## EASA EASA 

### AD No .: 2015-0130 

## AIRWORTHINESS DIRECTIVE AD No.: 2015-0130
Date: 07 July 2015 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 participate in the activities of EASA under Artide 66 of that Regu lation . This AD is issued in accordance with EU 748/2012 , Part 21 .A . 3B. In accordance with EU 1321/2014 Annex I, Part MA301 , the continuing airworth i ness of an aircraft shall be ensured by accomplishing any applicabl e ADs . Conseque ntly, no person may operate an a ircraft to which an AD applie s , except in accordance with the r equ ireme nts of that AD , unless otherwise specified by the Agency [EU 1321/2014 Annex I, Part MA 303) or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

### Design Approval Holder's Name: Type/Model designation(s): SOCATA TCDS Number: Fo r e i g n AD: Supersedure : 

### ATA55 Manufacturer{s): Applicability: Reason:

Effective Date : TB 

### aeroplanes EASA.A.378 Not applicable None 

### Stab ilizers - Horizontal Stab ilizer Spar - Inspection SOCATA (formerly EADS SOCATA, Societe de Construction d 'Avions de Tourisme et d' Affa ires) SOCATA TB 9, TB 10, TB 20 , TB 21 and TB 200 ae rop lanes , all manufacturer serial numbers. During accomplishment of SOCATA Service Bulletin {SB) SB10-152-55 at original issue, some operators reported finding heavy corrosion of the horizontal stab ili zer (HS) spar. The results of the technica l investigati on have identified that the corrosion was caused by humidity ingress in the HS on aerop lanes subject to severe environmental conditions
. This condition , if not d etected and corrected , could result in buckl i ng and permane nt HS distortion, possibly resulting in reduced control of the aeroplane
. To address this unsafe condition. SOCAT A issued SB 10- 152-55 Revision 1 to provide instructions fo r inspection and corrective action . For the reasons described above, this AD requires repeti ti ve inspections of the affected area of t h e HS and, depe nding on findings , accomplishment of applicable corrective action(s)
. 21 July 2015

TE.C AP . OO ll0-004 ©E uropean Aviation Safety Agency. All rights reserved. 1/2 Pro prietary document. Copies are not contro lled . C onfirm revision status through the EASA · lnternet{lntranet.EASAAD No .: 2015-0130 Required Action(s) Required as indicated, unless accomplished previously : and Compliance (1) Wrthin 13 months after the effective date of this AD. and, thereafter, at Time(s) : intervals not to exceed 72 months, accomplish a special detailed inspection of the HS spar in accordance with the instructions of SOCA TA SB 1 0-152-55 Revision 1. (2) If, during any inspection as required by paragraph (1) of th i s AD, no discrepancy is detected, protec t the HS spa r i n accordance with the instructions of SOCATA SB 10- 152-55 Revision 1. (3) If, during any inspection as required by paragraph (1) of this AD, any discrepancy is detected , before next flight, accomplish the applicable correc ti ve action(s) in accordance with the instructions of SOCATA SB 10-152-55 Revision 1 . (4) Accomp li shment of protection or corrective actions on an aeroplane as required by paragraph (2) or (3) of th is AD, as applicable, does not constitute terminating action for the repetitive inspections as requi r ed by paragraph (1) of this AD for that aeroplane. (5) Inspections and corrective actions on an aeroplane , accomplished before the effective date of this AD in accordance with the instructions of SOCATA SB 10-152- 55 at original issue, a re acceptable to comply wi th the requirements of this AD for that ae roplane. After the eff e ctive date of this AD , repetit ive inspections and applicable corrective actions , as requ ired by this AD, must be accomplished i n accordance with the instructions of SOCATA SB 10-152-55 Revision 1. Ref. Publications : SOCATA SB 10-152-55 original issue dated May 2013 , or Revis ion 1 dated Apri12015. The use of later approved revisions ofthis document is acceptable for compliance with the requ irements ofthis AD. Remarks: 1. If requested and appropriate ly substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 26 May 2015 as PAD 1 5- 068 for consu ltation unti l 23 June 2015. No comments were received during the consultation period. 3 . Enqui ri es regard in g this AD should be referred to the Safety Information Section, Certification Directorate, EASA. E- mail : ADs@easa .europa.e u . 4 . For a ny question concerning the technica l content of the requi rements in this AD , please contact: SOCATA, Direction des Services, 65921 Tarbes Cedex 9 , France. Tel. +33 (0) 5 62 41 73 00, Fax:+ 33 (0) 5 62 41 76 54 . or for the U.S
.A. SOCATA NORTH AMERICA , 601 NE 10 Street, Pompano Beach, FL 33060 , The United States ofAmerica
. Tel.: +1 (954) 366 3331

TE .CAP.OOU0-004 ©European Aviation Safety Agency. All rights reserved
. 2/2 Proprietary document. Copie s are not controlled. Confirm rev is ion status through the EASA- Internetjlntranet
.