of injuries and deaths worldwide of a class of road users, often referred to as “vulnerable road users” (VRUs), with a focus on pedestrians, cyclists, scooterists, highway road workers, safety, and emergency personnel. The potential to leverage pragmatic, evidence-based technology countermeasures to reduce these collisions, and the severity of those that do occur, is also examined.

The SAE Recommended Practice establishes minimum performance requirements and related uniform laboratory test procedures for evaluating lateral (curb) impact collision resistance of all wheels intended for use on passenger cars and light trucks.

This SAE Aerospace Recommended Practice (ARP) defines means to assess the effect of changes to seat back mounted IFE monitors on blunt trauma to the head and post-impact sharp edges. The assessment methods described may be used for evaluation of changes to seat back monitor delethalization (blunt trauma and post-test sharp edges) and head injury criterion (HIC) attributes (refer to ARP6448 Appendix A Items 3 and 6, respectively). Application is focused on type A-T (transport airplane) certified seat installations.

This document provides background information, rationale, and data (both physical testing and computer simulations) used in defining the component test methods and similarity criteria described in SAE Aerospace Recommended Practice (ARP) 6330. ARP6330 defines multiple test methods uses to assess the effect of seat back mounted IFE monitor changes on blunt trauma to the head and post-impact sharp edge generation. The data generated is based on seat and IFE components installed on type A-T (transport airplane) certified aircraft. While not within the scope of ARP6330, generated test data for the possible future development of surrogate target evaluation methods is also included.

This SAE Aerospace Recommended Practice (ARP) provides a framework for establishing methods and stakeholder responsibilities to ensure that seats with integrated electronic components (e.g., actuation system, reading light, inflatable restraint, inflight entertainment equipment, etc.) meet the seat TSO minimum performance standard. These agreements will allow seat suppliers to build and ship TSO-approved seats with integrated electronic components. The document presents the roles and accountabilities of the electronics manufacturer (EM), the seat supplier, and the TC/ATC/STC applicant/holder in the context of AC 21-49 Section 7.b (“Type Certification Using TSO-Approved Seat with Electronic Components Defined in TSO Design”). This document applies to all FAA seat TSOs C39( ), C127( ), etc.The document defines the roles and responsibilities of each party involved in the procurement of electronics, their integration on a TSO-approved seat, and the seat’s installation on an aircraft.

This SAE Aerospace Standard (AS) provides the method for presentation of gas turbine engine steady-state and transient performance calculated using computer programs. It also provides for the presentation of parametric gas turbine data including performance, weight, and dimensions computed by computer programs. This standard is intended to facilitate calculations by the program user without unduly restricting the method of calculation used by the program supplier. This standard is applicable, but not limited to, the following program types: data reduction, steady-state, transient, preliminary design, study, specification, status, and parametric programs.

This proposed revision of the Aerospace Recommended Practice (ARP6973) will provide minor edits to the existing document, plus an alternative third method for measuring the aircraft noise level reduction of building façades that is currently being validated. Airports and their consultants will be able to use any of the three methods presented in this revised ARP to determine the eligibility of structures exposed to aircraft noise to participate in an FAA-funded Airport Noise Mitigation Project, to determine the treatments required to meet project objectives, and to verify that such objectives are satisfied.

The range of test conditions on the dynamometer shall be sufficient to determine the primary operating characteristics corresponding to the full range of vehicle operations. The characteristics to be determined are: a Torque ratio versus speed ratio and output speed b Input speed versus speed ratio and output speed c Efficiency versus speed ratio and output speed d Capacity factor versus speed ratio and output speed e Input torque versus input speed NOTE: For more information about these characteristics and the design of hydrodynamic drives, refer to “Design Practices: Passenger Car Automatic Transmissions,” SAE Advances in Engineering, AE-18 (Third Ed.) or AE-29 (Fourth Ed.).

This SAE Aerospace Recommended Practice (ARP) documents a common understanding of terms, compliance issues, and design criteria to facilitate certification of seat installations specific to Part 25 aircraft. This ARP provides general guidance for seats to be installed in Part 23 aircraft and Parts 27 and 29 rotorcraft and does not specify specific designs or design methods for such certification.

This SAE Aerospace Standard defines the requirements for establishing a nondestructive inspection (NDI) program for aerospace systems to include but not limited to aircraft structure, aircraft stores (external structures such as antennas, pods, fuel tanks, weapons, radomes, etc.) and missile/rocket structural components when an NDI Program Plan is required by contract. NDI Programs are essential to ensuring NDI processes are implemented to support the lifecycle design requirements of the system and its components. NDI Programs are applicable to all phases of the system life cycle, including acquisition, modification, and sustainment. This standard may also be applicable to mechanical equipment, subsystems, and propulsion systems, but the requirements defined by the NDI Program Plan should be tailored by the contracting agency for such use.

This document provides a method/procedure for specifying the properties of vulcanized elastomeric materials (natural rubber or synthetic rubbers, alone or in combination) that are intended for, but not limited to, use in rubber products for automotive applications. This document covers materials that do not contain any re-use, recycled, or regrind materials unless otherwise agreed to by manufacturer and end user. The use of such materials, including maximum percent, must be specified using a “Z” suffix. This classification system covers thermoset High Consistency Elastomers (HCEs) only. Thermoplastic Elastomer (TPE) materials are classified using SAE J2558. Silicone Formed In Place Gasket (FIPG) systems such as Room Temperature Vulcanized (RTV) Silicones, and Liquid Silicone Rubber (LSR) systems are classified using ASTM F2468.

This document outlines the evaluation and documentation appropriate when the components of an approved aircraft seat restraint system are replaced or modified by a party other than the Original Equipment Manufacturer of the restraint system.

This SAE Aerospace Information Report (AIR) provides a comprehensive overview of primary water content measurement instrumentation, for both facility-based icing research and in-flight icing research, over the range of commonly used aircraft certification icing envelopes. It includes information on the theory of operation of the instruments, system errors and limitations, and practical considerations when using them for cloud characterization. This document does not address other icing cloud measurements of interest, such as particle sizing, or measurement of phenomena such as snow, sleet, or hail.

The purpose of this standard is to provide uniform methods for defining, quantifying, and classifying the residual stress in metallic structural alloy products and finished parts. These stresses may exist within a single element, or they may be the result of a joining process. Such quantification and classification may be required when residual stresses within mill stock or preforms can impact further in-process distortion during machining or other processes, and when residual stresses within finished components can impact final mechanical properties and performance (especially strength, durability, and fracture performance).

This paper describes a recommended practice and procedure for the correlation of test cells that are used for the performance testing of APU (auxiliary power unit) engines. Test cell correlation is performed to determine the effect of any given test cell enclosure and equipment on the performance of an engine relative to the baseline performance of that engine. The baseline performance is generally determined at the original equipment manufacturer (OEM) designated test facility. Although no original equipment manufacturer (OEM) documents are actually referenced, the experience and knowledge of several OEMs contributed to the development of this document. Each engine Manufacturer has their own practices relating to correlation and they will be used by those OEMs for the purpose of establishing certified test facilities.

This paper describes a recommended practice and procedure for the correlation of test cells that are used for the performance testing of turboprop and turboshaft engines. This Aerospace Recommended Practice (ARP) shall apply to both dynamometer and propeller based testing. Test cell correlation is performed to determine the effect of any given test cell enclosure and equipment on the performance of an engine relative to the baseline performance of that engine. Although no original equipment manufacturer (OEM) documents are actually referenced, the experience and knowledge of several OEMs contributed to the development of this document. Each engine manufacturer has their own practices relating to correlation and they will be used by those OEMS for the purpose of establishing certified test facilities.

This SAE Recommended Practice describes a test method for determination of heavy truck (Class VI, VII, and VIII) tire force and moment properties under cornering conditions. The properties are acquired as functions of normal force and slip angle using a sequence specified in this practice. At each normal force increment, the slip angle is continually ramped or stepped. The data are suitable for use in vehicle dynamics modeling, comparative evaluations for research and development purposes, and manufacturing quality control. This document is intended to be a general guideline for testing on an ideal machine. Users of this SAE Recommended Practice may modify the recommended protocols to satify the needs of specific use-cases, e.g., reducing the recommended number of test loads and/or pressures for benchmarking purposes. However, due care is necessary when modifying the protocols to maintain data integrity.