E ASA AD No.: 2013

- 0155

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

. : 2013

- 0155

Date: 18 July 201 3

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 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 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

- 535 and Trent 700 engines

TCDS Number s : United Kingdom No. 1044 and EASA.E.042

F oreign AD: Not applicable

Supersedure: None



### ATA 72 Engine

– High Pressure / Intermediate Pressure Turbine Discs

– Identification / Replacement

Manufacturer(s): Rolls

- Royce plc

Applicability: RB211

- 535E4

- 37, E4

- B

- 37 and E4

- C

- 37 engines, all serial numbers. These engines are known to be installed on, but not limited to, Boeing 757 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.

Reason: During a recent inspection of a high pressure (HP) turbine disc forged by a specific supplier, the disc was found to be contaminated with a steel inclusion, due to an inadequate cleaning procedure in the operation of the melt furnace, following a steel melt. Analysis of melt and inspection data concluded that all discs manufa ctured from the batch of material in which this steel inclusion was found, had a significant risk of containing steel inclusions. Rolls

- Royce has carried out an analysis of the effect of the steel inclusions on the Declared Safe Cyclic Lives (DSCL) of the affected HP and intermediate pressure (IP) turbine discs. This analysis concluded that the currently published DSCL cannot be supported for several discs containing the subject inclusions.
This condition, if not corrected, could lead to an uncontained HP o r IP turbine disc failure, possibly resulting in damage to, and reduced control of, the aeroplane.
For the reasons described above, this AD requires removal from service of certain HP and IP turbine discs before their accumulated cyclic lives have reached the revised limits.

Effective Date: 01 August 2013E ASA AD No.: 2013

- 0155

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 Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously:
(1) Within 30 days after the effective date of this AD, determine whether a HP or IP turbine disc, as identified by Part Number (P/N) and serial number (s/n) in Appendix 1 of this AD, is installed on the engine and, if so, determine the accumulated flight cycles (FC) since new for each affected HP or IP turbine disc as applicable.
(2) If , as a result of th e determination as required by paragraph (1) of this AD, the accumulated cyclic life since new of an affected HP or IP turbine disc is equal to or exceeds the applicable reduced cyclic life limit as specified in Appendix 1 of this AD, before next flight, r eplace the affected HP or IP turbine disc with a serviceable part in accordance with the instructions of Rolls

- Royce Non

- Modification Service Bulletin (NMSB) RB.211

- 72

- AH215 or NMSB RB.211

- 72

- AH152 Revision 1, as applicable.
(3) If, as a result of the dete rmination as required by paragraph (1) of this AD, the accumulated cyclic life since new of an affected HP or IP t urbine d isc is less than the applicable reduced cyclic life limit as specified in Table 1 of this AD, before exceeding the applicable reduced cyclic life limit as specified in Appendix 1 of this AD, replace th e affected HP or IP t urbine d isc with a serviceable disc in accordance with the instructions of Rolls

Royce NMSB RB.211

- 72

- AH215 or NMSB RB.211

- 72

- AH152 Revision 1, as applicable

. (4) From the effective date of this AD , do not install a HP or IP turbine disc having a P/N and s/n as listed in Appendix 1 of this AD, unless it has been determined that the total accumulated cyclic life since new of the component is less than the applicable reduc ed cyclic life limit as specified in Appendix 1 of this AD

.

Ref. Public ations: Rolls

- Royce NMSB RB.211

- 72

- AH215 original issue, dated 6 December 2012.

Rolls

- Royce NMSB RB.211

- 72

- AH152 original issue, dated 28 February 2013

, or Revision 1 dated 3 July 2013.
The use of later approved revisions of these 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 23 Ma rch 2013 as PAD 13

- 0 50 for consultation until 19 April 2013 . The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred to the S afety 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.aeromanager.com , or contact Rolls

- Royce plc. Corporate Communications, 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

.E ASA AD No.: 2013

- 0155

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: Reduced cyclic lives for HP / IP Turbine Discs

Engine P/N s/n Reduced Cyclic Life Limit

RB211

- 5 35 UL39767 LDRCZ19900

11 400 FC

UL39767 LDR CZ19903

UL39767 LDRCZ19904

Trent 700 FK26893 LDRCZ 19901

8 687 FC (see Note) FK26893 LDRCZ2008 1

FK26893 LDRCZ2008 2

FK26893 LDRCZ2008 4

FK26893 LDRCZ2008 8

FK26893 LDRCZ200 89

FK26893 LDRCZ200 90

FK26893 LDRCZ200 93

FK26893 LDRCZ200 94

FK26893 LDRCZ200 97

FK26893 LDRCZ20 099

FK26893 LDRCZ20 100

FK20795 or
FW53118 LDREB12176

9 270 FC (see Note) FK20795 or
FW53118 LDREB1217 7

FK20795 or
FW53118 LDREB1217 8

FK20795 or
FW53118 LDREB1217 9

FK20795 or
FW53118 LDREB121 80

Note: If maximum approved cyclic life of an affected HP or IP turbine disc, as specified in the latest issue of the applicable Time Limits Manual (TLM) , is lower than the applicable cyclic life limit specified in Appendix 1 of th is AD , the disc must be removed before exceeding the applicable TLM limit

.