EASA AD No.: 2010-0087

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0087 [corrected: 06 May 2010]

Date: 05 May 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 b e ensured by accomplishing any applicable ADs. Cons equently, no person may operate an aircraft to which an Airworthiness D irective applies, except in accordance with the req uirements 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, Ar ticle 14(4) exemption]. 

### Type Approval Holder’s Name : 

### ROLLS-ROYCE plc Type/Model designation(s) :
RB211 Trent 800 Engines

TCDS Number : UK CAA 1051

Foreign AD : Not applicable

Supersedure : This AD supersedes EASA AD 2008-0099 dated 21 May 2008 and corrected

on 12 June 2008



### ATA 72 Engine – High Pressure Compressor Stage 1- 4 Shaft – Life

Limit Reduction

Manufacturer(s): Rolls-Royce plc

Applicability: RB211 Trent 895-17, 892-17, 892B-17, 884-17, 884B-17, 877-17 and 875-17 engines if fitted with HP Compressor Stage 1 - 4 shaft part number FK32580. These engines are known to be installed on, but not limited to Boeing 777 series aircraft.

Reason: During manufacture of High Pressure (HP) Co mpressor stage 1 discs a small number of parts have been rejected due to a m achining defect that was found during inspection. Analysis of the possibility of less severe examples having been undetected and passed into service has concluded th at action is required to reduce the risk of failure. It was therefore necessary to reduce the life limit . The new applied life limits were required by AD 2008-0099. However, some life limits for the Heavy Flight Profile Parts were incorrect.

This new AD partially retains the requirements of E ASA AD 2008-0099, which is superseded, and, in addition, requires the implementation of more restrictive life limits for use in the Heavy Flight Profile Parts. This AD has been corrected as, inadvertently, a wr ong effective date wasEASA AD No.: 2010-0087

EASA Form 110 Page 2/3 indicated for the Heavy Flight Profile Parts.

Effective Date: 19 May 2010

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: RB211 Trent 800 Critical Part lives may be monitore d by one of two methods: “Multiple Flight Profile Monitoring”; or “ Heavy Flight Profile” (for details refer to RR Engine Manual Airworthiness Lim itations Section). This Compliance section is therefore divided into two se ctions to address these two possibilities.

(1) Multiple Flight Profile Monitoring parts:

(a) On 04 June 2008 (effective date of EASA AD 200 8-0099), if the part life is equal to or over 5 580 Standard Duty C ycles (SDC) then the part must be withdrawn from service before exceedin g 7 780 SDC.

Note 1: Standard Duty Cycles (SDC) is the product of Fligh t Cycles and Beta Factor, as specified in the RR Engine Manual A irworthiness Limitations Section.

(b) On 04 June 2008 (effective date of EASA AD 200 8-0099), if the part life is between 3 380 SDC and 5 580 SDC then t he part should be withdrawn from service before exceeding a further 2 200 SDC.

(c) On 04 June 2008 (effective date of EASA AD 200 8-0099), if the part life is equal to or below 3 380 SDC then the p art must be withdrawn from service before exceeding 5 580 SDC.

Note 2 : Operators should be aware that reassessment of th e revised life limit in accordance with this AD (including possibl e reassessment of the applicable subsection (a), (b), or (c) (above)) wil l be necessary if, at some time in the future, the operator changes the flight profile that was applicable before the Effective Date, such that par ts which are the subject of this AD are affected. To recalculate the revised life limit, the life of the part, in Standard Duty Cycles, at the Effective Dat e must be recalculated from the part's entry into service (zero life), and must use the Beta factor(s) for the new flight profile(s).

(2) Heavy Flight Profile Parts:

(a) On 04 June 2008 (effective date of EASA AD 200 8-0099), if the part life is equal to or over 5 280 Flight Cycles t hen the part must be withdrawn from service before exceeding 6850 Flight Cycles.

(b) On 04 June 2008 (effective date of EASA AD 200 8-0099), if the part life is between 3710 Flight Cycles and 5280 Fl ight Cycles then the part should be withdrawn from service before exceed ing further 1570 Flight Cycles.

(c) On 04 June 2008 (effective date of EASA AD 200 8-0099), if the part life is equal to or below 3710 Flight Cycles t hen the part must be withdrawn from service before exceeding 5280 Flight Cycles.
Ref. Publications: Rolls-Royce Alert Non Modificati on Service Bulletin RB211-72-AF825 Revision 3. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.EASA AD No.: 2010-0087

EASA Form 110 Page 3/3 Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The required actions and the risk assessment hav e granted the issuance of a Final AD with Requests for Comments, postponing the public consultation process after publication. 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 question concerning the technical conten t 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 24993 6. Email: tech.help@rolls-royce.com or download the publication from https://www.aeromanager.com

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