BPR-2-2S
Control Unit
Description
BPR-2-2S electronic control unit
BPR-2-2S belongs to the power-supply and electrical conversion unit family. This page identifies the exact execution by its complete marking. Function, system composition and application must be established from the product passport, illustrated parts catalogue and equipment documentation; a similar enclosure or related index does not prove interchangeability.
The wider context of onboard electronics is described under avionics. An electronic unit may control, switch, protect, supply, convert or process signals, but the specific role of BPR-2-2S must be confirmed for this execution rather than inferred from the category name.
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Recorded technical data
The source technical record for this position contains the following parameters. They are retained for this card and are not borrowed from adjacent models:
- Russian Designation: БПР-2-2с
- Associated Frame: 8G4.137008
- Russian Associated Frame: 8Г4.137008
- Function: Monitoring and limitation of critical operating parameters in engine / rotor control system
- Application / Where Used: Mi-26 / Mi-26T onboard automatic control and monitoring equipment
- System / Installation Area: Powerplant control, rotor speed limitation and engine protection circuits
- Compatible Aircraft / Equipment: Mi-26 and Mi-26T helicopters according to source context and documentation
- Associated Engines: D-136 engines, according to source context
- Associated Gearbox / Rotor System: VR-26 main gearbox / main rotor system, according to source context
- Associated Engine Regulator: ERD-VM / ERD-136 electronic engine regulator, according to source context
An omitted parameter does not mean a zero value or an absent function. Unknown characteristics must be checked in the passport. Every suffix, series reference, execution number, drawing designation and data-plate line should be included in the inquiry.
Role in the installed system
Within an installed system, an electronic unit works with power sources, sensors, actuators, protection, indication and interconnecting wiring according to the electrical diagram. Serviceability is assessed through input and output signals, control logic and permitted modes rather than appearance alone.
This card does not assign a particular aircraft or helicopter without a confirmed parts catalogue. Identical housings may contain different executions, while members of one family can differ in voltage, frequency, logic, pinout, calibration and associated equipment.
Pre-installation inspection
Incoming inspection compares the designation, series and every marking line and checks the housing, connectors, mounting, seals and contact condition. Approved test procedures then cover insulation, power input, current draw, inputs, outputs and relevant operating modes. Supply voltage must never be selected by analogy with a similar-looking unit.
Testing, adjustment and repair require the product passport or approved repair documentation and suitable bench equipment. Test status of an individual unit, operating time, production date, storage history and actual delivery set are confirmed separately and cannot be inferred from the model name.
Delivery set and identification
Supply may comprise the unit alone or a set with mating connectors, frame, shock mounts, cables, hardware and documentation. The quotation and passport define the exact composition. An accessory visible with a related model must not automatically be assigned to BPR-2-2S.
Photographs of the data plate, connectors and installation position, together with the system designation and removed-unit marking, help distinguish series and modifications and avoid selection by an abbreviated designation alone.
Before approving a replacement, compare connector number and type, pinout, supply voltage and frequency, input and output signal levels, switching logic, software or circuit execution and mounting dimensions. A matching base designation does not remove the need to verify its suffix and series. Any configuration-specific calibration stated in the documentation should also be included in the inquiry.
Storage and transport require protected contacts, control of moisture and contamination, intact seals and suitable cushioning. A unit held in long-term storage may require incoming inspection under an approved procedure. Storage conditions and test results belong to the individual unit and are confirmed separately by the supplier.
Ordering BPR-2-2S
An inquiry should state the complete designation, quantity, required condition, delivery set and documentation or testing requirements. More positions are listed in the Electronic Control Units category. Related products provide navigation among close families and do not establish automatic interchangeability.
Technical details
strong data-start=”3640″ data-end=”3657″>Product Type: Limit regulator unit / aircraft electronic control unit
Designation: BPR-2-2s
Russian Designation: БПР-2-2с
Alternative Designations: BPR-2-2S, BPR-2-2C, БПР-2-2С, БПР-2-2с с рамой 8Г4.137008
Associated Frame: 8G4.137008
Russian Associated Frame: 8Г4.137008
Function: Monitoring and limitation of critical operating parameters in engine / rotor control system
Application / Where Used: Mi-26 / Mi-26T onboard automatic control and monitoring equipment
System / Installation Area: Powerplant control, rotor speed limitation and engine protection circuits
Compatible Aircraft / Equipment: Mi-26 and Mi-26T helicopters according to source context and documentation
Associated Engines: D-136 engines, according to source context
Associated Gearbox / Rotor System: VR-26 main gearbox / main rotor system, according to source context
Associated Engine Regulator: ERD-VM / ERD-136 electronic engine regulator, according to source context
Input Signals: Rotational speed sensor signals, gas temperature signals, engine / rotor operating parameter signals according to system configuration
Example Associated Sensors: DTA-10, DChV-type speed sensors; T-102 or similar thermocouple circuits, according to source context
Output Signals: Control, limitation, warning or event-recording signals depending on system configuration
Associated Recording System: Tester-UZ type flight data / parameter recording system, according to source context
Associated Warning Equipment: Central warning light / cockpit warning panel and Almaz-UP voice warning system, according to source context
Power Supply: 27 V DC aircraft power supply
DC Supply Range: 24 to 29.4 V according to source context
Current Consumption Reference: Not more than 1.5–2 A in command-output mode, according to source context
Protection Structure: Two-channel / duplicated limit-monitoring logic according to source context
Construction: Metal modular / cassette-type vibration-resistant housing
Installation: On 8G4.137008 shock-mounted frame
Operating Temperature Range: −60 °C to +60 °C
Operating Environment: Helicopter vibration and linear loads according to aviation equipment requirements
Technical Documentation: Product passport, Mi-26 / Mi-26T maintenance documentation, wiring diagrams, test records and overhaul documents if available
Application: Per product passport, illustrated parts catalogue and installation documentation
Selection Basis: Complete designation, series, power, signals, pinout and mounting
Interchangeability: Only after checking documentation and all electrical and installation parameters
Testing: Per product passport or approved repair documentation using suitable bench equipment
Documentation: Product passport, parts catalogue, electrical diagram and delivery documents
Category: Electronic Control Units
Payment & delivery
Orders ship from our hub in Dubai. Partner stock is first transferred to Dubai, then shipped to you.
Dubai stock: 100% before dispatch. Partner stock (Remote stock) and Pre-order: 50% advance payment to start the order and 50% before shipment from Dubai to you.
Availability, lead time, delivery cost and payment terms are confirmed for your order before payment.
Payment & delivery terms