EASA AD No.: 2014-0243R1

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0243R1

Date: 10 December 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

Revision: This AD revises EASA AD 2014-0243 dated 06 November 2014, which 

superseded EASA AD 2014-0089 dated 15 April 2014.

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 fitted with fuel tube Part Number (P/N) FW53576, which was 

incorporated through RR modification 73-F343 in production, or by in-service 

modification 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. Previous experience on a 

similar engine type indicated that this movement was increased by 

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 in 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.
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Consequently, EASA issued AD 2014-0089 to require repetitive on-wing and 

in-shop inspections and, depending on findings, replacement of fan case LP 

fuel tubes, clips and FOHE mounting hardware.

Since that AD was issued, reports were received of a limited number of P-clip 

tang fractures at clip point 4881 that resulted in frettage and leaks from the LP 

Fuel tube between the FOHE to LP/HP fuel pump, which occurred prior to the 

next required inspection in accordance with NMSB RB.211-73-AH522. In all 

cases, it has been reported that the tangs were found broken at the clip point. 

Prompted by these occurrences, RR published NMSB RB.211-73-AH837 to 

provide instructions for additional specific visual inspections of the upper P-clip 

attaching feature and the bracket holding this P-clip to the oil tank, at shorter

intervals than those specified in NMSB RB.211-73-AH522.

For the reasons described above, EASA issued AD 2014-0243, retaining the 

requirements of EASA AD 2014-0089, which was superseded, and adding

repetitive on-wing inspections of the uppermost clip-stack (P/N CP4881) on 

the FOHE to fuel pump LP fuel tube (P/N FW53576) and the relevant 

associated bracket (P/N FW26692) and, depending on findings, 

accomplishment of the applicable corrective action(s).

This AD revises EASA AD 2014-0243, to correct an omission in paragraph (8)

and to add credit in paragraph (7) for certain in-shop inspections.

Effective Date: Revision 1: 10 December 2014

Original issue: 20 November 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 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 29 April 2014 [the 

effective date of EASA AD 2014-0089] 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 29 April 2014 [the effective 

date of EASA AD 2014-0089]

Compliance time

3 200 FH or more Within 800 FH after 29 April 

2014 [the effective date of 

EASA AD 2014-0089]

Less than 3 200 FH Before exceeding 4 000 FH 

since new

(3) Within 800 FH after the effective date of this AD and, thereafter, at 

intervals not to exceed 800 FH, visually inspect the uppermost clip-stack 

(P/N CP4881) on the FOHE to fuel pump LP fuel tubes (P/N FW53576) 

upper section and the relevant associated bracket (P/N FW26692) in 

accordance with the instructions of RR NMSB RB.211-73-AH837.
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(4) From 29 April 2014 [the effective date of EASA AD 2014-0089], 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.

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

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

detected, within the compliance time(s) specified in RR NMSB RB.211-

73-AH522 (for on-wing inspection), or before release to service of the 

engine (for in-shop inspection), as applicable, replace any damaged fan 

case LP fuel tube(s) and relevant associated clips, and/or any damaged 

FOHE, in accordance with the instructions of RR NMSB RB.211-73-

AH522.

(6) If, during any inspection as required by paragraph (3) of this AD, any 

discrepancies (as defined in RR NMSB RB.211-73-AH837) are detected, 

accomplish the applicable corrective action(s), depending on findings, as 

specified in paragraph (6.1) or (6.2) of this AD, as applicable.

(6.1) For the clip-stack (P/N CP4881), before next flight, remove the clip,

inspect the fuel tube in accordance with the instructions of RR 

NMSB RB.211-73-AH837, and, depending on condition, replace the 

affected fan case LP fuel tube and relevant associated clips in 

accordance with the instructions of RR NMSB RB.211-73-AH837.

(6.2) For the associated bracket (P/N FW26692), within 100 FH after 

detection of the discrepancy, replace the bracket and inspect the 

fuel tube in accordance with the instructions of RR NMSB RB.211-

73-AH837, and, depending on condition, replace the affected fan 

case LP fuel tubes and relevant associated clips in accordance with 

the instructions of RR NMSB RB.211-73-AH837.

(7) An in-shop inspection accomplished in accordance with the instructions of 

RR NMSB RB.211-73-AH522 is acceptable in lieu of an on-wing 

inspection as required by paragraph (1) of this AD.

An in-shop inspection accomplished in accordance with the instructions of 

RR NMSB RB.211-73-AH522 is acceptable in lieu of a visual inspection 

as required by paragraph (3) of this AD.

(8) 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 (5) or (6) of this AD, as applicable, does not 

constitute terminating action for the repetitive inspections required by 

paragraphs (1), (3) and (4) 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, or Revision 1 

dated 14 May 2009, or Revision 2 dated 1 July 2009, or Revision 3 dated 15 

July 2009, or Revision 4 dated 26 May 2011.

Rolls-Royce NMSB RB.211-73-AH837 dated 09 September 2014.

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. The original issue of this AD was posted on 10 September 2014 as PAD 

14-140 for consultation until 08 October 2014. The Comment Response 

Document can be found at http://ad.easa.europa.eu/.
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3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Certification 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.