EASA AD No.: 2013-0143

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0143

Date: 12 July 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 620, Tay 650, and Tay 651 engines

TCDS Number: EASA.E.063

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2013-0071 d ated 19 March 2013.



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

Manufacturer(s): Rolls-Royce plc

Applicability: Tay 620-15, Tay 620-15/20, Tay 650-1 5, Tay 650-15/10 and Tay 651-54 engines, all serial numbers. These engines are known to be installed on, but not limited to, Fokker F28 Mark 0070 and Mark 0100, and on Boeing 727 (STC-mod ified) series aeroplanes.
Reason: Service history of Tay series engines disco vered that low pressure compressor (LPC) fan blade leading edge is exposed to excessiv e deterioration. The LPC fan blade leading edge profile influences the LPC a erodynamic 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 at initial issue and revision 1 to pro vide instructions for reprofiling of LPC fan blade leading edge profile of Tay 650-15 and Tay 650- 15/10 engines. Consequently, EASA issued AD 2013-00 71 to require implementation of repetitive re-profiling for the a ffected parts. Since that AD was issued, RRD issued NMSB TAY-72-A1 782 Revision 2 to make the re-profiling instructions of LPC fan blade leading edge also applicable to Tay 620-15, Tay 620-15/20 and Tay 651-54 engines , due to the similarity ofEASA AD No.: 2013-0143

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. fan blade design used in these engines and hence po ssibility of fan blade root cracking imposed by fan flutter generated high stre ss. For the reasons described above, this AD retains th e requirements of AD 2013-0071, which is superseded, and expands the Applicability to Tay 620- 15, Tay 620-15/20 and Tay 651-54 engines.

Effective Date: 26 July 2013

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: Note: For the purpose of this AD, fan blade flight cycles (FC) means FC accumulated by the fan blade since new or since the last re-profiling in accordance with RRD NMSB TAY-72-A1782 or TAY-72-160 3, or in accordance with Engine Manual Repair HRS3629 (Engine Manual, C hapter 72-31-12, TASK 72-31-12-300-005), as applicable. Tay 620-15 and 620-15/20 engines: (1) Within the compliance time as specified in Tabl e 1 of this AD, as applicable, and thereafter at intervals not to exce ed 12 000 FC, accomplish a fan blade re-profiling in accordance with accompl ishment instructions of RRD Alert NMSB TAY-72-A1782.
Table 1

Fan blade FC accumulated on the effective date of this AD Compliance time
Less than 10 000 FC Before accumulating 12 000 FC Equal to or more than 10 000 FC Within 2 000 FC aft er the effective date of this AD Tay 650-15, Tay 650-15/10 and Tay 651-54 engines: (2) Within the compliance time as specified in Tabl e 2 of this AD, as applicable, and thereafter at intervals not to exce ed 10 000 FC, accomplish a fan blade re-profiling in accordance with accompl ishment instructions of RRD Alert NMSB TAY-72-A1782.
Table 2

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 (3) For Tay 650-15 and Tay 650-15/10 engines, fan b lade leading edge reprofiling accomplished before the effective date of this AD in accordance with RRD Alert NMSB TAY-72-A1782 at initial issue o r revision 1 is acceptable to comply with the initial requirements of paragraphs (2) of this AD. All engine models: (4) 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. (5) If, on the effective date of this AD, the engin e is in shop or undergoing overhaul, before release to service of the engine, accomplish a fan blade re-profiling in accordance with Instruction II of R RD Alert NMSB TAY-72-A1782.EASA AD No.: 2013-0143

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. (6) Compliance with the requirements of paragraphs (1) and (2) of this AD can be demonstrated by: (6.1) 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 (6.2) Complying with the approved AMP as described in paragraph (6.1) of this AD.

Ref. Publications: RRD Alert NMSB TAY-72-A1782 revi sion 2 dated 30 May 2013. RRD NMSB TAY-72-1603 Initial issue, dated 21 June 2 004. Engine Manual Repair HRS3629 issue 04, dated 15 Dec ember 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. 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 Tel: + 49 (0) 33 708 6 1200 (direct 1016) Fax: + 49 33 708 6 1212. E-mail: RRDTechnicalHelpdesk@Rolls-Royce.com

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