Document ID: chunk:federal_register_of_legislation:F2005L03899:body:0:p2
Version: federal_register_of_legislation:F2005L03899
Segment Type: other
Provision Reference: 
Character Range: 2970–4711

report all findings to the Type Certificate Holder of the aircraft and the MLG manufacturer.

             Note 3:  CAA-NL AD NL-2005-012 refers.
Compliance:     1. Before the next flight after 19 January 2006.

                2. Within 2,000 flight cycles after the accomplishment of Messier-Dowty SB F100-32-103 (Ref. Fokker SBF100-32-133) or Messier-Dowty SB F100-32-105 (Ref. Fokker SBF100-32-139), or within the next 4 calendar months, whichever occurs later after 19 January 2006.

                3. At intervals not to exceed 2,000 flight cycles.

                4. Before further flight.

                5. Within the next 50 flight cycles thereafter.
             This Amendment becomes effective on 19 January 2006.
Background:  A failure of the sliding member of a main landing gear occurred during a terminal departure push-back, following inadvertent brake application.  Investigation of the fractured surface revealed overload, initiated by a fatigue crack.  Inspection of other aircraft revealed cracking in the same area.

             Amendment 1 required a second one-time inspection in response to the results of the previous inspection required by this Directive; in order to establish fleet safety.

             Amendment 2 is issued in response to a new CAA-NL AD, which was prompted by the results of further inspections that have identified the need for a repetitive inspection on the MLG Sliding Member to establish fleet safety.  For this reason, this Directive requires repetitive magnetic particle inspections of all aircraft equipped with Dowty/Messier-Dowty Main Landing Gear units and replacement of cracked parts.

David Villiers
Delegate of the Civil Aviation Safety Authority

28 November 2005