EASA AD No: 2013-0240

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/5

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

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0240

[Correction: 04 October 2013]

Date: 30 September 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 plc

Type/Model designation(s) :

RB211 Trent 900 engines

TCDS Number : EASA.E.012

Foreign AD : Not applicable

Supersedure: None

ATA 72 Engine – Low Pressure Turbine Exhaust Case and Support 

Assembly (Tail Bearing Housing) – Inspection / Replacement

Manufacturer(s): Rolls-Royce plc

Applicability: RB211 Trent 970-84, 970B-84, 972-84, 972B-84, 977-84, 977B-84 and 980-84 

engines, all serial numbers.

These engines are known to be installed on, but not limited to, Airbus A380 

aeroplanes.

Reason: Rolls-Royce performed a re-analysis of the structural features of the Trent 900 

low pressure turbine exhaust case and support assembly (also known as Tail 

Bearing Housing, or TBH). The result of this re-analysis indicates that the TBH 

may not retain full limit load capability in all fail-safe conditions. In addition, 

during previous inspections of Trent 900 TBH mounts and vanes, cracks have 

been found in the outer annulus leading edge (LE) fillet of some vanes.

These conditions, if not detected and corrected, could lead to disconnection of 

the TBH structural ring from the mounts, possibly resulting in damage to, or 

reduced control of, the aeroplane.

To address this potential unsafe condition, Rolls-Royce have published Alert 

Non-Modification Service Bulletins (NMSB) RB.211-72-AG971 and RB.211-72-

AH154, now both at Revision 1, providing inspection instructions and criteria 

for replacement of parts.

For the reasons described above, this AD requires on-wing and in-shop 

inspections of the TBH structural features to detect cracks or damage and, 

depending on findings, the accomplishment of applicable corrective action(s).

This AD is re-published to correct a typographical error in paragraph (4).

Effective Date: 14 October 2013
EASA AD No: 2013-0240

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/5

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:

(1) Within the compliance times specified in Table 1 of Appendix 1 of this 

AD, as applicable, accomplish on-wing inspections of the TBH features

in accordance with the instructions of the specified sections of the 

Rolls-Royce Alert NMSB, as referenced in Table 1.

(2) Within the compliance times specified in Table 2 of Appendix 1 of this 

AD, as applicable, accomplish in-shop inspections of the TBH features

in accordance with the instructions of the specified sections of the 

Rolls-Royce Alert NMSB, as referenced in Table 2.

(3) If, during any on-wing inspection as required by paragraph (1) of this 

AD, any crack is found on the TBH Mount Lug Run-outs, remove the 

engine in accordance with the criteria and within the compliance times 

defined in paragraph 3.A.(2) of Royce Alert NMSB RB.211-72-AG971.

(4) If, during any in-shop inspection as required by paragraph (2) of this 

AD, any crack is found on the TBH Mount Lug Run-outs, before 

release to service, repair the engine in accordance with the instructions 

of sections 3.B.(1) or 3.C.(1), as applicable, of Rolls-Royce Alert NMSB 

RB.211-72-AG971.

(5) If, during any on-wing inspection as required by paragraph (1) of this 

AD, any crack or damage is found on the TBH Mount Lug Forging LE 

Areas or Fail Safe Catcher, re-inspect or remove the engine in 

accordance with the criteria and within the compliance times defined in 

sections 3.A.(3) or 3.A.(4), as applicable, of Rolls-Royce Alert NMSB 

RB.211-72-AH154.

(6) If, during any in-shop inspection as required by paragraph (2) of this 

AD, any crack or damage is found on the TBH Mount Lug Forging LE 

Areas or Fail Safe Catcher, before release to service, repair the engine 

in accordance with the instructions of sections 3.B.(2) or 3.B.(3), as 

applicable, of Rolls-Royce Alert NMSB RB.211-72-AH154.

(7) Inspections and corrective actions, accomplished before the effective 

date of this AD, in accordance with the instructions of applicable 

sections of Rolls-Royce Alert NMSB RB.211-72-AG971 Initial Issue or 

Rolls-Royce Alert NMSB RB.211-72-AH154 Initial Issue are acceptable 

for compliance with the requirements of paragraph (1) or (2) of this AD, 

as applicable.

(8) If, on or before the effective date of this AD, the last in-shop inspection 

of the Mount Lug Run-Outs was accomplished in accordance with the 

instructions of section 3.C of Rolls-Royce Alert NMSB RB.211-72-

AG971 Initial Issue, then the compliance time interval for the next inshop inspection of the Fail Safe Catcher, as required by paragraph (2) 

of this AD, may be counted from that previous inspection.

(9) Inspections and corrective actions, accomplished before the effective 

date of this AD, in accordance with the instructions of Rolls-Royce 

Technical Variance (TV) TV124801 or TV124851 (at any issue) are 

acceptable in lieu of actions in accordance with the instructions of 

section 3.A or 3.B, as applicable, of Rolls-Royce Alert NMSB RB.211-

72-AG971.

(10) Inspections and corrective actions, accomplished before the effective 

date of this AD, in accordance with the instructions of Rolls-Royce 

TV132043 or TV132217 (at any issue) are acceptable in lieu of actions 

in accordance with the instructions of section 3.A or 3.B, as applicable,

of Rolls-Royce Alert NMSB RB.211-72-AH154.

(11) Before exceeding 17 200 engine flight cycles (FC) by a TBH since first 

installation on an engine, that TBH must be removed from service. This 

life limit will be introduced in the applicable Airworthiness Limitation 

Section (ALS) of the Engine Manual.
EASA AD No: 2013-0240

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/5

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

(12) Corrective actions, as required by paragraph (3), (4), (5) or (6) of this 

AD, as applicable, do not constitute terminating action for the repetitive 

inspections required by paragraph (1) and (2) of this AD.

Ref. Publications: Rolls-Royce Alert NMSB RB.211-72-AG971 original issue dated 20 September 

2012, or Revision 1, dated 27 September 2013.

Rolls-Royce Alert NMSB RB.211-72-AH154 original issue dated 29 May 2013, 

or Revision 1, dated 18 June 2013.

Rolls-Royce TV124801 issue 2, dated 04 July 2012.

Rolls-Royce TV124851 issue 2, dated 04 July 2012.

Rolls-Royce TV132043 issue 1, dated 25 March 2013.

Rolls-Royce TV132217 issue 2, dated 15 April 2013.

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 04 July 2013 as PAD 13-096 for consultation until 

25 July 2013. The Comment Response Document can be found at 

http://ad.easa.europa.eu.

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

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

correspondence as being related to Airworthiness Directives.
EASA AD No: 2013-0240

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 4/5

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

Appendix 1

Note 1: FC = Flight Cycles.

Note 2: Since new = FC accumulated by the TBH since first installation on an engine.

Note 3: Rolls-Royce NMSB RB.211-72-AG971 Rev 1 Section 3.B provides instructions for in-shop 

inspections of Mount Lug Run-out and Fail Safe Catcher, as Section 3.C provides instructions for in-shop 

inspection of the full TBH.

Table 1 – TBH On-wing Inspections

TBH Feature

Applicable 

Rolls-Royce 

NMSB and 

Section

Acceptable 

Alternative

Rolls-Royce 

NMSB and 

Section

Compliance Time

Initial 

Inspection

Interval

(not to exceed)

Mount Lug Run-outs

RB.211-72-

AG971 Rev 1 

Section 3.A

In-shop: RB.211-

72-AG971 Rev 1 

Section 3.B or 3.C

(see Note 3)

Before 

exceeding

2 200 FC 

since new (see 

Note 2)

2 200 FC

Mount Lug Forging LE Areas 

and Fail Safe Catcher

– When TBH has accumulated 

no more than 900 FC since new 

(see Note 2) on the effective 

date of this AD

RB.211-72-

AH154 Rev 1 

Section 3.A

In-shop:

RB.211-72-

AH154 Rev 1 

Section 3.B, or

RB.211-72-

AG971 Rev 1 

Section 3.B or 

3.C, as applicable

(see Note 3)

Before 

exceeding

1 000 FC 

since new

(see Note 2)

1 000 FC

Mount Lug Forging LE Areas

and Fail Safe Catcher

– When TBH has accumulated 

more than 900 FC since new 

(see Note 2) on the effective 

date of this AD

RB.211-72-

AH154 Rev 1 

Section 3.A

In-shop:

RB.211-72-

AH154 Rev 1 

Section 3.B, or

RB.211-72-

AG971 Rev 1 

Section 3.B or 

3.C, as applicable

(see Note 3)

Within 100 FC 

after the 

effective date 

of this AD
EASA AD No: 2013-0240

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 5/5

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

Appendix 1 (continued)

Table 2 – TBH In-shop Inspections

TBH Feature

Applicable 

Rolls-Royce 

NMSB and 

Section

Acceptable 

Alternative 

Rolls-Royce 

NMSB and 

Section

Compliance Time

Initial 

Inspection

Interval

(not to 

exceed)

Mount Lug Run-outs

RB.211-72-

AG971 Rev 1 

Section 3.B

On-wing: RB.211-

72-AG971 Rev 1 

Section 3.A

In-shop:

RB.211-72-

AG971 Rev 1 

Section 3.C (see 

Note 3)

Before 

exceeding

2 200 FC since 

new

(see Note 2)

2 200 FC

Top Core Vanes

RB.211-72-

AG971 Rev 1 

Section 3.C

n/a

Before 

exceeding

3 800 FC since 

new

(see Note 2)

3 800 FC

Mount Lug Forging LE Areas 

and Fail Safe Catcher

– When TBH has accumulated 

no more than 900 FC since new 

(see Note 2) on the effective

date of this ADC

RB.211-72-

AH154 Rev 1 

Section 3.B

On-wing:

RB.211-72-

AH154 Rev 1 

Section 3.A

In-shop:

RB.211-72-

AG971 Rev 1 

Section 3.B or 

3.C, as applicable

(see Note 3)

Before 

exceeding

1 000 FC since 

new

(see Note 2)

1 000 FC

Mount Lug Forging LE Areas 

and Fail Safe Catcher

– When TBH has accumulated 

more than 900 FC since new 

(see Note 2) on the effective 

date of this AD

RB.211-72-

AH154 Rev 1 

Section 3.B

On-wing:

RB.211-72-

AH154 Rev 1 

Section 3.A

In-shop:

RB.211-72-

AG971 Rev 1 

Section 3.B or 

3.C, as applicable

(see Note 3)

Within 100 FC 

after the 

effective date of 

this AD