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 i ssued 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 t he 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, exc ept in accordance with the requirements of that Airworthine ss Directive unless otherwise specified by the Agency [EC 2042/2003 A nnex I, Part M.A.303] or agreed with the Authority of the Sta te 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 instal led 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 fou nd 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 vulnerab ility of the part to tensile stresses, which could reduce the life of the sha ft 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 us age 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 subs tantiated, 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 a llowance 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 & Re search Section, Certification Directorate, EASA. E-mail ADs@easa.europa.eu 4. For any question concerning the tec hnical 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