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Airworthiness Directive

AD 99-23-05 64 FR 61478 Active

Federal Aviation Administration · 14 CFR part 39

FR document
99-28746
Amendment
39-11401
Published
1999-11-12
Effective
1999-12-17
Models covered
1
Last live check
2026-10-03

Printed from https://aircraftdirectives.com/ad/99-23-05 · AircraftDirectives restates official FAA and manufacturer records; the official sources named on this sheet control. Not an airworthiness determination.

This page is a reference Record, not an airworthiness or compliance determination. Official FAA and manufacturer sources control over our restatement, subject to governing law. Check applicability, current requirements and incorporated documents before acting. The owner or operator remains responsible for airworthiness and required records under 14 CFR 91.403 and 91.417, as applicable. Terms of Use: /terms.

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AD

99-23-05

FR doc 99-28746 · 64 FR 61478

AD 99-23-05Published 1999-11-12Effective 1999-12-17

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 detailed visual inspections and high frequency eddy current inspections to detect cracking of the wing upper skin and ladder plates at over wing access panels between certain stations; and repair, if necessary.

Full official abstract

This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-8-101, -102, -103, -106, -201, - 202, -301, -311, and -315 series airplanes, that requires repetitive detailed visual inspections and high frequency eddy current inspections to detect cracking of the wing upper skin and ladder plates at over wing access panels between certain stations; and repair, if necessary. 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 fatigue cracking of the wing ladder plates, which, if not corrected, could reduce the structural integrity of the wing.

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All de Havilland DHC-8 Dash 8 directives

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Applies to 1 model in our index