EASA AD No.: 20 1 6
- 0 012

TE.CAP.0011 0
- 00 5 © 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 1 of 2 

# Airworthiness Directive AD No.: 20 1 6 - 0 012 Issued: 1 4 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 ope rate 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: 2 8 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 contro l 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 ru dder 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.: 20 1 6
- 0 012

TE.CAP.0011 0
- 00 5 © 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 ad justment 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 require d 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 a nd 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 th ese document s 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
.