AD 2011-10-04 Airworthiness Directives; Rolls-Royce plc RB211-Trent 800 Series Turbofan Engines

This AD applies to Rolls-Royce plc models RB211-Trent 875-17, -Trent 877-17, -Trent 884-17, -Trent 884B-17, -Trent 892-17, -Trent 892B-17, and -Trent 895-17 turbofan engines, with high-pressure (HP) compressor stage 1-4 shafts, part number (P/N) FK32580, installed. Reason (d) 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. European Aviation Safety Agency (EASA) AD 2010-0087, dated May 5, 2010 (corrected May 6, 2010) states the unsafe condition is as follows: During manufacture of high-pressure (HP) compressor stage 1 discs, a small number of parts have been rejected due to a machining defect that was found during inspection. Analysis of the possibility of less severe examples having been undetected and passed into service has concluded that action is required to reduce the risk of failure. It was therefore necessary to reduce the life limit. The HP compressor stage 1 disc is part of the HP compressor stage 1-4 shaft, P/N FK32580. We are issuing this AD to prevent failure of the HP compressor stage 1 disc, uncontained engine failure, and damage to the airplane.

Unless already done, do the following actions. Multiple Flight Profile Monitoring Parts (1) For RB211-Trent 800 series engines being monitored by “Multiple Flight Profile Monitoring,” remove the HP compressor stage 1-4 shaft, P/N FK32580, before accumulating 5,580 standard duty cycles (SDC) since-new or within 960 SDC from the effective date of this AD, whichever occurs later. Heavy Flight Profile Parts (2) For RB211-Trent 800 series engines being monitored by “Heavy Flight Profile,” remove the HP compressor stage 1-4 shaft, P/N FK32580, before accumulating 5,280 flight cycles since new or within 860 flight cycles from the effective data of this AD, whichever occurs later. FAA Differences (f) We have found it necessary to not incorporate the June 4, 2008 compliance date which is in EASA AD 2010-0087, dated May 5, 2010 (corrected May 6, 2010). We also updated the compliance times in the AD based on a more recent assessment of the unsafe condition. Alternative Methods of Compliance (AMOCs) (g) 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) Refer to EASA Airworthiness Directive 2010-0087, dated May 5, 2010 (corrected May 6, 2010), and Rolls-Royce plc Alert Service Bulletin No. RB.211-72-AF825, Revision 3, dated August 25, 2009 for related information. Contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ, telephone: 011-44-1332-242424; fax: 011-44-1332-245418; or e-mail via: http://www.rolls-royce.com/contact/civil_team.jsp, for a copy of this service information. (i) 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; telephone (781) 238-7143; fax (781) 238-7199, for more information about this AD. Issued in Burlington, Massachusetts, on April 25, 2011. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011-10520 Filed 5-2-11; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. Multiple Flight Profile Monitoring Parts (1) For RB211-Trent 800 series engines being monitored by “Multiple Flight Profile Monitoring,” remove the HP compressor stage 1-4 shaft, P/N FK32580, before accumulating 5,580 standard duty cycles (SDC) since-new or within 960 SDC from the effective date of this AD, whichever occurs later. Heavy Flight Profile Parts (2) For RB211-Trent 800 series engines being monitored by “Heavy Flight Profile,” remove the HP compressor stage 1-4 shaft, P/N FK32580, before accumulating 5,280 flight cycles since new or within 860 flight cycles from the effective data of this AD, whichever occurs later. FAA Differences (f) We have found it necessary to not incorporate the June 4, 2008 compliance date which is in EASA AD 2010-0087, dated May 5, 2010 (corrected May 6, 2010). We also updated the compliance times in the AD based on a more recent assessment of the unsafe condition. Alternative Methods of Compliance (AMOCs) (g) 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) Refer to EASA Airworthiness Directive 2010-0087, dated May 5, 2010 (corrected May 6, 2010), and Rolls-Royce plc Alert Service Bulletin No. RB.211-72-AF825, Revision 3, dated August 25, 2009 for related information. Contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ, telephone: 011-44-1332-242424; fax: 011-44-1332-245418; or e-mail via: http://www.rolls-royce.com/contact/civil_team.jsp, for a copy of this service information. (i) 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; telephone (781) 238-7143; fax (781) 238-7199, for more information about this AD. Issued in Burlington, Massachusetts, on April 25, 2011. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011-10520 Filed 5-2-11; 8:45 am] BILLING CODE 4910-13-P