EASA AD No.: 2013-0176

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0176

Date: 07 August 2013

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation 

(EC) No 216/2008 on behalf of the European Community, 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 EU 748/2012, Part 21.A.3B. In accordance with EC 2042/2003 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 [EC 

2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].

Design Approval Holder’s Name:

EUROCOPTER DEUTSCHLAND GmbH

Type/Model designation(s):

EC 135, EC 635 and MBB-BK 117 C-2 

helicopters

TCDS Numbers: EASA.R.009 and EASA.R.010

Foreign AD: Not applicable

Supersedure: None

ATA 22 Auto Flight System – Longitudinal, Lateral and Yaw Actuator / 

Control Rod Attachment Hardware – Inspection / Replacement

Manufacturer(s): Eurocopter Deutschland GmbH, Eurocopter España S.A., American 

Eurocopter LLC

Applicability: EC 135 P1 (CDS), EC 135 P1 (CPDS), EC 135 P2+, EC 135 P2 (CPDS), 

EC 135 T1 (CDS), EC 135 T1 (CPDS), EC 135 T2+, EC 135 T2 (CPDS),

EC 635 P2+, EC 635 T1 (CPDS) and EC 635 T2+ helicopters, all serial 

numbers (s/n), and MBB-BK 117 C-2 helicopters, all s/n.

Reason: During installation work on a helicopter, it was found impossible to establish 

attachment hardware on a threaded blind borehole between the Smart Electro

Mechanical Actuator (SEMA) and the control rod without play. 

The reason for this loose attachment hardware was an unfavourable adding of 

the tolerances of the individual attachment hardware elements. As a result, the 

screw pushed against the bottom of the threaded blind borehole on the SEMA 

and no clamping effect could be achieved on the screw head.

This condition, if not detected and corrected, could lead (in the worst case

scenario) to the loss of the concerned control axis, possibly resulting in loss of 

control of the helicopter.

To address this potential unsafe condition, Eurocopter Deutschland GmbH

(ECD) issued Alert Service Bulletin (ASB) No. EC135-22A-015 and ASB No. 

MBB BK117 C-2-22A-009.

For the reasons described above, this AD requires a one-time inspection of the 

affected SEMAs for attachment hardware connected to the respective control 

rod to detect improper connection / play and, depending on findings, 

replacement of the affected hardware.
EASA AD No.: 2013-0176

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

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Effective Date: 21 August 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 50 flight hours after the effective date of this AD, inspect the 

attachment hardware connection between the relevant SEMA and the 

SEMA control rod in accordance with the instructions of ECD ASB 

EC135-22A-015 or ASB MBB BK117 C-2-22A-009, as applicable to 

helicopter type.

(2) If, during the inspection as required by paragraph (1) of this AD, improper 

connection / play is detected, before next flight, correct the connection in 

accordance with the instructions of ECD ASB EC135-22A-015 or ASB 

MBB BK117 C-2-22A-009, as applicable to helicopter type.

(3) From the effective date of this AD, installation of attachment hardware 

between the SEMA and the SEMA control rod must be established without 

play in accordance with the instructions of ECD ASB EC135-22A-015 or 

ASB MBB BK117 C-2-22A-009, as applicable to helicopter type.

Note: The use of instructions specified in the EC 135 Aircraft Maintenance 

Manual (AMM), chapters 67-10-00, 4-9, 67-10-00, 4-10, 67-20-00, 4-12,

67-20-00, 4-13 and 67-20-00, 4-14; or MBB BK 117 C-2 AMM, chapter 

22-10-00, 6-2, as applicable to helicopter type, is acceptable to comply with 

the requirements of paragraph (3) of this AD.

Ref. Publications: ECD ASB EC135-22A-015 original issue, dated 13 May 2008, or Revision 01, 

dated 28 January 2013.

ECD ASB MBB BK117 C-2-22A-009 original issue, dated 13 May 2008, or

Revision 01, dated 03 August 2009.

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD.

EC 135 AMM Revision 10 or later.

MBB BK 117 C-2 AMM Revision 12 or later.

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. This AD was posted on 28 June 2013 as PAD 13-089 for consultation until 

26 July 2013. No comments were received during the consultation period.

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.

4. For any question concerning the technical content of the requirements in 

this AD, please contact: Eurocopter Deutschland GmbH, 

Industriestrasse 4, 86607 Donauwörth, Germany

Telephone: +49 (0)151 1422 8976, Fax: +49 (0)906 71 4111.