FAA AC 33.15-1 : 0
Current
The latest, up-to-date edition.
MANUFACTURING PROCESS OF PREMIUM QUALITY TITANIUM ALLOY ROTATING ENGINE COMPONENTS
Hardcopy , PDF
English
Important note : All end users must be registered with an Account prior to user licenses being assigned.
1 PURPOSE
2 RELATED READING MATERIAL
3 DEFINITIONS
4 BACKGROUND
5 GENERAL
6 RAW MATERIALS & STORAGE
7 CONSOLIDATION AND MELTING
8 BILLET CONVERSION, DISK FORGING, AND NDT
APPENDIX 1 MINIMUM RECOMMENDED PROCEDURE FOR 3D INCLUSION
CHARACTERIZATION
Gives guidance and information for compliance with the provisions under Title 14 under the Code of Federal Regulations, part 33 (14 CFR 33) pertaining to the materials suitability and durability requirements, section 33.15, as applicable to the manufacture of titanium alloy high energy rotating parts of aircraft engines.
| DocumentType |
Standard
|
| Pages |
20
|
| PublisherName |
Federal Aviation Administration
|
| Status |
Current
|
| FAA AC 33.15-2 : 2011 | MANUFACTURING PROCESSES FOR PREMIUM QUALITY NICKEL ALLOY FOR ENGINE ROTATING PARTS |
| FAA AC 33-2 : 2013 | GENERAL TYPE CERTIFICATION GUIDELINES FOR TURBINE ENGINES |
| FAA AC 33-4 : 0 | DESIGN CONSIDERATIONS CONCERNING THE USE OF TITANIUM IN AIRCRAFT TURBINE ENGINES |
| FAA AC 33-3 : 0 | TURBINE AND COMPRESSOR ROTORS TYPE CERTIFICATION SUBSTANTIATION PROCEDURES |
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