E ASA AD No : 20 14 - 0152

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 6 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014 - 0152 [Correction: 25 June 2014] Date: 20 June 2014 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 2 1.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 ope rate an aircraft to which an AD applies, except in accordance wi th 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) exempt ion]. 

### 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.047 and EASA

. E.060 Foreign AD : Not applicable Supersedure : This AD supersedes EASA AD 201 3 - 0 00 2 dated 04 January 201 3

. 

### ATA 72 Engine – Intermediate Pressure Compressor Rotor Shaft and

Balance Weights – Inspection / Modification Manufacturer(s): Rolls - Royce plc (RR) 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, al l serial numbers . 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 beh ind 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, possiblyE ASA AD No : 20 14 - 0152

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 6 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 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, RR improved the inspection methods for the Trent 700 and 800 engines and developed a modification for those engines, accomplishment of which terminate s the need for on - wing inspections. EASA AD 2010 - 0266 incorporated these changes and superseded EASA AD 2007 - 0052 requir ing , for the Trent 700 and 800 engines, repetitive on - wing borescope and in - shop Eddy Current (EC) 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 RR Alert Non Modification Service Bulletin (NMSB) RB

. 211 - 72 - AF260 at Revision 4 or, alternatively, in - shop EC inspections in acc ordance with RR 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 EC 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 and 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 RR concluded that the mechanism which led to this occurrence may be also present in Trent 900 engines. Consequently, EASA issued AD 2013 - 0002, retain ing the requirements of EASA AD 2011 - 0221R1, which was superseded , expand ing the Applicability to include all Trent 900 engines, and add ing repetitive on - wing inspections for Trent 500 and Trent 900 engines to the requirements. Since EASA AD 2013 - 0002 was issued, it was found that for post - mod 72 - G401 Trent 800 engines and post - mod 72 - G402 Trent 700 engines , which were excluded from the Applicability of that AD , the in - shop inspections must remain required

. Those modification s constitute terminating act ion only for the repetitive on - wing inspections

. In addition, RR have developed modifications for Trent 500 ( mod 72 - H555) and Trent 900 ( mod 72 - H561) , introduc ing the new balance weight design , which cancels the required on - wing inspections f o r those engines

. For the reasons described above, this AD retains the requirements of EASA AD 2013 - 0002, which is superseded, and requires modification of the affected engines. This AD also clarifies that modification does not constitute terminating action for the repetitive in - shop inspections. This AD is re - published to correct a RR NMSB in the section ‘Ref. Publications’ where the ATA number and issue date were wrong . Effective Date: 04 July 2014 Required Action(s) and Compliance Time(s): Required as indicated, unless already accomplished: Note: Where in this AD, reference is made to an RR Mod, SB or NMSB with an ‘A’ (Alert) in the number, it should be recognised that an earlier or later revision may not have that ‘A’. This kind of change does not effe ctively alter the publication reference s for the purpose of this AD.E ASA AD No : 20 14 - 0152

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 6 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 

### Trent 700 and Trent 800 engines: (1) Within the compliance time s specified in Table 1 or Table 2 of this AD, as applicable to engine type, accomplish repetitive on - wing visual borescope inspection s of the IP Compressor rotor shaft for discrepancies in accordance with the instructions of the associated NMSB

. On - wing inspections are not required for engines that have had SB ( mod ) 72 - G401 (Trent 800) or SB ( mod ) 72 - G402 (Trent 700) incorporated

.

Table 1

– Trent 700 engine inspections Compliance time NMSB Instructions Within 625 f light c ycles (FC) after 20 January 2011 [ the effective date of AD 2010 - 0266R1] and thereafter a t intervals not to exceed 625 FC RB

. 211 - 72 - AG270 Revision 4

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 a t intervals not to exceed 475 FC RB

. 211 - 72 - AG264 Revision 5 (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, accomplish an EC inspection of the IP Compressor rotor shaft for discrepancies in accordance with the instructions of RR NMSB RB

. 211 - 72 - AG085 Revision 2. (3) An EC inspection accomplish ed in shop in accordance with paragraph (2) of this AD is acceptable in lieu of an on - wing visual borescope inspection as required by paragraph (1) of this AD. If the engine is i nsufficiently disassembled to expose the rear face of the IP Compressor module, a n in - shop visual bor e scope inspection in accordance with the instructions of RR NMSB RB.211 - 72 - AG270 Revision 4 , or RR NMSB RB.211 - 72 - AG264 Revision 5 , as applicable to engine type, is acceptable in lieu of a n inspection as required by paragraph (1) of this AD

. ( 4 ) If, during any inspection as required by paragraph (1) or (2) of this AD, or as specified in paragraph (3) 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 f indings 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. ( 5 ) A t the next shop visit in which the IP C ompressor module is scheduled for a module check and repair, module overhaul, or e ngine refurbishment , or where the engine is disassembled sufficiently to expose the rear face of the IP Compressor module , or within 9 0 months , whichever occurs first after 28 November 2011 [the effective date of EASA AD 2011 - 0221] , modify the engine (introduction of new balance weight design) in accordance with the instructions of RR SB RB

. 211 - 72 - A G401 Revision 2 (for RB211 Trent 800) or SB RB

. 211 - 72 - A G402 Revision 2 (for RB211 Trent 700) , as applicable

.E ASA AD No : 20 14 - 0152

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 4 / 6 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. (6 ) Modification of an engine as required by paragraph ( 5 ) of this AD constitutes terminating action for the repetitive on - wing inspections as required by paragraph (1) of this AD for that engine. ( 7 ) 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 t o compl y with the requirements of paragraph s (1), ( 4 ) and ( 5 ) of this AD for that engine. 

### Trent 500 engines: ( 8 ) Within 340 FC after 18 January 2013 [the effective date of EASA AD 2013 - 0002] and, thereafter, at intervals not to exceed 340 FC, accomplish an on - wing visual borescope inspect ion of the IP Compressor rotor shaft rear balance land in accordance with the instructions of RR NMSB RB

. 211 - 72 - AH058. On - wing inspections are not required for engines that have had SB ( mod ) 72 - H555 incorporated

. ( 9 ) During each shop visit after the effective date of this AD in which the engine is sufficiently disassembled to expose the rear face of the IP Compressor module , accomplish an EC inspection of the IP Compressor rotor shaft in accordance with the instructions of RR NMSB RB.211 - 72 - G448 Revision 3

. ( 10 ) An EC inspection accomplish ed in shop in accordance with paragraph ( 9 ) of this AD is acceptable in lieu of an on - wing visual borescope inspection as requir ed by paragraph ( 8 ) of this AD. If the engine is i nsufficiently disassembled to expose the rear face of the IP Compressor module, an in - shop visual bor e scope inspection in accordance with the instructions of RR NMSB RB.211 - 72 - G448 Revision 3 is acceptable in lieu of an inspection as required by paragraph (8) of this AD. ( 11 ) If, during any inspection as required by paragraph ( 8 ) or ( 9 ) of this AD , or as specified in paragraph ( 10 ) of this AD, as applicable, discrepancies (as detailed in NMSB RB

. 211 - 72 - G448 or NMSB RB

. 211 - 72 - AH05 8, as applicable ) are detected, within the time period specified in the NMSB or before release to service of the engine, as applicable, accomplish the app licable corrective action(s) , depending on findings ( as detailed in NMSB RB

. 211 - 72 - G448 or NMSB RB

. 211 - 72 - AH05 8, as applicable ) or replace the affected parts with serviceable part s . ( 1 2 ) At the next shop visit in which the IP C ompressor module is scheduled for a module check and repair, module overhaul, or engine refurbishment, or where the engine is disassembled sufficiently to expose the rear face of the IP Compressor 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 RR SB RB .211 - 72 - A H555

. (1 3 ) Modification of an engine as required by paragraph ( 1 2 ) of this AD c onstitutes terminating action for the repetitive on - wing inspections as required by paragraph ( 8 ) of this AD for that engine

. 

### Trent 9 00 engines: ( 1 4 ) Within 280 FC after 18 January 2013 [the effective date of EASA AD 2013 - 0002] 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 RR NMSB RB.211 - 72 - AH059. On - wing inspections are not required for engines that have had SB ( mod ) 72 - H561 incorporated

. (1 5 ) During each shop visit after the effective date of this AD in which theE ASA AD No : 20 14 - 0152

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 5 / 6 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. engine is sufficiently disassembled to expose the rear face of the IP Compressor module, accomplish an EC inspection of the IP Compressor rotor shaft in accordance with the instructions of RR NMSB RB211 - 72 - G448 Revision 3. (1 6 ) An EC inspection accomplish ed in shop in accordance with paragraph (1 5 ) of this AD is ac ceptable in lieu of an on - wing visual borescope inspection as requir ed by paragraph (1 4 ) of this AD

. If the engine is i nsufficiently disassembled to expose the rear face of the IP Compressor module, a n in - shop visual bor e scope inspection in accordance with the instructions of RR NMSB RB.211 - 72 - G448 Revision 3 is acceptable in lieu of an inspection as required by paragraph (14) of this AD. (1 7 ) If, during any inspection as required by paragraph (1 4 ) or (1 5 ) of this AD, or as specified in paragraph (16) of this AD, as applicable, discrepancies (as detailed in NMSB RB.211 - 72 - G448 or in NMSB RB.211 - 72 - AH059, as applicable) are detected, within the time period specified in the NMSB or before release to service of the engine, as applicable, accomplish the app licable corrective action(s), depending on findings as detailed in NMSB RB.211 - 72 - G448 or NMSB RB.211 - 72 - AH059, as applicable, or replace the affected parts with serviceable parts. ( 1 8 ) At the next shop visit in which the IP C ompressor module is scheduled for a module check and repair, module overhaul, or engine refurbishment, or where the engine is disassembled sufficiently to expose the rear face of the IP Compressor module , or within 90 months, whichever occurs first aft er the effective date of this AD, modify the engine (introduction of new balance weight design) in accordance with the instructions of RR SB RB.211 - 72 - AH561. ( 19 ) Modification of an engine as required by paragraph (1 8 ) of this AD constitutes terminating action for the repetitive on - wing inspections as required by paragraph ( 1 4 ) of this AD for that engine. Ref. Publications: 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 - A G 401 Revision 2 dated 5 July 2011 , or Revision 3 dated 28 January 2014

. Rolls - Royce SB RB

. 211 - 72 - A G 402 Revision 2 dated 7 July 2011. Rolls - Royce NMSB RB.211 - 7 2 - AH058 dated 13 December 2012. Rolls - Royce NMSB RB.211 - 72 - AH059 dated 11 December 2012. Rolls - Royce SB RB.211 - 72 - AH555 original dated 18 October 2013, or Revision 1 dated 13 December 201 3

. Rolls - Royce SB RB.211 - 72 - AH561 dated 21 October 2013

. 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 23 January 2014 as PAD 14 - 019 for consultation until 20 February 2014. 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

.E ASA AD No : 20 14 - 0152

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 6 / 6 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 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.aeromana ger.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, T elephone: +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 a irworthiness d irectives

.