Abstract: A pivoting door type thrust reverser assembly for a dual flow engine incls a fixed cowling construction with a front body portion (9) and a rear body portion (12) joined by longitudinal beams (10,11) and defining reversal chambers in each of which a door (7) is pivotably received. The door pivot pins (17) are carried by two pairs of struts (15,16) such that the pivot pins are spaced from the engine axis X-X'.

Abstract: A thrust reverser for a turbo-fan engine having an improved system for security against inflight inadvertent deployment. The reverser has two pivoting doors for use on engines mounted on an aircraft rear fuselage or under the aircraft wing. The pivoting doors are positioned forward of an aft ring structure that is essentially the nacelle exit nozzle in forward thrust mode. The pivoting doors are actuated by a hydraulic actuator and are locked and unlocked by hook locks operated by an electric solenoid on one side of the door and a small hydraulic actuator on the opposite side. The two locking systems are completely independent, thereby assuring that an inadvertent in-flight deployment will not occur as a result from failure, faulty command or maintenance malpractice.

Abstract: The invention relates to thrust reversal devices for jet aircraft turboreactors and particularly for a turbo-fan type engine.The casing E surrounding the engine structure D comprises an intermediate section S3 formed by doors P4 pivoting about an axis 17-17' extending along a chord of passage CA so that the rear part of the door is short, which provides considerable clearance for the doors which may open up to 90.degree., as well as an action of flux F1 flowing in the passage promoting opening of the doors. A jack 21 coupled to each of the doors acts between the fixed structure of the casing and the internal part of the door.