AD 57-21-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-23 | Airworthiness Directives; Piper All Model PA-23 Aircraft |
Unsafe Condition
The use of a flat head pin for the rudder trim tab control rod attachment may fail, leading to loss of rudder trim control.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the attachment of the rudder trim tab control rod to the rudder trim tab. Replace any flat head pin with an AN 23-10 clevis bolt, AN 960-10L washer, AN 320-3 nut, and AN 380-2-2 cotter pin.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
next regular inspection period but not to exceed 100 hours
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Piper Aircraft Inc. PA-23 aircraft, all serial numbers.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Rudder Trim Tab Pin
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_57-21-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 57-21-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper All Model PA-23 Aircraft Subject: Rudder Trim Tab Pin Status: Current Citation: This information is not available. Citation Publish Date: 01/23/1958 Effective Date: Make: Piper Aircraft Inc. Model: PA-23 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part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 unable to find issue date AIRWORTHINESS DIRECTIVES FINAL RULES: 57-21-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 57-21-01 SUBJECT HEADING: Airworthiness Directives; Piper All Model PA-23 Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 57-21-01 PIPER: Applies to All Model PA-23 Aircraft. Compliance required at next regular inspection period but not to exceed 100 hours. Inspect the attachment of the rudder trim tab control rod to the rudder trim tab. If a flat head pin has been installed it must be replaced by an AN 23-10 clevis bolt and AN 960-10L washer, secured with an AN 320-3 nut and AN 380-2-2 cotter pin. (Piper Service Bulletin No. 159 covers this subject.) FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_57-21-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 57-21-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper All Model PA-23 Aircraft Subject: Rudder Trim Tab Pin Status: Current Citation: This information is not available. Citation Publish Date: 01/23/1958 Effective Date: Make: Piper Aircraft Inc. Model: PA-23 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 unable to find issue date AIRWORTHINESS DIRECTIVES FINAL RULES: 57-21-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 57-21-01 SUBJECT HEADING: Airworthiness Directives; Piper All Model PA-23 Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 57-21-01 PIPER: Applies to All Model PA-23 Aircraft. Compliance required at next regular inspection period but not to exceed 100 hours. Inspect the attachment of the rudder trim tab control rod to the rudder trim tab. If a flat head pin has been installed it must be replaced by an AN 23-10 clevis bolt and AN 960-10L washer, secured with an AN 320-3 nut and AN 380-2-2 cotter pin. (Piper Service Bulletin No. 159 covers this subject.) 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.
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