EASA AD No.: 2011-0010

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0010

Date: 20 January 2011

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 partic ipate in the activities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ens ured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which an Airworthiness Directive app lies, except in accordance with the requirements of that Airworthiness Directive unless otherwise specified by the Ag ency [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].


### Type Approval Holder’s Name :



### EADS-CASA Type/Model designation(s) :
CN-235-100, CN-235-200 and CN-235-300 aeroplanes.

TCDS Number : EASA.A.186

Foreign AD : Not applicable

Supersedure : None



### ATA 76 Engine controls – Engine Condition Control Cable – Inspection / Replacement

Manufacturer(s): EAD S-CASA; Construcciones Ae ronáuticas S.A.(CASA)
Applicability: CN-235-100, CN-235-200 and CN-235-300 airc raft with serial numbers (S/N) from C-030 to C-149.

Reason: EADS-CASA received reports of engine condition control cable (Part Number (P/N) 35-56382-0003) failures that, in one of the cases, occurred during the starting phase of one engine which led to an engine shut down following the procedures described within the Aircraft Operation Manual. The investigation revealed that the cable failure is due to a fracture in the area of the pulley MS 20219-1. The root cause of the fracture is an unsuitable ratio between the diameter of the pulley and the cable type and diameter. This condition, if not detected and corrected, could lead to the engine condition control cable failure and consequent runway excursion if it occurs during take-off or reduced control of the aeroplane if it occurs during flight. To address this condition, EADS-CASA has developed an engine condition control cable P/N 35-56382-0005 with improved characteristics. For the reason described above, this AD requires, at first, inspections for good condition of the engine condition control cable, and its replacement (scheduled or depending of the inspection findings) with engine condition control cable P/N 35-56382-0005.EASA AD No.: 2011-0010

EASA Form 110 Page 2/2 Effective Date: 03 February 2011.

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within 9 months or 300 flight hours (FH), whichever occurs first after the effective date of this AD, accomplish the following actions concurrently: (1.1) Identify the P/N of the engine control condition cable installed on the aeroplane to determine whether it has P/N 35-56382-0003

. (1.2) If the affected engine control condition cable is installed, inspect it in accordance with instructions of CN-235 Maintenance Manual (AMM), Task 76-10-00 block 601, Procedure (b) ‘Inspection’. (2) Thereafter, within 9 months or 300 FH, whichever occurs first after the initial inspection required by paragraph (1.2) of this AD, perform a second inspection of the engine control condition cable in accordance with instructions of CN-235 Maintenance Manual (AMM), Task 76-10-00 block 601, Procedure (b) ‘Inspection’

. (3) If, during the inspections required by paragraphs (1.2) and (2) of this AD, excessive wear of the engine control condition cable is detected, before next flight, replace the engine control condition cable P/N 35-56382-0003 with P/N 35-56382-0005, in accordance with instructions of CN-235 Maintenance Manual (AMM), Task 76-10-12 block 401. (4) Within 27 months or 900 flight hours (FH), whichever occurs first after the effective date of this AD, and unless the engine control condition cable has already been replaced in accordance with paragraph (3) of this AD, replace the engine control condition cable P/N 35-56382-0003 with P/N 35-56382-0005 in accordance with instructions of CN-235 Maintenance Manual (AMM), Task 76-10-12 block 401. (5) After the effective date of this AD, do not install engine control condition cable P/N 35-56382-0003 on CN-235-100, CN-235-200 and CN-235-300 aeroplanes.

Ref. Publications: CN-235 Maintenance Manual (AMM), Rev. 057, issued the 15 July 2010. The use of later approved revisions of this document 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. The required actions and the risk allowance have granted the issuance of a Final AD with Request for Comments, postponing the public consultation process after publication. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the te chnical content of the requirements in this AD, please contact: EADS-CASA, Military Transport Airc raft Division (MTAD), Integrated Customer Services (ICS), Technical Services, Avenida de Aragón 404, 28022 Madrid, Spain; Telephone +34 91 585 55 84; Facsimile +34 91 585 55 05; E-mail: MTA.TechnicalService@casa.eads.net

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