Federal Aviation Administration 2012 – Federal Register Recent Federal Regulation Documents

These special conditions are issued for the Gulfstream Aerospace LP, Model Gulfstream G280 airplane. This airplane will have novel or unusual design features associated with the architecture and connectivity capabilities of the airplane's computer systems and networks, which may allow access to or by external computer systems and networks. Connectivity to, or access by, external systems and networks may result in security vulnerabilities to the airplane's systems. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. 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 are adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes. This AD was prompted by reports of cracks found on the center section ribs of the horizontal stabilizers. This AD requires repetitive inspections for cracking of the aft face of the left and right rib hinge bearing lugs of the center section of the horizontal stabilizer; and crack measurement, repairs, post-repair repetitive inspections, and installation of a new center section rib if necessary. We are issuing this AD to detect and correct cracking in the left and right bearing lugs of the rib hinge spreading at the same time, which could result in failure of both hinge bearing lugs. Failure of the hinge bearing lugs could result in the inability of the horizontal stabilizer to sustain flight loads and thereby reduce the controllability of the airplane.

We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. That AD currently requires repetitive external detailed inspections or non-destructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S-1 and S-2R, between station (STA) 400 and STA 460, and repair if necessary. This new AD adds inspections for cracking in additional fuselage skin locations, and repair if necessary. This new AD also reduces the inspection thresholds and repetitive intervals for certain airplanes. This AD was prompted by reports of additional crack findings of the fuselage skin at the chem-mill steps. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels at the chem- mill steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane.

We are superseding an existing airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R and A300 F4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A310 series airplanes. That AD currently requires modifying the wiring in the right-hand electronics rack. This new AD requires replacing the cockpit multi-tank indicators (MTI), and for certain airplanes, replacing high-level, low-level, and overflow sensors and their harness connectors, and re-instating the low-level warning indication to the cockpit MTI. This AD was prompted by reports of failures of four fuel level sensor-amplifier and MTI units. This AD also adds Model A310 series airplanes to the applicability. We are issuing this AD to prevent degradation of the electrical insulation sleeves of the low- level indication lamps on the MTI, which could cause a short circuit that might result in high voltage being conveyed to the high- and low- level sensors in the wing tanks. This condition could cause the level sensor to heat above acceptable limits, possibly resulting in a fuel tank explosion, and consequent loss of the airplane.

We are adopting a new airworthiness directive (AD) for all BAE SYSTEMS (Operations) Limited Model 4101 airplanes. This AD was prompted by reports of cracking found in the wing rear spar. This AD requires a one-time detailed inspection for cracks, corrosion, and other defects of the rear face of the wing rear spar, and repair if necessary. We are issuing this AD to detect and correct cracking in the rear spar, which could propagate to a critical length, possibly affecting the structural integrity of the area and resulting in a fuel tank rupture, with consequent damage to the airplane and possible injury to its occupants.

We propose to adopt a new airworthiness directive (AD) for PIAGGIO AERO INDUSTRIES S.p.A. Model P-180 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 jamming of the external bearing of the screwjack drive gear, which resulted in failure of the main wing outboard flap external actuator. We are issuing this proposed AD to require actions to address the unsafe condition on these products.

This action modifies Jet Route J-2, and VOR Federal airways V- 16, V-66 and V-202 in southern Arizona and New Mexico due to the scheduled decommissioning of the Cochise, AZ, VHF Omnidirectional Range Tactical Air Navigation (VORTAC) which currently is used to define segments of the routes.

This action modifies the Colorado Springs, CO, Class C airspace area by amending the legal description to reflect the current airport reference point (ARP) information for the City of Colorado Springs Municipal Airport. The operating requirements remain the same.

We propose to adopt a new airworthiness directive (AD) for the Bell Helicopter Textron, Inc. (BHTI) Model 205A, 205A-1, and 205B helicopters with certain starter/generator power cable assemblies (power cable assemblies). This proposed AD is prompted by the determination that the power cable assembly connector (connector) can deteriorate, causing a short in the connector that may lead to a fire. This AD would require replacing the power cable assemblies and their associated parts, and performing continuity readings. We are proposing this AD to prevent a short in the connector that may lead to a fire in the starter/generator, smoke in the cockpit that reduces visibility, and subsequent loss of helicopter control.

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.

The ``FAA Modernization and Reform Act of 2012,'' enacted on February 14, 2012, in Section 305 of the Act, removed the line check performance evaluation requirements for pilots over 60 years of age that applied to air carriers engaged in part 121 operations. This technical amendment conforms to the FAA's regulations as a result of the Act.

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This proposed AD was prompted by reports of failure of wire support clamps in the forward section of the aft pressure bulkhead. This proposed AD would require a detailed inspection of the clamps on the power feeder cable auxiliary power unit (APU) to determine if certain clamps are installed, and related investigative and corrective actions if necessary. We are proposing this AD to prevent failure of the clamp, which could result in wire chafing and potential arcing and consequent fire in section 48 (a flammable fluid leakage zone) or heat damage to the APU power feeder cable, insulation blankets, or pressure bulkhead.

We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This proposed AD was prompted by reports of movement of the rudder pedals being impeded due to corrosion of the trunnion shaft of the rudder feel trim unit (RFTU). This proposed AD would require inspecting to determine if certain RFTUs are installed, an operational check for signs of seizure of affected parts, repetitive lubrication for certain RFTUs, and replacing the RFTU with a new RFTU if necessary. Installation of replaced RFTUs with conformal bushings terminates the repetitive lubrication requirements. We are proposing this AD to detect and correct any sign of 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.

We propose to supersede an existing airworthiness directive (AD) that applies to certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires a one-time inspection of the shafts of the main landing gear (MLG) side-brace fittings to detect corrosion, and the forward and aft bushings in the left-hand and right-hand MLG side-brace fittings to detect discrepancies. The existing AD also requires corrective and related actions if necessary. Since we issued that AD, we have received reports that the side brace fitting shafts of the MLG continue to fail. This proposed AD would require repetitive detailed inspections for corrosion and damage of the MLG side-brace fitting and replacing the side-brace fitting shaft with the re-designed side-brace fitting shaft of the MLG if necessary. This AD would also require eventual replacement of certain side-brace fitting shafts with the re-designed part. Replacement with a re-designed side-brace fitting shaft of the MLG is terminating action for the repetitive inspections. We are proposing this AD to prevent fractures of the side-brace fitting shafts of the MLG, and possible collapse of the MLG.

Pursuant to Section 10(a)(2) of the Federal Advisory Committee Act (Pub. L. 92-463, 5 U.S.C. App. 2), notice is hereby given of a teleconference of the Operations Working Group (OWG) of the Commercial Space Transportation Advisory Committee (COMSTAC). The teleconference will take place on Tuesday, July 17, 2012, starting at 1 p.m. Eastern Daylight Time. Individuals who plan to participate should contact Susan Lender, Designated Federal Officer (DFO), (the Contact Person listed below) by phone or email for the teleconference call in number. The proposed agenda for this teleconference is to follow up on issues raised during the May 10, 2012, OWG meeting. These issues include: Discussing the question of on-orbit authority for the FAA and the jurisdiction and regulation aspects of this question; and Examining possible next steps for the white paper that discussed possible revisions to the requirements for launch site licensing. Interested members of the public may submit relevant written statements for the COMSTAC working group members to consider under the advisory process. Statements may concern the issues and agenda items mentioned above or additional issues that may be relevant for the U.S. commercial space transportation industry. Interested parties wishing to submit written statements should contact Susan Lender, DFO, (the Contact Person listed below) in writing (mail or email) by July 10, 2012, so that the information can be made available to COMSTAC members for their review and consideration before the July 17, 2012, teleconference. Written statements should be supplied in the following formats: one hard copy with original signature or one electronic copy via email. An agenda will be posted on the FAA Web site at https://www.faa.gov/ go/ast. Individuals who plan to participate and need special assistance should inform the Contact Person listed below in advance of the meeting.

This document proposes to adopt a new airworthiness directive (AD) for Schweizer Aircraft Corporation (Schweizer) Model 269D and Model 269D Configuration A helicopters. The type certificate for these models is currently held by Sikorsky Aircraft Corporation (Sikorsky). This proposal is prompted by reports of loose horizontal stabilizers and cracks in the stabilizer-support structure for the extruded tailboom. The AD would require inspecting the aft fuselage assembly in the area around the attachment point of the horizontal stabilizer, including the paint, for a crack. This AD also would require inspecting the tailboom interior support structure, and if necessary, installing an inspection panel kit in the aft fuselage assembly, and installing doublers in the stabilizer support brackets. The actions specified by the proposed AD are intended to prevent separation of the horizontal stabilizer from the helicopter and subsequent loss of control of the helicopter.

We are adopting a new airworthiness directive (AD) for Cessna 206, 207, and 210 airplanes with Hartzell Engine Technologies (HET) turbochargers, part numbers (P/Ns) 406610-0005 and 406610-9005, installed. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires removing the affected turbochargers from service before further flight. This AD was prompted by a report of an HET turbocharger causing an engine in-flight power rollback. We are issuing this AD to prevent turbocharger bearing seizure, failed turbocharger components, and damage to the airplane.

This action amends Class E Airspace at Orlando, FL, as new Standard Instrument Approach Procedures have been developed at Orlando Executive Airport. This action enhances the safety and airspace management of Instrument Flight Rules (IFR) operations within the National Airspace System. This action also makes a minor adjustment to the geographic coordinates of Orlando Executive Airport, Orlando International Airport, and Kissimmee Municipal Airport.

This action proposes to establish Class E airspace at Fort Morgan, CO. Controlled airspace is necessary to accommodate aircraft using a new Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedure at Fort Morgan Municipal Airport, Fort Morgan, CO. The FAA is proposing this action to enhance the safety and management of aircraft operations at the airport.

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 superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, and -400ER series airplanes. That AD currently requires replacing the separation link assembly on the applicable entry and service doors with an improved separation link assembly, and doing related investigative and corrective actions if necessary. This new AD adds an airplane to the applicability and removes certain other airplanes. This AD was prompted by a report that an additional airplane is subject to the unsafe condition. We are issuing this AD to prevent failure of an entry or service door to open fully in the event of an emergency evacuation, which could impede exit from the airplane. This condition could result in injury to passengers or crewmembers.

We propose to supersede two existing airworthiness directives (AD) that apply to certain Fokker Services B.V. Model F.28 Mark 0100 airplanes. The first existing AD currently requires removing the actuator from the fuel-balance transfer-valve (FBTV) and installing a locking device on the FBTV. The second existing AD currently requires inspecting to verify that the position indicator of the FBTV is in the closed position and deactivating the fuel-balance transfer-system. Since we issued those ADs, we have received reports that the FBTV was inadvertently reactivated after required de-activation measures were undone. This proposed AD would require installing an FBTV locking device. We are proposing this AD to prevent fuel starvation and consequently a double-engine flameout, possibly resulting in a forced landing, damage to the airplane, and injury to occupants.

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 for a new information collection. The Federal Register Notice with a 60-day comment period soliciting comments on the following collection of information was published on August 4, 2011, vol. 76, no. 150, page 47287-47288. The FAA intends to collect safety-related data regarding the voluntary implementation of Commercial Aviation Safety Team (CAST) safety enhancements (SEs) from certificate holders conducting operations under 14 CFR Part 121 and Parts 121/135.

This action modifies Class D and Class E airspace at Bellingham, WA, to accommodate aircraft departing and arriving under Instrument Flight Rules (IFR) at Bellingham International Airport. This action, initiated by the biennial review of the Bellingham airspace area, enhances the safety and management of aircraft operations at the airport.

We are superseding an existing airworthiness directive (AD) for certain Bombardier Inc. Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) airplanes. That AD currently requires repetitive inspections to detect cracking of the lower cap of the wing front and rear spars at wing station (WS) 51.00, and the wing lower skin. Additional actions, if cracking is found, include reworking the lower cap of the front or rear spar, inspecting for cracking, and repairing any cracking. The existing AD also requires reporting inspection results. This new AD requires extending the inspection area of the rear spar lower cap from WS 51.00 to WS 49.50 and modifying the ultrasonic inspection calibration procedure. This AD was prompted by reports of cracking found outside the inspection area. We are issuing this AD to detect and correct cracking of the lower caps of the wing front and rear spars, and lower wing skin, which could result in reduced structural integrity of the airplane.