Document ID: chunk:federal_register_of_legislation:F2007L00122:body:0:p2
Version: federal_register_of_legislation:F2007L00122
Segment Type: other
Provision Reference: 
Character Range: 3131–6277

AD 2006-24-10 Appendix 1 and Appendix 2 may be obtained from the FAA Internet web site www.airweb.faa.gov/rgl or by request to the Authority Internet address airworthiness.directives@casa.gov.au

                   5. Model AT-502B aircraft, serial number 0643, serial number 0655 and subsequent, and all other aircraft that have been modified with replacement spar caps, part number part numbers 21058-1 and 21058-2, are not eligible to have STC SA00490LA installed without additional fatigue data being provided to the FAA.

                   6. Modify the applicable aircraft records as follows to show the reduced safe life for the wing lower spar cap by using the information contained in Requirement 1 and Requirement 4 of this Directive, and FAA AD 2006-24-10 Appendix 1, as applicable:

                   Incorporate the following into the Aircraft Logbook, "In accordance with AD/AT/21 Amdt 3, (AD/AT/21 Amdt 2 or AD/AT/20 Amdt 4) the wing lower spar cap is life limited to ___".

                7. Accomplish the actual replacement /modification in accordance with Snow Engineering Drawing No. 21050, Snow Engineering Service Letter No. 197 or No. 205, both revised 26 March 2001, as applicable.

                   8. To extend the safe life of the wing lower spar cap for certain aircraft, accomplish an eddy current inspection and modify the wing lower spar cap in accordance with the procedures included as part of the Alternative Method Of Compliance (AMOC) in Appendix 2 to FAA AD 2006-24-10.

                   9. For Model AT-502B aircraft, serial numbers 502B-0643 and 502B-0655 through 502B-0692:  Cold work the left hand and right hand two outboard wing centre splice block bolt holes (four total) in the lower spar cap, in accordance with Snow Engineering Service Letter No. 244, dated 25 April 2005.

             For all affected aircraft:  Aircraft that have the two-part modification accomplished in accordance with the applicable Snow Engineering Service Letters, but have over-sized outboard bolt holes at the splice block, must obtain an AMOC from the FAA to determine applicable inspection intervals.

             AMOCs approved for FAA AD 2001-10-04 and/or AD 2000-14-51 are not considered approved for AD 2006-24-10 (this Directive).

             AMOCs approved for AD 2001-10-04 R1, AD 2002-11-03, AD 2002-11-05, AD 2002-11-05 R1, or AD 2002-26-05 are considered approved for AD 2006-24-10 (this Directive).

             Note 2:  FAA AD 2006-24-10 Amdt 39-14839 refers.
Compliance:  Requirements 1, 2, 3 & 4:  As specified in Requirements 1, 2, 3 & 4.

                        Requirement 5: As specified in Requirement 5.

                        Requirement 6: For aircraft previously affected by FAA AD 2002-26-05, within 10 hours time in service after 20 March 2003.

                        For aircraft not previously affected by FAA AD 2002-26-05, within 10 hours time in service after 15 February 2007, unless already accomplished.

                        Requirement 7: Upon reaching the safe life specified in Requirement 1 or as re-calculated in Requirement 4, as applicable.  If,