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This specification describes the general connectors, contacts, and backshells in their shape and characteristic for cabin systems for commercial aircrafts. ARINC 600, ARINC 404, and ARINC 801 connector specifications are published as independent standards.

This specification describes the general connectors, contacts, and backshells in their shape and characteristic for cabin systems for commercial aircrafts. ARINC 600, ARINC 404, and ARINC 801 connector specifications are published as independent standards.

This document defines a secure Wi-Fi distribution network installed in the aircraft passenger cabin for passenger and crew use. Carry-on Portable Electronic Devices (PEDs) such as smart phones, tablets, and laptops may use this network to access public internet services provided on the aircraft.

Small aircraft and helicopters have an increasing need for heads out presentations, which means a projected presentation of symbols and images, primarily infrared, on an optical combiner in the pilots field of view. The information presented will appear at an infinite distance i.e. the focal point is far away enabling the pilot to see the symbology superimposed on and correlated to the outside world. The driving factors for a heads out presentations are increased safety through improved situation awareness in almost all weather conditions as well as operational improvements due to reduced landing minimal prerequisites in adverse weather conditions. Also safety during taxiing and landing are improved through early detection of eventual other aircraft and objects. The landing aid is important for small aircraft like business jets that often fly into unequipped airfields. The overall benefits are reduction in number of incidents/accidents, cost savings and reduced number of diversions.

Electroimpact Automatic Fiber Placement (AFP) machines lay-up composite parts by accurately placing carbon fiber tow (strips of impregnated carbon fiber) on a mould. In order to achieve high accuracy at high speeds, the processes of feeding and cutting tows must be tuned. Historically, the tuning has been a time-consuming, manual process. This paper will present a methodology to replace manual measurements with an automated laser, improve measurement speed by an order of magnitude, improve accuracy from +/? 0.020? (manual) to +/? 0.015? (laser), and eliminate human error. Presenter Joshua Cemenska, Electroimpact Inc.

The Aircraft Interiors subscription addresses the specialized needs and mechanical requirements for aircraft cabin interior design. The application of these standards will aid in the efficient and cost-effective manufacture of quality aircraft components. The standards in this resource include: Glossary of Technical and Physiological Terms Related to Aerospace Oxygen Systems Flight Deck Layout and Facilities Numeral, Letter and Symbol Dimensions for Aircraft Instrument Displays Oxygen Equipment for Aircraft Human Interface Design Methodology for Integrated Display Symbology

The 21 papers in this technical paper collection cover driver crash avoidance behavior; factors that influence drivers’ response choice decisions; collision avoidance systems; steering wheel switch technology; effects of hands-free phone conversation on visual behavior; seat support evaluation; and more.

This report defines the requirements and recommended practices for production testing of aircraft passenger seats and seat groups. Production testing is performed at the seat manufacturers' facilities prior to the shipment of the seats to the airframe manufacturers, Maintenance, Repair, and Overhaul (MRO), or airlines/operators for installation in the aircraft. Using this guidance, rework is minimized and schedules remain minimally affected.

ARINC 661 defines logical interfaces to Cockpit Display Systems (CDS) used in all types of aircraft installations. The CDS provides graphical and interactive services to user applications within the flight deck environment. When combined with data from user applications, it displays graphical images to the flight deck crew. The document emphasizes the need for independence between aircraft systems and the CDS. This document defines the interface between the avionics equipment and display system graphics generators. This document does not specify the "look and feel" of any graphical information, and as such does not address human factors issues. These are defined by the airline flight operations community. Supplement 7 adds the definition of: Selector Widget, Tree Widget, New FormatString options, Readouts available in MapItems, Provisions for Touch Screen Displays.

Abstract It is reasonable to use a two-phase heat transfer loop (TPL) in a thermal control system (TCS) of spacecraft with large heat dissipation. One of the key elements of TPL is a heat-controlled accumulator (HCA). The HCA represents a volume which is filled with vapor and liquid of a single working fluid without bellows. The pressure in a HCA is controlled by the heater. The heat and mass transfer processes in the HCA can proceed with a significant nonequilibrium. This has implications on the regulation of TPL. This article presents a mathematical model of nonequilibrium heat and mass transfer processes in an HCA for microgravity conditions. The model uses the equations of mass and energy conservation separately for the vapor and liquid phases. Interfacial heat and mass transfer is also taken into account. It proposes to use the convective component k for the level of nonequilibrium evaluation.

Abstract Improving the energy performance of batteries can increase the reliability of electric aircraft. To achieve this goal, battery management systems (BMS) are required to keep the temperature within the battery pack and cells below the safety limits and make the temperature distribution as even as possible. Batteries have a limited service life as a result of unwanted chemical reactions, physical changes that cause the loss of active materials in the structure, and internal resistance increase during the charging and discharging cycle of the battery. These changes usually affect the electrical performance of batteries. Battery life can be increased only by reducing or preventing unwanted chemical reactions. Lithium-ion (Li-ion) batteries are a suitable option due to their high specific energy and energy density advantages. In this study, the necessity of heat management is emphasized. The discharge tests of the Li-ion battery provided 94.6 Wh under 10C and 90.9 Wh under 1C.

• Define sub-roles within the primary J3016 roles • Define different human capabilities and list what those are (including definition of “capability”) • Frame issues • Document open questions

This SAE Recommended Practice applies to both Original Equipment Manufacturer (OEM) and aftermarket message-generating systems for light and heavy vehicles. The recommended practice covers both message prioritization and presentation (including simultaneous display of messages) for visual and auditory modalities. In addition, this recommended practice will consider temporal aspects of external events (e.g. merging into heavy traffic, time-to-collision) and their impact on temporal presentation and format (including multi-modal) of messages.

pilots, air traffic controllers, dispatchers, aviation meteorologists

The aim of this document is to provide a comprehensive synopsis of regulations applicable to aircraft oxygen systems. The context of physiological requirements, international regulations, operational requirements and airworthiness standards is shown to understand the role of aircraft oxygen systems and to demonstrate under which circumstances is needed on aircraft. With regards to National Aviation Regulations States are committed to the Convention on International Aviation (Chicago Convention). The majority of states have adopted, with some deviations, FAA and EASA systems including operational and airworthiness requirements. Accordingly the extent of this document is primarily focused on FAA/EASA requirements.

This document describes operational scenarios and examples of system operation based on the experience of different developers of airborne wake vortex safety systems. This information is intended to supplement the recommendations and guidance given in ARP 6267 “Airborne Wake Vortex Safety Systems” as well as facilitate the application of other wake vortex standards and guidance documents generated by SAE and RTCA.

The intent of this document is to provide example of acceptable protection strategies that can be used to achieve the performance required by the AS5722

This document shall address the emergency oxygen system and typical cabin environmental requirements for private and commercial transport aircraft which fly at altitudes above 40,000 feet, by discussing current technologies and certification procedures, which have enabled routine flights at those altitudes.

This SAE Aerospace Standard defines a bulkhead coupling (with different fitting end styles), which is used in bulkhead cone connection fittings installed in high pressure (3000 psi) oxygen systems for the purpose of mating to applicable oxygen equipment. Dimensions developed from AND10089, Detail Specification Sheet for Fitting End, Design Standard, For Cone Connection.