Document ID: chunk:federal_register_of_legislation:F2006B08801:body:0:p3
Version: federal_register_of_legislation:F2006B08801
Segment Type: other
Provision Reference: 
Character Range: 5415–8311

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 or splice plates and to the area of skin or splice plates visible through the inspection holes forward and aft of the front and centre spars. Restore the protective finish when the inspection is completed.

                   (c)     If cracking is present:-

                      (i)       At the inspection hole either forward or aft of the front spar but not extending past the inspection hole;

                      (ii)     At the first inspection hole only either forward or aft of the centre spar;

                      (iii)  In the vertical flange of the wrap-around skin or splice plate but not extending more than 3 1/2 inches forward or aft of the front or centre spar; repair the damage before further flight, either temporarily in accordance with Douglas Drawing Nos. 3481664 or 3481679 or permanently in accordance with para. 2(b) of this order.

                   (d)     Temporary repairs in accordance with Douglas Drawing Nos. 3481664 or 3481679 must be replaced with a permanent rework in accordance with para. 2(b) of this Order within the next 2,000 hours time in service after the temporary repairs have been effected.

                   (e)     If cracking is present:-

                      (i)       At the inspection hole either forward or aft of the front spar and extending past the inspection hole;

                      (ii)    At the second or further inspection hole either forward of aft of the centre spar;

                      (iii)  In the vertical flange of the wrap-around skin or splice plate and extending for more than 3 1/2 inches either forward or aft of the front or centre spar; or (iv) Exceeding in any other way the limits specified in para. 5 (c) of this Order, repair the damage before further flight in accordance with para. 2 (b) of this Order.

                   (f)      In cases where damage is present in the lower surface of the centre sections already reworked in accordance with para. 2 (b) of this Order, repairs may be effected by replacing only the damaged component of the joint with a new component of the same drawing number. In all other cases the complete rework specified in para. 2 (b) of this Order must be accomplished.

                 6.    Outer Wing and Centre Section Upper Surface Attachment Angle Doublers - Inspection:

                   (a)     Remove the outer wing panels and strip all paint and other organic finishes from the areas to be inspected and thoroughly clean the bare surfaces.

(b)     With the aid of a lens of not less than a x8 magnification, inspect the outer wing and centre section upper surface attachment angle doublers for cracking along the