AD 64-06-06
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-28-150 | Airworthiness Directives; Piper All Model PA-28 Aircraft |
| aircraft | Piper Aircraft Inc. | PA-28-160 | Airworthiness Directives; Piper All Model PA-28 Aircraft |
| aircraft | Piper Aircraft Inc. | PA-28-180 | Airworthiness Directives; Piper All Model PA-28 Aircraft |
| aircraft | Piper Aircraft Inc. | PA-28-235 | Airworthiness Directives; Piper All Model PA-28 Aircraft |
| aircraft | Piper Aircraft Inc. | PA-28S-160 | Airworthiness Directives; Piper All Model PA-28 Aircraft |
| aircraft | Piper Aircraft Inc. | PA-28S-180 | Airworthiness Directives; Piper All Model PA-28 Aircraft |
Unsafe Condition
Cracks in the control wheel hub front and back, and in the area of the retaining pin could lead to failure of the control wheel assembly.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 50 hours' time in service after the effective date, remove the Piper medallion, inspect the control wheel for cracks using dye penetrant and magnifying glass, and sand suspected areas. Repeat inspections at intervals not exceeding 100 hours if cracks are within limits; replace with new P/N 62824 or 62818 within 50 or 10 hours if cracks exceed specified lengths.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 hours' time in service after the effective date of this AD
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Affected Aircraft
Piper Aircraft Inc. PA-28-150, PA-28-160, PA-28-180, PA-28-235, PA-28S-160, PA-28S-180 aircraft, serial numbers 28-1 to 28-868 inclusive, with control wheel assembly P/N 62818 installed.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Control Wheels
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_64-06-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-06-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper All Model PA-28 Aircraft Subject: Control Wheels Status: Current Citation: Federal Register: March 5, 1964 Citation Publish Date: 03/05/1964 Effective Date: 04/06/1964 Make: Piper Aircraft Inc. Model: PA-28-150 | PA-28-160 | PA-28-180 | PA-28-235 | PA-28S-160 | PA-28S-180 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 64-06-06 CITATION: [Federal Register: March 5, 1964] PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 64-06-06 SUBJECT HEADING: Airworthiness Directives; Piper All Model PA-28 Aircraft ACTION: SUMMARY: DATES: Effective April 6, 1964. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. FOOTER:
Document Text
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AD Final Rules - DRS_64-06-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-06-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper All Model PA-28 Aircraft Subject: Control Wheels Status: Current Citation: Federal Register: March 5, 1964 Citation Publish Date: 03/05/1964 Effective Date: 04/06/1964 Make: Piper Aircraft Inc. Model: PA-28-150 | PA-28-160 | PA-28-180 | PA-28-235 | PA-28S-160 | PA-28S-180 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 64-06-06 CITATION: [Federal Register: March 5, 1964] PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 64-06-06 SUBJECT HEADING: Airworthiness Directives; Piper All Model PA-28 Aircraft ACTION: SUMMARY: DATES: Effective April 6, 1964. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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