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Airworthiness Directive

AD 2001-01-07 66 FR 57364 Active

Federal Aviation Administration · 14 CFR part 39

FR document
01-28571
Amendment
39-12504
Published
2001-11-15
Effective
2002-01-07
Models covered
1
Last live check
2026-10-01

Printed from https://aircraftdirectives.com/ad/2001-01-07 · 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

2001-01-07

FR doc 01-28571 · 66 FR 57364

AD 2001-01-07Published 2001-11-15Effective 2002-01-07

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 you to repetitively inspect the canted rib upper cap in the center wing carry-through area for cracks, and, if cracks are found, immediately repair the cracks or modify this area depending on the extent of any cracks found.

Full official abstract

This amendment adopts a new airworthiness directive (AD) that applies to certain Reims Aviation S.A. (Reims) Model F406 airplanes. This AD requires you to repetitively inspect the canted rib upper cap in the center wing carry-through area for cracks, and, if cracks are found, immediately repair the cracks or modify this area depending on the extent of any cracks found. This AD also requires you to modify the canted rib upper cap at a certain time period as terminating action for the repetitive inspections. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect and correct cracks in the canted rib upper cap in the center wing carry-through area, which could result in structural failure of the wing with possible loss of control of the airplane.

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All Cessna F406 Caravan II directives

View on Federal Register (opens in a new tab) Search DRS manually for AD 2001-01-07 (opens in a new tab)

Applies to 1 model in our index