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This SAE Aerospace Information Report (AIR) describes procedures for use in the field to determine if 115/200 Volt, 400 Hz aircraft external electrical power connectors are excessively worn, which may result in the inability of the external power plug to be retained, intermittent electrical performance and arcing.

A first attempt to study civil aircraft operations comprehensively, prior to having the airplane, occurred before the initial operation of U.S. subsonic jets. One airline carried out a manual-simulated “paper jet” operation lasting fifteen months. Today, computerized simulation of machines, methods, and operations has become commonplace, and replaces the slide rule and tedious day-by-day inputs of aircraft operational criteria. Computerized simulations are also applied to every aspect of the SST design and operations. These are important, but the results being should be used with caution and judgement.

Airline tenants at Dallas/Fort Worth International Airport (DFW Airport) use deicing/anti-icing chemicals, as may be needed, to maintain wintertime operations. DFW Airport has implemented best management practices for pollution prevention measures relating to deicing/anti-icing activities. However, as the planes leave the deicing pads, deicing/anti-icing fluids can drip from the planes onto the runways, taxiways, and ramp areas. As planes take off, the fluids can also shear off onto Airport property. During winter storm events, these deicing/anti-icing fluids are flushed off the runways, etc., with the stormwater. Stormwater containing deicing/anti-icing fluids can discharge through outfalls into Trigg Lake located in the southwestern part of the DFW Airport property.

This work presents a comprehensive numerical model for ice accretion and Ice Protection System (IPS) simulation over a 2D component, such as an airfoil. The model is based on the Myers model for ice accretion and extended to include the possibility of a heated substratum. Six different icing conditions that can occur during in-flight ice accretion with an Electro-Thermal Ice Protection System (ETIPS) activated are identified. Each condition presents one or more layers with a different water phase. Depending on the heat fluxes, there could be only liquid water, ice, or a combination of both on the substratum. The possible layers are the ice layer on the substratum, the running liquid film over ice or substratum, and the static liquid film between ice and substratum caused by ice melting. The last layer, which is always present, is the substratum. The physical model that describes the evolution of these layers is based on the Stefan problem. For each layer, one heat equation is solved.

The factors involved in the selection of a quick-disconnect are grouped into the following classifications for the purpose of discussion: (a) Functional considerations. (b) Weight considerations. (c) Environmental performance factors. (d) End fitting types. (e) Additional considerations.

The factors involved in the selection of a quick-disconnect are grouped into the following classifications for the purpose of discussion: (a) Functional considerations. (b) Weight considerations. (c) Environmental performance factors. (d) End fitting types. (e) Additional considerations.

The factors involved in the selection of a quick-disconnect are grouped into the following classifications for the purpose of discussion: (a) Functional considerations. (b) Weight considerations. (c) Environmental performance factors. (d) End fitting types. (e) Additional considerations.

The factors involved in the selection of a quick-disconnect are grouped into the following classifications for the purpose of discussion: a Functional considerations. b Weight considerations. c Environmental performance factors. d End fitting types. e Additional considerations. A quick-disconnect coupling as used in this AIR is one that can be rapidly and repetitively connected and disconnected without excessive fluid loss. The relative importance of the design factors depends upon the fluid medium of the particular system in which quick-disconnect is to be used. The effect of the fluid media on each factor is discussed in this report where applicable.

The purpose of this SAE Aerospace Information Report (AIR) is to provide management, designers, and operators with information to assist them to decide what type of power train monitoring they desire. This document is to provide assistance in optimizing system complexity, performance and cost effectiveness. This document covers all power train elements from the point at which the gas generator energy is transferred to mechanical energy for propulsion purposes. The document covers engine power train components, their interfaces, transmissions, gearboxes, hanger bearings, shafting and associated rotating accessories, propellers and rotor systems as shown in Figure 1. This document addresses application for rotorcraft, turboprop, and propfan drive trains for both commercial and military aircraft. Information is provided to assist in; a. Defining technology maturity and application risk b. Cost benefit analysis (Value analysis) c. Selection of system components d.

A new system has been developed to meet the difficult requirements for aircraft operation in low visibility conditions. Unlike automatic systems, this system utilizes and enhances the pilots' flying ability through a holographic head-up display which provides bright, clear information across a wide field of view. The information presented is monitored to ensure probabilities of misleading the pilot to be on the order of one part in 10−8. The system is now undergoing verification tests in a B-727 turbo jet aircraft with the objective to obtain certification for use in CAT IIIa, 700 feet visibility conditions.

The purpose of this SAE Aerospace Information Report (AIR) is to present a quantitative approach for evaluating the performance and capabilities of an Engine Monitoring System (EMS).

Airline aircraft maintenance and ground support services meet at the connection points for ground service. Ground power must be applied to the aircraft, but responsibility for the aircraft receptacle falls to aircraft maintenance. This responsibility gap is not currently being addressed by the industry. For years any difficulty in applying power to an aircraft on the ground has been blamed solely on the ground power cable or generator. Any potential problems with the receptacles was largely ignored by ground service personnel, since they are not allowed to touch the aircraft. No one thought to look closely at the receptacle as a potential source of the inability to reliably apply power to the aircraft (in fact, routine maintenance A,B,C or D maintenance did not routinely check or change the receptacle).

The Rocketdyne Division of Rockwell International Corporation is currently researching and evaluating the use of Artificial Intelligence and in particular Expert System technologies for the monitoring of large space-based electric power systems such as NASA's Space Station Freedom (SSF). Power System Security of space borne and lunar based electrical power systems provide unique challenges to power system software design engineers. The major responsibility of Power System Security is the monitoring of the state of health of the Power Distribution System. The role of system security is to ensure that uninterrupted electrical power of high quality is distributed to all the load centers [1]. Voltage, current, power source reliability, and power quality are main components that describe the integrity of an electrical power system and fall into the area of security control.

There is a trend in modern space systems to contain as much of the data processing function in the spaceborne component as possible. This relieves much of the operational burden of the ground support systems, but places inordinate requirements on the spaceborne systems. Future systems will need orders of magnitude improvements in processing power, reliability/availability and function while requiring equal decreases in cost, weight and power consumption. These considerations will shape the technologies and architectures of spaceborne data processing systems for the foreseeable future.

This document specifies the general functional and performance requirements for a self-propelled, boom type aerial device equipped with an aircraft deicing/anti-icing fluid (ADF) spraying system. The unit shall be highly maneuverable for deicing and anti-icing all exterior surfaces of wide-body and narrow-body aircraft, e.g., B747 and DC9. The vehicle shall be suitable for day and night operations. The vehicle and all associated systems shall operate satisfactorily under the temperature conditions between -40 and 50 °C (-40 and 122 °F) and in continuous humidity of up to 100%. It is not within the scope of this document to specify a comprehensive set of technical design criteria for aircraft deicing/anti-icing vehicles but only those relating to functional and performance requirements.