AD 47-50-12
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Univair Aircraft Corporation | 108 | Airworthiness Directives; Stinson Model 108 Series |
| aircraft | Univair Aircraft Corporation | 108-1 | Airworthiness Directives; Stinson Model 108 Series |
Unsafe Condition
Fatigue cracks in the stabilizer leading edge attachment to the fuselage
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect for fatigue cracks after each 100 hours of operation. Add reinforcements if cracks are present. Discontinue inspection after reinforcement installation.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
every 100 hours of operation
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Univair Aircraft Corporation Model 108 Series, serial numbers 1 through 3500
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Stabilizer attachment fitting
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_47-50-12.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 47-50-12 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Stinson Model 108 Series Subject: Stabilizer attachment fitting Status: Current Citation: This information is not available Citation Publish Date: Effective Date: Make: Univair Aircraft Corporation Model: 108 | 108-1 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 47-50-12 CITATION: This information is not available PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 47-50-12 SUBJECT HEADING: Airworthiness Directives; Stinson Model 108 Series ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 47-50-12 STINSON: Applies to Model 108 Series Serial Numbers 1 through 3500. Compliance required every 100 hours of operation. Inspection of the stabilizer leading edge attachment to the fuselage should be made for fatigue cracks, after each 100 hours of operation. If fatigue cracks are present, reinforcements to the stabilizer fitting should be added. Inspection may be discontinued after reinforcement is installed. (Stinson Service Bulletin No. 254 dated September 5, 1947, covers this same subject.) FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_47-50-12.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 47-50-12 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Stinson Model 108 Series Subject: Stabilizer attachment fitting Status: Current Citation: This information is not available Citation Publish Date: Effective Date: Make: Univair Aircraft Corporation Model: 108 | 108-1 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 47-50-12 CITATION: This information is not available PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 47-50-12 SUBJECT HEADING: Airworthiness Directives; Stinson Model 108 Series ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 47-50-12 STINSON: Applies to Model 108 Series Serial Numbers 1 through 3500. Compliance required every 100 hours of operation. Inspection of the stabilizer leading edge attachment to the fuselage should be made for fatigue cracks, after each 100 hours of operation. If fatigue cracks are present, reinforcements to the stabilizer fitting should be added. Inspection may be discontinued after reinforcement is installed. (Stinson Service Bulletin No. 254 dated September 5, 1947, covers this same 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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