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2017-0132R2 : Engine – Forward Engine Mount Main Beam Snout – Replacement

Number 2017-0132R2
Issued by Europe  Europe
Issue date 2021-08-03
Effective date 2021-08-10
EASA approval number
ATA Chapter 71
Approval Holder
/ Type Designation
  • AIRBUS S.A.S.
    • A318
      • A318-111
      • A318-112
    • A319
      • A319-111
      • A319-112
      • A319-113
      • A319-114
      • A319-115
    • A320
      • A320-211
      • A320-212
      • A320-214
      • A320-215
      • A320-216
    • A321
      • A321-111
      • A321-112
      • A321-211
      • A321-212
      • A321-213
Revision This AD revises EASA AD 2017-0132R1 dated 22 November July 2017
Correction Not applicable
Supersedure None
Publication(s) and related information Airbus SB A320-71-1065 original issue dated 01 December 2016, and Revision 01 dated 28 July 2017. Airbus SB A320-71-1066 original issue dated 01 December 2016. Goodrich Aerospace SB RA32071-159 original issue dated 20 November 2016. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.
PAD number 17-067
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 06 June 2017 as PAD 17-067 for consultation until 04 July 2017. The Comment Response Document can be found at https://ad.easa.europa.eu in the compressed (zipped) file attached to the record for this AD. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification Directorate, EASA. 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.