EASA AD No.: 2012-0158

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.: 2012-0158

Date: 22 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):

Spey 511-8 engines 

TCDS Number: EASA.E.064 

Foreign AD: Not applicable 

Supersedure: None 

ATA 72

Engine – Low Pressure Turbine Support Assembly, High Pressure 

Turbine Bearing Support Assembly and Air Seal Sleeve / 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 low pressure turbine (LPT) support 

assembly, high pressure turbine (HPT) bearing support assembly and HPT air 

seal sleeve bolts identified that, before installation, these bolts are not 

subjected to a complete quality inspection. 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, Rolls-Royce Deutschland (RRD), 

the design approval holder, issued Alert Service Bulletin (ASB) Sp72-A1068 

providing instructions to inspect bolts installed in 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 inspection 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. All rights reserved. 2/2 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Effective Date: 05 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 15 November 2007, 

within 4 500 engine cycles accumulated since that engine 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 paragraph (2) of this AD, any 

broken bolt, brown bolt or bolt with a rough oxidized surface is identified, 

before release to service of the engine, replace the affected bolt sets in 

accordance with the accomplishment instructions of RRD ASB Sp72-

A1068. 

(4) If, during the inspection as required by paragraph (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 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 the requirements of this AD. 

Ref. Publications: Rolls-Royce Deutschland ASB Sp72-A1068 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 23 July 2012 as PAD 12-084 for consultation until 

20 August 2012. No comments were received during the consultation 

period. 

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.