Wednesday, October 20, 2010
- 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.
- 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.
- 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.