Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG. (RRD) Models Tay 650-15 and Tay 651-54 Turbofan Engines, 51651-51654 [2010-20657]

Download as PDF Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Rules and Regulations • An assessment, including the underlying analysis, of costs and benefits of potentially effective and reasonably feasible alternatives to the planned regulation, identified by the agencies or the public (including improving the current regulation and reasonably viable nonregulatory actions), and an explanation why the planned regulatory action is preferable to the identified potential alternatives. The OTS has determined that this final rule is not a significant regulatory action under Executive Order 12866. We have concluded that the changes made by this final rule will not have an annual effect on the economy of $100 million or more. The OTS further concludes that this final rule does not meet any of the other standards for a significant regulatory action set forth in Executive Order 12866. As required by Executive Order 12866, the OTS prepared a Regulatory Impact Analysis, which was submitted to OIRA on March 9, 2010. The OTS’s final revisions were submitted to OIRA on July 12, 2010. As discussed in more detail in the Regulatory Impact Analysis, the OTS determined that given the constraints imposed on the OTS by the S.A.F.E. Act, and based on the estimated cost, the rule was the least cost option available to the OTS. The OTS’s Regulatory Impact Analysis in its entirety is available at https:// www.regulations.gov, Docket No. OTS– 2010–0021. sroberts on DSKD5P82C1PROD with RULES E. OCC and OTS Unfunded Mandates Reform Act of 1995 Determination Section 202 of the Unfunded Mandates Reform Act of 1995 (2 U.S.C. 1532), requires the OCC and OTS to prepare a budgetary impact statement before promulgating a rule that includes a Federal mandate that may result in the expenditure by State, local, and Tribal governments, in the aggregate, or by the private sector, of $133 million or more in any one year. However, this requirement does not apply to regulations that incorporate requirements specifically set forth in law. Because this proposed rule implements the S.A.F.E. Act, the OTS and OCC have not conducted an Unfunded Mandates Analysis for this rulemaking.67 F. OCC and OTS Executive Order 13132 Determination E.O. 13132 sets forth certain ‘‘Fundamental Federalism Principles’’ and ‘‘Federalism Policymaking Criteria’’ that must be followed by the OCC and OTS in developing any regulation that 67 See 2 U.S.C. 1531. VerDate Mar<15>2010 17:48 Aug 20, 2010 Jkt 220001 has Federalism implications. A regulation has Federalism implications if it has ‘‘substantial direct effects 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.’’ If a rule meets the test for Federalism implications, the executive order requires the agency, among other things, to prepare a Federalism summary impact statement for inclusion in the rule’s SUPPLEMENTARY INFORMATION section and must consult with State and local officials about the rule. The OCC and OTS have determined that their respective portions of the final rule do not have a substantial direct effect on the States, on the connection between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, the final rule does not have any Federalism implications for purposes of Executive Order 13132. G. NCUA Executive Order 13132 Determination Executive Order 13132 encourages independent regulatory agencies to consider the impact of their actions on State and local interests. In adherence to fundamental Federalism principles, the NCUA, an independent regulatory agency as defined in 44 U.S.C. 3502(5) voluntarily complies with the Executive Order. The final rule applies to credit unions and would not have substantial direct effects on the States, on the connection between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. The NCUA has determined that the final rule does not constitute a policy that has Federalism implications for purposes of the Executive Order. H. NCUA: The Treasury and General Government Appropriations Act, 1999— Assessment of Federal Regulations and Policies on Families The NCUA has determined that this final rule would not affect family wellbeing within the meaning of section 654 of the Treasury and General Government Appropriations Act, 1999, Public Law 105–277, 112 Stat. 2681 (1998). I. NCUA: Small Business Regulatory Enforcement Fairness Act The Small Business Regulatory Enforcement Fairness Act of 1996 (Pub. L. 104–121) (SBREFA) provides generally for congressional review of PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 51651 agency rules. A reporting requirement is triggered in instances where NCUA issues a final rule as defined by section 551 of the Administrative Procedure Act. 5 U.S.C. 551. NCUA does not believe this final rule is a ‘‘major rule’’ within the meaning of the relevant sections of SBREFA. NCUA has submitted the rule to the Office of Management and Budget (OMB) for its determination and OMB concurred that the rule is not a major rule. [FR Doc. C1–2010–18148 Filed 8–20–10; 8:45 am] BILLING CODE 1301–00–D DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0037; Directorate Identifier 2007–NE–41–AD; Amendment 39– 16404; AD 2010–17–12] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG. (RRD) Models Tay 650–15 and Tay 651–54 Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: SUMMARY: Strip results from some of the engines listed in the applicability section of this AD revealed excessively corroded low-pressure turbine disks stage 2 and stage 3. The corrosion is considered to be caused by the environment in which these engines are operated. Following a life assessment based on the strip findings it is concluded that inspections for corrosion attack are required. The action specified by this European Aviation Safety Agency (EASA) AD 2008– 0122 was intended to avoid a failure of a lowpressure turbine disk stage 2 or stage 3 due to potential corrosion problems which could result in uncontained engine failure and damage to the airplane. It has been later realized that the same unsafe condition could potentially occur on more serial numbers for the Tay 650–15 engines and on the Tay 651– 54 engines. This AD, superseding EASA AD 2008–0122, retaining its requirements, is therefore issued to expand the Applicability in adding further engine serial numbers for the Tay 650–15 engines and in adding the Tay 651–54 engines. E:\FR\FM\23AUR1.SGM 23AUR1 51652 Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Rules and Regulations Request to Reference the Current EASA Type Certificate Approval One commenter, RRD, requests that we revise the AD to reference the current EASA type certificate approval rather than the original United Kingdom type certificate approval. We agree that the current type certificate approval is from EASA, but since we do not repeat the preamble section of the proposed AD that references this information, we did not change the AD. We will reference the correct information in future AD actions. Discussion The FAA proposed to amend 14 CFR part 39 by superseding AD 2009–22–01, Amendment 39–16052 (74 FR 55121, October 27, 2009), with a proposed AD. The proposed AD applies to RRD Models Tay 650–15 and Tay 651–54 turbofan engines. We published the proposed AD in the Federal Register on May 6, 2010 (75 FR 24825). That action proposed to correct an unsafe condition for the specified products. The MCAI states: sroberts on DSKD5P82C1PROD with RULES We are issuing this AD to detect corrosion that could cause the stage 2 or stage 3 disk of the LP turbine to fail and result in an uncontained failure of the engine. DATES: This AD becomes effective September 27, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 27, 2010. ADDRESSES: 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. FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov; phone: (781) 238–7758; fax: (781) 238–7199. SUPPLEMENTARY INFORMATION: Request To Remove Gulfstream G–IV Airplane From the Applicability RRD requests that we delete the Gulfstream G–IV airplane from the applicability, as the Tay 650–15 and Tay 651–54 turbofan engines are not installed on that airplane. We agree and removed that airplane from the applicability. Strip results from some of the engines listed in the applicability section of this AD revealed excessively corroded low-pressure turbine disks stage 2 and stage 3. The corrosion is considered to be caused by the environment in which these engines are operated. Following a life assessment based on the strip findings it is concluded that inspections for corrosion attack are required. The action specified by this European Aviation Safety Agency (EASA) AD 2008– 0122 was intended to avoid a failure of a lowpressure turbine disk stage 2 or stage 3 due to potential corrosion problems which could result in uncontained engine failure and damage to the airplane. It has been later realized that the same unsafe condition could potentially occur on more serial numbers for the Tay 650–15 engines and on the Tay 651– 54 engines. This AD, superseding EASA AD 2008–0122, retaining its requirements, is therefore issued to expand the Applicability in adding further engine serial numbers for the Tay 650–15 engines and in adding the Tay 651–54 engines. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. VerDate Mar<15>2010 15:54 Aug 20, 2010 Jkt 220001 Request To Correct a Typographical Error RRD requests that we correct a typographical error under FAA’s Determination and Requirements of this Proposed AD. Specifically, change ‘‘HP’’ to ‘‘LP’’. We agree that ‘‘HP’’ should be ‘‘LP’’. However, that paragraph is not repeated in the Final Rule. We did not change the AD. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance Based on the service information, we estimate that this AD will affect about three Tay 651–54 engines installed on airplanes of U.S. registry. We also estimate that it will take about three work-hours per engine to comply with this AD. The average labor rate is $85 per work-hour. Required parts will cost about $40,000 per engine. Based on these figures, we estimate the cost of the AD on U.S. operators to be $120,765. 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 PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 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. Regulatory Findings We 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 this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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 regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 (phone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, ■ E:\FR\FM\23AUR1.SGM 23AUR1 Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Rules and Regulations the FAA amends 14 CFR part 39 as follows: TABLE 1—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (CARRIED FORWARD FROM AD 2008–10–14 AND AD 2009–22–01)—Continued PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–16052 (74 FR 55121, October 27, 2009), and by adding a new airworthiness directive, Amendment 39–16404, to read as follows: 2010–17–12 Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly Rolls-Royce plc, Derby, England): Amendment 39–16404. Docket No. FAA–2007–0037; Directorate Identifier 2007–NE–41–AD. Effective Date (a) This airworthiness directive (AD) becomes effective September 27, 2010. Affected ADs (b) This AD supersedes AD 2009–22–01, Amendment 39–16052. Applicability (c) This AD applies to: (1) RRD model Tay 650–15 turbofan engines that have a serial number listed in Table 1, Table 2, or Table 3 of this AD; (2) All model Tay 651–54 turbofan engines; and (3) Engines with a low-pressure (LP) turbine module M05300AA installed. These engines are installed on, but not limited to, Fokker F.28 Mark 0070 and 0100 airplanes, and Boeing 727 airplanes modified in accordance with Supplemental Type Certificate No. SA8472SW. TABLE 2—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (CARRIED FORWARD FROM AD 2009–22–01) Engine Serial No. 17249 17303 17358 17370 17425 17426 17433 17438 17445 17446 17460 17474 17478 17490 17491 17517 17518 17522 17534 17535 17536 17538 17540 17541 17552 17553 17585 17613 17723 17724 17740 17759 17760 17807 TABLE 1—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (CARRIED FORWARD FROM AD 2008–10–14 AND AD 2009–22–01) sroberts on DSKD5P82C1PROD with RULES Engine Serial No. 17251 17255 17256 17273 17275 17280 17281 17282 17300 17301 17327 17332 17365 17393 17437 17443 17470 17520 17521 17523 17539 15:54 Aug 20, 2010 Jkt 220001 Engine Serial No. 17344 17360 17376 17413 17537 17694 17698 17707 17716 17718 17719 17731 17756 17757 17542 17556 17561 17562 17563 17580 17581 17612 17618 17635 17637 17645 17661 17686 17699 17701 17702 17736 17737 17738 17739 17741 17742 17808 ■ VerDate Mar<15>2010 TABLE 3—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (ADDED NEW IN THIS AD) Engine Serial No. Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 51653 Reason (d) Strip results from some of the engines listed in the applicability section of this AD revealed excessively corroded low-pressure turbine disks stage 2 and stage 3. The corrosion is considered to be caused by the environment in which these engines are operated. Following a life assessment based on the strip findings it is concluded that inspections for corrosion attack are required. The action specified by this European Aviation Safety Agency (EASA) AD 2008– 0122 was intended to avoid a failure of a lowpressure turbine disk stage 2 or stage 3 due to potential corrosion problems which could result in uncontained engine failure and damage to the airplane. It has been later realized that the same unsafe condition could potentially occur on more serial numbers for the Tay 650–15 engines and on the Tay 651– 54 engines. This AD, superseding EASA AD 2008–0122, retaining its requirements, is therefore issued to expand the Applicability in adding further engine serial numbers for the Tay 650–15 engines and in adding the Tay 651–54 engines. We are issuing this AD to detect corrosion that could cause the stage 2 or stage 3 disk of the LP turbine to fail and result in an uncontained failure of the engine. Actions and Compliance (e) Unless already done, do the following actions. (1) Prior to accumulating 11,700 flight cycles (FC) since new of disk life, and thereafter at intervals not exceeding 11,700 FC of disk life, inspect the LP turbine disks stage 2 and stage 3 for corrosion using RRD Alert Service Bulletin (ASB) No. TAY–72– A1524, Revision 3, dated March 24, 2010. (2) For engines with disk life that already exceed 11,700 FC on the effective date of this AD, perform the inspection within 90 days after the effective date of this AD. (3) When, during any of the inspections as required by paragraphs (e)(1) and (e)(2) of this AD, corrosion is found, replace the affected parts. RRD TAY 650 Engine Manual—E–TAY–3RR, Tasks 72–52–23–200– 000 and 72–52–24–200–000, and RRD TAY 651 Engine Manual—E–TAY–5RR, Tasks 72– 52–23–200–000 and 72–52–24–200–000, contain guidance on performing the E:\FR\FM\23AUR1.SGM 23AUR1 51654 Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Rules and Regulations inspection for corrosion and rejection criteria. DEPARTMENT OF TRANSPORTATION Previous Credit Federal Aviation Administration (f) Initial inspections done before the effective date of this AD on LP turbine disks stage 2 and stage 3 listed in Table 1 and Table 2 of this AD using RRD ASB No. TAY– 72–A1524, Revision 1, dated September 1, 2006, or Revision 2, dated June 13, 2008, comply with the initial inspection requirements specified in this AD. Alternative Methods of Compliance (AMOCs) Airworthiness Directives; Rolls-Royce plc (RR) RB211–22B and RB211–524 Series Turbofan Engines We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: SUMMARY: (h) Refer to EASA AD 2010–060R1, dated April 14, 2010, for related information. Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlwitz, 15827 Blankenfelde-Mahlow, Germany; phone: 011 49 (0) 33–7086–1883; fax: 011 49 (0) 33– 7086–3276, for a copy of the service information referenced in this AD. (i) Contact Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov; phone: (781) 238–7758; fax (781) 238–7199, for more information about this AD. Material Incorporated by Reference (j) You must use RRD Alert Service Bulletin No. TAY–72–A1524, Revision 3, dated March 24, 2010, to do the inspections required by this AD. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlwitz, 15827 Blankenfelde-Mahlow, Germany; phone: 011 49 (0) 33–7086–1883; fax: 011 49 (0) 33– 7086–3276. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. sroberts on DSKD5P82C1PROD with RULES RIN 2120–AA64 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. Related Information Issued in Burlington, Massachusetts, on August 6, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010–20657 Filed 8–20–10; 8:45 am] BILLING CODE 4910–13–P 15:54 Aug 20, 2010 [Docket No. FAA–2009–1157; Directorate Identifier 2009–NE–26–AD; Amendment 39– 16402; AD 2010–17–10] AGENCY: (g) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. VerDate Mar<15>2010 14 CFR Part 39 Jkt 220001 Several low pressure turbine (LPT) shafts have been found with cracks originating from the rear cooling air holes. The cracks were found at normal component overhaul, by the standard Magnetic Particle Inspection (MPI) technique defined in the associated engine manual. The cracks have been found to initiate from corrosion pits. Propagation of a crack from the rear cooling air holes may result in shaft failure and subsequently in an uncontained Low Pressure Turbine failure. For the reasons stated above, this AD requires the inspection of the affected engines’ LPT shafts and replacement of the shaft, as necessary. We are issuing this AD to detect cracks, initiated by corrosion pits, originating from the rear cooling air holes, which could result in shaft failure and subsequently in an uncontained failure of the LPT and damage to the airplane. This AD becomes effective September 27, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 27, 2010. ADDRESSES: 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. FOR FURTHER INFORMATION CONTACT: Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; DATES: PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 e-mail: alan.strom@faa.gov; telephone (781) 238–7143; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on May 19, 2010 (75 FR 27964). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Several low pressure turbine (LPT) shafts have been found with cracks originating from the rear cooling air holes. The cracks were found at normal component overhaul, by the standard Magnetic Particle Inspection (MPI) technique defined in the associated engine manual. The cracks have been found to initiate from corrosion pits. Propagation of a crack from the rear cooling air holes may result in shaft failure and subsequently in an uncontained Low Pressure Turbine failure. For the reasons stated above, this AD requires the inspection of the affected engines’ LPT shafts and replacement of the shaft, as necessary. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. The commenter supports the NPRM. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance Based on the service information, we estimate that this AD will affect about 10 products of U.S. registry. We also estimate that it will take about 7 workhours per product to comply with this AD. The average labor rate is $85 per work-hour. Required parts will cost about $15,000 per product. Based on these figures, we estimate the cost of the AD on U.S. operators to be $155,950. 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 E:\FR\FM\23AUR1.SGM 23AUR1

Agencies

[Federal Register Volume 75, Number 162 (Monday, August 23, 2010)]
[Rules and Regulations]
[Pages 51651-51654]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-20657]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0037; Directorate Identifier 2007-NE-41-AD;
Amendment 39-16404; AD 2010-17-12]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG.
(RRD) Models Tay 650-15 and Tay 651-54 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) issued 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:

Strip results from some of the engines listed in the
applicability section of this AD revealed excessively corroded low-
pressure turbine disks stage 2 and stage 3. The corrosion is
considered to be caused by the environment in which these engines
are operated. Following a life assessment based on the strip
findings it is concluded that inspections for corrosion attack are
required. The action specified by this European Aviation Safety
Agency (EASA) AD 2008-0122 was intended to avoid a failure of a low-
pressure turbine disk stage 2 or stage 3 due to potential corrosion
problems which could result in uncontained engine failure and damage
to the airplane. It has been later realized that the same unsafe
condition could potentially occur on more serial numbers for the Tay
650-15 engines and on the Tay 651-54 engines. This AD, superseding
EASA AD 2008-0122, retaining its requirements, is therefore issued
to expand the Applicability in adding further engine serial numbers
for the Tay 650-15 engines and in adding the Tay 651-54 engines.

[[Page 51652]]

We are issuing this AD to detect corrosion that could cause the
stage 2 or stage 3 disk of the LP turbine to fail and result in an
uncontained failure of the engine.

DATES: This AD becomes effective September 27, 2010. The Director of
the Federal Register approved the incorporation by reference of certain
publications listed in this AD as of September 27, 2010.

ADDRESSES: 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.

FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
mark.riley@faa.gov; phone: (781) 238-7758; fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

The FAA proposed to amend 14 CFR part 39 by superseding AD 2009-22-
01, Amendment 39-16052 (74 FR 55121, October 27, 2009), with a proposed
AD. The proposed AD applies to RRD Models Tay 650-15 and Tay 651-54
turbofan engines. We published the proposed AD in the Federal Register
on May 6, 2010 (75 FR 24825). That action proposed to correct an unsafe
condition for the specified products. The MCAI states:

Comments

We gave the public the opportunity to participate in developing
this AD. We considered the comments received.

Request to Reference the Current EASA Type Certificate Approval

One commenter, RRD, requests that we revise the AD to reference the
current EASA type certificate approval rather than the original United
Kingdom type certificate approval.
We agree that the current type certificate approval is from EASA,
but since we do not repeat the preamble section of the proposed AD that
references this information, we did not change the AD. We will
reference the correct information in future AD actions.

Request To Correct a Typographical Error

RRD requests that we correct a typographical error under FAA's
Determination and Requirements of this Proposed AD. Specifically,
change ``HP'' to ``LP''.
We agree that ``HP'' should be ``LP''. However, that paragraph is
not repeated in the Final Rule. We did not change the AD.

Request To Remove Gulfstream G-IV Airplane From the Applicability

RRD requests that we delete the Gulfstream G-IV airplane from the
applicability, as the Tay 650-15 and Tay 651-54 turbofan engines are
not installed on that airplane.
We agree and removed that airplane from the applicability.

Conclusion

We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.

Costs of Compliance

Based on the service information, we estimate that this AD will
affect about three Tay 651-54 engines installed on airplanes of U.S.
registry. We also estimate that it will take about three work-hours per
engine to comply with this AD. The average labor rate is $85 per work-
hour. Required parts will cost about $40,000 per engine. Based on these
figures, we estimate the cost of the AD on U.S. operators to be
$120,765.

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.

Regulatory Findings

We 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 this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.

Examining the AD Docket

You may examine the AD docket on the Internet at https://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 (phone (800) 647-5527) is provided in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,

[[Page 51653]]

the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by removing Amendment 39-16052 (74 FR
55121, October 27, 2009), and by adding a new airworthiness directive,
Amendment 39-16404, to read as follows:

2010-17-12 Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly
Rolls-Royce plc, Derby, England): Amendment 39-16404. Docket No.
FAA-2007-0037; Directorate Identifier 2007-NE-41-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective
September 27, 2010.

Affected ADs

(b) This AD supersedes AD 2009-22-01, Amendment 39-16052.

Applicability

(c) This AD applies to:
(1) RRD model Tay 650-15 turbofan engines that have a serial
number listed in Table 1, Table 2, or Table 3 of this AD;
(2) All model Tay 651-54 turbofan engines; and
(3) Engines with a low-pressure (LP) turbine module M05300AA
installed. These engines are installed on, but not limited to,
Fokker F.28 Mark 0070 and 0100 airplanes, and Boeing 727 airplanes
modified in accordance with Supplemental Type Certificate No.
SA8472SW.

Table 1--Affected Tay 650-15 Engines by Serial Number (Carried Forward
From AD 2008-10-14 and AD 2009-22-01)
------------------------------------------------------------------------
Engine Serial No.
-------------------------------------------------------------------------
17251
17255
17256
17273
17275
17280
17281
17282
17300
17301
17327
17332
17365
17393
17437
17443
17470
17520
17521
17523
17539
17542
17556
17561
17562
17563
17580
17581
17612
17618
17635
17637
17645
17661
17686
17699
17701
17702
17736
17737
17738
17739
17741
17742
17808
------------------------------------------------------------------------

Table 2--Affected Tay 650-15 Engines by Serial Number (Carried Forward
From AD 2009-22-01)
------------------------------------------------------------------------
Engine Serial No.
-------------------------------------------------------------------------
17249
17303
17358
17370
17425
17426
17433
17438
17445
17446
17460
17474
17478
17490
17491
17517
17518
17522
17534
17535
17536
17538
17540
17541
17552
17553
17585
17613
17723
17724
17740
17759
17760
17807
------------------------------------------------------------------------

Table 3--Affected Tay 650-15 Engines by Serial Number (Added New in This
AD)
------------------------------------------------------------------------
Engine Serial No.
-------------------------------------------------------------------------
17344
17360
17376
17413
17537
17694
17698
17707
17716
17718
17719
17731
17756
17757
------------------------------------------------------------------------

Reason

(d) Strip results from some of the engines listed in the
applicability section of this AD revealed excessively corroded low-
pressure turbine disks stage 2 and stage 3. The corrosion is
considered to be caused by the environment in which these engines
are operated. Following a life assessment based on the strip
findings it is concluded that inspections for corrosion attack are
required. The action specified by this European Aviation Safety
Agency (EASA) AD 2008-0122 was intended to avoid a failure of a low-
pressure turbine disk stage 2 or stage 3 due to potential corrosion
problems which could result in uncontained engine failure and damage
to the airplane. It has been later realized that the same unsafe
condition could potentially occur on more serial numbers for the Tay
650-15 engines and on the Tay 651-54 engines. This AD, superseding
EASA AD 2008-0122, retaining its requirements, is therefore issued
to expand the Applicability in adding further engine serial numbers
for the Tay 650-15 engines and in adding the Tay 651-54 engines.
We are issuing this AD to detect corrosion that could cause the
stage 2 or stage 3 disk of the LP turbine to fail and result in an
uncontained failure of the engine.

Actions and Compliance

(e) Unless already done, do the following actions.
(1) Prior to accumulating 11,700 flight cycles (FC) since new of
disk life, and thereafter at intervals not exceeding 11,700 FC of
disk life, inspect the LP turbine disks stage 2 and stage 3 for
corrosion using RRD Alert Service Bulletin (ASB) No. TAY-72-A1524,
Revision 3, dated March 24, 2010.
(2) For engines with disk life that already exceed 11,700 FC on
the effective date of this AD, perform the inspection within 90 days
after the effective date of this AD.
(3) When, during any of the inspections as required by
paragraphs (e)(1) and (e)(2) of this AD, corrosion is found, replace
the affected parts. RRD TAY 650 Engine Manual--E-TAY-3RR, Tasks 72-
52-23-200-000 and 72-52-24-200-000, and RRD TAY 651 Engine Manual--
E-TAY-5RR, Tasks 72-52-23-200-000 and 72-52-24-200-000, contain
guidance on performing the

[[Page 51654]]

inspection for corrosion and rejection criteria.

Previous Credit

(f) Initial inspections done before the effective date of this
AD on LP turbine disks stage 2 and stage 3 listed in Table 1 and
Table 2 of this AD using RRD ASB No. TAY-72-A1524, Revision 1, dated
September 1, 2006, or Revision 2, dated June 13, 2008, comply with
the initial inspection requirements specified in this AD.

Alternative Methods of Compliance (AMOCs)

(g) The Manager, Engine Certification Office, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.

Related Information

(h) Refer to EASA AD 2010-060R1, dated April 14, 2010, for
related information. Contact Rolls-Royce Deutschland Ltd & Co KG,
Eschenweg 11, Dahlwitz, 15827 Blankenfelde-Mahlow, Germany; phone:
011 49 (0) 33-7086-1883; fax: 011 49 (0) 33-7086-3276, for a copy of
the service information referenced in this AD.
(i) Contact Mark Riley, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov;
phone: (781) 238-7758; fax (781) 238-7199, for more information
about this AD.

Material Incorporated by Reference

(j) You must use RRD Alert Service Bulletin No. TAY-72-A1524,
Revision 3, dated March 24, 2010, to do the inspections required by
this AD.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlwitz, 15827
Blankenfelde-Mahlow, Germany; phone: 011 49 (0) 33-7086-1883; fax:
011 49 (0) 33-7086-3276.
(3) You may review copies at the FAA, New England Region, 12 New
England Executive Park, Burlington, MA; or at the National Archives
and Records Administration (NARA). For information on the
availability of this material at NARA, call (202) 741-6030, or go
to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

Issued in Burlington, Massachusetts, on August 6, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-20657 Filed 8-20-10; 8:45 am]
BILLING CODE 4910-13-P

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