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THIS STANDARD ESTABLISHES THE DIMENSIONAL AND VISUAL QUALITY REQUIREMENTS, LOT REQUIREMENTS, AND PACKAGING AND LABELING REQUIREMENTS FOR D-RINGS MOLDED FROM MIL-P-25732 ACRYLONITRILE BUTADIENE (NBR) RUBBER. IT SHALL BE USED FOR PROCUREMENT PURPOSES.

A wide body aircraft carries almost a half–ton of water and ice between the cabin and skin of the aircraft. The water can get on wires and connectors, which can cause electrical problems, cause corrosion and rust, and, eventually, “rain in the plane”. The speaker is the CEO of CTT Systems that has developed a system that solves the condensation by using dry air. The speaker will discuss how condensation can be prevented and how airlines can also save maintenance costs in the process. This topic is relevant for the attendees at the Aerospace Expo, as they are decision makers who need to be aware of this issue. It is also important for the MRO shows as the attendees are on the front lines of dealing with this problem.

Mobility is in the midst of an electric revolution, propelled by industry innovators such as magniX. Headquartered in Redmond, Washington, the magniX team is focused on revolutionizing electric motors for commercial aviation applications.

The scope is determine if an 'Electronic Authorized Release Certificate' is viable and what is needed to make it viable.

For human beings who have been reared on the earth with its 1 G gravitational field, the condition of weightlessness is a world with which we are unfamiliar. Even if the layout and equipment configuration of a spacecraft designed to compensate for operation under Zero-G conditions, there are some things which are not effective under actual weightless conditions. In the design of a manned spacecraft, it is necessary to accumulate design data on human performance in a weightless condition, then to undertake design evaluations and verification under weightless conditions. In this paper, testing for the purpose of evaluating the effectiveness of Zero-G simulation using neutral buoyancy, conducted first of all in Japan, and recommendations on the equipment and Facilities required to conduct such simulations, are described.

The YF-23A Advanced Tactical prototype Fighter was a revolutionary statically unstable, twin engine aircraft that cruised at supersonic speeds without afterburner and was designed to out maneuver opponents at subsonic and supersonic speeds. Combining these capabilities into a chosen aircraft configuration demanded a flight control hydraulic system of unprecedented power and performance. Increased system reliability, and reduced maintenance also presented a challenging system design. The YF-23A's unique flight and maneuvering envelope required high surface rates and large actuator excursions at low flight speeds, as well as power to generate increased hinge moments at supersonic speeds. To achieve these specifications, Northrop developed a hydraulic system that utilized flow conservation and prioritization techniques. The hydraulic system configuration was maintained by using hydrologic, as well as electronic control.

The Reflection Grating Spectrometer experiment (RGS) on the ESA corner stone X-Ray Multi-Mirror Mission (XMM) uses charge coupled devices (CCD) as detectors. Thermal requirements are the main driver for the layout of the detector housing. Parasitic heat inputs stem primarily from radiative coupling and from conduction over the structural support. Improvements in the design of the electro optical model (EOM) over the bread board model (BBM) resulted in a system that guarantees a CCD temperature of -130 °C at the end of the mission while not precluding the possibility to heat the detectors as high as +130°C which might be useful for annealing the CCDs.

In October of 1997, the Federal Communications Commission (FCC) granted two national satellite radio licenses. The FCC allocated 25 MHz of the electromagnetic spectrum (2.3 GHz frequency band) for satellite digital broadcasting to two companies: 12.5 MHz to XM Satellite Radio and 12.5 MHz to Sirius Satellite Radio. This paper is an overview of the XM Satellite Radio technology. Four major components of the overall Network are described: a) The ground segment; b) The space segment; c) The terrestrial repeater segment and the d) The technology segment. Mobile antenna design challenges are also being addressed and optimum antenna configurations are presented.

XM Satellite Radio launched its nationwide service in September of 2001. With 6.5 million subscribers at the end of the first quarter of 2006, XM is one of the fastest growing audio formats and entertainment services. This paper addresses XM's technology and content evolution, primarily for the radio unit and the signaling protocols, from the early years to the present time, and the applicability of this technology in fostering exciting new infotainment services. The radio architecture includes an antenna, an RF tuner module, a baseband chipset and a microprocessor. All of these subsystems underwent a complete transformation in the past four years from a size perspective, capability and cost. Specifically the following phases of the radio platform are addressed: a) Phase 1: The early years; b) Phase 2: The invention of the Plug and Play ; c) Phase 3: Connect and Play ; d) Phase 4; The wearable; e) Phase 5: Infotainment convergence of audio plus data services.

The development of the XB-70 research aircraft produced advancements in many fields of technology. This paper covers a few of these advancements in the areas of materials, equipment, and manufacturing. These include honeycomb construction, PH 15-7 alloy steel, vacuum melted H-11 steel, equipment capable of withstanding high temperatures, chemical milling of many different alloys, miniaturized welding equipment, and exothermic brazing techniques.

Planning for ground servicing and maintenance started in the proposal phase and has been followed by test program experience with the XB-70 Mach 3 air vehicle. Servicing and associated safety requirements are summarized. Discussion of maintenance and support actions includes mention of equipment provided to meet the requirements. Preflight, postflight, and periodic operations are outlined, along with some indication of changes that resulted when plans were put into practice. The demands of a high performance flight test air vehicle limit movements toward simplification.

A non-destructive x-ray technique, the double crystal diffractometer method, is presented as a tool to investigate the aging and deformation behavior of the Al-Li alloy. This is a sensitive method for measuring the strain and dislocation density within individual grains through the x-ray rocking curve. In addition, models were developed to describe the aging and deformation characteristics of this alloy.

X-ray is an indispensable aid in locating and determining the extent of incipient failures in structure which is inaccessible by position or covered by multiple layers of metal. It is also the most feasible method for checking oil coolers for contamination; bonded honeycomb panels for water; fuel lines for erosion; and with a 360 deg emission tube, fuselage frames for structural integrity without removing the interior upholstery and panels from the passenger compartment or cargo compartments.

This SAE Aerospace Standard (AS) covers 6-point and 12-point flare nut crowfoot, flare nut wrenches, double end flare nut wrenches, combination box end and flare nut wrenches, combination open end and flare nut wrenches, and ratcheting flare nut wrenches that are designed with the following requirements: (a) non-distorting usage; (b) possessing the strength, clearances, and internal wrenching design to be used on hydraulic tube fittings that conform to the requirements of SAE J514 and ISO 8434-2; and (c) transmitting torque to tube fittings without bearing on the apex of fitting wrenching points. Inclusion of dimensional data in this document is not intended to imply that all of the products described herein are stock production sizes. Consumers are requested to consult with manufacturers concerning lists of stock production sizes.

This SAE Aerospace Standard (AS) covers high strength thin wall (commercial) sockets, universal sockets, box wrenches and torque adaptors which possess the strength, clearances, and internal wrenching design so configured that, when mated with bi-hexagonal fasteners conforming to the requirements of AS870 for inch sizes and ISO 4095 for metric sizes, they shall transmit torque to the fastener without bearing on the outer 5% of the fastener's wrenching points. Inclusion of dimensional data in this document is not intended to imply that all the products described herein are stock production sizes. Consumers are requested to consult with manufacturers concerning lists of stock production sizes. The dimensional limits of box and combination wrench lengths have been established to provide configuration control for tool storage applications.

This SAE Aerospace Standard (AS) covers adjustable and non-adjustable spanner wrenches generally used for aerospace machinery maintenance and for tightening and loosening hose couplings and hydrant caps. Inclusion of dimensional data in this document is not intended to imply all of the products described therein are stock production sizes. Consumers are requested to consult with manufacturers concerning lists of stock production sizes.