Federal Aviation Administration 2006 – Federal Register Recent Federal Regulation Documents

The FAA proposes to supersede Airworthiness Directive (AD) 2004-11-04, which applies to all CTRM Aviation Sdn. Bhd. (Formerly Eagle Aircraft (Malaysia) Sdn. Bhd.) Model Eagle 150B airplanes. AD 2004-11-04 currently requires you to inspect certain canard inboard flap hinge support brackets (initially before further flight and repetitively before the first flight of each day) and perform any necessary follow-up action. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Malaysia to require the installation of improved design inboard flap hinge brackets as terminating action for the repetitive inspections. Consequently, this proposed AD would initially retain the requirement that you inspect certain canard inboard flap hinge support brackets (initially before further flight and repetitively before the first flight of each day) and then require that you replace the parts with new design inboard flap hinge brackets as terminating action for the repetitive inspections or if cracks are found. We are issuing this proposed AD to detect and correct cracks in the canard inboard flap hinge support brackets, which could result in loss of retention of controls and consequently, loss of airplane control.

The FAA proposes to supersede an existing airworthiness directive (AD) for Rolls Royce plc (RR) RB211-524 series turbofan engines with certain part number (P/N) intermediate pressure compressor (IPC) stage 5 disks installed. That AD currently requires new reduced IPC stage 5 disk cyclic limits. This proposed AD would require the same reduced IPC stage 5 disk cyclic limits, the requirement to remove from service affected disks that already exceed the new reduced cyclic limit, and to remove from service other affected disks before exceeding their cyclic limits using a drawdown schedule. This proposed AD also would exempt disks reworked to RR Service Bulletin (SB) RB.211-72-E182, Revision 1, dated July 30, 2004, and would allow an on-wing eddy current inspection (ECI) on RB211-524G and RB211-524H series engines. This proposed AD results from the manufacturer issuing a revised Alert Service Bulletin (ASB) to remove certain disks from applicability, and to allow an on-wing ECI on RB211-524G and RB211-524H series engines. We are proposing this AD to prevent failure of the IPC stage 5 disk, which could result in uncontained engine failure and possible damage to the airplane.

This action amends VOR Federal Airway V-431, Alaska. Specifically, the FAA is re-designating V-431 as V-593 because the V- 431 designation is a duplicate number in the National Airspace System (NAS) and is causing problems with the Flight Data processors during route validation at the Anchorage Air Route Traffic Control Center.

On June 14, 2006, we published a document concerning proposed special conditions for Thielert Aircraft Engines GmbH, Piper PA 28-161 Cadet, Warrior II and Warrior III Series Airplanes with a Diesel Cycle Engine Using Turbine (Jet) Fuel. There was an error in the preamble of the proposed special conditions in the reference to the notice number. The notice number was used in a previous proposed special condition. This document contains a correction to the notice number; the docket number remains unchanged.

This action extends the comment period stated in the Notice of Availability of proposed Advisory Circular (AC) 120-YY, ``Widespread Fatigue Damage on Metallic Structure,'' that was published on May 22, 2006. In that document, the FAA announced the availability of and request for comments on proposed revisions to an AC which provides guidance to design approval holders for certain transport category airplanes related to repairs and alterations to preclude widespread fatigue damage.

This action extends the comment period for an NPRM that was published on April 21, 2006. In that document, the FAA proposed requirements for holders of design approvals to make available to operators damage tolerance data for repairs and alterations to fatigue critical structure. This extension is a result of requests from the Air Transport Association of America, Inc. (ATA), Airbus, Boeing Commercial Airplanes, Cargo Airline Association (CAA), and National Air Carrier Association, Inc. (NACA) to extend the comment period to the proposal.

On October 6, 2005, the FAA published the ``Enhanced Airworthiness Program for Airplane Systems/Fuel Tank Safety (EAPAS/ FTS)'' proposed rule. This proposal includes a discussion about our intent to coordinate the Instructions for Continued Airworthiness (ICA) for fuel tank system and electrical wiring interconnection systems (EWIS) to avoid redundancies in those ICA. It also discusses our intent to align the compliance dates for operators to include those ICA in their maintenance programs. The purpose of this document is to advise industry that while we still intend to avoid redundancies in the fuel tank system and EWIS ICA, it is no longer practical to align the compliance dates to incorporate those ICA into operator maintenance programs. As a result, the December 16, 2008 compliance date in the fuel tank safety operational rules remains firm, and industry should proceed with the necessary plans to meet this date.

Under the provisions of Title 49, U.S.C. Section 47153(c), notice is being given that the FAA is considering a request from the City of Concord to waive the requirement that approximately 7.30 acres of airport property, located at the Concord Regional Airport, be used for aeronautical purposes.

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Model SAAB-Fairchild SF340A and SAAB 340B airplanes. The existing AD currently requires repetitive inspections for wear of the brushes and leads and for loose rivets of the direct current (DC) starter generator, and related investigative/ corrective actions if necessary. This proposed AD would require installing new improved generator control units (GCUs). Installing the GCUs would end the repetitive inspection requirements of the existing AD. This proposed AD results from reports of premature failures of the DC starter generator prior to scheduled overhaul. We are proposing this AD to prevent failure of the starter generator, which could cause a low voltage situation in flight and result in increased pilot workload and reduced redundancy of the electrical powered systems.

The FAA's Aircraft Certification Service publishes proposed non-regulatory documents that are available for public comment on the Internet at https://www.faa.gov/aircraft/draftdocs/.

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-200 and A330-300 series airplanes; and Airbus Model A340-200 and A340-300 series airplanes. This AD requires lubrication of the upper and lower shortening mechanism (SM) link of the main landing gear, and consequent detection of resistance or blockage of the greaseway. Depending upon the resistance finding and upon whether or not the airplane has a certain modification, this AD also requires various other actions including unblocking the greaseway; accomplishing all necessary repairs; performing various inspections; and accomplishing the eventual replacement of the SM8 pin, if necessary. This action is necessary to prevent failure of the landing gear lengthening system, which could result in reduced controllability of the airplane on the ground during landing. This action is intended to address the identified unsafe condition.

The FAA is adopting a new airworthiness directive (AD) for certain transport category airplanes, identified above. This AD requires installing a bonding jumper from the boost pump volute to the fuel tank structure, and related investigative/corrective actions. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent point-contact arcing or filament heating in the fuel tank, which, in the event of a short or ground fault inside the fuel tank, could result in a fuel tank explosion and consequent loss of the airplane.

The FAA proposes to adopt a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This proposed AD would require repetitive inspections of the wing top skin under the rib 0 joint strap, and related investigative and corrective actions if necessary. This proposed AD results from a report of a significant crack in the wing top skin under the rib 0 joint strap. We are proposing this AD to detect and correct corrosion and cracking in that area, which could result in reduced structural integrity of the wing.

This action revokes the Bishop Nondirectional Radio Beacon (NDB) as an Alaskan low altitude reporting point. The FAA has determined that this reporting point should be removed from the National Airspace System (NAS), since the Bishop NDB was de- commissioned and is no longer in service.

The Federal Aviation Administration (FAA) announces that it is reviewing a proposed noise compatibility program that was submitted for McClellan-Palomar Airport under the provisions of 49 U.S.C. 47501 et seq. (the Aviation Safety and Noise Abatement Act, hereinafter referred to as ``the Act'') and 14 CFR Part 150 by the County of San Diego. This program was submitted subsequent to a determination by FAA that associated noise exposure maps submitted under 14 CFR Part 150 for McClellan-Palomar Airport were in compliance with applicable requirements, effective April 26, 2005, which was published in the Federal Register, Volume 70, No. 89, page 24671, on May 10, 2005. The proposed noise compatibility program will be approved or disapproved on or before December 17, 2006.

Pursuant to Section 176(c) of the Clean Air Act Amendments of 1990, the FAA announces the availability of the Final General Conformity Determination for Operations of Southwest Airlines Co. (Southwest) at Denver International Airport (DEN). FAA has determined that emissions from Southwest's operations at DEN conform to the Colorado State Implementation Plan (SIP). In accordance with the requirements of 40 CFR 93.156 (b), the Draft Conformity Determination, Proposed Operations of Southwest Airlines Co. at Denver International Airport, Denver, CO was made available for public review beginning April 21, 2006. Notice of the draft determination was published in the Rocky Mountain News, Denver, Colorado on April 21, 2006, and copies of the draft determination were made available at DEN. The Notice of Draft General Conformity Determination was published in the Federal 1Register on April 27, 2006 (71 FR 24903). No comments were submitted during the public comment period, which ended on May 30, 2006. Consequently, the Final General Conformity Determination consists of the Draft General Conformity Determination, with the following typographical corrections. The corrections are needed to clarify terms describing aircraft operations and to correct the reference to the maximum foreseeable aircraft activity used to predict aircraft emissions, as documented in Table 1. 1. Page 24903, last sentence on this page under SUPPLEMENTARY INFORMATION shall be revised to read: ``At that time Southwest indicated an interest in increasing service to as many as 50 or 60 daily landing/take-off cycles (LTOs) at DEN, but agreed to maintain * * *'' 2. Page 24904, second sentence of the last paragraph under SUPPLEMENTARY INFORMATION shall be revised to read: ``This General Conformity Determination addresses FAA's proposed Federal action to amend Southwest's operation specifications (OpSpecs) to accommodate future aircraft activity as high as 60 daily LTOs at DEN * * *'' 3. Page 24904, fourth sentence of the 1st paragraph under Aircraft and Supporting Equipment Emissions shall be revised to read: ``Under the Proposed Action scenario, aircraft emissions were quantified based on this maximum foreseeable level and conservatively assumed to occur every day of the year for a total of 21,900 LTOs per year.''

This document proposes adopting a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. This proposal would require replacing a certain hydraulic drive belt (drive belt). Also proposed is reducing the lubrication time interval for a certain hydraulic pump drive shaft (drive shaft). This proposal is prompted by in-flight failures of the drive belt and the drive shaft. The actions specified by this proposed AD are intended to prevent in-flight failure of the drive belt or drive shaft, loss of hydraulic power to the flight control system, and subsequent loss of control of the helicopter.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Fokker Model F27 Mark 050 and Model F.28 Mark 0070 and 0100 airplanes. This proposed AD would require repetitively removing the two existing escape rope assemblies in the flight compartment and installing new escape rope assemblies. This proposed AD results from reports of findings of small cracks in the polyester assembly block in which the cotton escape rope is stored. A test revealed that the escape ropes had deteriorated over time, and the load capability was considerably reduced. We are proposing this AD to ensure that flightcrew members safely reach the ground after exiting the flight compartment window during an emergency evacuation.

We are adopting a new airworthiness directive (AD) for all Mitsubishi Heavy Industries MU-2B series airplanes. This AD requires you to do the following: Remove and visually inspect the wing attach barrel nuts, bolts, and retainers for cracks, corrosion, and fractures; replace any cracked, corroded, or fractured parts; inspect reusable wing attach barrel nuts and bolts for deformation and irregularities in the threads; check the minimum breakaway torque of reused wing attach barrel nuts; replace any deformed or irregular parts; and install new or reusable parts and torque to the correct value. This AD results from a recent safety evaluation that used a data-driven approach to evaluate the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. We are issuing this AD to detect and correct cracks, corrosion, fractures, and incorrect torque values in the wing attach barrel nuts, which could result in failure of the wing barrel nuts and/or associated wing attachment hardware. This failure could lead to in-flight separation of the outer wing from the center wing section and result in loss of controlled flight.

The FAA withdraws a notice of proposed rulemaking (NPRM) that proposed a new airworthiness directive (AD) for certain EMBRAER Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. The proposed AD would have required modifying the routing of wire harness W407 near the fire extinguishing tube in the area of each engine, and installing new supports for related wiring. Since the proposed AD was issued, we have received new data indicating that the identified unsafe condition does not exist. Accordingly, the proposed AD is withdrawn.

The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 204: 406 MHz Emergency Locator Transmitters.

The FAA invites public comments about our intention to request the Office of Management and Budget (OMB) to approve a current information collection. The FAA Aviation Research and Development Grants Program establishes uniform policies and procedures for the award and administration of research grants to colleges, universities, not for profit organizations, and profit organizations for security research.

The FAA invites public comments about our intention to request the Office of Management and Budget (OMB) to approve a current information collection. This rule may require applicants to comply with the latest regulations in effect on the date of application for amended Type Certificates (TC) or a Supplemental TCs for aeronautical products.

The FAA is correcting an inadvertent error in an existing airworthiness directive (AD) that was published in the Federal Register on June 12, 2006 (71 FR 33606). The error resulted in an incorrect reference to the airplane manufacturer instead of the TSO holder. This AD applies to Goodrich evacuation systems approved under TSO-C69b and installed on certain Airbus Model A330-200 and -300 series airplanes, Model A340-200 and -300 series airplanes, and Model A340-541 and -642 airplanes. This AD requires inspecting to determine the part number of the pressure relief valves on the affected Goodrich evacuation systems, and corrective action if necessary.