Federal Aviation Administration December 23, 2009 – Federal Register Recent Federal Regulation Documents

The FAA proposes to adopt a new airworthiness directive (AD) for Honeywell International Inc. auxiliary power units (APU) models GTCP36-150(R) and GTCP36-150(RR). This proposed AD would require inspecting the fuel control unit (FCU) differential pressure (Delta P) sleeve bore for erosion, replacing the FCU if it fails the inspection, and installing a fuel deflector on the Delta P sleeve of the FCU. This proposed AD results from eight reports of fuel leakage from the fuel control unit. We are proposing this AD to prevent fuel leakage in the APU compartment, which could lead to ignition of fuel vapor, creating a fire and explosion hazard resulting in injury, and damage to the APU and the airplane.

This supplemental NPRM revises an earlier proposed airworthiness directive (AD) applicable to IAE V2500-A1, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 turbofan engines. That proposed AD would have required a one-time inspection of certain vortex reducers for cracks, and replacing the reducer and high-pressure (HP) compressor stage 3-8 drum if the reducer is cracked. That proposed AD resulted from reports of fractured vortex reducers found at shop visits. This supplemental NPRM revises the proposed AD to add four engine models and four additional part numbers of HP compressor stage 3-8 drums to the applicability requirement. This proposed AD results from the manufacturer's latest service information containing engine models and drum assembly P/Ns that were not specified in the proposed AD. We are proposing this AD to inspect for cracks in the vortex reducer. Cracks in the vortex reducer could result in an uncontained failure of the HP compressor stage 3-8 drum and subsequent damage to the airplane.

These special conditions are issued for the Cessna Aircraft Company, model 525C airplane. This airplane will have a novel or unusual design feature(s) associated with high fuel temperature. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These proposed special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

The FAA is correcting information in an existing airworthiness directive (AD) that was published in the Federal Register on October 1, 2009. The error resulted in use of an outdated division name and e-mail

The FAA invites public comments about our intention to request the Office of Management and Budget's (OMB) revision of a current information collection. The Federal Register Notice with a 60-day comment period soliciting comments on the following collection of information was published on October 16, 2009, vol. 74, no. 199, pages 53317-53318. This action responds to the Wendall H. Ford Investment and Reform Act for the 21st Century by requiring that all persons who remove any life-limited aircraft part have a method to prevent the installation of that part after it has reached its life limit.

The FAA invites public comments about our intention to request the Office of Management and Budget's (OMB) revision of a current information collection. The Federal Register Notice with a 60-day comment period soliciting comments on the following collection of information was published on October 16, 2009, vol. 74, no. 199, pages 53313-53314.