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PAD 23-058 : Fuselage – Crossbeam Splicing at Frames 16 and 20 – Inspection

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Number 23-058
Issued by Europe  Europe
Issue date 2023-05-23
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 Not applicable
Supersedure This AD supersedes EASA AD 2016-0139 dated 14 July 2016.
Publication(s) and related information Airbus SB A320-53-1286 original issue dated 29 June 2015, or Revision 01 dated 22 December 2015, or Revision 02 dated 01 October 2018, or Revision 03 dated 08 June 2022, or Revision 04 dated 22 February 2023. Airbus SB A320-53-1295 original issue dated 29 June 2015, or Revision 01 dated 27 September 2018, or Revision 02 dated 10 February 2020, or Revision 03 dated 19 May 2022. The use of later approved revisions of the above-mentioned documents is acceptable for compliance with the requirements of this AD.
Remarks 1. This Proposed AD will be closed for consultation on 20 June 2023. 2. Enquiries regarding this PAD should be referred to the EASA Safety Information Section, Certification Directorate. E-mail: ADs[at]easa.europa.eu. 3. Information about any failures, malfunctions, defects or other occurrences, which may be similar to the unsafe condition addressed by this PAD, and which may occur, or have occurred on a product, part or appliance not affected by this PAD, 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 PAD 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.

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