AD 54-24-04
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 main landing gear trunnion fittings (P/N 2021A23307, 2021A23308, 2021A23309, 2021A23310) have been reported in the area of the boss and the web, which could lead to failure of these parts.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect fittings using dye penetrant method, clean thoroughly. If cracks found, rework by grinding if within 2 inches length or 0.060 inch depth; replace otherwise. Reinspections required at intervals of 250 hours ±75 hours with 8-power magnifying glass or equivalent. New parts must be inspected at first 1,000 hours and subsequent 250-hour intervals. Improved design parts (P/N -1 suffix) require visual inspections every 500 hours initially, then dye penetrant at 7,500 hours and subsequent 250-hour intervals.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
As soon as practical but not later than December 10, 1954, unless already accomplished. If a crack is found, compliance required prior to return to service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Martin-Marietta Corporation Models 202 and 202A Aircraft, all serial numbers.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Landing Gear Trunnion Fittings
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_54-24-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 54-24-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: MARTIN Models 202 and 202A Aircraft Subject: Landing Gear Trunnion Fittings 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Make: Martin-Marietta Corporation Model: 202 | 202A Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 54-24-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 54-24-04 SUBJECT HEADING: MARTIN Models 202 and 202A Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 54-24-04 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required as indicated. Several cases of cracks in the main landing gear trunnion fittings (P/N 2021A23307, 2021A23308, 2021A23309, 2021A23310) have been reported. These cracks have been in the area of the boss and the web. To preclude failure of these parts all aircraft must be inspected and reworked as follows: I. Compliance required as soon as practical but not later than December 10, 1954, unless already accomplished. Thoroughly clean fittings and inspect using a dye penetrant inspection method. If a crack is found, rework the part in accordance with item II. If no cracks exist the part must be reinspected using an 8- power magnifying glass, dye penetrant method or equivalent every 250 hours plus or minus 75 hours. II. Compliance required prior to return to service if a crack is found. The fitting may be repaired by grinding provided the crack does not exceed either 2 inches in length or exceed 0.060 inch in depth. Parts having cracks exceeding either of the above limitations must be replaced. Repaired parts must be etch inspected. Repaired parts must be reinspected using an 8-power magnifying glass, dye penetrant method or equivalent every 250 hours plus or minus 75 hours. III. New parts of the same design (P/N 2021A23307 through 23310) must be inspected at the first regular inspection period of approximately 1,000 hours after installation, and thereafter at every 250 hours plus or minus 75 hours using an 8-power magnifying glass, dye penetrant method or equivalent. IV. Replacement parts of the improved design (P/N 2021A23307-1 through 23310-1) must be inspected visually at the first regular inspection period of 1,000 hours after installation, and thereafter at intervals not exceeding 500 hours. At 7,500 hours after installation, and thereafter at every 250 hours plus or minus 75 hours, inspect the fitting using a dye penetrant method or equivalent. (NOTE: All specified inspection intervals are based on an average landing frequency of one per hour. Where average landing frequency exceeds this, there should be a corresponding decrease in the inspection intervals.) (Martin telegram of November 3, 1954, to all 202 and 202A operators covers this subject.) FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_54-24-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 54-24-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: MARTIN Models 202 and 202A Aircraft Subject: Landing Gear Trunnion Fittings 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: 54-24-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 54-24-04 SUBJECT HEADING: MARTIN Models 202 and 202A Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 54-24-04 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required as indicated. Several cases of cracks in the main landing gear trunnion fittings (P/N 2021A23307, 2021A23308, 2021A23309, 2021A23310) have been reported. These cracks have been in the area of the boss and the web. To preclude failure of these parts all aircraft must be inspected and reworked as follows: I. Compliance required as soon as practical but not later than December 10, 1954, unless already accomplished. Thoroughly clean fittings and inspect using a dye penetrant inspection method. If a crack is found, rework the part in accordance with item II. If no cracks exist the part must be reinspected using an 8- power magnifying glass, dye penetrant method or equivalent every 250 hours plus or minus 75 hours. II. Compliance required prior to return to service if a crack is found. The fitting may be repaired by grinding provided the crack does not exceed either 2 inches in length or exceed 0.060 inch in depth. Parts having cracks exceeding either of the above limitations must be replaced. Repaired parts must be etch inspected. Repaired parts must be reinspected using an 8-power magnifying glass, dye penetrant method or equivalent every 250 hours plus or minus 75 hours. III. New parts of the same design (P/N 2021A23307 through 23310) must be inspected at the first regular inspection period of approximately 1,000 hours after installation, and thereafter at every 250 hours plus or minus 75 hours using an 8-power magnifying glass, dye penetrant method or equivalent. IV. Replacement parts of the improved design (P/N 2021A23307-1 through 23310-1) must be inspected visually at the first regular inspection period of 1,000 hours after installation, and thereafter at intervals not exceeding 500 hours. At 7,500 hours after installation, and thereafter at every 250 hours plus or minus 75 hours, inspect the fitting using a dye penetrant method or equivalent. (NOTE: All specified inspection intervals are based on an average landing frequency of one per hour. Where average landing frequency exceeds this, there should be a corresponding decrease in the inspection intervals.) (Martin telegram of November 3, 1954, to all 202 and 202A operators covers this 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.
Related Airworthiness Directives
71-09-06
final ruleAirworthiness Directives; MARTIN AIRCRAFT Models 202, 202A and 404 Airplanes
Unsafe Condition: Cracks or corrosion in the main landing gear aluminum gland nut, P/N 202SD81548 (Menasco Drawing No. 511034).
67-19-04
final ruleAirworthiness Directives; MARTIN Models 202, 202A and 404 Airplanes
Unsafe Condition: Cracks and corrosion in the engine mounts, specifically in the tubular members and welds, which could lead to structural failure of the engine mounts.
67-14-06
final ruleMARTIN 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%...
66-08-04
final ruleAirworthiness Directives; MARTIN Models 202, 202A, and 404 Airplanes
Unsafe Condition: Cracks in the piston of the piston and fork assembly of the nose landing gear, specifically part number 202SD84483, could lead to failure of the nose landing gear assembly.