AD 65-11-04

65-11-04 PIPER: Amdt. 39-66 Part 39 Federal Register May 14, 1965. Applies to Models PA-24-250, PA-24-260, PA-24-400, and PA-30 Aircraft Equipped with a Mitchell Altimatic II Autopilot.

Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished.

To prevent further jamming of the stabilator control system by the autopilot pitch servo breakaway ball link, accomplish the following:

(a) On autopilots with pitch servos, Mitchell P/N 1X312C, having serial numbers listed on page 2 of Mitchell Service Information Bulletin No. A55, dated March 23, 1965, install pitch servo rack, Mitchell P/N 44A75-1, and spacer, Mitchell P/N 43A284 or Piper P/N 25422, in accordance with the accomplishment instructions in that Service Bulletin, or later FAA-approved revision, or an FAA-approved equivalent. Attach spacer using AN510-10R16 screws, AN960-10 washers, and MS20365-1032C nuts, or FAA-approved equivalents.

(b) Install a fairlead in the fuselage in accordance with the sketch in Piper Service Bulletin No. 224, dated April 7, 1965, or later FAA-approved revision, or an FAA-approved equivalent.

This directive effective May 15, 1965.