AD 50-19-02

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AD Number:
50-19-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
CONVAIR Model 240 Aircraft
Subject:
Rudder Flight Tab Balance Weight Brackets
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
Make:
Kelowna Flightcraft R & D Ltd.
Model:
240 Series
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Superseded AD: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Superseded By: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: 50-19-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   50-19-02

SUBJECT HEADING:   CONVAIR Model 240 Aircraft

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
50-19-02 CONVAIR: Applies to All Model 240 Aircraft.

Compliance required as indicated.

Failures of the rudder flight tab balance weight brackets and of the rudder closing spar ahead of the flight tab have been experienced on service aircraft. In order to preclude the possibility of these failures progressing to such an extent that the airworthiness of the airplane is impaired, it is considered necessary that the following be accomplished on all CVAC Model 240 Series aircraft:

A. To be accomplished as soon as practicable but not later than next No. 1 inspection and to be repeated at each No. 2 inspection thereafter.

Inspect the rudder flight tab balance weight brackets for cracks in the neck down areas approximately 1 inch from the flight tab and also adjacent to the edges of the counterweight. Inspect the rudder closing spar for cracks in the areas adjacent to the rudder flight tab hinge brackets. All cracks, when found, must be replaced or suitably repaired before next flight.

B. To be accomplished by January 1, 1951.

Reinforce the rudder flight tab balance weight brackets, and the attachment of the brackets to the tab and to the balance weight.

(CVAC Service Bulletin 240-355A covers this same subject.)

NOTE: Although evidence indicates that these failures will be materially reduced after incorporation of the above, sufficient evidence of trouble-free operation is not available. Therefore, it will be necessary that the inspections outlined under part A, be continued at each No. 3 inspection after the incorporation of part B, until sufficient evidence of trouble-free operation has been supplied to the FAA to warrant discontinuance of this inspection.

This supersedes AD 50-06-03.

FOOTER: