EASA AD No.: 2014-0089

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3

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

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0089

Date: 15 April 2014

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 Change Approval Holder’s Name:

ROLLS-ROYCE plc

Type/Model designation(s):

RB211 Trent 700 engines

TCDS Number: EASA.E.042

Foreign AD: Not applicable

Supersedure: None

ATA 73 Engine Fuel and Control – Low Pressure Fuel Tubes and Clips, 

Fuel Oil Heat Exchanger Mounts – Inspection / Replacement

Manufacturer(s): Rolls-Royce plc (RR)

Applicability: RB211 Trent 768-60, 772-60, 772B-60 and 772C-60 engines, all serial 

numbers, if incorporating RR modification 73-F343 in production, or modified in 

service in accordance with RR Service Bulletin (SB) RB.211-73-F343.

These engines are known to be installed on, but not limited to, Airbus A330 

aeroplanes.

Reason: Fuel leaks from the engine have occurred in-service due to damage to sections 

of the fan case Low Pressure (LP) fuel tube which runs between the Fuel Oil 

Heat Exchanger (FOHE) and the High Pressure Fuel Pump. Frettage damage 

between the securing clips and the tube outer surface has been caused by 

excessive movement within the system that resulted from deterioration of the 

FOHE mounting hardware. The thinning of the tube wall causes the tube to 

fracture and fuel loss to occur.

Fuel leak detection and the associated flight crew procedures can be complex, 

leading to some flight crews failing to detect and/or address such situations.

This condition, if not detected and corrected, could lead to a critical fuel 

imbalance or in-flight fuel starvation, possibly resulting engine in-flight shutdown and, consequently, reduced control of the aeroplane.

To address this potential unsafe condition, RR issued Non-Modification Service 

Bulletin (NMSB) RB.211-73-AH522 to provide instructions to detect and replace 

deteriorated hardware.

For the reasons described above, this AD requires repetitive on-wing and inshop inspections and, depending on findings, replacement of fan case LP fuel 

tubes, clips and FOHE mounting hardware.
EASA AD No.: 2014-0089

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3

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

Effective Date: 29 April 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Note: Where in this AD, reference is made to an RR SB or NMSB with an ‘A’ 

(Alert) in the number, it should be recognised that an earlier or later revision 

may not have that ‘A’. This kind of change does not effectively alter the 

publication references for the purpose of this AD.

(1) Within the compliance time specified in Table 1 of this AD and, thereafter, 

at intervals not to exceed 4 000 flight hours (FH), accomplish an on-wing 

inspection of fan case LP fuel tubes Part Number (P/N) FW53576 and the 

relevant associated clips, and FOHE mounts and associated hardware in 

accordance with the instructions of RR NMSB RB.211-73-AH522.

(2) Inspections on an engine, accomplished before the effective date of this 

AD in accordance with instructions of RR NMSB RB.211-73-G848 (at any 

Revision), are acceptable in lieu of the initial inspections as required by 

paragraph (1) of this AD for that engine.

Table 1 

FH accumulated by the engine 

since new, on the effective 

date of this AD

Compliance time

3 200 FH or more Within 800 FH after the effective date 

of this AD

Less than 3 200 FH Before exceeding 4 000 FH since 

new

(3) From the effective date of this AD, during each engine shop visit, inspect 

the fan case LP fuel tubes P/N FW26589, P/N FW36335, P/N FW26587,

P/N FW53576 and P/N FW53577 and the relevant associated clips, and 

the FOHE mounts and associated hardware, in accordance with the 

instructions of RR NMSB RB.211-73-AH522.

(4) If, during any inspection as required by paragraph (1) or (3) of this AD, any 

discrepancies (as defined in RR NMSB RB.211-73-AH522) are detected, 

before next flight, or before release to service of the engines, as 

applicable, replace the affected fan case LP fuel tubes and relevant 

associated clips, and FOHE mounts and associated hardware, in 

accordance with the instructions of RR NMSB RB.211-73-AH522.

(5) An in-shop inspection accomplished in accordance with paragraph (3) of 

this AD is acceptable in lieu of an on-wing inspection as required by 

paragraph (1) of this AD.

(6) Replacement of fan case LP fuel tubes and the relevant associated clips or 

FOHE mounts and associated hardware with serviceable parts, as required 

by paragraph (4) of this AD, does not constitute terminating action for the 

repetitive inspections required by paragraphs (1) and (3) of this AD.

Ref. Publications: Rolls-Royce NMSB RB.211-73-AH522 dated 20 September 2013, or

Revision 1 dated 18 March 2014.

Rolls-Royce SB RB.211-73-F343 dated 08 November 2006.

The use of later approved revisions of these documents 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 31 January 2014 as PAD 14-028 for consultation 
EASA AD No.: 2014-0089

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3

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

until 28 February 2014. 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 your designated Rolls-Royce representative or 

download the publication from your Aeromanager account at 

www.aeromanager.com.

If you do not have a designated representative or Aeromanager account, 

please contact Corporate Communications at Rolls-Royce plc.,

P.O. Box 31, Derby, DE24 8BJ, United Kingdom,

telephone: +44 (0) 1332 242424, or send an e-mail through 

http://www.rolls-royce.com/contact/civil_team.jsp identifying the 

correspondence as being related to airworthiness directives.