« Back to Advisory Circulars Main Page

Will search within "Airworthiness Standards: Aircraft Engines" only. Search all ACs.

1 - 25 of 36 results.
First Previous [1] 2 Next Last
Number Office Title Date
33.90-1 ANE-110 Initial Maintenance Inspection (IMI), 14 CFR §33.90, Test for Turbine Engines Initial Maintenance Inspection (IMI), 14 CFR §33.90, Test for Turbine Engines 03-05-2004
33.87-2 ANE-110 Comparative Endurance Test Method to Show Durability for Parts Manufacturer Approval of Turbine Engine and Auxiliary Power Unit Parts Comparative Endurance Test Method to Show Durability for Parts Manufacturer Approval of Turbine Engine and Auxiliary Power Unit Parts 06-25-2009
33.87-1 ANE-111 Calibration Test Endurance Test and Teardown Inspection for Turbine Engine Certification (§§ 33.85, 33.87, 33.93) Provides information and guidance on acceptable methods, but not only methods, of compliance with the test requirements of § 33.85 (Calibration test) § 33.87 (endurance test), and §33.93 (teardown inspection) of Title 14 of the Code of Federal Regulations (14 CFR Part 33). 04-13-2006
33.83-1 ANE-111 Comparative Method to Show Equivalent Vibratory Stresses and High Cycle Fatigue Capability for Parts Manufacturer Approval of Turbine Engine and Auxiliary Power Unit Parts

This advisory circular (AC) describes 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). PMA applicants may use this comparative modal and high-cycle fatigue (HCF) method to show the vibratory stresses and HCF capability of their proposed blades or vanes are equivalent to those of the type design parts. This method supports showing that the engine or APU still complies with part 33 of Title 14 of the Code of Federal Regulations (14 CFR part 33) or Technical Standard Order (TSO) C77.

09-08-2009
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
33.76-1A ANE-111 Bird Ingestion Certification Standards

This advisory circular (AC) provides guidance and acceptable methods, but not the only methods, that may be used to demonstrate compliance with the bird ingestion requirements of Title 14 of the Code of Federal Regulations (14 CFR) § 33.76. Although this AC does refer to regulatory requirements that are mandatory, this AC is not, in itself, mandatory. This AC neither changes any regulatory requirements, nor authorizes changes in, or deviations from, the regulatory requirements.

08-07-2009
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
33.75-1A ANE-110 Guidance Material For 14 CFR 33.75, Safety Analysis 09-26-2007
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
33.74-92-1A ANE-110 Turbine Engine Continued Rotation and Rotor Locking 07-23-2003
33.70-2 ANE-111 Damage Tolerance of Hole Features in High-Energy Turbine

 

This advisory circular (AC) provides definitions, guidance, and acceptable methods, but not the only methods, that may be used to demonstrate compliance with requirements in § 33.70 of Title 14 of the Code of Federal Regulations related to the integrity of engine life-limited parts. Section 33.70 contains requirements applicable to the design and life management of propulsion system life-limited parts, including high-energy rotating parts.   This AC presents a damage tolerance approach which can be used to address manufacturing and operationally-induced anomalies in turbine engine rotating part hole features. This approach can be readily integrated with the existing “safe-life” process for high-energy rotors to produce an enhanced life management process. This approach does not replace existing safe-life methodology but supplements it. In the context of damage tolerance, this AC is not intended to allow operation beyond the component manual life limit set using the existing safe life approach which limits the useful rotor life to the minimum number of flight cycles required to initiate a crack. Rotor failure modes for which full containment of high-energy debris can be demonstrated are excluded from the procedures outlined in this AC and need not be accounted for in the overall risk assessment.
08-28-2009
33.70-1 ANE-111 Guidance Material for Aircraft Engine Life-Limited Parts Requirements 07-31-2009
33.7-3A ANE-111 FAA Certification Policy for Turbine Engine Lubricating Oils Qualified to AS5780 04-20-2007
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
33.63-1 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
33.47-1 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
33.4-3 ANE-111 Instructions for Continued Airworthiness, Aircraft Engine High Intensity Radiated Fields (HIRF) and Lightning Protection Features 09-16-2005
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
33.4-1 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
33.28-2 ANE-110 Guidance Material for 14 CFR 33.28, Reciprocating Engine, Electrical and Electronic Engine Control Systems Provides guidance and acceptable methods, but not the only methods, that may be used by designers of reciprocating engine electronic control systems to demonstrate compliance with §33.28 of Title 14 of the Code of Federal Regulations (14 CFR 33.28), Electrical and electronic engine control systems. 08-13-2003
33.28-1 ANE-110 Compliance Criteria for 14 CFR §33.28, Aircraft Engines, Electrical and Electronic Engine Control Systems This advisory circular (AC) provides guidance and acceptable methods, but not the only methods, that may be used to demonstrate compliance with 14 CFR 33.28, Electrical and Electronic Engine Control Systems. Like all AC material, this AC is not, in itself, mandatory and does not constitute a regulation. While these guidelines are not mandatory, they are derived from extensive Federal Aviation Administration (FAA) and industry experience in determining compliance with the pertinent regulations. 06-29-2001
33.19-1 ANE-110 Guidance Material for 14 CFR §33.19, Durability, for Reciprocating Engine Redesigned Parts This advisory circular (AC) provides guidance and acceptable methods, but not the only methods, that may be used to demonstrate the redesigned parts for reciprocating engines comply with the requirements of §33.19 of Title 14 of the Code of Federal Regulations (14 CFR). This AC addresses major types design changes, parts manufacturing approvals (PMA), and supplemental type certificates (STC) for drive system or structural parts in reciprocating engines. Like all AC material, this AC is not, in itself, mandatory and does not constitute a regulation. While these guidelines are not mandatory, they are derived from extensive Federal Aviation Administration (FAA) and industry experience in determining compliance with the pertinent regulations. 09-27-2004
33.17-1A ANE-111 Engine Fire Protection

This advisory circular (AC) provides definitions, guidance, and acceptable methods, but not the only methods, that may be used to demonstrate compliance with the engine fire protection requirements of Title 14 Code of Federal Regulations (14 CFR 33.17). The guidance provided in this AC supersedes information contained in AC 33-2B titled "Aircraft Engine Type Certification Handbook" (Chapter 3, Section 22, titled "Section 33.17, Fire Prevention").

08-03-2009
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
33.14-1 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
1 - 25 of 36 results.
First Previous [1] 2 Next Last