EASA AD No.: 2009-0021 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0021 

[Corrected 09 February 2009]

Date: 06 February 2009 

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 700 and Trent 800 Engines 

TCDS Number : UK CAA 1051, EASA.E.042 

Foreign AD : Not applicable 

Supersedure : None 

ATA 72 Engine – IP and HP Compressor shafts – Inspection 

Manufacturer(s): Rolls-Royce plc 

Applicability: 

RB211 Trent 768-60, 772-60, 772B-60 and 772C-60 engines; 

These engines are known to be installed on, but not limited to, Airbus A330 

series aircraft. 

And RB211 Trent 895-17, 892-17, 892B-17, 884-17, 884B-17, 877-17 and 

875-17 engines; 

These engines are known to be installed on, but not limited to, Boeing 777 

series aircraft. 

Reason: 

In completing a review of Engine Manual repair/acceptance limits for titanium 

compressor shafts, Rolls-Royce has found the specified limits to be incorrect 

such that the shot peened surface layer at life critical features (the axial dovetail 

slots) may have been inadvertently removed in-service. Removal of the shot 

peened layer results in increased vulnerability of the part to tensile stresses, 

which could reduce the life of the shaft to below the published life limits. 

The acceptable limits for material loss on these surfaces have now been 

corrected in the Engine Manual. 

This AD identifies shafts for which such dressing operations have been known 

to have been carried out and requires that an inspection for compliance with the 

corrected Engine Manual limits be accomplished and that the shafts be 

dispositioned accordingly. 

This AD has been corrected to amend a typographical error within the Ref. 

Publications and to specify the Manual revision dates. 
EASA AD No.: 2009-0021 

EASA Form 110 Page 2/3 

Effective Date: 20 February 2009 

Required 

action(s) and 

Compliance 

Time(s): 

The engine components as identified in Table 1 of this AD must be withdrawn 

from service prior exceeding the cyclic usage Compliance Period as specified in 

Table 1 of this AD, in order to carry out a one-time piece part full Focused 

Inspection, in accordance with current applicable RR Engine Manual 

acceptance limits (see Ref. Publications below). 

Table 1 – List of affected shafts 

Engine 

Type Affected Component Part Number 

Shaft Serial 

Number 

Compliance 

Period (Life from 04/12/08*

in flight cycles)

Trent 800 1-8 

IP Compressor Shaft FK24100 MW0115238 750 

Trent 800 1-4 

HP Compressor Shaft FK32580 MW0115512 750 

Trent 800 1-4 

HP Compressor Shaft FK32580 MW0004708 2000 

Trent 800 1-4 

HP Compressor Shaft FK32580 MW00063868 2500 

Trent 800 1-8 

IP Compressor Shaft FK24100 DN65507 2500 

Trent 800 1-8 

IP Compressor Shaft FK24100 DN65158 2500 

Trent 800 1-4 

HP Compressor Shaft FK32580 MW0125467 3500 

Trent 800 1-4 

HP Compressor Shaft FW11590 DN65189 3500 

Trent 800 1-8 

IP Compressor Shaft FK24100 MW0091518 3500 

Trent 800 1-8 

IP Compressor Shaft FK24100 MW0126365 3500 

Trent 800 1-8 

IP Compressor Shaft FK24100 DN66422 4750 

Trent 800 1-8 

IP Compressor Shaft FK24100 MW0203314 4750 

Trent 700 1-8 

IP Compressor Shaft FK22279 DN63228 3250 

Trent 700 1-8 

IP Compressor Shaft FK26048 MW0026046 4500 

* Note 1 - this date has been used to maintain consistency with the associated 

Rolls-Royce Alert Non Modification Service Bulletin RB211-72-AG086. 

Note 2 - Rolls-Royce Alert Non Modification Service Bulletin RB211-72-AG086 

provides a reference to the particular engines which may be fitted with the 

components identified above. 

Ref. 

Publications: 

Rolls-Royce Alert Non Modification Service Bulletin RB211-72-AG086 initial 

issue 

Rolls-Royce Trent 800 Engine Manual E-TRENT-2RR tasks 72-32-31-200-801 

(1-8 IP Compressor Shaft inspection) and 72-41-31-200-801 (1-4 HP 

Compressor Shaft inspection). Manual revision date June 2008 

Rolls-Royce Trent 700 Engine Manual E-TRENT-1RR tasks 72-32-31-200-801 

(1-8 IP Compressor Shaft inspection) and 72-41-31-200-801 (1-4 HP 

Compressor Shaft inspection). Manual revision date June 2008 

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. 
EASA AD No.: 2009-0021 

EASA Form 110 Page 3/3 

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. PO Box 31, Derby, DE24 8BJ, United Kingdom. Phone: 

+44 (0) 1332 242424, Fax: +44 (0) 1332 249936. 

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

https://www.aeromanager.com