Federal Aviation Administration 2006 – Federal Register Recent Federal Regulation Documents

The FAA proposes to revise an earlier proposed airworthiness directive (AD) that applies to all Mitsubishi Heavy Industries MU-2B series airplanes. The earlier NPRM would have required 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; replace any deformed or irregular parts; and install new or reusable parts and torque to the correct value. The earlier NPRM resulted 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. This proposed AD would retain the actions from the earlier NPRM, add airplanes to the applicability, revise the serial numbers of the affected airplanes, and update the manufacturer's contact information. This proposed AD results from the manufacturer revising the service information to include two additional airplane models. Since these actions impose an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these additional actions.

This action establishes Class E airspace at Galbraith Lake, AK to provide adequate controlled airspace to contain aircraft executing two amended Special Standard Instrument Approach Procedures (SIAPs). This rule results in new Class E airspace established upward from 700 feet (ft.) above the surface at Galbraith Lake, AK.

This action establishes Class E airspace at Kuparuk, AK to provide adequate controlled airspace to contain aircraft executing eight Special Standard Instrument Approach Procedures (SIAPs). This rule results in new Class E airspace established upward from 700 feet (ft.) above the surface at Ugnu-Kuparuk Airport, AK.

This action corrects an error in the airspace description contained in a Final Rule that was published in the Federal Register on Wednesday, April 5, 2006 (71 FR 16997). Airspace Docket No. 05-AAL-41.

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 January 18, 2006, volume 71, 11, page 2982. Standards have been established for the operation of agricultural aircraft and for the dispensing of chemicals, pesticides, and toxic substances. Information collected shows applicant compliance and eligibility for certification by FAA.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300, and A340-200 and -300 series airplanes. This proposed AD would require modifying certain rotary actuator assemblies for the leading edge slat. This proposed AD results from a leak found at the seal of the torque limiter output shaft of the Type A rotary actuator of leading edge slat No. 1. We are proposing this AD to prevent a decrease in the torque limiter function, which could result in degradation and damage to the attachment bolts of the leading edge slat, loss of the slat, and consequent reduced control of the airplane.

We propose to supersede Airworthiness Directive (AD) 98-12-01, which applies to certain Pilatus Aircraft Ltd (Pilatus) Models PC-6, PC-6/A, PC-6/B, and PC-6/C series airplanes equipped with turbo-prop engines. AD 98-12-01 currently requires you to modify the fuel system to improve the venting between the collector tank, the main wing tanks, and the engine. Since we issued AD 98-12-01, the FAA determined the action should also apply to all the models of the PC-6 airplanes listed in the type certification data sheet of Type Certificate (TC) No. 7A15 that are produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent of the applicability of AD 98-12- 01 was to apply to affected serial numbers of the airplane models listed in TC No. 7A15. Consequently, this proposed AD would retain all the actions of AD 98-12-01, would add those Fairchild Republic Company airplanes to the applicability of this proposed AD, and would list out the individual specific airplane models. We are proposing this AD to prevent engine fuel starvation during maximum climb and descent caused by poor fuel tank venting with low fuel levels, which could result in a loss of engine power during critical phases of flight.

The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. That AD currently requires repetitive detailed and ultrasonic inspections of the thrust links of the rear engine mounts for any crack or fracture and corrective actions if necessary. This new AD requires repetitive replacement of the thrust links with new or overhauled thrust links, which ends the repetitive detailed and ultrasonic inspections. This AD results from the finding of fractured and cracked forward lugs of the rear engine mount thrust link on the number one strut on two airplanes. We are issuing this AD to prevent cracked or fractured thrust links that could lead to the loss of the load path for the rear engine mount bulkhead and damage to other primary engine mount structure, which could result in the in-flight separation of the engine from the airplane and consequent loss of control of the airplane.

This action would require holders of design approvals to make available to operators damage tolerance data for repairs and alterations to fatigue critical airplane structure. This proposal is needed to support operator compliance with the requirement to include damage tolerance inspections and procedures in their maintenance programs, and to enable operators to take into account the possible adverse effects of repairs and alterations on fatigue critical structure. The intended effect of this proposal is to ensure the continued airworthiness of fatigue critical airplane structure by requiring design approval holders to support operator compliance with specified damage tolerance requirements.

In order to communicate safety information to the commercial aviation community more effectively, the FAA Flight Standards Service has issued FAA Order 8000.87, Safety Alert for Operators (SAFO). The public and operators can access this order at this Web site: https:// www.faa.gov/othervisit/aviationindustry/airlineoperators/ airlinesafety/safo.

This action proposes to establish Control 1485L and revise Control 1485H offshore airspace in the vicinity of Barrow, AK. These proposed actions would establish controlled airspace outside of 12 nautical miles (NM) of the U.S. shoreline upward from 1,200 feet mean sea level (MSL) along the North Slope of Alaska. Additionally, this proposal would revise the altitudes of Control 1485H from FL 230/FL 450 to FL 180/FL 600. The FAA is proposing these actions to provide additional controlled airspace for aircraft executing instrument flight rules (IFR) operations at the airfields along the North Slope of Alaska in anticipation of establishing Terminal Arrival Areas associated with Area Navigation (RNAV) Standard Instrument Arrival Procedures (SIAPs).

The FAA proposes to adopt a new airworthiness directive (AD). This proposed AD is for Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engines that were reassembled with certain previously used high pressure compressor (HPC) exit brush seal assembly parts and certain new or refurbished HPC exit diffuser air seal inner lands. This proposed AD would require replacing the HPC exit inner and outer brush seal packs with new brush seal packs, or replacing the HPC exit brush seal assembly with a new HPC exit brush seal assembly. This proposed AD results from a report of oil leaking into the high pressure turbine (HPT) interstage cavity and igniting, leading to an uncontained failure of the 2nd stage turbine air seal and engine in-flight shutdown. We are proposing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers.

The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CT64-820-4 turboprop engines with certain part number (P/N) rotating parts. The parts are in the compressor rotor assembly, gas generator turbine rotor assembly, and power turbine rotor assembly that are subject to low-cycle fatigue. This AD requires removing from service these affected rotating parts at reduced compliance times. This AD results from the manufacturer's discovery of cracks in some rotating parts. We are issuing this AD to prevent cracks in the rotating parts that could cause compressor and turbine wheel fracture and uncontained engine failure. An uncontained engine failure could cause possible damage to the airplane.

The FAA is adopting a new airworthiness directive (AD) for all Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes. This AD requires you to repetitively inspect (using the eddy current method) the two outboard fastener holes in both of the wing main spar lower caps at the center splice joint for cracks and repair or replace any cracked spar cap. This AD results from in-service fatigue cracking of the wing main spar lower cap at the center splice joint outboard fastener hole at hours time-in-service below the safe life limit established for these airplanes in AD 2002-11-05. We are issuing this AD to detect and correct cracks in the wing main spar lower cap at the center splice joint, which could result in failure of the spar cap and lead to wing separation and loss of control of the airplane.

The Federal Aviation Administration will begin assigning permanent Dealer's Aircraft Registration Certificate numbers to manufacturers and dealers who currently hold an unexpired dealer's certificate and any new issuances.

This action amends Title 14 Code of Federal Regulations, part 71 (14 CFR 71) by revising Class E airspace areas at Mason City Municipal Airport, IA. A review of the Class E airspace surface area and the Class E airspace area extending upward from 700 feet above ground level (AGL) revealed neither area complies with criteria in FAA Orders. These airspace areas and their legal descriptions are modified to conform to the criteria in FAA Orders.

This action is intended to prevent widespread fatigue damage by proposing to require that design approval holders establish operational limits on transport category airplanes. Design approval holders would also be required to determine if maintenance actions are needed to prevent widespread fatigue damage before an airplane reaches its operational limit. Operators of any affected airplane would be required to incorporate the operational limit and any necessary service information into their maintenance programs. Operation of an affected airplane beyond the operational limit would be prohibited, unless an operator has incorporated an extended operational limit and any necessary service information into its maintenance program.

The FAA proposes to revise an existing airworthiness directive (AD) for certain Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD currently requires initial and repetitive position checks of the gas generator 2nd stage turbine blades on all Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD also currently requires initial and repetitive replacements of 2nd stage turbines on 1B, 1D, and 1D1 engines only. This proposed AD revision would require the same actions, but would relax the compliance times for initially replacing 2nd stage turbines in Arriel 1B, 1D, and 1D1 turboshaft engines. This proposed AD revision results from a request by Turbomeca to clarify the compliance times for 2nd stage turbine initial replacement on Arriel 1D, 1D1, and 1B turboshaft engines. We are proposing this AD revision to clarify and relax the AD compliance times for 2nd stage turbine initial replacement on Arriel 1B, 1D, and 1D1 turboshaft engines. We are also proposing this AD revision to prevent inflight engine shutdown and subsequent forced autorotation landing or accident.

This action removes the Class E5 Airspace at Paducah Farrington Airpark, KY, as there is no longer a Standard Instrument Approach Procedure (SIAP) for Paducah Farrington Airpark requiring Class E5 airspace.

This document publishes in the Federal Register an amendment adopting emergency airworthiness directive (EAD) 2006-06-51 that we sent previously to all known U.S. owners and operators of GEAE CT7-8A turboshaft engines installed on Sikorsky S92 helicopters. This AD requires initial and repetitive inspections of the electrical chip detectors for the No. 3 bearing. This AD results from two failures of the No. 3 bearing in GEAE CT7-8A engines. We are issuing this AD to prevent failures of the No. 3 bearings and possible dual in-flight shutdowns of the engines.

This amendment amends Standard Instrument Approach Procedures (SIAPs) for operations at certain airports. These regulatory actions are needed because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, addition of new obstacles, or changes in air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.

This amendment adopts a new airworthiness directive (AD) for the specified Brantly International, Inc. (Brantly) model helicopters. This action requires certain inspections and measurements of the upper tail rotor vertical gearbox (gearbox), vertical shaft (shaft) and shaft housing (housing) and their associated parts; and of the intermediate gear box bushing (bushing). This amendment is prompted by an accident and an incident report of fatigue cracking of a shaft. The actions specified in this AD are intended to prevent fatigue cracking of a shaft, failure of a shaft, and subsequent loss of control of the helicopter.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 airplanes. This proposed AD would require a detailed inspection for cracks and marks on the carbon blades of the ram air turbine (RAT), and replacement of the RAT with a new or serviceable RAT if necessary. This proposed AD results from a report of three chord-wise cracks on the aft side of one carbon blade of a certain RAT. We are proposing this AD to detect and correct cracks and/or marks on the RAT carbon blades, which could result in reduced structural integrity of the carbon blade, and consequent loss of the RAT as a source of hydraulic and electrical power in an emergency.

The FAA proposes to adopt a new airworthiness directive (AD) for certain transport category airplanes, identified above. This proposed AD would require installing a bonding jumper from the boost pump volute to the fuel tank structure, and related investigative/ corrective actions. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing 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.