# Airplanes
> **Rule** · Final rule. · Published 1999-08-02 · Effective 1999-09-07 · 64 FR 41775
## Document
- **Document number:** 99-19453
- **Category:** other
- **Type:** Rule
- **Action:** Final rule.
- **Citation:** 64 FR 41775
- **Publication date:** 1999-08-02
- **Effective date:** 1999-09-07
- **FAA docket:** Docket No. 98-NM-370-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 would continue to require the same inspections. This amendment is prompted by an adverse comment received in response to the existing amendment. 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/1999/08/02/99-19453/airplanes)
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