EASA AD No.: 2014-0262

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/3 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2014-0262 

Date: 05 December 2014 

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 EU 748/2012, Part 21.A.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 AD applies, except in accordance with the requirements of that AD, 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]. 

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 de Aviación Civil (DGAC) of Spain AD No. 

03/00, dated 28 March 2000. 

ATA 76 Engine Controls – Engine Control System Cables / Teleflex Cables 

– Replacement 

Manufacturer(s): EADS-CASA; Construcciones Aeronáuticas 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 records of the affected parts 

showed that each cable accumulated more than 14 000 flight cycles (FC). 

The subsequent investigation determined that the disruption was attributed to 

fatigue related crack. 

This condition, if not corrected, could lead to failure of the engine control 

system resulting in a loss of the affected engine control. 

Prompted by this unsafe condition, DGAC Spain issued AD 03/00 to require 

rigging of the throttle stops, and one-time replacement of the affected engine 

control cable assembly (P/N 7-44728-12), or the affected 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 identified that the fatigue 

nucleation seemed to have been induced by microcracks along the cable 

surface. Additionally, another case of control cable (P/N 72830-20) failure was 
EASA AD No.: 2014-0262

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/3 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

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 cable failure. 

To address this potentially unsafe condition, Airbus Military issued Alert 

Operators Transmission (AOT) AOT-CN235-76-0001 to provide a repetitive 

replacement interval and instructions. 

For the reasons described above, this AD retains the requirements of DGAC 

Spain AD No. 03/00, which is superseded, but requires repetitive replacement 

of the affected Teleflex cables. 

Effective Date: 19 December 2014 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

Re-statement of requirements of DGAC Spain AD No. 03/00: 

(1) Within 15 days after 12 April 2000 [the effective date of DGAC Spain AD 

No 03/00], accomplish a rigging of the throttle stops 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 this AD and, thereafter, at 

intervals not to exceed 5 000 FC accumulated by a Teleflex cable P/N 

72830-20, replace each Power lever and Condition Lever 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 months after the 

effective date of this AD, whichever 

occurs first 

(3) From the effective date of this AD, installation of a Teleflex cable P/N 

72830-20 on an aeroplane is allowed only, if the part is new or 

accumulated less than 5 000 FC since its first installation on an aeroplane. 

Ref. Publications: CASA COM 235-140 revision 01, dated 21 March 2000. 

Airbus Military AOT-CN235-76-0001 original issue, dated 27 May 2014. 

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. This AD was posted on 04 November 2014 as PAD 14-164 for consultation 

until 02 December 2014. No comments were received during 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. Confirm revision status through the EASA-Internet/Intranet.

3. Enquiries regarding this AD should be referred to the Safety Information 

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 (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.