EASA AD No.: 2008-0109 R1 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2008-0109 R1 

Date: 17 June 2008 

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 Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness Directive 

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 engines 

TCDS Number: EASA E.060 

Foreign AD : Not applicable 

Revision: This AD revises and replaces EASA AD 2008-0109 dated 06 June 2008. 

ATA 72 Engine – Intermediate Pressure (IP) Turbine Blade Outer Shrouds – 

Inspection 

Manufacturer(s): Rolls-Royce plc 

Applicability: 

RB211-Trent 500 series engines, all marks without Rolls-Royce service bulletin 

No. 72-D733 embodied. 

These engines are known to be installed on, but not limited to, Airbus A340-500 

and Airbus A340-600 series aircraft. 

Reason: 

The IP turbine blade shrouds of the RB211-Trent 500 series engines feature closure 

welds (dust caps). Development engine testing has revealed the potential for dust 

caps to crack, lift and release. The latter may potentially allow hot annulus gas to be 

ingested down the core passages of IP turbine blades. Radial inflow of annulus gas 

into the IP disc rim region could cause local heating of the disc firtree, resulting in 

creep of the disc material. Failure of the disc rim in creep could simultaneously 

release two blades and a disc post. Failure to this extent could be beyond the 

containment capabilities of the casing. Consequently, release of the dust caps 

would constitute a potentially unsafe condition. 

This Airworthiness Directive is published to require inspection of IP Turbine Blade 

Outer Shrouds and, depending on the results, subsequent corrective actions. 

This AD has been revised in order to allow the option of carrying out the required 

inspections while the engine is not installed on an aircraft. 

Effective Date: 20 June 2008 
EASA AD No.: 2008-0109 R1 

EASA Form 110 Page 2/2 

Required action(s) 

and Compliance 

Time(s): 

1) Borescope Inspection 

Before 1st July 2008, carry out the borescope inspection as specified in 

Section 3, Accomplishment Instructions of Rolls-Royce Non Modification 

Service Bulletin (NMSB) No. 72-AF994. 

2) Actions following Borescope Inspection (see also 1 above) 

Depending on the results of the inspection carried out according to paragraph 

1) of this AD, carry out the following: 

Results of Borescope 

Inspection 

Actions that Must Be Carried Out 

Total Number of IP Turbine 

Blade Outer Shroud Dust 

Caps lifting is 0 

At intervals not to exceed 100 Cycles, 

re-inspect engine in accordance with 

Section 3, Accomplishment Instructions 

of Rolls-Royce NMSB No. 72-AF994 

Total Number of IP Turbine 

Blade Outer Shroud Dust 

Caps lifting exceeds 0 but is 

equal to or less than 10 

At intervals not to exceed 20 Cycles, 

re-inspect engine in accordance with 

Section 3, Accomplishment Instructions 

of Rolls-Royce NMSB No. 72-AF994 

Total Number of IP Turbine 

Blade Outer Shroud Dust 

Caps lifting exceeds 10 but 

is equal to or less than 20 

At intervals not to exceed 10 Cycles, 

re-inspect engine in accordance with 

Section 3, Accomplishment Instructions 

of Rolls-Royce NMSB No. 72-AF994 

Total Number of IP Turbine 

Blade Outer Shroud Dust 

Caps lifting exceeds 20 

Within 10 Cycles, remove engine from 

service and incorporate Rolls-Royce 

service bulletin No. 72-D733 

Total Number of IP Turbine 

Blade Outer Shroud Dust 

Caps missing is equal to or 

exceeds 1 

Before further flight, remove engine from 

service and incorporate Rolls-Royce 

service bulletin No. 72-D733 

Note: In deviation to the instructions of Rolls-Royce NMSB No. 72-AF994, the 

inspections required by 1) and 2) above can also be carried out while the 

engine is not installed on an aircraft.

Ref. Publications: 

Rolls-Royce RB211 Propulsion System Non Modification Service Bulletin 

(NMSB) No. 72-AF994. 

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. The required actions and the risk allowance have granted the issuance of a 

Final AD with Request for Comments, postponing the public consultation 

process after publication. 

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 question 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