EASA AD No.: 2013-0071

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.: 2013-0071

Date: 19 March 2013

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 650-15 and Tay 650-15/10 series engines

TCDS Number: EASA.E.063

Foreign AD: Not applicable

Supersedure: None



### ATA 72 Engine – Low Pressure Compressor / Rotor Blade Lead ing Edge – Re-profiling

Manufacturer(s): Rolls-Royce plc

Applicability: Tay 650-15 and Tay 650-15/10 engines , all serial numbers. These engines are known to be installed on, but not limited to, Fokker F28 Mark 0100 series aeroplanes.
Reason: Service history of Tay series engines disco vered that low pressure compressor (LPC) fan blade leading edge could be subject of ex cessive deterioration. The LPC fan blade leading edge profile influences the L PC aerodynamic characteristics and stability. This condition, if not corrected, could reduce fan flutter margin and, in some cases, could lead to fan blade failure, possibly re sulting in uncontained release of high energy debris with consequent damage to, an d/or reduced control of, the aeroplane. To address this potential unsafe condition, Rolls-R oyce Deutschland Ltd & Co KG (RRD) issued Alert Non-Modification Service Bull etin (NMSB) TAY-72-A1782 to provide instructions for re-profili ng of LPC fan blade leading edge profile. For the reasons described above, this AD requires i mplementation of repetitive re-profiling for the affected parts.

Effective Date: 02 April 2013EASA AD No.: 2013-0071

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. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within the compliance time as specified in Tabl e 1 of this AD, as applicable, and thereafter at intervals not to exce ed 10 000 flight cycles (FC), accomplish a fan blade re-profiling in accord ance with accomplishment instruction of RRD Alert NMSB TAY-72 -A1782.
Table 1

Fan blade FC accumulated on the effective date of this AD Compliance time
Less than 8 000 FC Before accumulating 10 000 FC Equal to or more than 8 000 FC Within 2 000 FC afte r the effective date of this AD Note: For the purpose of this AD, fan blade FC mean s FC accumulated by the fan blade since new or since the last re-profiling in accordance with RRD NMSB TAY-72-1603, or in accordance with Engine Manu al Repair HRS3629 (Engine Manual, Chapter 72-31-12, TASK 72-31-12-300 -005), as applicable. (2) From the effective date of this AD, do not inst all a LPC module on an engine, or an engine on an aeroplane, unless in com pliance with the requirements of this AD. (3) Compliance with the requirements of paragraphs (1) and (2) of this AD can be demonstrated by: (3.1) Revising as follows, the approved Aircraft Ma intenance Programme (AMP) on the basis of which the operator or the own er ensures the continuing airworthiness of each operated aeroplane : Incorporate the LPC fan blade repetitive re-profil ing as specified in RRD Alert NMSB TAY-72-A1782,
and (3.2) Complying with the approved AMP as described in paragraph (3.1) of this AD.

Ref. Publications: RRD Alert NMSB TAY-72-A1782 Init ial Issue dated 06 February 2013 or Revision 1 dated 08 February 2013. RRD NMSB TAY-72-1603 Initial issue, dated 21 June 2 004. Engine Manual Repair HRS3629 dated 15 December 2007

. The use of later approved revisions of these docume nts 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. This AD was posted on 14 February 2013 as PAD 13 -035 for consultation until 14 March 2013. No comments were received duri ng the consultation period. 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 Tel: + 49 (0) 33 708 6 1200 (direct 1016) Fax: + 49 33 708 6 1212.