## 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 ofan 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 TA (formerly EADS SOCATA) 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 tofatigue cracks in the shock strut cylinder ofthe MLG, which could result in a collapsed MLG during take-off or landing runs, and possibly reduce the structu ral integrity of the aeroplane. To address this unsafe condition , EASA issued AD 2006-0085 to require repetitive special detail inspections (SDI) for cracks ofthe 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 ofa reinforced MLG on the right hand (RH) side and left hand (LH) side as an optional terminating action for the repetitive SOl required bythis 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. TE.CAP.OOll0-004 ©European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled
. Confirm revision status through the EASA · Int ernet/lntranet.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 ofthis AD, as applicable, and, thereafter, at intervals not to exceed 

### 240 landings (LOG), accomplish a SDI ofthe 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 ofthis AD] since original issue ofthis 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 ) ofthis AD, any crack is suspected or confirmed, before next flight, remove the concerned MLG leg and confirm the presence ofthe 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 i nspection or fluorescent penetrant inspection as required by paragraph 

### (2) ofthis 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 ofthis AD, provided that, since aeroplane first flight, no MLG shock strut cyl inder 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 

### 068 1 62-1 (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) ofthis 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 ofthese documents is acceptable for compliance with the requirements ofthis AD.

n:.CAP.OOU0-004 ©European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-I nternet/Intranet.EASAAD No.: 2006-0085R2 Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD

. 2. The orig inal issue of this AD was posted on 10February 2006 as PAD 06-029 for consultation until10 March 2006. No comments were received during the consultation period. 3. Enquiries regar ding 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 ofthe 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. orfor the U.S.A SOCATA NORTH AMERICA, North Perry Airport, 750 1 South Airport Road, Pembroke Pines, Florida 33023, The United States ofAmerica

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

TE.CAP

.O Oll0-004 ©European Aviation Safety Agency. All rights reserved

. Proprietary document. Copies are not controlled. Confirm revision status th rough the EASA-Internet/Intranet. 3/3