Airworthiness Directive

AD 99-16-04 64 FR 41775 Active

Federal Aviation Administration · 14 CFR part 39

FR document
99-19453
Amendment
39-11239
Published
1999-08-02
Effective
1999-09-07
Models covered
1
Last live check
2026-10-01
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AD

99-16-04

FR doc 99-19453 · 64 FR 41775

AD 99-16-04Published 1999-08-02Effective 1999-09-07

FAA rule - 14 CFR 39

FAA rule. Compliance with an applicable AD is required under 14 CFR 39.7. Check its effective date, applicability, compliance times and current status.

Requires repetitive inspections to detect cracking on certain wing to fuselage frame-angles, and repair, if necessary.

Full official 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.

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All Canadair CL-215 / CL-415 directives

Applies to 1 model in our index