Department of Transportation October 2005 – Federal Register Recent Federal Regulation Documents

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.

The FAA is adopting a new airworthiness directive (AD) for certain British Aerospace Model HS 748 airplanes. This AD requires relocating the battery earth posts located on the nose landing gear (NLG) pintle webs. This AD results from an accident in which the nose landing leg, together with the pintle webs, detached from the airplane. As a result, the battery earth return cables were severed from their earth posts. We are issuing this AD to prevent loss of safety critical services including fuel shut-off and nacelle fire extinguishing services.

The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-135 airplanes and Model EMB-145, -145ER, -145MR, - 145LR, -145XR, -145MP, and -145EP airplanes. This AD requires repetitive detailed inspections for surface bruising of the main landing gear (MLG) trailing arms and integrity of the MLG pivot axle sealant, and corrective actions if necessary. This AD also provides for optional terminating action for the repetitive detailed inspections. This AD results from a report of a fractured axle of the trailing arm of the MLG due to corrosion of the axle. We are issuing this AD to prevent a broken trailing arm and consequent failure of the MLG, which could lead to loss of control and damage to the airplane during takeoff or landing.

The FAA is adopting a new airworthiness directive (AD) for Aviointeriors S.p.A. (formerly ALVEN), series 312 box mounted seats. This AD requires initial and repetitive inspections of the seat attachments for cracks, and if necessary, replacing the attachments. This AD results from 10 reports of cracked attachments of series 312 box mounted seats. We are issuing this AD to prevent series 312 box mounted seats from detaching from the passenger compartment floor, which could result in injury to the occupant of the seat, and prevent evacuation of passengers in the event of an emergency.

The FAA is revising Airworthiness Directive (AD) 2003-19-14 R1, which applies to certain BURKHART GROB LUFTUND RAUMFAHRT GmbH & CO KG (GROB) Models G103 TWIN ASTIR, G103A TWIN II ACRO, and G103C TWIN III ACRO sailplanes. AD 2003-19-14 R1 requires you to modify the airspeed indicators, install flight speed reduction and aerobatic maneuver restrictions placards (as applicable), and revise the flight and maintenance manuals. AD 2003-19-14 R1 approves simple aerobatic maneuvers for Model G103A TWIN II ACRO sailplanes and provides an option for modifying the rear fuselage for Models G103A TWIN II ACRO and G103C TWIN III ACRO sailplanes to terminate the flight limitation restrictions for aerobatic maneuvers. This AD retains all the actions from AD 2003-19-14 R1 for Models G103A TWIN II ACRO and G103C TWIN III ACRO and reinstates certain operating limits for Model G103 TWIN ASTIR sailplanes. We are issuing this AD to prevent damage to the fuselage during limit load flight, which could result in reduced structural integrity. This condition could lead to loss of control of the sailplane.

In accordance with the Paperwork Reduction Act of 1995, this notice announces the Maritime Administration's (MARAD's) intention to request extension of approval for three years of a currently approved information collection.

The Department of Transportation is directing all interested persons to show cause why it should not issue an order finding MAXjet Airways, Inc., fit, willing, and able, and awarding it a certificate of public convenience and necessity to engage in interstate scheduled air transportation of persons, property and mail.

In response to a petition for rulemaking from the Surge Brake Coalition, the Federal Motor Carrier Safety Administration proposes to amend the Federal Motor Carrier Safety Regulations (FMCSRs) to allow the use of automatic hydraulic inertia brake systems (surge brakes) on trailers operated in interstate commerce. A surge brake is a self- contained permanently closed hydraulic brake system activated in response to the braking action of the tow vehicle. The amount of trailer braking effort developed is proportional to the total trailer weight and deceleration rate of the tow vehicle. Currently, surge brakes are not considered by FMCSA to comply with the FMCSRs specifying that all brakes with which a motor vehicle is equipped must at all times be capable of operating, and that a single application valve must, when applied, operate all the service brakes on the motor vehicle or combination of motor vehicles. The intent of this rulemaking is to adopt performance-based brake system requirements to allow the use of surge brakes on certain combinations of commercial motor vehicles based upon engineering test data submitted by the Surge Brake Coalition.

The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 159: Global Positioning System.

The Coast Guard and the Maritime Administration (MARAD) announce that they have received an application for the licensing of a liquefied natural gas (LNG) deepwater port, and that the application appears to contain the required information. This notice summarizes the applicant's plans and the procedures that will be followed in considering the application.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Dassault Model Falcon 2000 airplanes. This proposed AD would require an inspection for the presence of fail-safe pins, nuts, and washers on each engine, and replacement of the fail-safe fastener assembly with a new assembly if necessary. This proposed AD results from a report of a missing pin of a fail-safe fastener. We are proposing this AD to prevent reduced structural integrity of an engine mount due to a missing pin of a fail-safe fastener, and possible separation of an engine from the airplane during flight.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing transport category airplanes. This proposed AD would require inspecting to determine if certain galleys and closets are installed, and replacing the spiral wire wrapping of the electrical cables of the galleys and closets with new spiral wire wrapping if necessary. This proposed AD results from testing and reports from the manufacturer indicating unacceptable flammability properties of wire wrapping installed in certain galleys and closets. We are proposing this AD to prevent fire propagation or smoke in the cabin area due to electrical arcing or sparking and ignition of the spiral wire wrapping.

The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 747 airplanes. This proposed AD would require the following actions for the drive mechanism of the horizontal stabilizer: Repetitive detailed inspections for discrepancies and loose ball bearings; repetitive lubrication of the ballnut and ballscrew; repetitive measurements of the freeplay between the ballnut and the ballscrew; and corrective action if necessary. This proposed AD is prompted by a report of extensive corrosion of a ballscrew in the drive mechanism of the horizontal stabilizer on a similar airplane model. We are proposing this AD to prevent an undetected failure of the primary load path for the ballscrew in the horizontal stabilizer and subsequent wear and failure of the secondary load path, which could lead to loss of control of the horizontal stabilizer and consequent loss of control of the airplane.

FMCSA adopts as final its interim regulations at 49 CFR part 303 governing civil rights matters, consistent with the savings provision of section 106(b) of the Motor Carrier Safety Improvement Act of 1999. As with the interim rule, this final rule clarifies and modifies the applicability of certain Federal Highway Administration (FHWA) and Departmental umbrella Title VI provisions of the Civil Rights Act of 1964, and related nondiscrimination statutes, as they apply to FMCSA Federal financial assistance recipients. Part 303 was created to provide FMCSA with initial guidelines and procedures, as well as future FMCSA Title VI implementing regulations and any future guidelines on Title VI compliance. FMCSA removed itself from the FHWA Title VI regulations in 23 CFR part 200 to avoid confusion, while not altering the substantive Title VI obligations of FMCSA and its grantees. FMCSA remains subject to the Departmental umbrella Title VI regulations in 49 CFR part 21 and will develop as needed further guidelines and procedures to assure effective and consistent implementation for financially assisted recipients. We have not made any changes to the interim rules in part 303, and we adopt the interim regulations as final without change.