Document ID: chunk:federal_register_of_legislation:F2006B04237:body:0:p1
Version: federal_register_of_legislation:F2006B04237
Segment Type: other
Provision Reference: 
Character Range: 4–2923

Beechcraft 90 and 65-90 (King Air) Series Aeroplanes

AIRWORTHINESS DIRECTIVE

    For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BEECH 90/48 Amdt 1 and issues the following AD under subregulation 39.1 (1) of CAR 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.

    AD/BEECH 90/48
    Amdt 2

    Wing Spar Fitting Fatigue - Inspection 11/2000

               Applicability: All model 65-90, 65-A90, B90, C90, and E90 aircraft, except serial nos. LJ-1085, and LJ 1088 and subsequent. All model F90 aircraft except serial nos. LA-226 and subsequent.

                 Requirement: 1. Remove the wing main spar lower attachment bolts in accordance with the manufacturer's instructions. Strip all paint from the "bathtub" portion of the four outer wing to centre section main spar lower attachment fittings.

2.    For all except F90: Perform a fluorescent liquid penetrant inspection of all four fittings in accordance with the Beechcraft Structural Inspection and Repair Manual (SIRM) P/N 98-39006B3 as revised May 28 1999, Chapter 57-13-01 Chart 201 Index Nos. 1 and 10, or 57-13-02 Chart 201 Index Nos. 1 and 5, as applicable to individual aeroplanes. When inspecting the "bathtub" portion of the fittings, pay particular attention to the bolt counterbore and fillet radius. As an alternative, this inspection may be performed using an eddy current (pencil probe) procedure as detailed in Chapter 20-00-00 of the SIRM in which case paint strip is not required.

3.    For model F90 aircraft only: Perform a fluorescent liquid penetrant inspection of all four fittings in accordance with the Beechcraft Structural Inspection and Repair Manual (SIRM) P/N 98-39006B3 as revised May 28 1999, Chapter 57-14-01 Chart 201 Index No. 1. Pay particular attention to the bolt counterbore and fillet radius in the "bathtub" portion of the centre wing fitting, and the radius at the end of the barrel nut recess in the outer wing fitting. As an alternative, this inspection may be performed using the eddy current procedure specified in 4 below.

4.    For model F90 aircraft only: Perform an eddy current inspection of all four fittings in accordance with the Beechcraft Structural Inspection and Repair Manual (SIRM) P/N 98-39006B3 as revised May 28 1999, Chapter 57-14-01 Chart 201 Index No. 2. Paint strip is not required for eddy current inspection.

               In accordance with the SIRM, should a fatigue crack be