EASA AD No.: 2015-0011

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0011

Date: 20 January 2015

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se specified by the Agency [EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, A rticle 14(4) exemption]. 

### Design Approval Holder’s Name:
EADS-CASA Type/Model designation(s): CN-235 aeroplanes

TCDS Number: EASA.A.186

Foreign AD: Not applicable

Supersedure: None



### ATA 26 Fire Protection – Engine Fire Extinguishing / Detec tion System – Modification

Manufacturer(s): EADS-CASA, formerly Construcciones Aeronáuticas S.A. (CASA)
Applicability: CN-235-200 and CN-235-300 aeroplanes , manufacturer serial numbers from C-018 to C-211, inclusive.
Reason: Several cases of false engine fire warning events were reported, which consequently led to engine in-flight shut down (IFS D) executed by the flight crew using the appropriate emergency procedures. Su bsequent investigation determined that these false engine fire warnings we re the result of insufficient insulation capability of the engine fire detection system. This allowed penetration of moisture into the fire detector conn ectors, reducing the insulation resistance between the inner electrode and connecto r housing below the required values. This condition, if not corrected, could lead to fur ther cases of unnecessary engine IFSD, possibly resulting in reduced control of the aeroplane. To address this potential unsafe condition, EADS-CA SA issued Service Bulletin (SB) SB235-26-0006 providing modification instructi ons. For the reasons described above, this AD requires m odification of the location and routing of the engine fire detection system.

Effective Date: 03 February 2015EASA AD No.: 2015-0011

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:
Within 18 months after the effective date of this A D, modify the location and routing of the engine fire detection system in acco rdance with EADS-CASA SB SB235–26–0006.

Ref. Publications: EADS-CASA SB235-26-0006 original issue, dated 08 July 2014. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 19 December 2014 as PAD 14 -178 for consultation until 16 January 2015. No comments were received du ring the consultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: EADS CASA (Airbus Military) 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

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