AD 65-15-05

65-15-05 PIPER: Amdt. 39-105 Part 39 Federal Register July 8, 1965. Applies to Models PA-25, Serial Numbers 25-1 through 25-731, and PA-25-235, Serial Numbers 25-2000 through 25-3565 Aircraft.

Compliance required as indicated.

To prevent loss of the elevator control system as a result of worn clevis bolts, accomplish the following:

(a) For aircraft with less than 250 hours' time in service on the effective date of this AD, comply with (c) before the accumulation of 260 hours' time in service unless already accomplished, and thereafter at intervals not to exceed 250 hours' time in service from the last inspection until modified in accordance with (d).

(b) For aircraft with 250 or more hours' time in service on the effective date of this AD, comply with (c) within the next 10 hours' time in service unless already accomplished within the last 240 hours' time in service, and thereafter at intervals not to exceed 250 hours' time in service from the last inspectionuntil modified in accordance with (d).

(c) Remove the clevis bolt, AN-24-14, from the center hole of the elevator cable link assembly, P/N 81352-15, at the lower end of the control column and inspect it for wear. Replace any clevis bolt that is worn where it contacts the link assembly with a new clevis bolt, AN-24-14.

(d) Replace link assemblies, P/N 81352-15, and spacer, P/N 61402-5, shown on Piper Drawing No. 64374, Revision B, with link assembly, P/N 64748, and bushing, P/N 64749, in accordance with Piper Service Letter No. 455 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.

This directive effective July 18, 1965.