FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft steering drives. Detector (13) comprises position transducer (15) engaged with screw (2) to measure the data describing its angular position and system (17) to disconnect said transducer (15) from screw (2) in case link (3) displaces relative to screw (2) at main section fault. Main section (1) has hollow spinning screw (2), secondary section (10) with emergency link (3) extending through said screw to take up the force. Flight control actuator (12) comprises main section (1), secondary section (10) with said link (3) extending through said screw (2) and main section fault detector (13). Secondary section (10) can tale up forces applied by said main section (1) at its fault.
EFFECT: higher reliability, decreased play between parts of actuator.
9 cl, 5 dwg
