Department of Transportation April 11, 2016 – Federal Register Recent Federal Regulation Documents

The FHWA and the State of California acting by and through its Department of Transportation (Caltrans), propose a renewal of the State's participation in the 23 U.S.C. 326 program. This program allows FHWA to assign to States its authority and responsibility for determining whether certain designated activities within the geographic boundaries of the State, as specified in the proposed Memorandum of Understanding (MOU), are categorically excluded from preparation of an Environmental Assessment or an Environmental Impact Statement under the National Environmental Policy Act. An amended MOU would renew the State's participation in the program. The MOU will be amended by incorporating the following change: FHWA may terminate the State's participation in this program if FHWA provides the State a notification of non-compliance, and a period of not less than 120 days to take corrective action as FHWA determines necessary, and if the State fails to take satisfactory corrective action as determined by FHWA.

We propose to adopt a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with high-pressure compressor (HPC) stage 8-10 spool, part numbers (P/Ns) 1694M80G04, 1844M90G01, or 1844M90G02, installed. This proposed AD was prompted by reports of cracks found on the seal teeth of the HPC stage 8-10 spool. This proposed AD would require eddy current inspections (ECIs) or fluorescent penetrant inspections (FPIs) of the HPC stage 8-10 spool seal teeth and removing from service those parts that fail inspection. We are proposing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane.

We propose to adopt a new airworthiness directive (AD) for Airbus Helicopters Model EC130B4, EC130T2, AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This proposed AD would require inspecting each bi-directional suspension cross-bar (cross-bar) for a crack. This proposed AD is prompted by two reports of cracks in a cross-bar. The proposed actions are intended to detect cracks in a cross-bar and prevent failure of the cross-bar and subsequent loss of control of the helicopter.

We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model EC225LP, AS332C, AS332L, AS332L1, and AS332L2 helicopters. This AD requires inspecting each TECALEMIT flexible hydraulic hose (hose) installed in the main gearbox (MGB) compartment and replacing the hose if a crack, cut, or other damage exists. This AD was prompted by reports about the loss of in-flight hydraulic pressure on Eurocopter France helicopters. The actions of this AD are intended to prevent loss of the hydraulic system and consequently, loss of helicopter control.

We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes. This AD requires repetitive eddy current high frequency (ETHF) inspections for any cracking in the left and right side center wing lower skin, and corrective actions if necessary. This AD was prompted by reports of cracking at certain stringers, associated end fittings, and skins in the center wing fuel tank where the stringers meet the end fittings. We are issuing this AD to detect and correct cracking in the center wing lower skin. Such cracking could cause structural failure of the wings.

We are superseding Airworthiness Directive (AD) 2015-20-13 for certain Piper Aircraft, Inc. Models PA-28-161, PA-28-181, and PA-28R- 201 airplanes. AD 2015-20-13 required inspecting the right wing rib at wing station 140.09 for cracks and taking necessary corrective action. This AD retains the actions for AD 2015-20-13 and adds airplanes to the applicability. This AD was prompted by reports that additional airplanes have been found with the same cracks. We are issuing this AD to correct the unsafe condition on these products.

We are adopting a new airworthiness directive (AD) for certain Airbus Defense and Space S.A. Model CN-235-200 and CN-235-300 airplanes. This AD was prompted by reports of false engine fire warning events, which consequently led to engine in-flight shutdowns. This AD requires modification of the location and routing of the engine fire detection system. We are issuing this AD to prevent unnecessary engine in-flight shutdown, which could result in reduced controllability of the airplane.

We are superseding Airworthiness Directive (AD) 95-18-08 for all Airbus Model A300-600 series airplanes. AD 95-18-08 required repetitive inspections to detect cracks in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, and repair if necessary. This new AD, for certain airplanes, reduces the compliance times for the inspections. This AD was prompted by a report that updated fatigue and damage tolerance analyses and a fleet survey found that certain inspection thresholds and intervals must be reduced to allow more timely findings of cracking. We are issuing this AD to detect and correct fatigue-related cracking in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, which could result in reduced structural integrity of the wing.

We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes), and Model A310 series airplanes. This AD was prompted by reports of insufficient clearance for the electrical wiring bundles in the leading and trailing edges of the right-hand (RH) and left-hand (LH) wings. This AD requires modifying the electrical routing installation at the RH and LH wings. We are issuing this AD to prevent insufficient clearance of electrical wiring bundles located in the leading and trailing edges of the RH and LH wings, which could lead to chafing damage and arcing, possibly resulting in an on-board fire.