MI-38

GENERAL DESCRIPTION

  • Mi-38 is a new helicopter embodying innovation technologies and best achievements under “Mi” brand. 
  • Mi-38 has a classical single-rotor design. Main elements of Mi-38 fuselage structure are made of aluminum alloys; separate assemblies and parts are made of steel, titanium and composite materials. 
  • Mi-38 features progressive and reliable design of helicopter systems. 
  • State-of-the-art avionics has an integrated architecture. 
  • The helicopter complies with the international aviation standards (FAR-29, CS-29, AP-29). 

Mi-38 helicopter features advanced flight performance. Low-consumption engines, advanced rotor system and high power-to-weight ratio ensure efficient helicopter performance in a wide range of operational conditions. 

Low maintenance labor input is one of Mi-38 advantages. 

The main criterion implemented in the design of Mi-38 is ensuring top level of  flight safety. 

Equipment installed on the helicopter permits to operate it in the following main versions:

  • transport;
  • search-and-rescue;
  • medevac;
  • passenger;
  • VIP cabin.

In comparison with other helicopters of the same class the Mi-38 helicopter features more spacious cargo cabin and higher load carrying capacity, that makes it optimum platform for creation of another special application modifications.

PERFORMANCE

General data at maximum take-off weight

The characteristics are given for the standard atmospheric conditions (ISA).

TRANSPORT

Mi-38 transport version helicopter is designed for cargo transportation inside the cargo cabin and by means of external sling, transportation of personnel (35-37 people on folding seats), as well as erection operations performing.

Mi-38 helicopter has spacious cargo cabin with capacity of 31 m3, this is maximum capacity in this class of helicopters. 

Rear cargo door is provided with loading (cargo) ramp with hydraulic actuator, side door with wide sliding door is provided on the starboard. Loading ramp is adapted for quick loading-unloading, including loading-unloading of self-propelled wheeled and caterpillar vehicles.

Cargoes tie-down is effected using standard tie-down equipment: tie-down cables, straps and cargo net. In order to protect cargo cabin floor surface against damages from transported cargoes installation of removable deck is provided.

Tie-down fittings are used for removable deck attachment.  


CARGO CABIN

SEARCH AND RESCUE (SAR)

Helicopter in search-and-rescue version is intended for application in emergency conditions, requiring fast response for rescue of people and elimination of the consequences of the accident, including areas remote for another search and rescue means.

For the purpose of search and rescue operations carrying out, transportation of rescuers to the area of emergency situation and evacuation of victims and injured persons helicopter cargo cabin is equipped with: 15 folding energy-absorbing seats; 2 berth-stretchers for critically injured persons; rack with medical equipment for rendering medical care, containers with ambulance equipment and oxygen apparatuses; furnishings rack; container with survival equipment sets, attached to cargo floor tie-down fittings; removable hoist boom with cargo hoist system SLG-300M and set of devices for lift and descent of cargo up to 300 kg or people on-board both from land and sea. To ensure good field of view when performing in-flight observing the necessary number of blisters can be installed in cargo cabin instead of standard windows.

MEDEVAC

Mi-38 medevac helicopter is intended for evacuation of 8 lying down cases (or 12 sitting injured persons) and three medical attendants in special medical institutions for rendering them qualified medical care; rendering to injured persons medical care in scope of the first aid with elements of qualified medical care by life-saving indications.

PASSENGER

Mi-38 helicopter in passenger version is intended for transportation of 29 passengers and one flight attendant. Set of passenger’s equipment and furnishings ensures the economy class level of transportation.

VIP

Helicopter in this version is intended for transportation of 12 passengers of “VIP” class, one attendant and one flight attendant. 

Cabin is divided into 3 compartments: forward vestibule, VIP cabin and rear compartment. Compartments are separated from each other by partitions with folding doors.

Arranged in VIP cabin are:

  • VIP armchears seats, provided with, height adjustable headrests, reclining seat backs, foot rests, swinging mechanisms;
  • tables are installed between seats; 
  • four-place sofas;
  • coat room for passengers’ outerwear;
  • table-cabinet for arrangement of onboard entertainment equipment;
  • bar;
  • LCD displays per each side, loudspeaker systems;
  • additional heat and sound insulation;
  • double-glass windows to reduce noise level;
  • blinds on windows.
  • light attendant’s seat;
  • baggage compartment;
  • galley;
  • air conditioning system.

Regarding customer request it is possible to install the additional equipment.

POWER PLANT 

Power plant of the helicopter consists of two ТV7-117V turboshaft engines, manufactured by the Russian company “Klimov”, or two PW127TS engines manufactured by Canadian company Pratt & Whitney. 

Engines transmit torques to main gearbox. Engines are located behind the main gearbox, which reduces the noise level inside the cabin and improves safety in a case of emergency landing. Each engine with its front assembly is attached to the spherical joint on main gearbox and with its rear flange it is attached by means of rods to the fittings on the cargo cabin ceiling. 

Twin engine installation improves safety of helicopter operation and allows continuing flight with one inoperative engine.

Engines have modular design.

Engine is provided with automatic control electronic hydromechanical system. Electronic portion of automatic control electronic-hydromechanical system is made on the basis of digital computer of FADEC type (Full Authority Digital Engine Control).

Engine has independent anti-icing system.


  • Engines air intakes, dust protection device and bypass device

Ambient air is supplied to the engine inlet device through the dust protection device and bypass device (tunnel with flap), with its flap in opened position. Dust protection device (DPD) of multicyclone type is designed in order to protect the engines against dust and extraneous objects from the air supplied to the main engines during helicopter taxiing, takeoff and landing. DPD is installed in the opening of rear part of gearbox compartment cowling panel in front of the engine inlet device. Bypass device is an air intake with air passage to the engine inlet device bypassing the dust protection device, which is provided by opening of turning flap of bypass device. In order to protect against icing bypass channel is heated with hot air bled from the engines.

  • Auxiliary power unit (APU)

Auxiliary power unit (APU) is designed to start main engines using air starters, AC is supplied to the helicopter power supply system and heating of helicopter cabins when engines are not running. APU ТА14-038 is single-shaft gas turbine engine, which is installed under cowlings on the ceiling panel of fuselage central section. Air is supplied from APU to air starter of each engine and to the heating pipes of cargo cabin through the air line, consisting of pipelines and pipes.

APU start is ensured at ambient air temperatures from minus 50 to plus 45°С, at altitude up to 5000 m, and up to 6500m in flight. Maximum time of continuous operation is 5 hours. Number of air bleeding cycles for the purpose of main engines starting is unlimited.

MAIN AND TAIL ROTORS, SWASH PLATE 

  • MAIN ROTOR

In order to generate aerodynamic lift and trust  required for the flight, helicopter is equipped with six-blade main rotor. Owing to the action of the swash plate to the rotor blades setting helicopter control relative to the longitudinal and lateral axes is realized.

  • MAIN ROTOR BLADES

Main rotor blades are made of composite materials and equipped with electrical anti-icing system.

  • MAIN ROTOR HUB

Main rotor hub is installed on the main gearbox shaft and designed to transmit torque from main gearbox shaft to blades. During flight MR hub takes and transmits to the fuselage aerodynamic forces and moments, generated on main rotor blades. 

  • SWASH PLATE

Swash plate is a mechanism that varies the amount and direction of the resultant aerodynamic forces of main rotor (propeller thrust).

  • TAIL ROTOR

The tail rotor is installed to compensate the main rotor torque and to provide directional control of the helicopter. Tail rotor is a four-blade pusher propeller, Х-shaped, two-row, with in-flight variable pitch. Tail rotor blades are made of composite materials and equipped with electrical anti-icing system.

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.

EMERGENCY FLOATATION SYSTEM (EFS)

To provide safety flight over water surface emergency floatation system (EFS) can be installed on the helicopter. This removable modular system provides buoyancy within the time that is sufficient for setting up the rafts, and for leaving the helicopter by the passengers and the crew.

The helicopter design makes possible to carry out high-quality maintenance and repair in the course of helicopter operation at minimum labour consumption. The helicopter assemblies and units are made ready accessible, easy removable and interchangeable. 

During the Mi-38 helicopter operation the following types of helicopter maintenance are provided: on-line maintenance, periodic maintenance, helicopter maintenance during storage, temporal maintenance, extra work maintenance, inspection and repair maintenance. 

Helicopter airframe service life/service time till discarded, as well as overhaul life are not specified. Helicopter is operated “on condition”. When reaching operation time of 18,000 flight hours/20 years operator addresses its request to helicopter developer to define any additional works required for continued airworthiness of the helicopter.

DELIVERY, GUARANTEE AND TECHNICAL SUPPORT

Standard delivery conditions of new helicopter comprise:

  • guarantee according to the contract requirements (usually 12 months);
  • individual kit of spare parts, tools and equipment;
  • maintenance kit, contained spare parts and equipment set;
  • technical documentation. 

Helicopter manufacturer provides a wide range of

services related to the helicopter operation, such as:

  • full technical support during helicopters operation;
  • guaranteed spare parts supply under AOG requirements during the whole period of helicopter operation;
  • helicopter modernization;
  • helicopter overhaul both at Kazan Helicopters or Customer´s premises;
  • flight and maintenance personnel training in Kazan Helicopters training center or at the Customer´s base. 

SERVICE LIFE AND OVERHAUL FREQUENCY