AD 69-19-06

69-19-06 GENERAL DYNAMICS: Amdt. 39-842. Applies to all Model 22 Aircraft equipped with axle beam P/N 9729-68-1 and Model 22M Aircraft equipped with axle beam P/N 1057-68-1.

Compliance required within the next 2000 hours' time in service after the effective date of this AD or before the accumulation of 9000 hours' total time in service, whichever occurs later, unless already accomplished.

Several failures of the main landing gear axle beam have been attributed to cracks originating near the center jack pad on the beam lower surface. The crack then progresses upward until complete failure of the beam occurs at a point above the axle beam pivot pin. The initial crack in the beam develops due to stress corrosion or hydrogen embrittlement. To prevent further failures of this nature, accomplish the following or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(a) Inspect and rework each Model 22 Aircraft axle beam assembly P/N 9729-68-1 in accordance with General Dynamics/Convair 880 Service Bulletin Number 32-87, dated February 7, 1966, (or later FAA approved revision), and each Model 22M Aircraft axle beam assembly P/N 1057-68-1 in accordance with General Dynamics/Convair 880M Service Bulletin Number 32-56, dated February 7, 1966, (or later FAA approved revision).

(b) Removal of beam material extending below .006 inch depth from the original beam surface will require individual evaluation by the Chief, Aircraft Engineering Division, FAA Western Region.

This amendment becomes effective October 18, 1969.