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This SAE Aerospace Standard (AS) specifies laboratory test procedures and minimum requirements for the manufacturer of restraint systems for use in civil aircraft. It is intended to establish a minimum level of quality which can be called upon by the designer of those systems. However, compliance with this standard alone may not assure adequate performance of the restraint system under normal and emergency conditions. Such performance requires consideration of factors beyond the scope of this standard, and must be demonstrated by a system evaluation procedure which includes the seat, the occupant, the specific restraint installation and the cabin interior configuration. This standard specifies the requirements for Type 1, Type 2, and Type 3 restraint systems. Buckles that release automatically or through any means other than the direct action of the fingers or thumb on the buckle are beyond the scope of this standard.

This SAE Aerospace Standard (AS) defines minimum performance standards, qualification requirements, and minimum documentation requirements for passenger and crew seats in civil rotorcraft, transport aircraft, and general aviation aircraft. The goal is to achieve comfort, durability, and occupant protection under normal operational loads and to define test and evaluation criteria to demonstrate occupant protection when a seat/occupant/restraint system is subjected to statically applied ultimate loads and to dynamic impact test conditions set forth in the applicable Federal Regulations 14 CFR 23, 25, 27, or 29. Guidance for test procedures, measurements, equipment, and interpretation of results is also presented to promote uniform techniques and to achieve acceptable data. While this document addresses system performance, responsibility for the seating system is divided between the seat supplier and the installation applicant.

This SAE Aerospace Standard (AS) defines minimum performance standards, qualification requirements, and minimum documentation requirements for passenger and crew seats in civil rotorcraft, transport aircraft, and general aviation aircraft. The goal is to achieve comfort, durability, and occupant protection under normal operational loads and to define test and evaluation criteria to demonstrate occupant protection when a seat/occupant/restraint system is subjected to statically applied ultimate loads and to dynamic impact test conditions set forth in Title 14, Code of Federal Regulations (14 CFR) parts 23, 25, 27, or 29 (as applicable to the seat type, see Table 1). Guidance for test procedures, measurements, equipment, and interpretation of results is also presented to promote uniform techniques and to achieve acceptable data. While this document addresses system performance, responsibility for the seating system is divided between the seat supplier and the installation applicant.

This SAE Aerospace Standard (AS) defines minimum performance standards, qualification requirements, and minimum documentation requirements for passenger and crew seats in civil rotorcraft, transport aircraft, and general aviation aircraft. The goal is to achieve comfort, durability, and occupant protection under normal operational loads and to define test and evaluation criteria to demonstrate occupant protection when a seat/occupant/restraint system is subjected to statically applied ultimate loads and to dynamic impact test conditions set forth in the applicable Federal Regulations 14 CFR 23, 25, 27, or 29. Guidance for test procedures, measurements, equipment, and interpretation of results is also presented to promote uniform techniques and to achieve acceptable data. While this document addresses system performance, responsibility for the seating system is divided between the seat supplier and the installation applicant.

This SAE Aerospace Standard (AS) defines minimum performance standards, qualification requirements, and minimum documentation requirements for passenger and crew seats in civil rotorcraft, transport aircraft, and general aviation aircraft. The goal is to achieve comfort, durability, and occupant protection under normal operational loads and to define test and evaluation criteria to demonstrate occupant protection when a seat/occupant/restraint system is subjected to statically applied ultimate loads and to dynamic impact test conditions set forth in Title 14, Code of Federal Regulations (14 CFR) parts 23, 25, 27, or 29 (as applicable to the seat type, see Table 1). Guidance for test procedures, measurements, equipment, and interpretation of results is also presented to promote uniform techniques and to achieve acceptable data. While this document addresses system performance, responsibility for the seating system is divided between the seat supplier and the installation applicant.

This document is a guide to the application of magnesium alloys to aircraft interior components including but not limited to aircraft seats. It provides background information on magnesium, its alloys and readily available forms such as extrusions and plate. It also contains guidelines for “enabling technologies” for the application of magnesium to engineering solutions including: machining, joining, forming, cutting, surface treatment, flammability issues, and designing from aluminum to magnesium.

This document provides informational background, rationale and a technical case to allow consideration of the removal of the magnesium alloy restriction in aircraft seat construction as contained in AS8049B. The foundation of this argument is flammability characterization work performed by the FAA at the William J. Hughes Technical Center (FAATC), Fire Safety Branch in Atlantic City, New Jersey, USA. The rationale and detailed testing results are presented along with flammability reports that have concluded that the use of specific types of magnesium alloys in aircraft seat construction does not increase the hazard level potential in the passenger cabin in a post-crash fire scenario. Further, the FAA has developed a lab scale test method, reference DOT/FAA/TC-13/52, to be used as a certification test, or method of compliance (MOC) to allow acceptability of the use of magnesium in the governing TSO-C127 and TSO-C39C.

This document provides informational background, rationale and a technical case to allow consideration of the removal of the magnesium alloy restriction in aircraft seat construction as contained in AS8049B. The foundation of this argument is flammability characterization work performed by the FAA at the William J. Hughes Technical Center (FAATC), Fire Safety Branch in Atlantic City, New Jersey, USA. The rationale and detailed testing results are presented along with flammability reports that have concluded that the use of specific types of magnesium alloys in aircraft seat construction does not increase the hazard level potential in the passenger cabin in a post-crash fire scenario. Further, the FAA has developed a lab scale test method, reference DOT/FAA/TC-13/52, to be used as a certification test, or method of compliance (MOC) to allow acceptability of the use of magnesium in the governing TSO-C127 and TSO-C39C.

This document provides an industry-recommended framework for establishing agreements to ensure that seats with integrated electronic components (e.g., actuation system, reading light, inflatable restraint, IFE, etc.) meet the seat TSO Minimum Performance Standard. These agreements will allow Seat Suppliers to build and ship completed, integrated and approved seat assemblies under TSOA with electronics included. The document presents the roles, responsibilities and accontibilities of the Electronics Manufacturer, the Seat Supplier, and the Seat Installer/Electronics Activator 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).

This document provides an industry recommended framework for establishing a multi-party agreement to support approval of electronic components (e.g., actuation system, reading light, inflatable restraint, IFE, etc.) integrated in aircraft seats and provide a framework that allows seat manufacturers to build and ship completed, integrated, and approved seat assemblies with electronics included. The primary purpose of this document is to provide roles, responsibilities and accountabilities to meet AC 21-49 Section 7.b ‘Type Certification using TSO-approved seat with electronic components defined in TSO design’. This document may be applied to all applicable seat TSOs (C39(), C127()…etc). The approval for the integration of the electronics will fall, in part or in full, under the type design authority of the Seat Installer rather than the Seat Supplier shipping the integrated seat.

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.