59-06-01 AERO COMMANDER: Applies to Model 500, Serial Numbers 618 Through 724 Except 700 and 718.
Compliance required as indicated.
I. Inspection.
Within the next five hours of flight unless previously accomplished, inspect each elevator front spar in the area of the outboard hinge brackets for cracks. The elevator outboard hinge brackets must be removed for this inspection. If no cracks are found, the horizontal stabilizer must be modified as outlined in Item II. If any cracks are found in the elevator front spar, the spar must be reworked as outlined in Item III and the horizontal stabilizer must be modified as outlined in Item II.
II. Modification.
The horizontal stabilizer will be modified by installation of lead weights on the horizontal stabilizer front spars by incorporating Aero Design Company Kit No. Service Bulletin 57 or an equivalent approved modification. Modification of aircraft without elevator spar cracks will be accomplished within 25 flight hours, but not later than May 1, 1959. Modification of aircraft with elevator spar cracks will be accomplished immediately.
III. Rework.
If cracks are present, contact the Service Department, Aero Design and Engineering Company, Post Office Box 118, Bethany, Oklahoma, for rework of the elevator front spars.
(Modification instructions are contained in Aero Design Service Bulletin No. 57. Rework of the elevator front spars is covered by Aero Design Salvage E.O. No. 5440000.)
This Airworthiness Directive supersedes the FAA telegraphic instruction of March 12, 1959.