EASA AD No.: 2012-0185-E

CAP.00111-001 © European Aviation Safety Agency. Al l rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2012-0185-E

Date: 12 September 2012

Note: This Emergency Airworthiness Directive (AD) i s issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the E uropean 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 be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption].


### Design Approval Holder’s Name: Rolls-Royce Deutschland Ltd & Co KG Type/Model designation(s): Tay 620-15 series engines

TCDS Number: EASA.E.063

Foreign AD: Not applicable

Supersedure: None



### ATA 72 Engine – Low Pressure Compressor Rotor Blades – Ins pection / Replacement

Manufacturer(s): Rolls-Royce plc

Applicability: Tay 620-15 engines, serial numbers 1 7054, 17085, 17088, 17107 and 17166. These engines are known to be installed on, but not limited to, Fokker F28 Mk.0070 and Fokker F28 Mk.0100 aeroplanes.

Reason: Fan blade off on a Tay 620-15 engine has re cently been reported. Subsequent investigation results identified vibration induced by a fan blade flutter as a possible cause of fan blade root failure leading to the blade off.
This condition, if not detected and corrected, coul d lead to the blade failure potentially causing release of high-energy debris, possibly resulting in damage to the aeroplane and/or injury to the occupants. To minimise the potential for further fan blade fai lure occurrences Rolls Royce Deutschland (RRD) issued a Non-Modification Service Bulletin (NMSB) Alert Tay-72-A1775 providing instruction for Low Pressure Compressor (LPC) fan blades inspection. The NMSB Alert Tay-72-A1775 was updated to Revision 1 shortly after Initial issue was released due to min or wording correction. For the reasons described above, this AD requires a ccomplishment of two ultrasonic inspections of the LPC fan blades and, d epending of finding, accomplishment of a corrective action.

Effective Date: 12 September 2012EASA AD No.: 2012-0185-E

CAP.00111-001 © European Aviation Safety Agency. Al l rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Before next flight, after the effective date of this AD, and thereafter before 1 500 engine flight hours (EFH) but not before 1 00 0 EFH after initial inspection, accomplish an ultrasonic inspection of the LPC fan blades in accordance with RRD NMSB 72-A1775 Revision 1. (2) If during any of the two inspections as require d by paragraph (1) of this AD, any indication of a fan blade crack is detected, be fore next flight, replace the complete set of LPC fan blades and the LPC fan disc with a serviceable LPC fan blade set and LPC fan disc. Aft er replacement return the removed parts to RRD for further investigation. (3) Replacement of the set of LPC fan blades and LP C fan disc, as required by paragraph (2) of this AD constitutes terminating action for inspections required by paragraph (1) of this AD.

Ref. Publications: RRD NMSB Alert Tay-72-A1775 Revi sion 1, dated 12 September 2012. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The results of the safety assessment have indica ted the need for immediate publication and notification, without the full public consultation process. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive 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 Deutschland Ltd & Co KG Eschenweg 11 - 15827 Dahlewitz – Germany Phone: +49 (0) 33 7086 1768 ; Fax: +49 (0) 33 7086 3356.