Airworthiness Directives; Rolls-Royce plc RB211 Trent 700 and Trent 800 Series Turbofan Engines, 58290-58292 [2010-23831]

Download as PDF hsrobinson on DSK69SOYB1PROD with RULES 58290 Federal Register / Vol. 75, No. 185 / Friday, September 24, 2010 / Rules and Regulations (7) * * * (iii) Short-term, small amount Loans (STS loans). (A) Notwithstanding the provisions in § 701.21(c)(7)(ii), a Federal credit union may charge an interest rate of 1000 basis points above the maximum interest rate as established by the Board, provided the Federal credit union is making a closed-end loan in accordance with the following conditions: (1) The principal of the loan is not less than $200 or more than $1000; (2) The loan has a minimum maturity term of one month and a maximum maturity term of six months; (3) The Federal credit union does not make more than three STS loans in any rolling six-month period to any one borrower and makes no more than one short-term, small amount loan at a time to a borrower; (4) The Federal credit union must not roll-over any STS loan; (A) The prohibition against roll-overs does not apply to an extension of the loan term within the maximum loan terms in paragraph (c)(7)(iii)(3) provided the Federal credit union does not charge any additional fees or extend any new credit. (B) [Reserved] (5) The Federal credit union fully amortizes the loan; (6) The Federal credit union sets a minimum length of membership requirement of at least one month; (7) The Federal credit union charges an application fee to all members applying for a new loan that reflects the actual costs associated with processing the application, but in no case may the application fee exceed $20; and (8) The Federal credit union includes, in its written lending policies, a limit on the aggregate dollar amount of loans made under this section of a maximum of 20% of net worth and implements appropriate underwriting guidelines to minimize risk; for example, requiring a borrower to verify employment by producing at least two recent pay stubs. (B) STS Loan Program Guidance and Best Practices. In developing a successful STS loan program, a Federal credit union should consider how the program will help benefit a member’s financial well-being while considering the higher degree of risk associated with this type of lending. The guidance and best practices are intended to help Federal credit unions minimize risk and develop a successful program, but are not an exhaustive checklist and do not guarantee a successful program with a low degree of risk. (1) Program Features. Several features that may increase the success of an STS loan program and enhance member VerDate Mar<15>2010 16:03 Sep 23, 2010 Jkt 220001 benefit include adding a savings component, financial education, reporting of members’ payment of STS loans to credit bureaus, or electronic loan transactions as part of an STS program. In addition, although a Federal credit union cannot require members to authorize a payroll deduction, a Federal credit union should encourage or incentivize members to utilize payroll deduction. (2) Underwriting. Federal credit unions need to develop minimum underwriting standards that account for a member’s need for quickly available funds, while adhering to principles of responsible lending. Underwriting standards should address required documentation for proof of employment or income, including at least two recent paycheck stubs. FCUs should be able to use a borrower’s proof of recurring income as the key criterion in developing standards for maturity lengths and loan amounts so a borrower can manage repayment of the loan. For members with established accounts, FCUs should only need to review a member’s account records and proof of recurring income or employment. (3) Risk Avoidance. Federal credit unions need to consider risk avoidance strategies, including: requiring members to participate in direct deposit and conducting a thorough evaluation of the Federal credit union’s resources and ability to engage in an STS loan program. * * * * * an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: In completing a review of Engine Manual repair/acceptance limits for titanium compressor shafts, Rolls-Royce has found the specified limits to be incorrect such that the shot peened surface layer at life critical features (the axial dovetail slots) may have been inadvertently removed in-service. Removal of the shot peened layer results in increased vulnerability of the part to tensile stresses, which could reduce the life of the shaft to below the published life limits. We are issuing this AD to prevent failure of the intermediate-pressure (IP) and high-pressure (HP) shaft, which could result in an overspeed condition, possible uncontained disc failure and damage to the airplane. DATES: This AD becomes effective October 29, 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: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: [FR Doc. 2010–23610 Filed 9–23–10; 8:45 am] Discussion BILLING CODE 7535–01–P 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 April 7, 2010 (75 FR 17630). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0364; Directorate Identifier 2009–NE–27–AD; Amendment 39– 16446; AD 2010–20–11] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211 Trent 700 and Trent 800 Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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 SUMMARY: PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 In completing a review of Engine Manual repair/acceptance limits for titanium compressor shafts, Rolls-Royce has found the specified limits to be incorrect such that the shot peened surface layer at life critical features (the axial dovetail slots) may have been inadvertently removed in-service. Removal of the shot peened layer results in increased vulnerability of the part to tensile stresses, which could reduce the life of the shaft to below the published life limits. The acceptable limits for material loss on these surfaces have now been corrected in the Engine Manual. This AD identifies shafts for which such dressing operations have been known to have been carried out and requires that an inspection for compliance with the corrected Engine Manual limits be accomplished and that the shafts be dispositioned accordingly. E:\FR\FM\24SER1.SGM 24SER1 Federal Register / Vol. 75, No. 185 / Friday, September 24, 2010 / Rules and Regulations Comments We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed. We gave the public the opportunity to participate in developing this AD. We considered the comments received. hsrobinson on DSK69SOYB1PROD with RULES Requests To Change Paragraphs (e)(1) and (e)(2) of the Proposed AD Two commenters, The Boeing Company and American Airlines, ask us to change paragraphs (e)(1) and (e)(2) of the proposed AD to clarify the focused inspections and to include a reference to Rolls-Royce (RR) Alert NonModification Service Bulletin (NMSB) RB.211–72–AG086. The Boeing Company asks us to change paragraph (e)(2) to include a reference to RR Alert NMSB RB.211–72– AG086. They state that guidance on fullfocused inspections and acceptance limits can be found in either the current applicable RR engine manual or RR Alert NMSB RB.211–72–AG086. The Boeing Company feels that the information contained in the engine manual is not as clear or as accessible as in the RR Alert NMSB and that including the RR Alert NMSB, as an additional source of guidance, will assist the operators in conducting the associated inspections properly. We agree. We changed paragraph (e)(2) to include a reference to RR Alert NMSB RB.211–72–AG086. American Airlines, asks us to change paragraph (e)(1) to include a requirement for ‘‘all applicable focus inspection subtasks of the IP and HP compressor shafts * * *’’ American Airlines states that the Rolls-Royce Time Limits Manual and the applicable Engine Inspection Tasks do not use ‘‘full-focused inspection’’ terminology (as used in the NPRM). American Airlines believes that the AD terminology should be consistent with the manuals. We agree. We changed paragraph (e)(1) to state ‘‘Perform a one-time, piece-part, full inspection, including all applicable focus inspection Subtasks, of the IP and HP compressor shafts, listed by part number and serial number in Table 1 of this AD, before exceeding the compliance period specified in Table 1 of this AD.’’ Conclusion We reviewed the available data, including the comment[s] received, and determined that air safety and the public interest require adopting the AD with the changes described previously. VerDate Mar<15>2010 16:03 Sep 23, 2010 Jkt 220001 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 would affect about 12 products of U.S. registry. We also estimate that it would take about 8 work-hours per product to comply with this AD. The average labor rate is $85 per work-hour. Required parts would cost about $15,000 per product. Based on these figures, we estimate the cost of the AD on U.S. operators to be $188,160. Our cost estimate is exclusive of possible warranty coverage. 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. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 58291 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 (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, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2010–20–11 Rolls-Royce plc: Amendment 39–16446. Docket No. FAA–2010–0364; Directorate Identifier 2009–NE–27–AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 29, 2010. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce plc model (RR) RB211 Trent 768–60, 772–60, 772B–60, 875–17, 877–17, 884–17, 884B–17, 892–17, 892B–17, and 895–17 turbofan engines that have a compressor shaft listed by part number and serial number in Table 1 of this AD. These engines are installed on, but not limited to, Airbus A330 series and Boeing 777 series airplanes. Reason (d) This AD results from a review of engine manual repair/acceptance limits for titanium compressor shafts by RR. We are issuing this AD to prevent failure of the intermediatepressure (IP) and high-pressure (HP) shaft, which could result in an overspeed condition, possible uncontained disc failure and damage to the airplane. Actions and Compliance (e) Unless already done, do the following actions. (1) Perform a one-time, piece-part, full inspection, including all applicable focus E:\FR\FM\24SER1.SGM 24SER1 58292 Federal Register / Vol. 75, No. 185 / Friday, September 24, 2010 / Rules and Regulations inspection Subtasks, of the IP and HP compressor shafts listed by part number and serial number in Table 1 of this AD before exceeding the compliance period specified in Table 1 of this AD. (2) Guidance on full and focused inspections and acceptance limits can be found in the current, applicable RR engine manual and RR Alert Non-Modification Service Bulletin (NMSB) RB.211–72–AG086. TABLE 1—LIST OF AFFECTED SHAFTS Engine series Trent Trent Trent Trent Trent Trent Trent Trent Trent Trent Trent Trent Trent Trent 800 800 800 800 800 800 800 800 800 800 800 800 700 700 ........................... ........................... ........................... ........................... ........................... ........................... ........................... ........................... ........................... ........................... ........................... ........................... ........................... ........................... Affected component 1–8 1–4 1–4 1–4 1–8 1–8 1–4 1–4 1–8 1–8 1–8 1–8 1–8 1–8 IP Compressor Shaft .............................................. HP Compressor Shaft ............................................ HP Compressor Shaft ............................................ HP Compressor Shaft ............................................ IP Compressor Shaft .............................................. IP Compressor Shaft .............................................. HP Compressor Shaft ............................................ HP Compressor Shaft ............................................ IP Compressor Shaft .............................................. IP Compressor Shaft .............................................. IP Compressor Shaft .............................................. IP Compressor Shaft .............................................. IP Compressor Shaft .............................................. IP Compressor Shaft .............................................. Other FAA AD Provisions Related Information (g) Refer to MCAI EASA Airworthiness Directive 2009–0021 (Corrected February 9, 2009), dated February 6, 2009, and RR Alert NMSB RB.211–72–AG086, for related information. (h) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238– 7199, for more information about this AD. Material Incorporated by Reference (i) None. Issued in Burlington, Massachusetts, on September 17, 2010. Robert J. Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010–23831 Filed 9–23–10; 8:45 am] hsrobinson on DSK69SOYB1PROD with RULES BILLING CODE 4910–13–P 16:03 Sep 23, 2010 FK24100 FK32580 FK32580 FK32580 FK24100 FK24100 FK32580 FW11590 FK24100 FK24100 FK24100 FK24100 FK22279 FK26048 DEPARTMENT OF TRANSPORTATION (f) Alternative Methods of Compliance (AMOCs): 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 Part no. Jkt 220001 Federal Aviation Administration 14 CFR Part 47 [Docket No. FAA–2008–0188; Amdt. No. 47– 29A] RIN 2120–AI89 Re-Registration and Renewal of Aircraft Registration; OMB Approval of Information Collection; Correction Federal Aviation Administration (FAA), DOT. ACTION: Final rule; approval of information collection; correction. AGENCY: The FAA is correcting the notification of the Office of Management and Budget (OMB) approval of information collection requirements contained in the ‘‘Re-Registration and Renewal of Aircraft Registration’’ final rule. The final rule was published on July 20, 2010. The notification of OMB approval of information collection was published on August 30, 2010. This document corrects the OMB approval expiration date referenced in the August 30, 2010, notification. DATES: The final rule, including the information collection requirements in part 47, published July 20, 2010, at 75 FR 41968, and August 20, 2010, at 75 FR 52859, will become effective on October 1, 2010. The FAA received OMB approval for the information collection requirements on August 16, 2010. FOR FURTHER INFORMATION CONTACT: John G. Bent, Civil Aviation Registry, Mike Monroney Aeronautical Center, 6500 South MacArthur Boulevard, Oklahoma SUMMARY: PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Shaft serial no. Compliance period (flight cycles in service after December 4, 2008) MW0115238 MW0115512 MW0004708 MW00063868 DN65507 DN65158 MW0125467 DN65189 MW0091518 MW0126365 DN66422 MW0203314 DN63228 MW0026046 750 750 2000 2500 2500 2500 3500 3500 3500 3500 4750 4750 3250 4500 City, OK 73169; telephone: (405) 954– 4331. SUPPLEMENTARY INFORMATION: Background On July 20, 2010, the FAA published the final rule ‘‘Re-Registration and Renewal of Aircraft Registration’’ (75 FR 41968). The final rule contained information collection requirements in part 47 that had not yet been approved by OMB at the time of publication. In accordance with the Paperwork Reduction Act, the FAA submitted a copy of the new information collection requirements to OMB for its review. OMB approved the collection on August 16, 2010, and assigned the information collection OMB Control Number 2120–0729, which expires on February 29, 2012. In the notification of OMB approval document that was published on August 30, 2010, the FAA incorrectly stated that the expiration date was February 29, 2010. The FAA also incorrectly referenced docket number FAA–2008– 0118 instead of docket number FAA– 2008–0188. The FAA also inadvertently included references to parts 13 and 91 in the heading of the document; however, parts 13 and 91 did not contain information collection requirements. In final rule FR Doc. 2010–21561 published on August 30, 2010 (75 FR 52859), make the following corrections: Corrections to Preamble 1. On page 52859, in the second column, in the third line of the heading, remove ‘‘14 CFR Parts 13, 47, and 91’’ and add in its place ‘‘14 CFR Part 47.’’ ■ E:\FR\FM\24SER1.SGM 24SER1

Agencies

[Federal Register Volume 75, Number 185 (Friday, September 24, 2010)]
[Rules and Regulations]
[Pages 58290-58292]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-23831]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0364; Directorate Identifier 2009-NE-27-AD; 
Amendment 39-16446; AD 2010-20-11]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 700 and 
Trent 800 Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: 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:

    In completing a review of Engine Manual repair/acceptance limits 
for titanium compressor shafts, Rolls-Royce has found the specified 
limits to be incorrect such that the shot peened surface layer at 
life critical features (the axial dovetail slots) may have been 
inadvertently removed in-service. Removal of the shot peened layer 
results in increased vulnerability of the part to tensile stresses, 
which could reduce the life of the shaft to below the published life 
limits.

We are issuing this AD to prevent failure of the intermediate-pressure 
(IP) and high-pressure (HP) shaft, which could result in an overspeed 
condition, possible uncontained disc failure and damage to the 
airplane.

DATES: This AD becomes effective October 29, 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: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; 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 April 7, 2010 (75 FR 
17630). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    In completing a review of Engine Manual repair/acceptance limits 
for titanium compressor shafts, Rolls-Royce has found the specified 
limits to be incorrect such that the shot peened surface layer at 
life critical features (the axial dovetail slots) may have been 
inadvertently removed in-service. Removal of the shot peened layer 
results in increased vulnerability of the part to tensile stresses, 
which could reduce the life of the shaft to below the published life 
limits. The acceptable limits for material loss on these surfaces 
have now been corrected in the Engine Manual.
    This AD identifies shafts for which such dressing operations 
have been known to have been carried out and requires that an 
inspection for compliance with the corrected Engine Manual limits be 
accomplished and that the shafts be dispositioned accordingly.

[[Page 58291]]

Comments

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD as proposed.
    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Requests To Change Paragraphs (e)(1) and (e)(2) of the Proposed AD

    Two commenters, The Boeing Company and American Airlines, ask us to 
change paragraphs (e)(1) and (e)(2) of the proposed AD to clarify the 
focused inspections and to include a reference to Rolls-Royce (RR) 
Alert Non-Modification Service Bulletin (NMSB) RB.211-72-AG086.
    The Boeing Company asks us to change paragraph (e)(2) to include a 
reference to RR Alert NMSB RB.211-72-AG086. They state that guidance on 
full-focused inspections and acceptance limits can be found in either 
the current applicable RR engine manual or RR Alert NMSB RB.211-72-
AG086. The Boeing Company feels that the information contained in the 
engine manual is not as clear or as accessible as in the RR Alert NMSB 
and that including the RR Alert NMSB, as an additional source of 
guidance, will assist the operators in conducting the associated 
inspections properly.
    We agree. We changed paragraph (e)(2) to include a reference to RR 
Alert NMSB RB.211-72-AG086.
    American Airlines, asks us to change paragraph (e)(1) to include a 
requirement for ``all applicable focus inspection subtasks of the IP 
and HP compressor shafts * * *'' American Airlines states that the 
Rolls-Royce Time Limits Manual and the applicable Engine Inspection 
Tasks do not use ``full-focused inspection'' terminology (as used in 
the NPRM). American Airlines believes that the AD terminology should be 
consistent with the manuals.
    We agree. We changed paragraph (e)(1) to state ``Perform a one-
time, piece-part, full inspection, including all applicable focus 
inspection Subtasks, of the IP and HP compressor shafts, listed by part 
number and serial number in Table 1 of this AD, before exceeding the 
compliance period specified in Table 1 of this AD.''

Conclusion

    We reviewed the available data, including the comment[s] 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 would 
affect about 12 products of U.S. registry. We also estimate that it 
would take about 8 work-hours per product to comply with this AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $15,000 per product. Based on these figures, we estimate the cost 
of the AD on U.S. operators to be $188,160. Our cost estimate is 
exclusive of possible warranty coverage.

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 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 (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, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
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 adding the following new AD:

    2010-20-11 Rolls-Royce plc: Amendment 39-16446. Docket No. FAA-
2010-0364; Directorate Identifier 2009-NE-27-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
29, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc model (RR) RB211 Trent 
768-60, 772-60, 772B-60, 875-17, 877-17, 884-17, 884B-17, 892-17, 
892B-17, and 895-17 turbofan engines that have a compressor shaft 
listed by part number and serial number in Table 1 of this AD. These 
engines are installed on, but not limited to, Airbus A330 series and 
Boeing 777 series airplanes.

Reason

    (d) This AD results from a review of engine manual repair/
acceptance limits for titanium compressor shafts by RR. We are 
issuing this AD to prevent failure of the intermediate-pressure (IP) 
and high-pressure (HP) shaft, which could result in an overspeed 
condition, possible uncontained disc failure and damage to the 
airplane.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) Perform a one-time, piece-part, full inspection, including 
all applicable focus

[[Page 58292]]

inspection Subtasks, of the IP and HP compressor shafts listed by 
part number and serial number in Table 1 of this AD before exceeding 
the compliance period specified in Table 1 of this AD.
    (2) Guidance on full and focused inspections and acceptance 
limits can be found in the current, applicable RR engine manual and 
RR Alert Non-Modification Service Bulletin (NMSB) RB.211-72-AG086.

                                                            Table 1--List of Affected Shafts
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                                       Compliance period
                                                                                                                                       (flight cycles in
             Engine series                    Affected component                   Part no.                   Shaft serial no.           service after
                                                                                                                                       December 4, 2008)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Trent 800.............................  1-8 IP Compressor Shaft.......  FK24100                        MW0115238                                     750
Trent 800.............................  1-4 HP Compressor Shaft.......  FK32580                        MW0115512                                     750
Trent 800.............................  1-4 HP Compressor Shaft.......  FK32580                        MW0004708                                    2000
Trent 800.............................  1-4 HP Compressor Shaft.......  FK32580                        MW00063868                                   2500
Trent 800.............................  1-8 IP Compressor Shaft.......  FK24100                        DN65507                                      2500
Trent 800.............................  1-8 IP Compressor Shaft.......  FK24100                        DN65158                                      2500
Trent 800.............................  1-4 HP Compressor Shaft.......  FK32580                        MW0125467                                    3500
Trent 800.............................  1-4 HP Compressor Shaft.......  FW11590                        DN65189                                      3500
Trent 800.............................  1-8 IP Compressor Shaft.......  FK24100                        MW0091518                                    3500
Trent 800.............................  1-8 IP Compressor Shaft.......  FK24100                        MW0126365                                    3500
Trent 800.............................  1-8 IP Compressor Shaft.......  FK24100                        DN66422                                      4750
Trent 800.............................  1-8 IP Compressor Shaft.......  FK24100                        MW0203314                                    4750
Trent 700.............................  1-8 IP Compressor Shaft.......  FK22279                        DN63228                                      3250
Trent 700.............................  1-8 IP Compressor Shaft.......  FK26048                        MW0026046                                    4500
--------------------------------------------------------------------------------------------------------------------------------------------------------

Other FAA AD Provisions

    (f) Alternative Methods of Compliance (AMOCs): 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

    (g) Refer to MCAI EASA Airworthiness Directive 2009-0021 
(Corrected February 9, 2009), dated February 6, 2009, and RR Alert 
NMSB RB.211-72-AG086, for related information.
    (h) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

Material Incorporated by Reference

    (i) None.

    Issued in Burlington, Massachusetts, on September 17, 2010.
Robert J. Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-23831 Filed 9-23-10; 8:45 am]
BILLING CODE 4910-13-P