EASA AD No.: 2012-0234

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0234

Date: 06 November 2012

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.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 Bla des – Inspection

Manufacturer(s): Rolls-Royce plc

Applicability: Tay 620-15/20 and Tay 620-15 engines , serial numbers 17085, 17088, 17166, 17072, 17073, 17078 and 17079. These engines are known to be installed on, but not limited to, Fokker F28 Mk.0070 and Fokker F28 Mk.0100 aeroplanes.

Reason: The Low Pressure Compressor (LPC) (fan) bla des of certain Tay 620-15/20 and Tay 620-15 engines show evidence of excessive l eading edge erosion. Excessive material removal during the maintenance r educes the LPC (fan) blade chordal width and potentially changes the bal ance of the fan blade. Reduced chordal width can affect LPC (fan) blade pe rformance and in combination with other circumstances could lead to a fan blade root failure and fan blade separation.
This condition, if not detected and corrected, coul d lead to the LPC (fan) blade failure, potentially causing release of high-energy debris, possibly resulting in damage to the aeroplane and/or injury to the occupa nts. To address this potential unsafe condition, Rolls R oyce Deutschland (RRD) issued Alert Non-Modification Service Bulletin (NMS B) Tay-72-A1777, providing instruction for LPC (fan) blade inspection.
For the reasons described above, this AD requires a ccomplishment of a onetime inspection of affected engine LPC (fan) blades , and depending on findings, repair or replacement with a serviceable part.EASA AD No.: 2012-0234

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Effective Date: 08 November 2012

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, accomplish a onetime inspection of the leading edge of the LPC (fan ) blades and determine if erosion is evident in accordance with accomplishment instructions of RRD NMSB 72-A1777. (2) If, during the inspection as required by paragr aph (1) of this AD, any erosion is detected, before next flight, repair the eroded leading edge in accordance with accomplishment instructions of RRD NMSB 72-A1777. (3) After a repair as required by paragraph (2) of this AD, before next flight, measure the repaired blade chordal width in accorda nce with accomplishment instructions of RRD NMSB 72-A1777. I f the measured blade chordal width is outside the requirements as referenced in RRD NMSB 72-A1777, before next flight, replace the comp lete set of LPC (fan) blades with a serviceable set of LPC (fan) bl ades in accordance with accomplishment instructions of RRD NMSB 72-A17 77. (4) Within 30 days after accomplishment of the meas urement as required by paragraph (3) of this AD, provide, for all repaired blades, the actual chordal width measurement to RRD, Service Engineeri ng.

Ref. Publications: RRD Alert NMSB Tay-72-A1777 Init ial issue, dated 26 October 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. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Commen ts, postponing the public consultation process until after publication

. 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.