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 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 900 series engines 

TCDS Number : EASA.E.012 

Foreign AD : Not applicable 

Supersedure : None 

ATA 72 Engine – IP Shaft Coupling Splines – Inspection 

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 turbine axial setting and 

wear through of the splines would permit the IP turbine to move 

rearwards. 

Rearward movement of the IP turbine would enable contact with static 

turbine components and would result in loss of engine performance with 

potential for in-flight shut down, oil migration and oil fire below the LP 

turbine discs prior to sufficient indication resulting in loss of LP turbine disc 

integrity. Some of these conditions present a potential unsafe condition to 

the aeroplane. 

This AD requires inspection of the IP shaft coupling splines and, 

depending on the results, requires further repetitive inspections or 

corrective actions. 

Effective Date: 29 January 2010 
EASA 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 this AD: 

(a) On-wing - Accomplish the actions specified in Table 1.a and 1.b of this 

AD in accordance with section 3.A of Rolls-Royce RB211-Trent 900 Alert 

Non Modification Service Bulletin (NMSB) 72-AG329 Revision 1. 

and, 

(b) In-shop - Accomplish the actions specified in section 3.B of RollsRoyce RB211-Trent 900 NMSB 72-AG329 Revision 1. 

Ref. Publications: Rolls-Royce RB211-Trent 900 Alert 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, EASA 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 to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA. E-mail ADs@easa.europa.eu. 

4. For any questions concerning the technical content 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 249936; 

Email: tech.help@rolls-royce.com or download the publication from 

https://www.aeromanager.com
EASA 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 accordance 

with 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 since new, however, if it is known that the coupling

(FW33264) was replaced with new during any shop visit then the life since that shop visit may be used in 

place of time since new, to establish the inspection 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 Remove the engine Within 10 flight cycles 

Equal to or more than 0,5 mm but less than 1 mm Repeat inspection Within 50 flight cycles 

Equal to or more than 1 mm but less than 1,5 mm Repeat inspection Within 100 flight cycles 

Equal to or more than 1,5 mm but less than 2 mm Repeat inspection Within 200 flight cycles 

Equal to or more than 2 mm but less than 2,4 mm Repeat 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.