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FAA
FAA AC 33.83-1 : 2009

FAA AC 33.83-1 : 2009

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Current

The latest, up-to-date edition.

COMPARATIVE METHOD TO SHOW EQUIVALENT VIBRATORY STRESSES AND HIGH CYCLE FATIGUE CAPABILITY FOR PARTS MANUFACTURER APPROVAL OF TURBINE ENGINE AND AUXILIARY POWER UNIT PARTS

Available format(s)

Hardcopy , PDF

Language(s)

English

Published date

01-01-2009

Publisher

Federal Aviation Administration

1. Purpose
2. Applicability
3. Related References
4. Definitions
5. Background
6. Prerequisites to Modal and Fatigue Testing - Geometry,
    Mass, and Material
7. Compliance with section 33.83 Requirements
8. Comparative Method for Assessing Modal Characteristics
9. Comparative Method of Assessing Fatigue Strength
10. Maintaining Compliance to section 33.83

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).

DocumentType
Standard
Pages
14
PublisherName
Federal Aviation Administration
Status
Current

FAA AC 33-10 : 2014 STATISTICAL ANALYSIS CONSIDERATIONS FOR COMPARATIVE TEST AND ANALYSIS BASED COMPLIANCE FINDINGS FOR TURBINE ENGINE AND AUXILIARY POWER UNIT REPLACEMENT, REDESIGN AND REPAIRED PARTS

FAA 8110.42 : 2014 PARTS MANUFACTURER APPROVAL PROCEDURES
FAA AC 33.83 : 2006 TURBINE ENGINE VIBRATION TEST

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Hardcopy - English
PDF - English
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