Home>FAA AC 33.83-1:2009

FAA AC 33.83-1:2009

FAA AC 33.83-1:2009 Comparative Method To Show Equivalent Vibratory Stresses And High Cycle Fatigue Capability For Parts Manufacturer Approval Of Turbine Engine And Auxiliary Power Unit Parts Specifies a comparative test and analysis method that may be used for turbine engine or auxiliary power unit (APU) blades or vanes when produced under parts manufacturer approval (PMA).

More details

Download

PDF AVAILABLE FORMATS IMMEDIATE DOWNLOAD
$17.60 tax incl.

$40.00 tax incl.

(price reduced by 56 %)

1000 items in stock

Table of Contents

1.Purpose
2.Applicability
3.RelatedReferences
4.Definitions
5.Background
6.PrerequisitestoModalandFatigueTesting-Geometry,
Mass,andMaterial
7.Compliancewithsection33.83Requirements
8.ComparativeMethodforAssessingModalCharacteristics
9.ComparativeMethodofAssessingFatigueStrength
10.MaintainingCompliancetosection33.83

Abstract

Specifies a comparative test and analysis method that may be used for turbine engine or auxiliary power unit (APU) blades or vanes when produced under parts manufacturer approval (PMA).

Contact us