AD 67-14-06

67-14-06 MARTIN: Amdt. 39-406 Part 39 Federal Register April 28, 1967. Applies to Models 202, 202A, and 404 Series Airplanes.

(a) Within the next 15 hours' time in service after the effective date of this AD unless already accomplished within the last 185 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection, inspect the following areas in both outer wing panel front spars located at 25% of the wing chord for cracks using X-ray or dye penetrant with a glass of at least 10 power, or an FAA-approved equivalent inspection.

(1) The lower spar cap in a region 3 inches long from the outer panel closing rib outboard.

(2) The spar web inboard of the outer panel closing rib between the rib and the splice bolts.

(3) The vertical angle that attaches this web to the outer panel closing rib.

(b) If a crack is found, before further flight, replace the cracked part with a part of the same part number that has been inspected in accordance with (a) and found free of cracks or with an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.

(c) Equivalent inspections may be approved by an FAA maintenance inspector.

(d) All fuel must be drained before X-ray inspection because of lead in the gasoline.

(e) Upon request of the operator, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region may increase the compliance times specified in this AD if the request contains substantiating data submitted through an FAA maintenance inspector to justify the increase for that operator.

This supersedes AD 59-26-05.

This directive effective upon publication in the Federal Register for all person except those to whom it was made effective by telegram dated April 20, 1967.