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  Safety Publications Tool

2016-0193R2 : Engine – Low Pressure Turbine Exhaust Case and Support Assembly (Tail Bearing Housing) – Inspection / Replacement

Number 2016-0193R2
Issued by Europe  Europe
Issue date 2026-08-13
Effective date 2026-08-27
EASA approval number
ATA Chapter 72
Approval Holder
/ Type Designation
  • ROLLS-ROYCE DEUTSCHLAND Ltd & Co KG
    • RB211 TRENT 900
      • 970-84
      • 972-84
      • 972E-84
Revision This AD revises EASA AD 2016-0193R1 dated 28 February 2018.
Correction Not applicable
Supersedure The original issue of this AD superseded EASA AD 2013-0240 issued 30 September 2013, including its Correction dated 04 October 2013.
Publication(s) and related information 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 the above-mentioned documents is acceptable for compliance with the requirements of this AD.
PAD number 16-088R1
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 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 in the EASA Safety Publications Tool, in the compressed (zipped) file attached to the record for this AD. 3. Enquiries regarding this AD should be referred to the EASA Safety Information Section, Certification Directorate. E-mail: ADs[at]easa.europa.eu. 4. Information about any failures, malfunctions, defects or other occurrences, which may be similar to the unsafe condition addressed by this AD, and which may occur, or have occurred on a product, part or appliance not affected by this AD, can be reported to the EU aviation safety reporting system. This may include reporting on the same or similar components, other than those covered by the design to which this AD applies, if the same unsafe condition can exist or may develop on an aircraft with those components installed. Such components may be installed under an FAA Parts Manufacturer Approval (PMA), Supplemental Type Certificate (STC) or other modification.