Provides guidance material for acceptable means of demonstrating compliance with the requirements of FAR Part 33, relating to detonation testing for reciprocating aircraft 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.

 

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 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.

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.

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.

Comparative Endurance Test Method to Show Durability for Parts Manufacturer Approval of Turbine Engine and Auxiliary Power Unit Parts

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).

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.

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

Contains guidance relating to type certification of aircraft engines which will constitute acceptable means, although not the sole means, of compliance with the Federal Aviation Regulations.