EASA AD No.: 2012-0247

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.: 2012-0247

Date: 20 November 2012

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 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 72 Engine – Low Pressure Compressor Blades – Inspection / 

Replacement

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: Low Pressure (LP) compressor partial aerofoil blade release events have 

occurred in service on RR Trent 700 engines. While primary containment of the 

released sections has been achieved in each case, some of the releases did 

exhibit secondary effects that are considered to present a potential hazard. 

Previously, expeditious actions by RR have mitigated the risks presented by 

these effects, by removal from service of batches of LP compressor blades. 

However, some causal factors still exist that are not fully understood.

This condition, if not detected and corrected, could lead to LP compressor 

blade release with possible consequent loss of the engine nose cowl, under 

cowl fires and forward projection of secondary debris, possibly resulting in 

damage to the aeroplane and/or injury to persons on the ground.

To mitigate the risk of further partial fan blade release events, RR issued NonModification SB (NMSB) RB.211-72-G872, providing instructions for an

ultrasonic inspection of the affected LP compressor blades to detect subsurface anomalies in the aerofoil and, depending on findings, replacement of 

LP compressor blades.

For the reasons described above, this AD requires a one-time inspection of the 

affected LP compressor blades.
EASA AD No.: 2012-0247

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.

This AD is considered an interim measure and further AD action is likely.

Effective Date: 04 December 2012

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) For LP Compressor blades that, on the effective date of this AD, have 

accumulated or exceeded 2 500 flight cycles (FC) since new, or since 

inspection in accordance with RR NMSB RB.211-72-G702, or since inshop ultrasonic inspection in accordance with the Engine Manual, replace

each LP compressor blade (either on-wing or in-shop) with a serviceable 

blade, within 500 FC or 10 months, whichever occurs first after the 

effective date of this AD, in accordance with the instructions of Section 3 of 

RR NMSB RB.211-72-G872, and accomplish an ultrasonic inspection on 

the removed LP compressor blades.

(2) From the effective date of this AD, do not install on an engine any LP 

compressor blades that have been removed as required by paragraph (1) 

of this AD, unless the LP compressor blades have passed the ultrasonic

inspection in accordance with the instructions of Section 3 of RR NMSB 

RB.211-72-G872.

Ref. Publications: Rolls-Royce NMSB RB.211-72-G702 dated 23 May 2011.

Rolls-Royce NMSB RB.211-72-G872 dated 2 April 2012, or Revision 1

dated 2 July 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. 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, 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.