EASA AD No.: 2012-0051

EASA Form 110 Page 1/2

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0051

Date: 26 March 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 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, Part 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

Foreign AD: Not applicable

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 known to be installed on, but not limited to, Boeing 777 

series aircraft.

Reason: Flight Profiles (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) RB211 Trent 800 engine previously had seven such FPs

and associated sets of life limits published in the RR Time Limits Manual.

However, the results of a recent review of operational flight data determined

that the existing FPs do not encompass the full range of Trent 800 operations. 

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 

Critical Parts have been developed, defined as FP 'MAX', that defines a new 

level of operation which is outside the 'HEAVY' FP, 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 2012
EASA AD No.: 2012-0051

EASA Form 110 Page 2/2

Required Action(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' FP.

(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 operated beyond the 

'HEAVY' FP, within 30 calendar days after the effective date of this AD, 

re-calculate 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 (NMSB) 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 paragraph (2) 

of this AD.

Ref. Publications: Rolls-Royce Alert NMSB RB211-72-AG801 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 appropriately 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 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:

Rolls-Royce plc. P.O. Box 31, Derby, DE24 8BJ, The United Kingdom.

Telephone: +44 (0) 1332 242424, Fax: +44 (0) 1332 249936.

Email: tech.help@rolls-royce.com or download the publication from 

https://www.aeromanager.com.