AD 47-10-39
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Aircraft Corporation | 49-46 | LOCKHEED Model 49 |
Unsafe Condition
Cracks in the trailing edge and aft portions of the ribs of the aileron inboard of the trim tab.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the aileron inboard of the trim tab for cracks in the trailing edge and ribs every 250 flight hours. Install heavier gauge parts and rebalance the aileron when cracks are found.
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Compliance Time
At periods not to exceed 250 hours
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Affected Aircraft
Lockheed Aircraft Corporation Model 49 serials up to and including 2046 with all metal ailerons not installed.
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Federal Register Abstract
Aileron Trailing Edge
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_47-10-39.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 47-10-39 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Model 49 Subject: Aileron Trailing Edge Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Lockheed Aircraft Corporation Model: 49-46 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 47-10-39 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 47-10-39 SUBJECT HEADING: LOCKHEED Model 49 ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 47-10-39 LOCKHEED: (Was Service Note 10 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2046 on Which All Metal Ailerons Are Not Installed. At periods not to exceed 250 hours, inspect the aileron inboard of the trim tab for evidence of cracks in the trailing edge and in the aft portions of the ribs. When cracks are found, parts of heavier gage should be installed and the aileron rebalanced. The periodic inspection may be discontinued when this modification has been made. (LAC Service Bulletin 49/SB-52 covers this same subject.) FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_47-10-39.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 47-10-39 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Model 49 Subject: Aileron Trailing Edge Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Lockheed Aircraft Corporation Model: 49-46 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: 47-10-39 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 47-10-39 SUBJECT HEADING: LOCKHEED Model 49 ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 47-10-39 LOCKHEED: (Was Service Note 10 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2046 on Which All Metal Ailerons Are Not Installed. At periods not to exceed 250 hours, inspect the aileron inboard of the trim tab for evidence of cracks in the trailing edge and in the aft portions of the ribs. When cracks are found, parts of heavier gage should be installed and the aileron rebalanced. The periodic inspection may be discontinued when this modification has been made. (LAC Service Bulletin 49/SB-52 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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