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- Fonte1
- INTERNATIONAL CIVIL AVIATION ORGANIATION. Annex 8 to the Convention on International Civil Aviation. Airworthiness of aircraft. 11th ed. Montreal, 2010.
- Nota adicional1
- The cyclic pitch control system is designed so that the rotor disc tilts slightly opposite tail rotor thrust when in a hover.
- Contexto
- The cyclic pitch control changes the pitch of each blade as a function of where it is in the plane of rotation. This allows for trimming the helicopter in pitch and roll during forward flight and for maneuvering in all flight conditions.
- The applicant must demonstrate by tests, analysis based on tests, or service experience on similar components, that each propeller blade pitch control system component, including governors, pitch change assemblies, pitch locks, mechanical stops, and feathering system components, can withstand cyclic operation that simulates the normal load and pitch change travel to which the component would be subjected during the initially declared overhaul period or during a minimum of 1,000 hours of typical operation in service.
- Tests shall be conducted to demonstrate proper and reliable functioning of the pitch control system.
- Subárea1
- Aerodynamics
- Related Term
- collective pitch control
- cyclic pitch control
- nose down pitch control
- pitch control effect
- pitch effect
- Português
- comando de passo