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2015-0036R4 : Fuselage – Fuselage Skin Repairs – Inspection

Number 2015-0036R4
Issued by Europe  Europe
Issue date 2021-10-08
Effective date 2021-10-15
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 2015-0036R3 dated 20 July 2021
Correction Not applicable
Supersedure None
Publication(s) and related information Airbus AOT A53N007-14 original issue dated 22 July 2014. The use of later approved revisions of the above-mentioned document is acceptable for compliance with the requirements of this AD.
PAD number 14-177R1
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 19 December 2014 as PAD 14-177 for consultation until 02 January 2015 and republished as PAD 14-177R1 on 11 February 2015 for consultation until 25 February 2015. 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.