FAA AC 33.83-1 : 2009
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
Hardcopy , PDF
English
01-01-2009
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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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