EASA AD No.: 2012-0120

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0120

Date: 04 July 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].

Design Approval Holder’s Name :

Rolls-Royce plc

Type/Model designation(s) :

RB211 Trent 800 Engines

TCDS Number: United Kingdom No. 1051

Foreign AD: Not applicable

Supersedure: None

ATA 73 Engine – Intermediate Pressure (IP) Turbine Disc – Identification / 

Inspection / Replacement

Manufacturer(s): Rolls-Royce plc

Applicability: RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17 and 895-17

engines, all serial numbers.

These engines are known to be installed on, but not limited to, Boeing 777 

series aeroplanes.

Reason: The inspection of several IP turbine discs at past engine overhauls identified the 

presence of steel inclusions in these parts. Further investigation concluded that 

all affected parts were manufactured from Waspalloy billets produced before 

1997 at a certain supplier who also melted steel in the same furnaces. Initial 

engineering evaluation concluded that the lives of the parts would not be 

affected by the presence of the said steel inclusions. This evaluation has been 

recently repeated, utilising improved structural analysis, and it is now concluded 

that the currently published lives of the components cannot be supported for 

some discs with a steel inclusion.

This condition, if not corrected, could lead to an uncontained IP turbine disc 

failure, possibly resulting in damage to, and reduced control of, the aeroplane.

For the reasons described above, this AD requires replacement of certain IP 

turbine discs.

This AD also prohibits (re)installation of certain IP turbine discs on an engine. 

Effective Date: 18 July 2012
EASA AD No.: 2012-0120

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) During the next engine shop visit after the effective date of this AD where 

the Module 05 is removed from the engine or, in case that, on the effective 

date of this AD, an engine happens to be in such a shop visit, inspect the IP 

turbine disc installed on the engine to identify the serial number (s/n).

(2) If, during the inspection as required by paragraph (1) of this AD, it is 

identified that a turbine disc is installed with a s/n as listed in Table 1 of this 

AD, accomplish one of the following actions, as applicable, in accordance 

with the instructions of Rolls-Royce RB211 Trent 800 Series Propulsion 

Systems Non-Modification Service Bulletin (NMSB) RB211-72-AG795

(hereafter referred to as the NMSB):

(2.1) If the IP turbine disc accumulated life exceeds 9 700 engine cycles, 

before returning the engine to service, replace the IP turbine disc with 

a serviceable part, in accordance with the instructions of the NMSB.

(2.2) If the accumulated life of the IP turbine disc is below the 9 700 engine 

cycles threshold, before the IP turbine disc exceeds that threshold,

replace the IP turbine disc with a serviceable part, in accordance with 

the instructions of the NMSB.

Table 1 – Affected IP Turbine Discs

IP turbine disc s/n

ADREB 73 ADREB 85 ADREB 92

ADREB 79 ADREB 86 ADREB 94

ADREB 80 ADREB 87 ADREB 96

ADREB 81 ADREB 88 ADREB 102

ADREB 82 ADREB 89 ADREB 103

ADREB 83 ADREB 90 ADREB 104

ADREB 84 ADREB 91

(3) From the effective date of this AD, do not install on any engine an IP turbine 

disc with a s/n as listed in Table 1 of this AD, except in accordance with the 

requirements of this AD.

Ref. Publications: Rolls-Royce RB211 Trent 800 Series Propulsion Systems NMSB RB211-72-

AG795, dated 28 October 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. This AD was posted on 04 June 2012 as PAD 12-058 for consultation until 

02 July 2012. No comments were received during the consultation period.

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, or contact at Rolls-Royce plc. Corporate 

Communications, P.O. Box 31, Derby, DE24 8BJ, United Kingdom,

telephone: +44 (0) 1332 242424, or send an e-mail through http://www.rollsroyce.com/contact/civil_team.jsp identifying the correspondence as being 

related to Airworthiness Directives.