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Airworthiness Directive

AD 95-03-03 60 FR 11615 Active

Federal Aviation Administration · 14 CFR part 39

FR document
95-4248
Amendment
39-9140
Published
1995-03-02
Effective
1995-03-17
Models covered
1
Last live check
2026-09-30

Printed from https://aircraftdirectives.com/ad/95-03-03 · 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

95-03-03

FR doc 95-4248 · 60 FR 11615

AD 95-03-03Published 1995-03-02Effective 1995-03-17

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 an initial and repetitive inspections, and specified rework or retirement, as necessary, of the propeller hub assemblies and propeller blades.

Full official abstract

This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller Inc. Model HC-B4TN-3/ T10173F(N)(B,K)-12.5 and HC-B4TN-3A/T10173F(N)(B,K)-12.5 propellers installed on Beech A100 and A100A aircraft. This action requires an initial and repetitive inspections, and specified rework or retirement, as necessary, of the propeller hub assemblies and propeller blades. This amendment is prompted by a determination that the current hub design and blade repair limits do not adequately protect against initiation of fatigue cracks in the propeller hub arm bore and do not prevent the resonant speed of the propeller from shifting into the permitted ground idle operating range. The actions specified in this AD are intended to prevent initiation of fatigue cracks in the propeller hub arm bore and subsequent progression to failure, with departure of the hub arm and blade, that may result in loss of aircraft control.

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Applies to 1 model in our index