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 

Regulation. 

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 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 MA303) 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: 

Foreign AD: 

Supersedure: 

ATA55 

Manufacturer{s): 

Applicability: 

Reason: 

Effective Date: 

TB aeroplanes 

EASA.A.378 

Not applicable 

None 

Stabilizers - Horizontal Stabilizer Spar - Inspection 

SOCATA (formerly EADS SOCATA, Societe de Construction d'Avions de 

Tourisme et d'Affaires) 

SOCATA TB 9, TB 10, TB 20, TB 21 and TB 200 aeroplanes, 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 stabilizer (HS) spar. 

The results of the technical investigation have identified that the corrosion was 

caused by humidity ingress in the HS on aeroplanes subject to severe 

environmental conditions. 

This condition, if not detected and corrected, could result in buckling and 

permanent HS distortion, possibly resulting in reduced control of the aeroplane. 

To address this unsafe condition. SO CAT A issued SB 10-152-55 Revision 1 to 

provide instructions for inspection and corrective action. 

For the reasons described above, this AD requires repetitive inspections of the 

affected area of the HS and, depending on findings, accomplishment of 

applicable corrective action(s). 

21 July 2015 

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Proprietary document. Copies are not controlled. Confirm revision status through the EASA· lnternet{lntranet. 
EASAAD No.: 2015-0130 

Required Action(s) Required as indicated, unless accomplished previously: 

and Compliance 

Time(s) (1) Wrthin 13 months after the effective date of this AD. and, thereafter, at : 

intervals not to exceed 72 months, accomplish a special detailed 

inspection of the HS spar in accordance with the instructions of SOCA T A 

SB 1 0-152-55 Revision 1. 

(2) If, during any inspection as required by paragraph (1) of this AD, no 

discrepancy is detected, protect the HS spar in 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 

corrective action(s) in accordance with the instructions of SOCATA 

SB 10-152-55 Revision 1. 

(4) Accomplishment of protection or corrective actions on an aeroplane as 

required by paragraph (2) or (3) of this AD, as applicable, does not 

constitute terminating action for the repetitive inspections as required 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, are acceptable to comply with the 

requirements of this AD for that aeroplane. After the effective date of this 

AD, repetitive inspections and applicable corrective actions, as required by 

this AD, must be accomplished in 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 Revision 1 dated 

Apri12015. 

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD. 

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

Alternative Methods of Compliance for this AD. 

2. This AD was posted on 26 May 2015 as PAD 15-068 for consultation until 

23 June 2015. No comments were received during the consultation period. 

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: 

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 of America. 

Tel.: +1 (954) 366 3331 

TE.CAP.OOU0-004 ©European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internetjlntranet.