Federal Aviation Administration 2013 – Federal Register Recent Federal Regulation Documents

This action corrects a final rule published in the Federal Register August 8, 2013 that establishes Class D airspace at Bryant Army Airfield (AAF), Anchorage, AK. In that rule, an error was made in the legal description for Bryant AAF, in that the language indicating Class D airspace as part time was left out.

This action establishes Class E airspace at the Wasatch VHF Omni-Directional Radio Range Tactical Air Navigational Aid (VORTAC) navigation aid, Wasatch, UT, to facilitate vectoring of Instrument Flight Rules (IFR) aircraft under control of Salt Lake City Air Route Traffic Control Center (ARTCC). This improves the safety and management of IFR operations within the National Airspace System. This action also makes a minor adjustment to the geographic coordinates of the Wasatch VORTAC navigation aid.

This action establishes Class E airspace at Metropolitan Oakland International Airport, Oakland, CA, to accommodate aircraft using the Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Metropolitan Oakland International Airport. This action also modifies Class E surface airspace designated as an extension to Class C airspace by removing the navigation aids from the airspace designation. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.

We are adopting a new airworthiness directive (AD) for AgustaWestland S.p.A. (AgustaWestland) Model A119 and AW119 MKII helicopters to require inspecting the pilot and co-pilot doors to ensure that the windows are properly bonded within the doors. If the windows are not properly bonded, the AD requires applying bonding to the windows, the seals, and the window frames of the pilot and co-pilot doors. This AD was prompted by the loss of a pilot-door window during a test flight. The actions of this AD are intended to ensure the windows do not detach from the doors, potentially injuring persons on the ground and damaging the helicopter's tailboom and the tail rotor blades.

This amendment adopts miscellaneous amendments to the required IFR (instrument flight rules) altitudes and changeover points for certain Federal airways, jet routes, or direct routes for which a minimum or maximum en route authorized IFR altitude is prescribed. This regulatory action is needed because of changes occurring in the National Airspace System. These changes are designed to provide for the safe and efficient use of the navigable airspace under instrument conditions in the affected areas.

The FAA is issuing this notice to advise the public of the ninety-first meeting of the RTCA Special Committee 159, Global Positioning Systems (GPS)

A NPRM published in the Federal Register of September 6, 2013, to amend the Class D airspace ceiling at Addison Airport, Dallas, TX, is being withdrawn. Upon review, the FAA determined that the proposed rulemaking action is premature in that an existing Dallas/Fort Worth Class B airspace rulemaking action is pending.

This action proposes to establish Class D airspace and Class E airspace at Laguna Army Air Field (AAF), (Yuma Proving Ground), Yuma, AZ. The establishment of an air traffic control tower has made this action necessary for the safety and management of Instrument Flight Rules (IFR) aircraft within this airspace.

This action grants with conditions a limited waiver of the slot usage requirement for operating authorizations (slots) at Newark Liberty International Airport (EWR) due to construction at the airport during the summer 2014 scheduling season. This waiver applies only to EWR slots for the following days and local times: (1) March 30 through June 15 for 0600-2259 slots; (2) Mondays through Saturdays from June 16 through September 19 for 0600-0629 slots; (3) Sundays from June 22 through September 14 for 0600-0859 slots; and (4) September 20 through October 25 for 0600-2259 slots.

We propose to supersede airworthiness directive (AD) 2012-12- 08, which applies to certain The Boeing Company Model 777-200 and -300 series airplanes. AD 2012-12-08 requires an inspection for the part number of the fuse pin, and replacement of the pin if necessary. Since we issued AD 2012-12-08, we have determined that additional airplanes may be subject to the identified unsafe condition. This proposed AD would retain the actions required by AD 2012-12-08 and add airplanes to the applicability. We are proposing this AD to prevent structural damage to the side and drag brace lock assemblies, which could result in landing gear collapse during touchdown, rollout, or taxi.

This notice contains a summary of a petition seeking relief from specified requirements of 14 CFR. The purpose of this notice is to improve the public's awareness of, and participation in, this aspect of FAA's regulatory activities. 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.

We propose to adopt a new airworthiness directive (AD) for Diamond Aircraft Industries Model DA 40 and DA 40 F 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 fatigue strength found in the aft main spar does not ensure unlimited lifetime structural integrity. We are issuing this proposed AD to require actions to address the unsafe condition on these products.

The FAA publishes a monthly notice, as appropriate, of PFC approvals and disapprovals under the provisions of the Aviation Safety and Capacity Expansion Act of 1990 (Title IX of the Omnibus Budget Reconciliation Act of 1990) (Pub. L. 101-508) and Part 158 of the Federal Aviation Regulations (14 CFR Part 158). This notice is published pursuant to paragraph d of Sec. 158.29.

The FAA publishes a monthly notice, as appropriate, of PFC approvals and disapprovals under the provisions of the Aviation Safety and Capacity Expansion Act of 1990 (Title IX of the Omnibus Budget Reconciliation Act of 1990) (Pub. L. 101-508) and Part 158 of the Federal Aviation Regulations (14 CFR Part 158). This notice is published pursuant to paragraph d of Sec. 158.29.

The FAA publishes a monthly notice, as appropriate, of PFC approvals and disapprovals under the provisions of the Aviation Safety and Capacity Expansion Act of 1990 (Title IX of the Omnibus Budget Reconciliation Act of 1990) (Pub. L. 101-508) and Part 158 of the Federal Aviation Regulations (14 CFR part 158). This notice is published pursuant to paragraph d of Sec. 158.29.

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by reports of cracked and corroded nuts on an outboard flap support rib. This AD requires, for certain airplanes, repetitive inspections of the cap seal for damaged sealant on nuts common to certain outboard flap support ribs, and related investigative and corrective actions if necessary. For certain other airplanes, this AD also requires repetitive inspections of the cap seal for damaged sealant on nuts common to certain outboard flap support ribs, related investigative and corrective actions if necessary, and if necessary, a detailed inspection to determine the nut type installed in the outboard flap support rib and corrective actions. This AD also provides terminating action for the repetitive inspections under certain conditions. We are issuing this AD to detect and correct cracked and corroded nuts and bolts and the installation of incorrect nuts on certain outboard flap support ribs, which could lead to additional nut and bolt damage in the joint, result in loss of an outboard flap, and adversely affect continued safe flight and landing of the airplane.

We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350 and AS355 helicopters, to require inspecting for a crack in the control lever attachment yokes, and if needed, replacing the tail rotor gearbox (TGB). This AD is prompted by improper casting of TGB casing assemblies, which may lead to cracking. A crack in the control lever attachment yokes could cause a loss of tail rotor pitch control, and consequently, loss of control of the helicopter.

This rule establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.

We propose to supersede an existing airworthiness directive (AD) that applies to certain Continental Motors, Inc. (CMI) IO-520, TSIO-520, and IO-550 series reciprocating engines, with certain replacement parts manufacturer approval (PMA) SAP investment cast cylinder assemblies installed. The existing AD currently requires initial and repetitive inspections and compression tests to detect cracks in those cylinders. Since we issued that AD, we became aware of additional engines that need to be added to the applicability. We are proposing this AD to prevent the separation of the cylinder head, damage to the engine, and damage to the airplane.

We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90-76B, -85B, -90B, -94B, -110B1, and - 115B turbofan engines. This AD was prompted by multiple reports of distress of certain stage 1 high-pressure turbine (HPT) stator shrouds due to accelerated corrosion and oxidation, including one engine in- flight shutdown (IFSD) caused by failure of the HPT stator shrouds. This AD requires initial and repetitive on-wing 360-degree borescope inspections (BSIs) for corrosion and oxidation of stage 1 HPT stator shrouds. If a shroud is found to be distressed, this AD requires reinspection at a reduced interval or removal from service before further flight. We are issuing this AD to prevent failure of stage 1 HPT stator shrouds, resulting in an IFSD of one or more engines, loss of thrust control, and damage to the airplane.

We are superseding revised Airworthiness Directive (AD) 76-12- 07 for all Bell Model 204B and certain serial-numbered Model 205A-1 helicopters with a certain tail rotor pitch control chain (chain) installed. AD 76-12-07 required visually inspecting the chain to detect a crack in the link segments and, for affected Model 205A-1 helicopters, replacing the chain and cable control system with a push- pull control system. This new AD requires, for Bell Model 204B, inspecting certain chains at specified intervals, revising the inspection procedures, installing a tail rotor cable and chain damper kit (damper kit), and revising the maintenance manual or Instructions for Continued Airworthiness (ICAs) to include the inspection intervals. This new AD also requires, for certain Bell Model 205A-1 helicopters, replacing the chain and cable control system with an airworthy tail rotor push-pull control system kit. This AD was prompted by the rapid growth of a crack leading to premature chain failure. The actions are intended to prevent failure of the chain, loss of tail rotor blade pitch control, and subsequent loss of control of the helicopter.

We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B, EC155B1, SA-365N, SA- 365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters. This AD requires inspecting the collective pitch lever for correct locking and unlocking conditions. This AD was prompted by two separate reports of inadvertent collective pitch lever locking and unlocking. The actions of this AD are intended to detect an incorrectly adjusted collective pitch lever, which could result in loss of control of the helicopter.

The FAA withdraws a notice of proposed rulemaking (NPRM) that proposed to rescind airworthiness directive (AD) 2008-06-03, which applies to certain The Boeing Company Model 737-600, -700, -700C, -800 and -900 series airplanes; and Model 757-200, -200PF, -200CB, and -300 series airplanes. The NPRM would have rescinded AD 2008-06-03, which requires an inspection to determine if certain motor-operated shutoff valve actuators for the fuel tanks are installed, and related investigative and corrective actions if necessary. AD 2008-06-03 also requires revising the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness to incorporate certain AWLs. Since the NPRM was issued, we have determined that it does not adequately address the safety concerns. Accordingly, the NPRM is withdrawn.

This action updates, simplifies, and streamlines rules of practice and procedure for filing and adjudicating complaints against federally-assisted airports. It improves efficiency by enabling parties to file submissions with the Federal Aviation Administration (FAA) electronically, and by incorporating modern business practices into how the FAA handles complaints. This amendment is necessary to reflect changes in applicable laws and regulations, and to apply lessons learned since the existing rules were implemented in 1996.

We propose to adopt a new airworthiness directive (AD) for certain the Boeing Company Model DC-9-10, DC-9-30, and DC-9-40 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft pressure bulkhead web area is subject to widespread fatigue damage (WFD). This proposed AD would require modifying the aft pressure bulkhead. The modification includes inspecting for cracks around the rivet holes, and repair of any cracking. We are proposing this AD to prevent fatigue cracking of the aft pressure bulkhead, which could result in reduced structural integrity of the airplane.