Federal Aviation Administration 2005 – Federal Register Recent Federal Regulation Documents

This document proposes superseding an existing airworthiness directive (AD) that currently applies to Eurocopter France (ECF) Model SA 365N, N1, and AS 365N2 helicopters. That AD currently requires inspecting the main gearbox (MGB) suspension diagonal cross-member (diagonal cross-member) for cracks and replacing it with an airworthy part if any crack is found. This action proposes to require more frequent inspections of the diagonal cross-member and adding the Model SA-366G1 helicopters to the applicability. This proposal is prompted by several reports of cracks in the diagonal cross-member. The actions specified by the proposed AD are intended to prevent failure of the diagonal cross-member, pivoting of the MGB, severe vibrations, and a subsequent forced landing.

The FAA is superseding an existing airworthiness directive (AD), which applies to all Aerospatiale Model ATR42-200, ATR42-300, and ATR42-320 airplanes. That AD currently requires inspections to determine the proper installation of rivets in certain key holes and to detect cracks in the area of the key holes where rivets are missing; and correction of discrepancies. The existing AD also requires various inspections of the subject area for discrepancies, and corrective actions if necessary; and replacement of certain cargo door hinges with new hinges. For certain airplanes, the existing AD also requires replacement of friction plates, stop fittings, and bolts with new parts. This new AD requires additional corrective actions for certain airplanes. This AD results from discovery of cracks around key holes on certain fuselage frames where rivets were missing. We are issuing this AD to prevent fatigue cracks of the cargo door skin, certain frames, and entry door stop fittings and friction plates, which could result in reduced structural integrity of the airplane.

The FAA is superseding an existing airworthiness directive (AD) that applies to certain EMBRAER Model EMB-135 and Model EMB-145 series airplanes. The existing AD currently requires repetitive inspections of the spring cartridges of the elevator gust lock system to determine if the lock washer projection correctly fits the slots in the cartridge flange, and corrective action if necessary. The existing AD also provides for optional terminating action for the repetitive inspections for certain airplanes. This AD retains the requirements of the existing AD and adds a requirement for final terminating action for all affected airplanes. This AD results from reports of an improperly fitting lock washer causing the clevis of the spring cartridge in the electromechanical elevator gust lock system to become unscrewed. We are issuing this AD to prevent the unscrewing of the spring cartridge clevis from jamming the elevator, which could lead to reduced controllability of the airplane.

The FAA is adopting a new airworthiness directive (AD) for certain Learjet Model 45 airplanes. This AD requires modifying the electrical wire bundle for the alternator on the left-hand engine, inspecting for clearance between wire harnesses and engine tubing for each engine, and corrective actions if necessary. For certain airplanes, this AD also requires replacing the fuses for the hydraulic shutoff valves with fuses having higher amperage. This AD results from a report of a fire in the left-hand engine nacelle. We are issuing this AD to prevent chafing between the wire bundle for the alternator on each engine and the hydraulic lines, which could result in a fire in the engine nacelle.

The FAA invites public comments about our intention to request the Office of Management and Budget's (OMB) renewal of a current information collection. The Federal Register Notices with a 60-day comment period soliciting comments on the following collection of information was published on July 27, 2005, vol. 143, pages 43502-43503. 14 CFR Part 121 prescribes the requirements governing air carrier operations. The information collected is used to determine air operators' compliance with the minimum safety standards set out in the regulation and the applicant's eligibility for air operations certification.

Under the provisions of Title 49, U.S.C. 47153(c), the Federal Aviation Administration is requesting public comment on the Owensboro- Daviess County Regional Airport Board's request to change a portion (2.362 acres) of airport property from aeronautical use to non- aeronautical use. The property is to be sold to The City of Owensboro, Kentucky for the completion of a connector walkway to David C. Adkisson Greenbelt Park. The 2.362 acres is located on the northeast boundary of Owensboro- Daviess County Regional Airport; adjacent to and immediately west of the Wendell Ford Expressway, adjacent to and immediately south of Bittel Road, Daviess County, Kentucky.

These special conditions are issued to Cessna Aircraft Co., for the Type Certificate of Model 510 Mustang airplane. This airplane will have novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. The novel and unusual design features include the installation of an Electronic Flight Instrumentation System (EFIS), Digital Air Data Computer (ADC), and a Full Authority Digital Engine Control (FADEC). The applicable regulations do not adequately consider failure of electrical and electronic systems performing critical functions from the effects of external HIRF. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to the airworthiness standards applicable to this airplane.

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A319, A320, and A321 series airplanes. The existing AD currently requires repetitive inspections to detect wear of the inboard flap trunnions, and to detect wear or de-bonding of the protective half-shells; corrective actions, if necessary; and terminating action. This proposed AD would remove the repetitive inspections to detect wear of the inboard flap trunnions and to detect wear or de-bonding of the protective half-shells; and corrective actions if necessary. This proposed AD would add repetitive detailed inspections of the inboard flap trunnions for any wear marks and of the sliding panels for any cracking at the long edges, and corrective actions if necessary. This proposed AD would also add airplanes to the applicability. This proposed AD results from reports of wear damage to the inboard flap trunnions after incorporation of the terminating modification. We are proposing this AD to detect and correct wear of the inboard flap trunnions, which could lead to loss of flap surface control and consequently result in the flap detaching from the airplane. A detached flap could result in damage to the tail of the airplane.

These special conditions are issued to Garmin AT, Inc., 2345 Turner Rd. SE, Salem, OR 97302, for a Supplemental Type Certificate for the Mooney M20M and M20R. These airplanes will have novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. These novel and unusual design features include the installation of an electronic flight instrument system (EFIS) display, Model G-1000, manufactured by Garmin International, for which the applicable regulations do not contain adequate or appropriate airworthiness standards for the protection of these systems from the effects of high intensity radiated fields (HIRF). These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to the airworthiness standards applicable to these airplanes.

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 adopting a new airworthiness directive (AD) for McCauley Propeller Systems propeller assemblies, models 2D34C53/74E-X; D2A34C58/90AT-X; 3AF32C87/82NC-X; D3AF32C87/82NC-X; D3A32C88/82NC-X; D3A32C90/82NC-X; and 3AF34C92/90LF-X. This AD requires, within 10 flight hours or 10 days after the effective date of this AD, whichever occurs first, removing certain serial number propeller hubs from service. This AD results from a report by the manufacturer that they manufactured and released 40 propeller hubs with improperly machined socket retention threads. We are issuing this AD to prevent cracked propeller hubs, which could cause failure of the propeller hub, blade separation, and loss of control of the airplane.

This notice announces the availability of and requests comments on a proposed advisory circular (AC) which sets forth an acceptable means, but not the only means, of demonstrating compliance with the provisions of the airworthiness standards for transport category airplanes related to Fuel Tank Flammability Reduction. This proposed AC complements revisions to the airworthiness standards that are being proposed by a separate notice. This notice is necessary to give all interested persons an opportunity to present their views on the proposed AC.

This action withdraws the notice of proposed rulemaking (NPRM) published in the Federal Register on November 7, 2002 (67 FR 67801). In that action, the FAA proposed to revise Federal Airway V-257 between the Phoenix, AZ, Very High Frequency Omni-directional Radio Range and Tactical Air Navigation Aids (VORTAC) and the Drake, AZ, VORTAC. The FAA has determined that withdrawal of the proposed rule is warranted since the proposed action would require the revision of numerous instrument procedures in the Phoenix area.

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.

This notice announces a public meeting of the FAA's Aviation Rulemaking Advisory Committee (ARAC) to discuss transport airplane and engine (TAE) issues.

The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 series airplanes, and Model A320-111 airplanes. This AD requires an inspection to determine whether certain braking and steering control units (BSCUs) are installed or have ever been installed. For airplanes on which certain BSCUs are installed or have ever been installed, this AD requires an inspection of the nose landing gear (NLG) upper support and corrective action if necessary, and a check of the NLG strut inflation pressure and an adjustment if necessary. For some of these airplanes, this AD also requires a revision to the aircraft flight manual to incorporate an operating procedure to recover normal steering in the event of a steering failure. This AD results from a report of an incident where an airplane landed with the NLG turned 90 degrees from centerline. We are issuing this AD to prevent landings with the NLG turned 90 degrees from centerline, which could result in reduced controllability of the airplane.

This NPRM proposes new rules that will require operators and manufacturers of transport-category airplanes to take steps that, in combination with other required actions, should greatly reduce the chances of a catastrophic fuel-tank explosion. The proposal follows seven years of intensive research by the FAA in collaboration with industry into promising technologies designed to make fuel tanks effectively inert, thus preventing electrical and other systems from igniting flammable vapors in the fuel tank ullage (vapor space). The result of that research is that fuel tank inerting, originally thought to be prohibitively expensive, can now be accomplished in a reasonably cost-effective fashion and protect the public from future calamities which, we have concluded, are otherwise virtually certain to occur. The new rules, if adopted, would not actually direct the adoption of specific inerting technology either by manufacturers or operators but would establish a performance-based set of requirements that do not specifically direct the use of fuel-inerting but rather set acceptable levels of flammability exposure in tanks most prone to explosion or require the installation of an ignition mitigation means in an affected fuel tank. Technology now provides a variety of commercially feasible methods to accomplish these vital safety objectives.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-300 series airplanes. This AD requires replacing the frequency converters used to supply power for medical and galley utility outlets with modified frequency converters, and related actions. This AD results from a report indicating that a hard short circuit condition between the output of certain frequency converters and their downstream circuit breakers will produce a continuous output current that could cause the undersized output wiring to overheat when the frequency converters fail to shut off. We are issuing this AD to prevent overheating of the output wiring of the frequency converters, which could result in the failure of a wire bundle and consequent adverse effects on other systems sharing the affected wire bundle.

The Federal Aviation Administration (FAA) has adopted a policy which, when implemented, will result in the expunction of airman identities from certain FAA accident and incident records.

This action proposes to modify the St. Louis, MO, (STL) Class B airspace area. Specifically, this action proposes airspace changes to contain large, turbine-powered aircraft operations to and from the new Runway 11/29 at the Lambert-St. Louis International Airport (KSTL), St. Louis, MO. The FAA is proposing this action to enhance safety and improve the management of aircraft operations in the KSTL terminal area. Further, this effort supports the FAA's national airspace redesign goal of optimizing terminal and en route airspace areas to reduce aircraft delays and improve system capacity.

This action establishes the Class E airspace area at Hillsboro Municipal Airport, Hillsboro, TX (INJ), to provide adequate controlled airspace for the area navigation (RNAV) global positioning system (GPS) standard instrument approach procedure (SIAP).

This action revokes Class E airspace, Eagle, Colorado published in the Federal Register October 13, 2005 (70 FR 59652). The FAA is taking this action due to errors in the effective date, airspace description, and geographic coordinates.

The FAA is superseding an existing airworthiness directive (AD), which applies to all BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This new AD requires revising the ALS of the Instructions for Continued Airworthiness to incorporate new and more restrictive life limits for certain items and new and more restrictive inspections to detect fatigue cracking in certain structures. This new AD results from issuance of a later revision to the airworthiness limitations of the BAe/Avro 146 Aircraft Maintenance Manual, which specifies new inspections and compliance times for inspection and replacement actions. We are issuing this AD to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.

The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-135 airplanes, and Model EMB-145, -145ER, - 145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD requires modification of the upper frame of the firewall for the auxiliary power unit (APU). This AD results from the discovery of a hole in the upper frame of the firewall for the APU. We are issuing this AD to ensure that the APU compartment is isolated from the rest of the airplane in the event of an APU fire. If the APU compartment is not isolated, smoke could enter the passenger cabin in the event of an APU fire.