E ASA AD No.: 2012

- 0051

EASA Form 110 Page 1 / 2 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 201 2

- 0051

Date: 26 March 201 2

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 Eur opean 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 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, P art M.A.303] or agreed with the Authority of the State of Registry [EC 216 / 2008 , 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

F oreign AD: Not appli cable

Supersedure: None



### ATA 72 Engine

– Critical Parts

– Life Limit Reduction

Manufacturer(s): Rolls

- Royce plc

Applicability: RB211 Trent 895

- 17, 892

- 17, 892B

- 17, 884

- 17, 884B

- 17, 877

- 17 and 875

- 17 engines, all serial numbers

. These engines are kn own to be installed on, but not limited to
, Boeing 777 series aircraft

.
Reason: Flight P rofiles (FP) define the limits of engine operation within which the engine will qualify for use of an associated set of Critical Parts life limits. The Rolls

- Royce (RR) RB2 11 Trent 800 engine previously had seven such FP s and associated sets of life limits published in the RR Time Limits Manual

. However
, the results of a recent review of operational f light data determined that the existing FP s do not encompass the full range of Trent 800 operation s

. To account for the consequent increased rate of fatigue life usage on the life limited Critical Parts
, a new FP and associated set of reduced life limits for C ritical P arts ha v e been developed, defined as FP 'MAX', that defines a new level of operation which is outside the 'HEAVY' F P, previously the most arduous.
Failure to account for the increased rate of fatigue life usage associated with FP ‘MAX’ may result in Critical Part failure, consequent release of high energy debris , damage to the aeroplane and/or injury to occupants. For the reasons described above, this AD requires the implementation of the FP ‘MAX’ into the life usage monitoring/recording processes for engines that are, or have been
, operated outside the ‘ HEAVY ’ FP limits

.

Effective Date: 09 April 201 2E ASA AD No.: 2012

- 0051

EASA Form 110 Page 2 / 2 Required A ction(s) and Compliance Time(s) : Required as indicated , unless accomplished previously: (1) Within 30 calendar days after the effective date of this AD, determine whether the engine is currently operating, or has previously been operated, beyond the 'HEAVY' F P

. (2) If , as a result of the action required by paragraph (1) of this AD, it is established that the engine has been or is currently operat ed beyond the 'HEAVY' FP, within 30 calendar days after the effecti ve date of this AD,
re
- calculat e the current life of each life limited Critical Part for the engine
, assign the appropriate life limit to each part in accordance with the instructions of Section 3 of Rolls

- Royce Alert Non Modification Service Bulletin ( NM SB ) 72

- AG801 and thereafter, before each affected part exceeds its life limit, replace it with a serviceable part

. (3) From the effective date of this AD, do not operate an engine beyond the ‘HEAVY’ FP, unless in compliance with the requirements of paragra ph (2) of this AD.

Ref. Public ations: Rolls

- Royce Alert NMSB RB211

- 72

- A G 8 01 dated 8 December 2011

. The use of later approved revisions of this document is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriate ly substantiated
, EASA can approve Alternative Methods of Compliance for this AD.
2. The required actions and the risk assessment have granted the issuance of a Final AD with Requests for Comments, postponing the public consultation process after publication.
3. Enquiries regarding this A D 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 t his AD, please contact: Rolls

- Royce plc. P

. O

. Box 31, Derby, DE24 8BJ, T he United Kingdom. Telep hone: +44 (0) 1332 242424, Fax: +44 (0) 1332 249936. Email: tech.help@rolls

- royce.com or download the publication from https://www.aeromanager.com

.