AD 50-26-01

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AD Number:
50-26-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CURTISS-WRIGHT Model C-46 Series Aircraft
Subject:
Landing Gear Side Braces
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
Make:
Airlift International, Inc. | Curtiss-Wright Corporation | Flying Tiger Line, Inc. | L. B. Smith Air...Show more
Model:
C-46A | C-46D | C-46F | C-46R | C-46E | C-46/CW20-T | Super C-46/CW20-T
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Superseded AD: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Superseded By: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: 50-26-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   50-26-01

SUBJECT HEADING:   Airworthiness Directives; CURTISS-WRIGHT Model C-46 Series Aircraft

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
50-26-01 CURTISS-WRIGHT Applies to Model C-46 Series Aircraft equipped with landing gear side braces, Curtiss-Wright P/N's 20-310-1028 and 20-310-1029.

Compliance required within 100 hours' time in service after the effective date of this amendment, unless already accomplished within the last 400 hours' time in service, and at intervals thereafter not to exceed 500 hours' time in service from the last inspection.

Thoroughly inspect the landing gear side braces P/N 20-310-1028 and 20-310-1029 for cracks in the vicinity of the welds at either end of the struts, using magnetic or X-ray inspection.

If cracks are found, the following will apply:

1. For one crack only in the weld proper less than 1/2 inch in length and 0.060-inch deep that does not penetrate into the tube member itself, stress relieve by grinding out the crack and polishing to remove all grinding marks. No rewelding required.

2. For more than one crack in the weld proper or cracks larger than those mentioned in item 1 that do not penetrate into the tube member itself, repair by grinding out the cracks and rewelding in a welding jig (using the oxyacetylene torch method) and reheat treat the tube assembly to 180,000 p.s.i. and Rockwell C-38.

3. If cracks are found in the tube member itself, the part should be replaced by a completely new assembly or repaired by replacing the tube and refabricating to the original specifications.

4. P/N S51E105 is considered a satisfactory replacement for P/N 20-310-1028. When P/N S51E105 is installed it should be inspected by magnetic particle or X-ray method of inspection prior to initial installation and at periods not to exceed 1,000 hours of operation thereafter.

5. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern 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.

This supersedes AD 50-19-1.

Revised December 28, 1964.

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