Provides information and guidance concerning compliance with Part 23 for self-locking nuts used on bolts subject to rotation in operation.

Provides information and guidance concerning compliance with Part 23 of the Federal Aviation Regulations (FAR) applicable to evaluation of empennage design flight loads on configurations where the horizontal tail surfaces are supported by the vertical tail, or have appreciable dihedral.

Provides information and guidance regarding compliance with Part 23 of the Federal Aviation Regulations (FAR) applicable to dynamic testing of airplane seats.

Provides information and guidance concerning an acceptable means of showing compliance with Part 23 through amdt.23-45 of the Federal Aviation Regulations applicable to replacing reciprocating engines with gas turbine engines (turbopropeller, turbojet, or turbofan).

Sets forth acceptable means of compliance with Part 23 of the Federal Air Regulations (FAR), for approval/certification to use automobile gasoline with or without oxygenates (alcohol, ethers, etc.) in Part 23 airplanes. These procedures also apply to those airplanes approved/certificated under previous regulations superseded by Part 23.

Provides information and guidance concerning an acceptable means of compliance with Part 3 of the Civil Air Regulations (CAR) and Part 23 of the Federal Aviation Regulations (FAR), applicable to approval procedures for certification of alternate fuels. Also apply to those airplanes approved under Part 4a of the CAR and Aeronautics Bulletin 7a.

Establishes an acceptable means, but not the only means, of obtaining FAA airworthiness approval for the installation of a TAWS that has been approved under Technical Standard Order (TSO)-C151A, Terrain Awareness and Warning System, in a Part 23 airplane. The FAA’s TSO process is a means for obtaining FAA design and performance approval for an appliance, system, or product; however, the TSO does not provide installation approval. This AC serves to provide guidance for designing an acceptable installation for a TAWS that complies with TSO-C151a. The guidance provided is specific to installations of these systems on airplanes certificated under Title 14 of the Code of Federal Regulations Part 23. It describes the airworthiness considerations for such installations as they apply to the unique features of the TAWS and the interface of the TAWS with other systems on the airplane.

Provides an acceptable means of compliance with Part 23 of the FAR for type certification of certain small airplanes.

Provides information and guidance concerning an acceptable means, but not the only means, of compliance with Title 14 of the Code of Federal Regulations (14 CFR) part 23. It is applicable to the material and process specifications, or other documents, used to ensure sufficient control of composite prepreg materials in normal, utility, acrobatic, and commuter category airplanes. Material in this AC is neither mandatory nor regulatory in nature and does not constitute a regulation.

Presents information and guidance to provide one means, but not the only means, of complying with Section 23.629, Flutter (including flutter, airfoil divergence, and control reversal) of Part 23 of the Federal Aviation Regulations.

The AC acknowledges the General Aviation Manufacturers Association (GAMA) Publication #12, “Recommended Practices and Guidelines for an Integrated Flightdeck/Cockpit in a 14 CFR (or equivalent) Certificated Airplane,” as an acceptable means for showing compliance with applicable requirements for electronic displays in part 23 airplanes. Guidance in AC 23.1311, SAE, and RTCA documents was used in developing the GAMA Publication #12. (GAMA Publication #12 is available from GAMA. Their website is 222.gama.aera.) A combined industry and FAA team developed the GAMA publication.

Sets forth on method that may be used to show compliance to the requirements contained within CFR, part 23, 23.1523, which prescribes the certification requirements for minimum flight crew on part 23 airplanes.

Sets guidelines for using the Approved Model List (AML) Supplemental Type Certificate (STC) process for the installation approval of avionics for 14 CFR, part 23 airplanes.

Provides information and guidance concerning an acceptable means of demonstrating compliance with the requirements of Part 23 of the Federal Aviation Regulations (FAR) regarding fatigue and fail-safe evaluation of metallic airplane structure.

Provides information and guidance concerning acceptable means, but not the only means, of complying with Title 14 of the Code of Federal Regulations (14 CFR) part 23 Subpart C and portions of Subpart D. It consolidates the substance of existing Civil Aeronautics Administration (CAA) and Federal Aviation Administration (FAA) letters into a single reference. It also presents information from certain presently existing AC's that cover general topics and specific airworthiness standards. Material in this AC is neither mandatory nor regulatory. AC methods may be freely chosen, or ignored, by an applicant who seeks to demonstrate regulatory compliance. Use of FAA published AC guidance frequently speeds the design approval process for an applicant.

This advisory circular (AC) sets forth an acceptable means of showing compliance with Title 14 Code of Federal Regulations (14 CFR) part 23 and Civil Air Regulations (CAR) 3 for the flammability testing of systems and equipment in normal, utility, acrobatic, and commuter category airplanes and airships. This AC applies to Subparts D and F of part 23 and applicable sections of CAR 3 as listed in Paragraph 6a. The revision addresses systems and equipment and references other general ACs that provide guidance for other subparts of part 23.

This advisory circular (AC) sets forth an acceptable means of showing compliance with Title 14 Code of Federal Regulations (14 CFR), part 23, for the certification of airplanes originally certificated to either European Aviation Safety Agency (EASA) CS-VLA or Joint Aviation Requirements (JAR) JAR-VLA.