Abstract: Flight deck information warning system for notifying the flight crew of abnormal engine operating conditions in the sub-idle region. The warning system is responsive to signals representative of engine exhaust temperature, engine core rotor speed, total air temperature, engine fuel flow and, airframe calibrated airspeed.

Abstract: A monitoring system for detecting a fault condition in any one of multiple power control actuator units used for positioning an aircraft's control surface includes sensors for producing sense signals corresponding to the load on each actuator unit under a given control surface loading condition. The sense signals are compared with a reference level signal corresponding to a maximum allowable load. An indication is produced in response to the load on any actuator unit exceeding its allowed value.

Abstract: A controlled method of anodizing aluminum comprises formation of an aqueous solution of sulfuric and boric acids, immersion of a workpiece in the solution maintained at about room temperature and controlled application of voltage to achieve a current density not greater than about 10 Amperes per square foot. Aluminum oxide coatings in the weight range of from about 200 to 600 milligrams per square foot applied in this manner have properties as good as or superior to coatings applied in traditional hexavalent chromium anodizing solutions.

Abstract: Each of a plurality of multifilament, resin-impregnated rovings (18) is routed through orthogonally disposed guide rollers (222, 224; 242,244) for compaction to a predetermined width and thickness between the radial faces of a compaction backup roller (250) and a compaction roller (254). The force applied to the compaction roller (254) is varied to assure the dimensions of each compacted roving. The compacted rovings (18) are then routed through a bandwidth adjustment assembly (290) that controls the spacing between adjacent rovings such that they emerge in a side-by-side alignment forming a band (90). The band (90) then passes over the surface of a final deliver roller (296) before being wound onto a rotating mandrel (92) in a band edge-to-edge configuration to form a filament-aligned structure. The structure is then cured, causing the flow of the resin impregnation and forming a unified structure.

Abstract: An ultrasonic inspection system for composite materials capable of detecting flaws near the surface of the inspected part which flaws are normally masked by strong reflections from the part surface. An electronic signal representative of the strong surface echo is stored in memory and subtracted in a differential amplifier from the entire test piece echo representative signal in time relationship which effects cancellation of the signal representative of the strong surface echo thereby allowing weaker echo representative signals from defects near the surface to the detected.

Abstract: An ultrasonic scanning system utilizing a selectively rotatable reflector permitting selective use of multiple transducers mounted around the periphery of a water jet for flaw detection in composite materials.

Abstract: A conductor rail assembly parallel to an aircraft passenger seat track is coupled by direct electrical connection to the aircraft passenger entertainment system power supply. Passenger seat entertainment system power connectors are inserted into and retained in the conductor rail assembly to distribute power to the individual seat receivers.

Abstract: A bidirection brake for a rotary device prevents a reverse load or an overrunning load at the output of the rotary device from rotating the output in either direction. The brake includes a pair of opposing plates having pockets formed in their surfaces which contain movable balls. A reverse load or an overrunning load causes relative motion between the plates which in turn causes the balls to move to shallower parts of the pockets thereby forcing the plates axially apart. As the plates move apart, they each engage respective skewed roller assemblies which inhibit the rotation of the plates and the shafts which are connected to the plates. The breakout and running friction of the skewed roller assemblies are almost equal so that the brake operates smoothly when it is engaged and when it is released.

Abstract: A container assembly secured in the back of a passenger seat contains food and beverage for a passenger sitting behind the seatback. The container includes an rounded portion which holds a beverage can and glass. The container is held by a holder assembly which is fastened to a recessed area inside the seat. The container is secured to the holder by first inserting the rounded portion of the container into a similarly rounded portion of the holder and then rotating the container into an interference fit with the holder.

Abstract: A twin-engine supersonic airplane having an arrow-shaped wing and an elongated fuselage extending approximately equally forward and rearward of the wing. The fuselage is configured for six passengers in a staggered two-abreast seating arrangement and for two pilots seated in tandem. A forebody section of the fuselage, which extends substantially forward of the wing, is of a specific geometric cross-sectional design, i.e., it is an egg-shaped cross section with opposite sidewalls sloping vertically inward in an upward direction. The sidewalls are only of a single curvature in a fore-and-aft direction, and this substantially flat surface has windows installed therein which have an optically flat surface in order that a minimum of visual distortion is produced due to thermal expansion during supersonic flight. Twin vertical stabilizers are spaced apart and each is mounted near a wing tip; and the stabilizers extend both vertically above and below the wing chord plane for functioning as wing tip end plates.

Abstract: Prevention of actuator oscillation due to failure mode in an aircraft pitch axis control system is provided by an oscillatory failure monitor. The oscillatory failure monitor provides power shutdown of the actuator through inner loop modeling and error signal processing of inner loop disturbances.

Abstract: A high energy absorbing aircraft tail skid assembly for protecting an aircraft fuselage lower skin portion from damage in the event of a tail strike due to over rotation on take-off of the aircraft. The high energy absorbing tail skid assembly is pivotally mounted to the aircraft bulkhead, and comprises a telescoping rod assembly including a crushable aluminum cartridge, positioned coaxially with respect to the central axis of the telescoping rods. The telescoping rod is coupled through linkage, including a fuse pin providing a predetermined failure mode for the high energy aircraft tail skid assembly, to prevent overloading critical aircraft structure.

Abstract: A spiral four fluted rotary carbide cutter has a one directional helix throughout much of its length, and a reverse directional helix adjacent the cutting end. Opposite lands, between the flutes, have square cornered axially aligned and equally spaced notches; with adjacent lands having the notches intermediately located with respect to each other. All of the notches are at an angle of about 20 degrees with respect to a line perpendicular to the axis of the cutter to in combination provide a cutter for Kevlar containing composite panels.

Abstract: A system and apparatus for ultrasonic pulse echo inspection of corners in laminated parts. A variable angle transducer including transducer, fixed reflector, and rotating reflector which effects scanning of the radial arc being tested by the sonic output from the transducer provides ultrasonic information which is processed through an ultrasonic signal processing system which digitizes, stores and displays the information.

Abstract: Noise and vibration in a structure is reduced through application to the structure of an oscillatory torque. An electromechanical energy converter provides the oscillatory torque when the input signal to the electromechanical energy converter has a frequency and harmonics thereof required to counteract the noise and vibration desired to be attenuated.

Abstract: A method and apparatus for removing frozen, stuck or sealant anchored fasteners from aircraft assemblies that cannot be unscrewed by conventional screwdrivers. A pulsating force is applied through the longitudinal axis of the apparatus to the head of the fastener while simultaneously torquing the fastener alternately and sequentially in counterclockwise and clockwise directions until resistance to the removal of the fastener has been reduced to permit removal by conventional screwdriver.

Abstract: A system for aircraft landing light alignment which includes a target of photocells distributed in a cross-like manner with a single photo detector centered about the common point of the cross-like distribution. A signal processing circuit coupled to the output of the target includes electronic readout devices distributed in a cross-like manner for indicating which way the beams should be directed to provide correct light adjustment. The aircraft landing light alignment system includes signal processing of photo detector derived signals which measures only the outer fringes of the Gaussian beam distribution.

Abstract: Retarding of the point of transition from laminar flow to turbulent flow in aerodynamic boundary layers on the surfaces of aircraft is accomplished by radiating acoustic energy at frequencies greater than twice the critical Tollmein-Schlichting frequency into the boundary layer. The acoustic energy interferes with the formation of Tollmein-Schlichting waves, thereby increasing the incidence of laminar flow and reducing aerodynamic drag.

Abstract: Plastic laminated window 40 for aircraft passenger cabin having a peripheral edge insert 50 for providing additional shear-bearing area with respect to the chamfered peripheral edge portion 46 of the outer ply 44 of window 40.

Abstract: A series of filaments are grouped into rovings (10), with each roving being impregnated with a viscous, tacky resin binder. The rovings are guided (12, 14, 16) to and compressed against a mandrel (18). By controlling intraroving spacing and compression force, the rovings are compressed such that their lateral expansion results in adjacent roving bonding, whereby a singular band (22) of defined width, height and filament count is formed. The height and width is controlled by varying the compression force and the intraroving spacing. Band contouring is realized by severing (24, 26) selected rovings prior to band formation. Linear and rotational relative motion is provided (FIG. 11: 110, 112, 114) between the roving guiding and compression means and the mandrel to precisely orient the band.