EASA AD No.: 2008-0122 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2008-0122 

Date: 01 July 2008 

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 Deutschland Ltd & Co KG 

Type/Model designation(s) : 

TAY 650 / TAY 650-15 

TCDS Number : LBA Germany No. 6328 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2006-0288, dated 15 September 2006. 

ATA 72 Engine - Low Pressure Turbine Discs Stage 2 and 3 – 

Inspection/Replacement 

Manufacturer(s): Rolls-Royce plc. 

Applicability: TAY 650-15 Engines, engine serial numbers 17249, 17251, 17255, 17256, 

17273, 17275, 17280, 17281, 17282, 17300, 17301, 17303, 17327, 17332, 

17358, 17365, 17370, 17393, 17425, 17426, 17433, 17437, 17438, 17443, 

17445, 17446, 17460, 17470, 17474, 17478, 17490, 17491, 17517, 17518, 

17520, 17521, 17522, 17523, 17534, 17535, 17536, 17538, 17539, 17540, 

17541, 17542, 17552, 17553, 17556, 17561, 17562, 17563, 17580, 17581, 

17585, 17612, 17613, 17618, 17635, 17637, 17645, 17661, 17686, 17699, 

17701, 17702, 17723, 17724, 17736, 17737, 17738, 17739, 17740, 17741, 

17742, 17759, 17760, 17807 and 17808 

with Module M05300AA (LP Turbine Module) installed. 

These engines are known to be installed in Fokker F28 Mark 0100 aircraft. 

Reason: Strip results from some of the engines listed in the applicability section of this 

directive revealed excessively corroded low pressure turbine discs stage 2 

and stage 3. The corrosion is considered to be caused by the environment in 

which these engines are operated. 

Following a life assessment based on the strip findings it is concluded that 

inspections for corrosion attack are required. 

The action specified by this AD is intended to avoid a failure of a low 

pressure turbine disk stage 2 or stage 3 due to potential corrosion problems 

which could result in uncontained engine failure and damage to the airplane. 

EASA Form 110 Page 1/2 
EASA AD No.: 2008-0122 

This Airworthiness Directive has been issued, superseding AD 2006-0288, to 

extend the Applicability to further engine serial numbers. 

Effective Date: 15 July 2008 

Required action(s) and 

Compliance Time(s): 

Required as indicated, unless accomplished previously: 

A) Prior to accumulating 11 700 flight cycles (FC) and thereafter at intervals 

not exceeding 11 700 FC of the engine, inspect the low pressure turbine 

discs stage 2 and stage 3 for corrosion in accordance with Rolls-Royce 

Deutschland Non-Modification Alert Service Bulletin TAY-72-A1524. 

B) When, during any of the inspections as required by paragraph A) of this 

directive, corrosion is found, replace the affected parts using the 

rejection criteria described in the Rolls-Royce TAY 650 Engine Manual - 

E-TAY-3RR, latest revision. 

All necessary inspections must be accomplished in accordance with the TAY 

650 Engine Manual - E-TAY-3RR, Chapters 72-52-23 and 72-52-24.

Ref. Publications: Rolls-Royce Deutschland Non-Modification Alert Service Bulletin TAY-72-

A1524, Revision 2, dated 13 June 2008. 

Rolls-Royce Deutschland TAY 650 Engine Manual - E-TAY-3RR, Chapters 

72-52-23 and 72-52-24. 

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 substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The required actions and the risk allowance 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 & Research Section, 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 Deutschland Ltd & Co KG 

Eschenweg 11 - 15827 Dahlewitz – Germany 

Phone: +49 (0) 33 7086 1768 ; Fax: +49 (0) 33 7086 3356 

EASA Form 110 Page 2/2