EASA AD No : 20 13 - 0 042

TE. CAP.0011 0 - 00 3 © 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 13 - 0 042

Date: 2 6 February 2013 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 E U 748/2012 , Part 21

. A.3B. In accordan ce with EC 2042/2003 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 [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]

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### Design Approval Holder’s Name : ROLLS - ROYCE PLC Type/Model designation(s) : RB211 - 524, Trent 500, Trent 700 and Trent 800 series Engines TCDS Numbers: EASA.E.042, EASA.E.060, United Kingdom Nos. 1046, 1048 and 1051 Foreign AD: Not applicable Supersedure: This AD supersedes EASA AD 2009 - 0073R1 dated 08 April 2009.



### ATA 72 Engine – High Pressure Compressor Rotor Discs and Rotor Shafts –

Inspection / Replacement Manufacturer(s): Rolls - Royce plc Applicability: RB211 Trent 553 - 61, 553A2 - 61, 556 - 61, 556A2 - 61, 556B - 61, 556B2 - 61, 560 - 61 and 560A2 - 61 engines, all serial numbers. These engines are known to be installed on, but not limited to, Airbus A340 series aeroplanes. RB211 Trent 768 - 60, 772 - 60, 772B - 60 and 772C - 60 engines, all serial numbers. These engines are known to be installed on, but not limited to, Airbus A330 series aeroplanes. RB211 T rent 875 - 17, 877 - 17, 884 - 17, 884B - 17, 892 - 17, 892B - 17 and 895 - 17 engines, all serial numbers. These engines are known to be installed on, but not limited to, Boeing 777 series aeroplanes. RB211 - 524G2 - T - 19, RB211 - 524G3 - T - 19, RB211 - 524H - T - 36 and RB211 - 524H2 - T - 19 engines. These engines are known to be installed on, but not limited to, Boeing 747 and 767 series aeroplanes. Reason: During manufacture of a number of high pressure compressor (HPC) Stage 1 and 2 discs with axial dovetail slots, anomalies at the disc post corners were found. Fatigue crack initiation and subsequent crack propagation at the disc post may result in failure of two blades and the disc post. This condition, if not detected and corrected, could lead to an uncontained engine failure and c onsequent release of high energy debris, possibly resulting inEASA AD No : 20 13 - 0 042

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. damage to the aeroplane and injury to occupants. To address this potential unsafe condition, EASA issued AD 2009 - 0073 (later revised) to require repetitive inspections of the axial dovetail sl ots and, depending on findings, accomplishment of the applicable corrective action(s). Since EASA AD 2009 - 0073R1 was published, the relevant Rolls - Royce (RR) Non - Modification Service Bulletin (NMSB), RB.211 - 72 - AF964, has been amended to Revision 3, adding several HPC rotor discs and - shafts, identified by Part Number (P/N) in Section 1.A of that NMSB, which also need to be inspected. For the reasons described above, this new EASA AD retains the requirements of EASA AD 2009 - 0073R1, which is superseded, and e xtends the applicability to all HPC rotor discs and HPC rotor shafts identified in Section 1.A of RR NMSB RB.211 - 72 - AF964 at Revision 3. Effective Date: 1 2 March 2013 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) For engines with a n HPC rotor disc / shaft installed with a P/N as listed in Section 1.A of RR NMSB RB.211 - 72 - AF964 Revision 3, as applicable to engine type , d uring each qualifying shop visit ( as defined in Sect ion 1.C.( 1 ) of RR NMSB RB.211 - 72 - AF964 Revision 3 ) after the part exceeds 1 000 cycles since new (CSN), inspect the axial dovetail slots in accordance with the instructions of Section 3 of RR NMSB RB.211 - 72 - AF964 Revision 3. ( 2 ) If, during any inspection a s required by paragraph ( 1 ) of this AD, discrepancies are detected, before release to service of the engine, accomplish the applicable corrective action(s) in accordance with the instructions of Section 3 of RR NMSB RB.211 - 72 - AF964 Revision 3. ( 3 ) If, on the effective date of this AD, an engine with an affected part (P/N as listed in Section 1.A of RR NMSB RB.211 - 72 - AF964 Revision 3 ) that has accumulated or exceeded 1 000 CSN is undergoing overhaul and in a condition as defined in Section 1.C.(2) of RR NMSB RB.211 - 72 - AF964 Revision 3, before release to service of the engine, inspect the axial dovetail slots and, depending on findings, accomplish the applicable corrective actio n(s) , in accordance with the instructions of Section 3 of RR NMSB RB.211 - 72 - AF964 Revision 3. (4) From the effective date of this AD, installation on an aeroplane of an engine that contains an affected part (HPC rotor disc / shaft with a P/N as listed in Sec tion 1.A of RR NMSB RB.211 - 72 - AF964 Revision 3) is allowed, provided that, after installation, that engine is inspected and, depending on findings, corrected, as required by paragraphs (1) and (2) of this AD. Ref. Publications: Rolls - Royce NMSB RB.211 - 72 - AF964 Revision 3 dated 11 January 2013. The use of later approved revisions of this document 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 21 January 2013 as PAD 13 - 0 17 for consultation until 18 February 2013

. T he Comment Response Document can be found at http://ad.easa.europa.eu

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

. 4. For any question concerning the technical content of the requirements in th is AD, please contact your designated Rolls - Royce representative or download the publication from your Aeromanager account at www.aeromanager.com .EASA AD No : 20 13 - 0 042

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. If you do not have a designated representative or Aeromanager acc ount, please contact Corporate 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 - ro yce.com/contact/civil_team.jsp identifying the correspondence as being related to Airworthiness Directives.