BVS-1

SSKUA-1 system composition

A documented SSKUA-1 set includes one DS-1 stall sensor, one BVS-1 output unit and the aircraft warning lights and controls. Technical descriptions place the BVS-1 electronics behind the pilot instrument panel or in the forward fuselage equipment area, while DS-1 is mounted on the lower leading edge of the left wing. The BVS enclosure contains a base, two electronic boards, a cover and a plug connector.

Aircraft application

SSKUA-1 with BVS-1 is documented on the Yak-18T; training-aircraft material also describes related installations on the Yak-52. The aircraft maintenance manual governs the exact warning thresholds and installation. A BVS-1 should be ordered for the documented SSKUA-1 configuration, not selected only because another aircraft uses a critical-angle warning system.

Electrical and warning data

Published SSKUA-1 data specify a 27 V DC supply and a warning output consisting of 27 V pulses at 24 Hz. The complete system consumes about 50 W, while DS-1 sensor heating is rated at about 150 W. These are system-level figures. Documentation gives the sensor vane working deflection as ±(15 ±2)°; warning thresholds are adjusted for the aircraft installation and test procedure.

Testing and ordering

Inspect the BVS-1 housing, connector, contacts, mounting and seals, then test it with the DS-1 channel and cockpit warning circuit under the approved procedure. A request should include BVS-1, aircraft type, SSKUA-1 configuration, quantity, condition, passport and delivery set. Related sensor and warning products are available in Electronic Control Units.