|20-47||ANM-100||Exterior Colored Band around Exits on Transport Airplanes Sets forth an acceptable means, but not the only means, of complying with the requirement for a 2-inch colored band outlining exits required to be openable from the outside on transport airplanes.||02-08-1966|
Establishing and Implementing Limit of Validity to Prevent Widespread Fatigue Damage
This advisory circular (AC)offers guidance on compliance with Title 14 Code of Federal Regulations (14 CFR) 26.21, 26.23, 121.1115, and 129.115. It tells design approval holders of transport category airplanes how to establish a limit of validity of the engineering data that supports the structural maintenance program (hereafter referred to as LOV) for those airplanes. It also tells design approval holders how to address maintenance actions that have been determined necessary to support an LOV. It tells operators of those airplanes how to incorporate the LOV into their maintenance programs. Finally, this AC provides guidance to anyone wishing to extend an LOV. Guidance for establishing an LOV for airplanes whose type certificate was applied for after (XXXX) is contained in AC 25.571-1X. Guidance for extending an LOV approved under § 25.571, § 26.21, or § 26.23 can be found here. The actions described in this AC are meant to prevent widespread fatigue damage (WFD) in the transport airplane fleet up to the LOV.
|25.1353-1A||ANM-100||Electrical equipment and installations||10-22-2007|
|25.899-1||ANM-100||Electrical bonding and protection against static electricity This advisory circular (AC) provides guidance for demonstrating compliance with the transport category airplane certification requirements of § 25.899 Electrical bonding and protection against static electricity||10-22-2007|
|25.1362-1||ANM-100||Electrical Supplies for Emergency Conditions This advisory circular (AC) provides guidance for demonstrating compliance with the transport category airplane certification requirements of § 25.1362, Electrical supplies for emergency conditions.||10-22-2007|
|25.1365-1||ANM-100||Electrical Appliances, Motors, and Transformers This advisory circular (AC) provides guidance for demonstrating compliance with the transport category airplane certification requirements of § 25.1365 Electrical appliances, motors, and transformers.||11-27-2007|
|25-26||ANM-100||Development of standard wiring practices documentation||11-14-2007|
Development of Transport Category Airplane Electrical Wiring Interconnection Systems Instructions for Continued Airworthiness Using and Enhanced Zonal Analysis Procedure
Airworthiness Program for Airplane Systems/Fuel Tank Safety (EAPAS/FTS)” rule. That rule requires design approval holders (DAHs) and applicants to develop instructions for continued airworthiness (ICA) consisting of maintenance and inspection tasks, intervals, and procedures for the representative airplane’s electrical wiring interconnection systems (EWIS) for each affected type design. The DAH must also review any fuel tank system ICA it has developed in compliance with Special Federal Aviation Regulation No. 88 (SFAR 88) in order to ensure compatibility with the EWIS ICA, including minimizing redundant requirements. The DAH must then submit the EWIS ICA to the Federal Aviation Administration (FAA) oversight office for review and approval.
This AC provides guidance for developing maintenance and inspection instructions for EWIS using an enhanced zonal analysis procedure (EZAP). For the purposes of this AC, the term “maintenance” encompasses both “maintenance” and “preventive maintenance,” as those terms are defined in Title 14, Code of Federal Regulations (14 CFR) 1.1. For airplane models whose maintenance programs already include a zonal inspection program, the logic described here provides guidance on improving those programs. For airplanes without a zonal inspection program, use of this logic will produce zonal inspections for wiring that can be added to the existing maintenance program. This AC contains information that can be used by operators to improve EWIS maintenance practices. It stresses the importance of inspecting EWIS and
promotes a philosophy of “protect and clean as you go” when performing maintenance, repair, or alterations on an airplane.
|120-93||ANM-100||Damage Tolerance Inspections for Repairs and Alterations This advisory circular (AC) provides guidance material for Type Certificate (TC) Holders, Supplemental Type Certificate (STC) Holders, and operators to comply with requirements in the Aging Airplane Safety Act to ensure the airworthiness of aging airplane parts and components. The Aging Airplane Safety Rule that supports the Act specifies incorporating damage tolerance-based inspections into an operator’s continuous airworthiness maintenance program. These inspections will help ensure the integrity of fatigue critical structure on transport category airplanes operated in air transportation. This guidance will provide persons who have developed repairs and alterations with a means to develop damage tolerance data to be used to determine damage tolerance inspections for repairs and alterations that affect fatigue critical structure. This AC will give guidance on developing compliance documents, schedules and plans that will assist in developing and incorporating damage tolerance inspections into maintenance programs of certain transport category airplanes with respect to repairs and alterations.||11-20-2007|
|120-73||ANM-100||Damage Tolerance Assessment of Repairs to Pressurized Fuselages Provides guidance to operators of certain transport category airplanes operated under 14 CFR Parts 91, 121, 125, and 129. The guidance provides an acceptable means of compliance with the regulations that require incorporating FAA-approved “repair assessment guidelines” into an operator’s FAA-approved maintenance or inspection program. The means of compliance described is intended to provide guidance to supplement the engineering and operational judgment that must form the basis of any compliance findings relative to repair assessments for pressurized fuselages.||12-14-2000|
Compliance with Requirements of § 121.321, Operations in Icing
This advisory circular (AC) describes an acceptable means for showing compliance with the requirements of Title 14, Code of Federal Regulations (14 CFR) 121.321, Operations in Icing. Part 121 contains the aircraft operating requirements applicable to domestic, flag, and supplemental operations. This AC provides guidance for:
a. Using visible moisture and temperature as a means for the flightcrew to know when the airframe ice protection system (IPS) must be activated.
b. Developing acceptable procedures for activating and deactivating the airframe IPS.
c. Installing a primary or advisory ice detection system.
|25.1357-1A||ANM-100||Circuit protective devices||10-22-2007|
Chemical Oxygen Generator Security Standards
This advisory circular (AC) provides guidance for an acceptable means of showing compliance with the requirements of Title 14, Code of Federal Regulations(14 CFR) 25.795(d), Chemical oxygen generators. Section 25.795(d) requires each chemical oxygen generator (COG) or its installation to be designed so it meets one of several criteria. The means of compliance described in this document provides guidance to supplement the engineering and operational judgment that must form the basis of any compliance findings relative to a COG installed on an airplane.
|25.1701-1||ANM-100||Certification of Electrical Wiring Interconnection Systems on Transport Category Airplanes This Advisory Circular (AC) provides guidance for certification of electrical wiring interconnection systems (EWIS) on transport category airplanes in accordance with 14 CFR part 25, subpart H, sections §§25.1701 through 25.1739 and sections H25.4 and H25.5 of Appendix H to part 25.||12-04-2007|
|25.795-5||ANM-100||Cargo Compartment Fire Suppression This advisory circular (AC) describes an acceptable means for showing compliance with the requirements of Title 14, Code of Federal Regulations (14 CFR), part 25, § 25.795(b)(3), “Cargo compartment fire suppression.” This section requires that the fire suppression system for the cargo compartment be designed to withstand a sudden and extensive explosion and fire, such as could be caused by an explosive or incendiary device. The means of compliance described in this document provides guidance to supplement the engineering and operational judgment that must form the basis of any compliance findings relative to the design of fire suppression systems for the cargo compartment.||10-24-2008|
|25.735-1||ANM-100||Brakes and Braking Systems Certification Tests and Analysis Describes an acceptable means for obtaining FAA airworthiness approval concerning new or revised requirements for braking systems, and associated test conditions for braking systems, installed in transport category airplanes.||04-10-2002|
|20-99||ANM-100||Antiskid and Associated Systems Provides an acceptable means, but not the only means, of complying with the requirement that anti-skid and associated systems must be designed so that no probable malfunction will result in a hazardous loss of braking or directional control of an airplane.||05-27-1977|
|120-94||ANM-100||Aircraft Electrical Wiring Interconnection Systems Training Program||11-20-1997|
|33-83A||ANE-111||Turbine Engine Vibration Test||09-29-2006|
Statistical Analysis Considerations for Comparative Test and Analysis Based Compliance Findings for Turbine Engine and Auxiliary Power Unit Replacement, Redesign and Repaired Parts
a. This advisory circular (AC) describes acceptable statistical methods, but not the only methods, to help develop substantiating data for comparative test and analysis compliance findings. The findings support the Federal Aviation Administration (FAA) approval of turbine engine and auxiliary power unit (APU) replacement, redesign and repaired parts produced under:
(1) Parts manufacturer approval (PMA),
(2) Type Certificate (TC),
(3) Supplemental Type Certificate (STC), or
(4) Repair or alteration.
b. The AC describes statistical principles that can be used to help determine adequate sample sizes for a comparative showing of equivalency of parts from different design or manufacturing processes. The guidance in this AC is acceptable for determining sample sizes and/or populations of specimens. The resulting data may be used to support a showing of compliance to the airworthiness requirements of Title 14 of the Code of Federal Regulations (14 CFR) 21.303, 14 CFR part 33, 14 CFR part 43 and Technical Standard Order (TSO) C77.
Ratings and Operating Limitations for Turbine Engines (Sections 33.7 and 33.8)
This advisory circular (AC) provides information and guidance on turbine engine compliance under part 33 of Title 14 of the Code of Federal Regulations (14 CFR), specifically §§ 33.7, Engine ratings and operating limitations, and 33.8, Selection of engine power and thrust ratings. This AC also provides information on preparing the data needed for the type certification data sheet (TCDS) specified in § 33.7(a).
Propeller Vibration and Fatigue
This advisory circular (AC) provides guidance and describes one method, but not the only method, for demonstrating compliance with §§ 23.907 and 25.907 of Title 14 of the Code of Federal Regulations (14 CFR) for the evaluation of vibratory stresses on propellers installed on airplanes. This evaluation uses fatigue and structural data obtained in accordance with 14 CFR part 35.
Propeller Fatigue Limits and Evaluation
This advisory circular (AC) provides guidance and describes methods, but not the only methods, for demonstrating compliance with § 35.37, Propeller fatigue limits and evaluation, of Title 14 of the Code of Federal Regulations (14 CFR).
|35.16-1||ANE-111||Propeller Critical Parts||01-17-2013|
Oxidation, Hot Corrosion, Thermal Fatigue, and Erosion Characteristics Testing to Support 14 CFR, Part 33, § 33.15, Compliancefor 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.