Abstract: A pylon (14) for supporting a turbo-fan jet engine, in particular, an ultra-high by-pass turbo-fan jet engine (12) is disclosed. The pylon (14) attaches to the forward and aft parts of the engine core (22) and supports the engine (12) from an airplane wing (10) while resisting static and dynamic forces applied by the engine and the nacelle of the engine to the pylon. The pylon (14) includes a pylon bifurcation portion(16), having an upper end (23) and a lower end. The upper end (23) is positioned exterior to the fan duct (8) of the engine and is attached to the wing (10). The lower end is positioned inside of the fan duct (8). The lower end further includes an aft section that is attached by lugs (38) to the aft part of the engine core (22), and a forward section that is attached to the forward part of the engine core.

Abstract: An engine mount assembly includes an axially pivotable engine support and a thrust mount with a three or four bar linkage which includes a thrust bar, as the first bar, pivotably joined to a forward axial position on the engine structure at the forward end of the first bar. The line of action of the thrust bar intersects the engine centerline at a forward vertical mount plane, which is generally perpendicular to the engine centerline and through which a forward pivotal support mount of the engine support acts to support the engine, substantially at the axial position where engine centerline and forward vertical support plane intersect. An alternate embodiment of the present invention provides a means to counter bending moments produced by aerodynamic forces acting on the nacelle of the engine particularly those referred to as lip loads.

Abstract: Means for mounting an engine component to the exterior of an engine's case that is mounted in an aircraft with limited access including a blind mount. The mount includes an elongated bracket fixed to the exterior of the engine case with a clevis at one end of the bracket to receive a blind mount on said engine component. Camming means operatively connected to an accessible torquing member secures the engine component in place. Hook elements on the bracket engage said engine component to allow the operator to free his hands to operate the torquing means. The mount is designed to be compatible with the existing vibratory isolation system built into the engine component.

Abstract: A flexible adaptor mounts an aircraft gas turbine engine to a test stand. The adaptor includes an upper frame configured for mounting on the test stand, and a lower frame spaced from the upper frame and configured for supporting the engine. A spring flexibly joins the lower frame to the upper frame to simulate the flexibility of an aircraft wing which supports the engine during operation.

Abstract: A device (19) for generating a rotating force vector and an oscillatory couple includes a plurality of non-concentric eccentric masses (22A, 22B, 22C, 22D, 22E, 22F) co-rotating at the same angular speed; and means (24A, 24B, 24C, 24D, 24E, 24F) for individually controlling the angular position of each of the masses; whereby, by selectively controlling the angular position of each eccentric mass, the device may generate a desired rotating force vector and a desired oscillatory couple. In use, the device performs an improved method for opposing the propagation of vibration from a dynamically unbalanced rotating rotor through a supporting structure (12).

Abstract: An aircraft engine thrust mount includes a pair of spaced apart thrust links pivotally joined at one end to an engine first frame and at opposite ends to a lever. A platform is fixedly joined to an aircraft pylon and includes first and second spaced apart clevises and a center clevis therebetween. The center clevis is pivotally joined to a center of the lever for carrying thrust force from the first frame through both thrust links and to the platform and pylon during normal operation. A pair of pins pivotally join the thrust links to the lever and extend through apertures in the platform first and second clevises to define predetermined gaps therebetween for allowing the lever to rotate relative to the platform center clevis up to a predetermined angular rotation. In a failure mode of operation the pins contact the platform first and second clevises for transmitting thereto either tension or compression thrust loads for providing an alternate failsafe loadpath.

Abstract: An aircraft engine mounting assembly using a clevis type joint to connect a link is provided with a mounting pin assembly disposed in an aperture of the link having inexpensive and easily replaceable concentric inner and outer non-rotational bushings surrounding a conventional pin and corresponding oppositely disposed sets of inner flat contact surfaces on the outer surface of inner bushing and outer flat contact surfaces on the inner surface of the outer bushing which provide reduced contact stresses between the pin and the aperture as compared to conventional assemblies. The contact surfaces are in general sliding engagement in the longitudinal direction and are provided with clearances between the inner and outer bushings in the longitudinal and transverse directions to allow for thermal growth of the engine.

Abstract: A frame for a gas turbine engine includes an outer casing, an inner hub, and a plurality of circumferentially spaced apart struts extending radially therebetween. Each strut includes first and second sidewalls defining a radial passage therein, and an elongate damper is disposed in respective ones of the strut passages. Each damper is disposed in an interference fit laterally between the first and second sidewalls for maintaining contact therewith for effecting sliding friction to dampen vibration of the struts.

Abstract: An aircraft engine mount includes an annular casing fixedly disposed in the engine, a mounting platform spaced radially outwardly from the casing and fixedly joinable to an aircraft pylon, and a pair of circumferentially spaced apart links pivotally joined to the platform and the casing at respective radially outer and inner joints. The inner joints are circumferentially spaced closer together than the outer joints so that the intersection point of the longitudinal axes of the two links is disposed radially below the two links themselves for reducing lateral deflection of the casing relative to the engine mount.

Abstract: An aircraft engine mount includes a frame fixedly joined in a gas turbine engine and a platform fixedly joined to an aircraft wing or tail pylon. A first beam is pivotally joined to the frame and the platform at first and second joints, respectively. The first beam is additionally joined to the platform at a third joint which allows longitudinal movement between the first beam and the platform at the third joint while preventing rotation of the first beam. A second beam is spaced from the first beam and is pivotally joined to the frame and platform at fourth and fifth joints, respectively, and is additionally joined to the platform at a sixth joint for allowing limited rotation of the second beam during normal operation while preventing rotation of the second beam upon a failure of the first beam to carry load.

Abstract: The exhaust casing of a turbojet engine has a polygonal cross-section and carries at least three hanging lugs provided with holes designed to receive fixing axles of a rear suspension structure for the engine. The axes of these holes are situated at vertices of the polygon defined by the cross-section of the casing, and this polygon is regular except at the position of each of the hanging lugs, where it is deformed to displace the respective vertex radially outward.

Abstract: The rear hanging structure by which a turbojet engine is suspended from a mast under the wing of an aircraft includes a brace which is fixed to the mast and to which the engine is attached by at least three suspension links, the brace includes two parts which are fitted one within the other and are dimensioned in such a way as to ensure that each is able to take all of the suspension stresses independently of the other, the pins by which the brace is connected to the mast and to the suspension links passing through both parts of the brace. The redundancy thus achieved increases considerably the reliability of the suspension.

Abstract: A detachable support structure for a large turbine aircraft engine having a nacelle which is attached to an auxiliary support frame. The auxiliary support frame has an upper portion which is attached to an upper portion of the nacelle. The auxiliary support frame has a lower portion which is detachable from the upper portion of the auxiliary frame. The lower portion of the auxiliary frame is connected to a lower portion of the nacelle, the lower portion of the nacelle being detachable from the upper portion of the nacelle. By removing the lower portion of the nacelle and the lower portion of the auxiliary support frame, the thrust producing section of the turbine engine can be removed intact.

Abstract: The exhaust casing of a turbojet engine has a cross-sectional shape in the form of a regular polygon and carries at least three external hanging lugs provided with holes for receiving fixing axles of a rear suspension structure for the engine. The lugs are carried by non-consecutive sides of the casing in ), manner that the geometrical axis of the hole of each lug is situated at the intersection of the median planes of the two sides of the casing adjacent the side carrying the lug.

Abstract: A support system for the aft end of fan jet gas turbine engines which reduces engine bending in operation while accommodating radial and longitudinal thermal expension forces. A first radial ring secured to the engine structure core cowl and the overall engine support pylon has a plurality of spaced longitudinal grooves. A second, cooperating radial ring secured to the engine has a plurality of outwardly extending tabs sized to fit within the first ring grooves. The tabs do not extend fully into the grooves at ambient temperatures. When operation of the engine begins, the engine heats up to a relatively high temperature. Radial thermal expansion is accommodated by expansion of the inner ring, causing the tabs to move deeper into the grooves. Longitudinal thermal expansion is accommodated by slippage of the tabs along the grooves in a longitudinal direction. Meanwhile, the engine is supported against bending and flexing beyond the amount permitted by the space between tab ends and bottoms of the grooves.

Abstract: A pod for suspending a turbojet engine unit below the wing of an aircraft includes a suspension assembly with two laterally spaced front beams connecting the turbojet fan casing to the wing, and two rear links disposed in a common vertical plane and pivotally connected at one end to the wing and at the other end to a connection link which is connected at least to the exhaust casing of the engine, the front beams being interconnected by cross-bracing and being connected at the level of the downstream edge of the cross-bracing to at least one fixed part of the engine.

Abstract: A structure for removing bending caused by an inlet lift load in the engine core of an aircraft having a support frame which is attached to a frame mount which connects to the pylon floor. The frame mount is located between a forward mount and a rear mount and to the front of the engine core. As a result of the frame mount, the moment created by the inlet lift load is not reacted through the engine core so engine performance is not affected.

Abstract: An aircraft engine mount adapter and method is provided that permits the coupling of an aircraft engine to an aircraft when the pickup points on the engine are incompatible with the location of the mounting pins on the aircraft. The adapter consists of an arcuate shaped member having sufficient lateral curvature so as to be selectively positionable along the length and about the circumference of the engine's casing. Means for locking onto the mounting pins are disposed along the outer surface of the member. The member has a plurality of flanges which are bolted to flanges extending outwards from the engine's casing.

Abstract: Mounting device for mounting a multiple cylinder, vertical in-line 2 cycle internal combustion engine to a frame or chassis. The frame or chassis has a pair of longitudinal rails, which are laterally spaced apart. In order to reduce transmission of engine vibration to the chassis or frame, the lateral spacing apart of the rails is related to the square root of the piston displacement of one cylinder and the number of inches of one rod length.

Abstract: A failure tolerant engine mounting is formed by three links between the engine and its support structure, one of the links being arranged so that in the event of failure of either of the other links it will form a connection between three points on the engine and supporting structure which are symmetrically arranged about a vertical axis through the engines center of gravity.

Abstract: Means for mounting an engine to an aircraft are provided which reduce the dynamic response of the airframe due to engine vibration. A mount comprises at least one strut extending between the engine and the airframe which is attached to the airframe by means of damping elements.

Abstract: An engine mounting system where an aft body mounted counter-rotation prop fan engine is mounted to aircraft structure. The engine is connected through a longitudinally extending beam to a mounting strut structure comprising a fore spar, a mid spar and a rear spar. Vertical loads and lateral loads are transmitted from the engine to the beam at forward and rear locations, and these vertical and lateral loads are in turn transmitted to the spars at forward and rear locations. The torque loads from the engine are transmitted at a selected location into the beam, and then transmitted through the beam to the spar or spars at a selected location or locations. The beam can initially be mounted to either the engine or to the spars of the aircraft.

Abstract: The present invention is a damper assembly included in a strut on the front frame for a jet propulsion engine. The damper assembly is disposed within the strut for damping vibration of the strut as a result of air stream pressure pulses from first stage fan blades causing strut excitation when the fan blades are operating at least at transonic speeds.

Abstract: When a breakage occurs to the connecting links which connect a gas turbine engine to aircraft structure, the engine drops onto a fail/safe mounting. The drop is minimal in magnitude and the invention provides a visual means for appreciating that the drop and therefore the breakage, has occurred. Relative movement between engine and airframe frees a pop up member and enables it to project beyond the engine envelope, for observation by inspection.

Abstract: An improved engine mount is disclosed which includes a latching mechanism for latching a pivotal jaw to a stationary jaw, thereby defining an engine pin housing. The latching mechanism is of the over-center type which provides a locking force to the latched engine mount. The latch includes locking members which may be remotely operated thereby allowing remote latching and unlatching of the engine mount.

Abstract: The present invention provides a fastener system for attaching a jet engine to a mounting bar requiring access to only one side of the mounting flanges. The fastener remains in place should either the bolt or the hollow pin fracture during operation of the engine. The fastener system has jet engine casing flanges extending on either side of a mounting bar with aligned openings extending through these elements. Hollow sleeves extend through the openings in each of the engine casing flanges with the rear, or downstream sleeve extending through the downstream flange having an internally threaded portion. A hollow pin passes through the interiors of the sleeves and the aperture in the mounting bar and engages the downstream sleeve such that rotation between this sleeve and the hollow pin is prevented. A bolt, having a headed portion, is inserted through the hollow pin at, and is threadingly engaged with, the threaded portion of the rear or downstream sleeve.

Abstract: An engine mounting system where an aft body mounted counter-rotation prop fan engine is mounted to aircraft structure. The engine is connected through a longitudinally extending beam to a mounting strut structure comprising a fore spar, a mid spar and a rear spar. Vertical loads and lateral loads are transmitted from the engine to the beam at forward and rear locations, and these vertical and lateral loads are in turn transmitted to the spars at forward and rear locations. The torque loads from the engine are transmitted at a selected location into the beam, and then transmitted through the beam to the spar or spars at a selected location or locations. The beam can initially be mounted to either the engine or to the spars of the aircraft.

Abstract: A dual engine drive system for a single propeller shaft includes a single torque-combining gearbox separated from the engines by gearbox input shafts. The engines, gearbox and propeller shaft are mounted as a unit on a common support frame adapted for installation in existing fixed-wing, single-engine aircraft. Each input shaft drives its own primary gear train within the gearbox. Each gear train includes its own output gear coupled to the propeller shaft through an overrunning clutch. An auxiliary drive train driven by the propeller shaft drives redundant propeller governors, an overspeed governor, and an oil pump for lubricating the propeller shaft and auxiliary gear train. The primary gear trains also drive oil pumps for lubricating their own gearbox sections. The three oil pumps are in separate subcircuits of a common oil circuit, and a mechanism is provided for enabling an operating oil pump of one subcircuit to supply oil to another subcircuit if the oil pump in such other circuit fails.

Abstract: An engine mounting structure for a turbojet engine is disclosed which incorporates a safety rod in addition to the normal support rods used to attach a turbojet engine to a mounting structure. Under normal conditions, the safety rod is unstressed and supports none of the engine's weight. Upon rupture of one of the support rods, a tensile or compressive force exerted on the safety rod will move it into an active position so as to assume support of the engine's weight. A locking structure is also disclosed which will securely lock the rod in its active position such that it assumes the portion of the engine weight normally undertaken by the ruptured support rod.

Abstract: A propulsion unit suspension for propeller driven aircrafts in which a supporting frame is supported at a fire wall; the propulsion unit together with auxiliary aggregates is retained at the supporting frame in several bearings. The bearings of the supporting frame are arranged in two horizontal planes offset in height to one another with an axial distance to one another. The arrangement of the bearings takes place in such a manner that a line of action of the gravity and a further line of action of the propeller thrust extend through an ideal surface delimited by the bearings. In particular, the forward bearing is retained at the supporting frame within the area of a vertical longitudinal plane through the center of gravity as well as above the line of action of the propeller thrust and two rear bearings are located in the supporting framework at approximately the same distance on both sides to the vertical longitudinal plane of the center of gravity and below the line of action of the propeller thrust.

Abstract: Fan casing (32) of turbo fan jet propulsion engine (20) is mounted to a forward portion of a wing strut (24) by a forward hanger assembly (50). The rearward portion of the core assembly (26) of engine (20) is suspended from wing strut (24) by a rearward hanger assembly (80). A yoke assembly (100) extends forwardly from rear hanger assembly (80) to interconnect with the forward portion of the engine core assembly (26) to restrain against axial movement thereof. Fan casing link (66) extends diagonally upwardly and rearwardly from fan casing (32) to intersect with wing strut (24) at a location rearwardly from the location at which the forward hanger assembly (50) is secured to the wing strut.

Abstract: In an aircraft having a jet engine mounted to and beneath a wing thereof wherein the engine is a predetermined distance from the wing and wherein further the engine is mounted on a strut affixed to the wing, a low-profile engine mount assembly is attachable to the strut and the engine to hold the engine on the strut. The engine mount assembly is constructed and arranged to occupy a minimum portion of the distance between the engine and the wing so as to provide the maximum strut vertical dimension (depth), thereby providing significant benefit in length-to-stiffness ratio in the strut. The engine mount is further constructed and arranged to accommodate longitudinal growth of the engine due to thermal expansion and includes a yoke assembly having a first arm and a second arm, the yoke being mounted to the strut so as to permit pivotal movement of the yoke about an axis substantially orthogonal to the engine axis.

Abstract: A low aerodynamic drag structural link suitable for use within the housing of a turbofan jet engine; the link includes length adjustment capability, pivotal end mounting provision, maintained airstream orientation capability, low mass and jam nut length and orientation locking. Several variations in link construction including a single ball and socket arrangement, varying link cross-section along its longitudinal length and the use of fairing nose and tail inserts are disclosed.

Abstract: An attachment arrangement for connecting a jet propulsion power plant to an aircraft wing, the power plant lying generally forward and below the wing, wherein the engine is not only anchored in the vertical, lateral and fore-and-aft senses against bodily displacement with reference to the wing, but is anchored against angular movement in its pitch, roll and yaw senses in the event of partial or total failure of any one element of the attachment arrangement.

Abstract: An upper pylon element suspended to a flexmount member to be attached to a supporting structure, includes a suspension device having a first hook device arranged to cooperate with an attachment device on a lower pylon element, and a second hook device for suspension of the fan duct, the suspension device having a first operating state in which the first hook device is coupled with the attachment device on the lower pylon element thereby to suspend the lower pylon element to the upper pylon element and a second operating state in which the first and second hook devices are disengaged from the corresponding attachment device; a locking unit arranged when it is operated, to lock the lower pylon element to the core cowl; and a drive unit to actuate the suspension device and the locking unit from one operating state to the other.

Abstract: A turbine engine drive and mounting assembly for a propeller-driven, fixed-wing aircraft includes an open support frame resiliently mounted to and cantilevered from an air frame portion of the aircraft. A gearbox is rigidly mounted to the free end of the open support frame and is adapted for mounting and driving a propeller. A turbine engine is positioned within the support frame in spaced relation to the gearbox. The turbine engine is suspended from a ring member of the support frame so as to enable expansion and contraction of the engine relative to the support frame and pivoting of the engine on the ring member for maintenance. The engine is drivingly connected to the gearbox through flexible couplings. High torque loads at the gearbox are transmitted through the support frame directly to the air frame, bypassing the engine.

Abstract: A mounting system for two turboshaft gas turbine engines which are connected by a coupling gearbox. The mounting system comprises a front mounting attached to the gearbox which permits pivotal movement of the engine/gearbox assembly but restrains longitudinal movement and two strut members which support the engines vertically but provide no lateral or longitudinal support. The engines are interconnected by link members and an intermediate member rotatably attached to the vehicle which permit relative lateral movement between the engines but constrain any lateral movements of the engines which are in unison relative to the vehicle.

Abstract: Aircraft gas-turbine engines (10) are often mounted and supported by strut type structures (12) which contain fuel, oil, electrical and hydraulic engine supply lines. The engine fan (18) is surrounded by a belt (24) made of tough flexible material designed to restrict travel of broken fan blade pieces, ingested objects or other debris (20). The forward strut section (12), adjacent the belt (24), is located outside of the maximum belt deflection envelope (26) except for the engine right and left cowl hinges (62 and 64) and its support structure (30), which structure (30) is made collapsible. This collapsible cowl hinge structure (30) utilizes mechanical fuse connections (68) which upon a dislocation force from the belt (24) allows the structure (30) to disconnect from the strut support structure (12).

Abstract: A dolly for use in the installation of a jet engine in an aircraft compartment. The dolly has longitudinal guide rails placed in the compartment and a device including two lateral guide rails and a lower, median guide rail; a foldable and removable front cradle carrying two runners and capable of being attached to the front of the engine, the runners cooperating with the lateral guide rails; a rear cradle that is removable and equipped with a runner cooperating with the lower median guide rail; a frame to which the lateral guide rails are adjustably attached; means for the vertical displacement and the longitudinal displacement of the frame.

Abstract: A gas turbine engine pod installation comprises a core engine with a stiff carcase from which the engine is supported from a pylon. The core engine drives a fan which operates within a fan casing extending to downstream of the core engine nozzle so that the core and fan flows are mixed to provide propulsive thrust when they exit from the fan duct nozzle. The fan casing is supported from the core engine carcase by forward and rearward supports so that these supports, the fan casing and the carcase form a stiff loop of structure which supports and stiffens the carcase.

Abstract: A helicopter transmission mounting structure is disclosed in which at least three decoupled inertial isolators (26,38,30,32) are connected to the transmission (12) to support the helicopter fuselage. Each of the inertial isolators (26,28,30,32) is mounted in the nodal plane of the transmission (12) to absorb inplane vibrations generated by a rotor blade and transmitted through a rotor mast (10). The inertial isolators (26,28,30,32) respond individually to applied vibrations which have predetermined frequencies and generate counteracting forces to reduce the amplitude of vibrations transmitted to the fuselage. In an alternative embodiment beam input links (134,136,138,140) are connected from the nodal plane of the transmission to inertial isolators (142,144,146,148). The beam input links (134,136,138,140) are connected to transmit only those forces parallel to the rotor mast (10).

Abstract: The apparatus for suspending a jet engine is composed of three assemblies: an assembly 1 of parts placed permanently on the engine, an assembly 3 of parts placed permanently on the cell, and a liaison assembly 5 for connection of the preceding parts. Assembly 3 placed on the cell is disposed at the bottom of a recess and the parts forming the liaison assembly are put into place across the recess and the assembly on the cell using tooling consisting of a guide tube and two spanners, the ends of which cooperate with the ends of the pieces of the liaison assembly. The invention also concerns a process and tooling for using the apparatus.

Abstract: A gas turbine powerplant has an inner casing (4A) containing a gas turbine engine, an outer casing (5) surrounding the inner casing, a fan driven by the engine and driving air through an annular duct defined between the casings. The powerplant is connected to an aircraft fuselage (1) by a front mounting (9,9A,9B,9C) and by a rear mounting (8,10,17,18). The front and rear mountings react lateral forces on the powerplant. The powerplant includes a thrust reverser (11) situated rearwards of the rear mounting and supported by a ring (18) lying in the annulus of the outer casing and forming part of the rear mounting. At each side of the powerplant there is provided a tie (14,15) which connects the inner casing at a joint (6,16A) adjacent the front mounting to the ring of the rear mounting. The ties therefore lie oblique to the main engine axis. The ties react the forward and reverse thrusts of the powerplant.

Abstract: A wing of an aircraft has a mass, for example an engine, secured to the wing by a pylon such that an imaginary line between the center of gravity of the mass and the region of the wing to which the pylon is attached is at an angle to the vertical, the force and the moment applied to the wing by the mass and the pylon being applied to the wing through at least one attachment member. The force and the moment can be applied to the wing through first and second attachment members respectively.

Abstract: A main thrust link having a forward end connected to the engine core housing at a first forward location, and extending rearwardly and moderately upwardly therefrom to connect to a main support structure at a second rearward location. Connected to the rear of the engine core housing is a rear support device designed to resist vertical loads generally parallel to the vertical force component exerted by the main thrust link, and also to resist side loads. There is a forward connecting device interconnecting the fan casing with the support structure at a location forward of the forward connecting location of the main thrust link. This forward support device comprises a plurality of tangential links connecting to the fan casing at evenly spaced locations around the circumference of the fan casing, thus resisting not only vertical loads, but also resisting torsional loads and side loads on the engine.

Abstract: This invention relates to motor mounts in general, and more specifically to a universal motor mount to be employed in a model airplane, which will allow the motor to be disposed at any desired angle or altitude to accommodate engine or exhaust equipment beneath the engine cowling.

Abstract: An accessory for a jet engine for tuning turbine exhaust gases for maximum thrust capabilities in the absence of a turbine thrust reverser and cowling combination normally for and utilized thereon. The accessory comprises an inner streamlined nozzle shell forming a continuation of the outer skin of the turbine exhaust duct, a center mounted engine plug providing a path for the turbine gases between the inner nozzle surface and the engine plug outer surface and a transition adapter for mating and attaching the plug to the center of the engine. The engine plug is further provided with an opening between its engine attached and outer ends providing communication between the engine and the atmosphere adjacent the rear end of the plug. The accessory further comprises a fairing for attachment to the pylon supporting the engine to further tune the gases leaving the nozzle.

Abstract: A main engine support structure having a rear portion hinge-mounted at two laterally spaced locations to a leading edge of a wing in a manner to permit limited up and down swing movement of the engine relative to the wing. A generally vertically aligned forward support link connects a forward inboard side portion of the engine support structure to the airplane fuselage, thus providing vertical support for the engine at its forward end. At the rear of the support structure there is a laterally extending link, connecting the support structure to the wing and resisting lateral loads exerted on the engine. This mounting system reliably mounts the engine to the wing, does not interfere with the wing's ability to flex upwardly and downwardly, and properly transmits the loads from the engine into the aircraft structure.

Abstract: A slot seal closure apparatus for use in an aircraft engine mounting strut comprises at least one door which covers a slot formed in the strut to accommodate fore/aft movement of a portion of the engine cowl. When the engine is in a cruise mode, the movable portion of the cowl is in its forwardmost position disengaged from the slot and the door is in a first position covering the slot so as to prevent airflow through the slot. When the engine is placed in a reverse mode, the movable portion of the cowl moves aft and the door swings to a second position spaced from the slot in reaction to the aft movement of the cowl portion so as to expose the slot thereby enabling the movable portion of the cowl to engage the slot.

Abstract: An aircraft engine installation is disclosed wherein a gas turbine engine is supported within the interior of a tubular cowling that is affixed to the aircraft and all other components of the engine installation such as an air inlet and exhaust system structurally depend from the cowling rather than being mounted to the gas turbine engine. To permit access to the engine for inspection, repair or removal. the lower portion of the cowling is linked to a stationary upper portion of the cowling by a set of jackscrew assemblies spaced apart along each axial boundary of the upper and lower cowling units. The jackscrew assemblies are operable to lower the lower cowling unit to a position at which integral locks, included in one set of the jackscrews, can be released to permit the lower cowling unit to be swung open about integral hinges that are included in the second set of jackscrews.