AD 64-08-02 ACTIVE

64-08-02 LOCKHEED: Amdt. 711 Part 507 Federal Register April 8, 1964. Applies to All Model 1649A Series Aircraft.

Compliance required as indicated.

(a) Within 350 hours' time in service after the effective date of this AD, unless already accomplished, and within each 5,500 hours' time in service thereafter following the initial inspection, inspect for cracks in the right and left hand wing upper milled skin panel (second plank aft of the front spar) in the area aft of the Nos. 2 and 3 nacelles between W.S. 175 and W.S. 283.5 at the forward and aftmost risers adjacent to the skin lap joints using the ultrasonic shear wave inspection technique described in Lockheed Letter FS/267105-L or an FAA approved equivalent.

(b) Within 1,400 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 1,050 hours' time in service, visually inspect for cracks in the right and left hand wing upper milled skin panel (second plank aft of the frontspar) in the area aft of the Nos. 2 and 3 nacelles between W.S. 175 and W.S. 283.5 at the forward and aft-most risers adjacent to skin lap joints.

(c) Any cracks found during the inspections specified in (a) and (b) shall be repaired in accordance with Lockheed Report 11885 (Structural Repair Manual), Figure 2-10 or an FAA approved equivalent before further flight, except that the aircraft may be ferried in accordance with the provisions of Section 1.76 of CAR Part 1 to a base where the repairs are to be accomplished.

(d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.

(Lockheed Letter FS/267105-L dated August 30, 1963, covers this same subject.)

This directive effective May 11, 1964.