AD 60-10-07

AD Final Rules - DRS_60-10-07.html
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AD Number:
60-10-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
MARTIN Models 202, 202A and 404 Airplanes
Subject:
Upper Nose Gear Torque Arm
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
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Superseded AD: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Superseded By: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: 60-10-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   60-10-07

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

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   60-10-07 MARTIN: Amdt. 141 Part 507 Federal Register May 4, 1960. Applies to All Models 202, 202A and 404 Airplanes.

Compliance required as indicated.

Fatigue failures have occurred on the upper nose gear torque arm, P/N 511653. These failures were approximately 3 inches aft of the safety pin, P/N AN 416-1, which connects the lower torque arm, P/N 511650, to the upper torque arm. As a result of investigation of these failures, the following shall be accomplished prior to June 1, 1960:

(a) Unless already accomplished, rework torque arms, P/N's 511650 and 511653, by increasing the 0.125-inch radius, where the arm tapers to the narrow section at the aft end, to 0.25 inch.

(b) Visually inspect for cracks, using a 10-power magnifying glass or equivalent, the areas on the nose landing gear upper and lower torque arms at all radii near the apex of each torque arm. If crack indications are found, reinspect the above area using dye penetrant or equivalent. Torque arms with cracks must be replaced prior to further flight.

(c) Visually inspect for and remove any nicks or dents in the radius described in (a).

(d) Inspect the scissor disconnect bolt safety pin, P/N AN 416-1, for proper overhang to prevent opening. Safety pins with less than 1/4-inch overhang shall be replaced prior to further flight.

(e) Repeat inspections (b) and (c) at intervals not to exceed 320 hours' time in service and inspection (d) at each safety pin installation.

FOOTER: