E ASA AD No.: 20 12

- 02 6 6

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No
. : 20 12 - 0266

Date: 18 December 2012

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 accordance 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 requ irements 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]

. 

### Design Approval Holder’s Name: ROLLS

- ROYCE plc Type/Model designation(s): RB211

- 535 Engines

TCDS Number s : U nited Kingdom No. 1044 and No. 1049

F oreign AD: N ot applicable Supersedure: N one



### ATA 72 Engine
– Low Pressure Turbine Stage 2 Disc s – Life Limit s

Manufacturer(s): Rolls

- Royce plc Applicability: RB211

- 535E4

- 37 , RB211

- 535 E4

- B

- 37 and RB211

- 535 E4

- C

- 37 engines, all serial numbers. These engines are known to be installed o n, but not limited to, Boeing 75 7 series aeroplanes. RB211

- 535E4

- B

- 75 engines, all serial numbers. These engines are known to be ins talled on, but not limited to, Tupolev TU 204 series aeroplanes.
Reason: A recent re

- evaluation of Critical Part lives carried out by Rolls

- Royce revealed changes to the thermal profile and stresses in certain features of the low pressure turbine ( LPT ) Stage 2 d isc. These changes have resulted in a reduction of the cyclic life of the LPT stage 2 disc s. Operation of an engine equipped with a Critical P art that has exceeded its cyclic life may result in Critical Part failure, consequent release of high ene rgy debris, damage to the aeroplane and/or injury to occupants. For the reason described above, this AD requires the implementation of new provisional life limit s to the LPT stage 2 d isc s, as well as replacement of LPT stage 2 d iscs , depending on the new p rovisional life limits and other operational criteria

. Effective Date: 01 January 2013E ASA AD No.: 20 12

- 02 6 6

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) W ithin 30 calendar days after the effective date of this AD, determine the accumulated cyclic life since new of each LPT Stage 2 d isc and assign the appropriate life limit to each LPT Stage 2 d isc in accordance with the instructions of Section 3 of Rolls

- Royce Alert Non

- Modification Servic e Bulletin (NMSB) RB.211

- 72

- AH029

. (2) Following accomplishment of the actions as specified by (1) above , replace each LPT Stage 2 disc with a serviceable part within the criteria as specified in , and in accordance with the instructions of, Section 3 of Rolls

Royce Alert NMSB RB .211

- 72

- AH029

. Ref. Public ations: Rolls

- Royce A l ert NMSB RB .211

- 72

- AH029 , initial issue , dated 13 December 2012

. The use of later approved revisions of th i s 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. Based on t he required actions and the compliance time, EASA have decided to issue a Final AD with Request for Comments, postponing the public consultation process until after publication

. 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 conte nt of the requirements in this AD, please contact y our designated Rolls

- Royce representative or download the publication from your Aeromanager account at www.aeromanager.com

. If y ou do not have a designated representative or Aeromanager account, please contact Corporate Communications at Rolls

- Royce plc., PO Box 31, Derby, DE24 8BJ, The 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

.