E ASA AD No.: 2012

- 0265

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 - 0265

Date: 18 De c em ber 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 desi gnation(s): RB211

- 535E4

- B

- 37 engines

TCDS Number: UK CAA TCDS No. 1044

F oreign AD: N ot applicable
Supersedure: N one



### ATA 72 Engine
– C ritical Parts
– Life Limit s

Manufacturer(s): Rolls

- Royce plc Applicability: RB211

- 535E4

- B

- 37 engines, all serial numbers. These engines are known to be installed o n, but not limited to, Boeing 75 7 series aeroplanes.
Reason: Flight Profiles (FP) define the limits of engine operation within which the engine will qualify for use of an associated set of Critical Parts l ife limits. The Rolls

Royce (RR) RB211

- 535E4

- B

- 37 engine previously had only one such FP and associated set of life limits published in the applicable RR Time Limits Manual. However, a recent review of operational flight data has revealed that some engines may have been operated beyond the currently valid datum FP

. Failure to account for the correct rate of fatigue damage associated with engine operation may lead to Critical Part failure, possibly resulting in release of high energy debris, damage to the ae roplane and/or injury to occupants. For the reason described above, this AD requires the implementation of two new flight profiles into the life usage monitoring/recording processes for engines that are, or have been, operate d outside the current FP limits , as well as the assignment of provisional life limits to the affected Critical Parts.
Effective Date: 01 January 2013E ASA AD No.: 2012

- 0265

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) Within 30 days after the effective date of this AD, establish whether the engine is now operating , or has previously been o perated , beyond the currently applicable datum FP

. Note: The currently applicable datum FP for the RB211

- 535E4

- B

- 37 engine model is identical to Flight Profile C as defined in Rolls

- Royce Alert Non

Modification Service Bulletin (NMSB) RB

. 211

- 72

- AG875. (2) If , as a result of the action required by paragraph (1) of this AD , it is determined that the engine has been , or is now, operat ed beyond the currently applicable datum FP , within 30 days after the effective date of this AD, re

- calculate the current life of each life limited Critical Part installed o n th at engine and assign the appropriate life limit to each part , in accordance with the instructions of Section 3 of Rolls

- Royce Alert NMSB RB

. 211

- 72

- AG875 and , thereafter , rep lace e ach Critical Part with a serviceable part in accordance with the criteria and the instructions provided in Section 3 of Rolls

- Royce Alert NMSB RB

. 211

- 72

- AG875. (3) From the effective date of this AD, do not operate an engine beyond the currently applicabl e FP, unless in compliance with the requirements of paragraph (2) of this AD.
Ref. Public ations: Rolls

- Royce Alert NMSB RB

. 211

- 72

- AG875 , initial issue , dated 13 De c em ber 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 content 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 you 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 identif ying the correspondence as being related to Airworthiness Directives

.