AD 2010-07-09

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

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

(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.

(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.

(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.

(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.

(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.

(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.

(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.

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

(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.

(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.

(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.

(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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.