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 b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in th e 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 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 10 51

Foreign AD : Not applicable

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



### ATA 72 Engine – Intermediate Pressure Compressor Rotor Sha ft 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-serv ice Trent 800 engines and on one in-service Trent 700 engine. The cracking ha d initiated from frettage marks caused by balance weights, but the key factor s behind the crack propagation are not fully understood. Stress analysis of the damage condition has shown t hat it presents a possible threat to the rotor integrity. This condition, if not detected and corrected, coul d lead to IP Compressor rotor shaft failure and consequent non-contained high ene rgy debris, possiblyEASA 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 me thods for the Trent 700 and 800 engines and produced a modification for tho se engines, accomplishment of which terminated the need for on- wing inspections. EASA AD 2010-0266 incorporated these changes and superse ded EASA AD 2007- 0052 requiring, for the Trent 700 and 800 engines, repetitive on-wing borescope and in-shop Eddy Current inspections of t he IP Compressor rotor shaft for discrepancies and, depending on findings, corrective actions. For the Trent 500 engines, EASA AD 2010-0266 requir ed 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 Ro lls-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 acco mplishment of the actions of the on-wing inspection during a shop vis it is acceptable to comply with the requirement of paragraph (1) of this AD. Since issuance of EASA AD 2010-0266R1, for Trent 70 0 and 800 engines, efforts to develop an on-wing eddy-current inspecti on have failed which were intended to have increased the effectiveness of the on-wing inspection programme. For the reasons described above, this AD, which sup ersedes EASA AD 2010- 0266R1, partially retaining its requirements, requi res accomplishment of the modification (introduction of new balance weight de sign) at the next qualifying shop visit, for Trent 700 and 800 engines. For Tren t 500 engines there are editorial changes only for consistency, the require ments 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 Ser vice 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 FCEASA 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 dat e of this AD, in which the engine is sufficiently disassembled to expose the I P Compressor module rear face, inspect the IP Compressor rotor shaft an d balance weights for discrepancies in accordance with the instructions o f NMSB RB211-72- AG085 Revision 2. (3) If, during any inspection as required by paragr aph (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 d etected, within the time period specified in the NMSB or before rel ease to service of the engine, as applicable, accomplish the appropriate c orrective action(s) (depending on findings as detailed in NMSB RB211-72 -AG264, NMSB RB211-72-AG270, or NMSB RB211-72-AG085, as applicab le) or replace the affected parts with serviceable parts. (4) At the next shop visit in which any level of in spection or strip is scheduled to be carried out on the IPC module, or within 90 m onths, whichever occurs first after the effective date of this AD, m odify the engine in accordance with the instructions of SB RB211-72-AG4 01 Revision 2 (for RB211 Trent 800) or SB RB211-72-AG402 Revision 2 (f or RB211 Trent 700) (introduction of new balance weight design). (5) Modification of an engine as required by paragr aph (4) of this AD constitutes terminating action for the repetitive i nspections required by paragraph (1) of this AD for that engine. (6) Inspections and modification of the engine (int roduction of new balance weight design) accomplished before the effective da te of this AD, in accordance with all referenced SBs and NMSBs at any previous revisions, are considered acceptable for compliance with the r equirements of paragraphs (1), (2) and (3) of this AD for that eng ine. 

### Trent 500 engines: (7) During each shop visit, after the effective dat e of this AD, in which the engine is sufficiently disassembled to expose the I P Compressor module rear face, inspect the IP Compressor rotor shaft an d balance weights for discrepancies in accordance with the instructions o f NMSB RB211-72- AF260 Revision 5. (8) As an alternative to each inspection as require d 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 acc omplished in accordance with the instructions of NMSB RB211-72-G 448 Revision 3. (9) If, during any inspection as required by paragr aph (7) or (8) of this AD, discrepancies (as detailed in NMSB RB211-72-AF260 o r NMSB RB211- 72-G448, as applicable) are detected, before releas e to service of the engine, accomplish the appropriate corrective actio n(s) (depending on findings as detailed in NMSB RB211-72-AF260 or in N MSB RB211-72- G448, as applicable) or replace the affected parts with serviceable parts. Note: Corrective action(s) as required by this AD p aragraph does/do not constitute terminating action for the repetitive in spections 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 J uly 2011. Rolls-Royce SB RB211-72-AG401 Revision 2 dated 5 Ju ly 2011. Rolls-Royce SB RB211-72-AG402 Revision 2 dated 7 Ju ly 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 docume nts is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA 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 Docume nt can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact your designated Rolls-Royce representative or download the publication from your Aeromanager acco unt at www.aeromanager.com. If you do not have a designate d representative or Aeromanager account, please contact Corporate Commu nications at RollsRoyce plc. PO Box 31, Derby, DE24 8BJ, United Kingd om, telephone: +44 (0) 1332 242424, or send an e-mail t hrough http://www.rolls-royce.com/contact/civil_team.jsp i dentifying the correspondence as being related to Airworthiness Di rectives.