EASA AD No: 2012-0220

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0220

Date: 22 October 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 900 engines

TCDS Number : EASA.E.012

Foreign AD : Not applicable

Supersedure: None

ATA 72 Engine – Low Pressure Turbine Disc Seal Fins and Interstage 

Seals – 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: Following a revenue service flight, a Trent 900 engine experienced increased 

low pressure vibration. The vibration did not exceed any engine limits, and the 

engine was not shut down during flight. Upon post-flight inspection of the 

engine, debris was found in the exhaust tail pipe and the engine was removed. 

The results of a subsequent strip inspection revealed that the stage 2 Low 

Pressure Turbine (LPT) disc had suffered material loss from a portion of the 

Interstage Seal (ISS) area of the disc, with impact damage to downstream LPT 

stages. All debris was contained within the engine casings.

Preliminary findings show that the ISS fin had rubbed into the stage 2 vane 

honeycomb seal, which overheated and cracked, finally resulting in releasing a 

portion of the ISS area of the disc.

This condition, if not detected and corrected, could lead to LPT stage 2 disc 

cracks, possibly resulting in an uncontained engine failure and subsequent 

damage to the aeroplane.

For the reasons described above, this AD requires on-wing inspections of LPT 

disc seal fins and interstage seals, each time it has been determined that the

Engine Health Monitoring (EHM) vibratory levels have been exceeded in flight, 
EASA AD No: 2012-0220

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and in-shop inspections of the LPT disc seal fins and interstage seals, to 

detect cracks or damage and, depending on findings, the accomplishment of 

applicable corrections action(s).

This AD is considered an interim measure and further AD action may follow.

Effective Date: 05 November 2012

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplish previously:

(1) From the effective date of this AD, accomplish the following actions:

(1.1) Within 10 engine flight cycles (EFC) following receipt of an Engine 

Health Monitoring (EHM) notification for N1 vibration levels 

exceeding the alert limits during flight (see Note 1), perform 

trouble shooting to determine vibration indication fault or high 

vibration, in accordance with the Airbus A380 Trouble Shooting 

Manual (TSM) Task 77-00-00-810-803-A, paragraph 2 - Fault 

Confirmation.

If it cannot be confirmed that the vibration increase has been 

caused by an indication fault, inspect the LPT disc seal fins and 

interstage seals in accordance with the instructions of Rolls-Royce 

Technical Variance (TV) 125060, or in accordance with the 

instructions of the relevant Aircraft Maintenance Manual (AMM) 

Chapter (see Note 2).

Note 1: Rolls-Royce Operational Service Desk (OSD) automatically receives, 

monitors and analyses EHM data, and will send a notification as shown in 

Appendix 1 of this AD.

Note 2: The instructions contained in TV125060 are expected to be 

incorporated in an upcoming Revision of the Airbus A380 AMM.

(1.2) For operators who are not using the Rolls-Royce EHM service, 

within 200 EFC after the effective date of this AD and thereafter, at 

intervals not to exceed 200 EFC, inspect the LPT disc seal fins 

and interstage seals in accordance with the instructions of RollsRoyce TV125060, or in accordance with the instructions of the 

relevant AMM Chapter (see Note 2).

(2) From the effective date of this AD, each time the engine is subject to a 

“Engine Check and Repair Shop Visit” or “Engine Refurbishment Shop 

Visit” in accordance with Trent 900 Generic Engine Management 

Programme (EMP) paragraph 5.3.1 Engine Rework Definitions, or if the 

engine is in such a shop visit on the effective date of this AD, inspect the 

LPT disc seal fins and interstage seals in accordance with the 

instructions of Rolls-Royce Alert Non-Modification Service Bulletin 

(NMSB) RB.211-72-AH054. If, during this inspection, any crack or 

material loss from the disc seal fin is found, before release to service of 

the engine, replace the affected parts with serviceable parts.

(3) Inspections and corrective actions, accomplished before the effective 

date of this AD, in accordance with the instructions of Rolls-Royce 

TV125658 are acceptable for compliance with the initial requirements of 

paragraphs (1.2) and (2) of this AD.

(4) If, during any inspection as required by paragraph (1.1) or (1.2) of this 

AD, as applicable, any crack or material loss from the disc seal fin is 

found, before next flight, remove the engine from the aeroplane and, 

before release to service of the engine, replace the affected parts with 

serviceable parts.

(5) Corrective actions, as required by paragraphs (2) or (4) of this AD, as 

applicable, do not constitute terminating action for the repetitive 

inspections required by paragraphs (1) and (2) of this AD.
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Ref. Publications: Airbus A380 AMM and TSM.

Rolls-Royce Trent 900 Generic EMP issue 14, dated 14 September 2012.

Rolls-Royce Alert NMSB RB.211-72-AH054 dated 14 September 2012.

Rolls-Royce Technical Variance TV125060 issue 1, dated 27 July 2012.

Rolls-Royce Technical Variance TV125658 issue 2, dated 14 August 2012.

The use of later approved revisions of these documents 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 17 September 2012 as PAD 12-120 for 

consultation until 01 October 2012. 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.

Appendix 1

Notification of N1 Vibration Exceedance sent to the Operator:

Engine: [serial number, position] on aircraft [registration]

Symptoms: Change in LP Vibration

Diagnosis: High LP Vibration

Please be advised that we have observed an LP vibration increase. The 

recommended fault isolation process for High LP vibration states:

Please be aware that 1st order LP Vibration levels have exceeded the 

alert limits.

Please contact your local Rolls-Royce Representative, who in turn will 

contact the Rolls-Royce Operational Service Desk, for additional 

recommendations.

This alert is the subject of an EASA AD, and inspection of the LPT 

interstage seals may be required.