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

We propose to adopt a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-200, and CN-235-300 airplanes. This proposed AD was prompted by reports of main landing gear (MLG) access doors detaching from the airplane as a result of excessive vibration and metal fatigue in the attach fittings. This proposed AD would require modification of the MLG access door by replacing seals in the MLG fairing and, for certain airplanes, adding an additional bolt. We are proposing this AD to prevent a fracture in the MLG access door associated with excessive vibration and metal fatigue in the attach fittings. This condition could lead to MLG access door detachment and consequent impact of flight controls, resulting in reduced control of an airplane.

We are superseding Airworthiness Directive (AD) 2013-22-11 for certain The Boeing Company Model 747-400 and -400D series airplanes. AD 2013-22-11 required repetitive inspections to detect cracks in the floor panel attachment fastener holes of certain upper deck floor beam upper chords, repetitive inspections, corrective actions if necessary, and replacement of the upper deck floor beam upper chords. Since we issued AD 2013-22-11, we received a report that certain fastener holes in the upper deck floor beam upper chords may not have been inspected in accordance with AD 2013-22-11. This AD adds additional repetitive inspections for cracks for certain airplanes, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam. Such cracks could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane.

We are superseding airworthiness directive (AD) 92-06-10 for SOCATA Models MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150ST, Rallye 150T, Rallye 235E, and Rallye 235C airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 fatigue failure of the nose landing gear wheel axle. We are issuing this AD to require actions to address the unsafe condition on these products.

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by reports indicating that the ram air turbine (RAT) assembly may fail to operate if deployed at low airspeeds. This AD requires replacing either the RAT pump and control module assembly or the entire RAT assembly. We are issuing this AD to prevent failure of the RAT assembly to operate at low air speeds. The volume fuse on the RAT assembly may be activated in-flight before the RAT is deployed. This may lead to improper pump hydraulic pressure offloading when the RAT is needed. Failure of the RAT to operate in an all engine out event would result in loss of control of the airplane.

Continental Tire the Americas, LLC (CTA), has determined that certain Continental Tire brand T-type spare tires do not fully comply with paragraph S4.3(a) of Federal Motor Vehicle Safety Standard (FMVSS) No. 109, New Pneumatic and Certain Specialty Tires. CTA has filed a report dated August 25, 2015 and amended on October 1, 2015, pursuant to 49 CFR part 573, Defect and Noncompliance Responsibility and Reports.

Morgan 3 Wheeler Limited (Morgan) has determined that certain model year (MY) 2012 and 2013 Morgan model M3W three-wheeled motorcycles do not comply with all of the requirements of Federal Motor Vehicle Safety Standard (FMVSS) No. 108, Lamps, reflective devices, and associated equipment. Specifically, the vehicles' headlamps are spaced further apart than permitted, and do not have the required ``DOT'' marking. Morgan has petitioned for an exemption from the recall notification and remedy requirements of 49 U.S.C. Chapter 301``Motor Vehicle Safety'' (Vehicle Safety Act) on the grounds that the noncompliances are inconsequential to motor vehicle safety. This notice announces and explains NHTSA's denial of Morgan's petition.

FMCSA announces receipt of applications from 46 individuals for exemption from the prohibition against persons with insulin-treated diabetes mellitus (ITDM) operating commercial motor vehicles (CMVs) in interstate commerce. If granted, the exemptions would enable these individuals with ITDM to operate CMVs in interstate commerce.

The Federal Transit Administration (FTA) issued Safety Advisory 16-1 regarding stop signal overruns on rail fixed guideway public transportation systems, and an accompanying letter to the State Safety Oversight (SSO) program managers and the chief safety officers of rail transit systems, seeking data and information on stop signal overruns during 2015. Safety Advisory 16-1 and the accompanying letter are available in their entirety on the FTA public Web site at https://www.fta.dot.gov/tso.html.

This notice contains a summary of a petition seeking relief from specified requirements of title 14 of the Code of Federal Regulations. The purpose of this notice is to improve the public's awareness of, and participation in, the FAA's exemption process. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of the petition or its final disposition.

This notice contains a summary of a petition seeking relief from specified requirements of title 14 of the Code of Federal Regulations. The purpose of this notice is to improve the public's awareness of, and participation in, the FAA's exemption process. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of the petition or its final disposition.

This notice contains a summary of a petition seeking relief from specified requirements of title 14 of the Code of Federal Regulations. The purpose of this notice is to improve the public's awareness of, and participation in, the FAA's exemption process. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of the petition or its final disposition.

On March 29, 2016, the Federal Transit Administration (FTA) published a Notice of Funding Opportunity (NOFO) in the Federal Register announcing the availability of approximately $211 million for Grants for Buses and Bus Facilities and $55 million for Low or No Emission Grants. The notice provided incomplete information regarding FTA's Buy America and Disadvantage Business Enterprise (DBE) requirements. Additionally, the NOFO was missing information in one place about how to submit applications through www.grants.gov. This notice corrects the March 29 notice.

We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes, and Model DHC-8-200 and -300 series airplanes. This proposed AD was prompted by a report of heat damage found on a nacelle firewall after an unsuccessful engine ground start and several events of heat damage found on direct current starter/generator terminal block assemblies. This proposed AD would require an inspection for damage on the nacelle firewalls and the terminal block assemblies and to make sure the insulating sleeves are installed and have no damage, and corrective action if necessary. We are proposing this AD to prevent arcing between the firewall and terminal blocks that are missing insulating sleeves on the conductive bushings, which could, in combination with a fuel or hydraulic fluid leak, be an ignition source for a fire.

We propose to supersede Airworthiness Directive (AD) 2008-15- 06, which applies to certain Textron Aviation Inc. Models 175 and 175A airplanes (type certificate previously held by Cessna Aircraft Company). AD 2008-15-06 currently requires checking the airplane logbook to determine if the original engine mounting brackets have been replaced. If the original engine mounting brackets are still installed, the AD requires repetitively inspecting those brackets for cracks and replacing any cracked engine mounting bracket until all four original engine mounting brackets are replaced. Replacing all four original engine mounting brackets terminates the actions required in AD 2008-15- 06. Since we issued AD 2008-15-06, we have determined that the applicability needs to be changed to add a serial number and take one out. This proposed AD would retain the actions required in AD 2008-15- 06 and would change the Applicability section. We are proposing this AD to correct the unsafe condition on these products.

We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, -200, and -300 series airplanes. This proposed AD was prompted by a report of a manufacturing defect that affects the durability of affected parts in the cargo and cabin compartment. This proposed AD would require an inspection of affected structural parts in the cargo and cabin compartments to determine if proper heat-treatment has been done, and replacement if necessary. We are proposing this AD to prevent crack initiation and propagation, which could result in reduced structural integrity of the fuselage.

We propose to adopt a new airworthiness directive (AD) for Airbus Helicopters Model AS355NP helicopters with certain fire extinguishing systems. This proposed AD would require removing and installing the fire extinguishing system so that each squib on the engine compartment fire extinguisher is controlled by a matching control button. This proposed AD is prompted by the discovery that the left-hand discharge system of the fire extinguishing system was incorrectly connected to the right-hand engine compartment and the right-hand discharge system was incorrectly connected to the left-hand engine compartment. The proposed actions would correct the connections and would prevent the fire extinguishing system discharging to the wrong engine compartment, failure of the fire extinguishing system to control a fire, and subsequent loss of control of the helicopter.

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.