E ASA AD No.: 20 1 5 - 0187

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No . : 20 1 5 - 0 1 87

Date: 09 September 2015 Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation. This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exempt ion]. 

### Design Approval Holder’s Name: ROLLS - ROYCE plc Type/Model designation(s): RB211 - 22 and RB211 - 5 24 engines TCDS Number s : U nited K ingdom No. 1039, 1043 , 104 6 and 104 8 F oreign AD: N ot applicable Supersedure: None 

### ATA 7 2 Engine – Low Pressure Turbine Roller Bearing – Replacement Manufacturer(s): Rolls - Royce plc (RR) Applicability: RB211 - 22B - 02, RB211 - 524B - 02, RB211 - 524B - B - 02, RB211 - 524B2 - 19, RB211 - 524B2 - B - 19, RB211 - 524B3 - 02, RB211 - 524B4 - 02, RB211 - 524B4 - D - 02, RB211 - 524C2 - 19, RB211 - 524C2 - B - 19, RB, RB211 - 524D4 - 19, RB211 - 524D4 - B - 19, RB211 - 524D4X - 19, RB211 - 524D4X - B - 19, RB211 - 524D4 - 39, RB211 - 524D4 - B - 39, RB211 - 524G2 - 19, RB211 - 524G3 - 19, RB211 - 524 - G2 - T - 19, RB211 - 524G3 - T - 19 , RB211 - 524H - 36, RB211 - 524H2 - 19, RB211 - 524H - T - 36 and RB211 - 524H2 - T - 19 engines , all serial numbers

. These engines are known to be installed o n, but not limited to, Lockheed Martin Corporation L - 1011 (TriStar) , Boeing 747 and Boeing 767 aeroplanes. Reason: An RB211 - 524G2 - T engine experienced an in - service event that resulted in breach of a turbine casing and some release of core engine debris through a hole in the engine nacelle. The investigation of the event determined the primary cause to have be en fracture and release of a Low Pressure ( LP ) turbine stage 2 blade. The blade release caused secondary damage to the LP turbine, producing significant out - of - balance forces. The event engine was fitted with an LP turbine support bearing where the roller retention cage is constructed from two halves that are riveted together. The LP turbine imbalance resulted in an overl oad of the LP turbine support bearing and caused separation of the riveted, two - piece roller retention cage. Radial location of the LP turbine shaft was lost, allowing further progression of the event that resulted in a breach of the IP turbine casing

. This condition, if not corrected, could lead to b reach of the turbine casing and release of high energy debris , possibly resulting in damage to the aeroplane and/or injury to the occupants.E ASA AD No.: 20 1 5 - 0187

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. To address this potentially unsafe condition, R R issued Alert Non - Modification Service Bulletin (NMSB) RB

. 211 - 72 - A G729 and NMSB RB.211 - 72 - AG800 to introduce a modified LP turbine support roller bearing. This modified LP turbine support roller bearing can withstand greater abnormal loads that could be generated when a turbine blade release occur, therefore preventing the failure progression as occurred during the event. For the reasons described above, this AD requires modification of the affected engines by replacing the LP turbine support roller bearing with a modified part

. Effective Date: 2 3 September 2015 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously : Note : Where, in this AD, reference is made to an RR Mod, SB or NMSB with an ‘A’ (Alert) in the number, it should be recognised that an earlier or later revision may not have that ‘A’. This kind of change does not effectively alter the publication references for the purpose of this AD. (1) Within 24 months after the effective date of this AD , replace each LP turbine support two - piece riveted cage roller bearing , Part Number ( P/N ) LK30313 or P/N UL29651 , as applicable , with a P/N FB500000 LP turbine support roller bearing in accordance with the instructions of RR NMSB RB.211 - 72 - A G729 or NMSB RB.211 - 72 - AG800, as applicable

. (2) An e ngine that emb odies RR MOD.72 - B540 in production, or has been modified in service in accordance with the instructions of RR SB RB.211 - 72 - B540 (introd uc ing P/N FB500000 LP turbine support roller bearing ), is compliant with the modification requirements of paragraph (1) of this AD, provided it is determined t hat the engine remains in that configuration

. ( 3 ) D o not to install an LP turbine support two - piece riveted cage roller bearing P/N LK30313 or P/N UL29651 on an engine , as required by paragraph ( 3 .1) or ( 3 .2) of this AD, as applicable. (3 .1) For an engine that, on the effective date of this AD, does not have a P/N FB500000 LP turbine support roller bearing installed : After modification of that engine as required by paragraph (1) of this AD. (3 .2) For an engine that, on the effective date of th is AD, has a P/N FB500000 LP turbine support roller bearing installed : From the effective date of this AD. ( 4 ) From the effective date of this AD, do not release an engine to service after a shop visit, unless that engine has a P/N FB500000 LP turbine support roller bearing installed. Ref. Public ations: Rolls - Royce NMSB RB

. 211 - 7 2 - A G 7 2 9 original issue dated 1 August 2011

. Rolls - Royce NMSB RB.211 - 72 - AG800 original issue dated 5 March 2012. Rolls - Royce SB RB.211 - 72 - B540 original issue dated 28 July 1995

. The u se of later approved revisions of th e s e document s is acceptable for compliance with the requirements of this AD. Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 06 August 2015 as PAD 15 - 1 03 for consultation until 03 September 2015. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred to the Safety Infor mation Section, Certification Directorate, EASA. E - mail: ADs@easa.europa.eu

.E ASA AD No.: 20 1 5 - 0187

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 4. For any question concerning the technical content of the requirements in this AD, please contact your designated Rolls - Royce representative or download the publication from your Aeromanager account at www.aeromanager.com . If you do not have a designated representative or Aeromanager account, please contact Co rporate Communications at Rolls - Royce plc., P.O. Box 31, Derby, DE24 8BJ, United Kingdom, telephone: +44 (0) 1332 242424, or send an e - mail through http://www.rolls - royce.com/contact/civil_team.jsp identifying the correspondence as being related to airworthiness directives

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