Document ID: chunk:federal_register_of_legislation:F2006B04123:body:0:p1
Version: federal_register_of_legislation:F2006B04123
Segment Type: other
Provision Reference: 
Character Range: 4–2974

Beechcraft 65 and 70 (Queen 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 65/22 Amdt 3 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 65/22
    Amdt 4

   Wing Spar and Lower Attachment Fittings 11/2000

    Applicability: All models.

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

                 2. 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 57-11-00 for models 65, 70 & 80, and Chapter 57-12-00 for the model 88, Chart 201, Index Nos. 1 and 10 (Note: the model designations used in the SIRM are the manufacturer's popular or marketing designations). 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 accordance with the SIRM, if a fitting fatigue crack is found, the complete outer wing main spar lower cap assembly must be replaced in before further flight.

               Note 1: The SIRM Chapter 20-00-00 "Warning" regarding not removing paint should be disregarded. To prevent corrosion, some form of protective treatment, such as a standard zinc chromate primer, should be applied between inspections, to surfaces from which the paint has been removed.

               Note 2: Solvent removers should be used wherever possible. If the use of other paint strippers is unavoidable, the complete removal of residue must be ensured before inspection. In either case, the use of mechanical or abrasive means of paint removal must be avoided.

               Note 3: It is recommended that the penetrant be applied to the counterbore radius using a fine artist's paint brush. This will simplify penetrant removal and minimise false indications. Care should be taken to ensure full coverage of the fillet radius and a similar distance (at least 5 mm) into the cylindrical portion of the counterbore, in particular on