AD 52-05-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Martin-Marietta Corporation | 202 | MARTIN Models 202 and 202A Aircraft |
| aircraft | Martin-Marietta Corporation | 202A | MARTIN Models 202 and 202A Aircraft |
Unsafe Condition
Cracks in the center wing rear spar lower chord fitting at the Station 187 rib.
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Required Actions
Inspect fittings P/N 2021U44473 and 2021U44474 within the next 100 flight hours using a 10-power magnifying glass after paint removal. Replace cracked base or base-extended cracks, or inspect every 85 flight hours if cracks are only in vertical legs. Shim gaps under 0.010 inch per item D for uncracked fittings.
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Compliance Time
within the next 100 hours
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Affected Aircraft
Martin-Marietta Corporation Models 202 and 202A Aircraft
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Federal Register Abstract
Center Wing Spar Rework
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_52-05-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 52-05-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: MARTIN Models 202 and 202A Aircraft Subject: Center Wing Spar Rework Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Martin-Marietta Corporation Model: 202 | 202A Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 52-05-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 52-05-02 SUBJECT HEADING: MARTIN Models 202 and 202A Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 52-05-02 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required as indicated. Due to a reported occurrence of cracks in the center wing rear spar lower chord fitting at the Station 187 rib, the following shall be accomplished: A. Inspect within the next 100 hours. Inspect the fittings (P/N 2021U44473 and 2021U44474) with a 10-power magnifying glass after removal of the paint with a solvent. Pay particular attention to the intersection of the spar leg with the other legs of the fittings. B. If cracks are discovered in the base or extending into the base of a fitting, the part must be replaced. C. If cracks are found in the vertical legs only, the part can either be replaced or remain installed in the airplane. If remaining installed, the fitting must be inspected every 85 hours in accordance with items A and B. Other inspection intervals may be approved based on the evaluation of the actual crack location by the manufacturer. D. For fittings that do not show any cracks, loosen the two bolts through the fitting, the spar stiffener and the spar chord tang. Also loosen the two spar web splice bolts through the fitting, the spar web stiffeners and rib 187 web. If any gap appears between the fitting and its mating surfaces, install shims so as to reduce this gap to less than 0.010 inch. E. New parts installed shall be shimmed in accordance with item D. (Glenn L. Martin Service Instruction Letter No. 17 covers this same subject.) FOOTER:
Document Text
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AD Final Rules - DRS_52-05-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 52-05-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: MARTIN Models 202 and 202A Aircraft Subject: Center Wing Spar Rework Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Martin-Marietta Corporation Model: 202 | 202A 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: 52-05-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 52-05-02 SUBJECT HEADING: MARTIN Models 202 and 202A Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 52-05-02 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required as indicated. Due to a reported occurrence of cracks in the center wing rear spar lower chord fitting at the Station 187 rib, the following shall be accomplished: A. Inspect within the next 100 hours. Inspect the fittings (P/N 2021U44473 and 2021U44474) with a 10-power magnifying glass after removal of the paint with a solvent. Pay particular attention to the intersection of the spar leg with the other legs of the fittings. B. If cracks are discovered in the base or extending into the base of a fitting, the part must be replaced. C. If cracks are found in the vertical legs only, the part can either be replaced or remain installed in the airplane. If remaining installed, the fitting must be inspected every 85 hours in accordance with items A and B. Other inspection intervals may be approved based on the evaluation of the actual crack location by the manufacturer. D. For fittings that do not show any cracks, loosen the two bolts through the fitting, the spar stiffener and the spar chord tang. Also loosen the two spar web splice bolts through the fitting, the spar web stiffeners and rib 187 web. If any gap appears between the fitting and its mating surfaces, install shims so as to reduce this gap to less than 0.010 inch. E. New parts installed shall be shimmed in accordance with item D. (Glenn L. Martin Service Instruction Letter No. 17 covers this same subject.) FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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