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2019-0044R1 : Wings – Centre Section Frame 40 Forward Fitting Radius at Tension Bolt Junction – Inspection / Repair

Number 2019-0044R1
Issued by Europe  Europe
Issue date 2025-10-22
Effective date 2025-11-05
EASA approval number
ATA Chapter 57
Approval Holder
/ Type Designation
  • AIRBUS S.A.S.
    • A300-600
      • A300B4-601
      • A300B4-603
      • A300B4-605R
      • A300B4-620
      • A300B4-622
      • A300B4-622R
      • A300C4-605R variant F
      • A300C4-620
      • A300F4-605R
Revision This AD revises EASA AD 2019-0044 dated 07 March 2019.
Correction Not applicable
Supersedure The original issue of this AD superseded DGAC France AD 1998-040-012(B)R1 dated 24 January 2001 and AD F-1995-063-177R5 dated 12 November 2003.
Publication(s) and related information Airbus SB A300-57-6062 Revision 02 dated 29 January 1997, or Revision 03 dated 26 October 2000, or Revision 04 dated 12 November 2002, and Revision 05 dated 03 October 2018. [Deleted] The use of later approved revisions of the above-mentioned document is acceptable for compliance with the requirements of this AD.
PAD number 18-152
Remarks 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. The original issue of this AD was posted on 12 November 2018 as PAD 18-152 for consultation until 10 December 2018. 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.