Department of Transportation 2005 – Federal Register Recent Federal Regulation Documents

This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron (Bell) Model 47D1, 47G, 47G-2, 47G-2A, 47G-2A- 1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A and Coastal Helicopters, Inc. Model OH-13H (Tomcat Mark 5A, 6B, 6C) helicopters that have a certain scissors assembly or weld assembly scissors bracket installed. The AD requires, within 60 days, determining and recording the total hours time-in-service (TIS) for each Parts Manufacturer Approval (PMA)-produced scissors assembly and weld assembly scissors bracket and establishes a life limit for each affected part. This amendment is prompted by the need to establish a life limit on scissors assemblies and weld assembly scissors brackets produced under PMA No. PQ808SW or installed per Supplemental Type Certificate (STC) No. SH2772SW. The actions specified by this AD are intended to establish a life limit to prevent using a scissors assembly or weld assembly scissors bracket past it's life limit, which could result in failure of the part and subsequent loss of control of the helicopter.

This amendment supersedes an existing airworthiness directive (AD) for the MD Helicopters, Inc. (MDHI) Model 369A, H, HE, HM, HS, D, and E helicopters with a certain part-numbered main rotor blade (blade) and modified with a Helicopter Technology Company, LLC (HTC), Supplemental Type Certificate (STC) No. SR09172RC, SR09074RC, or SR09184RC. That AD currently requires recording on the component history card or equivalent record (record) each torque event (TE) on each blade, inspecting both surfaces of the blade, and replacing any cracked blade with an airworthy blade. Also, that AD establishes life limits for certain part-numbered blades. This amendment revises the model applicability, adds MDHI part-numbered blades, removes any reference to the life limits of the blades, changes the requirements for inspecting the blades, and revises the STC applicability. This amendment also provides that compliance with portions of certain documents constitutes alternative methods of compliance with portions of this AD, contains editorial changes for clarification, and makes some corrections. This amendment is prompted by additional reports of cracked blades and by the comments received in response to AD 2003-24- 01. The actions specified in this AD are intended to detect fatigue cracking of the blade to prevent blade failure and subsequent loss of control of the helicopter.

This amendment supersedes an existing airworthiness directive (AD) that applies to Pratt & Whitney (PW) JT8D-200 series turbofan engines. That AD currently requires installing and periodically inspecting individual or sets of certain part number (P/N) temperature indicators on the No. 4 and 5 bearing compartment scavenge oil tube and performance of any necessary corrective action. This AD requires installing and periodically inspecting two temperature indicators on all PW JT8D-200 series turbofan engines, including those incorporating high pressure turbine (HPT) containment hardware. This AD results from five uncontained HPT shaft failures. We are issuing this AD to prevent oil fires and the resulting fracture of the HPT shaft which can result in uncontained release of engine fragments; engine fire; in-flight engine shutdown; and possible airplane damage.

The FAA is notifying operators of a proposed advisory circular entitled ``Guidance on Aircraft Noise Certification Documents for International Flights.'' This advisory circular (AC) is in response to the International Civil Aviation Organization (ICAO) adoption of three acceptable options for managing noise certification documents. This AC offers guidance to affected operators on aircraft noise certification documentation they may choose to carry on board the aircraft that fly to a foreign country. This AC is designed to assist operators in preparing noise certification documents that may be requested by foreign authorities or airports. A suggested document format for operators to present noise certification documentation is provided.

The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 135: Environmental Conditions and Test Procedures for Airborne Equipment.

This action establishes two colored Federal airways, Amber-5 (A-5) and Blue 1 (B-1), in Alaska. This action adds to the instrument flight rules (IFR) airway and route structure in Alaska. The FAA is taking this action to enhance safety and the management of aircraft operations in Alaska.

This action corrects an error in the legal description of a direct final rule, request for comments that was published in the Federal Register on Friday, July 29, 2005 (70 FR 43744).

As authorized by Public Law 105-383 and Public Law 107-295, the Secretary of Transportation, as represented by the Maritime Administration (MARAD), is authorized to grant waivers of the U.S.- build requirement of the coastwise laws under certain circumstances. A request for such a waiver has been received by MARAD. The vessel, and a brief description of the proposed service, is listed below. The complete application is given in DOT docket 2005-22695 at https:// dms.dot.gov. Interested parties may comment on the effect this action may have on U.S. vessel builders or businesses in the U.S. that use U.S.-flag vessels. If MARAD determines, in accordance with Public Law 105-383 and MARAD's regulations at 46 CFR part 388 (68 FR 23084; April 30, 2003), that the issuance of the waiver will have an unduly adverse effect on a U.S.-vessel builder or a business that uses U.S.-flag vessels in that business, a waiver will not be granted. Comments should refer to the docket number of this notice and the vessel name in order for MARAD to properly consider the comments. Comments should also state the commenter's interest in the waiver application, and address the waiver criteria given in Sec. 388.4 of MARAD's regulations at 46 CFR part 388.

The FHWA is issuing a notice to advise the public that an Environmental Impact Statement (EIS) will be prepared for a proposed highway project in Yamhill County, Oregon.

Consistent with Agency practice, this notice is issued to advise interested parties of the addition of the States of Idaho and Utah to the list of those thirty-three states from which the Aircraft Registration Branch (FAA Aircraft Registry), Mike Monroney Aeronautical Center, Oklahoma City, Oklahoma, will accept artisan liens for recordation. Since December 17, 1981, the Aeronautical Center Counsel has issued these notices in the Federal Register.

This final rule will revised Class E airspace at Cheyenne, WY. New Instrument Flight Rules (IFR) routes sequences from the en route environment to/from Cheyenne Regional Airport/Jerry Olson Field makes this proposal necessary. Additional controlled airspace extending upward from 1,200 feet above the surface is necessary for the safety of aircraft. This action also correct as an error in the geographic coordinates of the Cheyenne Very High Frequency Omnidirectional Range Colocated Tactical Air Navigation and the airport designation.

This final rule will establish Class E airspace at Eagle, CO. Additional Class E airspace is necessary to accommodate aircraft using a new Instrument Landing System or Localizer Distance Measuring Equipment (ILS or LOC DME) Standard Instrument Approach Procedure (SIAP) at Eagle County Regional Airport. This change is necessary for the safety of Instrument Flight Rules (IFR) aircraft executing the new SIAP at Eagle County Regional Airport, Eagle, CO.

The Federal Aviation Administration (FAA) is issuing this notice to advise the public that an Environmental Impact Statement (EIS) will be prepared to assess the potential impacts of the proposed relocation of Runway 11R/29L and associated development at Tucson International Airport. To ensure that all significant issues related to the proposed action are identified, one (1) public scoping meeting and one (1) governmental agency scoping meeting will be held.

These special conditions are issued for Learjet Model 35 series airplanes modified by Avcon Industries Inc. These modified airplanes will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. The modification incorporates the installation of new Kollsman 24771 Air data computers and Thommen AD30 displays. The applicable airworthiness regulations do not contain adequate or appropriate safety 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 that established by the existing airworthiness standards.

The Federal Aviation Administration (FAA) announces the availability of proposed policy for the repair and alteration of rotating turbine engine-life limited parts (RTE-LLPs). This proposed policy establishes that the FAA will treat all repairs and alterations of RTE-LLPs as major repairs and major alterations. We are also proposing that all RTE-LLP repair and alteration data must include a methodology to assess the life of the repaired or altered part and the continued operational safety of the repaired product. This proposed policy provides guidance for: (1) Technical substantiation for repair or alteration of RTE-LLPs; and (2) Aircraft Certification Offices (ACOs) and Designated Engineering Representatives to evaluate and approve repair and alteration data.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200CB, and -200PF series airplanes. This AD requires an inspection of each trailing edge flap transmission assembly to determine the part number and serial number, and related investigative and corrective actions and part marking if necessary. This AD results from a report indicating that cracked flap transmission output gears have been discovered during routine overhaul of the trailing edge flap transmission assemblies. We are issuing this AD to prevent an undetected flap skew, which could result in a flap loss, damage to adjacent airplane systems, and consequent reduced controllability of the airplane.

The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires examining the airplane's maintenance records to determine if the main landing gear (MLG) has been overhauled and if Titanine JC5A (also known as Desoto 823E508) corrosion- inhibiting compound (``CIC'') was used during the overhaul. For airplanes for which the maintenance records indicate that further action is necessary, or for airplanes on which CIC JC5A may have been used during manufacture, this AD requires a one-time detailed inspection for discrepancies of certain components of the MLG, and corrective action if necessary. This AD results from twelve reports of severe corrosion on one or more of three components of the MLG. We are issuing this AD to prevent collapse of the MLG, or damage to hydraulic tubing or the aileron control cables, which could result in possible departure of the airplane from the runway and loss of control of the airplane.

The FAA is superseding an existing airworthiness directive (AD) for Type R321/4-82-F/8, R324/4-82-F/9, R333/4-82-F/12, and R334/4- 82-F/13 propeller assemblies. That AD currently requires initial and repetitive ultrasonic inspections of propeller hubs, part number (P/N) 660709201. This AD requires the same initial and repetitive ultrasonic inspections, but reduces the initial and repetitive compliance times for Type R334/4-82-F/13 propeller assemblies when used on Construcciones Aeronauticas, S.A. (CASA) 212 airplanes. This AD results from a report of a hub separation on a CASA 212 airplane. We are issuing this AD to prevent propeller hub failure due to cracks in the hub, which could result in loss of control of the airplane.

In compliance with the National Environmental Policy Act of 1969, the FHWA, in cooperation with the Georgia Department of Transportation (GDOT), have jointly prepared a Draft Supplemental Environmental Impact Statement (DSEIS) for proposed transportation improvements in the US 411 Corridor. The project is within Bartow County. The DSEIS identifies various alternatives and the associated environmental impacts of the proposed alternatives. Interested citizens are invited to review the DSEIS and submit comments. Copies of the DSEIS may be obtained by telephoning or writing the contact person listed below under ADDRESSES. Public reading copies of the DSEIS are available at the locations listed under SUPPLEMENTARY INFORMATION.

This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727, 727C, 727-100, and 727-100C series airplanes. This AD requires repetitive inspections of the frame inner chord, outer chord, and web of the forward and aft edge frames of the lower lobe forward cargo door (FCD) cutout, and corrective action if necessary. The actions specified by this AD are intended to detect and correct fatigue cracking of the forward and aft edge frames of the lower lobe FCD cutout, which could result in the loss of the FCD and rapid decompression of the airplane. This action is intended to address the identified unsafe condition.

The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A340-211, -212, -311, and -312 airplanes. This AD requires an initial rotating probe inspection and initial and repetitive ultrasonic inspections for discrepancies of the first fastener hole of the horizontal flange of the keel beam on previously modified airplanes, installation of new fasteners, and corrective action if necessary. This AD results from a report that certain inspections done before accomplishing the modification of the lower keel beam fitting and forward lower shell connection, revealed cracking that was outside the modification limits specified in the service bulletin; the cracking was repaired by installing a titanium doubler. We are issuing this AD to find and fix discrepancies of the fastener holes of the horizontal flange of the keel beam, which could result in reduced structural integrity of the fuselage.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 300, 747SP, and 747SR series airplanes. This AD requires repetitive inspections to detect cracks in various areas of the upper deck floor beams, and repair if necessary. This AD results from fatigue testing that revealed severed upper chords of the upper deck floor beams due to fatigue cracking. We are issuing this AD to detect and correct cracking in the upper chords of the upper deck floor beams. Undetected cracking could result in large deflection or deformation of the upper deck floor beams, resulting in damage to wire bundles and control cables for the flight control system, and reduced controllability of the airplane. Multiple adjacent severed floor beams could result in rapid decompression of the airplane.