Federal Aviation Administration January 31, 2014 – Federal Register Recent Federal Regulation Documents

In accordance with the Paperwork Reduction Act of 1995, FAA invites public comments about our intention to request the Office of Management and Budget (OMB) approval to renew an information collection. The information enables the FAA to evaluate the validity of the user's request for National Airspace (NAS) data from FAA systems and equipment.

In order to provide the public additional time to submit comments on the proposed Policy, the Federal Aviation Administration (``FAA'') is extending the public comment period for thirty days. This action proposes to amend the FAA Policy and Procedures Concerning the Use of Airport Revenue published in the Federal Register at 64 FR 7696 on February 16, 1999 (``Revenue Use Policy'') to clarify FAA's policy on Federal requirements for the use of proceeds from taxes on aviation fuel. Under Federal law, airport operators that have accepted Federal assistance generally may use airport revenues only for airport-related purposes. The revenue use requirements apply to certain state and local government taxes on aviation fuel as well as to revenues received directly by an airport operator. This notice publishes a proposed clarification of FAA's understanding of the Federal requirements for use of revenues derived from taxes on aviation fuel. Briefly, an airport operator or state government submitting an application under the Airport Improvement Program must provide assurance that revenues from state and local government taxes on aviation fuel are used for certain aviation-related purposes. These purposes include airport capital and operating costs, and state aviation programs. In view of the interests of sellers and consumers of aviation fuel, and of state and local government taxing authorities in limits on use of proceeds from taxes touching aviation fuel, this notice solicits public comment on the proposed policy clarification. This notice also solicits comments about whether there are other reasonable interpretations regarding local taxes that are not enumerated here and should be considered by the FAA. Finally, this proposed policy clarification, if finalized, would apply prospectively to use of proceeds from both new taxes and to existing taxes that do not qualify for grandfathering from revenue use requirements.

We propose to supersede Airworthiness Directive (AD) 2012-10- 53 for Eurocopter Deutschland GmbH (ECD) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters. AD 2012-10-53 currently requires, before further flight and at specified intervals, checking and inspecting the upper and lower main rotor hub (MRH) shaft flanges for a crack, and inspecting the lower hub-shaft flange bolt attachment areas for a crack. Since we issued AD 2012-10-53, it has been determined that it is safe to increase the visual inspection intervals of the MRH shaft flanges from 10 hours time-in-service (TIS) to 50 hours TIS and remove the inspection of the lower MRH shaft flange bolt attachment areas. This proposed AD would continue to require checking and inspecting the upper and lower MRH shaft flanges for a crack. The proposed actions are intended to detect a crack on the MRH shaft flange, which if not corrected, could result in failure of the MRH and subsequent loss of control of the helicopter.

We propose to adopt a new airworthiness directive (AD) for Airbus Model EC225LP helicopters. This proposed AD would require repetitive visual and tap test inspections of each main rotor blade (blade) leading edge stainless steel protective strip (strip) for a crack, cut, or blind or open debonding (debonding), and taking approved corrective measures. If there is a crack or if there is debonding that exceeds acceptable limits, this AD would require, before further flight, repairing or replacing the blade with an airworthy part. This proposed AD is prompted by suspected water seepage through a crack in the blade strip resulting in significant debonding. The proposed actions are intended to prevent loss of the blade strip, excessive vibrations induced by blade weight imbalance, and subsequent loss of control of the helicopter.

We propose to adopt a new airworthiness directive (AD) for British Aerospace Regional Aircraft Jetstream Series 3101 and Jetstream Model 3201 airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as inadequate instructions for inspection for corrosion on the rudder upper hinge bracket and certain internal wing and drainage paths. We are issuing this proposed AD to require actions to address the unsafe condition on these products.

We are adopting a new airworthiness directive (AD) for Eurocopter Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, and AS350D1 helicopters. This AD requires measuring the distance between the end of the main rotor collective pitch lever (collective) locking stud (locking stud) and the locking strip and repairing the locking stud if the clearance is insufficient. This AD was prompted by a report that insufficient distance between the locking stud and the locking strip may cause the collective to become inadvertently locked in the low pitch (low) position. The actions of this AD are intended to prevent the collective from becoming inadvertently locked in the low position and subsequent loss of control of the helicopter.

We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B and EC155B1 helicopters. This AD requires repetitively inspecting the lower and upper front and rear fittings (fittings) that attach the upper fin to the fenestron for a crack and, if there is a crack, removing all four fittings from service. This AD also requires, within a specified time, removing all fittings from service, and the fittings would not be eligible to be installed on any helicopter. This AD was prompted by the loss of an upper fin in flight. The actions of this AD are intended to detect a crack in the fittings to prevent loss of the upper fin and subsequent loss of control of the helicopter.