AD 2011-09-07 Airworthiness Directives; Rolls-Royce plc (RR) RB211-524 Series and RB211 Trent 500, 700, and 800 Series Turbofan Engines

This AD applies to RR model RB211-524G2-T-19, -524G3-T-19, -524H-T-36, and -524H2-T-19; and RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, 560A2-61; RB211 Trent 768-60, 772-60, 772B-60; and RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 turbofan engines that have a high-pressure (HP) compressor stage 1 to 4 rotor disc with a part number (P/N) listed in Table 1 of this AD. These engines are installed on, but not limited to, Boeing 747, 767, and 777 series airplanes and Airbus A330 and A340 series airplanes. Table 1—Affected HP Compressor Stage 1 to 4 Rotor Disc P/Ns by Engine Model Engine model HP compressor stage 1 to 4 rotor disc P/N (1) RB211-524G2-T-19, -524G3-T-19, -524H-T-36, and -524H2-T-19 FW20195, FK25502, or FW23711. (2) RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 FK30524. (3) RB211 Trent 768-60, 772-60, and 772B-60 FK22745, FK24031, FK26185, FK23313, FK25502, FK32129, FW20195, FW20196, FW20197, FW20638, or FW23711. (4) RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 FK24009, FK26167, FK32580, FW11590, or FW61622. Reason (d) This AD results from reports that: During manufacture of a number of HP Compressor Stage 1 and 2 discs with axial dovetail slots, anomalies at the disc post corners have been found. Fatigue crack initiation and subsequent crack propagation at the disc post may result in release of two blades and the disc post. This may potentially be beyond the containment capabilities of the engine casings. Thus, these anomalies present at the disc posts constitute a potentially unsafe condition. We are issuing this AD to detect cracks in the high-pressure compressor (HPC) Stage 1 and 2 disc posts, which could result in failure of the disc post and release of HPC blades, release of uncontained engine debris, and damage to the airplane.

Unless already done, do the following actions. (1) Clean and perform a fluorescent penetrant inspection of the HP compressor stage 1 to 4 rotor discs at the first shop visit after accumulating 1000 cycles since new on the stage 1 to 4 rotor disks or at the next shop visit after the effective date of this AD, whichever occurs later. Use paragraph 3.A through 3.E.(11) of the Accomplishment Instructions of Rolls-Royce Alert Service Bulletin (ASB) RB.211-72-AF964, Revision 1, dated June 6, 2008 to do the inspections. (2) Thereafter at every engine shop visit, perform the inspection specified by paragraph (e)(1) of this AD. Definitions (f) For the purpose of this AD, an “engine shop visit” is whenever the engine high-pressure compressor module is separated from the intermediate case. Other FAA AD Provisions (g) 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 (h) See European Aviation Safety Agency Airworthiness Directive 2009-0073R1, dated April 8, 2009, for related information. (i) Contact Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; telephone (781) 238-7143; fax (781) 238-7199, for more information about this AD. Material Incorporated by Reference (j) You must use Rolls-Royce Alert Service Bulletin RB.211-72-AF964, Revision 1, dated June 6, 2008, to do the actions 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 Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; phone: 011 44 1332 242424, fax: 011 44 1332 249936; e-mail: tech.help@rolls-royce.com. (3) 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. Issued in Burlington, Massachusetts, on April 12, 2011. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011-10517 Filed 5-2-11; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. (1) Clean and perform a fluorescent penetrant inspection of the HP compressor stage 1 to 4 rotor discs at the first shop visit after accumulating 1000 cycles since new on the stage 1 to 4 rotor disks or at the next shop visit after the effective date of this AD, whichever occurs later. Use paragraph 3.A through 3.E.(11) of the Accomplishment Instructions of Rolls-Royce Alert Service Bulletin (ASB) RB.211-72-AF964, Revision 1, dated June 6, 2008 to do the inspections. (2) Thereafter at every engine shop visit, perform the inspection specified by paragraph (e)(1) of this AD. Definitions (f) For the purpose of this AD, an “engine shop visit” is whenever the engine high-pressure compressor module is separated from the intermediate case. Other FAA AD Provisions (g) 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 (h) See European Aviation Safety Agency Airworthiness Directive 2009-0073R1, dated April 8, 2009, for related information. (i) Contact Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; telephone (781) 238-7143; fax (781) 238-7199, for more information about this AD. Material Incorporated by Reference (j) You must use Rolls-Royce Alert Service Bulletin RB.211-72-AF964, Revision 1, dated June 6, 2008, to do the actions 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 Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; phone: 011 44 1332 242424, fax: 011 44 1332 249936; e-mail: tech.help@rolls-royce.com. (3) 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. Issued in Burlington, Massachusetts, on April 12, 2011. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011-10517 Filed 5-2-11; 8:45 am] BILLING CODE 4910-13-P