AD 63-13-04

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AD Number:
63-13-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
MARTIN Model 404 Aircraft
Subject:
Landing Gear Piston/Axle Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/15/1963
Make:
Martin-Marietta Corporation
Model:
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Superseded AD: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Superseded By: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: 63-13-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   63-13-04

SUBJECT HEADING:   MARTIN Model 404 Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective July 15, 1963.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
63-13-04 MARTIN: Amdt. 575 Part 507 Federal Register June 13, 1963. Applies to All Model 404 Aircraft With Main Landing Gear Piston/Axle Assembly P/N 202SD82087 (Menasco P/N 511017).

Compliance required as indicated.

There have been cracks found in the upper portion of the 0.250 inch radius at the junction of the axle and the piston terminal (approximately 2.4 inches from the centerline of the main gear) of main landing gear piston/axle assemblies. As this condition is likely to develop in other such aircraft, accomplish the following:

(a) Thoroughly clean the radius area around the periphery of the section on the left and right sides of both main landing gear in the region of the junction of the axle to the piston terminal, removing all grease and dirt.

(b) Visually inspect for cracks all main landing gear assemblies with 5,000 or more hours' time in service on the effective date of this AD, within the next 150 hours' time in service and thereafter within each 150 hours' time in service from the last inspection.

(c) Visually inspect for cracks all main landing gear assemblies with less than 5,000 hours' time in service on the effective date of this AD, prior to 5,150 hours' time in service and thereafter within each 150 hours' time in service from the last inspection.

(d) At each fifth visual inspection i.e., each 750 hours' time in service after the initial inspection, inspect for cracks all main landing gear assemblies using dye penetrant, Zyglo or FAA approved equivalent, in conjunction with at least a 10-power magnifying glass.

(e) If a crack is found, the following rework or replacement is required:

(1) Parts with a crack that may be eliminated by removal of not more than 0.050 square inch of material without exceeding a material depth of 0.020 inch shall be reworked prior to further flight except that a ferry flight may be made in accordance with the provisions of CAR 1.76 prior to rework. In eliminating the crack, blend the reworked section into the radius, removing all nicks and dents. Polish the affected area to an RMS 32 finish.

(2) Parts with a crack that cannot be removed as set forth in (e)(1) shall be replaced prior to further flight with parts of the same part number (Menasco P/N 511017) or an FAA approved equivalent.

(f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.

This directive effective July 15, 1963.

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