EASA AD No.: 2015-0034-E

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2015-0034-E

Date: 27 February 2015

Note: This Emergency Airworthiness Directive (AD) i s issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the E uropean 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 EU 748/2012, P art 21.A.3B. In accordance with EU 1321/2014 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 [EU 1321/2014 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:
STEMME GmbH & Co. KG Type/Model designation(s): TSA-M powered sailplanes and ASP aeroplanes

TCDS Numbers: EASA.A.143 and EASA.A.612

Foreign AD: Not applicable

Supersedure: None



### ATA 27 Flight Controls – Aileron, Speed Brake and Flap Con trol Systems – Modification

Manufacturer(s): Stemme AG
Applicability: TSA-M powered sailplanes, S6 and S6- RT models, all manufacturer serial numbers (MSN); and ASP Model S15-1 aeroplanes, all MSN.

Reason: A report was received concerning a broken f ork head, installed in the speed brake control circuit of a TSA-M Model S6-RT powere d sailplane. Preliminary investigation results revealed additional cases of bending defect of the same part, which were installed in the aileron and flaps control systems of the TSA-M type design. The same fork heads are also installed in the control systems of ASP Model S15-1 aeroplanes. This condition, if not corrected, could lead to fai lure of the flight control system, possibly resulting in loss of control of the aeropl ane. For the reasons described above, this AD prohibits the operation of the affected aeroplanes pending the availability of a modificati on of the affected flight control systems in accordance with approved instructions. This AD is a temporary measure and further AD actio n may follow.

Effective Date: 02 March 2015EASA AD No.: 2015-0034-E

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: Before next flight, after the effective date of thi s AD, modify the affected flight control systems, or take other actions, in accordan ce with a method approved by EASA. At the time of issuance of this AD, no design solut ion is available to restore the airworthiness of the type designs to a level corres ponding to the respective approved type design specification.

Ref. Publications: None.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The results of the safety assessment have indica ted the need for immediate publication and notification, without the full public consultation process. 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: Stemme AG, Flugplatzstraße F2, Nr. 6-7, D-15344 Str ausberg, Germany, Telephone: +49 (0) 3341/3612 0, E-mail: info@stemme.de

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