AIRBUS HELICOPTERSEC175

ID: 17-161
Issue date: 2017-12-04
Source: EASA
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Equipment / Furnishings – Automatic Deployable Emergency Locator Transmitter – Inspection / Replacement send comment

EASA PAD No.: 17-161


Notification of a Proposal to issue
an Airworthiness Directive
PAD No.: 17-161
Issued: 04 December 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):
AIRBUS HELICOPTERS EC175 B helicopters

Effective Date:
[TBD - standard: 14 days after AD issue date]
TCDS Number(s): EASA.R.150
Foreign AD: Not applicable
Supersedure: None


ATA 25 – Equipment / Furnishings – Automatic Deployable Emergency Locator
Transmitter – Inspection / Replacement


Manufacturer(s):

Airbus Helicopters (AH)

Applicability:

EC175 B helicopters, all manufacturer serial numbers, delivered before 01 July 2017.

Note 1: For the purpose of this AD, the delivery date is the “date of statement of conformity”
indicated on the identification plate of the helicopter.

Reason:

Several occurrences were reported of finding deviations from the approved design of the electrical
bonding braid installation connected to the System Interface Unit (SIU), Part Number
(P/N) 503-42-G, of the Automatic Deployable Emergency Locator Transmitter (ADELT). The reported
deviations were detected during the manufacturing of the helicopters. Subsequent investigation
identified a specific group of helicopters affected by this manufacturing deficiency.




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EASA PAD No.: 17-161

This condition, if not detected and corrected, could damage the integrity of the SIU, possibly
resulting in unwanted deployment of the ADELT beacon, malfunction of the emergency signalling
system during an emergency, or injuries to persons on the ground.

To address this potential unsafe condition, AH corrected the installation instructions used in
production and published Alert Service Bulletin (ASB) EC175-25A013 (hereafter referred to as ‘the
ASB’ in this AD), providing inspection and replacement instructions.

For the reasons described above, this AD requires repetitive inspections of the installation of the
electrical bonding braid connected to the SIU and replacement.

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

Required as indicated, unless accomplished previously:

Repetitive Inspection(s):
(1) Within 30 days after the effective date of this AD and, thereafter, at intervals not to exceed 3
months, visually inspect the electrical bonding braid connected to the SIU in accordance with
the instructions of Paragraph 3.B.2.a of the ASB.

Corrective Action(s):
(2) If, during any inspection as required by paragraph (1) of this AD, any discrepancy, as defined in
the ASB, is detected, before next flight, accomplish the applicable corrective action(s) in
accordance with the instructions of Paragraph 3.B.2.a of the ASB.

Replacement:
(3) Within 12 months after the effective date of this AD, or within 2 months after accomplishment
of a corrective action, as required by paragraph (2) of this AD, as applicable, replace the SIU
with a serviceable part in accordance with the instructions of Paragraph 3.B.2.b of the ASB.

Terminating Action:
(4) Replacement on a helicopter of an SIU, as required by paragraph (3) of this AD, constitutes
terminating action for the repetitive inspections as required by paragraph (1) of this AD for that
helicopter.

Ref. Publications:

AH ASB No. EC175-25A013 original issue, dated 26 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 01 January 2018.

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




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.: 17-161

3. For any question concerning the technical content of the requirements in this PAD, please
contact Airbus Helicopters (Technical Support), Aéroport de Marseille Provence - 13725
Marignane Cedex, France, Telephone +33 (0)4 42 85 97 97, Fax +33 (0)4 42 85 99 66,
Web portal: https://keycopter.airbushelicopters.com > Technical Requests Management, or
E-mail: support.technical-airframe.ah@airbus.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.