| Number |
2017-0158R1 |
| Issued by |
 Europe |
| Issue date |
2022-12-01 |
| Effective date |
2022-12-15 |
| EASA approval number |
|
| Contributor |
EASA Large Aeroplanes Department |
| ATA Chapter |
57 |
Approval Holder
/ Type Designation |
-
AIRBUS S.A.S.
-
A300-600
-
A300B4-605R
-
A300B4-622R
-
A300C4-605R variant F
-
A300F4-605R
-
A300F4-622R
-
A300-600ST (Beluga)
|
| Revision |
This AD revises EASA AD 2017-0158 dated 25 August 2017.
|
| Correction |
Not applicable
|
| Supersedure |
This original issue of this AD superseded EASA AD 2016-0179 dated 12 September 2016.
|
| Publication(s) and related information |
Airbus AOT A57W009-16 original issue dated 25 February 2016, or Revision 01 dated 13 July 2016.
Airbus SB A300-57-6120 original issue dated 28 April 2017, or Revision 01 dated 13 October 2022.
Airbus SB A300-57-9035 original issue dated 28 April 2017.
The use of later approved revisions of the above-mentioned documents is acceptable for compliance with the requirements of this AD. |
| PAD number |
17-101 |
| 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, EASA have decided to issue a Final AD with Request for Comments, postponing the public consultation process until after publication.
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.
|
