Number |
2015-0036R4 |
Issued by |
Europe |
Issue date |
2021-10-08 |
Effective date |
2021-10-15 |
EASA approval number |
|
Contributor |
EASA Large Aeroplanes Department |
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.
|