EASA AD No.: 20 13

- 0 035

TE. CAP.0011 0

- 00 3 © 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

. : 20 13

- 0 035

Date: 2 2 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 ope rate an aircraft to which an AD applies, except in accordance with the requ irements 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

F oreign AD: Not applicable

Supersedure: This AD supersedes DGAC France AD 2000

- 307(A) dated 0 9 August 200 0

.



### ATA 55 Stabilizers

– Horizontal Stabilis er O utboard F ittings

– 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, s everal 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 advers ely affect the structural integrity of the h orizontal stabilis er . The in

- flight loss of the h orizontal stabilis er w ould result in reduce d control of the aeroplane.

To address this unsafe condition, DGAC France issued AD 1999

- 060 (A)

, requiring repetitive inspection s 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 iss ued 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 furtherEASA AD No.: 20 13

- 0 035

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved

. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. analysi s revealed that the final design (installation of shim s 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 t he 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 shim s on the outboard hinge fittings of the horizontal stabiliser

.

Effective Date: 8 March 2013

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously:

Within 110 f light h ours after the effective date of this AD, install shim s on the outboard hinge fittings of the horizontal stabiliser, in accordance with the instructions of SOCATA Service Bulletin (SB) 7 0

- 080

- 55.

Ref. Public ations: SOCATA SB SB 70

- 080

- 55 Original issue dated July 2000 , or Revision 1 dated August 2000 , or Revision 2 dated August 20 1 2.
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

- 0 19 for consultation until 1 9 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
t his 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.