EASA AD No.: 2016-0193

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Airworthiness Directive

AD No.: 2016-0193

Issued: 30 September 2016

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation 

(EC) 216/2008 on behalf of the European Union, 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 Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 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 [Regulation (EU) 1321/2014 Annex I, 

Part M.A.303] or agreed with the Authority of the State of Registry [Regulation (EC) 216/2008, Article 14(4) exemption].

Design Approval Holder’s Name:

ROLLS-ROYCE plc

Type/Model designation(s):

RB211 Trent 900 Engines

Effective Date: 14 October 2016

TCDS Number(s): EASA.E.012

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2013-0240 issued 30 September 2013, including its 

Correction dated 04 October 2013.

ATA 72 – Engine – Low Pressure Turbine Exhaust Case and Support Assembly (Tail 

Bearing Housing) – Inspection / Replacement

Manufacturer(s):

Rolls-Royce plc (RR)

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:

RR 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 reanalysis indicated 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 were 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, RR published Alert Non-Modification Service Bulletin 

(NMSB) RB.211-72-AG971 and NMSB RB.211-72-AH154, providing inspection instructions and 

criteria for replacement of parts.
EASA AD No.: 2016-0193

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Consequently, EASA issued AD 2013-0240, to require 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).

Since that AD was issued, further inspection results were analysed, and concluded that on-wing 

inspections of the Fail Safe Catcher are no longer necessary, but that in-shop inspections of the 

Central Male Catcher Run-out should be required. In addition, a modification (mod) of the TBH was 

developed by RR, available for in-service engines through Service Bulletin (SB) RB.211-72-J024, 

introducing a cutback of the leading edge profile through rework of existing parts, which reduces

the stress and minimises the risk of cracking. An inspection regime for post-mod 72-J024 engines

was therefore developed and RR published Alert NMSB RB.211-72-AJ101 accordingly. In addition, 

further analysis has shown that a TBH life limit is no longer necessary. In addition, RR developed a 

modification (mod 72-J055), made available for in-service engines through SB RB.211-72-J055, 

which introduces a TBH with increased strength capability, deleting the need for inspections.

For the reasons described above, this AD partially retains the requirements of EASA AD 2013-0240, 

which is superseded, deleting the TBH life limits previously imposed by that AD, changing certain 

inspection requirements, introducing repetitive inspections for post-SB 72-J024 engines, and 

specifying the (optional) terminating action.

Required Action(s) and Compliance Time(s):

Required as indicated, unless accomplished previously:

Note 1: Where, in this AD, reference is made to a 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.

Note 2: The TBH affected by this AD are identified by Part Number (P/N):

- pre-mod 72-J024: P/N FW27718, P/N FW35923 and P/N FW51434

- post-mod 72-J024: P/N KH45090, P/N KH46677 and P/N KH46678.

On-wing Inspections:

(1) Within the compliance times specified in Appendix 1 of this AD, as applicable to the TBH P/N, 

accomplish on-wing inspections of the TBH features in accordance with the instructions of the 

specified sections of the applicable RR Alert NMSB, as referenced in Appendix 1 of this AD.

In-shop Inspections:

(2) Within the compliance times specified in Appendix 2 of this AD, as applicable to the TBH P/N, 

accomplish in-shop inspections of the TBH features in accordance with the instructions of the 

specified sections of the applicable RR Alert NMSB, as referenced in Appendix 2 of this AD.

Corrective Action(s):

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

is found on the TBH Mount Lug Run-outs or on the Central Male Catcher Run-outs, in 

accordance with the criteria and within the compliance times defined in paragraph 3.A.(1) or 

3.A.(2), as applicable, of RR Alert NMSB RB.211-72-AG971, remove the engine from service, 
EASA AD No.: 2016-0193

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contact RR for approved corrective action instructions and, before release to service of that 

engine, accomplish those actions accordingly.

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

is found on the TBH Mount Lug Run-outs or on the Central Male Catcher Run-outs, before 

release to service of the engine, replace the TBH with a serviceable TBH.

(5) If, during any in-shop inspection of the TBH as required by paragraph (2) of this AD, any crack 

is found on the Top Core Vanes, before release to service, repair the engine in accordance 

with the instructions of section 3.C.(1) of RR Alert NMSB RB.211-72-AG971.

(6) If, during any on-wing inspection of a pre-mod 72-J024 TBH (see Note 2 of this AD) as required 

by paragraph (1) of this AD, any crack or damage is found on the TBH Mount Lug Forging LE 

Areas, in accordance with the criteria and within the compliance times defined in section 

3.A.(3) of RR Alert NMSB RB.211-72-AH154, re-inspect the engine, or remove the engine from 

service, contact RR for approved corrective action instructions and, before release to service 

of that engine, accomplish those actions accordingly.

(7) If, during any in-shop inspection of a pre-mod 72-J024 TBH (see Note 2 of this AD) as required 

by paragraph (2) of this AD, any crack or damage is found on the TBH Mount Lug Forging LE 

Areas, before release to service, repair the engine in accordance with the instructions of 

section 3.B.(2) of RR Alert NMSB RB.211-72-AH154, or of section 3.C.(1) of RR Alert NMSB 

RB.211-72-AG971, as applicable.

(8) If, during any on-wing inspection of a post-mod 72-J024 TBH (see Note 2 of this AD) as 

required by paragraph (1) of this AD, any crack is found on the TBH Mount Lug Forging LE or 

Cutback Areas, as applicable, in accordance with the criteria and within the compliance times 

defined in paragraph 3.A.(3) of RR Alert NMSB RB.211-72-AJ101, re-inspect the engine, or 

remove the engine from service, contact RR for approved corrective action instructions and, 

before release to service of that engine, accomplish those actions accordingly.

(9) If, during any in-shop inspection of a post-mod 72-J024 TBH (see Note 2 of this AD) as 

required by paragraph (2) of this AD, any crack is found on the TBH Mount Lug Forging LE or 

Cutback Areas, as applicable, before release to service, repair the engine in accordance with 

the instructions of section 3.B.(2) of RR Alert NMSB RB.211-72-AJ101, or of section 3.C.(1) of 

RR Alert NMSB RB.211-72-AG971, as applicable.

Credit:

(10) Inspections and corrective actions, accomplished on an engine before the effective date of 

this AD, in accordance with the instructions of applicable sections of earlier issues of RR Alert 

NMSB RB.211-72-AG971, or earlier issues of RR Alert NMSB RB.211-72-AH154, as applicable,

are acceptable to comply with the initial requirements of paragraphs (1) and (2) of this AD, as 

applicable to that engine.
EASA AD No.: 2016-0193

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Terminating Action:

(11) Accomplishment of corrective actions on an engine, as required by paragraph (3), (4), (5), (6),

(7), (8) or (9) of this AD, as applicable, does not constitute terminating action for the repetitive 

inspections required by paragraphs (1) and (2) of this AD for that engine.

(12) Modification of an engine in accordance with the instructions of RR SB RB.211-72-J055 

constitutes terminating action for the repetitive inspections required by paragraph (1) and (2) 

of this AD for that engine, provided that, following modification, no affected TBH (see Note 2 

of this AD) is installed on that engine.

(13) No actions are required by this AD for an engine that embodies RR mod 72-J055 in production, 

provided that, after entry into service, no affected TBH (see Note 2 of this AD) is installed on 

that engine.

Ref. Publications:

Rolls-Royce Alert NMSB RB.211-72-AG971 original issue dated 20 September 2012, or Revision 1 

dated 27 September 2013, or Revision 2 dated 05 May 2016.

Rolls-Royce Alert NMSB RB.211-72-AH154 original issue dated 29 May 2013, or Revision 1 dated 

18 June 2013, or Revision 2 dated 19 September 2014, or Revision 3 dated 23 September 2014, or 

Revision 4 dated 07 July 2015, or Revision 5 dated dated 05 May 2016.

Rolls-Royce Alert NMSB RB.211-72-AJ101 original issue dated 05 May 2016.

Rolls-Royce SB RB.211-72-J024 original issue dated 01 March 2016.

Rolls-Royce SB RB.211-72-J055 original issue dated 22 March 2016.

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 13 June 2016 as PAD 16-088 for consultation until 27 June 2016, and 

republished on 17 August 2016 as PAD 16-088R1 for additional consultation until 31 August 

2016. The Comment Response Document can be found at http://ad.easa.europa.eu.

3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,

Certification Directorate. 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 

Rolls Royce Care account at https://customers.rolls-royce.com.
EASA AD No.: 2016-0193

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If you do not have a designated representative or Rolls Royce Care 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 email through http://www.rolls-royce.com/contact/civil_team.jsp identifying the 

correspondence as being related to Airworthiness Directives.
EASA AD No.: 2016-0193

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Notes for the purpose of Appendix 1 and Appendix 2 of this AD:

Note A1: Since new = FC accumulated by the TBH since first installation on an engine.

Note A2: Rolls-Royce NMSB RB.211-72-AG971 Rev 2 Section 3.B provides instructions for in-shop inspections of Mount Lug Run-out, as Section 3.C 

provides instructions for in-shop inspection of the full TBH.

Appendix 1 – TBH On-wing Inspections

Affected TBH P/N (see Note 2 of this AD)

– Feature

Applicable NMSB and 

Section

Alternative NMSB and 

Section (see Note A2)

Compliance Time

Initial Inspection Interval

(not to exceed)

All – Mount Lug Run-outs

RB.211-72-AG971 

Rev 2, Section 3.A

In-shop: RB.211-72-AG971 

Rev 2, Section 3.B or 3.C

Before exceeding 2 200 

flight cycles (FC) since new 

(see Note A1)

2 200 FC

Pre-mod 72-J024 TBH – Mount Lug Forging LE 

Areas - For a TBH that has not exceeded 900 FC 

since new (see Note 2) on 14 October 2013

[the effective date of EASA AD 2013-0240]

RB.211-72-AH154 

Rev 5, Section 3.A

In-shop: RB.211-72-AH154 

Rev 5 Section 3.B, or

RB.211-72-AG971 Rev 2 

Section 3.C

Before exceeding 1 000 FC 

since new (see Note A1)

1 000 FC

Pre-mod 72-J024 TBH – Mount Lug Forging LE 

Areas - For a TBH that has exceeded 900 FC 

since new (see Note 2) on 14 October 2013 

[the effective date of EASA AD 2013-0240]

RB.211-72-AH154 

Rev 5, Section 3.A

In-shop: RB.211-72-AH154 

Rev 5, Section 3.B, or

RB.211-72-AG971 Rev 2,

Section 3.C

Within 100 FC after 

14 October 2013 [the 

effective date of EASA AD 

2013-0240]

Post-mod 72-J024 TBH – Mount Lug Forging LE 

and Cutback Areas

RB.211-72-AJ101,

Section 3.A

In-shop: RB.211-72-AG971 

Rev 2, Section 3.C, or

RB.211-72-AJ101, Section 3.B

Before exceeding 1 000 FC 

since mod 72-J024 

embodiment
EASA AD No.: 2016-0193

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Appendix 2 – TBH In-shop Inspections

Affected TBH P/N (see Note 2 of this AD)

– Feature

Applicable NMSB and 

Section

Alternative NMSB and 

Section (see Note A2)

Compliance Time

Initial Inspection Interval

(not to exceed)

All – Mount Lug Run-outs

RB.211-72-AG971 

Rev 2, Section 3.B

On-wing: RB.211-72-AG971 

Rev 2, Section 3.A, or

In-shop: RB.211-72-AG971 

Rev 2 Section 3.C

Before exceeding 2 200 FC 

since new (see Note A1)

2 200 FC

All – Top Core Vanes and Central Male Catcher 

Run-outs

RB.211-72-AG971 

Rev 2, Section 3.C None Before exceeding 3 800 FC since new (see Note A1)

3 800 FC

Pre-mod 72-J024 TBH – Mount Lug Forging LE 

Areas - For a TBH which has not exceeded 900 

FC since new (see Note 2) on 14 October 2013

[the effective date EASA AD 2013-0240]

RB.211-72-AH154 

Rev 5, Section 3.B

On-wing: RB.211-72-AH154 

Rev 5, Section 3.A, or

In-shop: RB.211-72-AG971 

Rev 2, Section 3.C

Before exceeding 1 000 FC 

since new (see Note A1)

1 000 FC

Pre-mod 72-J024 TBH – Mount Lug Forging LE 

Areas - For a TBH which has exceeded 900 FC 

since new (see Note 2) on 14 October 2013

[the effective date of EASA AD 2013-0240]

RB.211-72-AH154 

Rev 5, Section 3.B

On-wing: RB.211-72-AH154 

Rev 5, Section 3.A, or

In-shop: RB.211-72-AG971 

Rev 2, Section 3.C

Within 100 FC after the 

effective date of this AD

Post-mod 72-J024 TBH – Mount Lug Forging LE 

and Cutback Areas

RB.211-72-AJ101, 

Section 3.B

On-wing: RB.211-72-AJ101, 

Section 3.A, or

In-shop: RB.211-72-AG971 

Rev 2 Section 3.C

Before exceeding 1 000 FC 

since mod 72-J024 

embodiment