Airworthiness Directives; Rolls-Royce plc RB211-Trent 700 Series Turbofan Engines, 16655-16657 [2010-7283]

Download as PDF Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations (1) Where Boeing Alert Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008, specifies a compliance time relative to the date of issuance of that service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008, specifies contacting Boeing for repair data: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Optional New Modification for Areas 1, 2, 3, and 4 (m) For areas 1, 2, 3, and 4 as defined in Boeing Alert Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008: Doing the modification and post-modification actions specified in Boeing Alert Service Bulletin 747–53A2696, dated October 16, 2008, terminates the repetitive inspection requirements of paragraphs (g) and (h) of this AD. Doing the modification and postmodification actions specified in Boeing Alert Service Bulletin 747–53A2696, dated October 16, 2008, terminates the repetitive inspection requirements of paragraph (l) of this AD, except at the upper deck floor beam at body station (BS) 460 and 480 and the upper deck floor beams aft of BS 520. wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 No Reporting Requirement (n) Although Boeing Alert Service Bulletin 747–53A2439, Revision 1, dated March 10, 2005; and Boeing Alert Service Bulletin 747– 53A2439, Revision 2, dated July 17, 2008; specify to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (o)(1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6437; fax (425) 917–6590. Or, e-mail information to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (3) AMOCs approved previously in accordance with AD 2006–08–02, are approved as AMOCs for the corresponding provisions of this AD. (4) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO VerDate Nov<24>2008 12:54 Apr 01, 2010 Jkt 220001 to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Material Incorporated by Reference (p) You must use Boeing Alert Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008, to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the new optional actions specified by this AD, you must use Boeing Alert Service Bulletin 747–53A2696, dated October 16, 2008, to perform those actions, 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 Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1, fax 206–766– 5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on March 17, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–6546 Filed 4–1–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–19559; Directorate Identifier 2004–NE–03–AD; Amendment 39– 16254; AD 2010–07–09] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211–Trent 700 Series Turbofan Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc RB211–Trent 700 series PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 16655 turbofan engines. That AD currently requires initial and repetitive borescope inspections of the high-pressure-andintermediate pressure (HP–IP) turbine internal and external oil vent tubes for coking and carbon buildup, and cleaning or replacing the vent tubes if necessary. This AD requires the same actions, but adds additional inspections of the vent flow restrictor. This AD results from further analysis that the cleaning of the vent tubes required by AD 2007–02–05 could lead to loosened carbon fragments, causing a blockage downstream in the vent flow restrictor. We are issuing this AD to prevent internal oil fires due to coking and carbon buildup that could cause uncontained engine failure and damage to the airplane. DATES: This AD becomes effective May 7, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of May 7, 2010. ADDRESSES: You can get the service information identified in this AD from Rolls-Royce plc, P.O. Box 31, Derby, England; telephone: 011–44–1332– 249428; fax: 011–44–1332–249223. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by superseding AD 2007–02–05, Amendment 39–14892 (72 FR 2603, January 22, 2007), with a proposed AD. The proposed AD applies to Rolls-Royce plc RB211–Trent 700 series turbofan engines. We published the proposed AD in the Federal Register on October 26, 2009 (74 FR 54940). That action proposed to require initial and repetitive borescope inspections of the HP–IP turbine internal and external oil vent tubes for coking and carbon buildup, cleaning or replacing the vent tubes if necessary, and inspections of the vent flow restrictor. 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, E:\FR\FM\02APR1.SGM 02APR1 16656 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations 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 (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request to Reference the Latest Service Bulletin One commenter, Rolls-Royce plc, requests that we incorporate by reference the latest alert service bulletin (ASB) in the AD, which is ASB No. RB.211–72–AE302, Revision 8, dated October 21, 2009. We agree. We changed the AD to incorporate by reference Revision 8 of that ASB. Request To Allow Previous Credit Rolls-Royce plc requests that we allow previous credit to operators that performed the initial inspections specified in paragraph (f) of the proposed AD before the AD effective date, using Revision 4, Revision 5, Revision 6, or Revision 7 of ASB No. RB.211–72–AE302. We agree and added a previous credit paragraph to the AD. Request to Change Initial Inspection Threshold Rolls-Royce plc requests that we change the initial inspection threshold from 3 months to 2 months, to agree with the ASB. We agree and changed the AD. wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 Clarification of AD Compliance Section We clarified paragraphs (g) and (h) of the AD compliance section to better align with the Rolls-Royce plc ASB. Conclusion We have carefully 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 have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance Based on the service information, we estimate that this AD will affect about VerDate Nov<24>2008 12:54 Apr 01, 2010 Jkt 220001 33 engines of U.S. registry. We also estimate that it will take about one work-hour per engine to comply with this AD. The average labor rate is $80 per work-hour. Required parts will cost about $2,000 per engine. Based on these figures, we estimate the cost of the AD on U.S. operators to be $68,640. 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 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 that this AD: (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) 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 summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration 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 removing Amendment 39–14892 (72 FR 2603, January 22, 2007), and by adding a new airworthiness directive, Amendment 39–16254, to read as follows: ■ 2010–07–09 Rolls-Royce plc: Amendment 39–16254. Docket No. FAA–2005–19559; Directorate Identifier 2004–NE–03–AD. Effective Date (a) This airworthiness directive (AD) becomes effective May 7, 2010. Affected ADs (b) This AD supersedes AD 2007–02–05, Amendment 39–14892. Applicability (c) This AD applies to Rolls-Royce plc RB211–Trent 768–60, RB211–Trent 772–60, and RB211–Trent 772B–60 series turbofan engines. These engines are installed on, but not limited to, Airbus A330–243, –341, –342 and –343 series airplanes. Unsafe Condition (d) This AD results from further analysis that the cleaning of the vent tubes required by AD 2007–02–05 could lead to loosened carbon fragments, causing a blockage downstream in the vent flow restrictor. We are issuing this AD to prevent internal oil fires due to coking and carbon buildup that could cause uncontained engine failure and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Initial Inspections, Cleaning, and Replacements (f) Using the schedule in Table 1 of this AD, borescope-inspect and clean as necessary, the high-pressure-andintermediate pressure (HP–IP) turbine internal oil vent tubes, external oil vent tubes, and bearing chamber. E:\FR\FM\02APR1.SGM 02APR1 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations 16657 TABLE 1—INITIAL INSPECTION SCHEDULE If the engine or the 05 Module Then initially inspect Has reached 10,000 hours time-since-new (TSN) or reached 2,500 cycles-since-new (CSN) on the effective date of this AD. Has fewer than 10,000 hours TSN and fewer than 2,500 CSN on the effective date of this AD. Is returned for an engine shop visit ......................................................... (1) If after cleaning, there is still carbon in the vent tube that prevents cleaning tool number HU80298 from passing through the tube, then replace the internal oil vent tube within 10 cycles-in-service (CIS). (2) If after cleaning, there is still carbon of visible thickness in either of the two external oil vent tubes, then replace the external oil vent tube before further flight. (3) Use paragraphs 3.A. through 3.A.(7) of the Accomplishment Instructions and Appendix A of Rolls-Royce plc Alert Service Bulletin (ASB) No. RB.211–72–AE302, Revision 8, dated October 21, 2009, to do the borescope inspections and cleaning of the oil vent tubes and bearing chamber. wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 Initial Visual Inspection of the Vent Flow Restrictor (g) For engines that, on the effective date of this AD, have not accumulated 25 service cycles since the last cleaning and inspection specified in paragraphs (f) through (f)(3) of this AD, visually inspect the vent flow restrictor: (1) Either after a high-power ground run immediately following the cleaning and inspection; or (2) Within 25 service cycles of the last cleaning and inspection. (h) For engines that, on the effective date of this AD, have accumulated 25 or more service cycles since the last cleaning and inspection specified in paragraphs (f) through (f)(3) of this AD, visually inspect the vent flow restrictor within 25 service cycles after the effective date of this AD. (i) Use paragraph 3.A.(8) of the Accomplishment Instructions of Rolls-Royce plc ASB No. RB.211–72–AE302, Revision 8, dated October 21, 2009, to do the visual inspections. Repetitive Inspections, Cleaning, and Replacements (j) Within 6,400 hours time-in-service since last inspection and cleaning, or within 1,600 cycles-since-last inspection and cleaning, or at the next engine shop visit, whichever occurs first, borescope-inspect the HP–IP turbine internal and external oil vent tubes and bearing chamber, and clean the oil vent tubes as necessary. (1) If after cleaning there is still carbon in the internal oil vent tube that prevents cleaning tool, number HU80298, from passing through the tube, then replace the internal oil vent tube within 10 CIS. (2) If after cleaning there is still carbon of visible thickness, in either of the two external oil vent tubes, then replace the external oil vent tube before further flight. (3) Use paragraphs 3.A. through 3.A.(7) of the Accomplishment Instructions and Appendix A of Rolls-Royce plc ASB No. VerDate Nov<24>2008 12:54 Apr 01, 2010 Jkt 220001 Within 2 months after the effective date of this AD. Within 2 months after reaching 10,000 hours TSN or 2,500 CSN, whichever occurs first. Before returning to service. RB.211–72–AE302, Revision 8, dated October 21, 2009, to do the borescope inspections and cleaning of the oil vent tubes and bearing chamber. (k) Visually inspect the vent flow restrictor either after a high-power ground run or within 25 service cycles after performing the cleaning and inspection specified in paragraph (f) through (f)(3) of this AD. Use paragraph 3.A.(8) of the Accomplishment Instructions of Rolls-Royce plc ASB No. RB.211–72–AE302, Revision 8, dated October 21, 2009, to do the visual inspection. MA; or 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. Definition (l) For the purpose of this AD, an engine shop visit is induction of the engine into the engine shop for any cause. BILLING CODE 4910–13–P Previous Credit (m) Initial inspections specified in paragraph (f) of this AD and performed before the effective date of this AD using RollsRoyce plc ASB No. RB.211–72–AE302, Revision 4, dated April 30, 2007, or Revision 5, dated May 22, 2007, or Revision 6, dated January 29, 2009, or Revision 7, dated April 30, 2009, satisfy the initial inspection requirements in paragraph (f) of this AD. Federal Aviation Administration Alternative Methods of Compliance (n) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (o) European Aviation Safety Agency AD 2007–0201, dated August 1, 2007, and AD 2007–0202 (corrected August 8, 2007), also address the subject of this AD. (p) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238– 7199, for more information about this AD. Material Incorporated by Reference (q) You must use Rolls-Royce plc Alert Service Bulletin No. RB.211–72–AE302, Revision 8, dated October 21, 2009, including Appendix A, to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Rolls-Royce plc, P.O. Box 31, Derby, England; telephone: 011–44–1332– 249428; fax: 011–44–1332–249223 for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 Issued in Burlington, Massachusetts, on March 25, 2010. Robert J. Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010–7283 Filed 4–1–10; 8:45 am] DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. FAA–2009–1166; Directorate Identifier 2009–NM–107–AD; Amendment 39–16255; AD 2010–07–10] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: One operator reported loss of both pitch trims following autopilot disengagement after take off. Subsequent shop findings revealed severe damage to the power gears. Malphasing between the hydraulic motors was suspected to have induced excessive loads into the gear train, leading to collapse of one bearing on a shaft of the main gear, causing severe tooth damage. The combination of tooth damage and gear tilting caused the disconnection of two of the three hydraulic motors, resulting in jamming of the THSA [trimmable horizontal stabilizer actuator] gearbox and consequent loss of THSA control. E:\FR\FM\02APR1.SGM 02APR1

Agencies

[Federal Register Volume 75, Number 63 (Friday, April 2, 2010)]
[Rules and Regulations]
[Pages 16655-16657]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-7283]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-19559; Directorate Identifier 2004-NE-03-AD; 
Amendment 39-16254; AD 2010-07-09]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Rolls-Royce plc RB211-Trent 700 series turbofan engines. That 
AD currently requires initial and repetitive borescope inspections of 
the high-pressure-and-intermediate pressure (HP-IP) turbine internal 
and external oil vent tubes for coking and carbon buildup, and cleaning 
or replacing the vent tubes if necessary. This AD requires the same 
actions, but adds additional inspections of the vent flow restrictor. 
This AD results from further analysis that the cleaning of the vent 
tubes required by AD 2007-02-05 could lead to loosened carbon 
fragments, causing a blockage downstream in the vent flow restrictor. 
We are issuing this AD to prevent internal oil fires due to coking and 
carbon buildup that could cause uncontained engine failure and damage 
to the airplane.

DATES: This AD becomes effective May 7, 2010. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of May 7, 2010.

ADDRESSES: You can get the service information identified in this AD 
from Rolls-Royce plc, P.O. Box 31, Derby, England; telephone: 011-44-
1332-249428; fax: 011-44-1332-249223.
    The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by 
superseding AD 2007-02-05, Amendment 39-14892 (72 FR 2603, January 22, 
2007), with a proposed AD. The proposed AD applies to Rolls-Royce plc 
RB211-Trent 700 series turbofan engines. We published the proposed AD 
in the Federal Register on October 26, 2009 (74 FR 54940). That action 
proposed to require initial and repetitive borescope inspections of the 
HP-IP turbine internal and external oil vent tubes for coking and 
carbon buildup, cleaning or replacing the vent tubes if necessary, and 
inspections of the vent flow restrictor.

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,

[[Page 16656]]

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 (telephone (800) 647-5527) is 
provided in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request to Reference the Latest Service Bulletin

    One commenter, Rolls-Royce plc, requests that we incorporate by 
reference the latest alert service bulletin (ASB) in the AD, which is 
ASB No. RB.211-72-AE302, Revision 8, dated October 21, 2009.
    We agree. We changed the AD to incorporate by reference Revision 8 
of that ASB.

Request To Allow Previous Credit

    Rolls-Royce plc requests that we allow previous credit to operators 
that performed the initial inspections specified in paragraph (f) of 
the proposed AD before the AD effective date, using Revision 4, 
Revision 5, Revision 6, or Revision 7 of ASB No. RB.211-72-AE302.
    We agree and added a previous credit paragraph to the AD.

Request to Change Initial Inspection Threshold

    Rolls-Royce plc requests that we change the initial inspection 
threshold from 3 months to 2 months, to agree with the ASB.
    We agree and changed the AD.

Clarification of AD Compliance Section

    We clarified paragraphs (g) and (h) of the AD compliance section to 
better align with the Rolls-Royce plc ASB.

Conclusion

    We have carefully 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 have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 33 engines of U.S. registry. We also estimate that it will 
take about one work-hour per engine to comply with this AD. The average 
labor rate is $80 per work-hour. Required parts will cost about $2,000 
per engine. Based on these figures, we estimate the cost of the AD on 
U.S. operators to be $68,640.

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 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 that this AD:
    (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) 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration 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 removing Amendment 39-14892 (72 FR 
2603, January 22, 2007), and by adding a new airworthiness directive, 
Amendment 39-16254, to read as follows:

2010-07-09 Rolls-Royce plc: Amendment 39-16254. Docket No. FAA-2005-
19559; Directorate Identifier 2004-NE-03-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 7, 
2010.

Affected ADs

    (b) This AD supersedes AD 2007-02-05, Amendment 39-14892.

Applicability

    (c) This AD applies to Rolls-Royce plc RB211-Trent 768-60, 
RB211-Trent 772-60, and RB211-Trent 772B-60 series turbofan engines. 
These engines are installed on, but not limited to, Airbus A330-243, 
-341, -342 and -343 series airplanes.

Unsafe Condition

    (d) This AD results from further analysis that the cleaning of 
the vent tubes required by AD 2007-02-05 could lead to loosened 
carbon fragments, causing a blockage downstream in the vent flow 
restrictor. We are issuing this AD to prevent internal oil fires due 
to coking and carbon buildup that could cause uncontained engine 
failure and damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Initial Inspections, Cleaning, and Replacements

    (f) Using the schedule in Table 1 of this AD, borescope-inspect 
and clean as necessary, the high-pressure-and-intermediate pressure 
(HP-IP) turbine internal oil vent tubes, external oil vent tubes, 
and bearing chamber.

[[Page 16657]]



                  Table 1--Initial Inspection Schedule
------------------------------------------------------------------------
     If the engine or the 05 Module           Then initially inspect
------------------------------------------------------------------------
Has reached 10,000 hours time-since-new  Within 2 months after the
 (TSN) or reached 2,500 cycles-since-     effective date of this AD.
 new (CSN) on the effective date of
 this AD.
Has fewer than 10,000 hours TSN and      Within 2 months after reaching
 fewer than 2,500 CSN on the effective    10,000 hours TSN or 2,500 CSN,
 date of this AD.                         whichever occurs first.
Is returned for an engine shop visit...  Before returning to service.
------------------------------------------------------------------------

    (1) If after cleaning, there is still carbon in the vent tube 
that prevents cleaning tool number HU80298 from passing through the 
tube, then replace the internal oil vent tube within 10 cycles-in-
service (CIS).
    (2) If after cleaning, there is still carbon of visible 
thickness in either of the two external oil vent tubes, then replace 
the external oil vent tube before further flight.
    (3) Use paragraphs 3.A. through 3.A.(7) of the Accomplishment 
Instructions and Appendix A of Rolls-Royce plc Alert Service 
Bulletin (ASB) No. RB.211-72-AE302, Revision 8, dated October 21, 
2009, to do the borescope inspections and cleaning of the oil vent 
tubes and bearing chamber.

Initial Visual Inspection of the Vent Flow Restrictor

    (g) For engines that, on the effective date of this AD, have not 
accumulated 25 service cycles since the last cleaning and inspection 
specified in paragraphs (f) through (f)(3) of this AD, visually 
inspect the vent flow restrictor:
    (1) Either after a high-power ground run immediately following 
the cleaning and inspection; or
    (2) Within 25 service cycles of the last cleaning and 
inspection.
    (h) For engines that, on the effective date of this AD, have 
accumulated 25 or more service cycles since the last cleaning and 
inspection specified in paragraphs (f) through (f)(3) of this AD, 
visually inspect the vent flow restrictor within 25 service cycles 
after the effective date of this AD.
    (i) Use paragraph 3.A.(8) of the Accomplishment Instructions of 
Rolls-Royce plc ASB No. RB.211-72-AE302, Revision 8, dated October 
21, 2009, to do the visual inspections.

Repetitive Inspections, Cleaning, and Replacements

    (j) Within 6,400 hours time-in-service since last inspection and 
cleaning, or within 1,600 cycles-since-last inspection and cleaning, 
or at the next engine shop visit, whichever occurs first, borescope-
inspect the HP-IP turbine internal and external oil vent tubes and 
bearing chamber, and clean the oil vent tubes as necessary.
    (1) If after cleaning there is still carbon in the internal oil 
vent tube that prevents cleaning tool, number HU80298, from passing 
through the tube, then replace the internal oil vent tube within 10 
CIS.
    (2) If after cleaning there is still carbon of visible 
thickness, in either of the two external oil vent tubes, then 
replace the external oil vent tube before further flight.
    (3) Use paragraphs 3.A. through 3.A.(7) of the Accomplishment 
Instructions and Appendix A of Rolls-Royce plc ASB No. RB.211-72-
AE302, Revision 8, dated October 21, 2009, to do the borescope 
inspections and cleaning of the oil vent tubes and bearing chamber.
    (k) Visually inspect the vent flow restrictor either after a 
high-power ground run or within 25 service cycles after performing 
the cleaning and inspection specified in paragraph (f) through 
(f)(3) of this AD. Use paragraph 3.A.(8) of the Accomplishment 
Instructions of Rolls-Royce plc ASB No. RB.211-72-AE302, Revision 8, 
dated October 21, 2009, to do the visual inspection.

Definition

    (l) For the purpose of this AD, an engine shop visit is 
induction of the engine into the engine shop for any cause.

Previous Credit

    (m) Initial inspections specified in paragraph (f) of this AD 
and performed before the effective date of this AD using Rolls-Royce 
plc ASB No. RB.211-72-AE302, Revision 4, dated April 30, 2007, or 
Revision 5, dated May 22, 2007, or Revision 6, dated January 29, 
2009, or Revision 7, dated April 30, 2009, satisfy the initial 
inspection requirements in paragraph (f) of this AD.

Alternative Methods of Compliance

    (n) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD, if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (o) European Aviation Safety Agency AD 2007-0201, dated August 
1, 2007, and AD 2007-0202 (corrected August 8, 2007), also address 
the subject of this AD.
    (p) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

Material Incorporated by Reference

    (q) You must use Rolls-Royce plc Alert Service Bulletin No. 
RB.211-72-AE302, Revision 8, dated October 21, 2009, including 
Appendix A, to perform the actions required by this AD. The Director 
of the Federal Register approved the incorporation by reference of 
this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Contact Rolls-Royce plc, P.O. Box 31, Derby, England; 
telephone: 011-44-1332-249428; fax: 011-44-1332-249223 for a copy of 
this service information. You may review copies at the FAA, New 
England Region, 12 New England Executive Park, Burlington, MA; or 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 March 25, 2010.
Robert J. Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-7283 Filed 4-1-10; 8:45 am]
BILLING CODE 4910-13-P
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