AIRBUSA318A319A320A321

ID: 2017-0215
Issue date: 2017-10-24
Effective date: 2017-11-07  
Source: EASA
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Time Limits / Maintenance Checks – Safe Life Airworthiness Limitations Items – ALS Part 1 – Amendment

EASA AD No.: 2017-0215


Airworthiness Directive
AD No.: 2017-0215
Issued: 24 October 2017
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EC) 216/2008 on behalf of the European Union, its Member States and of the European third
countries that participate in the activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 Annex I, Part M.A.301, the
continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which
an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [Regulation (EU) 1321/2014 Annex I,
Part M.A.303] or agreed with the Authority of the State of Registry [Regulation (EC) 216/2008, Article 14(4) exemption].


Design Approval Holder’s Name: Type/Model designation(s):
AIRBUS A318, A319, A320 and A321 aeroplanes

Effective Date:
07 November 2017
TCDS Number(s): EASA.A.064
Foreign AD: Not applicable
Supersedure: This AD supersedes EASA AD 2012-0008 dated 16 January 2012 and EASA AD
2014-0141 dated 04 June 2014.


ATA 05 – Time Limits / Maintenance Checks – Safe Life Airworthiness Limitations
Items – ALS Part 1 – Amendment


Manufacturer(s):

Airbus (formerly Airbus Industrie)

Applicability:

Airbus A318-111, A318-112, A318-121, A318-122, A319-111, A319-112, A319-113, A319-114,
A319-115, A319-131, A319-132, A319-133, A320-211, A320-212, A320-214, A320-215, A320-216,
A320-231, A320-232, A320-233, A320-251N, A320-271N, A321-111, A321-112, A321-131, A321-211,
A321-212, A321-213, A321-231, A321-232, A321-251N, A321-253N and A321-271N aeroplanes, all
manufacturer serial numbers.

Reason:

The airworthiness limitations for Airbus A320 family aeroplanes, which are approved by EASA, are
currently defined and published in the A318, A319, A320 and A321 Airworthiness Limitations
Section (ALS) document(s). The Safe Life Airworthiness Limitation Items are specified in ALS Part 1.
These instructions have been identified as mandatory for continued airworthiness.

Failure to accomplish these instructions could result in an unsafe condition.




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EASA AD No.: 2017-0215

Previously, EASA issued AD 2012-0008 to require the implementation of the airworthiness
limitations as specified in Airbus A318/A319/A320/A321 ALS Part 1 Revision 02, and EASA AD
2014-0141 to require the implementation of specific life limits for the main landing gear (MLG)
upper cardan pin Part Number (P/N) 201163620.

Since those ADs were issued, studies were conducted in the frame of in-service events or during life
extension campaigns, the results of which prompted revision of the life limits of several
components installed on A320 family aeroplanes. Consequently, Airbus successively issued Revision
03, Revision 04 and Revision 05 of the A318/A319/A320/A321 ALS Part 1. ALS Part 1 Revision 05
also includes the life limits required by EASA AD 2014-0141. A318/A319/A320/A321 ALS Part 1
Revision 05 issue 02 was issued to provide clarifications.

For the reason described above, this AD retains the requirements of EASA AD 2012-0008 and EASA
AD 2014-0141, which are superseded, and requires accomplishment of the actions specified in
A318/A319/A320/A321 ALS Part 1 Revision 05 (hereafter referred to as ‘the ALS’ in this AD).

Required Action(s) and Compliance Time(s):

Required as indicated, unless accomplished previously:

Replacement of Life Limited Parts:
(1) From the effective date of this AD, replace each component before exceeding the applicable life
limit, as specified in the ALS, as applicable to aeroplane model and depending on aeroplane
configuration.

Aircraft Maintenance Programme (AMP) Revision:
(2) Within 12 months after the effective date of this AD, revise the approved AMP, on the basis of
which the operator or the owner ensures the continuing airworthiness of each operated
aeroplane, by incorporating the limitations described in the ALS, as applicable to aeroplane
model and depending on aeroplane configuration.

Credit:
(3) For an AMP that, on the effective date of this AD, is already updated to incorporate the life
limitations as specified in A318/A319/A320/A321 ALS Part 1 Revision 02, that action ensures
(see Note 1 of this AD) the continued accomplishment of those limitations.

Consequently, for an aeroplane to which that AMP applies, it is acceptable to accomplish the
new and more restrictive limitations, as defined in A318/A319/A320/A321 ALS Part 1 Revision
03, Revision 04 and Revision 05, respectively, to comply with paragraph (1) of this AD.

For that AMP, it is acceptable to incorporate the new and more restrictive limitations, as
defined in A318/A319/A320/A321 ALS Part 1 Revision 03, Revision 04 and Revision 05,
respectively, into the AMP to comply with paragraph (2) of this AD.

(4) For an AMP that, on the effective date of this AD, is already updated to incorporate the life
limitations as specified in A318/A319/A320/A321 ALS Part 1 Revision 03, that action ensures
(see Note 1 of this AD) the continued accomplishment of those limitations.



TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 4
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EASA AD No.: 2017-0215

Consequently, for an aeroplane to which that AMP applies, it is acceptable to accomplish the
new and more restrictive limitations, as defined in A318/A319/A320/A321 ALS Part 1 Revision
04 and Revision 05, respectively, to comply with paragraph (1) of this AD.

For that AMP, it is acceptable to incorporate the new and more restrictive limitations, as
defined in A318/A319/A320/A321 ALS Part 1 Revision 04 and Revision 05, respectively, into the
AMP to comply with paragraph (2) of this AD.

(5) For an AMP that, on the effective date of this AD, is already updated to incorporate the life
limitations as specified in A318/A319/A320/A321 ALS Part 1 Revision 04, that action ensures
(see Note 1 of this AD) the continued accomplishment of those limitations.

Consequently, for an aeroplane to which that AMP applies, it is acceptable to accomplish the
new and more restrictive limitations, as defined in the ALS Part 1 Revision 05, to comply with
paragraph (1) of this AD.

For that AMP, it is acceptable to incorporate the new and more restrictive limitations, as
defined in the ALS Part 1 Revision 05, into the AMP to comply with paragraph (2) of this AD.

Recording AD compliance:
(6) When the AMP of an aeroplane has been revised as required by paragraph (2), (3), (4) or (5) of
this AD, as applicable, that action ensures (see Note 1 of this AD) continued accomplishment of
the tasks as required by paragraph (1) of this AD for that aeroplane. Consequently, after
revising the AMP, as required by paragraph (2), (3), (4) or (5) of this AD, as applicable, it is not
necessary that accomplishment of individual action is recorded for demonstration of AD
compliance on a continued basis.

Note 1: For affected A318, A319, A320 and A321 aeroplanes registered in Europe, complying with
the approved AMP, as specified in paragraph (2), (3), (4) or (5) of this AD, as applicable, is required
by Commission Regulation (EU) 1321/2014, Part M.A.301, paragraph 3.

Ref. Publications:

Airbus ALS Part 1 Revision 05 dated 06 April 2017, or Airbus ALS Part 1 Revision 05 issue 02 dated 19
April 2017.

The use of later approved variations or revisions of this document is acceptable for compliance with
the requirements of this AD.

Remarks:
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of
Compliance for this AD.

2. This AD was posted on 19 September 2016 as PAD 16-134 for consultation until 17 October
2016, and republished on 26 June 2017 as PAD 16-134R1 for additional consultation until 24
July 2017. 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.



TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 3 of 4
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
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EASA AD No.: 2017-0215

3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,
Certification Directorate. E-mail: ADs@easa.europa.eu.

4. For any question concerning the technical content of the requirements in this AD, please
contact: AIRBUS – Airworthiness Office – EIAS; Fax +33 5 61 93 44 51;
E-mail: account.airworth-eas@airbus.com.




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This is a partial extract of the full document - please refer to the actual report for full information.
Sources as credited.