This advisory circular (AC) provides guidance to demonstrate compliance with Title 14 of the Code of Federal Regulations (14 CFR), Section 33.74, Continued Rotation and Section 33.92, Rotor Locking Tests.

 a. This advisory circular (AC) provides a method of compliance for the test requirements of Title 14, of the Code of Federal Regulations (14 CFR) 33.84 (engine overtorque test) when the applicant chooses to run that test as part of the endurance test of § 33.87. It also provides information and guidance on the test requirements of § 33.85 (calibration test), § 33.87 (endurance test), and § 33.93 (teardown inspection).

b. This AC applies to part 33 type certification endurance testing of all classes of 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.

This advisory circular (AC) provides guidance and describes acceptable methods, butnot the only methods, for demonstrating compliance with the engine control systems requirements of § 33.28 of Title 14 of the Code of Federal Regulations (14 CFR part 33) at amendment level 3326.

This advisory circular (AC) provides general guidance concerning type certification projects for aircraft turbine engines. This AC applies to certain sections of Title 14 of the Code of Federal Regulations (14 CFR) parts 21, 33, and 45, and describes or references methods of compliance that may be acceptable for engine type certification work. This guidance is general in nature, and where necessary, further reference is made to other documents, which may be the primary source for information on a particular subject.

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.

This advisory circular (AC) provides guidance for developing substantiation data to support the design approval of critical and complex turbine engine and auxiliary power unit (APU) parts produced under parts manufacturer approval (PMA). This guidance is for the comparative test and analysis method used to show compliance to the airworthiness requirements under test and computation, per § 21.303 of Title 14 of the Code of Federal Regulations(14 CFR). This method supports showing the engine or APU still complies with 14 CFR part 33 and Technical Standard Order (TSO) C77.

b. Additionally, this AC provides information on developing a continued operational safety (COS) plan and part numbering for turbine engine parts.

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.

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").

This advisory circular (AC) provides guidance and describes acceptable methods, but not the only methods, for demonstrating compliance with the safety analysis requirements of § 33.75 of Title 14 of the Code of Federal Regulations (14 CFR). The information provided in this AC replaces the guidance in AC 33.75-1, issued on March 4, 2005.