Safety Publications Tool
2022-0115 : Fuselage – Cargo Compartment Fitting Brackets, Tack and Rivet Holes – Inspection / Repair
EASA approval number
EASA Large Aeroplanes Department
/ Type Designation
This AD supersedes EASA AD 2018-0233R1 dated 28 November2018.
Publication(s) and related information
Airbus SB A320-53-1257 original issue dated 21 December 2012, or Rev. 01 dated 28 April 2016, or Rev. 02 dated 29 November 2016, or Rev. 03 dated 23 September 2019. Airbus SB A320-53-1261 original issue dated 21 December 2012, or Rev. 01 dated 30 June 2015, or Rev. 02 dated 01 March 2016, or Rev. 03 dated 08 August 2016, or Rev. 04 dated 03 May 2017, or Rev. 05 dated 15 December 2021. Airbus SB A320-53-1360 original issue dated 01 December 2016, or Rev. 01 dated 01 March 2018. Airbus SB A320-53-1364 original issue dated 04 May 2018. Airbus SB A320-53-1365 original issue dated 17 April 2018. The use of later approved revisions of the above-mentioned documents is acceptable for compliance with the requirements of this AD.
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 19 April 2022 as PAD 22-046 for consultation until 17 May 2022. 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.
EASA_PAD_22_046.zip (628 kb)
EASA_AD_2022_0115.pdf (236 kb)
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