E ASA AD No.: 20 14

- 02 5 0

TE. CAP.0011 0

- 00 4 © 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 14
- 02 5 0

Date: 19 N o vem ber 2014

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 7 48 /20 12 , 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

- 5 24 engines

TCDS Number: U nited K ingdom No. 1043

F oreign AD: N ot applicable Supersedure: None



### ATA 7 2 Engine

– High Pressure Turbine Blade s – Replacement (Life Limitation)

Manufacturer(s): Rolls

- Royce plc (RR) Applicability: RB211

- 524B4

- 02, RB211

- 524C2

- 19 and RB211

- 524D4

- 19 engines , all serial numbers, except those that embod y RR Modification (MOD) 72

- 7730 in production, o r were modified in service in accordance with RR Service Bulletin (SB) RB.211

- 72

- 7730

. These engines are known to be installed o n, but not limited to, Lockheed Martin Corporati on L

- 1011 (TriStar) series and Boeing 747 series aeroplanes.
Reason: There were a number of pre - MOD/ SB 72

- 7730 High Pressure Turbine (HPT) blade failures , with some occurring within a relatively short time

. Engineering analysis carried out by R R on those occurrences indicates that certain pre MOD/ SB 72

- 7730 blades , Part Number (P/N) UL32958 and P/N UL21691 ( hereafter referred to as ‘affected HPT blade’ ), with an accumulated life of 6 500 flight hours (FH) since new or more , have an increased risk of in

- service failure. This condition, if not corrected, could lead to HPT blade failure, release of debris and consequent ( partial or complete ) loss of engine power, possibly resulting in reduced control of the aeroplane. To address this potentially unsafe condition, R R issued Alert Non

- Modification Service Bulletin (NMSB) RB

. 211

- 72

- AH789 to introduce a life limit for the affected pre - MOD/ SB 72

- 7730 HPT blades. For the reasons described above, this AD requires implementation of the reduced life limit and replacement of the affected HPT blades that have already reached or exceeded the reduced life

. Effective Date: 0 3 December 2014E ASA AD No.: 20 14

- 02 5 0

TE. CAP.0011 0

- 00 4 © 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 : Note 1 : 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 referen ces for the purpose of this AD. (1) Within 2 months after the effective date of this AD , or before exceeding 6 500 FH accumulated by an affected HPT blade since first installation on an engine , whichever occurs later, replace each affected HPT blade with a serviceable blade in accordance with the instructions of RR NMSB RB.211

- 72

- AH789. An affected blade where the accumulated FH cannot be determined must be replaced with a serviceable blade (see Note 2 ) within 2 months after the effective date of this AD. Note 2 : For the purpose of this AD, a serviceable blade is one that is an affected blade that has not exceeded 6 500 FH since first installation on an engine , or a blade which is not an affected blade. (2) From the effective date of this AD, it is allowed to install an affected HPT blade on engine, or an engine with an affected HPT blade on an aeroplane, provided the blade is a service able blade (see Note 2 ) and, following installation, the affected HPT blad e is replaced before exceeding 6 500 FH since first installation on an engine

. Ref. Public ations: Rolls

- Royce NMSB RB

. 211

- 7 2

- AH789 original issue dated 13 June 2014

. Rolls

- Royce SB RB.211

- 72

- 7730 original issue dated 17 June 1994. 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 2 0 Oct o ber 2014 as PAD 14

- 1 5 3 for consultation until 17 November 2014

. No comments were received during the consultation peri o d

. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification Directorate, EASA. E

- mail: ADs@easa.europa.eu

. 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 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

- royce.com/contact/civil_team.jsp identifying the correspondence as being related to airworthiness directives

.