AD 2016-24-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier | Various | Airworthiness Directives; Bombardier, Inc. Airplanes |
Unsafe Condition
Shims might not have been installed between certain longerons and longeron joint fittings, which could result in a gapping condition and lead to stress corrosion cracking of the longeron joint fittings, adversely affecting the structural integrity of the wing-to-fuselage attachment joints.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the external surface of the fuselage skin panel for loose or working fasteners and take corrective action if necessary. Conduct a detailed visual inspection of the longeron joint fittings for the existence of shims. Perform high frequency eddy current inspections of the longeron and the longeron joint fittings for any cracking. Replace longeron fittings, shims, and fasteners as required.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 flight hours after the effective date of this AD.
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Affected Aircraft
Bombardier, Inc. Model DHC-8-400 series airplanes, specifically at fuselage station X373-380, stringers 7 on the left and right hand side.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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