AD 48-51-02

AD Final Rules - DRS_48-51-02.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
48-51-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
CONVAIR Model 240 Aircraft
Subject:
Horizontal Tail Surfaces
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Superseded AD: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Superseded By: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: 48-51-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   48-51-02

SUBJECT HEADING:   CONVAIR Model 240 Aircraft

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
48-51-02 CONVAIR: Applies to All Model 240 Aircraft.

Recently reported difficulties concerning the horizontal tail surfaces for Convair Model 240 aircraft have indicated the necessity of conducting thorough and frequent inspections of all critical items to detect any fatigue cracks and to minimize the development of hazardous conditions. The several reported difficulties appear to result from tail vibrations induced by the engines and/or propellers at certain r.p.m.'s. Pending completion of the necessary investigations and determination of adequate remedial measures, the following must be accomplished:

A. To be accomplished daily on the left horizontal surfaces. (NOTE: Time limit may be extended to each No. 3 operation upon incorporation of AD 49-44-02 and CVAC Service Bulletins 240-219 and 240-247).

Utilizing available inspection openings but without removing any surfaces, conduct a close, visual inspection of the following:

1. Horizontal stabilizer skin, rear spar and hinge brackets.

2. Elevator skin, leading edge ribs, spars, hinge brackets and balance weight installations.

3. Tab skin, spar, hinge brackets and balance weight installations.

Particular care should be taken to detect any evidence of loose balance weights, sheared rivets or cracked hinge brackets. Any failed parts should be adequately repaired or replaced prior to the next flight.

NOTE: Inspection procedures which have been satisfactorily demonstrated to the CAA Agent to provide equivalent safety may be accepted in lieu of the inspection procedures outlined above.

NOTE: The following static balance tolerances about the respective hinge lines must be retained after rework of any surface:

1. Left elevator, including flight tab; 72-87 inch-pounds tail heavy with the seal curtain removed.

2. Right elevator, including trim tab: 0-15 inch-pounds nose heavy with the seal curtain removed.

3. Elevator flight tab: 6-8 inch-pounds nose heavy.

B. To be accomplished at periods not to exceed 50 hours until close tolerance bolts and bushings have been installed in elevator tab hinges in accordance with CVAC Service Bulletin 240-205.

Remove all elevator flight tab hinge pins and inspect the pins, bushings and bearings for sign of wear. Worn parts should be replaced.

This supersedes AD 48-47-01.

FOOTER: