# Airworthiness Directives; Bombardier Model CL-215-1A10 and CL-215-6B11 Series Airplanes
> **Rule** · Final rule. · Published 2002-06-20 · Effective 2002-07-25 · 67 FR 41818
## Document
- **Document number:** 02-15242
- **Category:** airworthiness
- **Manufacturer:** Bombardier Model CL-215-1A10 and CL-215-6B11 Series
- **Type:** Rule
- **Action:** Final rule.
- **Citation:** 67 FR 41818
- **Publication date:** 2002-06-20
- **Effective date:** 2002-07-25
- **FAA docket:** Docket No. 2000-NM-398-AD
## Abstract

This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-215-1A10 and CL-215- 6B11 series airplanes, that currently requires repetitive inspections to detect cracking on certain wing-to-fuselage frame angles; and repair, if necessary. This amendment decreases the compliance time for the initial inspection to detect cracking on certain wing-to-fuselage frame angles and decreases the interval between repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. 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.

## Source
- [Federal Register document](https://www.federalregister.gov/documents/2002/06/20/02-15242/airworthiness-directives-bombardier-model-cl-215-1a10-and-cl-215-6b11-series-airplanes)
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