AD 75-12-06
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-24 | Airworthiness Directives; Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-24-250 | Airworthiness Directives; Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-24-260 | Airworthiness Directives; Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-24-400 | Airworthiness Directives; Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 Airplanes |
Unsafe Condition
Cracks in the fin forward spar to fuselage attachment assembly channel P/N 20749-0 and straps P/N 20749-5 and -6 in the area of the channel bend relief holes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the channel and straps for cracks using dye penetrant or approved equivalent inspection within 25 hours' time in service (if not done in last 75 hours). Polish rough edges of bend relief holes. Repeat visual inspections with 5 power magnifying glass or equivalent every 100 hours' time in service. Repair or replace cracked parts with FAA approved methods or equivalent parts before further flight.
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 (for initial inspection), and subsequent inspections within 100 hours' time in service from the last inspection.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Piper Models PA-24, PA-24-250, PA-24-260, and PA-24-400 certificated in all categories where the fin forward spar uses channel P/N 20749-0 and straps P/N 20749-5 and -6.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Fin Forward Spar
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_75-12-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-12-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 Airplanes Subject: Fin Forward Spar Status: Current Citation: This information is not available. Citation Publish Date: 06/02/1975 Effective Date: 06/05/1975 Make: Piper Aircraft Inc. Model: PA-24 | PA-24-250 | PA-24-260 | PA-24-400 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: 75-12-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2227 AD NUMBER: 75-12-06 SUBJECT HEADING: Airworthiness Directives; Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 Airplanes ACTION: SUMMARY: DATES: Effective June 5, 1975. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-12-06 PIPER: Amendment 39-2227. Applies to Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 certificated in all categories. Compliance required as indicated. 1. Affects the fin forward spar to fuselage attachment assembly where the channel P/N 20749-0 and the straps P/N 20749-5 and -6 are riveted together. (a) Within the next 25 hours' time in service, unless already accomplished within the last 75 hours' time in service: (i) Inspect the channel P/N 20749-0 and the two straps P/N 20749-5 and -6 in the area of the channel bend relief holes for cracks using a dye penetrant method or an approved equivalent inspection. (ii) Polish the rough edges of the bend relief holes. (b) Within 100 hours' time in service after the inspection specified in "a" above, visually inspect the channel and straps in the area of the channel relief holes for cracks using a magnifying glass of at least 5 power or an approved equivalent inspection. (c) The inspection specified in "b" above shall be repeated at intervals not to exceed 100 hours' time in service from the last inspection. 2. Repair cracked parts with an FAA approved repair or replace parts with an unused part of the same number or an approved equivalent part prior to further flight. 3. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection interval specified in this AD. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective June 5, 1975. FOOTER:
Document Text
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AD Final Rules - DRS_75-12-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-12-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 Airplanes Subject: Fin Forward Spar Status: Current Citation: This information is not available. Citation Publish Date: 06/02/1975 Effective Date: 06/05/1975 Make: Piper Aircraft Inc. Model: PA-24 | PA-24-250 | PA-24-260 | PA-24-400 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: 75-12-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2227 AD NUMBER: 75-12-06 SUBJECT HEADING: Airworthiness Directives; Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 Airplanes ACTION: SUMMARY: DATES: Effective June 5, 1975. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-12-06 PIPER: Amendment 39-2227. Applies to Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 certificated in all categories. Compliance required as indicated. 1. Affects the fin forward spar to fuselage attachment assembly where the channel P/N 20749-0 and the straps P/N 20749-5 and -6 are riveted together. (a) Within the next 25 hours' time in service, unless already accomplished within the last 75 hours' time in service: (i) Inspect the channel P/N 20749-0 and the two straps P/N 20749-5 and -6 in the area of the channel bend relief holes for cracks using a dye penetrant method or an approved equivalent inspection. (ii) Polish the rough edges of the bend relief holes. (b) Within 100 hours' time in service after the inspection specified in "a" above, visually inspect the channel and straps in the area of the channel relief holes for cracks using a magnifying glass of at least 5 power or an approved equivalent inspection. (c) The inspection specified in "b" above shall be repeated at intervals not to exceed 100 hours' time in service from the last inspection. 2. Repair cracked parts with an FAA approved repair or replace parts with an unused part of the same number or an approved equivalent part prior to further flight. 3. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection interval specified in this AD. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective June 5, 1975. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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