Federal Aviation Administration 2006 – Federal Register Recent Federal Regulation Documents

This document announces the Office of Management and Budget's (OMB) approval of the information collection requirement in the final rule published on August 29, 2006 (FR 71 51382). The sections of the final rule pending approval of this information collection will become effective on the date included in the published final rule; October 29, 2006.

Pursuant to FAA's rulemaking provisions governing the application, processing, and disposition of petitions for exemption part 11 of Title 14, Code of Federal Regulations (14 CFR), this notice contains a summary of certain petitions seeking relief from specified requirements of 14 CFR. The purpose of this notice is to improve the public's awareness of, and participation in, this aspect of FAA's regulatory activities. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of any petition or its final disposition.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -200CB series airplanes. This AD requires doing initial and repetitive detailed or high frequency eddy current inspections for cracks around the rivets at the upper fastener row of the skin lap splice of the fuselage, and repairing any crack found. This AD results from a report indicating that certain rivets were incorrectly installed in some areas of the skin lap splices during production because they were drilled with a countersink that was too deep. We are issuing this AD to detect and correct premature fatigue cracking at certain skin lap splice locations of the fuselage, and consequent rapid decompression of the airplane.

The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 777 airplanes. This proposed AD would require repetitive measurements of the freeplay of the right and left elevators, rudder, and rudder tab, and related investigative and corrective actions if necessary. This proposed AD would also require repetitive lubrications of the elevator, rudder, and rudder tab components. This proposed AD results from reports of freeplay-induced vibration of unbalanced control surfaces. Excessive freeplay of control surfaces can cause unacceptable airframe vibration during flight. The potential for vibration of the control surface should be avoided because the point of transition from vibration to divergent flutter is unknown. We are proposing this AD to prevent flutter, which can cause damage to the control surface structure and consequent loss of control of the airplane.

The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus Model A310 airplanes. This proposed AD would require doing repetitive inspections for any missing, damaged, or incorrectly installed wiper rings in the splined couplings of the flap transmissions shafts; inspections for any missing, damaged, or incorrectly installed rubber gaiters and straps on the sliding bearing/ plunging joints of the flap transmission; and corrective action if necessary. This proposed AD results from reviews in which the manufacturer determined that the splined couplings and sliding bearings of the flap transmission system could be affected by corrosion and wear. We are proposing this AD to detect and correct damaged, missing, or incorrectly installed components of the flap transmission system, which could result in reduced functional integrity of the flap transmission system and consequent reduced control of the airplane.

The FAA is revising an earlier proposed airworthiness directive (AD) for certain Boeing Model 777-200 and 777-300 series airplanes. The original NPRM would have required repetitive inspections for discrepancies of the splined components that support the inboard end of the inboard trailing edge flap; related investigative, corrective, and other specified actions if necessary; a one-time modification of the inboard support of the inboard trailing edge flap by installing a new isolation strap and attachment hardware; and repetitive replacement of the torque tube assembly. The original NPRM resulted from reports of corrosion on the torque tube and closeout rib fittings that support the inboard end of the inboard trailing edge flap, as well as a structural reassessment of the torque tube joint that revealed the potential for premature fatigue cracking of the torque tube that would not be detected using reasonable inspection methods. This action revises the original NPRM by providing the terminating action for the repetitive inspections of modifying the inboard main flap. This action also revises the original NPRM by specifying prior or concurrent accomplishment, for certain Boeing Model 777-200 series airplanes, of one-time inspections of the flap seal panels for cracking and minimum clearances, and of the torque tubes for damage; and related investigative and corrective actions if necessary. We are proposing this supplemental NPRM to detect and correct corrosion or cracking of the torque tube and closeout rib fittings that support the inboard end of the inboard trailing edge flap. Cracking in these components could lead to a fracture, which could result in loss of the inboard trailing edge flap and consequent reduced controllability of the airplane.

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.

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

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.

The FAA is adopting a new airworthiness directive (AD) for certain Lycoming Engines (L)O-360, (L)IO-360, AEIO-360, O-540, IO-540, AEIO-540, (L)TIO-540, IO-580, and IO-720 series reciprocating engines. This AD requires replacing certain crankshafts. This AD results from reports of 23 confirmed failures of similar crankshafts in Lycoming Engines 360 and 540 series reciprocating engines. We are issuing this AD to prevent failure of the crankshaft, which will result in total engine power loss, in-flight engine failure, and possible loss of the aircraft.

We are adopting a new airworthiness directive (AD) for certain Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes. This AD requires you to repetitively inspect the attach angles on the firewall mounted hopper rinse tank shelf for damage and/or cracks and replace damaged and/or cracked attach angles with steel attach angles. Replacing the attach angles with steel attach angles terminates the repetitive inspection requirement. Reports of an uncommanded change in the engine power setting caused by separation of the hopper rinse tank shelf from the firewall prompted this AD. We are issuing this AD to detect and correct damage and/or cracks in the attach angles on the firewall mounted hopper rinse tank shelf, which could result in failure of the attach angles. This failure could lead to shelf movement under maneuver load and shifting of the engine power cables, which could result in an uncommanded engine power setting change.

This action establishes Class E airspace at Butler, GA. Area Navigation (RNAV) Global Positioning System (GPS) and Nondirectional Radio Beacon (NDB) Standard Instrument Approach Procedures (SIAP) Runway (RWY) 18 and RWY 36 have been developed for Butler Municipal Airport. As a result, controlled airspace extending upward from 700 feet Above Ground Level (AGL) is needed to contain the SIAPs and for Instrument Flight Rules (IFR) operations at Butler Municipal Airport. The operating status of the airport will change from Visual Flight Rules (VFR) to include IFR operations concurrent with the publication of the SIAP.

This action modifies Class E airspace at Pierre, SD. Standard Instrument Approach Procedures have been developed for Pierre Regional Airport, Pierre, SD. Controlled airspace extending upward from 700 feet or more above the surface of the earth is needed to contain aircraft executing these approaches.This action increases the area of the existing controlled airspace for Pierre, SD.

The FAA proposes to adopt a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ airplanes. This proposed AD would require calculating the current life of each lift spoiler jack, and eventually replacing each lift spoiler jack. This proposed AD results from a review of all system components as part of the life-extension program for the affected airplanes that indicated the fatigue life limit of certain lift spoiler jacks cannot be extended from the current life limit. We are proposing this AD to prevent failure of the lift spoiler jack, and consequent increased drag and uncommanded roll inputs, which could reduce the flightcrew's ability to control the airplane.

The FAA is proposing a Special Federal Aviation Regulation (SFAR) applicable to the Mitsubishi MU-2B series airplane that would create new pilot training, experience, and operating requirements. Following an increased accident and incident rate in the MU-2B series airplane, the FAA conducted a safety evaluation of the MU-2B series airplane and found that changes in the training and operating requirements for that airplane are needed. These proposed regulations would mandate additional operating requirements and improve pilot training for the MU-2B series airplane.

The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) models 250-C30, 250-40, and 250-C47 series turboshaft engines with a third-stage turbine wheel, part number (P/N) 6898663 or P/N 23065843 installed, or a fourth-stage turbine wheel, P/N 6892764 or P/N 23066744, installed. This AD adds an additional life limit for third- and fourth-stage turbine wheels. This AD results from analysis by RRC of failures of third-stage turbine wheels. We are issuing this AD to prevent loss of power, possible engine shutdown, or uncontained engine failure.

The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310 airplanes. This AD requires revising the Limitations section of the airplane flight manual by incorporating restrictions for high altitude operations. This AD results from several incidents of pitch oscillations with high vertical loads that occurred during turbulence at high altitudes. We are issuing this AD to prevent pitch oscillations during turbulence, which could result in reduced controllability of the airplane.

The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-102, -103, and -106 airplanes, and Model DHC-8-200 and DHC-8-300 series airplanes. This AD requires performing a one-time general visual inspection for non-conforming chain links of chain assemblies of the elevator trim system and gust lock system, and corrective actions if necessary. This AD also requires temporary revisions to the airplane flight manuals of the affected airplanes, which describe procedures for elevator trim checks. This AD results from reports of several failures of the elevator trim chain, due to hydrogen embrittlement. We are issuing this AD to prevent breakage of the elevator trim chain, which would prevent the actual position of the elevator trim tab from being annunciated to the flightcrew. Attempting to adjust the trim tab from the full nose up or full nose down position with a broken trim chain could result in misleading information relative to takeoff trim settings and consequent loss of control on takeoff.

Pursuant to FAA's rulemaking provisions governing the application, processing, and disposition of petitions for exemption part 11 of Title 14, Code of Federal Regulations (14 CFR), this notice contains a summary of certain petitions seeking relief from specified requirements of 14 CFR. The purpose of this notice is to improve the public's awareness of, and participation in, this aspect of FAA's regulatory activities. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of any petition or its final disposition.

The Federal Aviation Administration (FAA) announces it has terminated its review of the noise compatibility program, at the request of the city of Fresno, owner and operator of Fresno Yosemite International 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.

We propose to adopt a new airworthiness directive (AD) for certain EADS SOCATA Model TBM 700 airplanes. This proposed AD would require you to inspect the pilot door locking stop-fittings for correct length and, if any incorrect length pilot door locking stop-fittings are found, replace them. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. We are proposing this AD to detect and replace incorrect length pilot door locking stop-fittings. This condition, if not corrected, could result in depressurization of the airplane.

Pursuant to FAA's rulemaking provisions governing the application, processing, and disposition of petitions for exemption part 11 of Title 14, Code of Federal Regulations (14 CFR), this notice contains a summary of certain petitions seeking relief from specified requirements of 14 CFR. The purpose of this notice is to improve the public's awareness of, and participation in, this aspect of FAA's regulatory activities. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of any petition or its final disposition.

This document makes two minor corrections to a final rule that amends commercial space transportation regulations governing the launch of expendable launch vehicles. 71 FR 50507 (Aug. 25, 2006). This action is necessary to correct a paragraph designation and add a notation of a reserved appendix. This correction does not make substantive changes to the final rule.

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Bombardier Model DHC-8-100, - 200, and -300 series airplanes. The existing AD currently requires modification of the flight compartment door; repetitive inspections for wear of the flight compartment door hinges following modification; and repair or replacement of the hinges with new hinges if necessary. This proposed AD would require using revised procedures for modifying and inspecting the flight compartment door and would reduce the applicability of the existing AD. This proposed AD results from a determination that certain cockpit doors are no longer subject to the existing requirements. We are proposing this AD to prevent failure of the alternate release mechanism of the flight compartment door, which could delay or impede the evacuation of the flightcrew during an emergency. This failure also could result in the flightcrew not being able to assist passengers in the event of an emergency.