Federal Aviation Administration (FAA), DOT.
The FAA is adopting a new airworthiness directive (AD) for IAE V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 turbofan engines. This AD requires a onetime fluorescent penetrant inspection of certain vortex reducers for cracks. This AD results from reports of fractured vortex reducers found at shop visits. We are issuing this AD to inspect for cracks in the vortex reducer. Cracks in the vortex reducer could result in an uncontained failure of the high-pressure (HP) compressor stage 3-8 drum and subsequent damage to the airplane.
This AD becomes effective April 22, 2010.
The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-0001.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin email@example.com; telephone (781) 238-7117; fax (781) 238-7199.End Further Info End Preamble Start Supplemental Information
The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to IAE V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 turbofan engines. We published the proposed AD in the Federal Register on April 30, 2009 (74 FR 19904), and a supplemental proposed AD on December 23, 2009 (74 FR 68192). That action proposed to require a onetime inspection of certain vortex reducers for cracks, and replacing the reducer and HP compressor stage 3-8 drum if the reducer is cracked.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.
We provided the public the opportunity to participate in developing this AD. We responded to the comments received on the NPRM, in the supplemental NPRM. We received no comments on the supplemental NPRM or on the determination of the cost to the public.
We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
We estimate that this AD will affect six IAE turbofan engines installed on airplanes of U.S. registry. We also estimate that it will take about one work-hour per engine to perform the actions, and that the average labor rate is $80 per work-hour. No parts are required. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $480.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a “significant regulatory action” under Executive Order 12866;
(2) Is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES.Start List of Subjects
List of Subjects in 14 CFR Part 39End List of Subjects
Adoption of the AmendmentStart Amendment Part
Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amendsEnd Amendment Part Start Part
PART 39—AIRWORTHINESS DIRECTIVESEnd Part Start Amendment Part
1. The authority citation for part 39 continues to read as follows:End Amendment Part
2. The FAA amends § 39.13 by adding the following new airworthiness directive:End Amendment Part
2010-06-18 International Aero Engines: Amendment 39-16243. Docket No. FAA-2007-29060; Directorate Identifier 2007-NE-34-AD.
(a) This airworthiness directive (AD) becomes effective April 22, 2010.Start Printed Page 12972
(c) This AD applies to International Aero Engines (IAE) V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 turbofan engines with high-pressure (HP) compressor stage 3-8 drums, part numbers (P/Ns) 6A4900, 6A5467, 6A6473, 6A7383, 6A7384, 6A7385, and 6A7401, installed. These engines are installed on, but not limited to, Airbus A319, A320, and A321 series airplanes and Boeing MD-90 airplanes.
(d) This AD results from reports of fractured vortex reducers found at shop visits. We are issuing this AD to inspect for cracks in the vortex reducer. Cracks in the vortex reducer could result in an uncontained failure of the HP compressor stage 3-8 drum and subsequent damage to the airplane.
(e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
Onetime Fluorescent Penetrant Inspection
(f) Fluorescent penetrant inspect the vortex reducer for cracks when the HPC stage 3-8 drum has between 3,000 and 13,500 cycles-since-new (CSN) if all of the following conditions also apply:
(1) The HPC stage 3-8 drum has ever operated in an engine at the V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, or V2533-A5 thrust ratings,
(2) The vortex reducer had cycles accumulated on it when mated with the HPC stage 3-8 drum, and
(3) The HPC stage 3-8 drum had fewer than 3,000 CSN when mated to the vortex reducer.
(g) If the vortex reducer is cracked, remove both the vortex reducer and the HPC stage 3-8 drum from service.
(h) After the effective date of this AD, do not return to service any HPC stage 3-8 drum that was removed as specified in paragraph (g) of this AD.
Alternative Methods of Compliance
(i) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19.
(j) Contact Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin firstname.lastname@example.org; telephone (781) 238-7117; fax (781) 238-7199, for more information about this AD.
Material Incorporated by Reference
(k) None.Start Signature
Issued in Burlington, Massachusetts, on March 11, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2010-5860 Filed 3-17-10; 8:45 am]
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