EASA AD No.: 2012-0163

CAP.00110-001 © 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.: 2012-0163

Date: 28 August 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 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]. 

Design Approval Holder’s Name: 

Rolls-Royce Deutschland Ltd & Co KG 

Type/Model designation(s): 

Tay 611-8 engines 

TCDS Number: EASA.E.063 

Foreign AD: Not applicable 

Supersedure: None 

ATA 72 Engine – Low Pressure Turbine Stage 1 Air Seal and High Pressure 

Turbine Stage 1 Air Seal / Bolts – Inspection / Replacement

Manufacturer(s): Rolls-Royce Deutschland Ltd & Co KG (RRD), formerly Rolls-Royce plc 

Applicability: Tay 611-8 engines, serial numbers 16245, 16256, 16417, 16418, 16584, 

16585, 16639, 16640, 16701, 16702, 16813, 16814, 16853, 16854, 16879, 

16880, 16898, 16905, 16906, 16911, 16923, 16935 and 16936. 

These engines are known to be installed on, but not limited to, Gulfstream IV 

aeroplanes. 

Reason: The results of a recent quality review of low pressure turbine (LPT) stage 1 

static air seal and high pressure turbine (HPT) stage 1 air seal support bolts 

identified that, before installation, these bolts may have not been inspected. As 

a consequence, bolts with reduced material properties may have been installed 

in some engines. 

This condition, if not detected and corrected, could lead to failure of a bolt, 

potentially causing turbine disc fracture and release of high-energy debris, 

possibly resulting in damage to the aeroplane and/or injury to the occupants. 

To address this potential unsafe condition, RRD issued Alert Service Bulletin 

(ASB) TAY-72-A1696 providing instructions to inspect bolts installed in the LPT 

stage 1 static air seal and HPT stage 1 air seal support on a number of 

engines. 

For the reasons described above, this AD requires inspection of the affected 

bolts and, depending on findings, replacement with serviceable ones and 

reporting of findings. 
EASA AD No.: 2012-0163

CAP.00110-001 © 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: 11 September 2012 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 30 days after the effective date of this AD, review the engine 

maintenance records and identify the date of the engine last shop visit. 

(2) For engines with a date of the last shop visit before 08 December 2006, 

within 5 500 engine cycles accumulated since that engine last shop visit, 

inspect bolts installed in the LPT stage 1 static seal and HPT stage 1 air 

seal support in accordance with the accomplishment instructions of RRD 

ASB TAY-72-A1696. 

(3) If, during the inspection as required by paragraph (2) of this AD, any brown 

bolt or bolt with a rough oxidized surface is identified, before release to 

service of the engine, replace the applicable bolt sets in accordance with 

accomplishment instructions of RRD ASB TAY-72-A1696. 

(4) If, during the inspection as required by paragraph (2) of this AD, any bolt 

heads and visible threads discoloration and oxidation are identified, within 

30 days after the inspection, complete the Accomplishment Form of the 

ASB TAY-72-A1696 and send it to RRD Service Engineering, and 

accomplish RRD instructions accordingly, if applicable. 

(5) From the effective date of this AD, do not install an HPT and/or LPT 

module on an engine, or an engine on aeroplane, unless in compliance 

with requirements of this AD. 

Ref. Publications: Rolls-Royce Deutschland ASB TAY-72-A1696 at Revision 1. 

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. This AD was posted on 20 July 2012 as PAD 12-083 for consultation until 

17 August 2012. The Comment Response Document can be found at 

http://ad.easa.europa.eu. 

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 

Tel: + 49 (0) 33 708 6 1200 (direct 1016) Fax: + 49 33 708 6 1212.