Safety Publications Tool

2025-0166R1 : Fuselage – Inner Cap and Frame Flange at Frame 68 Stringer 22 – Inspections

Number 2025-0166R1
Issued by Europe  Europe
Issue date 2026-03-24
Effective date 2026-03-31
EASA approval number
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 This AD revises EASA AD 2025-0166 dated 30 July 2025.
Correction Not applicable
Supersedure The original issue of this AD supersedes EASA AD 2024-0210R1 dated 22 July 2025.
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.
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, the original issue of this AD was posted on 30 July 2025 as Final AD with Request for Comments, postponing the public consultation process until 27 August 2025. 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.