EASA AD No : 2010-0008

EASA Form 112 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0008

Date: 15 January 2010

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 participat e 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordance with the requirements of that AD, unl ess 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 900 series engines

TCDS Number : EASA.E.012

Foreign AD : Not applicable

Supersedure : None



### ATA 72 Engine – IP Shaft Coupling Splines – Inspect ion

Manufacturer(s): Rolls-Royce plc

Applicability: RB211 Trent 900 series engines, all marks, all serial numbers. These engines are known to be installed on, but not limited to, Airbus A380 series aircraft.
Reason: Wear, beyond Engine Manual limits, has been identified on the abutment faces of the splines on the Trent 900 Intermediate Pressure (IP) shaft rigid coupling on several engines during strip. The shaft to coupling spline interface provides the means of controlling the tur bine axial setting and wear through of the splines would permit the IP tur bine to move rearwards. Rearward movement of the IP turbine would enable co ntact with static turbine components and would result in loss of engi ne performance with potential for in-flight shut down, oil migration an d oil fire below the LP turbine discs prior to sufficient indication result ing in loss of LP turbine disc integrity. Some of these conditions present a poten tial unsafe condition to the aeroplane. This AD requires inspection of the IP shaft couplin g splines and, depending on the results, requires further repetiti ve inspections or corrective actions.
Effective Date: 29 January 2010EASA AD No : 2010-0008

EASA Form 112 Page 2/3 Required Action(s) and Compliance Time(s): Required as indicated after the effective date of t his AD: (a) On-wing - Accomplish the actions specified in T able 1.a and 1.b of this AD in accordance with section 3.A of Rolls-Royce RB 211-Trent 900 Alert Non Modification Service Bulletin (NMSB) 72-AG329 R evision 1. and, (b) In-shop - Accomplish the actions specified in s ection 3.B of RollsRoyce RB211-Trent 900 NMSB 72-AG329 Revision 1.
Ref. Publications: Rolls-Royce RB211-Trent 900 Aler t Non Modification Service Bulletin (NMSB) 72-AG329 Revision 1, dated 13 January 2010. The use of later approved updates of this document is acceptable for compliance with the requirement 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 02 December 2009 as PAD 09 -136 for consultation until 30 December 2009. The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred t o the Airworthiness Directives, Safety Management & Research Section, C ertification Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any questions concerning the technical conte nt of the requirements in this AD, please contact: Rolls-Royce plc ., P.O. Box 31, Derby, DE24 8BJ, United Kingdom; Telephone: +44 (0) 1332 242424, Fax: +44 (0) 1332 2 49936; Email: tech.help@rolls-royce.com or download the publication from https://www.aeromanager.comEASA AD No : 2010-0008

EASA Form 112 Page 3/3 Table 1.a: On-wing Borescope Inspection – Initial Inspection
Configuration / Condition Action Compliance Time

Engines where the life since new is 250 flight cycles or less ( 1 ) Before the engine has accumulated 400 flight cycles since new
Engines where the life since new is more than 250 flight cycles ( 1 ) Inspect the IP shaft coupling splines – measurement of spline crest – in accordancewith section 3.A of RollsRoyce NMSB 72-AG329 revision 1 Within 150 flight cycles

Note ( 1 ): Coupling life is assumed to be the engine time s ince new, however, if it is known that the coupling (FW33264) was replaced with new during any shop vis it then the life since that shop visit may be used in place of time since new, to establish the inspectio n threshold.

Table 1.b: On-wing Borescope Inspection – Further Action and Repetitive Inspection Intervals

Condition Measured spline crest in accordance with section 3.A of Rolls-Royce NMSB 72-AG329 Revision 1 is: Action Compliance Time / Repetitive Interval (not to exceed)

Less than 0,5 mm with no material remaining Remove the engine Before next flight Less than 0,5 mm with some material remaining Remov e the engine Within 10 flight cycles Equal to or more than 0,5 mm but less than 1 mm Rep eat inspection Within 50 flight cycles Equal to or more than 1 mm but less than 1,5 mm Rep eat inspection Within 100 flight cycles Equal to or more than 1,5 mm but less than 2 mm Rep eat inspection Within 200 flight cycles Equal to or more than 2 mm but less than 2,4 mm Rep eat inspection Within 300 flight cycles Equal to or more than 2,4 mm ( 2 ) Repeat inspection Within 400 flight cycles Note (

2 ): The nominal unworn dimension of the spline crest is 2,65 mm.