EASA AD No.: 2012-0158

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.: 2012-0158

Date: 22 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):

Spey 511-8 engines

TCDS Number: EASA.E.064

Foreign AD: Not applicable

Supersedure: None



### ATA 72 Engine – Low Pressure Turbine Support Assembly, Hig h Pressure

Turbine Bearing Support Assembly and Air Seal Sleev e / Bolts – Inspection / Replacement

Manufacturer(s): Rolls-Royce plc.

Applicability: Spey 511-8 engines, serial numbers: 8847, 8853, 8879, 8989, 8994 and 9817.

These engines are known to be installed on, but not limited to, Gulfstream II
and III series aircraft.

Reason: The results of a recent quality review of l ow pressure turbine (LPT) support assembly, high pressure turbine (HPT) bearing suppo rt assembly and HPT air seal sleeve bolts identified that, before installat ion, these bolts are not subjected to a complete quality inspection. As a co nsequence, bolts with reduced material properties 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, Rolls-R oyce Deutschland (RRD), the design approval holder, issued Alert Service Bu lletin (ASB) Sp72-A1068 providing instructions to inspect bolts installed i n LPT support assembly, HPT bearing support assembly and HPT air seal sleeve 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 report of findings.EASA AD No.: 2012-0158

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: 05 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 15 November 2007, within 4 500 engine cycles accumulated since that e ngine last shop visit, inspect bolts installed in the LPT support assembly , HPT bearing support assembly and HPT air seal sleeve in accordance with the accomplishment instructions of RRD ASB Sp72-A1068.

(3) If, during the inspection as required by paragr aph (2) of this AD, any broken bolt, brown bolt or bolt with a rough oxidiz ed surface is identified, before release to service of the engine, replace th e affected bolt sets in accordance with the accomplishment instructions of RRD ASB Sp72-
A1068.

(4) If, during the inspection as required by paragr aph (2) of this AD, any bolt discoloration and oxidation are identified, within 30 days after the inspection, complete the Accomplishment Form of the ASB Sp72-A1068 and send it to RRD Service Engineering, and accompl ish RRD instructions accordingly, if applicable.

(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 the requirements of this AD.

Ref. Publications: Rolls-Royce Deutschland ASB Sp72 -A1068 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 23 July 2012 as PAD 12-084 for consultation until 20 August 2012. No comments were received during th e consultation period.

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.