EASA AD No.: 2014-0015

TE.CAP.00110-003 © 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.: 2014-0015

Date: 14 January 2014

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 EC 2042/2003 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 [EC 2042/2003 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: This AD supersedes Civil Aviation Offi ce (CAO) of Poland AD SP-0052-2003-A,

dated 22 July 2003.



### ATA 27 Flight Controls – Airbrake Control Torque Tube – In spection / Replacement

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: Several occurrences of airbrake torque tube failure were reported on SZD-50-3 “Puchacz” sailplanes. In all cases, as a result of disruption of the welded joint between torque tube and the lever, the broken torqu e tube detached from the lever located in the fuselage. The result of subseq uent investigations identified fatigue damage, as a consequence of periodical stri king load exceeding the established maximum value, to be a possible failure cause. Additionally, corrosion damage was identified at internal surface of the opened tube. This condition, if not detected and corrected, woul d inhibit the function of the airbrake, possibly resulting in reduced control of the sailplane. Prompted by these findings, Allstar PZL issued Serv ice Bulletin (SB) No. BE-052/SZD-50-3/2003 to provide inspection instruct ions. CAO of Poland issued AD SP-0052-2003-A to require a one-time insp ection of the airbrake torque tube in the area of welded joint in accordan ce with that SB. Since that AD was issued, Allstar PZL issued SB No. BE-062/SZD-50-3/2013 to introduce repetitive inspections and accomplishment instructions for reinforced torque tube inspections. For the reasons described above, this AD supersedes CAO of Poland AD SP-0052-2003-A and requires repetitive inspections of the airbrake torque tube and, depending on findings, replacement with a serv iceable part.EASA AD No.: 2014-0015

TE.CAP.00110-003 © 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. Effective Date: 28 January 2014

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 and, thereafter, at intervals not to exceed the values as defined in Al lstar PZL SB No. BE-062/SZD-50-3/2013, as applicable, depending on t orque tube configuration, inspect the airbrake torque tube in accordance with the instructions of Allstar PZL SB No. BE-062/SZD-50-3/ 2013. (2) If, during the inspection as required by paragr aph (1) of this AD, any discrepancy is detected, as detailed in Allstar PZL SB No. BE-062/SZD-50-3/2013, before next flight, repla ce the airbrake torque tube with a serviceable airbrake torque tube in acc ordance with the instructions of Allstar PZL SB No. BE-062/SZD-50-3/ 2013. (3) Replacement of an airbrake torque tube, as requ ired by paragraph (2) of this AD, does not constitute terminating action for repetitive inspections as required by paragraph (1) of this AD. (4) Compliance with the requirements of paragraphs (1) and (2) of this AD can be demonstrated by: (4.1) Revising as follows the approved Aircraft Mai ntenance Programme (AMP), on the basis of which, the operator or the o wner ensures the continuing airworthiness of each operated sailplane : Incorporate the applicable repetitive inspections a nd follow-on corrective actions, as specified in Allstar PZL SB No. BE-062/SZD-50-3/2013,
and (4.2) Complying with the approved AMP described in paragraph (4.1) of this AD.

Ref. Publications: Allstar PZL SB No. BE-062/SZD-50 -3/2013 dated 16 September 2013. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 12 December 2013 as PAD 13 -182 for consultation until 09 January 2014. No comments were received du ring the consultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive 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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