EASA AD No : 2013-0002

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0002

Date: 04 January 2013

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 EU 748/2012, Part 21.A.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, 800 and 900 engines

TCDS Numbers: EASA.E.012, EASA.E.042, EASA.E.060 and United Kingdom No. 1051

Foreign AD : Not applicable

Supersedure: This AD supersedes EASA AD 2011-0221R1 dated 25 November 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, except those having Modification (mod.) 72-G402 embodied. 

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, except those having mod. 72-G401 

embodied. These engines are known to be installed on, but not limited to, 

Boeing 777 series aeroplanes.

Models RB211 Trent 970-84, 970B-84, 972-84, 972B-84, 977-84, 977B-84 

and 980-84 engines, all serial numbers. These engines are known to be 

installed on, but not limited to, Airbus A380 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 
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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 

resulting in damage to the aeroplane. 

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

visual inspections of the balance land. Subsequently, Rolls-Royce improved 

the inspection methods for the Trent 700 and 800 engines and developed a 

modification for those engines, accomplishment of which terminates 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 (later revised) required 

repetitive in-shop visual inspections, in accordance with Rolls-Royce Alert 

Non-Modification Service Bulletin (NMSB) RB.211-72-AF260 at Revision 4 or, 

alternatively, in-shop Eddy Current inspections in accordance with RollsRoyce NMSB RB.211-72-G448 Revision 1, to detect discrepancies in the IP 

Compressor rotor shaft and, depending on findings, corrective actions.

Since EASA AD 2010-0266R1 was issued, efforts to develop an on-wing 

eddy-current inspection, intended to increase the effectiveness of the 

programme for Trent 700 and 800 engines, failed. Consequently, EASA 

issued AD 2011-0221 (later revised), superseding EASA AD 2010-0266R1, 

partially retaining its requirements, to require introduction of new balance 

weight design for Trent 700 and 800 engines. For Trent 500 engines, the 

requirements are not changed technically relative to EASA AD 2010-0266R1.

Since EASA AD 2011-0221R1 was issued, it was reported that during a 

recent inspection at shop visit, cracking was detected in a Trent 500 IP 

Compressor rotor shaft rear balance land. Further engineering evaluation 

carried out by Rolls-Royce concluded that the mechanism which led to this 

occurrence may be also present in Trent 900 engines.

For the reasons described above, this AD retains the requirements of EASA 

AD 2011-0221R1, which is superseded, expands the Applicability to include 

all Trent 900 engines, and adds repetitive on-wing inspections for Trent 500 

and Trent 900 engines to the requirements.

Effective Date: 18 January 2013

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 NMSB:

Table 1 – Trent 700 engine inspections

Compliance time NMSB Instructions

Within 625 flight cycles (FC) after 

20 January 2011 [the effective 

date of AD 2010-0266R1] and 

thereafter at intervals not to 

exceed 625 FC

RB.211-72-AG270 Revision 4, or 

RB.211-72-AG085 Revision 2.
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Table 2 – Trent 800 engine inspections

Compliance time NMSB Instructions

Within 475 FC after 20 January 

2011 [the effective date of AD

2010-0266R1] and thereafter at 

intervals not to exceed 475 FC

RB.211-72-AG264 Revision 5, or 

RB.211-72-AG085 Revision 2.

(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 RB.211-72-

AG085 Revision 2.

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

discrepancies (as detailed in NMSB RB.211-72-AG264, NMSB RB.211-

72-AG270, or NMSB RB.211-72-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 applicable corrective 

action(s), depending on findings as detailed in NMSB RB.211-72-

AG264, NMSB RB.211-72-AG270, or NMSB RB.211-72-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 (introduction of new balance weight design) in accordance with 

the instructions of SB RB.211-72-G401 Revision 2 (for RB211 Trent 

800) or SB RB.211-72-G402 Revision 2 (for RB211 Trent 700), as 

applicable.

(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 an 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 to comply with the requirements of 

paragraphs (1), (2), (3) and (4) 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 RB.211-72-

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 RB.211-72-G448 Revision 3.

(9) Within 340 FC after the effective date of this AD and, thereafter, at 

intervals not to exceed 340 FC, accomplish an on-wing visual borescope 

inspection of the IP Compressor rotor shaft rear balance land in 

accordance with the instructions of NMSB RB.211-72-AH058.

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

AD, discrepancies (as detailed in NMSB RB211-72-AF260, or NMSB 
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RB.211-72-G448, or NMSB RB.211-72-AH058, as applicable) are 

detected, before release to service of the engine, accomplish the 

applicable corrective action(s), depending on findings as detailed in 

NMSB RB.211-72-AF260, or in NMSB RB.211-72-G448, or in NMSB 

RB.211-72-AH058, as applicable) or replace the affected parts with 

serviceable parts.

Trent 900 engines:

(11) 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 RB.211-72-

G269.

(12) As an alternative to each inspection as required by paragraph (11) 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.

(13) Within 280 FC after the effective date of this AD and, thereafter, at 

intervals not to exceed 280 FC, accomplish an on-wing visual borescope 

inspection of the IP Compressor rotor shaft rear balance land in 

accordance with the instructions of NMSB RB.211-72-AH059.

(14) If, during any inspection as required by paragraph (11), (12), or (13) of 

this AD, discrepancies (as detailed in NMSB RB.211-72-G269, or in 

NMSB RB.211-72-G448, or in NMSB RB.211-72-AH059, as applicable) 

are detected, before release to service of the engine, accomplish the 

appropriate corrective action(s), depending on findings as detailed in 

NMSB RB.211-72-G269 or in NMSB RB.211-72-G448, or NMSB 

RB.211-72-AH059, as applicable, or replace the affected parts with 

serviceable parts.

Trent 500 and 900 engines – No terminating action:

(15) Corrective action on an engine, as required by paragraph (10) or 

paragraph (14) of this AD, as applicable, does not constitute terminating 

action for the repetitive inspections required by this AD for that engine.

Ref. Publications: Rolls-Royce NMSB RB.211-72-AF260 Revision 5 dated 7 July 2011.

Rolls-Royce NMSB RB.211-72-AG085 Revision 2 dated 7 July 2011.

Rolls-Royce NMSB RB.211-72-AG264 Revision 5 dated 21 March 2011.

Rolls-Royce NMSB RB.211-72-AG270 Revision 4 dated 21 March 2011.

Rolls-Royce NMSB RB.211-72-G448 Revision 3 dated 7 July 2011.

Rolls-Royce SB RB.211-72-G401 Revision 2 dated 5 July 2011.

Rolls-Royce SB RB.211-72-G402 Revision 2 dated 7 July 2011.

Rolls-Royce NMSB RB.211-71-AH058 dated 7 November 2012. 

Rolls-Royce NMSB RB.211-72-AH059 dated 11 December 2012.

Rolls-Royce NMSB RB.211-72-G269 dated 10 August 2009.

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. Based on the required actions and the compliance time, EASA have 
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decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until 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 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 Rolls-Royce plc.,

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.