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Number Office Title Date
33.4-2 ANE-110 Instructions for Continued Airworthiness: In-Service Inspection of Safety Critical Turbine Engine Parts at Piece-Part Opportunity Instructions for Continued Airworthiness: In-Service Inspection of Safety Critical Turbine Engine Parts at Piece-Part Opportunity 03-08-2001
33.76-1 ANE-110 Bird Ingestion Certification Standards

Provide guidance and acceptable methods, but not the only methods, for demonstrating compliance with bird ingestion requirement of § 33.76 of the Federal Aviation Regulations, Title 14 of the Code of Federal Regulations

01-19-2001
33.14-1 ANE-110 Damage Tolerance for High Energy Turbine Engine Rotors This advisory circular describes an acceptable means for showing compliance with the requirements of section 33.14 of the Federal Aviation Regulations (Title 14, Code of Federal Regulations). Section 33.14 contains requirements applicable to the design and life management of high energy rotating parts of aircraft gas turbine engines. 01-08-2001
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
33.4-1 ANE-110 Instructions for Continued Airworthiness Provides guidance on acceptable methods, but not the only methods, of compliance with section 33.4 of the Federal Aviation Regulations, Title 14, Code of Federal Regulations. 08-27-1999
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
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
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
33.47-1 ANE-110 Detonation Testing in Reciprocating Aircraft Engines Provides guidance material for acceptable means of demonstrating compliance with the requirements of FAR Part 33, relating to detonation testing for reciprocating aircraft engines. 06-27-1988
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
33-4 ANE-110 Design Considerations Concerning the Use of Titanium in Aircraft Turbine Engines Provides guidance and acceptable means, not the sole means, by which compliance may be shown with the design requirements of Part 33 to minimize the probability of the occurrence of an internal fire when titanium is used in aircraft turbine engines. 07-28-1983
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
33-3 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

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