Department of Transportation March 12, 2013 – Federal Register Recent Federal Regulation Documents
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Special Conditions: GE Aviation CT7-2E1 Turboshaft Engine Model
These final special conditions are issued for the General Electric Aviation (GE) CT7-2E1 engine model. This engine model will have a novel or unusual design feature, which is a combination of two existing ratings into a new rating called ``flat 30-second and 2-minute OEI'' rating. This rating is intended for the continuation of flight of a multi-engine rotorcraft after one engine becomes inoperative. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These final special conditions contain the additional safety standards the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
Airworthiness Directives; The Boeing Company Airplanes
We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This proposed AD was prompted by reports of spanwise cracks and corrosion in the wing center box upper skin and rear spar upper chord between left buttock line (LBL) 70.50 and right buttock line (RBL) 70.50 at body station (STA) 870. This proposed AD would require repetitive inspections of the wing center box for cracking around certain fastener rows on the rear spar upper chord horizontal flange; for certain airplanes, repetitive inspections for cracking of the rear spar upper chord radius; for certain other airplanes, repetitive inspections for damage, cracking, and corrosion of the pressure seal; and repair if necessary. We are proposing this AD to detect and correct cracking and corrosion of the upper skin and rear spar upper chord of the wing center box, which could result in loss of the airplane wing and consequent loss of control of the airplane.
Airworthiness Directives; Bombardier, Inc. Airplanes
We are revising an earlier proposed airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. That NPRM proposed to require an inspection to determine if certain rudder feel trim units (RFTUs) are installed, an operational check for signs of seizure of affected parts, repetitive lubrication for certain RFTUs, and replacement of the RFTU if necessary. Installing replaced RFTUs with conformal bushings would terminate the repetitive lubrication requirements. That NPRM was prompted by reports of movement of the rudder pedals being impeded due to corrosion of the trunnion shaft of the RFTU. This action revises that NPRM by reducing compliance times, increasing compliance costs, expanding affected parts to include additional serial numbers and include those parts with a suffix `A,' and adding the condition of rough movement to the operational check. We are proposing this AD to detect and correct any sign of rough movement or seizure of the trunnion shaft and its bushing, which could cause a rudder control jam or a large and rapid alternating rudder input leading to a structural failure of the vertical fin. Since these actions impose an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes.
Waiver of Aeronautical Land-Use Assurance: Rolla National Airport (VIH), Rolla, MO
The Federal Aviation Administration (FAA) is considering a proposal from the City of Rolla (sponsor), Rolla, MO, to release a 10 acre parcel (Lot 1) of land from the federal obligation dedicating it to aeronautical use and to authorize this parcel to be used for revenue-producing, non-aeronautical purposes.
Airworthiness Directives; Sikorsky Aircraft-Manufactured Model S-64F Helicopters
We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation-manufactured Model S-64F helicopters, now under the Erickson Air-Crane Incorporated (Erickson) Model S-64F type certificate. This AD supersedes an existing AD which requires inspections, rework, and replacement, if necessary, of the main gearbox (MGB) second stage lower planetary plate (plate). Since we issued that AD, the manufacturer has conducted a configuration review and analysis, and a review of the service history of certain components. The actions of this AD are intended to establish life limits for certain components, remove various parts from service, and require consistency in the part numbers of certain four bladed tail rotor (T/R) assemblies to prevent fatigue cracking, failure from static overload, and subsequent loss of control of the helicopter.
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