AD 72-21-07
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-23-250 (Navy UO-1) | Airworthiness Directives; Piper Model PA-23-250 Airplanes |
Unsafe Condition
Longitudinal stick force reversal during certain flight conditions due to insufficient longitudinal stability characteristics.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Accomplish the alteration specified in Piper Service Bulletin No. 345 dated 7 October 1971, or an equivalent method approved by the FAA. Compliance must be completed within 30 days after the AD's effective date unless already done.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within 30 days after the effective date of this AD, unless already accomplished
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Affected Aircraft
Piper Model PA-23-250 (Navy UO-1) airplanes with serial numbers 27-4575 to 27-4587, 27-4589 to 27-4620, 27-4622 to 27-4672, 27-4674 to 27-4682, and 27-4684 to 27-4694 inclusive, and those altered by substituting specific Piper part numbers for older ones.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Longitudinal Stability
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_72-21-07.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 72-21-07 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-23-250 Airplanes Subject: Longitudinal Stability Status: Current Citation: This information is not available. Citation Publish Date: 04/26/1976 Effective Date: 04/29/1976 Make: Piper Aircraft Inc. Model: PA-23-250 (Navy UO-1) Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part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: 72-21-07 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2586 AD NUMBER: 72-21-07 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-23-250 Airplanes ACTION: SUMMARY: DATES: Effective April 29, 1976. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 72-21-07 PIPER AIRCRAFT CORP: Amendment 39-1540 as amended by Amendment 39-2586. Applies to PA23-250 airplanes, S/Ns 27-4575 to 27-4587 inclusive, 27-4589 to 27- 4620 inclusive, 27-4622 to 27-4672 inclusive, 27-4674 to 27-4682 inclusive, and 27-4684 to 27- 4694 inclusive, and PA-23-250 airplanes which have been altered by substitution of Piper P/N 32958-00, Section Assembly - Fuselage, Nose, 34552-00, Section Assembly - Fuselage, Nose, or 33346-05, Radome Assembly for Piper P/N 30517-00, Section Assembly - Fuselage, Nose, or 30517-06, Section Assembly - Fuselage, Nose, certificated in all categories. Compliance required within 30 days after the effective date of this AD, unless already accomplished. To improve the longitudinal stability characteristics and to prevent longitudinal stick force reversal during certain flight conditions, accomplish the alteration contained in Piper Service Bulletin No. 345, dated 7 Oct. 1971; or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Upon request through a maintenance inspector, accompanied by substantiating data, the compliance time specified in the AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-1540 was effective October 19, 1972. This amendment 39-2586 is effective April 29, 1976. FOOTER:
Document Text
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AD Final Rules - DRS_72-21-07.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 72-21-07 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-23-250 Airplanes Subject: Longitudinal Stability Status: Current Citation: This information is not available. Citation Publish Date: 04/26/1976 Effective Date: 04/29/1976 Make: Piper Aircraft Inc. Model: PA-23-250 (Navy UO-1) 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: 72-21-07 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2586 AD NUMBER: 72-21-07 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-23-250 Airplanes ACTION: SUMMARY: DATES: Effective April 29, 1976. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 72-21-07 PIPER AIRCRAFT CORP: Amendment 39-1540 as amended by Amendment 39-2586. Applies to PA23-250 airplanes, S/Ns 27-4575 to 27-4587 inclusive, 27-4589 to 27- 4620 inclusive, 27-4622 to 27-4672 inclusive, 27-4674 to 27-4682 inclusive, and 27-4684 to 27- 4694 inclusive, and PA-23-250 airplanes which have been altered by substitution of Piper P/N 32958-00, Section Assembly - Fuselage, Nose, 34552-00, Section Assembly - Fuselage, Nose, or 33346-05, Radome Assembly for Piper P/N 30517-00, Section Assembly - Fuselage, Nose, or 30517-06, Section Assembly - Fuselage, Nose, certificated in all categories. Compliance required within 30 days after the effective date of this AD, unless already accomplished. To improve the longitudinal stability characteristics and to prevent longitudinal stick force reversal during certain flight conditions, accomplish the alteration contained in Piper Service Bulletin No. 345, dated 7 Oct. 1971; or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Upon request through a maintenance inspector, accompanied by substantiating data, the compliance time specified in the AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-1540 was effective October 19, 1972. This amendment 39-2586 is effective April 29, 1976. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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