EASA AD No.: 2012-0060

EASA Form 110 Page 1/3

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0060

Date: 18 April 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) :

RB211-524 and RB211-535 Engines

TCDS Numbers: United Kingdom No. 1046, 1048, 1044 and 1049

Foreign AD: Not applicable

Supersedure: None

ATA 73 Engine – Intermediate Pressure Turbine Disc – Identification / 

Inspection / Replacement

Manufacturer(s): Rolls-Royce plc

Applicability: RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19, RB211-524G3-T-19, 

RB211-524H2-19, RB211-524H2-T-19, RB211-524H-36 and RB211-524H-T-36 

engines, all serial numbers.

These engines are known to be installed on, but not limited to, Boeing 747 and 

Boeing 767 series aeroplanes.

RB211-535E4-37, RB211-535E4-B-37, RB211-535E4-B-75 and RB211-535E4-

C-37 engines, all serial numbers.

These engines are known to be installed on, but not limited to, Boeing 757 and 

Tupolev Tu204 series aeroplanes.

Reason: The inspection of several intermediate pressure (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 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 removal and inspection of 

certain IP turbine discs and, depending on findings, replacement with a 

serviceable part. This AD also prohibits (re)installation of certain IP turbine discs 

on an engine. 

Effective Date: 02 May 2012
EASA AD No.: 2012-0060

EASA Form 110 Page 2/3

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 for disassembly where any 

casing is removed or, in case that, on the effective date of this AD, an 

engine happens to be in such a shop visit, identify the Part Number (P/N) 

and serial number (s/n) of the IP turbine disc installed on the engine.

(2) If a turbine disc is installed with a P/N as listed in Table 1 of this AD and a 

s/n as listed in Appendix 1 (for RB211-524G and -524H series engines) or 

Appendix 2 (for RB211-535E4 series engines), as applicable, of RollsRoyce Propulsion Systems Non-Modification Service Bulletin (NMSB) 

RB211-72-AG493 Revision 1 (hereafter referred to as the NMSB), 

accomplish the following action, as applicable:

(2.1) If the accumulated life (in cycles) of the IP turbine disc exceeds the 

inspection threshold, but is below the maximum life as identified in 

the applicable Time Limits Manual, or below the maximum life as 

specified in Appendix 1 (for RB211-524G and -524H series engines) 

or Appendix 2 (for RB211-535E4 series engines) of the NMSB, as 

applicable, remove the IP turbine disc from the engine and 

accomplish an inspection in accordance with the instructions of 

Section 3 of the NMSB.

(2.2) If the accumulated life (in cycles) of the IP turbine disc is below the 

inspection threshold, before the IP turbine disc exceeds that 

inspection threshold, remove the IP turbine disc from the engine and 

accomplish an inspection in accordance with the instructions of 

Section 3 of the NMSB.

Note 1: As an alternative to the inspection required by paragraph (2.1) or (2.2) of 

this AD, as applicable, it is acceptable to replace the removed IP turbine disc 

with a serviceable part.

Table 1 – Affected IP Turbine Discs

Engine type IP turbine disc P/N

RB211-524G and 

RB211-524H series 

engines

LK82335

UL27958

UL37681

UL37721

RB211-524G-T and 

RB211-524H-T 

series engines

UL38383

UL38384

UL38467

UL38929

UL38930

RB211-535E4

series engines

UL17774

UL19818

UL27940

Note 2: A typographical error has been identified in Appendix 4 “SQUID 

inspection of RB211 IP Turbine Disc QCTP” of Rolls-Royce Propulsion Systems 

NMSB RB211-72-AG493 Revision 1, dated 11 November 2011. Part reference 

UL82335 should read LK82335, as in Table 1 of this AD.
EASA AD No.: 2012-0060

EASA Form 110 Page 3/3

(3) If the results of an inspection as required by paragraph (2) of this AD do not 

meet the criteria as detailed in Appendix 4 of the NMSB, or if the affected IP 

turbine disc has reached or exceeded its life limit, as specified in Appendix 

1 (for RB211-524G and -524H series engines) or Appendix 2 (for RB211-

535E4 series engines) of the NMSB, as applicable, before returning the 

engine to service, replace the disc with a serviceable part.

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

disc with a P/N as listed in Table 1 of this AD and a s/n as listed in 

Appendix 1 or Appendix 2 of the NMSB, as applicable to engine model, 

except in accordance with the inspection and replacement requirements of 

this AD.

Ref. Publications: Rolls-Royce Propulsion Systems NMSB RB211-72-AG493 Revision 1,

dated 11 November 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 01 February 2012 as PAD 12-007 for consultation 

until 29 February 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, 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.rolls-royce.com/contact/civil_team.jsp identifying the 

correspondence as being related to Airworthiness Directives.