Department of Transportation August 16, 2013 – Federal Register Recent Federal Regulation Documents

The National Highway Traffic Safety Administration (NHTSA) published in the Federal Register of July 9, 2013, a request for comments about thefts of model year (MY) 2011 passenger motor vehicles that occurred in calendar year (CY) 2011. This document corrects errors that were made in that publication. In the July 9, 2013 publication, the vehicle theft rate for CY/MY 2011 vehicles was erroneously reported to be 0.10 thefts per thousand vehicles produced. The actual theft rate for CY/MY 2011 vehicles is 0.99 thefts per thousand vehicles produced. Accordingly, Figure 1: Theft Rate Data Trend (1993-2011) has been amended to reflect the revised theft rate for CY/MY 2011. The publication also erroneously reported that the theft rate for CY/MY 2011 decreased significantly by 91.45 percent from the theft rate for CY/MY 2010 vehicles. The publication should be corrected to reflect that the theft rate for CY/MY 2011 decreased significantly by 15.38 percent from the theft rate for CY/MY 2010 vehicles (1.17 thefts per thousand vehicles). The republishing of this document in its entirety corrects those errors. This document also extends the comment period to allow 60 days from the publication of this notice. Publication of these data fulfills NHTSA's statutory obligation to periodically obtain accurate and timely theft data, and publish the information for review and comment.

This action proposes to establish Class E airspace at Sisseton, SD. Controlled airspace is necessary to accommodate new Standard Instrument Approach Procedures (SIAP) at Sisseton Municipal Airport. The FAA is taking this action to enhance the safety and management of Instrument Flight Rules (IFR) operations for SIAPs at the airport.

The FAA is issuing this notice to advise the public of a meeting of the ARAC.

We propose to supersede airworthiness directive (AD) 2002-10- 11, which applies to certain the Boeing Company Model 737-100, -200, - 200C, -300, -400, and -500 series airplanes. AD 2002-10-11 currently requires repetitive inspections for cracking and corrosion of the aft pressure bulkhead, and corrective actions if necessary; and, for certain airplanes, enlargement of frame chord drain holes, and repetitive inspections of the frame chord drain path for debris, and corrective actions if necessary. Since we issued AD 2002-10-11, we have received three reports of severe corrosion in the area affected by that AD. This proposed AD would, for certain airplanes, reduce the repetitive inspection interval, and add repetitive inspections of the frame chord drain path for obstructions and debris, and corrective actions if necessary. This proposed AD would also limit corrosion and cracking repairs of the aft pressure bulkhead accomplished after the effective date of this AD to those approved by the FAA in a manner described therein. In reviewing AD 2002-10-11, we noted that the drain path inspection was not required for certain airplanes, and could be eliminated for all airplanes if operators accomplished certain actions required by AD 2002-10-11. This proposed AD would add a drain path inspection for all airplanes. We are proposing this AD to detect and correct corrosion or cracking of the aft pressure bulkhead, which could result in loss of the aft pressure bulkhead web and stiffeners, and consequent rapid decompression of the airplane.

We are superseding airworthiness directive (AD) 2004-15-07, for certain Airbus Model A310 series airplanes. AD 2004-15-07 required repetitive inspections for fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors of the bottom skin panel of the wings, and related corrective action. AD 2004- 15-07 also provided for an optional terminating action to end the repetitive inspections. This new AD reduces the initial inspection compliance time and intervals, and provides additional terminating action options. This AD was prompted by a reassessment of a previous fatigue threshold and inspection interval, which resulted in a determination that reduced inspection thresholds and intervals for accomplishment of the tasks are necessary. We are issuing this AD to detect and correct fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors and the bottom skin panel of the wings, which could result in reduced structural integrity of the wings.

PHMSA is proposing to amend the pipeline safety regulations to incorporate by reference (IBR) all or parts of new, updated, or reaffirmed editions of voluntary consensus standards that are available on the Internet, free-of-charge, to the public. PHMSA is also proposing to make non-substantive edits and to clarify regulatory language in certain provisions. These proposed changes are relatively minor, and would not require pipeline operators to undertake any significant new pipeline safety initiatives.

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 727 airplanes. This AD was prompted by an evaluation by the design approval holder indicating that the frame-to- floor beam attachment is subject to widespread fatigue damage. This AD requires repetitive high frequency eddy current inspections for any crack of the frames at body station (STA) 188 through STA 344, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking at the frame-to-floor beam attachment, on both the left- and right-sides, which could result in reduced structural integrity of the airplane, and decompression of the cabin.

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of an inboard main landing gear (MLG) door assembly departure due to premature fatigue cracking in the inboard MLG door hinge fittings. This AD requires repetitive inspections for cracking of the inboard MLG door hinge fittings; and replacement or modification of cracked fittings. This AD also provides an option to remove the affected MLG door. We are issuing this AD to detect and correct fatigue cracking in the inboard MLG door hinge fittings, which could result in loss of the MLG door assembly from the airplane, and the MLG door assembly could impact the flight control surfaces and result in reduced controllability of the airplane.