EASA AD No.: 2015-0046

TE.CAP.00110-004 © 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 AIRWORTHINESS DIRECTIVE

AD No.: 2015-0046

Date: 16 March 2015

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 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: ALLSTAR PZL GLIDER Sp. z o.o. Type/Model designation(s): SZD-50-3 “Puchacz” sailplanes

TCDS Number: EASA.A.312

Foreign AD: Not applicable

Supersedure: None



### ATA 27 Flight Controls – Rudder Control Cable Fitting – In spection / Reinforcement

Manufacturer(s): Allstar PZL Glider Sp. z o.o. (All star PZL)
Przedsi ę biorstwo Do ś wiadczalno-Produkcyjne Szybownictwa „PZL-Bielsko”.
Applicability: SZD-50-3 “Puchacz” sailplanes, all s erial numbers
Reason: An occurrence was reported involving a SZD- 50-3 “Puchacz” sailplane, where a rudder cable fitting block, located in the forward part of the fuselage, detached after application of a high load on the steering pe dal during spin recovery operation. Subsequent investigations determined tha t the failure was either caused by a manufacturing deficiency or originated by a crack. This condition, if not detected and corrected, coul d lead to further cases of rudder cable fitting block detachment, resulting in reduced control of the sailplane. To address this unsafe condition, Allstar PZL issue d Service Bulletin (SB) No. BE-063/SZD-50-3/2014, to provide inspection and rei nforcement instructions. For the reasons described above, this AD requires a ccomplishment of a onetime inspection of both (right hand (RH) and left h and (LH)) rudder cable fitting blocks to verify proper attachment to the fuselage shell and, depending on finding(s), a repair. This AD also requires reinfor cement of the affected structural area.

Effective Date: 30 March 2015EASA AD No.: 2015-0046

TE.CAP.00110-004 © 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: (1) Within 30 days after the effective date of this AD, inspect the area around both (RH and LH) rudder cable fitting blocks in acc ordance with the instructions of Allstar PZL SB No. BE-063/SZD-50-3/ 2014. (2) If, during the inspection as required by paragr aph (1) of this AD, any crack or fitting block detachment is detected, before nex t flight, repair and reinforce the attachment of both (RH and LH) rudder cable fitting blocks in accordance with the instructions of Allstar PZL SB No. BE-063/SZD-50- 3/2014. (3) Unless accomplished as required by paragraph (2 ) of this AD, within 12 months after the effective date of this AD, reinfor ce the attachment of both (RH and LH) rudder cable fitting blocks in accordan ce with the instructions of Allstar PZL SB No. BE-063/SZD-50-3/2014. (4) Sailplanes modified, before the effective date of this AD, in accordance with former German Democratic Republic Änderungsanw eisung No. SZD50-3/3 are compliant with the requirements of this AD.

Ref. Publications: Allstar PZL SB No. BE-063/SZD-50 -3/2014 dated 14 December 2014. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD. Änderungsanweisung No. SZD-50-3/3 dated 18 May 1988

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Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 20 January 2015 as PAD 15- 003 for consultation until 17 February 2015. The Comment Response Docume nt can be found at http://ad.easa.europa.eu

. 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: Allstar PZL Glider Sp. z o.o., ul. Cieszy ń ska 325 43-300 Bielsko-Biała / Poland Telephone / Fax: +48 33 812 50 26, E-mail: techsupport@szd.com.pl

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