| AD Number | 49-38-01 | Status | Active |
| Effective Date | Not specified | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | N/A |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Kelowna Flightcraft R & D Ltd. |
| Model(s) | 240 Series |
49-38-01 CONVAIR: Applies to All Model 240 Aircraft Incorporating Original Type Nose Strut Outer Cylinder, Bendix P/N 156842.
To be accomplished on No. 1 inspection on all nose landing gear struts whose total operating time exceeds 1,000 hours.
Cracking of the nose gear landing struts in the areas directly below the drag link attachment legs, has been experienced on some CV-240 service aircraft whose total time exceeds approximately 1,000 hours. These cracks appear to be the result of repeated loadings experienced by the gear during landings. In order to insure the continued airworthiness of the aircraft, the nose landing gear shall be examined closely, using visual means, for evidence of any cracks in the areas directly below the drag strut attachment lugs.
When cracks are found, it may be possible to repair the damage by grinding, blending and polishing, depending upon the extent and depth of the cracks. All struts not eligible for such repairs are to be retired from service.
(Bendix Service Bulletin L. G. 509 covers the subject.)
The above-described inspection may be discontinued on those struts which have been reinforced by the addition of a support clamp and eyebolts, or their equivalent, to alleviate the loading condition which caused the development of cracks.
Struts reworked in accordance with Bendix Service Bulletin L.G. 511 and incorporating a support clamp and eyebolts in accordance with Bendix Service Bulletin L.G. 510 are eligible for service and do not require the above inspection.
(Bendix Service Bulletin L.G. 310 covers this same subject.)