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Bombardier Model CL-215-1A10 and CL-215-6B11 Series |
 | | The actions specified by this AD are intended to detect and correct cracking in the wing-to-fuselage frame angles, which could result in reduced structural integrity of the airframe. |
 | | The incorporation by reference of Bombardier Alert Service Bulletin 215-A476, Revision 3, dated August 21, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as September 7, 1999 (64 FR 41775, August 2, 1999). |
 | | (2) The incorporation by reference of Bombardier Alert Service Bulletin 215-A476, Revision 3, dated August 21, 1998, was approved previously by the Director of the Federal Register as of September 7, 1999 (64 FR 41775, August 2, 1999). |
| www.airweb.faa.gov /Regulatory_and_Guidance_Library/rgAD.nsf/0/A1DBA44609269F8A86256BDE004A74AB?OpenDocument (1613 words) |
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