EASA AD No.: 2010-0233

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0233

Date: 26 November 2010

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 participat e 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 a ccomplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise specified by the Age ncy [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) exemptio n]. 

### Type Approval Holder’s Name :
DYN AVIATION Type/Model designation(s) :

CAP10

TCDS Number : EASA.A.370

Foreign AD : Not applicable

Supersedure : None



### ATA 27 Flight Controls – Turnbuckles – Inspection

Manufacturer(s): CAARP, Avions Mu dry et Cie, Apex Industries.

Applicability: CAP10B and CAP10B with Major Change 000302 (commercial name CAP10C), all serial numbers.

Reason: A fatal accident occurred to a CAP 10C , in which the pilot lost control of the aeroplane. The following investigation has revealed that the probable cause of the accident was the improper locking of a turnbuckle (locking clip missing) of the flight control cables, and the subs equent inadvertent release of the pitchup control cable from the turnbuckle. For the above described reasons, this AD requires repetitive inspections to verify the correct installation of the tu rnbuckles of the flight control cables and, if foreseen by the applicable design configuration of the turnbuckles and found to be missing, to restore the locking clip and the safety wire.

Effective Date: 10 December 2010

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) At the next maintenance opportunity giving access to the turnbuckles of the flight control cables, but no late r than 2 months after the effective date of this AD:EASA AD No.: 2010-0233

EASA Form 110 Page 2/2 (1.1) If the turnbuckles are designed to be locked with locking clips and safety wire, verify that the locki ng clips are properly installed in the corresponding groove, that the safety wire of a minimum diameter of 0.8 millimetre (mm) is correctly in stalled and that there is no damage to the whole turnbuckle installation. (1.2) For all other designs of turnbuckles, verify the correct installation of the safety locking devices. (1.3) If any discrepancy is found during the inspection required by paragraph (1.1) or (1.2) of this AD, before next flight restore the correct turnbuckle installation in accordance with standard maintenance practice. (2) Repeat the inspection required by paragraph (1.1) or (1.2) of this AD, as applicable to the turnbuckles de sign, and the associated corrective actions required by paragraph (1.3) of this AD at intervals not to exceed 110 flight hours or 13 months since the last inspection, whichever occurs first.

Ref. Publications: None

Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was published on 17 June 2010 as PAD 10-056 for consultation until 15 July 2010. The Comment Re sponse Document can be found at http://ad.easa.europa.eu/

. 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 tec hnical content of the requirements in this AD, please contact the General Aviation Section, Certification Directorate, EASA. E-mail: jean-bruno.marciacq@easa.europa.eu

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