Airworthiness Directives; Rolls-Royce plc RB211 Trent 700 and Trent 800 Series Turbofan Engines, 17630-17632 [2010-7830]

Download as PDF 17630 Federal Register / Vol. 75, No. 66 / Wednesday, April 7, 2010 / Proposed Rules findings and conclusions as to whether FHFA made a demand that was substantially in excess of the decision in the underlying adversary adjudication and that was unreasonable when compared with that decision; and, if at issue, whether the applicant has committed a willful violation of the law or otherwise acted in bad faith, or whether special circumstances would make the award unjust. (e) In decisions on applications filed pursuant to § 1203.4(b), the adjudicative officer must include written findings and conclusions as to whether the applicant is a prevailing party and whether the position of FHFA was substantially justified; and, if at issue, whether the applicant unduly protracted or delayed the underlying adversary adjudication or whether special circumstance make the award unjust. CHAPTER XVII—OFFICE OF FEDERAL HOUSING ENTERPRISE OVERSIGHT, DEPARTMENT OF HOUSING AND URBAN DEVELOPMENT § 1203.27 Airworthiness Directives; Rolls-Royce plc RB211 Trent 700 and Trent 800 Series Turbofan Engines Review by FHFA. Within 30 days after the adjudicative officer issues an initial decision under § 1203.26, either the applicant or agency counsel may request the Director to review the initial decision of the adjudicative officer. The Director may also decide, at his or her discretion, to review the initial decision. If review is ordered, the Director must issue a final decision on the application for award or remand the application for award to the adjudicative officer for further proceedings under § 1203.25. § 1203.28 Judicial review. Any party, other than the United States, that is dissatisfied with the final decision on an application for award of fees and expenses under this part may seek judicial review as provided in 5 U.S.C. 504(c)(2). WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS § 1203.29 Payment of award. To receive payment of an award of fees and other expenses granted under this part, the applicant must submit a copy of the final decision that grants the award and a certification that the applicant will not seek review of the decision in the United States courts to the Director, Federal Housing Finance Agency, 1700 G Street, NW., Washington, DC 20552. FHFA must pay the amount awarded to the applicant within 60 days of receipt of the submission of the copy of the final decision and the certification, unless judicial review of the award has been sought by any party to the proceedings. VerDate Nov<24>2008 15:16 Apr 06, 2010 Jkt 220001 [FR Doc. 2010–7889 Filed 4–6–10; 8:45 am] the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. BILLING CODE 8070–01–P Examining the AD Docket PART 1705—[REMOVED] 2. Remove part 1705. Dated: April 1, 2010. Edward J. DeMarco, Acting Director, Federal Housing Finance Agency. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0364; Directorate Identifier 2009–NE–27–AD] RIN 2120–AA64 AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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, RollsRoyce 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 proposing 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: We must receive comments on this proposed AD by May 24, 2010. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–0364; Directorate Identifier 2009–NE–27–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). E:\FR\FM\07APP1.SGM 07APP1 Federal Register / Vol. 75, No. 66 / Wednesday, April 7, 2010 / Proposed Rules You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009–0021 (Corrected February 9, 2009), dated February 6, 2009 (referred to after this as ‘‘the MCAI’’), 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. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Rolls-Royce plc has issued Alert Service Bulletin RB.211–72–AG086, dated December 4, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of the United Kingdom, and is approved for operation in the United States. Pursuant to our bilateral agreement with the United Kingdom, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. VerDate Nov<24>2008 15:16 Apr 06, 2010 Jkt 220001 Costs of Compliance Based on the service information, we estimate that this proposed 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 proposed 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 proposed 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: 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. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 17631 We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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: Rolls-Royce plc: Docket No. FAA–2010– 0364; Directorate Identifier 2009–NE– 27–AD. Comments Due Date (a) We must receive comments by May 24, 2010. Affected Airworthiness Directives (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, fullfocused inspection 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-focused inspections and acceptance limits can be found in the current, applicable RR engine manual. E:\FR\FM\07APP1.SGM 07APP1 17632 Federal Register / Vol. 75, No. 66 / Wednesday, April 7, 2010 / Proposed Rules 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 (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 09 February, 2009), dated February 6, 2009, 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. Issued in Burlington, Massachusetts, on March 31, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0342; Directorate Identifier 2002–NE–08–AD] WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS ................................ ................................ ................................ ................................ ................................ ................................ ................................ ............................... ................................ ................................ ................................ ................................ ................................ ................................ SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for certain serial numbers (S/Ns) of Bombardier-Rotax GmbH type 912 F and 914 F series reciprocating engines. That AD currently requires initial and repetitive visual inspections of the engine crankcase for cracks. This proposed AD would require those same inspections, would add the 912 S series to the affected population, add a test procedure to determine the engine suitability for a special flight permit, and would change applicability from engine S/N to crankcase S/N. This proposed AD results from an increase in the affected crankcase population. We are proposing this AD to prevent oil loss caused by cracks in the engine crankcase, which could lead to in-flight failure of the engine and forced landing. Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. Contact BRP–Rotax GmbH & Co. KG, Welser Strasse 32, A–4623 Gunskirchen, Austria, for the service information identified in this proposed AD. ADDRESSES: BILLING CODE 4910–13–P RIN 2120–AA64 Airworthiness Directives; BombardierRotax GmbH Type 912 F, 912 S, and 914 F Series Reciprocating Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). 15:16 Apr 06, 2010 FK24100 FK32580 FK32580 FK32580 FK24100 FK24100 FK32580 FW11590 FK24100 FK24100 FK24100 FK24100 FK22279 FK26048 DATES: We must receive any comments on this proposed AD by June 7, 2010. [FR Doc. 2010–7830 Filed 4–6–10; 8:45 am] VerDate Nov<24>2008 Part No. Jkt 220001 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 Shaft serial No. MW0115238 ........................... MW0115512 ........................... MW0004708 ........................... MW00063868 ......................... DN65507 ................................ DN65158 ................................ MW0125467 ........................... DN65189 ................................ MW0091518 ........................... MW0126365 ........................... DN66422 ................................ MW0203314 ........................... DN63228 ................................ MW0026046 ........................... Compliance period (flight cycles in service after December 4, 2008.) 750 750 2000 2500 2500 2500 3500 3500 3500 3500 4750 4750 3250 4500 FOR FURTHER INFORMATION CONTACT: Richard Woldan, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7136; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–0342; Directorate Identifier 2002–NE–08–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Examining the AD Docket You may examine the AD docket on the Internet at https:// E:\FR\FM\07APP1.SGM 07APP1

Agencies

[Federal Register Volume 75, Number 66 (Wednesday, April 7, 2010)]
[Proposed Rules]
[Pages 17630-17632]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-7830]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0364; Directorate Identifier 2009-NE-27-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed 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 proposing 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: We must receive comments on this proposed AD by May 24, 2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0364; 
Directorate Identifier 2009-NE-27-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed AD. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.).

[[Page 17631]]

You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78).

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2009-0021 (Corrected February 9, 2009), dated 
February 6, 2009 (referred to after this as ``the MCAI''), 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.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Rolls-Royce plc has issued Alert Service Bulletin RB.211-72-AG086, 
dated December 4, 2008. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of the 
United Kingdom, and is approved for operation in the United States. 
Pursuant to our bilateral agreement with the United Kingdom, they have 
notified us of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all information provided by EASA and determined the unsafe 
condition exists and is likely to exist or develop on other products of 
the same type design.

Costs of Compliance

    Based on the service information, we estimate that this proposed 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 
proposed 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 proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    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 proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Rolls-Royce plc: Docket No. FAA-2010-0364; Directorate Identifier 
2009-NE-27-AD.

Comments Due Date

    (a) We must receive comments by May 24, 2010.

Affected Airworthiness Directives (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-focused inspection 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-focused inspections and acceptance limits 
can be found in the current, applicable RR engine manual.

[[Page 17632]]



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

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 09 February, 2009), dated February 6, 2009, 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.

    Issued in Burlington, Massachusetts, on March 31, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-7830 Filed 4-6-10; 8:45 am]
BILLING CODE 4910-13-P
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