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.
The design reaction loads prescribed in CS 29.395 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, CS 29.305 and CS 29.547 (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 to CS 29.399 should be added to these loads appropriately.
[Amdt No: 29/11]
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