AD 71-12-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-23 | Airworthiness Directives; Piper Model PA-23, PA-23-160, and PA-23-250 Aircraft |
| aircraft | Piper Aircraft Inc. | PA-23-160 | Airworthiness Directives; Piper Model PA-23, PA-23-160, and PA-23-250 Aircraft |
| aircraft | Piper Aircraft Inc. | PA-23-250 (Navy UO-1) | Airworthiness Directives; Piper Model PA-23, PA-23-160, and PA-23-250 Aircraft |
Unsafe Condition
Failure of the engine controls support bracket in the cockpit pedestal.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect P/N 17892-00 engine control cable support bracket for cracks, distortion, and secure attachment. Replace any cracked or distorted parts before further flight. Repeat inspections every 100 hours' time in service until an improved bracket (Piper P/N 16975-00 or equivalent) is installed.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 15 hours' time in service for airplanes with 2000 hours' or more total time and 50 hours' time in service with less than 2000 hours' total time 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 Model PA-23, PA-23-160 (serial numbers 23-1 and up), and PA-23-250 (serial numbers 27-1 through 27-140 inclusive).
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Engine Control Support Bracket
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_71-12-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 71-12-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-23, PA-23-160, and PA-23-250 Aircraft Subject: Engine Control Support Bracket Status: Current Citation: This information is not available. Citation Publish Date: 06/03/1971 Effective Date: 06/08/1971 Make: Piper Aircraft Inc. Model: PA-23 | PA-23-160 | PA-23-250 (Navy UO-1) Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part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: 71-12-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1220 AD NUMBER: 71-12-01 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-23, PA-23-160, and PA-23-250 Aircraft ACTION: SUMMARY: DATES: Effective June 8, 1971. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 71-12-01 PIPER AIRCRAFT: Amdt. 39-1220. Applies to all PA-23 and PA-23-160 type aircraft serial numbers 23-1 and up and PA-23-250 aircraft serial numbers 27-1 through 27- 140 inclusive. Compliance required as indicated unless already accomplished. To prevent failure of the engine controls support bracket in the cockpit pedestal, accomplish the following: 1. Within 15 hours' time in service for airplanes with 2000 hours' or more total time and 50 hours' time in service with less than 2000 hours' total time after the effective date of this AD, visually inspect P/N 17892-00 engine control cable support bracket for cracks, distortion and security of attachment. Any part found cracked or distorted must be replaced prior to further flight. 2. The inspection described in paragraph (1) above must be accomplished at intervals of 100 hours' time in service until an improved bracket, Piper P/N 16975-00 or an equivalent part approved by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region, is installed. Upon installation of the improved part, the above repetitive inspections are no longer required. 3. Upon submission of substantiating data through an FAA maintenance inspector by an owner or operator, the Chief, Engineering & Manufacturing Branch, FAA Eastern Region, may adjust the compliance time specified in this AD. (Piper Aircraft Corp. Service Bulletin No. 335 pertains to this subject.) This amendment is effective June 8, 1971. FOOTER:
Document Text
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AD Final Rules - DRS_71-12-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 71-12-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-23, PA-23-160, and PA-23-250 Aircraft Subject: Engine Control Support Bracket Status: Current Citation: This information is not available. Citation Publish Date: 06/03/1971 Effective Date: 06/08/1971 Make: Piper Aircraft Inc. Model: PA-23 | PA-23-160 | 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: 71-12-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1220 AD NUMBER: 71-12-01 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-23, PA-23-160, and PA-23-250 Aircraft ACTION: SUMMARY: DATES: Effective June 8, 1971. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 71-12-01 PIPER AIRCRAFT: Amdt. 39-1220. Applies to all PA-23 and PA-23-160 type aircraft serial numbers 23-1 and up and PA-23-250 aircraft serial numbers 27-1 through 27- 140 inclusive. Compliance required as indicated unless already accomplished. To prevent failure of the engine controls support bracket in the cockpit pedestal, accomplish the following: 1. Within 15 hours' time in service for airplanes with 2000 hours' or more total time and 50 hours' time in service with less than 2000 hours' total time after the effective date of this AD, visually inspect P/N 17892-00 engine control cable support bracket for cracks, distortion and security of attachment. Any part found cracked or distorted must be replaced prior to further flight. 2. The inspection described in paragraph (1) above must be accomplished at intervals of 100 hours' time in service until an improved bracket, Piper P/N 16975-00 or an equivalent part approved by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region, is installed. Upon installation of the improved part, the above repetitive inspections are no longer required. 3. Upon submission of substantiating data through an FAA maintenance inspector by an owner or operator, the Chief, Engineering & Manufacturing Branch, FAA Eastern Region, may adjust the compliance time specified in this AD. (Piper Aircraft Corp. Service Bulletin No. 335 pertains to this subject.) This amendment is effective June 8, 1971. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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