Federal Aviation Administration 2013 – Federal Register Recent Federal Regulation Documents

This action modifies Class E airspace at Portland-Hillsboro Airport, Portland-Hillsboro, OR, to accommodate aircraft departing and arriving under Instrument Flight Rule (IFR) operations at the airport. Also, the geographic coordinates are updated for the airport. This action, initiated by the biennial review of the Portland-Hillsboro airspace area, improves the safety and management of IFR operations at the airport.

We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 C-2 helicopters. This AD requires revising the operating limitations to prohibit flights under instrument flight rules (IFR) or under night visual flight rules (VFR) when the autotrim is inoperative. The actions of this AD are intended to prevent a workload situation whereby stabilizing the helicopter in flight would be difficult if not impossible, resulting in possible loss of helicopter control.

We are superseding an existing airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. That AD currently requires repetitive inspections to detect cracking of the lower corners of the door frame and cross beam of the forward cargo door, and corrective actions if necessary. That AD also requires eventual modification of the outboard radius of the lower corners of the door frame and reinforcement of the cross beam of the forward cargo door, which terminates the existing repetitive inspections. This new AD revises the compliance times for the preventive modification; adds certain inspections for cracks in the number 5 cross beam of the forward cargo door; and adds inspections of the number 4 cross beam if cracks are found in the number 5 cross beam, and corrective actions if necessary. For certain airplanes, this new AD also adds a one-time inspection for airplanes previously modified or repaired, and a one-time inspection of the reinforcement angle for excessive shimming or fastener pull-up, and corrective actions if necessary. This AD was prompted by additional reports of fatigue cracking in the radius of the lower frames and in the lower number 5 cross beam of the forward cargo door. We are issuing this AD to prevent fatigue cracking of the lower corners of the door frame and number 5 cross beam of the forward cargo door, which could result in rapid depressurization of the airplane.

We propose to adopt a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters to require inspecting each linear transducer bearing (bearing) for freedom of movement. This proposed AD would also require replacing the bearing if there is binding or rough turning or if there is chafing or damage on the lower side of the floor. Also, this proposed AD would require modifying and re-identifying a certain rod. This proposed AD is prompted by an incident involving limited control of a tail rotor because of the binding of a bearing. The proposed actions are intended to detect and replace each bearing subject to binding, which could lead to subsequent loss of control of the helicopter.

We propose to adopt a new airworthiness directive (AD) for Hamilton Standard Division model 6/5500/F and 24PF and Hamilton Sundstrand Corporation model 14RF, 14SF, 247F, and 568F series propellers. This proposed AD was prompted by the amount of corrosion detected during major inspections (MIs). This proposed AD would require incorporating inspections, based on a calendar time, into the propeller maintenance schedule. We are proposing this AD to prevent corrosion that could result in propeller failure and loss of airplane control.

We propose to adopt a new airworthiness directive (AD) for all Eclipse Aerospace, Inc. Model EA500 airplanes equipped with Avio, Avio with ETT, or Avio NG 1.0 avionics suites. This proposed AD was prompted by a report of potential aircraft hardware failure in the autopilot control panel and the center switch panel. This proposed AD would require either incorporating updates to the aircraft computer system or incorporating a temporary revision to the aircraft flight manual. We are proposing this AD to correct the unsafe condition on these products.

We propose to adopt a new airworthiness directive (AD) for all DASSAULT AVIATION Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE-FALCON 200 airplanes; and Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20-F5 airplanes. This proposed AD was prompted by reports of a manufacturing defect in the charge indicator on fire extinguisher bottles. This proposed AD would require repetitive weighing of fire extinguisher bottles having a certain part number, and eventual replacement of those bottles to terminate the repetitive weighing. We are proposing this AD to detect and correct a dormant failure in the fire suppression system, which could result in the inability to put out a fire in an engine, auxiliary power unit, or rear compartment.

This notice contains a summary of a petition seeking relief from specified requirements of Title 14, Code of Federal Regulations (14 CFR). The purpose of this notice is to improve the public's awareness of, and participation in, this aspect of the 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.

This action modifies two jet routes and seven VOR Federal airways; and removes two VOR Federal airways in the vicinity of Jackson, MS. The FAA is taking this action due to the scheduled decommissioning of the Jackson, MS, VORTAC, and the commissioning of the Magnolia, MS, VORTAC.

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 collection of information is for the purpose of obtaining essential information concerning the applicant's professional and personal qualifications. The FAA uses the information provided to screen and select designees who act as representatives of the FAA Administrator in performing various certification and examination functions under Title VI of Federal Aviation Act.

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 collected is needed for applicants' noise certification compliance reports in order to demonstrate compliance with 14 CFR Part 36.

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. This program requires public agencies and certain members of the aviation industry to prepare and submit applications and reports to the FAA. Through this program the FAA provides additional funding for airport development which is needed now and in the future.

This notice contains a summary of a petition seeking relief from specified requirements of Title 14, Code of Federal Regulations (14 CFR). The purpose of this notice is to improve the public's awareness of, and participation in, this aspect of the 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.

In accordance with the National Environmental Policy Act of 1969, as amended (NEPA; 42 United States Code 4321 et seq.), Council on Environmental Quality NEPA implementing regulations (40 Code of Federal Regulations parts 1500 to 1508), and FAA Order 1050.1E, Change 1, Environmental Impacts: Policies and Procedures, the FAA is announcing the availability of the ROD to issue a reentry license to Lockheed Martin Corporation for the reentry of the Orion MPCV from Earth orbit to a location in the Pacific Ocean.

These special conditions are issued for the Cessna Aircraft Company (Cessna) Model J182T airplane. This airplane will have a novel or unusual design feature(s) associated with the installation of an aircraft diesel engine (ADE). The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This proposed AD was prompted by fuel system reviews conducted by the manufacturer. This proposed AD would require, depending on airplane configuration, replacing fuel pump power control relays with new relays having a ground fault interrupter (GFI) feature, installing ground studs and a bonding jumper, doing certain bonding resistance measurements, and changing the GFI relay position. This proposed AD would also require revising the maintenance program to incorporate certain airworthiness limitations. We are proposing this AD to prevent damage to the fuel pumps caused by electrical arcing that could introduce an ignition source in the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.

We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 757-200 and -200PF series airplanes. That AD currently requires modifying the nacelle strut and wing structure, and repairing any damage found during the modification. This new AD specifies a maximum compliance time limit that overrides the optional threshold formula results. This AD was prompted by reports indicating that the actual operational loads applied to the nacelle are higher than the analytical loads that were used during the initial design. Subsequent analysis and service history, which includes numerous reports of fatigue cracking on certain strut and wing structure, indicated that fatigue cracking can occur on the primary strut structure before an airplane reaches its design service objective. We are issuing this AD to prevent fatigue cracking in primary strut structure and consequent reduced structural integrity of the strut.

We are superseding an existing airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A119 and AW119 MKII helicopters. The existing AD currently requires inspecting the pilot and copilot engine rotary variable differential transformer (RVDT) control box assemblies to determine if the control gear locking pin is in its proper position. Since we issued that AD, Agusta has developed a terminating action for this inspection. This AD requires the same actions as the existing AD as well as modifying the RVDT control box assemblies. The actions of this AD are intended to prevent failure of an RVDT control box assembly, loss of manual control of the engine throttle, and subsequent loss of control of the helicopter.

We are revising an earlier proposed airworthiness directive (AD) for certain Hawker Beechcraft Corporation (HBC) Models 58, 58TC, 58P, 95C55, E55, and 56TC airplanes. That NPRM proposed requiring inspections of elevator balance weights and replacement of defective elevator balance weights. That NPRM was prompted by reports of elevator balance weights becoming loose or failing because the balance weight material was under strength and did not meet material specifications. This action revises that NPRM to prohibit the installation of designated spare parts and to clarify applicability. We are proposing this supplemental NPRM to correct the unsafe condition on these products. 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.

This action amends the Order Limiting Operations at Newark Liberty International Airport (EWR) that published on May 21, 2008, and was amended on October 7, 2009, and April 4, 2011. The Order remains effective until the final Rule on Slot Management and Transparency for LaGuardia Airport, John F. Kennedy International Airport, and Newark Liberty International Airport becomes effective but not later than October 24, 2014.

The FAA issued BST a safety approval, subject to the provisions of Title 51 U.S.C Subtitle V, ch. 509, and the orders, rules and regulations issued under it. Pursuant to Title 14 Code of Federal Regulations (14 CFR) Sec. 414.35, this Notice publishes the criteria that were used to evaluate the safety approval application. Background: BST applied for, and received, a safety approval for its ability to provide as a service, scenario based physiology training, which includes hypobaric chamber training. BST may offer its scenario based physiology altitude training as a service to a prospective launch and reentry operator to meet the applicable crew and participant training requirements of 14 CFR 460.5 and 14 CFR 460.51. Criteria Used To Evaluate Safety Approval Application: The performance criteria for this safety approval include 14 CFR 61.31(g) for additional training required for operating pressurized aircraft capable of operating at high altitudes. These criteria are FAA regulations, which are acceptable technical criteria for reviewing a safety approval application per 14 CFR 414.19(a)(1). The FAA's evaluation included assessment of BST's scenario based physiology training lesson plan and objectives, which include classroom and hypobaric chamber training for crew and space flight participants to experience and demonstrate knowledge of the following through testing: Understand fundamental principles of the atmosphere and how it relates to the human body. Understand the fundamentals of respiratory physiology and how it relates to hypoxia. Show competence in the identification of the many different symptoms and physical signs of hypoxia. Show advanced competence in the phenomena of neurological impairment (time of useful consciousness) due to hypoxia. Understand the effects of prolonged oxygen use. Understand the difference between decompression illness and hypoxia. Demonstrate using different scenarios the difference between slow decompression and rapid decompression. Identify personal symptoms of hypoxia and demonstrate donning of oxygen mask and ability to perform within a hypobaric chamber.

We propose to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A318-111 and -112 airplanes, Model A319 series airplanes, Model A320 series airplanes, and Model A321 series airplanes. The existing AD currently requires repetitive inspections of the 80VU rack lower lateral fittings for damage; repetitive inspections of the 80VU rack lower central support for cracking; and corrective action if necessary. That existing AD also specifies optional terminating action for the repetitive inspections. Since we issued that AD, we have received reports of worn lower lateral fittings of the 80VU rack. This proposed AD would reduce the inspection compliance time, add an inspection of the upper fittings and shelves of the 80VU rack, and add airplanes to the applicability. We are proposing this AD to detect and correct damage or cracking of the 80VU fittings and supports, which could lead to possible disconnection of the cable harnesses to one or more computers and, if occurring during a critical phase of flight, could result in reduced control of the airplane.

We propose to supersede an existing airworthiness directive (AD) that applies to all Rolls-Royce plc (RR) model RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61; and RB211 Trent 768-60, 772-60, and 772B-60; and RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17; and RB211-524G2- T-19, -524G3-T-19, -524H-T-36, and -524H2-T-19 turbofan engines that have a high-pressure (HP) compressor stage 1 to 4 rotor disc installed, with a certain part number (P/N) installed. The existing AD requires repetitive inspections of the axial dovetail slots, and follow-on corrective action depending on findings. This proposed AD expands the population of affected parts. This proposed AD also changes, for the purposes of this AD, the definition of ``engine shop visit.'' We are proposing this AD to detect cracks in the HP compressor stage 1 and 2 disc posts, which could result in failure of the disc post and HP compressor blades, damage to the engine, and damage to the airplane.

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 are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of two in-service incidents where the left main landing gear (MLG) failed to extend. This AD requires installing stopper plates on the aft uplock frames in the MLG bay adjacent to the right and left MLG uplock assemblies. We are issuing this AD to prevent incorrect installation of the upper bolt in the MLG uplock assembly, which could prevent the MLG from extending and could adversely affect the safe landing of the airplane.