EASA AD No.: 2013-0035

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0035

Date: 22 February 2013

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 Article 66 of that 

Regulation.

This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EC 2042/2003 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 [EC 

2042/2003 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:

SOCATA

Type/Model designation(s):

TBM 700 aeroplanes

TCDS Number: EASA A.010

Foreign AD: Not applicable

Supersedure: This AD supersedes DGAC France AD 2000-307(A) dated 09 August 2000.

ATA 55 Stabilizers – Horizontal Stabiliser Outboard Fittings – Modification

Manufacturer(s): SOCATA (formerly EADS SOCATA)

Applicability: SOCATA TBM 700 aeroplanes, manufacturer serial numbers (MSN): 1 through 

161 inclusive, except MSN 99 and 157, which were already modified during 

production.

Reason: During the 1990s, several occurrences were reported of finding cracks in the 

outboard hinge fittings of the horizontal stabiliser on TBM 700 aeroplanes.

This condition, if not detected and corrected, could result in rupture of the 

outboard hinge fittings, which would adversely affect the structural integrity of 

the horizontal stabiliser. The in-flight loss of the horizontal stabiliser would 

result in reduced control of the aeroplane.

To address this unsafe condition, DGAC France issued AD 1999-060(A), 

requiring repetitive inspections of the fittings and, depending on findings, 

corrective action.

After that AD was issued, SOCATA determined that the cause of the cracks 

was a wrong installation of the fittings during production, inducing stress. 

Consequently, DGAC France issued AD 2000-307(A), partially retaining the 

requirements of DGAC France AD 1999-060(A), which was superseded, and 

required, depending on findings, that the installation of the fittings of in-service

aeroplanes be rectified by introduction of adjusting shims, a modification which 

was introduced as standard on the production line from MSN 162. The 

periodical inspection of the fittings for cracks was still required, pending a better 

understanding of the cause of the cracks.

Since DGAC France AD 2000-307(A) was issued, the results of the further 
EASA AD No.: 2013-0035

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

analysis revealed that the final design (installation of shims on the outboard 

hinge fittings of the horizontal stabiliser) guarantees a service fatigue life which 

exceeds the one established for the TBM 700 during certification. 

Consequently, for aeroplanes with this modification, the repetitive inspections of 

the fittings can be discontinued. However, as the installation of the fittings was 

only required depending on findings, this modification may not have been 

accomplished on all affected aeroplanes.

For the reasons described above, this AD supersedes (and thereby cancels the 

requirements of) DGAC France AD 2000-307(A) and requires installation of 

shims on the outboard hinge fittings of the horizontal stabiliser.

Effective Date: 8 March 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Within 110 flight hours after the effective date of this AD, install shims on the 

outboard hinge fittings of the horizontal stabiliser, in accordance with the 

instructions of SOCATA Service Bulletin (SB) 70-080-55.

Ref. Publications: SOCATA SB SB 70-080-55 Original issue dated July 2000, or Revision 1 dated 

August 2000, or Revision 2 dated August 2012.

The use of later approved revisions of these documents 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 22 January 2013 as PAD 13-019 for consultation 

until 19 February 2013. No comments were received during the 

consultation period.

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive 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, North Perry Airport, 7501 South Airport

Road, Pembroke Pines, Florida 33023, The United States of America.

Tel.: +1 (954) 893 1400 Fax: +1 (954) 964 4141.