ICE PROTECTION SYSTEM
Helicopter ice protection system is designed to protect from icing the main and tail rotors’ blades, cockpit windshields, Pitot tubes and engines compressors inlet devices.
Helicopter ice protection system comprises: ice protection system of main and tail rotors, ice protection system of engines and dust protection system bypass device, heating of cockpit windshields, heaters automatic temperature control unit, windshield spraying system and windshield wipers.
Main and tail rotors blades are provided with heating elements of electrothermal type. Windshield ice protection system comprises both hot air blowing (air bled from engines compressors) and electrical heating. Windshield wipers and washing fluid spraying system are installed for the purpose of cockpit windshield cleaning. Pitot tube ice protection system is of electrothermal and automatic type.
Bypass channel of dust protection device is heated by hot air bled from engines. Components of compressors inlet devices are heated with hot oil taken from engines.
ELECTRICAL POWER SUPPLY SYSTEM
Electrical power supply system is designed to supply electrical power to the helicopter equipment both in flight and on ground.
Electrical power supply system includes 400 Hz
115/200 V three-phase A.C. generation system, 27V DC generation system, electrical power distribution system, as well as emergency electrical power supply system. Each AC and DC generation system has two independent channels. Power supply of the helicopter equipment during parking in airfield conditions is realized by ground power source.
The power sources of the helicopter primary electrical power supply system, three-phase A.C, are two generators installed on the accessory gearbox of main gearbox. Generator, installed on auxiliary power unit, is independent power supply source of three-phase A.C.
DC generation system is a secondary electrical power supply system is supplied with power from primary three-phase AC electrical power supply system by rectifiers. Two storage batteries are emergency power supply sources in this system.
Information about system functioning and failures is supplied to pilots and displayed in data frame on multifunctional displays.
HELICOPTER INTEGRATED AVIONICS SYSTEM, INSTRUMENTS
Navigation, radio navigation, radio communication and common Mi-38 helicopter equipment, having data communication channels, is combined into Integrated Avionics System (IBKO-38) by means of data exchange management, information management and integrated data processing.
Integrated Avionics System is designed to provide helicopter crew with necessary flight and navigation information, centralized monitoring and control of airborne, radio navigation and radio communication equipment.
Integrated Avionics System comprises:
- two flight management computers;
- information-management field units;
- flight-navigation equipment;
- radio communication equipment;
- airborne monitoring system;
- flight data and cockpit voice recorder.
Standby equipment is used to complete flight in case of failure of IBKO-38 system.
Information-management filed of Integrated Avionics System comprises five multifunctional displays), two multipurpose control and display units, flight-navigation and radio communication equipment control panels and units.
Radio communication equipment set comprises:
- VHF radio station;
- HF radio station;
- emergency locator transmitter;
- portable emergency locator transmitter ;
- radio direction finder, intended for search and rescue operations fulfillment;
- transponder, intended for operation with secondary radars of air traffic control systems, for transmission of helicopter coordinates code signals, registration number, altitude, fuel reserve etc;
- combined unit of intercommunication system and voice information reporting system;
- aircraft “friend or foe” identification.
Airborne monitoring system (BSK-38) is intended to fulfill the following tasks:
- reception and conversion of analog signals and event signals from power plant and common helicopter equipment sensors to digital code;
- reception of information from airborne equipment via code communication line;
- information output to adjacent systems via code communication line;
- self-test for proper functioning in flight and on ground.
Flight data and cockpit voice recorder is intended for collection, recording and safe keeping of flight parameters and crew-members talks, as well as marking of recorder unit location in case of falling into water.
Warning and caution system is provided in the helicopter. Annunciators are located on pilots’ instrument panel and center console.