EASA AD No.: 20 13

- 02 1 4

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

- 02 1 4

Date: 16 September 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 EU 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]

. 

### Design Approval Holder’s Name: ROLLS

- ROYCE plc Type/Model designation(s): RB211 Trent 500 engines

TCDS Number: EASA.E.060

F oreign AD: Not applicable

Supersedure: None



### ATA 72 Engine

– Low Pressure Compressor Blade Leading Edge Profile

–

Rework / Restoration

Manufacturer(s): Rolls

- Royce plc

Applicability: Models 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

- 500 and A340

- 600 series aeroplanes.

Reason: Erosion of the leading edge profile of Trent 500 engines’ low pressure ( LP )
c ompressor b lades is proven to contribute to fan flutter, a risk that is mitigated by regular restoration of the leading edge of these blades

. Recently, Rolls

- Royce have conducted a review re garding the in

- service restoration of the leading edge profile o f LP c ompressor b lades. Th e results of th is re view concluded that not all LP c ompressor b lades have been restored as intended. This condition, if not corrected, could lead to f an flutter
, LP c ompressor b lade cracking and uncontained LP c ompressor b lade failures , possibly resulting in damage to, and reduced control of, the aeroplane. For the reasons described above, this AD requires initial and repetitive leading edge restoration of the LP c omp ressor b lades.

Effective Date: 30 September 2013EASA AD No.: 20 13

- 02 1 4

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. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within t he compliance time as specified in Appendix 1 of this AD, as applicable, restore the leading edge profile of the engine’s LP compressor blades in accordance with the instructions of Section 3 of Rolls

- Royce (RR) Non

- Modification Service Bulletin (NMSB) RB. 211

- 7 2

- AH149
, or in accordance with the instructions of Section 3 of RR NMSB RB.211

- 72

- H464.
Note: Application of RR NMSB RB.211

- 72

- H464 is permitted only for the initial restoration of the leading edge profile of the engine’s LP compressor blades as required by paragraph (1) of this AD

. (2) Within 4000 FC after the initial leading edge profile restoration of the engine’s LP compressor blades as required by paragraph (1) of this AD
, and, thereafter, at intervals not to exceed 4 000 FC
, restore the leading edge profile of the engine’s LP compressor blades in accordance with the instructions of Section 3 of RR NMSB RB.211

- 72

- AH149. (3 ) From the effective date of this AD, installation of LP compressor blades on an engine is allowed, provid ed that, prior to or following installation, as applicable, the leading edge profile of the blades is restored, within the compliance times as required by this AD.

Ref. Public ations: Rolls

- Royce NMSB RB.211

- 7 2

- AH149 original issue, dated 0 1 March 2013.
Rolls

- Royce NMSB RB.211

- 72

- H 464 original issue, dated 28 August 2013.
The u se of later approved revisions of th ese 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 30 April 2013 as PAD 13

- 0 6 2 and republished on 03 May 2013 as PAD 13

- 062R1 for consultation until 28 May 2013 . The 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 this AD, please contact your designated Rolls

- Royce representative or download the publication from your Aeromanager account at www.aeromana ger.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, o r send an e

- mail through http://www.rolls

- royce.com/contact/civil_team.jsp identifying the correspondence as being related to Airworthiness Directives

.EASA AD No.: 20 13

- 02 1 4

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. 

### Appendix 1

– Initial LP Compressor Blade (LPCB) Leading Edge Profile Restoration

Defin i tions used in the Table below: L: accumulated FC of the LPCB since new, on the effective date of this AD Lr: accumulated FC of the LPCB since the last leading edge profile restoration, on the effective date of this AD
NK: not known NO: the leading edge profile of the LPCB has never been restored before

L (FC) Lr (FC) Compliance time

< 3 75 0 NK Before exceeding 4 000 FC since new NO

< 3 75 0 Before exceeding 4 000 FC since last restoration

≥ 3 75 0 and

< 4 4 00 NK

Within 250 FC a f te r the effective date of this AD NO

≥ 3 75 0

< 3 75 0 Before exceeding 4 000 FC since last restoration

≥ 4 4 00 NK Within 100 FC a f te r the effective date of this AD NO

< 3 75 0 Before exceeding 4 000 FC since last restoration

≥ 3 75 0 and < 4 4 00 Within 250 FC a f te r the effective date of this AD

≥ 4 4 00 Within 100 FC a f te r the effective date of this AD

NK NK or NO Within 100 FC a f te r the effective date of this AD