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The scope of this ARP, "Startle Effect" and Crew Performance, includes pilots of turbine powered transport category aircraft and may also pertain to general aviation, the military, and/or other sectors of aircraft operations. It is focused on flight crews certified by the United States, however, may also pertain to crews certified by other countries.

A 10 KWe dual-mode space power system concept has been identified which is based on INEL's Small Externally-fueled Heat Pipe Thermionic Reactor (SEHPTR) concept. This power system will enhance user capabilities by providing reliable electric power and by providing two propulsion systems; electric power for an arc-jet electric propulsion system and direct thrust by heating hydrogen propellant inside the reactor. The low thrust electric thrusters allow efficient station keeping and long-term maneuvering. The direct thrust capability can provide tens of pounds of thrust at a specific impulse of around 730 seconds for maneuvers that must be performed more rapidly. The direct thrust allows the nuclear power system to move a payload from Low Earth Orbit (LEO) to Geosynchronous Earth Orbit (GEO) in less than one month using approximately half the propellant of a cryogenic chemical stage.

Design requirements for the Cardinal included a takeoff ground roll of 300 ft, a landing ground roll of 400 ft, cruise at 350 knots with a range of up to 1500 nm with reserves, payload of 24 passengers and baggage for a commercial version or a military version with a 10,000 lb payload, capable of carrying two GE F110 engines for the F-14D, and a spot factor requirement of 60 feet by 29 feet.

Systems such as the one being investigated are likely to be suitable for the More-Electric Aircraft (MEA) concepts presently under industry and military study. The present Sundstrand single-channel testbed is being further expanded to better understand the electrical system performance characteristics and power quality requirements of an MEA in which traditional mechanical subsystems are replaced by those of a “more-electric” nature.

Therefore, ice shapes resulting from tests with the same icing similarity parameters are compared to each other allowing the assessment of icing scaling laws for helicopter applications. This paper presents the icing scaling laws used at Airbus Helicopters on blade profiles, the different test set ups and test models and it presents the comparison of the ice shapes collected during the icing wind tunnel test campaigns. ...Different Airbus Helicopters main rotor blade profiles were tested in different icing wind tunnels and for different icing conditions. ...One of the objectives of the accretion tests was to validate the use of 2D icing scaling laws established for fixed wing aircraft on helicopter blade profiles. Therefore, ice shapes resulting from tests with the same icing similarity parameters are compared to each other allowing the assessment of icing scaling laws for helicopter applications.

A helicopter blade profile was tested in the DGA Aero-engine Testing's icing altitude test facility S1 in Saclay, France during the winter of 2013/2014. ...The airfoil was a helicopter main rotor OA312 blade profile made out of composite material and with a metallic erosion shield.

These capabilities are illustrated by the MUSTPAC-1, a portable 3-D ultrasound telemedicine system recently developed for the U.S. military. Design, implementation, and field experiences with the MUSTPAC-1 are discussed, and extensions for use in space are proposed.

MRO providers are discovering ways to innovate their procedures while remaining viable and profitable through the current downturn in government spending.

This Specification defines general architectural philosophy and aircraft infrastructure for the proper use and interface of various cabin related IFE equipment. Compliance with ARINC Specification 808 allows each respective system to operate in concert when integrated with other relevant cabin equipment. ARINC Specification 808 defines standards for the aircraft 3rd Generation Cabin Network (3GCN), IFE Cabin Distribution System (CDS), wiring, connectors, power, identification codes, space envelopes, and mounting principles. Although some of these standards also apply to 3GCN wireless IFE systems, the overall 3GCN wireless IFE network specification is covered in ARINC Specification 820. The equipment itself is not a subject of this specification because it may be unique to the system manufacturer or marketplace-driven. Design guidelines are included for informational purposes as these guidelines impact the interfaces and installation of cabin equipment aboard the aircraft.

This specification defines general architectural philosophy and specific design guidance for the proper installation and interface of various cabin equipment within the seats. Consistency with this specification allows each component installed on the seat to operate in concert when integrated with other relevant cabin type equipment. Standard electrical and mechanical interfaces of the In- Flight Entertainment System (IFES) equipment for the 3rd Generation Cabin Network (3GCN) associated with the seat are defined. This equipment consists of the headphone jacks (HPJ), passenger control unit (PCU)/multi function handset (including the cord), seat video display (SVD), remote data outlet (RDO), integrated seat box (ISB) which includes the seat power box (SPB)/seat data box (SDB), remote power outlet (RPO), and in-seat cables. Appropriate definitions are also provided for other electrical devices associated with the seat control/position mechanism.

It provides CM implementation guidance for all users (CM professionals and practitioners within the commercial and industry communities, DoD, military service commands, and government activities (e.g., National Aeronautics and Space Administration (NASA), North Atlantic Treaty Organization (NATO)) with a variety of techniques and examples.

Advantages and disadvantages of each configuration were identified and specific recommendations made for both dynamic and static seals within the context of existing military specifications.

The power levels of military aircraft hydraulic systems have continued to rise. This is primarily due to higher aerodynamic loading, combined with the increased hydraulic functions and operations of each new aircraft.

The power levels of military aircraft hydraulic systems have continued to rise. This is primarily due to higher aerodynamic loading, combined with the increased hydraulic functions and operations of each new aircraft.

이 문서는 공급자가 9100의 조항을 준수하고자 할 때 AQAP-2110을 적용하는 것에 관한 정보와 지침을 제공하기 위해 작성 및 발행된 것이다. 이 문서는 AQAP-2110-SRD.2 및 IA9137로 간행된다. 이는 NATO와 산업계에서 AQAP-2110과 9100 간의 관계에 대한 이해와 활용을 촉진하기 위해 NATO와 산업계 대표들이 공동으로 작성한 것이다. 획득 국가가 자국의 조달 방법으로 대외군사판매(FMS)를 이용할 때는 AQAP가 필요할 수 있다. 이 문서는 획득 국가와 9100을 준수하고자 하는 공급 국가의 AQAP-2110 요구사항 해석에 있어 공통성을 제공하는 데에 목적을 두고 있다. 이 문서의 내용은 법적 또는 계약상의 지위를 갖지 않으며, 일체의 AQAP-2110 또는 9100 요구사항을 대체하거나 그 요구사항에 추가되는 것도 아니다. 있을 수 있는 조건의 다양성(작업 또는 공정의 유형, 사용 기기 및 관련 인원의 역량에 따르는) 때문에, 이 지침이 모든 것에 적용되는 것으로 간주하거나, 계약 요구사항 충족에 필요한 특정 수단 또는 방법을 강요하는 것으로 간주해서는 안 된다. 이해당사자들은 이러한 요구사항을 충족하기 위해 다른 수단 또는 방법을 사용할 수도 있다는 점을 알고 있어야 한다. 이 지침 사용자는 계약서에 명시되는 바와 같이 AQAP 2110 요구사항이 공급자와 하청업체가 지켜야 하는 의무사항임을 명심해야 한다.