Federal Aviation Administration Federal Register Final Rules, Proposed Rules and Notices, Wednesday, October 20, 2010

Wednesday, October 20, 2010

Rules

  • Airworthiness Directives; The Boeing Company Model 767–200, –300, and –300F Series Airplanes. 14 CFR Part 39 [Docket No. FAA–2010–1036; Directorate Identifier 2009–NM– 247–AD; Amendment 39–16480; AD 2010–22–01] RIN 2120–AA64.  SUMMARY: We are superseding an existing  airworthiness directive (AD) for the products listed above. That AD currently  requires repetitive inspections for fatigue cracking and corrosion of the upper link  fuse pin of the nacelle struts, and related investigative and corrective actions if  necessary. The existing AD also provides terminating action for the repetitive  inspections. This AD revises certain criteria for the terminating action. This AD  was prompted by two reports of cracked upper link fuse pins. We are issuing this  AD to prevent fatigue cracking or corrosion of the upper link fuse pin, which could  result in failure of the fuse pin and consequent reduced structural integrity of the nacelle strut and possible separation of the strut and engine from the airplane during flight. DATES: This AD is effective November 4, 2010. The Director of the  Federal Register approved the incorporation by reference of a certain  publication listed in the AD as of November 4, 2010. The Director of the Federal  Register approved the incorporation by reference of a certain other publication  listed in this AD as of November 5, 2009 (74 FR 50692, October 1, 2009). We  must receive comments on this AD by December 6, 2010.
  • Airworthiness Directives; Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) Airplanes. 14 CFR Part 39 [Docket No. FAA–2010–1037; Directorate Identifier 2010–NM– 202–AD; Amendment 39–16481; AD 2010–22–02] RIN 2120–AA64. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from  mandatory continuing airworthiness information (MCAI) originated by an  aviation authority of another country to identify and correct an unsafe condition  on an aviation product. The MCAI describes the unsafe condition as: Seven cases  of on-ground hydraulic accumulator screw cap/end cap failure have been  experienced on CL–600–2B19 aeroplanes, resulting in the loss of the associated  hydraulic system and high-energy impact damage to adjacent systems and structure. * * * * * * * * A detailed analysis of the calculated line of trajectory of a  failed screw cap/end cap for each of the accumulators has been conducted,  resulting in the identification of several areas where systems and/or structural components could potentially be damaged. Although all of the failures to date  have occurred on the ground, an in-flight failure affecting such components could  potentially have an adverse effect on the controllability of the aeroplane. * * * * * This AD requires actions that are intended to address the unsafe condition  described in the MCAI. DATES: This AD becomes effective November 4, 2010. The Director of the Federal Register approved the incorporation by reference of  certain publications listed in the AD as of November 4, 2010. We must receive  comments on this AD by December 6, 2010.

Proposed Rules

  • Airworthiness Directives; General Electric Company  (GE) CF6–45 Series and CF6–50 Series Turbofan Engines. 14 CFR Part 39 [Docket No. FAA–2010–0998; Directorate Identifier 2010–NE– 29–AD] RIN 2120–AA64. SUMMARY: The  FAA proposes to adopt a new airworthiness directive (AD) for GE CF6–45 and  CF6–50 series turbofan engines. This proposed AD would require performing a  fluorescent penetrant inspection (FPI) of the stage 3 low-pressure turbine (LPT)  rotor at every shop visit at which the LPT module is separated from the engine. This proposed AD results from seven reports of uncontained failures of LPT stage   disks and eight reports of cracked LPT stage 3 disks found during shop  visit inspections. We are proposing this AD to prevent LPT rotor separation, which could result in an uncontained engine failure and damage to the airplane. DATES: We must receive any comments on this proposed AD by December 20, 2010.

Notices

  • Petition for Exemption; Summary of Petition Received. [Summary Notice No. PE–2010–45]. SUMMARY: This notice contains a summary of a petition seeking  relief from specified requirements of 14 CFR Part 43. 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 the  petition or its final disposition.  DATES: Comments on this petition must identify the petition docket number involved and must be received on or before  November 9, 2010.
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