Aircraft avionics

[Flight Deck]

Designed from the outset to be truly competitive in world markets, the Tu 204-120 incorporates levels of technology seen only in new generation aircraft. This technology is particularly evident in the avionics and flight control systems. The cockpit features a full Electronic Flight Information System (EFIS) based on the 'dark' or 'lights-out' cockpit principle. The aircraft flight control system is fully fly-by-wire with a master and stand-by flight control system each having three independent channels. The master control system can operate independently with one channel failure. In the event of a double channel failure on the master system, control is automatically transferred to the stand-by system. The back-up actuation system uses irreversible hydraulic units. The aircraft hydraulic system comprises three independent systems. There are two engine-driven constant-pressure pumps in each main system with back-up from an electrically driven pump. Redundancy is further complemented by an additional hydraulic pump driven by a ram air turbine which is extended into the air flow in case of both engine and electrical pump failures. The electrical power supply to the control systems is supplied from the main AC system with a full alternate AC system and an additional standby DC supply system.

Tu 204. Primary avionics architecture

The primary features of the design are that all major avionics systems are fully ARINC compatible with a triplicated fly-by-wire primary flight control system. The Tu 204-120 control system has been designed, tested and produced to meet - and in some cases exceed - the requirements of the FAA's DO-160C and DO-178A design objectives.

• Full ARINC compatibility in all major avionics systems.
• Triplicated "fly-by-wire" primary flight control systems with two channels of manual reversion.
• Full "EFIS" cockpit with full "EICAS" (engine indication display/crew alerting system) in six full color large-format displays.
• ARINC "429" Digital Data Bus.
• Dual Flight Management System ("FMS") and control/display units (CDU).
• Triplicated Inertial Reference System ("IRS")
• Triplicated Digital Air Data Computer System ("DADCS")
• Dual Auto-Throttle systems.
• Full Communication and Navigation ("Com/Nav") suite including HF radios.
• Ground Proximity Warning System ("GPWS")
• Color weather radar with Windshear detection capability.
• Standby analogue instruments.
• "Dark" or "Lights-Out" flight-deck concept.
• TCAS.
• Multiple aural warnings.

Flight Deck

The combination of the ergonomic cockpit layout and the aircraft's fly-by-wire control systems ensure maximum crew operating efficiency. The control yokes incorporate artificial feel systems and electrical position transmitters and feedback is provided to the flight crew through an automatic yoke control system utilizing digital computers, analogue control units and control lever position transmitters/ rate gyros and normal acceleration sensors. In addition to the third crew position for a flight engineer there is provision in the cockpit for a further, fourth, crew position for an observer.

Advanced design. Dark "Lights-out" quiet flight deck concept. Dual full autoflight control systems (AFCS). Large flat panel with cockpit displays. Efficient working environment. Navigation and communication equipment upgraded to international standards. Dual flight management system (FMS).

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