EASA AD No.: 2016-0012

TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified.

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

An agency of the European Union

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Airworthiness Directive

AD No.: 2016-0012

Issued: 14 January 2016

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:

EADS-CASA

Type/Model designation(s):

CN-235 and C-295 aeroplanes

Effective Date: 28 January 2016

TCDS Number(s): EASA.A.186

Foreign AD: Not applicable

Supersedure: None

ATA 27 – Flight Controls – Rudder Pedal Control System – Inspection

Manufacturer(s):

EADS-CASA; formerly Construcciones Aeronáuticas S.A.(CASA).

Applicability:

CN-235, CN-235-100, CN-235-200, CN-235-300 and C-295 aeroplanes, all manufacturer serial 

numbers.

Reason:

An occurrence was reported involving disconnection of the kinematic chain from the co-pilot rudder 

pedals to the rudder control bars located under the cockpit floor. Subsequent investigation revealed 

that the failure was caused by disconnection of the pedal adjustment device from the adjustment 

actuator.

This condition, if not detected and corrected, could lead to loss of the rudder control from the 

affected side, possibly resulting in reduced control of the aeroplane.

To address this potential unsafe condition, Airbus Defence and Space (Airbus D&S) issued Alert 

Operators Transmission (AOT) AOT-CN235-27-0002 and AOT-C295-27-0001, as applicable to 

aeroplane model, to provide inspection instructions.
EASA AD No.: 2016-0012

TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified.

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

An agency of the European Union

Page 2 of 2

For the reasons described above, this AD requires a one-time general visual inspection (GVI) of the 

rudder control system and correctness of the installation connection between the adjustment 

actuators and the adjustment devices of the rudder pedals and, depending on findings, 

accomplishment of applicable corrective action(s).

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

Required as indicated, unless accomplished previously:

(1) Within 30 days after the effective date of this AD, accomplish a GVI of the rudder control 

system in accordance with the instructions of Airbus D&S AOT-CN235-27-0002 or 

AOT-C295-27-0001, as applicable to aeroplane model.

(2) If, during the GVI as required by paragraph (1) of this AD, any discrepancy is detected, as 

defined in Airbus D&S AOT-CN235-27-0002 or AOT-C295-27-0001, as applicable to aeroplane 

model, before next flight, contact Airbus D&S to obtain approved repair and/or maintenance 

instructions and accomplish those instructions accordingly.

Ref. Publications:

Airbus D&S AOT-CN235-27-0002 original issue, dated 23 October 2014.

Airbus D&S AOT-C295-27-0001 original issue, dated 23 October 2014.

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 26 November 2015 as PAD 15-146 for consultation until 24 December 

2015. No comments were received during the consultation period.

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 D&S

Services / Engineering Support 

E-mail: MTA.TechnicalService@military.airbus.com. 

Fax: +34 91 585 3127

For US operators, contact alternatively:

E-mail: TechnicalSupport@airbusmilitaryna.com.