Document ID: chunk:federal_register_of_legislation:F2008L00495:body:0:p2
Version: federal_register_of_legislation:F2008L00495
Segment Type: other
Provision Reference: 
Character Range: 2853–4433

SB J41-57-021 Revision 1, or later EASA approved revision, or repair the wing upper splice plate in accordance with a repair approved by EASA.

                Note 2:  Installing a replacement wing upper splice plate part number 14157126-3PF in accordance with SB J41-57-021 Revision 1, or later EASA approved revision, provides terminating action for the repeat inspections of Requirements 3 or 4, as applicable.

                Note 3:  EASA AD 2007-0056 refers.
Compliance:        1. Within 3 months after 20 February 2008, unless already accomplished.

                   2. Before further flight after the Requirement 1 inspection.

                   3. At intervals not to exceed 12 months.

                   4. At intervals not to exceed 12 months and, within 3 years of the corrosion being discovered, replace the wing upper splice plate in accordance with SB
                   J41-57-021 Revision 1, or later EASA approved revision.

                   5. Before further flight.
                This Airworthiness Directive becomes effective on 20 February 2008.
Background:     A report was received of corrosion of the wing upper splice plate detected during a routine four year structural inspection of an in-service aircraft.  Investigation revealed that the susceptibility of the wing upper splice plate to corrosion was linked to the material conductivity.  Revision 1 of SB J41-57-020 extends applicability to include aircraft construction numbers 41102 through 41104.

David Villiers
Delegate of the Civil Aviation Safety Authority

15 February 2008