Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 75831-75833 [2012-30650]

Download as PDF Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Renton, Washington, on December 5, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–30305 Filed 12–21–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1198; Directorate Identifier 2012–NE–35–AD; Amendment 39– 17289; AD 2012–25–08] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: tkelley on DSK3SPTVN1PROD with Examining the AD Docket We are adopting a new airworthiness directive (AD) for certain serial numbers (S/Ns) of Rolls-Royce plc (RR) RB211-Trent 768–60, 772–60, and 772B–60 turbofan engines. This AD requires initial and repetitive on-wing or in-shop inspections of the high pressure/intermediate pressure (HP/IP) turbine bearing support oil feed tube outer heat shield. This AD also requires installation of a revised HP/IP turbine bearing support structure as terminating action to the repetitive inspections of the HP/IP turbine bearing support oil feed tube outer heat shield. This AD was prompted by a report of high oil consumption due to an oil leak from the HP/IP turbine bearing support oil feed tube. We are issuing this AD to prevent failure of the HP turbine disc, uncontained engine failure, and damage to the airplane. DATES: This AD becomes effective January 10, 2013. We must receive comments on this AD by February 11, 2013. The Director of the Federal Register approved the incorporation by reference of a certain publication as of January 10, 2013. The Director of the Federal Register approved the incorporation by reference of certain other publications as of December 14, 2007 (72 FR 67568, November 29, 2007). SUMMARY: VerDate Mar<15>2010 04:58 Dec 22, 2012 Jkt 229001 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: 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. 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 email: https:// www.rolls-royce.com/contact/ civil_team.jsp. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238– 7125. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (phone: 800–647–5527) is 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: Robert Morlath, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238 7154; fax: 781–238 7199; email: robert.c.morlath@faa.gov. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2012– 0201, dated September 26, 2012 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: In August 2011, a Trent 700 engine was removed for high oil consumption, which was found to have been caused by a small hole in the oil feed tube of the High Pressure/ PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 75831 Intermediate Pressure (HP/IP) Bearing Support. The hole was the result of frettage (chafing) with a fractured outer heat shield. This is a known problem and recognized unsafe condition that has re-emerged having been previously addressed by EASA AD 2007–0260R1. Investigation by RR revealed a build error that, in contradiction to the build records, the previous configuration of outer heat shield (Pre-Service Bulletin (SB) 72–F117 standard) was fitted on the oil feed tube service pipe of the HP/IP structure. As the build error may have been reproduced several times, it is assumed that further post-SB 72–F117 standard structures may be in service with pre-SB 72–F117 outer heat shields fitted to the oil feed tube. The frettage on the oil feed tube within the HP/IP turbine bearings support structure results from contact with the fracture edges of the tubes outermost heat shield, which has been found to fracture under thermal cycling and then to chafe against the oil tube with the potential to cause holes and consequent oil leaks. You may obtain further information by examining the MCAI in the AD docket. On November 20, 2007, we issued AD 2007–24–09 (72 FR 67568, November 29, 2007) which corresponds with EASA AD 2007–0260R1. Our AD has a mandatory terminating action date of May 31, 2010, however, there were, and currently are, no U.S. operators of the engines affected by those ADs. Those ADs are only applicable to engines that do not incorporate Modification Standard 72–F117. Since those ADs were issued, EASA has issued AD 2012– 0201 that is applicable to a specific set of engines that may have had Modification Standard 72–F117 incorporated incorrectly. EASA did not supersede EASA AD 2007–0260R1 with EASA AD 2012–0201 because EASA AD 2012–0201 only affects a very specific population of engines that, having incorporated Modification Standard 72– F117, either correctly or incorrectly, are no longer affected by EASA AD 2007– 0260R1. We are issuing our AD as a standalone document for the same reasons. This new AD also is applicable only to the engines specified in the MCAI, none of which are currently registered to U.S. operators. Also, this new AD lists certain service bulletins that were previously incorporated by reference in AD 2007–24–09. Relevant Service Information RR has issued Alert Service Bulletin No. RB.211–72–AG873, dated February 27, 2012. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. E:\FR\FM\26DER1.SGM 26DER1 75832 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations FAA’s Determination and Requirements of This AD This product has been approved by the United Kingdom and is approved for operation in the United States. Pursuant to our bilateral agreement with the European Community, EASA has notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing 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. FAA’s Determination of the Effective Date No domestic operators use any of the RB211-Trent 768–60, 772–60, and 772B–60 turbofan engines listed by S/N in this AD. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2012–1198; Directorate Identifier 2012–NE–35–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 with FAA personnel concerning this 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). 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. 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. List of Subjects in 14 CFR Part 39 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: Air transportation, Aircraft, Aviation safety, Incorporation by reference, 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: ■ 2012–25–08 Rolls-Royce plc: Amendment 39–17289; Docket No. FAA–2012–1198; Directorate Identifier 2012–NE–35–AD. (a) Effective Date This airworthiness directive (AD) becomes effective January 10, 2013. (b) Affected ADs None. (c) Applicability This AD applies to Rolls-Royce plc (RR) RB211 Trent 768–60, 772–60, and 772B–60 turbofan engines with serial numbers (S/Ns) listed in Table 1 to paragraph (c) of this AD. TABLE 1 TO PARAGRAPH (C)—AFFECTED ENGINE S/NS 41221 41425 41428 41430 41431 41432 41435 41437 41438 41440 41442 41445 41446 41451 41452 41454 41455 41456 tkelley on DSK3SPTVN1PROD with (d) Reason (e) Actions and Compliance This AD was prompted by a report of high oil consumption due to an oil leak from the high pressure/intermediate pressure (HP/IP) turbine bearing support oil feed tube. We are issuing this AD to prevent a failure of the HP turbine disc, uncontained engine failure, and damage to the airplane. Unless already done, do the following actions. VerDate Mar<15>2010 04:58 Dec 22, 2012 Jkt 229001 (f) Initial Inspection (1) Initially inspect the HP/IP turbine bearing support oil feed tube within the compliance times specified in paragraphs PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 41459 41460 41461 41462 41463 41464 41465 41466 41468 41469 41470 41471 1.D.(1)(a) through 1.D.(1)(a)(ii) of RR Alert Service Bulletin (ASB) No. RB.211–72– AG873, dated February 27, 2012. Perform the initial inspection in accordance with paragraphs 3.A (1)(a) through 3.A (1)(j) of RR ASB No. RB.211–72–AG873, dated February 27, 2012. E:\FR\FM\26DER1.SGM 26DER1 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations (2) If the HP/IP turbine bearing support oil feed tube outer heat shield is not present, accept the module as compliant. No further action is required. DEPARTMENT OF TRANSPORTATION (h) Mandatory Terminating Action As mandatory terminating action to the repetitive inspections required by this AD, install a revised HP/IP turbine bearing support structure, at the next 05 Module overhaul after the effective date of this AD, in accordance with either: (1) Sections 3.B (1)(a) through 3.B (1)(f) of RR Service Bulletin (SB) No. RB.211–72– F117, Revision 2, dated September 25, 2006; or (2) Sections 3.B (1)(a) through 3.B (1)(e) and 3.B (2)(a) of RR SB No. RB.211–72–F227, Revision 1, dated October 8, 2007. (i) Definition For the purpose of this AD, ‘‘next 05 Module overhaul’’ is any time that the HP/ IP turbine internal oil tubes have been exposed and the HP/IP turbine bearing support oil feed tube heat shields are subjected to visual inspection. tkelley on DSK3SPTVN1PROD with (k) Related Information (1) For more information about this AD, contact Robert Morlath, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238 7154; fax: 781–238 7199; email: robert.c.morlath@faa.gov. (2) Refer to European Aviation Safety Agency AD 2012–0201, dated September 26, 2012, for related information. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Rolls-Royce plc Alert Service Bulletin No. RB.211–72–AG873, dated February 27, 2012, approved for IBR January 10, 2013. (ii) Reserved. (3) The following service information was approved for IBR on December 14, 2007 (72 FR 67568, November 29, 2007). (i) Rolls-Royce plc Service Bulletin No. RB.211–72–F117, Revision 2, dated September 25, 2006. (ii) Rolls-Royce plc Service Bulletin No. RB.211–72–F227, Revision 1, dated October 8, 2007. Jkt 229001 Discussion Issued in Burlington, Massachusetts, on December 4, 2012. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2012–30650 Filed 12–21–12; 8:45 am] BILLING CODE 4910–13–P 14 CFR Part 39 (j) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. 04:58 Dec 22, 2012 This AD becomes effective January 30, 2013. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 30, 2013. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of April 15, 2010 (75 FR 11435, March 11, 2010). ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Federal Aviation Administration (g) Repetitive Inspections If the HP/IP turbine bearing support oil feed tube outer heat shield is present, perform repetitive inspections of the HP/IP turbine bearing support oil feed tube, in accordance with paragraphs 3.A (2)(b) through 3.A (2)(f) of RR ASB No. RB.211–72– AG873, dated February 27, 2012. VerDate Mar<15>2010 (4) 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 email: https://www.rolls-royce.com/contact/ civil_team.jsp. (5) You may view this 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. (6) You may view this service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. 75833 [Docket No. FAA–2012–0858; Directorate Identifier 2011–NM–183–AD; Amendment 39–17287; AD 2012–25–06] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for certain Airbus Model A300 B4–2C, B4– 103, and B4–203 airplanes; and Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, and B4–622R airplanes. That AD currently requires performing a onetime detailed visual inspection of the forward fitting at frame (FR) 40 on both sides of the airplane for cracks, and repair if necessary. This new AD requires repetitive detailed inspections of the forward fitting at FR 40 without nut removal, and a one-time eddy current or liquid penetrant inspection of the forward fitting at FR 40 with nut removal, and repair if necessary. This AD was prompted by reports that new cracks were found in the FR 40 forward fitting. We are issuing this AD to detect and correct cracking of the FR 40 forward fitting, which could result in a deterioration of the structural integrity of the frame. SUMMARY: PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 DATES: 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 August 27, 2012 (77 FR 51717), and proposed to supersede AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010). That NPRM proposed to correct an unsafe condition for the specified products. The Mandatory Continuing Airworthiness Information (MCAI) states: One A300–600 aeroplane operator reported that, during a routine inspection, a crack was found in the right hand frame (FR) 40 forward fitting between stringer 32 and stringer 33. The subject aeroplane had previously been modified in accordance with Airbus SB A300–57–6053 (Mod. 10453). Therefore and pending completion of the full analysis using a refined Finite Element Model, EASA [European Aviation Safety Agency] issued AD 2009–0094 [which corresponds with FAA AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)] to require a one-time Detailed Visual Inspection (DVI) of the post-SB A300– 57–6053 A300–600 aeroplanes and post-SB A300–53–0297 A300 aeroplanes in order to ensure the structural integrity of frame 40. During a recent maintenance check, on two aeroplanes (one A300B4 and one A300–600), cracks were found in the FR 40 forward fitting. These new crack findings are considered as unexpected, since they were found after: —Application of modification SB A300–57– 6053 or SB A300–53–0297 which cancels the inspection programme, and —Accomplishment of EASA AD 2009–0094. E:\FR\FM\26DER1.SGM 26DER1

Agencies

[Federal Register Volume 77, Number 247 (Wednesday, December 26, 2012)]
[Rules and Regulations]
[Pages 75831-75833]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-30650]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1198; Directorate Identifier 2012-NE-35-AD; 
Amendment 39-17289; AD 2012-25-08]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
serial numbers (S/Ns) of Rolls-Royce plc (RR) RB211-Trent 768-60, 772-
60, and 772B-60 turbofan engines. This AD requires initial and 
repetitive on-wing or in-shop inspections of the high pressure/
intermediate pressure (HP/IP) turbine bearing support oil feed tube 
outer heat shield. This AD also requires installation of a revised HP/
IP turbine bearing support structure as terminating action to the 
repetitive inspections of the HP/IP turbine bearing support oil feed 
tube outer heat shield. This AD was prompted by a report of high oil 
consumption due to an oil leak from the HP/IP turbine bearing support 
oil feed tube. We are issuing this AD to prevent failure of the HP 
turbine disc, uncontained engine failure, and damage to the airplane.

DATES: This AD becomes effective January 10, 2013.
    We must receive comments on this AD by February 11, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication as of January 10, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications as of December 14, 2007 (72 FR 
67568, November 29, 2007).

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: 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.
    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 email: https://www.rolls-royce.com/contact/civil_team.jsp. You may view this service 
information at the FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803. 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 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 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: Robert Morlath, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238 7154; 
fax: 781-238 7199; email: robert.c.morlath@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2012-0201, dated September 26, 2012 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    In August 2011, a Trent 700 engine was removed for high oil 
consumption, which was found to have been caused by a small hole in 
the oil feed tube of the High Pressure/Intermediate Pressure (HP/IP) 
Bearing Support. The hole was the result of frettage (chafing) with 
a fractured outer heat shield. This is a known problem and 
recognized unsafe condition that has re-emerged having been 
previously addressed by EASA AD 2007-0260R1.
    Investigation by RR revealed a build error that, in 
contradiction to the build records, the previous configuration of 
outer heat shield (Pre-Service Bulletin (SB) 72-F117 standard) was 
fitted on the oil feed tube service pipe of the HP/IP structure. As 
the build error may have been reproduced several times, it is 
assumed that further post-SB 72-F117 standard structures may be in 
service with pre-SB 72-F117 outer heat shields fitted to the oil 
feed tube.
    The frettage on the oil feed tube within the HP/IP turbine 
bearings support structure results from contact with the fracture 
edges of the tubes outermost heat shield, which has been found to 
fracture under thermal cycling and then to chafe against the oil 
tube with the potential to cause holes and consequent oil leaks.

    You may obtain further information by examining the MCAI in the AD 
docket.
    On November 20, 2007, we issued AD 2007-24-09 (72 FR 67568, 
November 29, 2007) which corresponds with EASA AD 2007-0260R1. Our AD 
has a mandatory terminating action date of May 31, 2010, however, there 
were, and currently are, no U.S. operators of the engines affected by 
those ADs. Those ADs are only applicable to engines that do not 
incorporate Modification Standard 72-F117. Since those ADs were issued, 
EASA has issued AD 2012-0201 that is applicable to a specific set of 
engines that may have had Modification Standard 72-F117 incorporated 
incorrectly. EASA did not supersede EASA AD 2007-0260R1 with EASA AD 
2012-0201 because EASA AD 2012-0201 only affects a very specific 
population of engines that, having incorporated Modification Standard 
72-F117, either correctly or incorrectly, are no longer affected by 
EASA AD 2007-0260R1. We are issuing our AD as a standalone document for 
the same reasons. This new AD also is applicable only to the engines 
specified in the MCAI, none of which are currently registered to U.S. 
operators. Also, this new AD lists certain service bulletins that were 
previously incorporated by reference in AD 2007-24-09.

Relevant Service Information

    RR has issued Alert Service Bulletin No. RB.211-72-AG873, dated 
February 27, 2012. The actions described in this service information 
are intended to correct the unsafe condition identified in the MCAI.

[[Page 75832]]

FAA's Determination and Requirements of This AD

    This product has been approved by the United Kingdom and is 
approved for operation in the United States. Pursuant to our bilateral 
agreement with the European Community, EASA has notified us of the 
unsafe condition described in the MCAI and service information 
referenced above. We are issuing 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.

FAA's Determination of the Effective Date

    No domestic operators use any of the RB211-Trent 768-60, 772-60, 
and 772B-60 turbofan engines listed by S/N in this AD. Therefore, we 
find that notice and opportunity for prior public comment are 
unnecessary and that good cause exists for making this amendment 
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2012-1198; Directorate 
Identifier 2012-NE-35-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this 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 
with FAA personnel concerning this 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).

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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

2012-25-08 Rolls-Royce plc: Amendment 39-17289; Docket No. FAA-2012-
1198; Directorate Identifier 2012-NE-35-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective January 10, 
2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211 Trent 768-60, 772-
60, and 772B-60 turbofan engines with serial numbers (S/Ns) listed 
in Table 1 to paragraph (c) of this AD.

             Table 1 to Paragraph (c)--Affected Engine S/Ns
------------------------------------------------------------------------
 
------------------------------------------------------------------------
     41221          41435          41446          41459          41465
     41425          41437          41451          41460          41466
     41428          41438          41452          41461          41468
     41430          41440          41454          41462          41469
     41431          41442          41455          41463          41470
     41432          41445          41456          41464          41471
------------------------------------------------------------------------

(d) Reason

    This AD was prompted by a report of high oil consumption due to 
an oil leak from the high pressure/intermediate pressure (HP/IP) 
turbine bearing support oil feed tube. We are issuing this AD to 
prevent a failure of the HP turbine disc, uncontained engine 
failure, and damage to the airplane.

(e) Actions and Compliance

    Unless already done, do the following actions.

(f) Initial Inspection

    (1) Initially inspect the HP/IP turbine bearing support oil feed 
tube within the compliance times specified in paragraphs 1.D.(1)(a) 
through 1.D.(1)(a)(ii) of RR Alert Service Bulletin (ASB) No. 
RB.211-72-AG873, dated February 27, 2012. Perform the initial 
inspection in accordance with paragraphs 3.A (1)(a) through 3.A 
(1)(j) of RR ASB No. RB.211-72-AG873, dated February 27, 2012.

[[Page 75833]]

    (2) If the HP/IP turbine bearing support oil feed tube outer 
heat shield is not present, accept the module as compliant. No 
further action is required.

(g) Repetitive Inspections

    If the HP/IP turbine bearing support oil feed tube outer heat 
shield is present, perform repetitive inspections of the HP/IP 
turbine bearing support oil feed tube, in accordance with paragraphs 
3.A (2)(b) through 3.A (2)(f) of RR ASB No. RB.211-72-AG873, dated 
February 27, 2012.

(h) Mandatory Terminating Action

    As mandatory terminating action to the repetitive inspections 
required by this AD, install a revised HP/IP turbine bearing support 
structure, at the next 05 Module overhaul after the effective date 
of this AD, in accordance with either:
    (1) Sections 3.B (1)(a) through 3.B (1)(f) of RR Service 
Bulletin (SB) No. RB.211-72-F117, Revision 2, dated September 25, 
2006; or
    (2) Sections 3.B (1)(a) through 3.B (1)(e) and 3.B (2)(a) of RR 
SB No. RB.211-72-F227, Revision 1, dated October 8, 2007.

(i) Definition

    For the purpose of this AD, ``next 05 Module overhaul'' is any 
time that the HP/IP turbine internal oil tubes have been exposed and 
the HP/IP turbine bearing support oil feed tube heat shields are 
subjected to visual inspection.

(j) Alternative Methods of Compliance (AMOCs)

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

(k) Related Information

    (1) For more information about this AD, contact Robert Morlath, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238 7154; fax: 781-238 7199; email: 
robert.c.morlath@faa.gov.
    (2) Refer to European Aviation Safety Agency AD 2012-0201, dated 
September 26, 2012, for related information.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Rolls-Royce plc Alert Service Bulletin No. RB.211-72-AG873, 
dated February 27, 2012, approved for IBR January 10, 2013.
    (ii) Reserved.
    (3) The following service information was approved for IBR on 
December 14, 2007 (72 FR 67568, November 29, 2007).
    (i) Rolls-Royce plc Service Bulletin No. RB.211-72-F117, 
Revision 2, dated September 25, 2006.
    (ii) Rolls-Royce plc Service Bulletin No. RB.211-72-F227, 
Revision 1, dated October 8, 2007.
    (4) 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 email: https://www.rolls-royce.com/contact/civil_team.jsp.
    (5) You may view this 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.
    (6) You may view this service information at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on December 4, 2012.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2012-30650 Filed 12-21-12; 8:45 am]
BILLING CODE 4910-13-P
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