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 participate 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 ensured by accomplishing any applicable ADs. Consequently, no person 

may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of that 

Airworthiness Directive 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]. 

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

Applicability: CN-235-100, CN-235-200 and CN-235-300 aircraft 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 & Research Section, Certification 

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

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

in this AD, please contact: 

EADS-CASA, Military Transport Aircraft 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.