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  Safety Publications Tool

2024-0077 : [Correction] Fuselage – Pressure Panel Longitudinal Beams – Inspection / Repair / Modification

Number 2024-0077
Issued by Europe  Europe
Issue date 2024-04-25
Effective date 2024-04-02
EASA approval number
Contributor EASA Large Aeroplanes Department
ATA Chapter 53
Approval Holder
/ Type Designation
  • AIRBUS S.A.S.
    • A318
      • A318-111
      • A318-112
      • A318-121
      • A318-122
    • A319
      • A319-111
      • A319-112
      • A319-113
      • A319-114
      • A319-115
      • A319-131
      • A319-132
      • A319-133
    • A320
      • A320-211
      • A320-212
      • A320-214
      • A320-215
      • A320-216
      • A320-231
      • A320-232
      • A320-233
    • A321
      • A321-111
      • A321-112
      • A321-131
      • A321-211
      • A321-212
      • A321-213
      • A321-231
      • A321-232
Revision Not applicable
Correction This AD is republished to correct typographical errors and the effective date in Appendix 1.
Supersedure This AD supersedes EASA AD 2016-0206 dated 13 October 2016, including its Correction dated 14 October 2016.
Publication(s) and related information Airbus SB A320-53-1029 original issue dated 05 January 2000, or Revision 01 dated 29 April 2002. Airbus SB A320-53-1030 original issue dated 05 January 2000, or Revision 01 dated 21 May 2002. Airbus SB A320-53-1240 original issue dated 19 March 2015, or Revision 01 dated 04 April 2016, or Revision 02 dated 14 March 2017, or Revision 03 dated 15 February 2021, or Revision 04 dated 05 May 2022. Airbus SB A320-53-1263 original issue dated 19 March 2015, or Revision 01 dated 29 February 2016, or Revision 02 dated 06 December 2017, or Revision 03 dated 16 December 2020, or Revision 04 dated 05 May 2022, or Revision 05 dated 04 September 2023. Airbus SB A320-53-1264 original issue dated 19 March 2015, or Revision 01 dated 04 July 2016, or Revision 02 dated 23 May 2018, or Revision 03 dated 08 September 2021. The use of later approved revisions of the above-mentioned 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. 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. All interested persons may send their comments, referencing the AD Number, to the E-mail address specified in below Remark 3, prior to 16 April 2024. Only if any comment is received during the consultation period, a Comment Response Document will be published in the EASA Safety Publications Tool, in a 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.