EASA 

EASA AD No.: 2006-0085R2 

AIRWORTHINESS DIRECTIVE 

AD No.: 2006-00~5R2 

Date: 16 January 2015 

Note: This Airworthiness Directive {AD) is issued by EASA, acting in accordance with Regulation 

(EC) No 21612008 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 EU 1321/2014 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 [EU 

1321/2014 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: Type/Model designation(s): 

SOCATA 

TCDS Number: 

Foreign AD: 

Revision: 

ATA32 

Manufacturer(s): 

Applicability: 

Reason: 

TBM 700 aeroplanes 

EASA.A.010 

Not applicable 

This AD revises EASA AD 2006-0085R1 dated 22 December 2014. 

Landing Gear- Main Landing Gear Shock Strut CylinderInspection I Replacement I Modification 

SOCA T A (formerly EADS SOCA T A) 

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

638, and MSN 687. 

Cracks on several main landing gear (MLG) cylinders have been reported in 

service. 

This condition, if not to detected and corrected, could lead to fatigue cracks in 

the shock strut cylinder of the MLG, which could result in a collapsed MLG 

during take-off or landing runs, and possibly reduce the structural integrity of 

the aeroplane. 

To address this unsafe condition, EASA issued AD 2006-0085 to require 

repetitive special detail inspections (SDI) for cracks of the MLG shock strut 

cylinder and, depending on findings, relevant investigative and corrective 

actions. 

After that AD was issued, SOCAT A performed an analysis to demonstrate that 

the inspection interval could be extended, and developed a reinforced MLG 

less prone to fatigue, which is embodied in production through SOCATA 

modification (MOD) 70-0190-32 and can be introduced in service through 

SOCAT A Service Bulletin (SB) 70-130-32 at Revision 03. 

Prompted by these developments, EASA issued AD 2006-0085R1 to increase 

the inspection interval and to introduce the installation of a reinforced MLG on 

the right hand (RH) side and left hand (LH) side as an optional terminating 

action for the repetitive SOl required by this AD. 

Since that AD was issued, it was found that aeroplanes MSN 639 to 683 

(inclusive) are not affected by this AD. The applicability has therefore been 

revised to remove those MSN. 

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EASA AD No.: 2006-0085R2 

Effective Date: Revision 2: 30 January 2015 

Revision 1: 05 January 2015 

Original issue: 26 April 2006 

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

and Compliance (1) For aeroplanes equipped with a MLG with forging body, initially within the 

Time(s): compliance time specified in Table 1 of this AD, as applicable, and, 

thereafter, at intervals not to exceed 240 landings (LOG), accomplish a 

SDI of the MLG forging body in accordance with the instructions of 

SOCATA SB 70-130-32. 

Table 1 -Initial inspection 

LOG accumulated by the MLG on Compliance time after 26 April 

26 April 2006 [the effective date of 2006 [the effective date of the 

the original issue of this AD] since original issue of this AD] 

first installation on an aeroplane 

3 500 LOG or more Within 25 LOG 

1 750 LOG or more, but less than Within 100 LOG 3 500 LOG 

Less than 1 750 LOG Before exceeding 1 850 LOG since 

first installation on an aeroplane 

(2) If, during any SOl as required by paragraph (1 ) of this AD, any crack is 

suspected or confirmed, before next flight, remove the concerned MLG leg 

and confirm the presence of the crack with dye penetrant inspection or 

fluorescent penetrant inspection in accordance with the instructions of 

SOCATA SB 70-130-32. 

(3) If, during the dye penetrant inspection or fluorescent penetrant inspection 

as required by paragraph (2) of this AD, any crack is confirmed, before next 

flight, contact SOCAT A for approved instructions (repair or replacement) 

and, within the compliance time specified in those instructions, accomplish 

the repair or replacement, as applicable, accordingly. 

(4) Aeroplanes on which SOCATA MOD 70-0190-32 has been embodied in 

production are not affected by the requirements of this AD, provided that, 

since aeroplane first flight, no MLG shock strut cylinder other than part 

number (PIN) 068161 or 068161-1 (LH) and P/N 068162 or 068162-1 

(RH), has been installed on that aeroplane. 

(5) Modification of an aeroplane in service, by installation of reinforced MLG 

shock strut cylinder P/N 068161 or 068161-1 (LH) and P/N 068162 or 

068162-1 (RH) in accordance with the instructions of SOCATA 

Component Maintenance Manuals (CMM) 32-11-01 and 32-11-02 or 

SOCATA SB 70-130-32 Revision 03 constitutes terminating action for 

the repetitive SOl as required by paragraphs (1) and (2) of this AD. 

Ref. Publications: SOCATA SB 70-130-32 original issue dated January 2006, or Revision 1 dated 

November 2013, or Revision 2 dated June 2014, or Revision 3 dated October 

2014. 

SOCATA Component Maintenance Manuals (CMM) 32-11-01 Revision 4 dated 

October 2014 and 32-11 -02 Revision 3 dated October 2014. 

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD. 

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EASAAD No.: 2006-0085R2 

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

Alternative Methods of Compliance for this AD. 

2. The original issue of this AD was posted on 10 February 2006 as 

PAD 06-029 for consultation until10 March 2006. 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, North Perry Airport, 7501 South Airport 

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

Tel.: +1 (954) 8931400 Fax: +1 (954) 964 4141. 

TE.CAP.OOll0-004 ©European Aviation Safety Agency. All rights reserved. 

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

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