EASA AD No.: 2014-0086

TE.CAP.00110-003 © 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.: 2014-0086

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 operate 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: E.060

Foreign AD: Not applicable

Supersedure: None

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 engines, 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 shaft 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 unsafe 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 above, 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 2014
EASA AD No.: 2014-0086

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

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 3 months or 200 flight cycles, whichever occurs first after the 

effective date of this AD, modify the engine by installing 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 on that engine, or install EEC software, as applicable, 

unless the software standard is L.6.1.2, or a later standard approved by 

EASA, or approved under RR DOA.

Ref. Publications: 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 this 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 

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, DE24 8BJ, 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.