71-09-06: Cracks In Main Gear Gland Nut

71-09-06 MARTIN AIRCRAFT: Amdt. 39-1200. Applies to Models 202, 202A and 404 airplanes certificated in all categories. Compliance required as indicated. To detect cracks or corrosion in the main landing gear aluminum gland nut, P/N 202SD81548, (Menasco Drawing No. 511034), accomplish the following: (a) Within the next 25 hours in service, after the effective date of this AD, unless already accomplished within the last 475 hours in service, and thereafter at intervals not to exceed 500 hours in service from the last inspection, comply with (b). (b) Unscrew the left and right main landing gear aluminum gland nut, P/N 202SD81548, so that all threads are visible. Inspect the nut for evidence of cracks or corrosion, using dye penetrant in conjunction with at least a 10-power glass or an equivalent inspection. Cracked or corroded parts must be replaced with an unused part or an equivalent before further flight, except that the airplane may be flown in accordance withFAR 21.197 to a base where the repair can be performed. (c) The repetitive inspection specified in (a) may be discontinued when the aluminum gland nut is replaced by a part made of steel, as per ECD 32590 to Menasco Drawing No. 511034, change L, dated 8 March 1961, or replaced by a steel gland nut in accordance with Eastern Air Lines Drawing No. 204-8125, or with an equivalent part. (d) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering & Manufacturing Branch, FAA, Eastern Region, may adjust the initial inspection and the repetitive inspection interval specified in this AD. Equivalent parts and inspections must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective May 4, 1971.