ATRATR42

ID: 17-156
Issue date: 2017-11-07
Source: EASA
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Wings – Outer Wing Box Upper Rib Feet – Inspection send comment

EASA PAD No.: 17-156


Notification of a Proposal to issue
an Airworthiness Directive
PAD No.: 17-156
Issued: 07 November 2017
Note: This Proposed Airworthiness Directive (PAD) 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.

In accordance with the EASA Continuing Airworthiness Procedures, the Executive Director is proposing the issuance of an EASA Airworthiness Directive
(AD), applicable to the aeronautical product(s) identified below.
All interested persons may send their comments, referencing the PAD Number above, to the e-mail address specified in the ‘Remarks’ section, prior to
the consultation date indicated.


Design Approval Holder’s Name: Type/Model designation(s):
ATR-GIE AVIONS de TRANSPORT RÉGIONAL ATR 42 aeroplanes

Effective Date:
[TBD - standard: 14 days after AD issue date]
TCDS Number(s): EASA A.084
Foreign AD: Not applicable
Supersedure: This AD supersedes DGAC France AD F-2004-191 (EASA approval 2004-12117)
dated 22 December 2004.


ATA 57 – Wings – Outer Wing Box Upper Rib Feet – Inspection


Manufacturer(s):

ATR-GIE Avions de Transport Régional (formerly Aerospatiale – Aeritalia, Aerospatiale – Alenia,
Aerospatiale ATR – ALENIA, EADS ATR – Alenia)

Applicability:

ATR 42-200, ATR 42-300, ATR 42-320, ATR 42-400 and ATR 42-500 aeroplanes, all manufacturer
serial numbers.

Reason:

Occurrence was reported of detecting cracks on the wing of one in-service ATR 42 aeroplane in
2004. The cracks were found on the upper feet of ribs and on the upper skin of the wing outer
boxes.

This condition, if not detected and corrected, could adversely affect the structural integrity of the
aeroplane.

To address this potential unsafe condition, ATR issued Service Bulletin (SB) ATR42-57-0064 to
provide inspection instructions and DGAC France issued AD F-2004-191 (EASA approval 2004-12117)

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EASA PAD No.: 17-156

to require, for aeroplanes having accumulated more than 4 000 flight cycles (FC), a one-time
Detailed Visual Inspection (DVI) of outer wing box upper skin and upper rib feet, on the right hand
(RH) and left hand (LH) sides, from rib 24 to rib 29. After that AD was issued, based on inspection
results (all aeroplanes inspected, no similar case found), it was determined that these cracks were
an isolated case.

More recently, three other cases were reported, indicating that this may not be an isolated case and
that cracks could occur in this area of the wings on other ATR 42 aeroplanes. Consequently, ATR
published SB ATR42-57-0074 (hereafter referred as ‘ATR SB’ in this AD) to provide inspection
instructions.

For the reasons described above, this AD supersedes DGAC France AD F-2004-191 and requires
repetitive DVI of the same wing areas and, depending on findings, accomplishment of a repair.

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

Required as indicated, unless accomplished previously:

Repetitive Inspections:
(1) Within the compliance time defined in Table 1 of this AD and, thereafter, at intervals not to
exceed 48 months or 6 000 FC, whichever occurs first, accomplish a DVI of the LH and RH wing
rib upper feet and upper panel between rib 24 and rib 29, in accordance with the instructions
of ATR SB.

Table 1 – Initial Inspection
Compliance Time (whichever occurs later, A or B)
Within 48 months or 6 000 FC, whichever occurs first since
A
aeroplane first flight
B Within 12 months after the effective date of this AD

Corrective Action(s):
(2) If, during any inspection as required by paragraph (1) of this AD, any discrepancy is detected,
before next flight, contact ATR for approved repair instructions and, within the compliance
time(s) specified in those instructions, accomplish those instructions accordingly.

Terminating Action:
(3) Repair of an aeroplane, as required by paragraph (2) of this AD, does not constitute terminating
action for the repetitive DVI as required by paragraph (1) of this AD, unless the ATR repair
instructions specify otherwise.

Reporting:
(4) Within 30 days after each DVI as required by paragraph (1) of this AD, as applicable, the
inspection results (including no findings) have to be sent to ATR in accordance with the
instructions of ATR SB.




TE.CAP.00112-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA PAD No.: 17-156

Ref. Publications:

ATR Service Bulletin ATR42-57-0074 original issue dated 19 October 2017.

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

Remarks:
1. This Proposed AD will be closed for consultation on 05 December 2017.

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

3. For any question concerning the technical content of the requirements in this PAD, please
contact: ATR - GIE Avions de Transport Régional, Continued Airworthiness Service,
Telephone: +33 (0)5 62 21 62 21, Fax: +33 (0) 5 62 21 67 18;
E-mail: continued.airworthiness@atr-aircraft.com.




TE.CAP.00112-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 3 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union

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