Airworthiness Directives; Rolls-Royce plc RB211-524 Series, RB211-Trent 700 Series, and RB211-Trent 800 Series Turbofan Engines, 65941-65944 [2011-27513]

Download as PDF Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Rules and Regulations required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus SAS–EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet: http:// www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (4) You may also review copies of the service information that is incorporated by 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: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on October 13, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–27393 Filed 10–24–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0993; Directorate Identifier 2010–NE–08–AD; Amendment 39– 16849; AD 2011–22–07] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211–524 Series, RB211–Trent 700 Series, and RB211–Trent 800 Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: erowe on DSK2VPTVN1PROD with RULES SUMMARY: Cracking has been found on the inner wall between intermediate dilution chutes on a total of five front combustion liners of the standard corresponding to Rolls-Royce VerDate Mar<15>2010 15:13 Oct 24, 2011 Jkt 226001 RB211 Service Bulletin No. 72–D133. The lives of two of these liners were confirmed to be below the currently valid borescope inspection interval. Ultimately, crack propagation could result in hot gas breakout with potential of downstream component distress and multiple turbine blade release beyond containment capabilities of the engine casings. Thus, cracking of this nature constitutes a potentially unsafe condition. Since Rolls-Royce Service Bulletin No. 72– E902 introduces further developments of Rolls-Royce RB211 Service Bulletin No. 72– D133, engines incorporating Rolls-Royce RB211 Service Bulletin No. 72–E902 are also considered to be potentially affected and are therefore included in the applicability of this AD. We are issuing this AD to detect cracks in the front combustion liner, which could result in hot section distress, multiple blade release, and possible damage to the airplane. DATES: This AD becomes effective November 29, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 29, 2011. ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; phone: 781– 238–7143; fax: 781–238–7199. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on October 5, 2010 (75 FR 61363). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that: Cracking has been found on the inner wall between intermediate dilution chutes on a total of five front combustion liners of the standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72–D133. The lives of two of these liners were confirmed to be below the currently valid borescope inspection interval. Ultimately, crack propagation could result in hot gas breakout with potential of downstream component distress and multiple turbine blade release beyond containment capabilities of the engine casings. Thus, cracking of this nature constitutes a potentially unsafe condition. Since Rolls-Royce Service Bulletin No. 72– E902 introduces further developments of PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 65941 Rolls-Royce RB211 Service Bulletin No. 72– D133, engines incorporating Rolls-Royce RB211 Service Bulletin No. 72–E902 are also considered to be potentially affected and are therefore included in the applicability of this AD. This AD requires a change to the initial and repeat borescope inspection intervals for the front combustion liner. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. Request To Expand Address for Service Information One commenter, Rolls-Royce plc (RR), asked us to consider changing the information for getting the service information to ‘‘For any questions concerning the technical content of the requirements in this AD (NPRM), please contact your designated Rolls-Royce representative for a copy of the service information, please download the publication from your Aeromanager account at http:// www.aeromanager.com. If you do not have a designated representative or an Aeromanager account, please contact Corporate Communications at RollsRoyce plc, PO Box 31, Derby, DE24 8BJ, United Kingdom, phone: 011–44–1331– 242424, fax: 011–44–1332–249936, or e-mail: http://www.rolls-royce.com/ contact/civil_team.jsp identifying the correspondence as being related to Airworthiness Directives.’’ RR states that this should make sure that any questions from operators of their engines and those from other parties are directed to the area best equipped to answer. We partially agree. We agree that operators and maintenance providers need to get timely and accurate service information, and that additional information is worth including. We changed paragraph (k) of the AD to state ‘‘* * * contact Corporate Communications at Rolls-Royce plc PO Box 31, Derby, DE24 8BJ, United Kingdom, Phone: 011–44–1331–242424, fax 011–44–1332–249936 or e-mail from http://www.rolls-royce.com/contact/ civil_team.jsp identifying the correspondence as being related to Airworthiness Directives.’’ We do not agree that operators or maintenance providers should contact RR for questions about this AD. We did not include that information in the AD. Requests To Change References to the Service Bulletin That Is Incorporated by Reference Two commenters, American Airlines (AA) and The Boeing Company (Boeing), asked us to add ‘‘or later E:\FR\FM\25OCR1.SGM 25OCR1 65942 Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Rules and Regulations this AD to reflect six known cracking events. Request To Remove an Engine Model From the Applicability One commenter, AA, asked us to remove the RR RB211–535 engine model from the applicability of the proposed AD. AA stated they have recorded no crack findings against the RB211–535 model. We agree. The thermal, acoustical, and vibratory stress environment of the RB211–535 combustion liner is different from that of the other engines to which this AD applies. We removed the RB211–535E4–37, RB211–535E4–B–37, RB211–535E4–C–37, and RB211– 535E4–B–75 from the Applicability paragraph (c) of this AD, and updated our cost estimate to reflect the fewer affected engines. erowe on DSK2VPTVN1PROD with RULES revision’’ after ‘‘Service Bulletin No. RB.211–72–AF458, Revision 2, dated December 21, 2007.’’ Boeing stated the latest revision of Service Bulletin (SB) No. RB.211–72–AF458 is Revision 4. Boeing stated that airlines have been inspecting their combustion liners to Revision 4 of the SB and the compliance intervals specified in the NPRM are consistent with RR SB RB.211–72– AF458, Revision 4 and EASA AD 2009– 0243R1. AA stated the borescope inspection is the same on later revisions, so the life should be counted from the latest SB revision. We do not agree. On review of the SB, we determined that the inspection requirements and limits called out in the SB are already in the engine and aircraft maintenance manuals. We changed the AD to remove the incorporation by reference of the SB. One commenter, AA, asked us to revise paragraph (f) of the AD to specifically call out which paragraphs of SB RB.211–72–AF458 are incorporated by reference. AA stated the NPRM called out all of section 3 of the SB, which is too prescriptive given the nature of the inspections. We do not agree. On review of the SB, we found incorporation by reference unnecessary. We changed the AD to remove the incorporation by reference of the SB. We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Request To Change the Number of Cracking Events One commenter, Boeing, asked us to change paragraph (d) of the proposed AD to specify that six cracking events have been found instead of five. Boeing states that changing paragraph (d) of the proposed AD will more accurately reflect the need for the inspections. We agree. Although an additional cracking event has occurred, the AD was prompted by the investigation of five events. We changed paragraph (d) of VerDate Mar<15>2010 15:13 Oct 24, 2011 Jkt 226001 Request To Add a Grace Period for Compliance One commenter, Boeing asked us to change paragraphs (f)(1)(i) and (f)(1)(iii) of the proposed AD to add ‘‘within 15 cycles of the date of issue of the AD’’ before the word ‘‘or.’’ Boeing states that adding the 15 cycle grace period will give operators time to get back to base for the inspection. We partially agree. No additional grace period is required. This AD does not require inspecting any engine earlier than 250 cycles after the effective date of the AD. We clarified the wording of paragraph (f) to make this clearer. Statement of the Possibility of Cost and Operational Impact Increasing One commenter, Federal Express, stated that cost and operational impact could increase if certain RB211–535 models are added to the applicability of the proposed AD. The commenter provided no reason for its statement. We agree. However, additional engine models are not being added, and we are specifically excluding the RB211–535 engine in response to another comment. We did not change the AD in response to this comment. Conclusion Costs of Compliance Based on the service information, we estimate that this AD will affect about 46 products of U.S. registry. We also estimate that it will take about 1.5 workhours per product to comply with this AD. The average labor rate is $85 per work-hour. No parts are required so parts will cost $0 per product. Based on these figures, we estimate the cost of the AD on U.S. operators to be $5,865. 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, PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 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), 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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (phone: (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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: E:\FR\FM\25OCR1.SGM 25OCR1 Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Rules and Regulations Reason 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 65943 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: 2011–22–07 Rolls-Royce: Amendment 39– 16849. Docket No. FAA–2010–0993; Directorate Identifier 2010–NE–08–AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 29, 2011. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce (RR) turbofan engine models RB211–524G2–T–19, RB211–524G3–T–19, RB211–524H2–T–19, RB211–524H–T–36, RB211–Trent 768–60, RB211–Trent 772–60, RB211–Trent 772B–60, RB211–Trent 875–17, RB211–Trent 877–17, RB211–Trent 884–17, RB211–Trent 884B–17, RB211–Trent 892–17, RB211–Trent 892B–17 and RB211–Trent 895–17 that incorporate RR Service Bulletin (SB) RB.211–72–D133 or RB.211–72–E902. These engines are installed on, but not limited to, Airbus A330 series airplanes; Boeing 747–400 series, 767 series, and 777 series airplanes. Initial Inspection (d) This AD results from: Cracking has been found on the inner wall between intermediate dilution chutes on a total of five front combustion liners of the standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72–D133. The lives of two of these liners were confirmed to be below the currently valid borescope inspection interval. Ultimately, crack propagation could result in hot gas breakout with potential of downstream component distress and multiple turbine blade release beyond containment capabilities of the engine casings. Thus, cracking of this nature constitutes a potentially unsafe condition. Since Rolls-Royce Service Bulletin No. 72– E902 introduces further developments of Rolls-Royce RB211 Service Bulletin No. 72– D133, engines incorporating Rolls-Royce RB211 Service Bulletin No. 72–E902 are also considered to be potentially affected and are therefore included in the applicability of this AD. Since EASA issued its AD, another cracking event has occurred, bringing to six the total of crack events of which we are aware. We are issuing this AD to detect cracks in the front combustion liner, which could result in hot section distress, multiple blade release, and possible damage to the airplane. (f) Perform a borescope inspection of the front combustion liner inner wall, before accumulating the cyclic limits specified in paragraphs (f)(2) and (f)(3) of this AD. (1) If you incorporated paragraph 3.A.(2)(a) of RR Alert Service Bulletin (ASB) RB.211– 72–AF458, Revision 4, dated March 9, 2009, or ASB RB.211–72–AF458, Revision 5, dated April 20, 2011, you have satisfied the requirements of paragraph (f) of this AD. (2) If the engine has a combustion liner installed with: (i) A LIFE on the effective date of this AD, that is equal to or greater than the initial inspection threshold specified in column (b) of Table 1 of this AD or a LIFE on the effective date of this AD, that is not known, within 250 cycles after the effective date of this AD, perform a borescope inspection as specified in paragraph (f) of this AD. (ii) A LIFE on the effective date of this AD, that is less than the initial inspection threshold specified in column (b) of Table 1 of this AD, perform the borescope inspection before the LIFE exceeds the limit specified in column (c) of Table 1 of this AD. Actions and Compliance (e) Unless already done, do the following actions. Repeat Inspection (3) Thereafter, repeat the borescope inspection specified in paragraph (f) of this AD at intervals not to exceed the cycles specified in column (d) of Table 1 of this AD. TABLE 1—INITIAL INSPECTION THRESHOLDS AND LIMITS Column (a) Column (b) Column (c) Column (d) Engine model Initial inspectionthreshold Initial inspection limit if LIFE is less than the initial inspection threshold Repeat inspection interval (i) RB211–524G2–T–19, 524G3–T–19 and 524H2–T–19 ......... (ii) RB211–524H–T–36 ............................................................... (iii) RB211–Trent 768–60, 772–60 and 772B–60 ...................... (iv) RB211–Trent 892–17, RB211–Trent 884–17, RB211–Trent 884B–17, RB211–Trent 877–17, RB211–Trent 875–17, RB211–Trent 892B–17 and RB211–Trent 895–17 engines. 1,150 cycles ............................. 550 cycles ................................ 1,250 cycles ............................. 750 cycles ................................ 1,400 cycles .............. 800 cycles ................. 1,500 cycles .............. 1,000 cycles .............. erowe on DSK2VPTVN1PROD with RULES Definitions (g) This AD defines LIFE as the lowest of: (1) The number of cycles-since-new of the combustion liner, or (2) The number of cycles-in-service (CIS) since replacement of the inner wall, or (3) The number of CIS since the inner wall of the combustion liner was last borescopeinspected, or inspected by performing paragraph 3.A.(2)(a) of RR ASB RB.211–72– AF458, Revision 4, dated March 9, 2009 or ASB RB.211–72–AF458, Revision 5, dated April 20, 2011. FAA AD Differences (h) This AD differs from the Mandatory Continuing Airworthiness Information (MCAI) in that the MCAI AD applies to the RB211–Trent 772C–60 engine, which is not type certificated in the United States. The VerDate Mar<15>2010 16:47 Oct 24, 2011 Jkt 223001 MCAI also allows use of later revisions of the SBs. This AD does not. Other FAA AD Provisions (i) 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 (j) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2009– 0243R2, Corrected, dated February 22, 2011, for related information. (k) Rolls-Royce ASB RB.211–72–AF458, Revision 4, dated March 9, 2009, or ASB RB.211–72–AF458, Revision 5, dated April 20, 2011, provide information on how to do the actions required by this AD. For service PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 1,400 cycles. 800 cycles. 1,500 cycles. 1,000 cycles. information identified in this AD, contact Corporate Communications at Rolls-Royce plc, PO Box 31, Derby, DE24 8BJ, United Kingdom, phone: 011–44–1331–242424, fax: 011–44–1332–249936, or e-mail: http:// www.rolls-royce.com/contact/civil_team.jsp identifying the correspondence as related to airworthiness directives. (l) Contact Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; phone: 781–238–7143; fax: 781–238–7199, for more information about this AD. Material Incorporated by Reference (m) None. E:\FR\FM\25OCR1.SGM 25OCR1 65944 Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Rules and Regulations Issued in Burlington, Massachusetts, on October 18, 2011. Peter A. White, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011–27513 Filed 10–24–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2011–0757; Airspace Docket No. 11–AAL–10] Establishment of Class E Airspace; Tatitlek, AK Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action establishes Class E airspace at Tatitlek, AK, to accommodate the creation of one standard instrument approach procedure at the Tatitlek Airport. The FAA is taking this action to enhance safety and management of Instrument Flight Rules (IFR) operations at the Tatitlek Airport. DATES: Effective 0901 UTC, December 15, 2011. The Director of the Federal Register approves this incorporation by reference action under title 1, Code of Federal Regulations, part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. SUMMARY: FOR FURTHER INFORMATION CONTACT: Martha Dunn, AAL–538G, Federal Aviation Administration, 222 West 7th Avenue, Box 14, Anchorage, AK 99513– 7587; telephone number (907) 271– 5898; fax: (907) 271–2850; e-mail: Martha.ctr.Dunn@faa.gov. Internet address: http://www.faa.gov/about/ office_org/headquarters_offices/ato/ service_units/systemops/fs/alaskan/ rulemaking/. SUPPLEMENTARY INFORMATION: erowe on DSK2VPTVN1PROD with RULES History On Wednesday, August 10, 2011, the FAA published a notice of proposed rulemaking (NPRM) in the Federal Register to establish Class E airspace at Tatitlek, AK (76 FR 49388). Interested parties were invited to participate in this rulemaking proceeding by submitting written comments on the proposal to the FAA. A comment was received that the coordinates for the Tatitlek Airport were incorrect. That error is corrected in this action. VerDate Mar<15>2010 15:13 Oct 24, 2011 Jkt 226001 The Class E airspace areas are published in paragraphs 6002 and 6005, respectively, of FAA Order 7400.9V, Airspace Designations and Reporting Points, signed September 9, 2011, and effective September 15, 2011, which is incorporated by reference in 14 CFR 71.1. The Class E airspace designations listed in this document will be published subsequently in the Order. With the exception of editorial changes, and the changes described above, this rule is the same as that proposed in the NPRM. The Rule This action amends Title 14 Code of Federal Regulations (14 CFR) part 71 by establishing Class E airspace at the Tatitlek Airport, Tatitlek, AK, to accommodate the creation of a standard instrument approach procedure. The Class E airspace provides adequate controlled airspace extending upward from 700 and 1,200 feet above the surface that is necessary for the safety and management of IFR operations at the airport. The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. It, therefore—(1) is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034; February 26, 1979); and (3) does not warrant preparation of a regulatory evaluation as the anticipated impact is so minimal. Because this is a routine matter that will only affect air traffic procedures and air navigation, it is certified that this rule will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. Subtitle 1, Section 106 describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the agency’s authority. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart 1, Section 40103, Sovereignty and use of airspace. Under that section, the FAA is charged with prescribing regulations to ensure the safe and efficient use of the navigable airspace. This regulation is within the scope of that authority because it establishes Class E airspace sufficient in size to contain aircraft executing the instrument procedure at PO 00000 Frm 00012 Fmt 4700 Sfmt 9990 the Tatitlek Airport and represents the FAA’s continuing effort to safely and efficiently use the navigable airspace. List of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (air). Adoption of the Amendment In consideration of the foregoing, the Federal Aviation Administration amends 14 CFR part 71 as follows: PART 71—DESIGNATION OF CLASS A, B, C, D, AND E AIRSPACE AREAS; AIR TRAFFIC SERVICE ROUTES; AND REPORTING POINTS 1. The authority citation for 14 CFR part 71 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40103, 40113, 40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959– 1963 Comp., p. 389. § 71.1 [Amended] 2. The incorporation by reference in 14 CFR 71.1 of Federal Aviation Administration Order 7400.9V, Airspace Designations and Reporting Points, signed September 9, 2011, and effective September 15, 2011, is amended as follows: ■ Paragraph 6005 Class E airspace extending upward from 700 feet or more above the surface of the earth. * * AAL AK E5 * * * Tatitlek, AK [Added] Tatitlek Airport, AK (Lat. 60°52′21″ N., long. 146°41′28″ W.) That airspace extending upward from 700 feet above the surface within a 6.4-mile radius of the Tatitlek Airport, AK and within 2 miles southwest and 3.4 miles northeast of the 149° radial from the Tatitlek Airport, AK extending from the 6.4-mile radius to 11.8 miles southeast of the Tatitlek Airport, AK and that airspace extending upward from 1,200 feet above the surface within a 60-mile radius of the Tatitlek Airport, AK. Issued in Anchorage, AK, on October 14, 2011. Marshall G. Severson, Acting Manager, Alaska Flight Services. [FR Doc. 2011–27368 Filed 10–24–11; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\25OCR1.SGM 25OCR1

Agencies

[Federal Register Volume 76, Number 206 (Tuesday, October 25, 2011)]
[Rules and Regulations]
[Pages 65941-65944]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-27513]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0993; Directorate Identifier 2010-NE-08-AD; 
Amendment 39-16849; AD 2011-22-07]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211-524 Series, 
RB211-Trent 700 Series, and RB211-Trent 800 Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    Cracking has been found on the inner wall between intermediate 
dilution chutes on a total of five front combustion liners of the 
standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72-
D133. The lives of two of these liners were confirmed to be below 
the currently valid borescope inspection interval. Ultimately, crack 
propagation could result in hot gas breakout with potential of 
downstream component distress and multiple turbine blade release 
beyond containment capabilities of the engine casings. Thus, 
cracking of this nature constitutes a potentially unsafe condition.
    Since Rolls-Royce Service Bulletin No. 72-E902 introduces 
further developments of Rolls-Royce RB211 Service Bulletin No. 72-
D133, engines incorporating Rolls-Royce RB211 Service Bulletin No. 
72-E902 are also considered to be potentially affected and are 
therefore included in the applicability of this AD.

We are issuing this AD to detect cracks in the front combustion liner, 
which could result in hot section distress, multiple blade release, and 
possible damage to the airplane.

DATES: This AD becomes effective November 29, 2011. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of November 29, 2011.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

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

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on October 5, 2010 (75 
FR 61363). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    Cracking has been found on the inner wall between intermediate 
dilution chutes on a total of five front combustion liners of the 
standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72-
D133. The lives of two of these liners were confirmed to be below 
the currently valid borescope inspection interval. Ultimately, crack 
propagation could result in hot gas breakout with potential of 
downstream component distress and multiple turbine blade release 
beyond containment capabilities of the engine casings. Thus, 
cracking of this nature constitutes a potentially unsafe condition.
    Since Rolls-Royce Service Bulletin No. 72-E902 introduces 
further developments of Rolls-Royce RB211 Service Bulletin No. 72-
D133, engines incorporating Rolls-Royce RB211 Service Bulletin No. 
72-E902 are also considered to be potentially affected and are 
therefore included in the applicability of this AD.
    This AD requires a change to the initial and repeat borescope 
inspection intervals for the front combustion liner.

Comments

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

Request To Expand Address for Service Information

    One commenter, Rolls-Royce plc (RR), asked us to consider changing 
the information for getting the service information to ``For any 
questions concerning the technical content of the requirements in this 
AD (NPRM), please contact your designated Rolls-Royce representative 
for a copy of the service information, please download the publication 
from your Aeromanager account at http://www.aeromanager.com. If you do 
not have a designated representative or an Aeromanager account, please 
contact Corporate Communications at Rolls-Royce plc, PO Box 31, Derby, 
DE24 8BJ, United Kingdom, phone: 011-44-1331-242424, fax: 011-44-1332-
249936, or e-mail: http://www.rolls-royce.com/contact/civil_team.jsp 
identifying the correspondence as being related to Airworthiness 
Directives.'' RR states that this should make sure that any questions 
from operators of their engines and those from other parties are 
directed to the area best equipped to answer.
    We partially agree. We agree that operators and maintenance 
providers need to get timely and accurate service information, and that 
additional information is worth including. We changed paragraph (k) of 
the AD to state ``* * * contact Corporate Communications at Rolls-Royce 
plc PO Box 31, Derby, DE24 8BJ, United Kingdom, Phone: 011-44-1331-
242424, fax 011-44-1332-249936 or e-mail from http://www.rolls-royce.com/contact/civil_team.jsp identifying the correspondence as 
being related to Airworthiness Directives.''
    We do not agree that operators or maintenance providers should 
contact RR for questions about this AD. We did not include that 
information in the AD.

Requests To Change References to the Service Bulletin That Is 
Incorporated by Reference

    Two commenters, American Airlines (AA) and The Boeing Company 
(Boeing), asked us to add ``or later

[[Page 65942]]

revision'' after ``Service Bulletin No. RB.211-72-AF458, Revision 2, 
dated December 21, 2007.'' Boeing stated the latest revision of Service 
Bulletin (SB) No. RB.211-72-AF458 is Revision 4. Boeing stated that 
airlines have been inspecting their combustion liners to Revision 4 of 
the SB and the compliance intervals specified in the NPRM are 
consistent with RR SB RB.211-72-AF458, Revision 4 and EASA AD 2009-
0243R1. AA stated the borescope inspection is the same on later 
revisions, so the life should be counted from the latest SB revision.
    We do not agree. On review of the SB, we determined that the 
inspection requirements and limits called out in the SB are already in 
the engine and aircraft maintenance manuals. We changed the AD to 
remove the incorporation by reference of the SB.
    One commenter, AA, asked us to revise paragraph (f) of the AD to 
specifically call out which paragraphs of SB RB.211-72-AF458 are 
incorporated by reference. AA stated the NPRM called out all of section 
3 of the SB, which is too prescriptive given the nature of the 
inspections.
    We do not agree. On review of the SB, we found incorporation by 
reference unnecessary. We changed the AD to remove the incorporation by 
reference of the SB.

Request To Remove an Engine Model From the Applicability

    One commenter, AA, asked us to remove the RR RB211-535 engine model 
from the applicability of the proposed AD. AA stated they have recorded 
no crack findings against the RB211-535 model.
    We agree. The thermal, acoustical, and vibratory stress environment 
of the RB211-535 combustion liner is different from that of the other 
engines to which this AD applies. We removed the RB211-535E4-37, RB211-
535E4-B-37, RB211-535E4-C-37, and RB211-535E4-B-75 from the 
Applicability paragraph (c) of this AD, and updated our cost estimate 
to reflect the fewer affected engines.

Request To Change the Number of Cracking Events

    One commenter, Boeing, asked us to change paragraph (d) of the 
proposed AD to specify that six cracking events have been found instead 
of five. Boeing states that changing paragraph (d) of the proposed AD 
will more accurately reflect the need for the inspections.
    We agree. Although an additional cracking event has occurred, the 
AD was prompted by the investigation of five events. We changed 
paragraph (d) of this AD to reflect six known cracking events.

Request To Add a Grace Period for Compliance

    One commenter, Boeing asked us to change paragraphs (f)(1)(i) and 
(f)(1)(iii) of the proposed AD to add ``within 15 cycles of the date of 
issue of the AD'' before the word ``or.'' Boeing states that adding the 
15 cycle grace period will give operators time to get back to base for 
the inspection.
    We partially agree. No additional grace period is required. This AD 
does not require inspecting any engine earlier than 250 cycles after 
the effective date of the AD. We clarified the wording of paragraph (f) 
to make this clearer.

Statement of the Possibility of Cost and Operational Impact Increasing

    One commenter, Federal Express, stated that cost and operational 
impact could increase if certain RB211-535 models are added to the 
applicability of the proposed AD. The commenter provided no reason for 
its statement.
    We agree. However, additional engine models are not being added, 
and we are specifically excluding the RB211-535 engine in response to 
another comment. We did not change the AD in response to this comment.

Conclusion

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

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 46 products of U.S. registry. We also estimate that it 
will take about 1.5 work-hours per product to comply with this AD. The 
average labor rate is $85 per work-hour. No parts are required so parts 
will cost $0 per product. Based on these figures, we estimate the cost 
of the AD on U.S. operators to be $5,865.

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),
    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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (phone: (800) 647-5527) is provided in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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:

[[Page 65943]]

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]

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

2011-22-07 Rolls-Royce: Amendment 39-16849. Docket No. FAA-2010-
0993; Directorate Identifier 2010-NE-08-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
29, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce (RR) turbofan engine models 
RB211-524G2-T-19, RB211-524G3-T-19, RB211-524H2-T-19, RB211-524H-T-
36, RB211-Trent 768-60, RB211-Trent 772-60, RB211-Trent 772B-60, 
RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-
Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17 and RB211-
Trent 895-17 that incorporate RR Service Bulletin (SB) RB.211-72-
D133 or RB.211-72-E902. These engines are installed on, but not 
limited to, Airbus A330 series airplanes; Boeing 747-400 series, 767 
series, and 777 series airplanes.

Reason

    (d) This AD results from:
    Cracking has been found on the inner wall between intermediate 
dilution chutes on a total of five front combustion liners of the 
standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72-
D133. The lives of two of these liners were confirmed to be below 
the currently valid borescope inspection interval. Ultimately, crack 
propagation could result in hot gas breakout with potential of 
downstream component distress and multiple turbine blade release 
beyond containment capabilities of the engine casings. Thus, 
cracking of this nature constitutes a potentially unsafe condition.
    Since Rolls-Royce Service Bulletin No. 72-E902 introduces 
further developments of Rolls-Royce RB211 Service Bulletin No. 72-
D133, engines incorporating Rolls-Royce RB211 Service Bulletin No. 
72-E902 are also considered to be potentially affected and are 
therefore included in the applicability of this AD.

    Since EASA issued its AD, another cracking event has occurred, 
bringing to six the total of crack events of which we are aware. We 
are issuing this AD to detect cracks in the front combustion liner, 
which could result in hot section distress, multiple blade release, 
and possible damage to the airplane.

Actions and Compliance

    (e) Unless already done, do the following actions.

Initial Inspection

    (f) Perform a borescope inspection of the front combustion liner 
inner wall, before accumulating the cyclic limits specified in 
paragraphs (f)(2) and (f)(3) of this AD.
    (1) If you incorporated paragraph 3.A.(2)(a) of RR Alert Service 
Bulletin (ASB) RB.211-72-AF458, Revision 4, dated March 9, 2009, or 
ASB RB.211-72-AF458, Revision 5, dated April 20, 2011, you have 
satisfied the requirements of paragraph (f) of this AD.
    (2) If the engine has a combustion liner installed with:
    (i) A LIFE on the effective date of this AD, that is equal to or 
greater than the initial inspection threshold specified in column 
(b) of Table 1 of this AD or a LIFE on the effective date of this 
AD, that is not known, within 250 cycles after the effective date of 
this AD, perform a borescope inspection as specified in paragraph 
(f) of this AD.
    (ii) A LIFE on the effective date of this AD, that is less than 
the initial inspection threshold specified in column (b) of Table 1 
of this AD, perform the borescope inspection before the LIFE exceeds 
the limit specified in column (c) of Table 1 of this AD.

Repeat Inspection

    (3) Thereafter, repeat the borescope inspection specified in 
paragraph (f) of this AD at intervals not to exceed the cycles 
specified in column (d) of Table 1 of this AD.

                                Table 1--Initial Inspection Thresholds and Limits
----------------------------------------------------------------------------------------------------------------
             Column (a)                       Column (b)                Column (c)              Column (d)
----------------------------------------------------------------------------------------------------------------
                                                                    Initial inspection
                                                Initial            limit if LIFE is less     Repeat inspection
            Engine model                  inspectionthreshold        than the initial            interval
                                                                   inspection threshold
----------------------------------------------------------------------------------------------------------------
(i) RB211-524G2-T-19, 524G3-T-19 and  1,150 cycles..............  1,400 cycles..........  1,400 cycles.
 524H2-T-19.
(ii) RB211-524H-T-36................  550 cycles................  800 cycles............  800 cycles.
(iii) RB211-Trent 768-60, 772-60 and  1,250 cycles..............  1,500 cycles..........  1,500 cycles.
 772B-60.
(iv) RB211-Trent 892-17, RB211-Trent  750 cycles................  1,000 cycles..........  1,000 cycles.
 884-17, RB211-Trent 884B-17, RB211-
 Trent 877-17, RB211-Trent 875-17,
 RB211-Trent 892B-17 and RB211-Trent
 895-17 engines.
----------------------------------------------------------------------------------------------------------------

Definitions

    (g) This AD defines LIFE as the lowest of:
    (1) The number of cycles-since-new of the combustion liner, or
    (2) The number of cycles-in-service (CIS) since replacement of 
the inner wall, or
    (3) The number of CIS since the inner wall of the combustion 
liner was last borescope-inspected, or inspected by performing 
paragraph 3.A.(2)(a) of RR ASB RB.211-72-AF458, Revision 4, dated 
March 9, 2009 or ASB RB.211-72-AF458, Revision 5, dated April 20, 
2011.

FAA AD Differences

    (h) This AD differs from the Mandatory Continuing Airworthiness 
Information (MCAI) in that the MCAI AD applies to the RB211-Trent 
772C-60 engine, which is not type certificated in the United States. 
The MCAI also allows use of later revisions of the SBs. This AD does 
not.

Other FAA AD Provisions

    (i) 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

    (j) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2009-0243R2, Corrected, dated February 22, 2011, for 
related information.
    (k) Rolls-Royce ASB RB.211-72-AF458, Revision 4, dated March 9, 
2009, or ASB RB.211-72-AF458, Revision 5, dated April 20, 2011, 
provide information on how to do the actions required by this AD. 
For service information identified in this AD, contact Corporate 
Communications at Rolls-Royce plc, PO Box 31, Derby, DE24 8BJ, 
United Kingdom, phone: 011-44-1331-242424, fax: 011-44-1332-249936, 
or e-mail: http://www.rolls-royce.com/contact/civil_team.jsp 
identifying the correspondence as related to airworthiness 
directives.
    (l) Contact Alan Strom, Aerospace Engineer, Engine Certification 
Office, FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; 
phone: 781-238-7143; fax: 781-238-7199, for more information about 
this AD.

Material Incorporated by Reference

    (m) None.


[[Page 65944]]


    Issued in Burlington, Massachusetts, on October 18, 2011.
Peter A. White,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-27513 Filed 10-24-11; 8:45 am]
BILLING CODE 4910-13-P