AD 60-14-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Kelowna Flightcraft R & D Ltd. | 340 | CONVAIR Models 340/440 Aircraft |
| aircraft | Kelowna Flightcraft R & D Ltd. | 440 | CONVAIR Models 340/440 Aircraft |
Unsafe Condition
Fatigue failures have occurred in the threaded area (piston end) of the main landing gear actuating cylinder rod assembly, P/N 340-5150107, leading to complete failure of the rod end and excessive airframe loading.
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Required Actions
Conduct a visual inspection using at least a 10-power magnifying glass or equivalent for cracks in the threaded portion of the main landing gear actuating cylinder rod assembly. If cracks are found, replace or rework the cylinder rod assembly in accordance with Convair Service Engineering Report 340-12, 440-11 or equivalent prior to further flight.
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Compliance Time
Within the next 425 hours' time in service, and every 425 hours thereafter
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Affected Aircraft
CONVAIR Models 340/440 Aircraft with main landing gear actuating cylinder rod assembly, P/N 340-5150107, having more than 5,000 hours' time in service.
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Federal Register Abstract
Main Landing Gear
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_60-14-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 60-14-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: CONVAIR Models 340/440 Aircraft Subject: Main Landing Gear Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Kelowna Flightcraft R & D Ltd. Model: 340 | 440 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 60-14-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 60-14-01 SUBJECT HEADING: CONVAIR Models 340/440 Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 60-14-01 CONVAIR: Amdt. 177 Part 507 Federal Register July 1, 1960. Applies to All Models 340/440 Aircraft. Compliance required as indicated. Fatigue failures have occurred in the threaded area (piston end) of the main landing gear actuating cylinder rod assembly, P/N 340-5150107. In at least two instances, complete failure of the rod end occurred allowing the main gear to free fall to the down position causing excessive load to be placed on the airframe. As a result, the following must be accomplished on rod assemblies with more than 5,000 hours' time in service. Within the next 425 hours' time in service, and every 425 hours thereafter, conduct a visual inspection using at least a 10-power magnifying glass or equivalent for cracks in the threaded portion of the main landing gear actuating cylinder rod assembly, P/N 340-5150107. If cracks are found, the cylinder rod assembly must be replaced or reworked in accordance with Convair Service Engineering Report 340-12, 440-11 or equivalent prior to further flight. Reworked salvaged parts or reworked sound parts are not subject to the special inspections. FOOTER:
Document Text
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AD Final Rules - DRS_60-14-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 60-14-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: CONVAIR Models 340/440 Aircraft Subject: Main Landing Gear Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Kelowna Flightcraft R & D Ltd. Model: 340 | 440 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 60-14-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 60-14-01 SUBJECT HEADING: CONVAIR Models 340/440 Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 60-14-01 CONVAIR: Amdt. 177 Part 507 Federal Register July 1, 1960. Applies to All Models 340/440 Aircraft. Compliance required as indicated. Fatigue failures have occurred in the threaded area (piston end) of the main landing gear actuating cylinder rod assembly, P/N 340-5150107. In at least two instances, complete failure of the rod end occurred allowing the main gear to free fall to the down position causing excessive load to be placed on the airframe. As a result, the following must be accomplished on rod assemblies with more than 5,000 hours' time in service. Within the next 425 hours' time in service, and every 425 hours thereafter, conduct a visual inspection using at least a 10-power magnifying glass or equivalent for cracks in the threaded portion of the main landing gear actuating cylinder rod assembly, P/N 340-5150107. If cracks are found, the cylinder rod assembly must be replaced or reworked in accordance with Convair Service Engineering Report 340-12, 440-11 or equivalent prior to further flight. Reworked salvaged parts or reworked sound parts are not subject to the special inspections. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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