Department of Transportation November 22, 2005 – Federal Register Recent Federal Regulation Documents

The Federal Aviation Administration (FAA) has adopted a policy which, when implemented, will result in the expunction of airman identities from certain FAA accident and incident records.

This document announces a decision by the National Highway Traffic Safety Administration (NHTSA) that certain 2001 Chevrolet Blazer (plant code ``K'' or ``2'') multipurpose passenger vehicles (MPVs) that were not originally manufactured to comply with all applicable Federal motor vehicle safety standards (FMVSS) are eligible for importation into the United States because they are substantially similar to vehicles originally manufactured for sale in the United States and that were certified by their manufacturer as complying with the safety standards (the U.S. certified version of the 2001 Chevrolet Blazer (plant code ``K'' or ``2'') MPV), and they are capable of being readily altered to conform to the standards.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) Models 58P and 58TC airplanes used as a lead airplane by the United States Forest Service. This proposed AD would require you to insert a new supplement into the Limitations Section of the Pilot's Operating Handbook and Airplane Flight Manual (POH/AFM) that establishes new limits for the structural life of the airframe (wing, fuselage, empennage, or associated structure); and dispose of the life-limited airframe following 14 CFR 43.10 when the limit of the structural life of the airframe is reached. This proposed AD results from Raytheon issuing a POH/AFM supplement that establishes the structural life limit of 4,500 hours time-in- service (TIS) for the airframe (wing, fuselage, empennage, and associated structure) for any Models 58P and 58TC airplanes used as a lead airplane by the United States Forest Service; and FAA's determination that the structural life limit is necessary. We are issuing this proposed AD to prevent cumulative fatigue damage and fatigue cracking damage that would sufficiently reduce residual strength of the airframe and result in failure. Failure of the airframe (wing, fuselage, empennage, or associated structure) could lead to loss of control of the airplane.

This document grants in full the petition of DaimlerChrysler Corporation (DaimlerChrysler) for an exemption of a high-theft line, the Dodge Charger, from the parts-marking requirements of the Federal Motor Vehicle Theft Prevention Standard. This petition is granted because the agency has determined that the antitheft device to be placed on the line as standard equipment is likely to be as effective in reducing and deterring motor vehicle theft as compliance with the parts-marking requirements of the Theft Prevention Standard.

This action corrects an omission in the legal description of Class E2 airspace in a direct final rule, request for comments correction that was published in the Federal Register on Thursday, October 13, 2005 (70 FR 59651).

The Federal Aviation Administration (FAA) announces the availability of final policy on smoke penetration tests conducted under the provisions of Sec. 25.857.

The FAA is superseding an existing airworthiness directive (AD), which applies to all BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This new AD requires revising the ALS of the Instructions for Continued Airworthiness to incorporate new and more restrictive life limits for certain items and new and more restrictive inspections to detect fatigue cracking in certain structures. This new AD results from issuance of a later revision to the airworthiness limitations of the BAe/Avro 146 Aircraft Maintenance Manual, which specifies new inspections and compliance times for inspection and replacement actions. We are issuing this AD to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.