E ASA AD No.: 20 13

- 0 223

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 - 0 223

Date: 19 September 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 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 operate an air craft 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 8 00 engines

TCDS Number: E ASA.E.047

F oreign AD: N ot applicable
Supersedure: None



### ATA 72 Engine

– L ow P ressure Turbine Bearing Support and Exhaust C ase

Assembly

– Inspection / Replacement

Manufacturer(s): Rolls

- Royce plc Applicability: RB211 Trent 875

- 17, 877

- 17, 884

- 17, 884B

- 17, 892

- 17, 892B

- 17 and 895

- 17 engines, all serial numbers , except those that have been reworked in accordance with Rolls

- Royce Service Bulletin (SB) RB

. 211

- 72

- G604. These engines are known to be installed on, but not limited to, Boeing 777 series aeroplanes.
Reason: Rolls

- Royce has identified that limitations in the drawing definition for the Trent 800 low pressure ( LP ) Turbine Bearing Support and Exhaust Case assembly (EIPC 72

- 52

- 51, 0 3

- 300, also known as the Tail Bearing Housing or TBH) may have resulted in thin wall section parts being delivered into service. Further analysis has concluded that under certain circumsta nces , the structural integrity of a thin walled part may be insufficient to withstand a fan blade failure event

. This condition, if not detected and corrected, could , in case of fan blade failure , lead to a loss of integrity of the TBH and leave the engine unsupported at the rear mount , possibly resulting in damage to , or reduced control of, the aeroplane

. For the reasons described above, t his AD requires identification and replacement or rework of certain known thin walled TBHs and inspection of the TBHs of all other engines

. Effective Date: 03 October 2013E ASA AD No.: 20 13

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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) At the next engine shop visit (for Serviceability, Check and Repair, Refurbishment or Overhaul ) , but not later than 30 June 2017 , whichever occurs first after the effective date of this AD , identify the Part Number (P/N) and serial number (s/n) of the TBH installed on the engine and, i f the P/N and s/n of the T BH are as listed in Appendix 1 of this AD , before release to service of the engine, r eplace the TBH with a serviceable part in accordance with the instructions of Rolls

- Royce N on - M odification S ervice B ulletin (NMSB ) RB.211

- 72

- AG644

. Note 1: Rolls

- Royce NMSB RB.211

- 72

- AG644 identifies the s/n of Modules and engines in which the affected TBH are likely installed; see Figure 7 in that document. (2) For engines that do not have a TBH installed as identified in Appendix 1 of this AD , within the compliance time specified in Table 1 of this AD, as applicable, inspect the TBH in accordance with the instructions of Section 3, Part B, of R olls

- Royce NMSB RB.211

- 72

- AG644. Table 1

– TBH Inspection Compliance Time, whichever occurs first, A, B or C

A During shop visit for those engines currently (on the effective date of this AD) in the shop where the affected part is exposed and substantial rebuild has not yet started

B At the next R efurbishment or Overhaul engine shop visit, or during any other shop visit where the module is sufficiently exposed to accomplish the inspection C Not later than 31 December 2020 (3) If, during the inspection as required by paragraph (2) of this AD, the TBH fails the inspection , before release to service of the engine, r eplace the TBH with a serviceable part

. Note 2 : A TBH that ha s been reworked in accordance with the instructions of Rolls

- Royce S ervice B ulletin (SB) RB.211

- 72

- G604 is considered a serviceable part for the purpose of the AD.
Ref. Public ations: Rolls

- Royce NMSB RB.211

- 72

- A G644 original issue dated 30 April 20 13

. Rolls

- Royce SB RB

. 211

- 72

- G604 original issue dated 18 March 2013

. The u se of later approved revisions of these documents 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 19 June 2013 as PAD 13

- 084 and republished on 2 3 August 2013 as PAD 13

- 084R1 for consultation until 06 September 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 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 , or contact at 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.: 20 13

- 0 223

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

– Part

- and Serial Numbers of TBH affected by paragraph (1) of this AD