|33.15-1||ANE-110||Manufacturing Process of Premium Quality Titanium Alloy Rotating Engine Components Provides guidance 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, 33.15, as applicable to the manufacture of titanium alloy high energy rotating parts of aircraft engines.||09-22-1998|
Oxidation, Hot Corrosion, Thermal Fatigue, and Erosion Characteristics Testing to Support 14 CFR, Part 33, § 33.15, Compliancefor Turbine Engines
This advisory circular (AC) describes an acceptable method, but not the only method, to support certain comparative assessment compliance findings to Title 14 of the Code of Federal Regulations (14 CFR) part 33, § 33.15, Materials, for turbine engine projects. Comparative assessment of certain data is often necessary to show the required functional and durability equivalencies between engine combustor and turbine section parts from different design or manufacturing processes, e.g., parts manufacturer approvals (PMA) versus type design parts. These equivalencies relate to oxidation, hot corrosion, and thermal fatigue and erosion characteristics in the engine environment. This data is necessary to support overall FAA design approval of turbine engine and auxiliary power unit (APU) parts approved under PMA, type certificate (TC) design change, supplemental type certificate (STC), or repair or alteration authority.
Statistical Analysis Considerations for Comparative Test and Analysis Based Compliance Findings for Turbine Engine and Auxiliary Power Unit Replacement, Redesign and Repaired Parts
a. This advisory circular (AC) describes acceptable statistical methods, but not the only methods, to help develop substantiating data for comparative test and analysis compliance findings. The findings support the Federal Aviation Administration (FAA) approval of turbine engine and auxiliary power unit (APU) replacement, redesign and repaired parts produced under:
(1) Parts manufacturer approval (PMA),
(2) Type Certificate (TC),
(3) Supplemental Type Certificate (STC), or
(4) Repair or alteration.
b. The AC describes statistical principles that can be used to help determine adequate sample sizes for a comparative showing of equivalency of parts from different design or manufacturing processes. The guidance in this AC is acceptable for determining sample sizes and/or populations of specimens. The resulting data may be used to support a showing of compliance to the airworthiness requirements of Title 14 of the Code of Federal Regulations (14 CFR) 21.303, 14 CFR part 33, 14 CFR part 43 and Technical Standard Order (TSO) C77.
|33.65-1||ANE-110||Surge and Stall Characteristics of Aircraft Turbine Engines Provides guidance material for acceptable means of demonstrating compliance with the requirements of Part 33 of the Federal Aviation Regulations (FAR) relative to surge and stall characteristics and thrust response of turbine engines. These guidelines do not constitute a regulation and are therefore not mandatory.||12-06-1985|
|33.74-92-1A||ANE-110||Turbine Engine Continued Rotation and Rotor Locking||07-23-2003|
|33.74/92-1A||ANE-110||Turbine Engine Continued Rotation and Rotor Locking Provides guidance and acceptable methods, but not the only methods, that may be used to demonstrate compliance with the continued rotation and rotor locking requirements of part 33 of the Federal Aviation Regulations (FARs).||07-23-2003|
|33-1B||ANE-100||Turbine Engine Foreign Object Ingestion and Rotor Blade Containment Type Certification Procedures Provides guidance and acceptable means, not the sole means, by which compliance may be shown with the design and construction requirements of Part 33 of the Federal Aviation Regulations.||04-22-1970|
|33.78-1||ANE-110||Turbine Engine Power-Loss and Instability in Extreme Conditions of Rain and Hail Provides guidance and acceptable methods, but not the only methods, that may be used to demonstrate compliance with the requirements contained under Title 14 of the Code of Federal Regulations (14 CFR), part 33, sections 33.78(a)(2) and 33.78(c).||02-08-2000|
|33-5||ANE-110||Turbine Engine Rotor Blade Containment/Durability Provides guidance and acceptable methods, but not the only methods, that may be used by an applicant in showing compliance with the turbine engine rotor blade containment requirements of Part 33 of the Federal Aviation Regulations (FAR).||06-18-1990|
|33.63-1||ANE-110||Turbine Engine Vibration This advisory circular (AC) provides guidance and acceptable methods, but not the only methods, that may be used to demonstrate compliance with the vibration requirements of § 33.63 of Title 14 of the Code of Federal Regulations (14 CFR part 33).||07-25-2007|
|33-83A||ANE-111||Turbine Engine Vibration Test||09-29-2006|
|33-3||ANE-100||Turbine and Compressor Rotors Type Certification Substantiation Procedures Sets forth guidance and acceptable means, not the sole means, by which compliance may be shown with the turbine and compressor rotor substantiation requirements in FAR Part 33.||09-09-1968|
|33-6||ANE-110||Weld Repair of Aluminum Crankcases and Cylinders of Piston Engines Provides information and guidance concerning acceptable means, but not the only means, for the development of process specifications for weld repairs on crankcases and cylinders of piston engines.||12-20-1994|