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.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next 25 hours' time in service after the effective date of this AD
AI-generated summary from the source AD text. Verify against the official source before acting.
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).
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Stabilator Control System
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_65-11-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 65-11-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Models PA-24-250, PA-24-260, PA-24-400, and PA-30 Aircraft Subject: Stabilator Control System Status: Current Citation: Federal Register: May 14, 1965 Citation Publish Date: 05/14/1965 Effective Date: 05/15/1965 Make: Piper Aircraft Inc. Model: PA-24-250 | PA-24-260 | PA-24-400 | PA-30 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 65-11-04 CITATION: [Federal Register: May 14, 1965] PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-66 AD NUMBER: 65-11-04 SUBJECT HEADING: Airworthiness Directives; Piper Models PA-24-250, PA-24-260, PA-24-400, and PA-30 Aircraft ACTION: SUMMARY: DATES: Effective May 15, 1965. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_65-11-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 65-11-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Models PA-24-250, PA-24-260, PA-24-400, and PA-30 Aircraft Subject: Stabilator Control System Status: Current Citation: Federal Register: May 14, 1965 Citation Publish Date: 05/14/1965 Effective Date: 05/15/1965 Make: Piper Aircraft Inc. Model: PA-24-250 | PA-24-260 | PA-24-400 | PA-30 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 65-11-04 CITATION: [Federal Register: May 14, 1965] PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-66 AD NUMBER: 65-11-04 SUBJECT HEADING: Airworthiness Directives; Piper Models PA-24-250, PA-24-260, PA-24-400, and PA-30 Aircraft ACTION: SUMMARY: DATES: Effective May 15, 1965. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
2024-14-03
final ruleAirworthiness Directives; Various Airplanes
Unsafe Condition: an un-commanded automatic pitch trim runaway when the autopilot was first engaged, which could result in un-commanded automatic pitch trim runaway and loss of control of the airplane.
2023-09-09 Recurring
final ruleAirworthiness Directives; Various Airplanes, Helicopters, and Engines
Unsafe Condition: Multiple failures of spot-welded, multi-segment v-band couplings at the tailpipe to the turbocharger exhaust housing flange.
2022-03-15
final ruleAirworthiness Directives; Various Airplanes
Unsafe Condition: The displayed fuel quantity can have an error as much as four gallons/fuel tank with the display indicating four gallons with an empty tank. In the context of this event, the end level effect is th...
2015-24-05
final ruleAirworthiness Directives; Piper Aircraft, Inc. Airplanes
Unsafe Condition: Fuel starvation due to the shape of the wing fuel tanks and fuel below a certain level in the tank allowing fuel to move away from the tank outlet during certain maneuvers.