AD 61-01-02

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AD Number:
61-01-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
MARTIN Models 202, 202A and 404 Aircraft
Subject:
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/06/1961
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Superseded AD: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Superseded By: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: 61-01-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   61-01-02

SUBJECT HEADING:   MARTIN Models 202, 202A and 404 Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective January 6, 1961.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   61-01-02 MARTIN: Amdt. 239 Part 507 Federal Register January 5, 1961. Applies to All Models 202, 202A and 404 Aircraft With Main Landing Gear Torque Arms Having More Than 12,000 Hours' Time In Service.
Compliance required as indicated.
Failures of Model 404 main landing gear torque arms have occurred in the lower attachment point where the torque scissors attach to the strut. Also, a failure was found in the apex (upper to lower torque arm attach point). As a result, the following must be accomplished within the next 225 hours' time in service, unless already accomplished within the last 225 hours' time in service, and every 450 hours' time in service thereafter.
Inspect all surfaces of the torque arm lugs which attach the torque scissors to the strut for cracks or corrosion, using dye penetrant, ultrasonic or radiographic method, or FAA approved equivalent. Beginning with the first repetitive inspection, also inspect all surfaces of the torque arm apex using dye penetrant, ultrasonic or radiographic method, or FAA approved equivalent. Removal of bolts and bushings is required only if dye penetrant is used. If cracks or corrosion are found, the torque arm must be replaced before the next flight.
This directive effective January 6, 1961.

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