EASA AD No : 2011-0080

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0080

Date: 06 May 2011

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an 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 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD unless other wise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption]. 

### Type Approval Holder’s Name :

ROLLS-ROYCE PLC Type/Model designation(s) :
RB211 Trent 800 engines

TCDS Number : UK CAA 1051

Foreign AD : Not applicable

Supersedure : None



### ATA 72 Engine – Front Combustion Liner Head Section – Inspection/Replacement

Manufacturer(s): Rolls-Royce plc

Applicability: Models RB211 Trent 800 series engine s, all serial numbers. These engines are known to be installed on, but not limited to, Boeing 777 series aeroplanes.

Reason: Routine inspections have revealed cracking on the head sections of two Trent 800 front combustion liners. This condition, if not detected and corrected, coul d lead to hot gas breakout with subsequent downstream component release potent ially leading to uncontained high energy debris, possibly resulting in damage to the aeroplane or injury to persons on the ground. To address this unsafe condition, EASA AD 2009-0187 R1 was issued requiring a one-time borescope inspection of the he ad section of the front combustion liner and report findings to Rolls Royce

. Rolls Royce have now defined a repetitive inspectio n programme for the RB211 Trent 800 series engines only. This programme allows crack propagation to be safely monitored during continued operation and for engines to be withdrawn from service before loss of combustion liner integrity can occur. For the reasons described above, this AD takes over the requirements of EASA AD 2009-0187R1 for the RB211 Trent 800 series engines only. It requires repetitive on-wing and in-shop inspections of the Front Combustion Liner Head Section for discrepancies and, depending on findings, corrective actions.EASA AD No : 2011-0080

EASA Form 110 Page 2/3 Effective Date: 20 May 2011

Required Action(s) and Compliance Time(s): Required as indicated, unless already accomplished: (1) ON-WING Inspections : (1.1) Within 1 000 Flight Cycles (FC) after the eff ective date of this AD and thereafter at intervals not to exceed 2 000 FC, inspect the Front Combustion Liner Head Section for cracking in accordance with the On-Wing Accomplishment Instructions of Rol ls-Royce Non-Modification Service Bulletin (NMSB) RB211-72-A G456. (1.2) If, during any inspection as required by para graph (1.1) of this AD, cracking is found, take the corrective actions as d etailed in Table 1 of this AD, as applicable.

Table 1 – Inspection Findings and Follow-on Actions
Inspection Findings Action(s) and Compliance Time(s)
Cumulative crack length up to 150 mm (up to 2 heatshields) Reduce the inspection intervals to 250 FC

Cumulative crack length 150 mm to 300mm (up to 4 heatshields) Reduce the inspection intervals to 100 FC

Cumulative crack length 300 mm to 450mm (up to 6 heatshields) Replace the engine within 50 FC

Cumulative crack length 450 mm to 900mm (up to 12 heatshields) Replace the engine within 5 FC

Cumulative crack length greater than 900 mm (more than 12 heatshields) Replace the engine before next flight

(2) IN-SHOP Inspections : (2.1) At every shop visit after the effective date of this AD, inspect the Front Combustion Liner Head Section for cracking in accordance with the In-shop Accomplishment Instructions of Rol ls-Royce NMSB RB211-72-AG456. (2.2) If any cracking is identified, before release of the engine to service, replace the Front Combustion Liner Head Section wit h a new or serviceable part. (2.3) Accomplishment of a shop visit inspection as required by paragraph (2.1) of this AD may substitute the accom plishment of an on-wing inspection as required by paragraph (1) of this AD. (3) Replacement of the Front Combustion Liner Head Section with a new or serviceable part does not constitute terminating ac tion for the repetitive inspection requirements of this AD. After replaceme nt, the requirements of this AD remain applicable.

Ref. Publications: Rolls-Royce Non-Modification Ser vice Bulletin RB211-72-AG456 dated 09 September 2010.EASA AD No : 2011-0080

EASA Form 110 Page 3/3 The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 05 April 2011 as PAD 11-03 8 for consultation until 03 May 2011. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred t o the Airworthiness Directives, Safety Management & Research Section, C ertification Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact your designated Rolls-Royce representative or download the publication from your Aeromanager acco unt at www.aeromanager.com

. If you do not have a designated representative or Aeromanager account, please contact Corporate Communications at Rolls-Royce plc. PO Box 31, Derby, DE24 8BJ, United Kingdom, telephone: +44 (0) 1332 242424, or send an e-mail t hrough http://www.rolls-royce.com/contact/civil_team.jsp identifying the correspondence as being related to Airworthiness Directives

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