EASA AD No.: 2014-0262

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0262

Date: 05 December 2014

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 EC 2042/2003 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 [EC 2042/2003 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: This AD supersedes Dirección General d e Aviación Civil (DGAC) of Spain AD No.

03/00, dated 28 March 2000.



### ATA 76 Engine Controls – Engine Control System Cables / Te leflex Cables

– Replacement

Manufacturer(s): EADS-CASA; Construcciones Aeronáut icas S.A.(CASA)

Applicability: CN-235-100 and CN-235-200 aeroplanes , serial numbers from C-016 through C-073, inclusive.

Reason: Three occurrences of cable disruption were reported in 1999. The failed parts, having a part number (P/N) 7-44728-20, were part of the engine control system assembly P/N 7-44728-12. Two cables were connected to the Power Lever and one cable to the Condition Lever control. Service r ecords of the affected parts showed that each cable accumulated more than 14 000 flight cycles (FC). The subsequent investigation determined that the di sruption was attributed to fatigue related crack. This condition, if not corrected, could lead to fai lure of the engine control system resulting in a loss of the affected engine c ontrol. Prompted by this unsafe condition, DGAC Spain issue d AD 03/00 to require rigging of the throttle stops, and one-time replace ment of the affected engine control cable assembly (P/N 7-44728-12), or the aff ected cable (P/N 7-44728-20) before exceeding 12 000 FC. After that AD was issued, a new occurrence of cable (P/N 72830-20) disruption was reported. In that case, the affected cable was part of the Condition Lever control and had accumulated 8 497 flight hours (FH) and 8 858 FC. Fractographic analysis of the affected cable identi fied that the fatigue nucleation seemed to have been induced by microcrac ks along the cable surface. Additionally, another case of control cabl e (P/N 72830-20) failure wasEASA AD No.: 2014-0262

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. reported, where the affected part accumulated 9 936 FH and 10 552 FC and was part of the Power Lever control. Investigation of the latter case identified again a fatigue nucleation to be the cause of the c able failure. To address this potentially unsafe condition, Airbu s Military issued Alert Operators Transmission (AOT) AOT-CN235-76-0001 to p rovide a repetitive replacement interval and instructions. For the reasons described above, this AD retains th e requirements of DGAC Spain AD No. 03/00, which is superseded, but requir es repetitive replacement of the affected Teleflex cables.

Effective Date: 19 December 2014

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: Re-statement of requirements of DGAC Spain AD No. 0 3/00: (1) Within 15 days after 12 April 2000 [the effecti ve date of DGAC Spain AD No 03/00], accomplish a rigging of the throttle sto ps in accordance with the instructions of CASA COM 235-140. New requirements of this AD: (2) Within the threshold as defined in Table 1 of t his AD and, thereafter, at intervals not to exceed 5 000 FC accumulated by a T eleflex cable P/N 72830-20, replace each Power lever and Condition Le ver Teleflex cable P/N 72830-20 with a serviceable part in accordance with the instructions of Airbus Military AOT-CN235-76-0001.

Table 1 – Teleflex Cable Replacement Threshold
FC accumulated by the Teleflex cable P/N 72830-20 on the effective date of this AD Compliance Time (since first installation on an aeroplane)

Less than 4 700 FC Before exceeding 5 000 FC Equal to or more than 4 700 FC but less than 6 000 FC Within 300 FC or 12 months after the effective date of this AD, whichever occurs first Equal to or more than 6 000 FC but less than 7 000 FC Within 200 FC or 6 months after the effective date of this AD, whichever occurs first Equal to or more than 7 000 FC Within 100 FC or 3 m onths after the effective date of this AD, whichever occurs first
(3) From the effective date of this AD, installatio n of a Teleflex cable P/N 72830-20 on an aeroplane is allowed only, if the pa rt is new or accumulated less than 5 000 FC since its first inst allation on an aeroplane.

Ref. Publications: CASA COM 235-140 revision 01, da ted 21 March 2000. Airbus Military AOT-CN235-76-0001 original issue, d ated 27 May 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 04 November 2014 as PAD 14 -164 for consultation until 02 December 2014. No comments were received d uring the consultation period.EASA AD No.: 2014-0262

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 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.