Airworthiness Directive · Amendment 39-18243 · Landing gear
SOCATA Airplanes
This AD applies to SOCATA Model TBM 700 airplanes, serial numbers 1 through 638 and 687, that:
(1) are not equipped with a left-hand main landing gear (MLG) body part number (P/N) D68161 or D68161-1 and a right-hand MLG body P/N D68162 or D68162-1; and
(2) are certificated in any category.
We are superseding Airworthiness Directive (AD) 2007-04-13 for certain SOCATA Model TBM 700 airplaness (type certificate previously held by EADS SOCATA). This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks found on the main landing gear cylinders. We are issuing this AD to require actions to address the unsafe condition on these products.
Unless already done, do the actions in paragraphs (f)(1), (f)(2), and (h) of this AD:
(1) For MLG with forging body that were either at or under 1,750 landings as of March 23, 2007 (the effective date of (AD 2007-04-13): Upon or before accumulating 1,750 landings on the MLG with forging body since new or within the next 100 landings after September 29, 2015 (the effective date of this AD), whichever occurs later, inspect the forging body for cracks. Do the inspection following the Accomplishment Instructions of EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014.
(2) If no cracks are detected during the inspection required in paragraph (f)(1) of this AD, repetitively thereafter inspect at intervals not to exceed 240 landings until a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014, is installed.
Unless already done, do the actions in paragraphs (g)(1), (g)(2), and (h) of this AD, including all subparagraphs:
(1) As of March 23, 2007 (the effective date retained from AD 2007-04-13), for MLG with forging body totaling more than 1,750 landings but less than 3,501 landings since new:
(i) Inspect the forging body for cracks within 100 landings after March 23, 2007 (the effective date retained from AD 2007-04-13), following the Accomplishment Instructions of EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014.
(ii) If no cracks are detected during the inspection required in paragraph (g)(1)(i) of this AD, repetitively thereafter inspect at intervals not to exceed 240 landings until a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014, is installed.
(2) As of March 23, 2007 (the effective date retained from AD 2007-04-13), for MLG with forging body totaling more than 3,500 landings since new:
(i) Inspect the forging body for cracks within 25 landings after March 23, 2007 (the effective date retained from AD 2007-04-13), following the Accomplishment Instructions of EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014.
(ii) If no cracks are detected during the inspection required in paragraph (g)(2)(i) of this AD, repetitively thereafter inspect at intervals not to exceed 240 landings until a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014, is installed.
If any cracks are detected during any inspection required in paragraphs (f)(1) through (g)(2) of this AD, including all subparagraphs:
(1) Before further flight, remove the affected landing gear leg and confirm the presence of the crack with dye penetrant inspection or fluorescent penetrant inspection.
(2) If the crack is confirmed, before further flight, contact SOCATA at the address in paragraph (l)(5) of this AD to coordinate the FAA-approved landing gear repair/replacement and implement any FAA-approved repair/replacement instructions obtained from SOCATA, or replace the cracked landing gear with a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014. This replacement terminates the repetitive inspections required by this AD.
The compliance times of this AD are presented in landings instead of hours time-in-service (TIS). If the number of landings is unknown, hours TIS may be used by dividing the number of hours TIS by 1.35.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
