AD 67-14-06
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Martin-Marietta Corporation | 202 | MARTIN Models 202, 202A, and 404 Series Airplanes |
| aircraft | Martin-Marietta Corporation | 202A | MARTIN Models 202, 202A, and 404 Series Airplanes |
| aircraft | Martin-Marietta Corporation | 404 | MARTIN Models 202, 202A, and 404 Series Airplanes |
Unsafe Condition
Cracks in the lower spar cap, spar web inboard of the outer panel closing rib, and vertical angle attaching the web to the outer panel closing rib in the front spars of the outer wing panels at 25% wing chord.
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Required Actions
Inspect the specified areas in both outer wing panel front spars using X-ray or dye penetrant with 10x magnification or FAA-approved equivalent. Replace cracked parts with inspected crack-free same part number parts or approved equivalent before further flight. Drain fuel before X-ray due to lead gasoline hazard.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 15 hours' time in service after the effective date (April 28, 1967) unless already accomplished within last 185 hours' time in service, thereafter every 200 hours' time in service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Martin-Marietta Corporation Models 202, 202A, and 404 Series Airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Wing Inspection
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_67-14-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 67-14-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: MARTIN Models 202, 202A, and 404 Series Airplanes Subject: Wing Inspection Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/28/1967 Make: Martin-Marietta Corporation Model: 202 | 202A | 404 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 67-14-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-406 AD NUMBER: 67-14-06 SUBJECT HEADING: MARTIN Models 202, 202A, and 404 Series Airplanes ACTION: SUMMARY: DATES: Effective April 28, 1967. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 67-14-06 MARTIN: Amdt. 39-406 Part 39 Federal Register April 28, 1967. Applies to Models 202, 202A, and 404 Series Airplanes. (a) Within the next 15 hours' time in service after the effective date of this AD unless already accomplished within the last 185 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection, inspect the following areas in both outer wing panel front spars located at 25% of the wing chord for cracks using X-ray or dye penetrant with a glass of at least 10 power, or an FAA-approved equivalent inspection. (1) The lower spar cap in a region 3 inches long from the outer panel closing rib outboard. (2) The spar web inboard of the outer panel closing rib between the rib and the splice bolts. (3) The vertical angle that attaches this web to the outer panel closing rib. (b) If a crack is found, before further flight, replace the cracked part with a part of the same part number that has been inspected in accordance with (a) and found free of cracks or with an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Equivalent inspections may be approved by an FAA maintenance inspector. (d) All fuel must be drained before X-ray inspection because of lead in the gasoline. (e) Upon request of the operator, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region may increase the compliance times specified in this AD if the request contains substantiating data submitted through an FAA maintenance inspector to justify the increase for that operator. This supersedes AD 59-26-05. This directive effective upon publication in the Federal Register for all person except those to whom it was made effective by telegram dated April 20, 1967. FOOTER:
Document Text
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AD Final Rules - DRS_67-14-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 67-14-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: MARTIN Models 202, 202A, and 404 Series Airplanes Subject: Wing Inspection Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/28/1967 Make: Martin-Marietta Corporation Model: 202 | 202A | 404 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: 67-14-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-406 AD NUMBER: 67-14-06 SUBJECT HEADING: MARTIN Models 202, 202A, and 404 Series Airplanes ACTION: SUMMARY: DATES: Effective April 28, 1967. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 67-14-06 MARTIN: Amdt. 39-406 Part 39 Federal Register April 28, 1967. Applies to Models 202, 202A, and 404 Series Airplanes. (a) Within the next 15 hours' time in service after the effective date of this AD unless already accomplished within the last 185 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection, inspect the following areas in both outer wing panel front spars located at 25% of the wing chord for cracks using X-ray or dye penetrant with a glass of at least 10 power, or an FAA-approved equivalent inspection. (1) The lower spar cap in a region 3 inches long from the outer panel closing rib outboard. (2) The spar web inboard of the outer panel closing rib between the rib and the splice bolts. (3) The vertical angle that attaches this web to the outer panel closing rib. (b) If a crack is found, before further flight, replace the cracked part with a part of the same part number that has been inspected in accordance with (a) and found free of cracks or with an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Equivalent inspections may be approved by an FAA maintenance inspector. (d) All fuel must be drained before X-ray inspection because of lead in the gasoline. (e) Upon request of the operator, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region may increase the compliance times specified in this AD if the request contains substantiating data submitted through an FAA maintenance inspector to justify the increase for that operator. This supersedes AD 59-26-05. This directive effective upon publication in the Federal Register for all person except those to whom it was made effective by telegram dated April 20, 1967. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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