AMC1 29.395 Control system

• ED Decision 2023/001/R found in: CS-29 Amdt 11 - Large Rotercraft (Feb 2023)

AMC1 29.395 Control system ED Decision 2023/001/R This AMC supplements FAA AC 29-2C, § AC 29.395 and should be used in conjunction with that AC when demonstrating compliance with [CS 29.395](#_DxCrossRefBm1178331808). The design reaction loads prescribed in [CS 29.395](#_DxCrossRefBm1178331808) for the flight control system should apply to the part of the control system from the pilot cockpit control sticks/pedals to the main/tail rotor servo-actuators. The remaining part of the flight control systems located between the attachment of the servo-actuators and the (main/tail) blades (i.e. rotating parts, servo-actuators and their attachments) should be substantiated to the highest of: — maximum loads expected in service (limit loads) as per [CS 29.301](#_DxCrossRefBm1178331782), [CS 29.305](#_DxCrossRefBm1178331784) and [CS 29.547](#_DxCrossRefBm1178331812) (nominal conditions); — maximum loads for a single failure of the hydraulic system leading to an operating hydraulic overpressure; — the maximum loads due to a jamming of the flight control system (rotating parts). The maximum pilot loads from [CS 29.397](#_DxCrossRefBm1178331799) to [CS 29.399](#_DxCrossRefBm1178331811) should be added to these loads appropriately. [Amdt No: 29/11] ##### AMC1 29.395 Control system *ED Decision 2023/001/R* This AMC supplements FAA AC 29-2C, § AC 29.395 and should be used in conjunction with that AC when demonstrating compliance with [CS 29.395](#_DxCrossRefBm1685772273). The design reaction loads prescribed in [CS 29.395](#_DxCrossRefBm1685772273) for the flight control system should apply to the part of the control system from the pilot cockpit control sticks/pedals to the main/tail rotor servo-actuators. The remaining part of the flight control systems located between the attachment of the servo-actuators and the (main/tail) blades (i.e. rotating parts, servo-actuators and their attachments) should be substantiated to the highest of: — maximum loads expected in service (limit loads) as per [CS 29.301](#_DxCrossRefBm1685772247), [CS 29.305](#_DxCrossRefBm1685772249) and [CS 29.547](#_DxCrossRefBm1685772277) (nominal conditions); — maximum loads for a single failure of the hydraulic system leading to an operating hydraulic overpressure; — the maximum loads due to a jamming of the flight control system (rotating parts). The maximum pilot loads from [CS 29.397](#_DxCrossRefBm1685772264) to [CS 29.399](#_DxCrossRefBm1685772276) should be added to these loads appropriately. [Amdt No: 29/11]