Airworthiness Directives; Rolls-Royce plc (RR) Turbofan Engines, 65136-65138 [2011-27069]

Download as PDF 65136 Proposed Rules Federal Register Vol. 76, No. 203 Thursday, October 20, 2011 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0562; Directorate Identifier 2009–NE–29–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc (RR) Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) that applies to all RR model RB211– 524G2–T–19, –524G3–T–19, –524H–T– 36, and –524H2–T–19; and RB211– Trent 553–61, 553A2–61, 556–61, 556A2–61, 556B–61, 556B2–61, 560–61, 560A2–61; RB211–Trent 768–60, 772– 60, 772B–60; and RB211–Trent 875–17, 877–17, 884–17, 884B–17, 892–17, 892B–17, and 895–17 turbofan engines that have a high-pressure (HP) compressor stage 1 to 4 rotor disc with a part number (P/N) listed in Table 1 of this proposed AD. The existing AD currently requires repetitive inspections of the axial dovetail slots, and follow-on corrective action depending on findings. Since we issued that AD, we determined that the definition of shop visit is too restrictive in the existing AD. This proposed AD would continue to require those repetitive inspections and followon corrective actions, and it would change the definition of a shop visit to be less restrictive. We are proposing this AD to detect cracks in the HP compressor stage 1 and 2 disc posts, which could result in failure of the disc post and HP compressor blades, release of uncontained engine debris, and damage to the airplane. DATES: We must receive comments on this proposed AD by December 19, 2011. ADDRESSES: You may send comments, using the procedures found in 14 CFR pmangrum on DSK29S0YB1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 15:27 Oct 19, 2011 Jkt 226001 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011–44–1332–242424; fax: 011–44– 1332–245418 or e-mail from https:// www.rolls-royce.com/contact/ civil_team.jsp, or download the publication from https:// www.aeromanager.com. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility 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 Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7143; fax: 781–238– 7199; e-mail: alan.strom@faa.gov. 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. PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 FAA–2010–0562; Directorate Identifier 2009–NE–29–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 because of 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 we receive about this proposed AD. Discussion On April 12, 2011, we issued AD 2011–09–07, Amendment 39–16669 (76 FR 24793, May 3, 2011), for all RR model RB211–524G2–T–19, –524G3–T– 19, –524H–T–36, and –524H2–T–19; and RB211 Trent 553–61, 553A2–61, 556–61, 556A2–61, 556B–61, 556B2–61, 560–61, 560A2–61; RB211 Trent 768– 60, 772–60, 772B–60; and RB211 Trent 875–17, 877–17, 884–17, 884B–17, 892– 17, 892B–17, and 895–17 turbofan engines. That AD requires initial and repetitive fluorescent penetrant inspections of the HP compressor stage 1 to 4 rotor discs at the first shop visit after accumulating 1,000 cycles-sincenew on the stage 1 to 4 rotor discs or at the next shop visit after the effective date of that AD, which ever occurs later. That AD also requires repetitive inspections at every shop visit. That AD resulted from findings of anomalies at the corners of the disc posts during manufacture of stage 1 and stage 2 discs with axial dovetails slots. We issued that AD to detect cracks in the HP compressor stage 1 and stage 2 disc posts, which could result in failure of the disc post and release of HP compressor blades, release of uncontained engine debris, and damage to the airplane. Actions Since Existing AD Was Issued Since we issued AD 2011–09–07, Amendment 39–16669 (76 FR 24793, May 3, 2011), we found that the definition of ‘‘shop visit’’ in the AD is too restrictive, in that it would require operators to inspect more often than required to ensure safety. We also found that Alert Service Bulletin (ASB) No. RB.211–72–AF964, Revision 2, dated June 8, 2011, also may be appropriate to E:\FR\FM\20OCP1.SGM 20OCP1 Federal Register / Vol. 76, No. 203 / Thursday, October 20, 2011 / Proposed Rules the corrective action in that AD, as is ASB No. RB.211–72–AF964, Revision 1, dated June 6, 2008 which is referenced in AD 2011–09–07. Relevant Service Information We reviewed RR ASB No. RB.211–72– AF964, Revision 1, dated June 6, 2008, and Revision 2, dated June 8, 2011. The ASB describes procedures for cleaning and inspecting the axial dovetail slots. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the definition of shop visit was too restrictive, and that the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would change the definition of a shop visit in AD 2011– 09–07 to ‘‘whenever all compressor blades are removed from the HP compressor drum.’’ This proposed AD would also allow using ASB No. RB.211–72–AF964, Revision 1, dated June 6, 2008, or ASB No. RB.211–72– AF964, Revision 2, dated June 8, 2011, to perform the inspection. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 371 products of U.S. registry. We also estimate that it would take about 20 work-hours per product to comply with this AD. The average labor rate is $85 per work-hour. No parts would be required per product. Based on these figures, we estimate the cost of the AD on U.S. operators to be $630,700. 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 have 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 that the 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), (3) Will not affect intrastate aviation in Alaska, and (4) 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. 65137 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, 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 removing airworthiness directive (AD) 2011–09–07, Amendment 39–166679 (76 FR 24793, May 3, 2011), and adding the following new AD: Rolls-Royce plc: Docket No. FAA–2010– 0562; Directorate Identifier 2009–NE– 29–AD. (a) Comments Due Date The FAA must receive comments on this AD action by December 19, 2011. (b) Affected ADs This AD supersedes AD 2011–09–07, Amendment 39–16669 (76 FR 24793, May 3, 2011). (c) Applicability This AD applies to Rolls-Royce plc (RR) model RB211–524G2–T–19, –524G3–T–19, –524H–T–36, and –524H2–T–19; and RB211– Trent 553–61, 553A2–61, 556–61, 556A2–61, 556B–61 556B2–61, 560–61, 560A2–61; RB211–Trent 768–60, 772–60, 772B–60; and RB211–Trent 875–17, 877–17, 884–17, 884B– 17, 892–17, 892B–17, and 895–17 turbofan engines that have a high-pressure (HP) compressor stage 1 to 4 rotor disc with a part number (P/N) listed in Table 1 of this AD. TABLE 1—AFFECTED HP COMPRESSOR STAGE 1 TO 4 ROTOR DISC P/NS BY ENGINE MODEL Engine model HP compressor stage 1 to 4 rotor disc P/N (1) RB211–524G2–T–19, –524G3–T–19, –524H–T–36, and –524H2–T–19 ..................................... (2) RB211 Trent 553–61, 553A2–61, 556–61, 556A2–61, 556B–61, 556B2–61, 560–61, and 560A2-61. (3) RB211 Trent 768–60, 772–60, and 772B–60 ................................................................................ pmangrum on DSK29S0YB1PROD with PROPOSALS (4) RB211 Trent 875–17, 877–17, 884–17, 884B–17, 892-17, 892B–17, and 895–17 ..................... (d) Unsafe Condition This AD was prompted by our determination that the definition of ‘‘shop visit’’ in the existing AD is too restrictive, in that it would require operators to inspect more often than required to ensure safety. We are issuing this AD to detect cracks in the HP VerDate Mar<15>2010 15:27 Oct 19, 2011 Jkt 226001 compressor stage 1 and 2 disc posts, which could result in failure of the disc post and HP compressor blades, release of uncontained engine debris, and damage to the airplane. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 FW20195, FK25502, or FW23711. FK30524. FK22745, FK24031, FK26185, FK23313, FK25502, FK32129, FW20195, FW20196, FW20197, FW20638, or FW23711. FK24009, FK26167, FK32580, FW11590, or FW61622. (e) Compliance Comply with this AD within the compliance times specified, unless already done. E:\FR\FM\20OCP1.SGM 20OCP1 65138 Federal Register / Vol. 76, No. 203 / Thursday, October 20, 2011 / Proposed Rules (f) Cleaning and Inspection DEPARTMENT OF THE TREASURY (1) Clean and perform a fluorescent penetrant inspection of the HP compressor stage 1 to 4 rotor discs at the first shop visit after accumulating 1,000 cycles since new on the stage 1 to 4 rotor discs or at the next shop visit after the effective date of this AD, which ever occurs later. (2) Use paragraph 3.A through 3.E.(11) of the Accomplishment Instructions of RollsRoyce Alert Service Bulletin (ASB) No. RB.211–72–AF964, Revision 1, dated June 6, 2008, or ASB No. RB.211–72–AF964, Revision 2, dated June 8, 2011, to do the inspections. (3) Thereafter at every engine shop visit, perform the inspection specified by paragraph (f) of this AD. (g) Definition For the purpose of this AD, an ‘‘engine shop visit’’ is whenever all compressor blades are removed from the HP compressor drum. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (i) Related Information pmangrum on DSK29S0YB1PROD with PROPOSALS (1) For more information about this AD, contact Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7143; fax: 781–238–7199; e-mail: alan.strom@faa.gov. (2) See European Aviation Safety Agency Airworthiness Directive 2011–0073R1, dated April 8, 2009, for related information. (3) For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011–44–1332– 242424; fax: 011–44–1332–245418 or e-mail from https://www.rolls-royce.com/contact/ civil_team.jsp, or download the publication from https://www.aeromanager.com. You may review copies at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on October 14, 2011. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011–27069 Filed 10–19–11; 8:45 am] BILLING CODE 4910–13–P Internal Revenue Service 40 CFR Part 60 and 63 26 CFR Part 1 [REG–140280–09] [EPA–HQ–OAR–2010–0505; FRL–9481–8] RIN 1545–BK16 RIN 2060–AP76 Tax Return Preparer Penalties Under Section 6695; Correction Oil and Natural Gas Sector: New Source Performance Standards and National Emission Standards for Hazardous Air Pollutants Reviews; Correction of Comment Period Closing Date Internal Revenue Service (IRS), Treasury. ACTION: Correction to notice of proposed rulemaking and notice of public hearing. AGENCY: This document contains a correction to a notice of proposed rulemaking and notice of public hearing (REG–140280–09) that would modify existing regulations related to the tax return preparer penalties under section 6695 of the Internal Revenue Code. The document was published in the Federal Register on Tuesday, October 11, 2011 (76 FR 62689). FOR FURTHER INFORMATION CONTACT: Concerning these proposed regulations, Spence Hanemann, (202) 622–4940 (not a toll-free number). SUPPLEMENTARY INFORMATION: SUMMARY: Background The correction notice that is the subject of this document is under section 6695 of the Internal Revenue Code. Need for Correction As published, a notice of proposed rulemaking and notice of public hearing (REG–140280–09) contains an error that may prove to be misleading and is in need of clarification. Correction of Publication Accordingly, the publication of a notice of proposed rulemaking and notice of public hearing (REG–140280– 09), which was the subject of FR Doc. 2011–26247, is corrected as follows: On page 62690, column 2, in the preamble, under the paragraph heading ‘‘Explanation of Provisions’’, first paragraph of the column, line 17, the language ‘‘proposed § 1.6695–2(c)(2) provides that,’’ is removed and is replaced with the new language ‘‘proposed § 1.6695–2(c)(3) provides that,’’. LaNita Van Dyke, Chief, Publications and Regulations Branch, Legal Processing Division, Associate Chief Counsel (Procedure and Administration). [FR Doc. 2011–27183 Filed 10–19–11; 8:45 am] BILLING CODE 4830–01–P VerDate Mar<15>2010 15:27 Oct 19, 2011 Jkt 226001 ENVIRONMENTAL PROTECTION AGENCY PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Environmental Protection Agency (EPA). ACTION: Proposed rule; correction of public comment period closing date. AGENCY: The EPA is announcing that the period for providing public comments on the August 23, 2011, ‘‘Oil and Natural Gas Sector: New Source Performance Standards and National Emission Standards for Hazardous Air Pollutants Reviews,’’ closes on October 31, 2011. This notice does not address the requests the EPA has received for extending this period. DATES: Comments. The public comment period for the proposed rules published on August 23, 2011 (76 FR 52738) closes on October 31, 2011. ADDRESSES: Comments. Written comments on the proposed rules may be submitted to the EPA electronically, by mail, by facsimile or through hand delivery/courier. Please refer to the proposal for the addresses and detailed instructions. Docket. Publicly available documents relevant to this action are available for public inspection either electronically in https://www.regulations.gov, or in hard copy at the EPA Docket Center, Room 3334, 1301 Constitution Avenue, NW., Washington, DC. The Public Reading Room is open from 8:30 a.m. to 4:30 p.m., Monday through Friday, excluding legal holidays. A reasonable fee may be charged for copying. World Wide Web. The EPA Web site for this rulemaking is located at: https:// www.epa.gov/airquality/oilandgas.html. FOR FURTHER INFORMATION CONTACT: Mr. Bruce Moore, Fuels and Incineration Group (E143–05), Sector Policies and Programs Division, Office of Air Quality Planning and Standards, U.S. Environmental Protection Agency, Research Triangle Park, North Carolina 27711; Telephone number: (919) 541– 5460; Fax number (919) 541–3470; Email address: moore.bruce@epa.gov. SUPPLEMENTARY INFORMATION: SUMMARY: E:\FR\FM\20OCP1.SGM 20OCP1

Agencies

[Federal Register Volume 76, Number 203 (Thursday, October 20, 2011)]
[Proposed Rules]
[Pages 65136-65138]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-27069]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 76, No. 203 / Thursday, October 20, 2011 / 
Proposed Rules

[[Page 65136]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0562; Directorate Identifier 2009-NE-29-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc (RR) Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to all RR model RB211-524G2-T-19, -524G3-T-19, -524H-
T-36, and -524H2-T-19; and RB211-Trent 553-61, 553A2-61, 556-61, 556A2-
61, 556B-61, 556B2-61, 560-61, 560A2-61; RB211-Trent 768-60, 772-60, 
772B-60; and RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-
17, and 895-17 turbofan engines that have a high-pressure (HP) 
compressor stage 1 to 4 rotor disc with a part number (P/N) listed in 
Table 1 of this proposed AD. The existing AD currently requires 
repetitive inspections of the axial dovetail slots, and follow-on 
corrective action depending on findings. Since we issued that AD, we 
determined that the definition of shop visit is too restrictive in the 
existing AD. This proposed AD would continue to require those 
repetitive inspections and follow-on corrective actions, and it would 
change the definition of a shop visit to be less restrictive. We are 
proposing this AD to detect cracks in the HP compressor stage 1 and 2 
disc posts, which could result in failure of the disc post and HP 
compressor blades, release of uncontained engine debris, and damage to 
the airplane.

DATES: We must receive comments on this proposed AD by December 19, 
2011.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Rolls-Royce 
plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; 
phone: 011-44-1332-242424; fax: 011-44-1332-245418 or e-mail from 
https://www.rolls-royce.com/contact/civil_team.jsp, or download the 
publication from https://www.aeromanager.com. You may review copies of 
the referenced service information at the FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA. For 
information on the availability of this material at the FAA, call 781-
238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
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 Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Alan Strom, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7143; fax: 
781-238-7199; e-mail: alan.strom@faa.gov.

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-2010-0562; 
Directorate Identifier 2009-NE-29-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 because of 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 we 
receive about this proposed AD.

Discussion

    On April 12, 2011, we issued AD 2011-09-07, Amendment 39-16669 (76 
FR 24793, May 3, 2011), for all RR model RB211-524G2-T-19, -524G3-T-19, 
-524H-T-36, and -524H2-T-19; and RB211 Trent 553-61, 553A2-61, 556-61, 
556A2-61, 556B-61, 556B2-61, 560-61, 560A2-61; RB211 Trent 768-60, 772-
60, 772B-60; and RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 
892B-17, and 895-17 turbofan engines. That AD requires initial and 
repetitive fluorescent penetrant inspections of the HP compressor stage 
1 to 4 rotor discs at the first shop visit after accumulating 1,000 
cycles-since-new on the stage 1 to 4 rotor discs or at the next shop 
visit after the effective date of that AD, which ever occurs later. 
That AD also requires repetitive inspections at every shop visit. That 
AD resulted from findings of anomalies at the corners of the disc posts 
during manufacture of stage 1 and stage 2 discs with axial dovetails 
slots. We issued that AD to detect cracks in the HP compressor stage 1 
and stage 2 disc posts, which could result in failure of the disc post 
and release of HP compressor blades, release of uncontained engine 
debris, and damage to the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2011-09-07, Amendment 39-16669 (76 FR 24793, May 
3, 2011), we found that the definition of ``shop visit'' in the AD is 
too restrictive, in that it would require operators to inspect more 
often than required to ensure safety. We also found that Alert Service 
Bulletin (ASB) No. RB.211-72-AF964, Revision 2, dated June 8, 2011, 
also may be appropriate to

[[Page 65137]]

the corrective action in that AD, as is ASB No. RB.211-72-AF964, 
Revision 1, dated June 6, 2008 which is referenced in AD 2011-09-07.

Relevant Service Information

    We reviewed RR ASB No. RB.211-72-AF964, Revision 1, dated June 6, 
2008, and Revision 2, dated June 8, 2011. The ASB describes procedures 
for cleaning and inspecting the axial dovetail slots.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the definition of shop visit was too 
restrictive, and that the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs.

Proposed AD Requirements

    This proposed AD would change the definition of a shop visit in AD 
2011-09-07 to ``whenever all compressor blades are removed from the HP 
compressor drum.'' This proposed AD would also allow using ASB No. 
RB.211-72-AF964, Revision 1, dated June 6, 2008, or ASB No. RB.211-72-
AF964, Revision 2, dated June 8, 2011, to perform the inspection.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 371 products of U.S. registry. We also estimate that 
it would take about 20 work-hours per product to comply with this AD. 
The average labor rate is $85 per work-hour. No parts would be required 
per product. Based on these figures, we estimate the cost of the AD on 
U.S. operators to be $630,700.

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 have 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 that the 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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 removing airworthiness directive 
(AD) 2011-09-07, Amendment 39-166679 (76 FR 24793, May 3, 2011), and 
adding the following new AD:

Rolls-Royce plc: Docket No. FAA-2010-0562; Directorate Identifier 
2009-NE-29-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by December 19, 
2011.

(b) Affected ADs

    This AD supersedes AD 2011-09-07, Amendment 39-16669 (76 FR 
24793, May 3, 2011).

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) model RB211-524G2-T-19, 
-524G3-T-19, -524H-T-36, and -524H2-T-19; and RB211-Trent 553-61, 
553A2-61, 556-61, 556A2-61, 556B-61 556B2-61, 560-61, 560A2-61; 
RB211-Trent 768-60, 772-60, 772B-60; and RB211-Trent 875-17, 877-17, 
884-17, 884B-17, 892-17, 892B-17, and 895-17 turbofan engines that 
have a high-pressure (HP) compressor stage 1 to 4 rotor disc with a 
part number (P/N) listed in Table 1 of this AD.

                  Table 1--Affected HP Compressor Stage 1 to 4 Rotor Disc P/Ns by Engine Model
----------------------------------------------------------------------------------------------------------------
                   Engine model                              HP compressor stage 1 to 4 rotor disc P/N
----------------------------------------------------------------------------------------------------------------
(1) RB211-524G2-T-19, -524G3-T-19, -524H-T-36,     FW20195, FK25502, or FW23711.
 and -524H2-T-19.
(2) RB211 Trent 553-61, 553A2-61, 556-61, 556A2-   FK30524.
 61, 556B-61, 556B2-61, 560-61, and 560A2[dash]61.
(3) RB211 Trent 768-60, 772-60, and 772B-60......  FK22745, FK24031, FK26185, FK23313, FK25502, FK32129,
                                                    FW20195, FW20196, FW20197, FW20638, or FW23711.
(4) RB211 Trent 875-17, 877-17, 884-17, 884B-17,   FK24009, FK26167, FK32580, FW11590, or FW61622.
 892[dash]17, 892B-17, and 895-17.
----------------------------------------------------------------------------------------------------------------

(d) Unsafe Condition

    This AD was prompted by our determination that the definition of 
``shop visit'' in the existing AD is too restrictive, in that it 
would require operators to inspect more often than required to 
ensure safety. We are issuing this AD to detect cracks in the HP 
compressor stage 1 and 2 disc posts, which could result in failure 
of the disc post and HP compressor blades, release of uncontained 
engine debris, and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

[[Page 65138]]

(f) Cleaning and Inspection

    (1) Clean and perform a fluorescent penetrant inspection of the 
HP compressor stage 1 to 4 rotor discs at the first shop visit after 
accumulating 1,000 cycles since new on the stage 1 to 4 rotor discs 
or at the next shop visit after the effective date of this AD, which 
ever occurs later.
    (2) Use paragraph 3.A through 3.E.(11) of the Accomplishment 
Instructions of Rolls-Royce Alert Service Bulletin (ASB) No. RB.211-
72-AF964, Revision 1, dated June 6, 2008, or ASB No. RB.211-72-
AF964, Revision 2, dated June 8, 2011, to do the inspections.
    (3) Thereafter at every engine shop visit, perform the 
inspection specified by paragraph (f) of this AD.

(g) Definition

    For the purpose of this AD, an ``engine shop visit'' is whenever 
all compressor blades are removed from the HP compressor drum.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(i) Related Information

    (1) For more information about this AD, contact Alan Strom, 
Aerospace Engineer, Engine Certification Office, FAA, Engine and 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7143; fax: 781-238-7199; e-mail: 
alan.strom@faa.gov.
    (2) See European Aviation Safety Agency Airworthiness Directive 
2011-0073R1, dated April 8, 2009, for related information.
    (3) For service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, 
England, DE248BJ; phone: 011-44-1332-242424; fax: 011-44-1332-245418 
or e-mail from https://www.rolls-royce.com/contact/civil_team.jsp, 
or download the publication from https://www.aeromanager.com. You 
may review copies at the FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA. For information on the 
availability of this material at the FAA, call 781-238-7125.

    Issued in Burlington, Massachusetts, on October 14, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-27069 Filed 10-19-11; 8:45 am]
BILLING CODE 4910-13-P

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