EASA AD No.: 2013-0229R1

TE.CAP.00110-003 © 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.: 2013-0229R1

Date: 21 November 2013

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 EU 748/2012, Part 21.A.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): 

BR700-725A1-12 engines 

TCDS Number: EASA.E.018 

Foreign AD: Not applicable 

Revision: This AD revises EASA AD 2013-0229 dated 23 September 2013. 

ATA 73 Engine Fuel and Control – Fuel Metering Unit – Replacement

Manufacturer(s): Rolls-Royce Deutschland Ltd & Co KG (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 wear 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 fuel leak resulting in engine inflight shutdown and consequent reduced control of the aeroplane. 

To address this potential unsafe condition, RRD issued Alert NonModification Service Bulletin (NMSB) SB-BR700-73-A900309, providing 

instructions for FMU replacement in accordance with revised installation 

procedure. 

For the reasons described above, this AD requires repetitive replacement of 

the FMU and prohibits installation of FMU with Part Number (P/N) 

G3000FMU02. 

This AD is revised to extend the definition of serviceable FMU units qualified 

for installation on an engine. 

Effective Date: Revision 1: 21 November 2013 

Original issue: 07 October 2013 
EASA AD No.: 2013-0229R1

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2 

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Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

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 approved 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 FMU in 

accordance with the instructions of RRD Alert NMSB SB-BR700-73-

A900309. 

(2) Thereafter, at intervals not to exceed 650 FH accumulated by the FMU 

(see Note above), replace each FMU with a serviceable 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, or an engine with 

FMU P/N G3000FMU02 installed on an aeroplane. 

Ref. Publications: RRD Alert NMSB SB-BR700-73-A900309 Initial Issue dated 24 July 2013 or 

Revision 1 dated 8 November 2013. 

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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication. 

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, Dahlewitz 

15827 Blankenfelde-Mahlow, Germany 

Telephone: +49 (0) 33 7086 1200 Fax: +49 (0) 33 7086 1212 

E-mail: RRDTechnicalHelpdesk@Rolls-Royce.com.