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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2007–0004 

Date: 08 January 2007

No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the 

requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry.

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: This AD supersedes and cancels EASA AD 2006-0239 R2 dated 13 October 2006, the 

original publication of which superseded and cancelled CAA UK Airworthiness Directive 002-08-2002.

ATA 05 Time Limits - HP Compressor Stage 5-6 Rotor Disc Cyclic Life 

Manufacturer: Rolls-Royce plc 

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

and 875-17, known to be installed on Boeing 777 series aeroplanes. 

Reason: Rolls-Royce Service Bulletin RB 211-72-AE082 was initially issued in 2002 

and was made mandatory by UK CAA Airworthiness Directive 002-08-2002. 

The Service Bulletin addressed cracking in Trent 800 HP Compressor stage 

5-6 rotor disc stage 5 and 6 loading slots. A cyclic life limit lower than that 

declared in the Time Limits manual was applied to the disc. The cyclic life 

was a function of engine thrust rating and model with a lower life being 

applied to the higher thrust rating models. Later revisions (2 & 3) introduced 

further life reductions and a rework solution to restore component life. 

Rolls-Royce has now introduced a Multiple Flight Profile Monitoring 

methodology (NMSB 72-AE935) for life limited parts in which the published 

lives are in the form of Standard Duty Cycles. Standard Duty Cycles are 

obtained by multiplying flight cycles by a factor (the Beta factor) that is 

defined according to the flight profile group which is applicable to the fleet. A 

separate flight profile (called “Heavy”) is also introduced and is based on 

normal flight cycles. 

Rolls-Royce has therefore re-issued Service Bulletin RB 211-72-AE082 to 

define this new methodology. As this is a significant revision to the original 

Service Bulletin affecting compliance methodology, it was deemed 

necessary to supersede CAA Airworthiness Directive 002-08-2002, which 

was done by the issuance of EASA AD 2006-0239. 
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Revision 1 of EASA AD 2006-0239 was issued to delay the introduction of 

the new cyclic lives. 

Revision 2 of EASA AD 2006-0239 was necessary due to a delay in the 

introduction of the new Multiple Flight Profile Monitoring methodology which 

has affected the dates quoted in the Compliance section. 

A minor error was then discovered in the lifing calculations for FK25230 

which resulted in a reduction in some of the lives. It was therefore 

necessary to supersede EASA Airworthiness Directive 2006-0239 with this 

AD. 

This AD is necessary as life reductions are applicable in some cases and 

failure to comply with the revised life limits could result in an unsafe 

condition. 

Effective Date: 22 January 2007 

Compliance: The following HP Compressor stage 5-6 rotor disc cyclic life limits must be 

complied with as detailed below: 

1) Up to and including 30 January 2007: 

Part number FK 25230 and FK 27899: 

a) Trent 875-17, 877-17, 884-17, 884B-17, 892-17 and 892B-17 

ratings, no component to exceed 7500 flight Cycles. 

b) Trent 895-17 rating, no component may exceed 7370 Flight 

Cycles. 

2) From 31 January 2007 to 31 May 2009: 

a) Part number FK 25230: 

i) Aircraft operating within Multiple Flight Profile Monitoring 

(other than “Heavy”) as defined in the Aircraft Maintenance 

Manual 70-01-10, no component may exceed 7470 Standard 

Duty Cycles. 

ii) Aircraft operating in the “Heavy” Flight Profile as defined in 

the Aircraft Maintenance Manual 70-01-10, no component 

may exceed 6410 Flight Cycles. 

b) Part number FK 27899: 

i) Aircraft operating within Multiple Flight Profile Monitoring 

(other than “Heavy”) as defined in the Aircraft Maintenance 

Manual 70-01-10, no component may exceed 7500 Standard 

Duty Cycles. 

ii) Aircraft operating in the “Heavy” Flight Profile as defined in 

the Aircraft Maintenance Manual 70-01-10, no component 

may exceed 7400 Flight Cycles. 

3) After 31 May 2009: 

Part Number FK 25230 and FK 27899: 

Aircraft operating within Multiple Flight Profile Monitoring or the 

“Heavy” Flight Profile as defined in the Aircraft Maintenance 
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Manual 70-01-10, no component may exceed 5000 Standard 

Duty Cycles or 5000 Flight Cycles respectively. 

Ref. Publications: Rolls-Royce RB211 Propulsion System Non Modification Service Bulletin 

Alert RB211-72-AE082 Revision 5 or later approved revisions. 

Remarks: 1. If requested and appropriately substantiated the responsible EASA 

manager for the related product has the authority to accept Alternative 

Methods of Compliance (AMOCs) for this AD. 

2. The original AD 2006-0239 was posted on 07 July 2006 as PAD 06-

179 for consultation until 07 August 2006. No comments were received 

during the consultation period. Given this fact and the limited time 

available it was considered reasonable not to submit this AD for 

consultation. 

3. Enquiries regarding this Airworthiness Directive should be referred to 

the Airworthiness Directive Focal Point - Certification Directorate, 

EASA. E-mail: ADs@easa.europa.eu

4. For any questions concerning the technical content of the 

requirements in this AD, please contact Rolls-Royce plc. PO Box 31, 

Derby, DE24 8BJ, United Kingdom; Telephone +44 (0)1332-242424; 

Facsimile +44 (0)1332-249936.