EASA AD No.: 2012-0163

CAP.00110-001 © European Aviation Safety Agency. Al l rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0163

Date: 28 August 2012

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 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 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 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 / Rep lacement

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

Applicability: Tay 611-8 engines, serial numbers 16 245, 16256, 16417, 16418, 16584, 16585, 16639, 16640, 16701, 16702, 16813, 16814, 16 853, 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 l ow pressure turbine (LPT) stage 1 static air seal and high pressure turbine (HPT) sta ge 1 air seal support bolts identified that, before installation, these bolts m ay have not been inspected. As a consequence, bolts with reduced material properti es may have been installed in some engines.

This condition, if not detected and corrected, coul d lead to failure of a bolt, potentially causing turbine disc fracture and relea se of high-energy debris, possibly resulting in damage to the aeroplane and/o r injury to the occupants.

To address this potential unsafe condition, RRD iss ued Alert Service Bulletin (ASB) TAY-72-A1696 providing instructions to inspe ct bolts installed in the LPT stage 1 static air seal and HPT stage 1 air seal su pport on a number of engines.

For the reasons described above, this AD requires i nspection 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. Al l rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Effective Date: 11 September 2012

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:

(1) Within 30 days after the effective date of this AD, review the engine maintenance records and identify the date of the en gine 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 e ngine last shop visit, inspect bolts installed in the LPT stage 1 static s eal 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 paragr aph (2) of this AD, any brown bolt or bolt with a rough oxidized surface is ident ified, 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 paragr aph (2) of this AD, any bolt
heads and visible threads discoloration and oxidati on are identified, within 30 days after the inspection, complete the Accompli shment Form of the ASB TAY-72-A1696 and send it to RRD Service Enginee ring, and accomplish RRD instructions accordingly, if applica ble.

(5) From the effective date of this AD, do not inst all an HPT and/or LPT module on an engine, or an engine on aeroplane, unl ess 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 documen t 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. This AD was posted on 20 July 2012 as PAD 12-083 for consultation until 17 August 2012. The Comment Response Document can b e found at http://ad.easa.europa.eu

. 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.