EASA AD No.: 2010-0097 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0097 

Date: 26 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 AD applies, except in accordance with the requirements of that AD 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 series engines 

TCDS Number : UK CAA 1051 

Foreign AD : Not applicable 

Supersedure : None 

ATA 72 Engine – Low Pressure Compressor Fan Blades - Inspection 

Manufacturer(s): Rolls-Royce plc 

 Applicability: Models RB211 Trent 895-17, 892-17, 892B-17, 884-17, 884B-17, 877-17 

and 875-17. 

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

aeroplanes. 

Reason: In January 2009 a Trent 895 powered Boeing 777-200 aircraft experienced 

release of a Low Pressure (LP) compressor blade which failed due to fatigue 

cracking in the root section of the blade. The released blade (undercut root 

standard) had received a part life processing to apply a compression layer to the 

blade root (Service Bulletin SB72-D672 - Introduction of Laser Shock Peening 

(LSP)) and also a part life upgrade to the retention feature lubrication system. 

Investigation has revealed that the effectiveness of this upgraded blade root 

lubrication coating system may be reduced dependant on the extent of previous 

running with the earlier standard, leading to increased blade root stress levels. In 

the specific case of the released blade, a review of its in-service modification 

history has shown that it operated for a relatively high number of flight cycles prior 

to the compression layer processing and the new retention feature lubrication 

system. A review of the Engine Health Monitoring data has also identified it 

operated at high N1 speeds compared to the Trent 800 fleet average N1 speeds. 

The combination of these factors has resulted in increased fatigue life usage 

which is considered to have led to crack initiation and propagation prior to 

reaching the blades declared life limit. A review of all in-service undercut / LSP 
EASA AD No.: 2010-0097 

EASA Form 110 Page 2/3 

standard Trent 800 LP compressor blades has identified specific blades that carry 

a similar increased susceptibility to cracking. 

This AD is issued to mitigate the risk of possible multiple fan blades failure 

affecting those blades identified as described above which could lead to high 

energy non contained debris from the engine. 

This AD requires repetitive ultrasonic inspections of the specific LP compressor 

blades as identified in the Rolls Royce Non Modification Service Bulletin (NMSB) 

RB211-72-AG244 to detect possible root cracks developing in the undercut radius 

shear key slot area and, if necessary, replacement of any LP compressor blade. 

Effective Date: 09 June 2010 

Required 

Action(s) and 

Compliance 

Time(s): 

Required as indicated: 

(1) Initial Inspection: as specified in the first column of Table 1 (below) inspect 

the affected LP compressor blades complying with the corresponding 

thresholds indicated in the second column, in accordance with (i.a.w.) 

Section 3 “Accomplishment Instructions” of Rolls Royce Non Modification 

Service Bulletin (NMSB) RB211-72-AG244, rejected LP compressor blades 

must be removed from the engine before next flight.

(2) Repetitive Inspections: following Initial Inspection, repeat the inspection at 

recurring intervals not exceeding 100 flight cycles and reject, as required, 

the affected LP compressor blades as detailed in paragraph (1) of this AD. 

(3) After the thresholds indicated in Table 1 of this AD, do not install any affected 

LP compressor blade unless previously inspected i.a.w. the requirements of 

paragraph (1) of this AD and thereafter, repeat the inspection i.a.w. 

paragraph (2) of this AD. 

Table 1: 

Appendix number of NMSB RB211-72-AG244 

which identifies affected LP compressor blades by 

Serial Number: 

Initial Inspection threshold 

3A 120 Flight Cycles after the 

effective date of this AD 

3B No later than 1 January 

2012 

3C No later than 1 January 

2013 

3D No later than 1 January 

2014 

3E No later than 1 January 

2015 

3F No later than 1 January 

2016 
EASA AD No.: 2010-0097 

EASA Form 110 Page 3/3 

Ref. 

Publications: 

Rolls-Royce RB211 Propulsion System Non Modification Service Bulletin RB211-

72-AG244 Initial issue. 

The use of later approved revisions 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. This AD was posted on 23 March 2010 as PAD 10-030 for consultation until 

20 April 2010. No comments were received during the consultation period. 

3. Enquiries regarding this AD should be referred to the Airworthiness Directives, 

Safety Management & Research Section, Certification Directorate, EASA. Email 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.