AIRBUS HELICOPTERS DEUTSCHLANDEC135/635

ID: 2017-0243
Issue date: 2017-12-06
Effective date: 2017-12-20
Source: EASA
LinkOpen

 AD_2017-0243_1

Share

        QR_Code

Time Limits / Maintenance Checks – Airworthiness Limitations –Amendment

EASA AD No.: 2017-0243


Airworthiness Directive
AD No.: 2017-0243
Issued: 06 December 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 HELICOPTERS DEUTSCHLAND GmbH EC135 and EC635 helicopters

Effective Date:
20 December 2017
TCDS Number(s): EASA.R.009
Foreign AD: Not applicable
Supersedure: This AD supersedes EASA AD 2013-0178 dated 07 August 2013.

ATA 04 – Time Limits / Maintenance Checks – Airworthiness Limitations –
Amendment


Manufacturer(s):

Airbus Helicopters Deutschland GmbH (AHD), formerly Eurocopter Deutschland GmbH (ECD),
Eurocopter España S.A.

Applicability:

EC135 P1, EC135 P2, EC135 P2+, EC135 P3, EC135 T1, EC135 T2, EC135 T2+, EC135 T3, EC635 P2+,
EC635 P3, EC635 T1, EC635 T2+ and EC635 T3 helicopters, all serial numbers (s/n).

Reason:

The airworthiness limitations for AHD EC135 and EC635 helicopters, which are approved by EASA,
are currently defined and published in the Airbus Helicopters (AH) EC135 Master Servicing Manual
(MSM), Chapter 04, Airworthiness Limitations Section (ALS). These instructions have been identified
as mandatory for continued airworthiness.

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

Previously, EASA issued AD 2013-0178 to require accomplishment of the maintenance tasks as
described in MSM Chapter 04 Revision 15, including Temporary Revision 16a.

Since that AD was issued, new EC135 and EC635 models have been certified, and new and/or more
restrictive life limits have been determined for some components. Consequently, AH revised the

TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 4
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2017-0243

MSM Chapter 04, and issued Alert Service Bulletin (ASB) EC135-04A-012, providing instructions to
determine the flight hours (FH) accumulated by the tail rotor hub body, and for periodic
replacement.

For the reason described above, this AD retains the requirements of EASA AD 2013-0178, which is
superseded, and requires accomplishment of the actions as specified in the latest ALS.

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

Required as indicated, unless accomplished previously:

Note 1: AH MSM Revision 23, Chapter 04, dated 26 June 2017 is hereafter referred to as “the ALS”
in this AD.

Maintenance Tasks and Replacement of Life Limited Parts:
(1) From the effective date of this AD, accomplish the following actions, as specified in the ALS, as
applicable depending on helicopter configuration:

(1.1) Replace each component before exceeding the applicable life limit, and

(1.2) Within the thresholds and intervals (see Note 2 of this AD), accomplish all applicable
maintenance tasks.

(1.3) For the tail rotor hub body, Part Number L642A2003102, first replacement as required by
paragraph (1.1) of this AD may be deferred until 9 months after the effective date of this
AD (see Note 3 of this AD).

Note 2: For the purpose of this AD, the thresholds and intervals as defined in the ALS include
specific tolerances for certain tasks.

Note 3: AH ASB EC135-04A-012 provides an acceptable method to determine the FH accumulated
by the tail rotor hub body since first installation on a helicopter.

Corrective Action(s):
(2) In case of finding discrepancies (as defined in the ALS) during accomplishment of any task as
required by paragraph (1) of this AD, within the compliance time specified in the ALS,
accomplish the applicable corrective action(s) in accordance with the approved maintenance
documentation. If no compliance time is identified in the ALS, accomplish the applicable
corrective action(s) before next flight. If a detected discrepancy is not identified in the ALS,
before next flight, contact AHD for approved instructions and accomplish those instructions
accordingly.

Aircraft Maintenance Programme (AMP) Revision:
(3) 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
helicopter, by incorporating the limitations, tasks and associated thresholds and intervals
described in the ALS, as applicable, depending on helicopter configuration.



TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 4
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2017-0243

Credit:
(4) For an AMP that, on the effective date of this AD, is already updated to incorporate the
maintenance tasks and life limitations as specified in a previous revision (see Note 4 of this AD)
of the ALS, that action ensures (see Note 5 of this AD) the continued accomplishment of those
tasks and limitations.

Consequently, for a helicopter to which that AMP applies, it is acceptable to accomplish the
new and more restrictive tasks and limitations (see Note 4 of this AD), as applicable, depending
on helicopter configuration, as defined in, and within the compliance times (see Note 2 of this
AD) as specified in the ALS to comply with paragraph (1) of this AD.

For that AMP, it is acceptable to incorporate the new and more restrictive tasks and limitations
(see Note 4 of this AD), as applicable to helicopter configuration, as defined in the ALS, into the
AMP to comply with paragraph (3) of this AD.

Note 4: For the purpose of this AD, the “previous revision” of the ALS is the one currently
incorporated in the AMP of the helicopter, while “the new and more restrictive tasks” are those
that have been included in the ALS since that previous revision was incorporated in the AMP of the
helicopter.

Recording AD compliance:
(5) When the AMP of a helicopter has been revised as required by paragraph (3) or (4) of this AD,
as applicable, that action ensures (see Note 5 of this AD) continued accomplishment of the
tasks as required by paragraphs (1) and (2) of this AD for that helicopter. Consequently, after
revising the AMP, as required by paragraph (3) or (4) 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 5: For affected EC135 and EC635 helicopters registered in Europe, complying with the
approved AMP, as specified in paragraph (3) or (4) of this AD, as applicable, is required by
Commission Regulation (EU) 1321/2014, Part M.A.301, paragraph 3.

Ref. Publications:

AH MSM Revision 23, Chapter 04, dated 26 June 2017.

AH ASB EC135-04A-012 original issue dated 11 September 2017.

The use of later approved revisions of these documents 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 03 November 2017 as PAD 17-155 for consultation until 01 December
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.
An agency of the European Union
EASA AD No.: 2017-0243

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 Helicopters Deutschland GmbH, Industriestrasse 4,
86609 Donauwörth, Federal Republic of Germany
Telephone: + 49 (0)151 1422 8976; Facsimile: + 49 (0)906 71 4111
Web portal: https://keycopter.airbushelicopters.com > Technical Requests Management
E-mail: customersupport.helicopters@airbus.com.




TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 4 of 4
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.