Document ID: chunk:federal_register_of_legislation:F2006L01338:body:0:p2
Version: federal_register_of_legislation:F2006L01338
Segment Type: other
Provision Reference: 
Character Range: 2623–5407

originate, enlarge the hole to 1/4-inch, and inspect the wing lower skin around the hole.  If no wing skin crack is detected, install a close tolerance -8 rivet or 1/4-inch bolt.  If cracks are detected, accomplish Requirements 4, 5, or 6, as applicable.

      4. For aircraft with wing skin cracks less than 6-inches in length, unless already repaired in accordance with Requirements 6 or 7, modify and inspect as follows:

        a. For wing skin cracks less than 2-inches long, before further flight, stop drill each end of the crack with a 0.50-inch diameter drill.  Repetitively inspect thereafter in accordance with Requirement 1, 2, or 3, as applicable.  If during any inspection the crack is found to have progressed beyond a stop drill hole, but the total length remains less than 2-inches, the crack may be stop drilled and the 100-hour interval inspections continued.  When a crack reaches the 2-inch limit, the provisions of Requirement 4.b. apply.

        b. For wing cracks between 2 and 3-inches in length, before further flight, stop drill each end of the crack with a 0.50-inch diameter drill and revise the airspeed limitations for the aircraft by reducing the never exceed speed (Vne) to 243 knots and the normal operating speed (Vno) to 217 knots and install a placard in the cockpit, in full view of the pilot stating the reduced speeds.  An internal visual repetitive inspection of the stop drilled crack is to be accomplished in accordance with Requirements 1, 2, or 3, as applicable.  If during any inspection the crack is found to have progressed beyond a stop drill hole, but the total length remains less than 3-inches, the crack may be stop drilled and the 100-hour interval inspections and speed restrictions continued.  When a crack reaches the 3-inch limit, the provisions of Requirement 4.c. apply.

        c. For wing skin cracks between 3 and 6-inches in length, before further flight, repair the wing lower skin by installing internal reinforcement plates inboard of Station 8 in accordance with Convair Service Engineering Report No. 6820-340-47B/440-47B, dated 15 January 1963, and revise the airspeed limitations for the aircraft by reducing the never exceed speed (Vne) to 243 knots and the normal operating speed (Vno) to 217 knots and install a placard in the cockpit, in full view of the pilot stating the reduced speeds.  An internal visual repetitive inspection is to be accomplished in accordance with Requirements 1, 2, or 3, as applicable.  If during any inspection further cracking is detected, but in no case more than 1,000 hours time in service from above mentioned temporary repair, repair the aircraft in accordance with Requirement 6.

      5. An aircraft with wing skin cracks less than 2-inches in length, including