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2024-0210 : Fuselage – Inner Cap and Frame Flange at Frame 68 Stringer 22 – Inspections

Number 2024-0210
Issued by Europe  Europe
Issue date 2024-10-29
Effective date 2024-11-12
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 2022-0030 dated 25 February 2022.
Publication(s) and related information Airbus SB A320-53-1491 original issue dated 14 August 2020, or Revision 01 dated 2 May 2022, or Revision 02 dated 30 July 2024. The use of later approved revisions of the above-mentioned document is acceptable for compliance with the requirements of this AD.
PAD number 24-113
Remarks 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 30 September as PAD 24-113 for consultation until 14 October 2024. 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.