EASA AD No.: 2014-0192

TE.CAP.00110-004 © 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.: 2014-0192

Date: 01 September 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 Approval Holder’s Name:

ROLLS-ROYCE plc

Type/Model designation(s):

Trent 1000 engines

TCDS Number: EASA.E.036

Foreign AD: Not applicable

Supersedure: None

ATA 73 Engine Fuel and Control – Engine Electronic Controller –

Modification / Replacement

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

Applicability: Trent 1000-A, Trent 1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G and

Trent 1000-H engines, all serial numbers.

These engines are known to be installed on, but not limited to, Boeing 787

series aeroplanes.

Reason: An investigation carried out by RR has identified the risk of Intermediate 

Pressure (IP) shaft failure that may not be detected and accommodated by the 

engine control system. An IP shaft failure that is not detected may result in IP 

turbine overspeed.

This condition, if not corrected, could lead to IP turbine burst and consequent

release of high energy debris, possibly resulting in damage to, and reduced 

control of, the aeroplane.

To address this potentially unsafe condition, RR has developed improved 

Engine Electronic Controller (EEC) software that ensures detection of IP shaft 

failure and prevents IP turbine overspeed.

For the reasons described above, this AD requires the introduction of the 

improved EEC software, either by modification (software upload) of the current 

EEC, or replacement with an EEC that contains the improved software.

Effective Date: 03 September 2014
EASA AD No.: 2014-0192

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2

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

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Note: Where, in this AD, reference is made to an RR Mod, 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 30 days or 180 flight cycles, whichever occurs first after the effective 

date of this AD, modify the engine by installing software standard MB6.15

in the EEC, or by replacing the EEC with a unit that contains software 

standard MB6.15, in accordance with the instructions of RR Service 

Bulletin (SB) TRENT 1000 73-AH914.

(2) After expiry of the compliance time as required by paragraph (1) of this AD, 

it is allowed to install an unmodified engine on an aeroplane, or an 

unmodified EEC on an engine, provided that, before first operation of that 

engine, the engine is modified by installing software standard MB6.15 in 

the EEC, or by replacing the EEC with a unit that contains software 

standard MB6.15, in accordance with the instructions of RR SB TRENT 

1000 73-AH914, or a later standard approved by EASA, or approved under 

RR DOA, in accordance with approved instructions.

Ref. Publications: RR SB TRENT 1000 73-AH914 original issue, dated 23 July 2014.

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, 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

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

correspondence as being related to Airworthiness Directives.