EASA AD No.: 2013-0190

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.: 2013-0190

Date: 20 August 2013

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 700 engines

TCDS Number: EASA.E.042

Foreign AD: Not applicable

Supersedure: None

ATA 73

Engine Fuel & Control – Engine Electronic Control – Software

Update

Manufacturer(s): Rolls-Royce plc (RR)

Applicability: 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 

aeroplanes.

Reason: An operator of an A330 aeroplane fitted with RR Trent 772B engines 

experienced an engine uncontained multiple turbine blade failure. Investigation

results showed that High Pressure/Intermediate Pressure (HP/IP) oil vent tubes 

may be affected by carbon deposit and may also be damaged by their outer 

heat shields, which in this case led to combustion inside the tube. The 

consequent chain of events resulted in an engine internal fire which caused the 

failure of the IP Turbine (IPT) disc drive arm.

This condition, if not corrected, could lead to uncontained multiple turbine blade 

failures or an HP/IP turbine disc burst, possibly resulting in damage to, and 

reduced control of, the aeroplane.

Prompted by these findings, an Intermediate Pressure Turbine Overspeed 

System (IPTOS) protection function was introduced, and subsequently required

by EASA AD 2009-0075 for Airbus A330 aeroplanes.

Since that AD was issued, following further engineering evaluation, some 

limitations have been identified and modifications have been developed to 

improve the effectiveness of the IPTOS protection function within the Engine 

Electronic Control (EEC).
EASA AD No.: 2013-0190

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.

For the reasons described above, this AD requires introduction of the enhanced

IPTOS protection function by installation of a reprogrammed EEC, which shuts 

down the engine when shaft failure is detected.

Effective Date: 03 September 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Not later than 31 December 2018, modify the engine by installing an EEC 

incorporating EEC software standard A14.1.3 in accordance with the 

instructions of Rolls-Royce Alert Service Bulletin (ASB) RB.211-73-AG829.

(2) The modification as required by paragraph (1) of this AD does not affect 

the aeroplane modifications as required by EASA AD 2009-0075. After 

installation on an aeroplane of Trent 700 engines, modified as required by 

paragraph (1) of this AD, that aeroplane remains compliant with EASA AD 

2009-0075.

(3) Installation of an EEC incorporating an EEC software standard later than 

A14.1.3 is acceptable to comply with the requirement of this AD.

(4) After modification of an engine as required by paragraph (1) of this AD, do 

not install any EEC unit on that engine, unless the software standard is 

A14.1.3 or higher.

Ref. Publications: Rolls-Royce ASB RB.211-73-AG829 dated 18 April 2012.

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. This AD was posted on 02 July 2013 as PAD 13-090 for consultation until 

30 July 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 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, 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.