EASA AD No: 2012

- 0 145

CAP.0011 0

- 001 © 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

. : 2012

- 0145

Date: 06 August 201 2

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 EC 1702/2003, Part 21A.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 900 engines

TCDS Number : EASA.E.0 12

F oreign AD : Not applicable

Supersedure : None



### ATA 72 Engine

– Low Pressure Turbine Shaft and Bearing Housing End Cover

– Inspection / Replacement

Manufacturer(s): Rolls

- Royce plc

Applicability: RB211 Trent 970

- 84, 970B

- 84, 972

- 84, 972B

- 84, 977

- 84, 977B

- 84 and 980

- 84 engines, all serial numbers. These engines are known to be installed on, but not limited to, Airbus A380 aeroplanes.

Reason: During a revenue service flight, a Trent 900 engine experienced a high Intermediate Pressure ( IP/ N2) vibration fault along with several other fluctuating engine parameters, including Low Pressure ( LP/ N1) faults. The flight crew decided to throttle back the engine to idle and performed an air turn back

. The other engines continued to operate normally and an uneventful landing was made

. The results of a n initial investigation revealed that the LP system was seized

. Removal of the Low Pressure Turbine (LPT) b earing h ousing e nd c over revealed that the oil transfer tube assembly had fractured because the spherical seat between the o il t ransfer t ube and the e nd c over was missing (not installed ).
Th is non

- conformity caused the fracture of the oil transfer tube
, leading to reduced oil flow and subsequent damage to the LP and IP bearings . Rolls

Royce has identified that other Trent 900 engines could potentially be affected. This condition, if not detected and corrected, could lead to LP location bearing damage which could result in uncon tained engine failure and su bsequentEASA AD No: 2012

- 0 145

CAP.0011 0

- 001 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet

. damage to the aeroplane

. For the reason s described above, this AD requires an inspect ion for the presence of the spherical seat plate between the o il t ransfer t ube and the LPT b earing h ousing e nd c over and
, depending on findings, replacement of the LP T shaft and bearing housing end c over

.

Effective Date: 13 August 2012

Required A ction(s) and Compliance Time(s) : R equired as indicated, unless accomplished previously : ( 1 ) Within the compliance time specified in Table 1 of this AD, as applicable , i nspect the LPT s haft and b earing h ousing e nd c over assembly P art Number (P /N ) FW22780 for conformity and presence of the spherical seat ( P/N CU38971 ) in accordance with the instructions of paragraph 3 of Rolls

- Royce Alert Non

- Modification Service Bulletin ( NMSB ) RB.211

- 72

- AH051
, or NMSB RB.211

- 72

- H 056 , as applicable to engine s/n.
Table 1

Affected e ngine s, on the effective date of this AD Compliance time

Engine s/n listed in paragraph 1.A of Alert NMSB RB.211

- 72

- AH051 and i nstalled on an aeroplane within 20 engine cycles after the effective date of this AD

E ngine s /n listed in paragraph 1.A of NMSB RB.211

- 72

- H 056 and installed on an aeroplane within 200 engine cycles after the effective date of this AD

All engines i n shop b efore release to service of the engine

( 2 ) If , during the inspection as required by paragraph (1) of this AD, a discrepancy is found
, before n ext flight
, replace the LP T s haft and b earing h ousing e nd c over assembly P/N FW22780 with a serviceable part in accordance with the instructions of paragraph 3 of Rolls

- Royce Alert NMSB 72

- AH051
, or NMSB RB.211

- 72

- AH056 , as applicable to engine s/n

. ( 3 ) Inspection s and replacements accomplished before the effective date of this AD, in accordance with the instructions of Rolls

- Royce Technical Variance TV125436
, are acceptable for compliance with the requirements paragraphs (1) and (2) of this AD. ( 4 ) From the effective date of this AD, do not inst all a LPT b earing h ousing
e nd c over assembly P/N FW22780 on a n engine, or an engine with a LPT b earing h ousing e nd c over assembly P/N FW22780 installed o n an aeroplane, unless it has been determined that the assembly is conform and the spherical seat P/N CU38971 is installed in that LPT b earing h ousing e nd c over assembly

.

Ref. Publications: Rolls

- Royce Alert NMSB RB.211

- 72

- AH051 initial i ssue dated 03 August 2012

. Rolls

- Royce NMSB RB.211

- 72

- H 056 initial issue dated 03 August 2012 The use of later approved revisions of th e s e document s is acceptable for compliance with the requirements of this AD.EASA AD No: 2012

- 0 145

CAP.0011 0

- 001 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet

. Remarks : 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.

2. Based on the 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 A D 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.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

, D E 24 8BJ, The United Kingdom. Telephone : +44 (0) 1332 242424, or email from http://www.rolls

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

.