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FAA AC 33.70-2 : 2009

Current
Current

The latest, up-to-date edition.

DAMAGE TOLERANCE OF HOLE FEATURES IN HIGH-ENERGY TURBINE ENGINE ROTORS
Available format(s)

Hardcopy , PDF

Language(s)

English

Published date

01-01-2009

CHAPTER 1 - ENHANCED LIFE MANAGEMENT PROCESS
CHAPTER 2 - DAMAGE TOLERANCE ASSESSMENTS
CHAPTER 3 - "SOFT TIME INSPECTION" ROTOR LIFE MANAGEMENT
APPENDIX 1 - MANUFACTURING-INDUCED ANOMALY CALIBRATION TEST CASE
APPENDIX 2 - DEFAULT ANOMALY DISTRIBUTION CURVES
APPENDIX 3 - DEFAULT POD APPLICABILITY
APPENDIX 4 - DEFAULT POD CURVES
APPENDIX 5 - DEFINITION OF A HOLE FOR MANUFACTURING ANOMALY
             ASSESSMENTS
APPENDIX 6 - MANUFACTURING CREDITS
APPENDIX 7 - SURFACE (MANUFACTURING INDUCTED ANOMALY) DAMAGE
             TOLERANCE ASSESSMENT

Gives definitions, guidance, and acceptable methods, but not the only methods, that may be used to demonstrate compliance with requirements in section 33.70 of Title 14 of the Code of Federal Regulations related to the integrity of engine life-limited parts.

DocumentType
Standard
Pages
48
PublisherName
Federal Aviation Administration
Status
Current

SAE AIR 1537 : 1996 REPORT ON AIRCRAFT ENGINE CONTAINMENT
FAA AC 33.70-1 : 2009 GUIDANCE MATERIAL FOR AIRCRAFT ENGINE LIFE-LIMITED PARTS REQUIREMENTS
FAA AC 33-3 : 0 TURBINE AND COMPRESSOR ROTORS TYPE CERTIFICATION SUBSTANTIATION PROCEDURES
SAE AIR 4003 : 1991 REPORT ON AIRCRAFT ENGINE CONTAINMENT
FAA AC 33.14-1 : 0 DAMAGE TOLERANCE FOR HIGH ENERGY TURBINE ENGINE ROTORS

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