Document ID: chunk:federal_register_of_legislation:F2006L03877:body:0:p2
Version: federal_register_of_legislation:F2006L03877
Segment Type: other
Provision Reference: 
Character Range: 2802–5126

accordance with Snow Engineering Co. Service Letter No. 240 dated 30 September 2004.

                   4. For aircraft with serial numbers 602-0337 through 602-0584, repair or replace a cracked spar cap found during any inspection, by accomplishing one of the following:

                  a. For cracks that can be removed by performing the terminating action listed in Requirement 3, accomplish the action specified in Requirement 3.

                  b. For cracks that cannot be removed by performing the terminating action listed in Requirement 3, replace the lower spar caps and associated parts listed in Requirement 5 before continued flight.

                5. For all Model AT-602 aircraft, replace the wing lower spar caps, splice blocks and hardware, wing attach angles and hardware, and install the steel web plate part number 20996-2, if not already installed, in accordance with Snow Engineering Co. Drawing 20776, Sheet 2, Revision A dated 30 August 2004.  This Requirement terminates the inspection requirements of Requirement 2.

             Note:  FAA AD 2006-23-09 Amdt 39-14798 refers.
Compliance:     1. As specified in Requirement 1.

                2.a. Unless the initial inspection is already accomplished, inspect upon the accumulation of 2,000 hours time in service or within 50 hours time in service after 18 January 2007, whichever occurs later.  Inspect thereafter at intervals not to exceed 1,000 hours time in service.

                2.b. Repetitively inspect thereafter at intervals not to exceed 2,000 hours time in service.

                3. As specified in Requirement 3.

                4. Before further flight.

                5. Upon the accumulation of 6,500 hours time in service on the wing spar lower caps or within 50 hours time in service after 18 January 2007, whichever occurs later.
             This Airworthiness Directive becomes effective on 18 January 2007.
Background:  The FAA received reports of fatigue cracking at the wing centre splice joint outboard fastener hole in one of the wing main spar lower caps.  Such cracking, unless detected and corrected, could result in failure of the spar cap and lead to wing separation and loss of control of the aircraft.

David Villiers
Delegate of the Civil Aviation Safety Authority

23 November 2006