Abstract: This invention is a portable pneumatic cutter tool for cutting countersinks into a workpiece 17 having pre-drilled holes 15. When pressure is applied, a piston return cylinder 57 and a feed rate cylinder 79 are also pressurized, which sets a body piston 72 and spindle piston 80 reacts against a spindle bar 82 which holds nose 94 in its outer-most limit position. A pistol grip drill 44 drives a geared belt 34 to cut the countersink after actuation by trigger 45. A flare tube shaft 14 expands a multiple finger and pad arrangement of a collet 12 to provide clamp-up on the back side of workpiece 17. Clamp-up on the front side of workpiece 17 is provided by pneumnatic pressure and solid mechanical stops 16. The countersink cutter 18 advances into workpiece 17, reaching its depth, and returns automatically to its start position.

Abstract: A latch for a thrust reverser duct on an aircraft engine. The latch accomplishes work during both the closing stroke and the handle folding stroke. An outer handle 100 release trigger 112 can lock an outer handle 100 to an inner handle 60 to fix the relative position of the outer handle 100, the inner handle 60, an idler link 80, a rocker link 78 and a secondary link 75. While they are in fixed position, the parts act as a closing handle unit 125 during the closing stroke. Once the closing stroke is completed, the inner handle 60 is locked into a fixed position with hook arm 40 and a primary link 70. The outer handler release trigger 112 can then be disengaged and the secondary link 75, the rocker link 78 and the idler link 80 work to provide mechanical advantage during the folding of the outer handle 100.

Abstract: This invention is a countersink, counterbore or spotface, external pilot guide 98 which aligns a countersink cutter's edges 170, 171 and 172 into the center of a pre-drilled hole 15. The pilot guide indexes and attaches by lock down screw 165 to the countersink cutter 18 external body hole 160, three pilot legs 100 are recessed into the countersink cutter 18's flute pockets 150 and allows the cutting edges 170, 171 and 172 to extend through the pilot countersink cut-outs 140. Button nose 110 outside diameter comes in a range of sizes dependent on the pre-drilled hole 15 size (example: Pre-drilled hole size 0.375", button nose size 0.372") this allows clearance for friction expansion. All button nose 110 outside diameter's fit the same countersink cutter 18 and all have a hole in the center which allows the flare tube shaft 14 to move freely during the countersinking operation.

Abstract: The invention is an aircraft two part hinge line fairing design for preventing physical interference between the two fairing parts while eliminating unacceptable gaps between the the two fairing parts. The problems are made worse by the fact that the hinge line is not perpendicular to the longitudinal centerline of the fairing which is aligned with the airflow. The problems, such as gaps, are unsightly and also increase drag. These problems are solved by the use of two matching surfaces of the fairing having substantially the same curvature and radius in all directions. The slight difference in curvature, and radius, is appropriate to allow a smaller fairing part to extend into a larger fairing part for freedom of movement with respect to each other.

Abstract: The torque limiter described herein is a device for preventing the transmission of torque from a drive source to a torque responsive element when a predetermined torque limit has been reached. The device also provides subsequent mechanical indication that the predetermined torque limit has been reached. The device operates by transmitting torque between two axial members, a drive member and a driven member, having a plurality of balls therebetween with the balls engaged within precisely shaped sockets contained within each axial member. As excess torque occurs, the plurality of balls cause the driven member to axially displace with respect to the drive member, engaging a set of teeth contained on the driven member with a second set of teeth aligned with the first set of teeth and restrained within the housing, thereby preventing torque transmission.

Abstract: The problem solved by this invention is to eliminate an oil can movement of the web of an aircraft pressurized bulkhead. A hat section support stiffener is attached to the web by an adhesive. Two end brackets are attached by Hi-Loc bolts to bulkhead stiffeners and the end brackets are attached and arranged to provide a downward pressure on the hat section stiffener to assist in holding it in place. This invention is characterized by the absence of any new fasteners passing through the fatigue critical bulkhead web and also is characterized by the absence of any requirement for removal of existing fasteners, including, but not limited to those passing through the bulkhead web.

Abstract: This invention defines an improved method for superplastic forming (SPF) of metallic parts in which a cutout is formed in the blank from which the parts will be formed, and a secondary sheet is located between the blank and the pressurized gas. The cutout area of the blank becomes stretched so that there is minimal thinning in the air near the periphery of the cutout(s) in the blank, the secondary sheet is required to carry the gas pressure and to form the parts.

Abstract: A molded clip for attaching wire bundles and the like to aircraft stringers is described. The clip has two major parts, each of which has a matching 45.degree. inclined surface. When a vertically aligned bolt that connects the two parts is tightened, the bottom portion of the clip slides upwardly along the matching 45.degree. inclined surface of the top portion of the clip. This movement causes gripping surfaces of the top and bottom portions to engage and secure the clip to a stringer flange. An upstanding boss having a metallic threaded insert for receiving another bolt is used to secure the wire bundle clamp to the clip.

Abstract: This invention is a method and apparatus for determining whether or not auxiliary airfoils on an aircraft wing are skewed or lost. It employs either of two types of systems and their associated computer monitor and control requirements. One system utilizes a cable and a spring-loaded mechanism with a cable displacement position sensor. The second system utilizes a drive system position sensor, proximity sensors and segmented proximity targets. These two systems are capable of skew and loss detection for adjacent or individual auxiliary airfoil arrangements. A computer electronic unit is used to perform logic functions to verify the authenticity of sensor signals, and, if appropriate, to shut down the drive system and to compute new flight control parameters including those relating to stall speed and the stick shaker, while alerting the flight crew.

Abstract: Disclosed is an aircraft clip for attaching insulation blankets and other nonstructual items, such as wire bundles and hydraulic conduits, to structural members. The clip has a molded plastic shaped base and a "T" shaped grip rotatably connected to the base. The grip is rotated to secure the nonstructural item by a "C" shaped clamp which is pushed into a detent to assure that the clip is locked. The "T" shaped grip is allowed to rotate by a flexible and thin tab interconnecting the base and "T" shaped grip which, in a preferred embodiment, are integrally molded. Optionally, the "C" shaped clamp may be made of spring steel rather than molded of plastic. Also optionally, the "T" shaped grip may be allowed to rotate into position by a metal hinge pin.

Abstract: This invention is a method and apparatus for determining whether or not auxiliary airfoils on an aircraft wing are skewed or lost. It employs either of two types of systems and their associated computer monitor and control requirements. One system utilizes a cable and a spring-loaded mechanism with a cable displacement position sensor. The second system utilizes a drive system position sensor, proximity sensors and segmented proximity targets. These two systems are capable of skew and loss detection for adjacent or individual auxiliary airfoil arrangements. A computer electronic unit is used to perform logic functions to verify the authenticity of sensor signals, and, if appropriate, to shut down the drive system and to compute new flight control parameters including those relating to stall speed and the stick shaker, while alerting the flight crew.

Abstract: Apparatus for detecting and signaling a skewing or misalignment of adjacent aircraft leading edge slats is disclosed. A cable is attached to an actuator having a compression spring system and located in an outboard slat. The cable passes through cable guides in several adjacent slats before being attached to an inboard slat. The compression spring system utilizes a dual concentric pair of compression springs for maintaining a tight cable. When a misaligned condition is detected by a proximity switch, the increased cable load will cause the actuator to lock itself in a position out of the range of the proximity sensor.

Abstract: A target acquisition system for a mobile air defense system is capable of acquiring and engaging targets in rapid sequence while mounted on a moving vehicle. It incorporates a gyrostabilized turret drive system, an optical sight, a forward looking infrared scanner, an infared guided missile subsystem, an onboard computer, and system controls and displays. The turret drive will maintain a particular elevation and azimuth regardless of the motion of the vehicle on which the turret is mounted so that the target tracking system need not account for movement of the vehicle over the ground. The optical sight projects a set of reticles on a combining glass in front of the gunner, which shows the target on which the missile seeker is locked as well as the target at which the turret is pointed so that gunner can insure that the missile is locked on the correct target.

Abstract: A processor for an FM/CW sensor divides the sweep periods of the sensor into a number of subsweep intervals, measures the received power within a multiplicity of frequency windows during each of the subsweep intervals, and then performs a spectrum analysis of the power measurements in each frequency window to characterize the reflectors in the corresponding range bins of the FM/CW sensor footprint.

Abstract: An electrical cable having a wire bundle core surrounded by a thermal protection sleeve, the thermal protection sleeve consisting of a sandwich structure of outer acrylic adhesive layer and a silicone foam core.

Abstract: (A.) A process for forming a cobalt conversion coating on a metal substrate, thereby imparting corrosion resistance and paint adhesion properties. The invention was developed as a replacement for the prior art chromic acid process. The process includes the steps of: (a) providing a cobalt conversion reaction solution comprising an aqueous, alkaline solution containing a soluble cobalt-III hexacoordinated complex, the concentration of the cobalt-III hexacoordinated complex being from about 0.1 mole per gallon of solution to the saturation limit of the cobalt-III hexacoordinated complex; and (b) contacting the substrate with the aqueous reaction solution for a sufficient amount of time, whereby the cobalt conversion coating is formed. The substrate may be aluminum or aluminum alloy, as well as Cd plating, Zn plating, Zn-Ni plating, and steel. The cobalt-III hexacoordinated complex may be present in the form of [Co(NH.sub.3).sub.6 ]X.sub.3 wherein X is Cl, Br, NO.sub.3, CN, SCN, Y.sub.3 PO.sub.4, SO.sub.4, C.

Abstract: A chip breaker drill bushing is provided for a metal drilling apparatus. The bushing has a central channel through which a drill bit or drilling tool extends and rotates. The bushing is shaped at the workpiece end to collect metal offal carried up by the drill. Angled troughs guide the offal up and away from the workpiece and cutting edges on the end of the bushing chop the strands into small, easily handled chips.