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) 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 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 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]. 

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 KG, Rolls-Royce plc. 

Applicability: TAY 611-8 engines, serial numbers (s/n) 16870, 16879, 16880, 16897, 

18046, 18051, 18052, 18053, 18058, 18065, 18066, 18169 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-Royce Deutschland has identified that 

certain Stage 2 High Pressure Turbine (HPT) disc spanner retaining nuts did 

not receive the proper heat treatment after application 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 requires the removal of 

the affected engines from service. 

This AD is considered to be an interim action, pending availability of 

approved instructions for corrective action, which would allow these engines 

to be released to service. 

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

EASA Form 111 Page 2/2 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 20 flight cycles (FC), or within 200 FC after the latest engine shop 

visit, whichever occurs first after the effective date of this AD, remove the 

engine from the aeroplane. 

(2) From the effective date of this AD, do not install 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, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The safety assessment has requested not to implement the full 

consultation process and an immediate publication and notification. 

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.