EASA AD No.: 2012-0039-E

EASA Form 111 Page 1/2 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2012-0039-E

Date: 09 March 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 accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption]. 

### Type Approval Holder’s Name : Rolls-Royce Deutschland Ltd & Co KG Type/Model designation(s) : Tay 611-8 and 611-8C engines

TCDS Number: EASA.E.063

Foreign AD: Not applicable

Supersedure: None



### ATA 72 Engine – Stage 2 High Pressure Turbine Disc Spanner Retaining Nut – Replacement

Manufacturer(s): Rolls-Royce Deutschland Ltd & Co K G, Rolls-Royce plc.

Applicability: TAY 611-8 engines, serial numbers (s /n) 16870, 16879, 16880, 16897, 18046, 18051, 18052, 18053, 18058, 18065, 18066, 18 169 and 18194 TAY 611-8C engine, s/n 85313. These engines are known to be installed on, but not limited to, Gulfstream Aerospace G-IV, GIV-SP and GIV-X aeroplanes.
Reason: A recent quality investigation by Rolls-Roy ce Deutschland has identified that certain Stage 2 High Pressure Turbine (HPT) disc sp anner retaining nuts did not receive the proper heat treatment after applica tion of silver plating. This condition, if not corrected, could result in a Stage 2 HPT disc failure, possibly leading to release of high energy debris, resulting in damage to the aeroplane and/or injury to occupants. For the reason described above, this Emergency AD r equires the removal of the affected engines from service. This AD is considered to be an interim action, pend ing availability of approved instructions for corrective action, which would allow these engines to be released to service.

Effective Date: 09 March 2012EASA AD No.: 2012-0039-E

EASA Form 111 Page 2/2 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 20 flight cycles (FC), or within 200 FC after the latest engine shop visit, whichever occurs first after the effective d ate of this AD, remove the engine from the aeroplane. (2) From the effective date of this AD, do not inst all an engine, identified by s/n in the Applicability section of this AD, on an aeroplane.

Ref. Publications: None.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The safety assessment has requested not to imple ment the full consultation process and an immediate publication a nd notification. 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.