EASA AD No.: 2013-0229R1

TE.CAP.00110-003 © European Aviation Safety Agency. All 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.: 2013-0229R1

Date: 21 November 2013

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an 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 EU 748/2012, P art 21.A.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 accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption]. 

### Design Approval Holder’s Name:

ROLLS-ROYCE DEUTSCHLAND Ltd & Co KG Type/Model designation(s):
BR700-725A1-12 engines

TCDS Number: EASA.E.018

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2013-0229 dated 2 3 September 2013.



### ATA 73 Engine Fuel and Control – Fuel Metering Unit – Repl acement

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

Applicability: BR700-725A1-12 engines, all serial numbers. These engines are known to be installed on, but not limited to, Gulfstream GVI (commercial designation G650) aeroplanes.

Reason: Occurrences have been reported of finding w ear on the receptors of the double ended unions in the Fuel Metering Unit (FMU) housing on BR700-725A1-12 engines. This condition, if not corrected, could lead to fue l leak resulting in engine inflight shutdown and consequent reduced control of t he aeroplane. To address this potential unsafe condition, RRD iss ued Alert NonModification Service Bulletin (NMSB) SB-BR700-73-A9 00309, providing instructions for FMU replacement in accordance with revised installation procedure. For the reasons described above, this AD requires r epetitive replacement of the FMU and prohibits installation of FMU with Part Number (P/N) G3000FMU02.
This AD is revised to extend the definition of serv iceable FMU units qualified for installation on an engine.

Effective Date: Revision 1: 21 November 2013 Original issue: 07 October 2013EASA AD No.: 2013-0229R1

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: Note: For the purpose of this AD, a serviceable FMU is a FMU with P/N G3000FMU03 having accumulated less than 650 flight hours (FH) since first installation on an aeroplane, or since last rework in accordance with RRD NMSB SB-BR700-73-A900309 at Revision 1 or later app roved revisions, as applicable. (1) Before exceeding 650 FH accumulated by the FMU (see Note above), or within 30 days after 07 October 2013 [the effective date of the original issue of this AD], whichever occurs later, replace each FMU P/N G3000FMU02 and P/N G3000FMU03 with a serviceable FM U in accordance with the instructions of RRD Alert NMSB SB-BR700-73- A900309. (2) Thereafter, at intervals not to exceed 650 FH a ccumulated by the FMU (see Note above), replace each FMU with a serviceab le FMU in accordance with the instructions of RRD Alert NMSB SB-BR700-73-A900309. (3) From 07 October 2013 [the effective date of the original issue of this AD], do not install a FMU P/N G3000FMU02 on an engine, o r an engine with FMU P/N G3000FMU02 installed on an aeroplane.

Ref. Publications: RRD Alert NMSB SB-BR700-73-A9003 09 Initial Issue dated 24 July 2013 or Revision 1 dated 8 November 2013. 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. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Commen ts, postponing the public consultation process until after publication

. 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, Dahlewitz 15827 Blankenfelde-Mahlow, Germany Telephone: +49 (0) 33 7086 1200 Fax: +49 (0) 33 708 6 1212 E-mail: RRDTechnicalHelpdesk@Rolls-Royce.com

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