Federal Aviation Administration June 2012 – Federal Register Recent Federal Regulation Documents

The FAA is issuing this notice to advise the public of the meeting of RTCA Special Committee 223, Airport Surface Wireless Communications.

This notice announces the FAA's intent to cancel TSO-C68a, Airborne automatic dead reckoning computer equipment utilizing aircraft heading and Doppler ground speed and drift angle data. The effect of the cancelled TSO-68a will result in no new TSO-C68a design or production approvals.

We propose to adopt a new airworthiness directive (AD) for all Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This proposed AD was prompted by a report that the safe life limit and inspection requirements for the horizontal stabilizer trim actuator (HSTA) attachment pins and trunnions were not listed in the Airworthiness Limitations Section of the maintenance program. This proposed AD would require inspecting the trunnions and upper and lower pins for gouges, scratches, and corrosion, and replacing if necessary; and adding serial numbers and new part numbers to certain trunnions, and upper and lower pins. This proposed AD would also require revising the maintenance program to incorporate the information specified in certain temporary revisions of the limitations section. We are proposing this AD to detect and correct cracking, gouges, scratches, and corrosion of the HSTA attachment pins and trunnions, which could result in failure of these pins and trunnions and consequent disconnection of the horizontal stabilizer and subsequent loss of controllability of the airplane.

The Federal Aviation Administration (FAA) is considering a proposal to change a portion of the airport from aeronautical use to nonaeronautical use and to authorize the conversion of the airport property. The proposal consists of one parcel of land containing a total of approximately 3.19 acres located on the west side of the airport at the corner of Hazel Street and 4th Street. The parcel was originally acquired as part of a donation to the County of Saline in 1999. The land comprising this parcel is outside the forecasted need for aviation development and, thus, is no longer needed for indirect or direct aeronautical use. The airport wishes to develop this land for compatible commercial, nonaeronautical use. The income from the conversion of this parcel will benefit the aviation community by reinvestment in the airport. Approval does not constitute a commitment by the FAA to financially assist in the conversion of the subject airport property nor a determination of eligibility for grant-in-aid funding from the FAA. The disposition of proceeds from the conversion of the airport property will be in accordance with FAA's Policy and Procedures Concerning the Use of Airport Revenue, published in the Federal Register on February 16, 1999. In accordance with Section 47107(h) of Title 49, United States Code, this notice is required to be published in the Federal Register 30 days before modifying the land-use assurance that requires the property to be used for an aeronautical purpose.

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 Eurocopter France Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with certain Aerazur emergency flotation gear attachment brackets (brackets) installed. This proposed AD would require an initial and recurring inspection of the brackets for a crack, and if there is a crack, replacing the cracked bracket with an airworthy bracket. This proposed AD is prompted by reports of cracks on the brackets. The proposed actions are intended to prevent failure of the emergency flotation system and loss of float stability in the event of a water landing.

We propose to adopt a new airworthiness directive (AD) for all Eurocopter France (Eurocopter) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365C, SA-365C1, SA-365C2, and SA-366G1 helicopters. This proposed AD is prompted by reports of corrosion on the main gearbox (MGB) casing lower area between the two servo-control anchoring fitting attachment ribs. An investigation determined that the corrosion was associated with sealing compound on the lower part of the fitting/casing attachment. The proposed actions are intended to detect corrosion on the MGB casing, which could lead to a crack, failure of the MGB, and subsequent loss of control of the helicopter.

We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A300 B4-601, B4-603, and B4-605R airplanes, Model A300 F4-605R airplanes, Model A300 C4-605R Variant F airplanes, and Model A310-204 and -304 airplanes, powered by General Electric (GE) CF6-80C2 series engines. This proposed AD was prompted by reports of two single-engine flame-out events during inclement weather. This proposed AD would require installing a shunt of the rotary selector (introducing an auto-relight function). We are proposing this AD to prevent a long engine restart sequence after a non-selection of continuous re-light by the crew and a flame-out event of both engines, which could result in reduced controllability of the airplane, especially at low altitude.

We propose to adopt a new airworthiness directive (AD) for certain Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This proposed AD was prompted by reports of in-service events related to electrical power system malfunctions resulting in damage to electrical load management system (ELMS) P200 and P300 power panels and the surrounding area. This proposed AD would require installing enclosure trays to contain debris in certain ELMS panels, and replacing certain ELMS contactors. We are proposing this AD to prevent contactor failures, which could result in uncontained hot debris flow due to ELMS contactor breakdown, consequent smoke and heat damage to airplane structure and equipment during ground operations, and possible injuries to passengers and crew.

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 Federal Register Notice with a 60-day comment period soliciting comments on the following collection of information was published on April 3, 2012, vol. 77, no. 64, page 20093. The information on FAA Form 8420-8, Application for Pilot School Certificates, is required from applicants who wish to be issued pilot school certificates and associated ratings.

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.