# Policy Statement on Acceptance of a Component Test Method To Demonstrate
**AGENCY:**
Federal Aviation Administration (FAA), DOT.
**ACTION:**
Notice of final policy.
**SUMMARY:**
The Federal Aviation Administration (FAA) announces the availability of final policy on a component method for demonstrating that a seat with a replacement bottom cushion complies with § 25.562(c)(2). This policy addresses non-flotation monolithic (single layer) cushions.
**DATES:**
This final policy was issued by the Transport Airplane Directorate on August 9, 2005.
**FOR FURTHER INFORMATION CONTACT:**
Michael T. Thompson, Federal Aviation Administration, Transport Airplane Directorate, Transport Standards Staff, Standardization Branch, ANM-113, 1601 Lind Avenue, SW., Renton, WA 98055-4056; telephone (425) 227-1157; fax (425) 227-1232; e-mail; *[email protected].*
**SUPPLEMENTARY INFORMATION:**
**Disposition of Comments**
A notice of proposed policy; request for comments, was published in the *Federal Register* on April 11, 2005 (70 FR 18453). Three commenters responded to the request for comments.
**Background**
Historically, substantiating changes to the bottom cushion of a seat certificated to § 25.562 that could affect the lumbar load typically required a full-scale 14g downward dynamic test using the actual seat. Industry desired a quicker and less expensive method in lieu of full scale testing. As a result, the FAA funded a research project to develop a component test methodology for demonstrating that a replacement bottom cushion would not produce a higher lumbar load than a certificated bottom cushion for a seat certificated to § 25.562. This research resulted in an acceptable methodology that is documented in DOT/FAA/AR-05/5,I “Development and Validation of an Aircraft Seat Cushion Component Test—Volume I,” dated March 2005. This method provides a simplified means of demonstrating compliance with § 25.562 and will streamline the seat certification process by reducing the costs and time associated with seat certification.
Seat bottom cushion changes must be evaluated to determine that compliance with § 25.562 is maintained when considering both the 14g downward test and the 16g longitudinal test specified in the regulation. This policy addresses demonstrating compliance with the lumbar load criteria of § 25.562(c)(2) that is determined in a 14g downward test.
The final policy memorandum as well as the disposition of public comments received is available on the Internet at the following address: *http://www.airweb.faa.gov/rgl* . If you do not have access to the Internet, you can obtain a copy of the final policy memorandum by contacting the person listed under *FOR FURTHER INFORMATION CONTACT.*
Issued in Renton, Washington, on August 9, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification Service.