EASA AD No : 2011-0221 

EASA Form 110 Page 1/4 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0221 

Date: 14 November 2011 

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 500, 700 and 800 engines 

TCDS Number : EASA E.042, EASA.E.060 and UK CAA 1051 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2010-0266R1 dated 06 January 2011. 

ATA 72 Engine – Intermediate Pressure Compressor Rotor Shaft and 

Balance Weights – Inspection / Modification 

Manufacturer(s): Rolls-Royce plc 

Applicability: Models RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2-

61, 560-61 and 560A2-61 engines, all serial numbers. 

These engines are known to be installed on, but not limited to, Airbus A340-

500 and A340-600 series aeroplanes. 

Models RB211 Trent 768-60, 772-60, 772B-60 and 772C-60 engines, all serial 

numbers. 

These engines are known to be installed on, but not limited to, Airbus A330 

series aeroplanes. 

Models 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: Cracks have been found on the rear balance land feature of the Intermediate 

Pressure (IP) Compressor rotor shaft of two in-service Trent 800 engines and 

on one in-service Trent 700 engine. The cracking had initiated from frettage 

marks caused by balance weights, but the key factors behind the crack 

propagation are not fully understood. 

Stress analysis of the damage condition has shown that it presents a possible 

threat to the rotor integrity. 

This condition, if not detected and corrected, could lead to IP Compressor rotor 

shaft failure and consequent non-contained high energy debris, possibly 
EASA AD No : 2011-0221 

EASA Form 110 Page 2/4 

resulting in damage to the aeroplane. 

EASA initially issued AD 2007-0052 to address this unsafe condition with visual 

inspections of the balance land. 

Rolls-Royce subsequently improved the inspection methods for the Trent 700 

and 800 engines and produced a modification for those engines, 

accomplishment of which terminated the need for on-wing inspections. EASA 

AD 2010-0266 incorporated these changes and superseded EASA AD 2007-

0052 requiring, for the Trent 700 and 800 engines, repetitive on-wing 

borescope and in-shop Eddy Current inspections of the IP Compressor rotor 

shaft for discrepancies and, depending on findings, corrective actions. 

For the Trent 500 engines, EASA AD 2010-0266 required repetitive in-shop 

visual inspections, in accordance with Rolls-Royce Alert Non-Modification 

Service Bulletin (NMSB) RB211-72-AF260 at Revision 4 or, alternatively, inshop Eddy Current inspections in accordance with Rolls-Royce NMSB RB211-

72-G448 Revision 1, to detect discrepancies in the IP Compressor rotor shaft 

and, depending on findings, corrective actions. 

EASA AD 2010-0266R1 was issued to confirm that accomplishment of the 

actions of the on-wing inspection during a shop visit is acceptable to comply 

with the requirement of paragraph (1) of this AD. 

Since issuance of EASA AD 2010-0266R1, for Trent 700 and 800 engines, 

efforts to develop an on-wing eddy-current inspection have failed which were 

intended to have increased the effectiveness of the on-wing inspection 

programme. 

For the reasons described above, this AD, which supersedes EASA AD 2010-

0266R1, partially retaining its requirements, requires accomplishment of the 

modification (introduction of new balance weight design) at the next qualifying 

shop visit, for Trent 700 and 800 engines. For Trent 500 engines there are 

editorial changes only for consistency, the requirements are not changed 

technically relative to EASA AD 2010-0266R1. 

Effective Date: 28 November 2011 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless already accomplished:

Trent 700 and Trent 800 engines: 

(1) Within the time period indicated in Table 1 or Table 2 of this AD, as 

applicable to engine type, accomplish inspections (on-wing or in-shop) of 

the IP Compressor rotor shaft for discrepancies in accordance with the 

instructions of the associated Non Modification Service Bulletin (NMSB): 

Table 1 – Trent 700 engine inspections 

Inspection Compliance time NMSB 

Initial Within 625 Flight Cycles 

(FC) after 20 January 

2011 [the effective date 

of AD 2010-0266R1] 

RB211-72-AG270 Revision 4 

or RB211-72-AG085 

Revision 2. 

Repetitive At intervals not to exceed 

625 FC 
EASA AD No : 2011-0221 

EASA Form 110 Page 3/4 

Table 2 – Trent 800 engine inspections 

Inspection Compliance time NMSB 

Initial Within 475 FC after 20 

January 2011 [the 

effective date of AD 

2010-0266R1] 

RB211-72-AG264 Revision 5 

or RB211-72-AG085 

Revision 2. 

Repetitive At intervals not to exceed 

475 FC 

(2) During each shop visit, after the effective date of this AD, in which the 

engine is sufficiently disassembled to expose the IP Compressor module 

rear face, inspect the IP Compressor rotor shaft and balance weights for 

discrepancies in accordance with the instructions of NMSB RB211-72-

AG085 Revision 2. 

(3) If, during any inspection as required by paragraph (1) or (2) of this AD, 

discrepancies (as detailed in NMSB RB211-72-AG264, NMSB RB211-72-

AG270, or NMSB RB211-72-AG085, as applicable) are detected, within 

the time period specified in the NMSB or before release to service of the 

engine, as applicable, accomplish the appropriate corrective action(s) 

(depending on findings as detailed in NMSB RB211-72-AG264, NMSB 

RB211-72-AG270, or NMSB RB211-72-AG085, as applicable) or replace 

the affected parts with serviceable parts. 

(4) At the next shop visit in which any level of inspection or strip is scheduled 

to be carried out on the IPC module, or within 90 months, whichever 

occurs first after the effective date of this AD, modify the engine in 

accordance with the instructions of SB RB211-72-AG401 Revision 2 (for 

RB211 Trent 800) or SB RB211-72-AG402 Revision 2 (for RB211 Trent 

700) (introduction of new balance weight design). 

(5) Modification of an engine as required by paragraph (4) of this AD 

constitutes terminating action for the repetitive inspections required by 

paragraph (1) of this AD for that engine. 

(6) Inspections and modification of the engine (introduction of new balance 

weight design) accomplished before the effective date of this AD, in 

accordance with all referenced SBs and NMSBs at any previous revisions, 

are considered acceptable for compliance with the requirements of 

paragraphs (1), (2) and (3) of this AD for that engine. 

Trent 500 engines: 

(7) During each shop visit, after the effective date of this AD, in which the 

engine is sufficiently disassembled to expose the IP Compressor module 

rear face, inspect the IP Compressor rotor shaft and balance weights for 

discrepancies in accordance with the instructions of NMSB RB211-72-

AF260 Revision 5. 

(8) As an alternative to each inspection as required by paragraph (7) of this 

AD, an Eddy Current inspection of the IP Compressor rotor shaft and 

visual inspection of the balance weights can be accomplished in 

accordance with the instructions of NMSB RB211-72-G448 Revision 3. 

(9) If, during any inspection as required by paragraph (7) or (8) of this AD, 

discrepancies (as detailed in NMSB RB211-72-AF260 or NMSB RB211-

72-G448, as applicable) are detected, before release to service of the 

engine, accomplish the appropriate corrective action(s) (depending on 

findings as detailed in NMSB RB211-72-AF260 or in NMSB RB211-72-

G448, as applicable) or replace the affected parts with serviceable parts. 

Note: Corrective action(s) as required by this AD paragraph does/do not 

constitute terminating action for the repetitive inspections required by this 

AD for that engine. 
EASA AD No : 2011-0221 

EASA Form 110 Page 4/4 

Ref. Publications: Rolls-Royce NMSB RB211-72-AF260 Revision 5 dated 7 July 2011. 

Rolls-Royce NMSB RB211-72-AG085 Revision 2 dated 7 July 2011. 

Rolls-Royce NMSB RB211-72-AG264 Revision 5 dated 21 March 2011. 

Rolls-Royce NMSB RB211-72-AG270 Revision 4 dated 21 March 2011. 

Rolls-Royce NMSB RB211-72-G448 Revision 3 dated 7 July 2011. 

Rolls-Royce SB RB211-72-AG401 Revision 2 dated 5 July 2011. 

Rolls-Royce SB RB211-72-AG402 Revision 2 dated 7 July 2011. 

The reference number of the applicable Rolls-Royce NMSB/SB might change 

to incorporate an “A” (indicating categorisation as “Alert”, within the RollsRoyce system). 

The use of later approved revisions of these documents 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 October 2011 as PAD 11-104 for consultation 

until 01 November 2011. 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. If you do not have a designated representative or 

Aeromanager account, please contact Corporate Communications at RollsRoyce plc. PO 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.