EASA AD No.: 2015-0034-E 

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EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2015-0034-E 

Date: 27 February 2015 

Note: This Emergency 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 EU 1321/2014 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 [EU 

1321/2014 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: 

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 Control 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 fork head, installed in the speed 

brake control circuit of a TSA-M Model S6-RT powered 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 failure of the flight control system, 

possibly resulting in loss of control of the aeroplane. 

For the reasons described above, this AD prohibits the operation of the affected 

aeroplanes pending the availability of a modification of the affected flight control 

systems in accordance with approved instructions. 

This AD is a temporary measure and further AD action may follow. 

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

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 2/2 

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Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

Before next flight, after the effective date of this AD, modify the affected flight 

control systems, or take other actions, in accordance with a method approved 

by EASA. 

At the time of issuance of this AD, no design solution is available to restore the 

airworthiness of the type designs to a level corresponding to the respective 

approved type design specification. 

Ref. Publications: None. 

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The results of the safety assessment have indicated the need for 

immediate publication and notification, without the full public consultation 

process. 

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: 

Stemme AG, Flugplatzstraße F2, Nr. 6-7, D-15344 Strausberg, Germany, 

Telephone: +49 (0) 3341/3612 0, E-mail: info@stemme.de.