AD/TBM 700/46 Main Landing Gear Shock Strut Cylinder (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Aerospatiale (Socata) TBM 700 Series Aeroplanes

AD/TBM 700/46 Main Landing Gear Shock Strut Cylinder 4/2007

Applicability:

Model TBM 700 A, B, C1, C2 and N aircraft, all serial numbers.

Note:  “TBM 850” is the trade name of Model TBM 700N aircraft.

Requirement:

Inspect in accordance with the Accomplishment Instructions of EADS Socata Service Bulletin No. 70-130 original issue, or later EASA approved revision.

If any cracks are detected during any inspection, before further flight, remove the affected main landing gear leg and confirm the presence of the crack with a dye penetrant or fluorescent penetrant inspection.  If cracking is confirmed, before further flight, contact EADS Socata to coordinate the repair/replacement and then conform to further instructions required by the manufacturer.

Note:  EASA AD 2006-0085 refers.

Compliance:

a.    For aircraft with a main landing gear forging body with more than 1,750 landings since new; inspect within 100 landings after 12 April 2007, unless already accomplished.  If no cracking is detected, inspect thereafter at intervals not to exceed 175 landings.

b.    For aircraft with a main landing gear forging body with more than 3,500 landings since new; inspect within 25 landings after 12 April 2007, unless already accomplished.  If no cracking is detected, inspect thereafter at intervals not to exceed 175 landings.

This Airworthiness Directive becomes effective on 12 April 2007.

Background:

The manufacturer received reports of fatigue cracks that were detected on main landing gear forging bodies during overhaul.

David Villiers
Delegate of the Civil Aviation Safety Authority

28 February 2007