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Airworthiness Directive

AD 2010-26-51 76 FR 13059 Active

Federal Aviation Administration · 14 CFR part 39

Prompted by another incident in which the tail rotor blade (blade) tip weight separated from a blade during flight causing vibration.

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FR document
2011-4465
Amendment
39-16587
Published
2011-03-10
Effective
2011-03-25
Models covered
6

Last live check: 2026-10-04

Printed from https://aircraftdirectives.com/ad/2010-26-51 · 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

2010-26-51

FR doc 2011-4465 · 76 FR 13059

AD 2010-26-51Published 2011-03-10Effective 2011-03-25

Supersedes 2009-08-03

Supersedence is read from the Federal Register text of the newer AD — the FAA publishes no structured field for it — and names only ADs held in our index.

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.

Prompted by another incident in which the tail rotor blade (blade) tip weight separated from a blade during flight causing vibration.

Full official abstract

This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (AD) 2010-26-51, which was sent previously to all known U.S. owners and operators of the specified model helicopters by individual letters. This AD also supersedes existing AD 2009-08-03. This AD is prompted by another incident in which the tail rotor blade (blade) tip weight separated from a blade during flight causing vibration. This unsafe condition led to the determination that additional blades could be affected and should be added to the applicability. The actions specified by this AD are intended to prevent loss of the blade tip weight, loss of a blade, and subsequent loss of control of the helicopter.

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View on Federal Register (opens in a new tab) View this AD in FAA DRS (opens in a new tab) Print AD packet (opens the full Federal Register document in a new tab)

Applies to 6 models in our index