AD 65-11-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-24-250 | Airworthiness Directives; Piper Models PA-24-250, PA-24-260, PA-24-400, and PA-30 Aircraft |
| aircraft | Piper Aircraft Inc. | PA-24-260 | Airworthiness Directives; Piper Models PA-24-250, PA-24-260, PA-24-400, and PA-30 Aircraft |
| aircraft | Piper Aircraft Inc. | PA-24-400 | Airworthiness Directives; Piper Models PA-24-250, PA-24-260, PA-24-400, and PA-30 Aircraft |
| aircraft | Piper Aircraft Inc. | PA-30 | Airworthiness Directives; Piper Models PA-24-250, PA-24-260, PA-24-400, and PA-30 Aircraft |
Unsafe Condition
Jamming of the stabilator control system by the autopilot pitch servo breakaway ball link.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Install pitch servo rack Mitchell P/N 44A75-1 and spacer Mitchell P/N 43A284 or Piper P/N 25422 using specified fasteners. Attach spacer with AN510-10R16 screws, AN960-10 washers, and MS20365-1032C nuts or equivalents. Install a fairlead in the fuselage per Piper Service Bulletin No. 224.
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Compliance Time
within the next 25 hours' time in service after the effective date of this AD
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Affected Aircraft
Piper Models PA-24-250, PA-24-260, PA-24-400, and PA-30 Aircraft equipped with Mitchell Altimatic II Autopilot and pitch servos with serial numbers listed in Mitchell Service Information Bulletin No. A55 (dated March 23, 1965).
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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