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 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 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) Compressor stage 1 discs a 

small number of parts have been rejected due to a machining defect that 

was found during inspection. 

Analysis of the possibility of less severe examples having been 

undetected and passed into service has concluded that 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 EASA 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which is superseded, and, in addition, requires the implementation of more 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 wrong effective date was 
EASA 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 previously: 

RB211 Trent 800 Critical Part lives may be monitored by one of two 

methods: “Multiple Flight Profile Monitoring”; or “Heavy Flight Profile” (for 

details refer to RR Engine Manual Airworthiness Limitations Section). This 

Compliance section is therefore divided into two sections to address these 

two possibilities. 

(1) Multiple Flight Profile Monitoring parts:

(a) On 04 June 2008 (effective date of EASA AD 2008-0099), if the 

part life is equal to or over 5 580 Standard Duty Cycles (SDC) then the 

part must be withdrawn from service before exceeding 7 780 SDC. 

Note 1: Standard Duty Cycles (SDC) is the product of Flight Cycles and 

Beta Factor, as specified in the RR Engine Manual Airworthiness 

Limitations Section. 

(b) On 04 June 2008 (effective date of EASA AD 2008-0099), if the 

part life is between 3 380 SDC and 5 580 SDC then the part should be 

withdrawn from service before exceeding a further 2 200 SDC. 

(c) On 04 June 2008 (effective date of EASA AD 2008-0099), if the 

part life is equal to or below 3 380 SDC then the part must be 

withdrawn from service before exceeding 5 580 SDC. 

Note 2: Operators should be aware that reassessment of the revised life 

limit in accordance with this AD (including possible reassessment of the 

applicable subsection (a), (b), or (c) (above)) will be necessary if, at some 

time in the future, the operator changes the flight profile that was 

applicable before the Effective Date, such that parts 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 Date 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 2008-0099), if the 

part life is equal to or over 5 280 Flight Cycles then the part must be 

withdrawn from service before exceeding 6850 Flight Cycles. 

(b) On 04 June 2008 (effective date of EASA AD 2008-0099), if the 

part life is between 3710 Flight Cycles and 5280 Flight Cycles then the 

part should be withdrawn from service before exceeding further 1570 

Flight Cycles. 

(c) On 04 June 2008 (effective date of EASA AD 2008-0099), if the 

part life is equal to or below 3710 Flight Cycles then the part must be 

withdrawn from service before exceeding 5280 Flight Cycles.

Ref. Publications: Rolls-Royce Alert Non Modification Service Bulletin RB211-72-AF825 

Revision 3. 

The use of later approved revisions of this document 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, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The required actions and the risk assessment have 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 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.