AD 64-06-06

64-06-06 PIPER: Amdt. 696 Part 507 Federal Register March 5, 1964. Applies to All Model PA-28 Aircraft, Serial Numbers 28-1 to 28-868 Inclusive, with Control Wheel Assembly, P/N 62818, Installed.

Compliance required as indicated.

To preclude failure of the control wheel, accomplish the following:

(a) Within 50 hours' time in service after the effective date of this AD:

(1) Remove the Piper medallion from the face of the control wheel.

(2) Inspect the control wheel for cracks in the hub front and back, and in the area of the retaining pin, using dye penetrant in conjunction with at least a 5-power magnifying glass, or FAA approved equivalent inspection method.

(3) Sand any suspected area with crocus cloth or equivalent to remove any mold marks and reinspect as in (2).

(b) If no cracks are found, or if the total cumulative length of all cracks found does not exceed 3/16 inch, repeat the inspection in (a) at intervals not exceeding 100 hours'time in service.

(c) If the total cumulative length of all cracks found exceeds 3/16 inch, but does not exceed 3/8 inch, replace the assembly with a new control wheel assembly, P/N 62824 or P/N 62818, within the next 50 hours' time in service.

(d) If the total cumulative length of all cracks found exceeds 3/8 inch, replace the assembly, as in (c), within 10 hours' time in service.

(e) When a new control wheel assembly, P/N 62824, is installed, this AD is no longer applicable.

(f) When a new control wheel assembly, P/N 62818, is installed, accomplish the inspections per paragraph (a) at intervals of 100 hours' time in service.

(Piper Service Letter No. 396 on the Model PA-28 pertains to this same subject.)

This directive effective April 6, 1964.