E ASA AD No.: 20 14

- 0086

TE. CAP.0011 0

- 00 3 © 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

- 0086

Date: 11 April 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 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 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 desi gnation(s):
RB211 Trent 500 e ngines

TCDS Number: E.060

F oreign AD: N ot applicable

Supersedure: N one



### ATA 73 Engine Fuel and Control

– Engine Electronic Controller

– Modification / Replacement

Manufacturer(s): Rolls

- Royce plc (RR)

Applicability: 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 series aeroplanes.

Reason: Investigation carried out by RR has identified the risk of fan flutter during ground maintenance running
, which indicated the need to introduce a fan flutter Keep Out Zone (KOZ). In addition, following Intermediate Pressure (IP) turbine overspeed events experienced on other Trent series engi nes, the need to introduce a protection against IP shaft failures in the event of an internal engine fire was identified. Fan flutter may result in multiple fan blade failures and consequent release of uncontained high energy debris. An unprotected IP sha ft failure may result in IP turbine overspeed, IP turbine burst and
, ultimately
, release of uncontained high energy debris. These conditions, if not corrected, could result in damage to, and reduced control of, the aeroplane. To address these potentially un safe conditions, RR developed improved Engine Electronic Controller ( EEC ) software that provides a fan flutter KOZ as well as a protection against IP shaft failures.
For the reasons described abo ve, this AD requires the introduction of the improved EEC software , either by modification (software upload) of the current EEC, or replacement with an EEC that contains the improved software

.
Effective Date: 18 April 2014E ASA AD No.: 20 14

- 0086

TE. CAP.0011 0

- 00 3 © 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: (1) Within 3 months or 200 flight cycles, whichever occurs first after the effective date of this AD
, modify the engine by install ing software standard L.6.1.2 in the EEC, or by replacing the EEC with a unit that contains software standard L.6.1.2
, in accordance with the instructions of RR Service Bulletin (SB) RB

. 211

- 73

- AH531

. (2) After modification of an engine as required by paragraph (1) of this AD, do not install an EEC o n that engine , or install EEC software
, as applicable, unless t he software standard is L.6.1.2 , or a later standard approved by EASA, or approved under RR DOA

.
Ref. Public ations: RR SB RB.211

- 73

- AH531 original issue, dated 15 January 2014 , or Revision 1 dated 7 March 2014

. The use of later approved revisions of th i s document 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. 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 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 t his 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, Uni ted 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

.