Document ID: chunk:federal_register_of_legislation:F2006B08801:body:0:p2
Version: federal_register_of_legislation:F2006B08801
Segment Type: other
Provision Reference: 
Character Range: 2914–5653

in para. 3(a).

                  (ii)     Remove each 10th attach angle bolt as a sample and inspect removed bolts for corrosion and general condition. Identify removed bolts before reinstallation and select different samples at each subsequent inspection.

                  (iii)  Check that the attach angle bolts and spar cap bolts are tightened to the correct torque values.

(c)     Attachment angles which are cracked or which are corroded beyond the limitations specified in Douglas SB No. 262 Re-issue No. 2, 6 Dec. 1963, shall be replaced before further flight.

(d)     Loose or damaged attachment angle bolts, together with at least the next two bolts on each side of the defective item, shall be replaced with new bolts before further flight, and at the same time a torque check shall be made of all bolts in the affected joint.

(e)     Loose or damaged spar cap bolts shall be replaced with new items or re- torqued as necessary before further flight. When bolts are tightened a check shall be made to ensure that the countersunk head on each bolt makes at least a 75 per cent blue contact with the countersink in the attachment angle and that the bolt holes in the vertical flanges of the wing and centre section attachment angles are in proper alignment.

             4.    Outer Wing Panel Lower Surface Attachment Angle Doublers and Skin - Inspection:

(a)     Remove the outer wing panels and strip all paint and organic finishes from the area to be inspected and for a distance of at least 6 inches outboard of the wing joint and thoroughly clean the bare surfaces.

(b)     With the aid of a lens of not less than a x8 magnification inspect the lower surface skin and doublers adjacent to the wing joint for cracking, paying particular attention to the vertical flange of the doublers. Restore the protective finish when the inspection is completed.

(c)     Cracked doublers shall be replaced with new items, preferably of the heavy gauge type referred to in para. 1 of this Order, before further flight. Cracked skin shall be renewed or repaired before further flight in accordance with a scheme approved by the Secretary.

             5.    Centre Section Lower Surface Skin Doublers - Inspection:

(a)     Remove the outer wing panels and strip all paint and other organic finishes from the area to be inspected and for a distance of at least 6 inches inboard of the wing joint and thoroughly clean the bare surfaces.

                   (b)     With the aid of a lens of not less than a x8 magnification, inspect the lower surface doublers, skin and, if fitted, splice plates for cracks in the area adjacent to the wing joint. Pay particular attention to the radius and vertical flange of the wrap-around skin