EASA AD No.: 2012-0234 

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2012-0234 

Date: 06 November 2012 

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 EU 748/2012, Part 21.A.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 AD applies, except in accordance with the requirements of that AD, 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]. 

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 – 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) blades of certain Tay 620-15/20 

and Tay 620-15 engines show evidence of excessive leading edge erosion. 

Excessive material removal during the maintenance reduces the LPC (fan) 

blade chordal width and potentially changes the balance of the fan blade. 

Reduced chordal width can affect LPC (fan) blade performance 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, could 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 occupants. 

To address this potential unsafe condition, Rolls Royce Deutschland (RRD) 

issued Alert Non-Modification Service Bulletin (NMSB) Tay-72-A1777, providing 

instruction for LPC (fan) blade inspection. 

For the reasons described above, this AD requires accomplishment 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. Confirm revision status through the EASA-Internet/Intranet.

Effective Date: 08 November 2012 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(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 paragraph (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 accordance with 

accomplishment instructions of RRD NMSB 72-A1777. If the measured 

blade chordal width is outside the requirements as referenced in RRD 

NMSB 72-A1777, before next flight, replace the complete set of LPC 

(fan) blades with a serviceable set of LPC (fan) blades in accordance 

with accomplishment instructions of RRD NMSB 72-A1777. 

(4) Within 30 days after accomplishment of the measurement as required by 

paragraph (3) of this AD, provide, for all repaired blades, the actual 

chordal width measurement to RRD, Service Engineering. 

Ref. Publications: RRD Alert NMSB Tay-72-A1777 Initial issue, dated 26 October 2012. 

The use of later approved revisions of this document 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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication. 

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu. 

4. For any question 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.