AD 74-10-09

74-10-09 BOEING: Amendment 39-1838 as amended by Amendment 39-2825. Applies to Boeing Model 707-100 series, -100B series and -200 series airplanes certificated in all categories. Compliance required as indicated. To detect cracks in the upper wing splice plate and upper rib cap at wing station 360, accomplish the following: Unless X-Ray or low frequency eddy current inspected within the last 300 flights, X-Ray or low frequency eddy current inspect the upper wing surface splice plate and rib cap at wing station 360 within the next 25 flights after the effective date of this AD, on airplanes with more than 24,000 flights, or within the next 50 flights after the effective date of this AD, on airplanes with more than 17,000 flights in accordance with instructions in Boeing Alert Service Bulletin No. 3160 dated April 19, 1974, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Northwest Region. If cracks are found, repair prior to further flight in accordance with Part VII or VIII or install external doubler in accordance with Part IX of Boeing Service Bulletin No. 2576, Revision 2, or later approved revisions or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. The Manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents may obtain copies upon request to The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, Boeing Field, Seattle, Washington.

Amendment 39-1838 became effective on May 10, 1974. This amendment 39-2825 becomes effective February 21, 1977.