Browse Topic: Thrust reversers

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Custom Flexible ShaftsTBMG-3336212/01/2018
S.S. White Technologies St. Petersburg, FL 727-626-2800
Tech Briefs: October 201818AERP1010/01/2018
Detecting Drones with Doppler-Based Radar Digital Transformation for a Connected Enterprise Using Electromagnetic Brakes to Keep Thrust Reversers in Place Thermostatic Solutions for Temperature Control Applications Bringing RF into the Embedded World: It's Time Compact Power Amplifier Solution for Electronic Warfare Burner Rig Testing of A500® C/SiC Test method simulates, in a laboratory environment, the service conditions ceramic-matrix composite material would experience in turbine engine exhaust applications. Space Debris Orbit and Attitude Prediction for Enhanced and Efficient Space Situational Awareness Developing accurate models to predict the behavior of manmade debris in space could be the key to preventing collisions with satellites. Maintaining Enterprise Resiliency Via Kaleidoscopic Adaption and Transformation of Software Services (MEERKATS) Implementing new technologies to create a more resilient, secure cloud computing environment. Fundamental Aspects of Single Molecule
Using Electromagnetic Brakes to Keep Thrust Reversers IN PLACETBMG-3301810/01/2018
Applying reverse thrust redirecting engine power to oppose the direction of travel is a standard technique for decelerating aircraft after touchdown. The approach saves wear on the brakes of the landing gear wheels and reduces stopping distance. Although accidental deployment of the thrust reverser cowl could and did happen, it was assumed for decades that this would only present a hazard in the moments around takeoff and landing. With changes to engine design and aircraft aerodynamics, this assumption no longer held, as demonstrated by the catastrophic loss of Lauda Air Flight 004.
Guidelines for Time-Limited-Dispatch (TLD) Analysis for Electronic Engine Control SystemsARP5107C (Current)09/04/2018
This SAE Aerospace Recommended Practice (ARP) provides methodologies and approaches which have been used for conducting and documenting the analyses associated with the application of Time Limited Dispatch (TLD) to the thrust control reliability of Full Authority Digital Engine Control (FADEC) systems. The TLD concept is one wherein a fault-tolerant system is allowed to operate for a predetermined length of time with faults present in the redundant elements of the system, before repairs are required. This document includes the background of the development of TLD, the structure of TLD that was developed and implemented on present generation commercial transports, and the analysis methods used to validate the application of TLD on present day FADEC equipped aircraft. Although this document is specific to TLD analyses (for FADEC systems) of the loss of thrust control, the techniques and processes discussed in this document are considered applicable to other FADEC system failure effects
E-36 Electronic Engine Controls Committee
Reverse ThrustAIR6064 (Current)05/07/2018
Propulsion measurements and thrust methods presented in the current published versions of AIR1703 and AIR5450 place a primary focus on the engine reactionary force (thrust) acting to propel an aircraft in the forward direction. In contrast, this document addresses the use of the engine reactionary force in the opposite direction (reverse thrust) to supplement aircraft deceleration. This document’s application spans commercial and military transport turbofan engine applications for various engine and reverse thrust configurations. The discussion and examples primarily focus on separate flow exhaust turbofan engines. Piston and turboprop variable-pitch propeller blade applications are not covered. Although reverse thrust has been utilized for in-flight deceleration, primarily for short takeoff and landing aircraft and military fighter applications, this application of reverse thrust is only covered in a cursory manner.
E-33 In Flight Propulsion Measurement Committee
Architecture and Parameter Optimization for Aircraft Electro-Hydraulic Power Generation and Distribution Systems2015-01-241409/15/2015
The All-Electric-Engine with only electrical power offtake is a main goal in aircraft system development. The use of electric-motor pumps instead of engine-driven pumps for powering the central hydraulic systems could be a part of this objective. Additionally, the concept would meet the incremental development strategy performed by the aerospace industry today and saves costs by using state-of-the-art hydraulic actuation technology. This paper describes a process for optimizing such systems regarding their architecture and design parameters. For this task a methodology for the hydraulic consumer allocation called OPAL is used and extended by an automatic power system sizing. Feasible allocations, called permutations, are determined on the basis of preliminary system safety assessments regarding multiple top failure events. In the next step an automated sizing of the permutations is performed based on simplified hydraulic load analyses. This enables a comparison of a large number of
Dunker, Carsten, Bornholdt, Riko, Thielecke, Frank, Behr, Robert
Simulation-Driven Methodology for the Requirements Verification and Safety Assessment of Innovative Flight Control Systems2015-01-247809/15/2015
The paradigm shift to focus on an enhancement of existing aircraft systems raises the question which of the many possible incremental improvements results in an advantageous solution still considering all existing requirements. Hence, new methodologies for aircraft system design are a prerequisite to cope with such huge and complex design spaces. In the case of flight control system optimization, major design variables are the control surface configuration and actuation as well as their functional allocation. Possible architecture topologies have to be verified inter alia with respect to system safety requirements. In this context, flight dynamic characteristics and handling qualities of the fully operational as well as of several degraded system states of each topology have to be evaluated and checked against common specifications. A model-based verification of the requirements is favorable, resulting in a rapid reduction of the design space. Safety objectives for valid configurations
Kreitz, Tobias, Bornholdt, Riko, Krings, Matthias, Henning, Karsten, Thielecke, Frank
Composites design optimization for automated fiber placement15MEIP03_0303/01/2015
Coriolis Composites and SAFRAN Aircelle worked together on a thrust reverser component demonstrator made with carbon-fiber-reinforced plastic (CFRP) material and an AFP process. Complex composites structures are becoming more common, especially in aeronautics. Composites preforms can now be manufactured by automated processes, such as automated fiber placement (AFP) and automated tape laying (ATL), to achieve the expected production volumes. The AFP process is the most interesting since it can address complex double-curvature layup surfaces with good productivity rates and low material scrap, according to Coriolis Software. The main advantages of this technology are that material can be steered to address the problem of curvature, and fiber angular deviation from the engineering rosette can be easily managed. This opens interesting possibilities to optimize the design of composites structures and to change the current traditional “black metal” approach of design offices.
Composites Design Optimization for Automated Fiber Placement Process2014-01-226109/16/2014
Today, the design and optimization of complex 3D composites structures is managed by taking into account engineering and manufacturing constraints. If the manufacturing process is automated, especially using a robot, these constraints are particularly complex and a difficult compromise needs to be reached. Most of the technology available on the market, dedicated to automated processes offline programming, neglects some of these constraints, or can only highlight the manufacturing defects without any automatic or manual tools to solve the tape course programming issues. A new innovative approach has been developed to include engineering, material and process specifications, to help designers and NC programmers to optimize the final layup program in terms of structural properties and productivity rate. An aerospace case study using the automated fiber placement (AFP) process will be presented to highlights these offline programming capabilities.
Blanchard, Yvan
Small Airplane Considerations for the Guidelines for Development of Civil Aircraft and Systems2013-01-223309/17/2013
On September 30, 2011, certification authorities released Advisory Circular 20-174[1], Development of Civil Aircraft and Systems, which recognizes the Society of Automotive Engineers (SAE) Aerospace Recommended Practice (ARP) 4754A and the European equivalent ED-79A [2], in order to address “the concern of possible development errors due to the ever increasing complexity of modern aircraft and systems.” ARP4754A/ED-79A describes a process of development assurance which helps reduce the risk of design errors in the development of aircraft systems. This process is necessary for complex systems not easily comprehended by deterministic analyses or tests. This ARP was developed “in the context of Title 14 of the Code of Federal Regulations (14 CFR) part 25,” a category which includes complex systems such as full fly-by-wire flight controls. However, this paper shows that such systems are the exception to most, recent civil airplane designs. Of new airplanes designed in the last 10 years
Voros, Robert E.
Power Electronic and Powerplant Environment2013-01-208109/17/2013
The power plant is the area in an aircraft where they are a lot of power conversion. The power plant is the core of the aircraft from energy point of view. The engines allow to take off but not only, it also provides energy to the aircraft from many different manners. They are electrical, hydraulic, mechanical, …. The power plant is definitively a power generator but also a power consumer. Since now some years, the power electronic technology is spread into the aircraft. One can say that some pedigree has been collected with this technology embedded to the aircraft. For the power plant domain, it is different. This technology is really not usual for use. Our environment is really not friendly and even if the integration of the power converters has been improved over the last years, there is not a lot of space around the engines. These are probably the mains reason of the low deployment of the power electronic in this domain but not only. The reliability of the thrust function is
Ambroise, Richard
Automatic Braking System (ABS)ARP4102/2A (Current)07/31/2012
This document recommends design criteria for an Automatic Braking System. The ABS shall enhance braking performance under most aircraft configurations and all runway conditions.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Determination of the Operational Environment of the Propeller Blades on Beech 1900D Aircraft2008-01-222608/19/2008
Data obtained from digital flight data recorders are used to assess the actual operational environment of propellers on a fleet of Beech 1900D aircraft in commuter role. Information is given on various aerodynamic parameters as well as those pertaining to engine and propeller usage. The takeoff rotation has been identified as the most demanding phase of flight in terms of unsteady loads exerted on the propeller blades. Special attention is paid to ground operations.
Dorfling, J., Kliment, L. K., Rokhsaz, K., DeFiore, T., Nguyen, C., Turnberg, J. E.
Design Objectives for Handling Qualities of Transport AircraftARP4104 (Current)07/11/2007
This document specifies the requirements for the design objectives for handling qualities applicable to transport aircraft operating in the subsonic, transonic, and supersonic speed range. These objectives are not necessarily applicable to rotor or VTOL aircraft.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Appendix C Electronic Display Symbology for Engine DisplaysARP4102/7_APXC (Current)07/10/2007
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Electronic DisplaysARP4102/7 (Current)07/10/2007
This document recommends criteria for electronic displays on the flight deck of transport aircraft. Electronic displays include electronic flight instruments, alert displays, aircraft system displays and control/display units for flight management and radio management systems.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Guidelines for Time-Limited-Dispatch (TLD) Analysis for Electronic Engine Control SystemsARP5107A (Historical)01/28/2005
This SAE Aerospace Recommended Practice (ARP) provides methodologies and approaches which have been used for conducting and documenting the analyses associated with the application of Time Limited Dispatch (TLD) to the thrust control reliability of Full Authority Digital Electronic Control (FADEC) systems. The TLD concept is one wherein a redundant system is allowed to operate for a predetermined length of time with faults present in the redundant elements of the system, before repairs are required. This document includes the background of the development of TLD, the structure of TLD that was developed and implemented on present generation commercial transports, and the analysis methods used to validate the application of TLD on present day FADEC equipped aircraft. Although this document is specific to TLD analyses (for FADEC systems) of the loss of thrust control, the techniques and processes discussed in this document are considered applicable to other FADEC system failure effects or
E-36 Electronic Engine Controls Committee
Study of Lightning Effects in Aircraft2004-01-323611/16/2004
Lightning is a high voltage and high current phenomenon and it originates by build up of electrical charge in the air or, more commonly, in clouds. It is constituted of an electric current peak of short duration (0,5 ms) and high intensity (200 kA), followed by a low intensity (400 A) but high duration (1s) periods. The lightning effects in aircraft can be divided in two groups: direct effects (physical effects such as melting, rupture, damage of surfaces and structures due to conduction of lightning current or high power magnetic force) and indirect effects (electromagnetic fields generating levels of transient voltage and current on interconnecting wiring and cable leads within the equipment circuits eventually damaging internal components). The objective of this work is present and discuss the lightning effects and, subsequently, possible lightning protection applied to aircrafts by establishing adequate conductive paths for lightning current to flow through the aircraft structure
Baldacim, Sandro Aparecido, Cristofani, Nivaldo, Santos, Carlos do Nascimento, Lautenschlager, José Rui
Automatic Braking System (ABS)ARP4102/2 (Historical)06/23/2004
This document recommends design criteria for an Automatic Braking System. The ABS shall enhance braking performance under most aircraft configurations and all runway conditions.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Monolithic Structure Affordability: 737 Classic Versus Next Generation2003-01-290909/08/2003
One recent evolution in commercial transport structure has been the emergence of monolithic structure applications. Monolithic structure reduces the number of parts that must be managed, eliminates sub-assembly operations and contributes strongly to determinant assembly practices. The cost of three components from the Boeing 737-200 and their counterparts on the Boeing 737-600 will be compared. The mid 1960's 737-200 components were assembled from sheet metal details. The mid 1990's 737-600 components are monolithic designs and utilize superplastic forming, casting and NC machining technologies. The built-up solutions and the monolithic solutions are compared based on cost infrastructures from the 1960's and the 1990's.
Weber, Gary R., Morgan, Jeffrey D.
Cessna establishes its SovereigntyAEROAPR02_0604/01/2002
The company finalizes development of the Sovereign and prepares it for FAA certification, which is expected late this year. Engineers at Cessna Aircraft Co. recently conducted the first engine run for the Sovereign. The aircraft's power plant is one of the few remaining systems being tested prior to first flight, which is scheduled for early spring. FAA certification is expected to be awarded in late 2003, with customer deliveries beginning in early 2004. The Sovereign will be powered by two Pratt & Whitney PW306C engines, each with a takeoff thrust of 5686 lb flat-rated to ISA +15°C, enabling a cruising speed of up to 444 kts. Controlled by dual Full Authority Digital Electronic Control (FADEC) systems and using a single-pivot thrust reverser design, the engine has 3000 h HIS and 6000 h TBO maintenance intervals. The company has finalized the design of the aircraft's engine nacelle assembly, which consists of the engine cowling, inlet assembly, throttle quadrant, and thrust reverser
Applicability of System Safety Processes and Operational Risk Management Training for Future Pilots2001-01-263609/11/2001
System safety is taught as a discipline in some aeronautical programs. Such a course maybe designed to prepare career-minded aviation students with a solid background to face the technical intricacies of the commercial flight arena. Over the course of the past decade, the complexity of large modern transport category aircraft has grown, and along with that growth the command and control functions built into the avionics and flight control systems have become automatic. Most new pilots entering into the cockpits of these aircraft require an understanding of how to manage these new systems in light of the basic design principles used. One excellent method of providing education for students in aeronautical studies is through courses in system safety and operational risk management (ORM). The advantage of doing this is to provide an aircrew member sufficient understanding of the logic processes and analysis inherent in system safety to permit him to quickly learn how to handle issues and
Reynolds, Randolph S.
A Paradigm for Developing Operational Decision-Making (ODM) Training2001-01-302709/11/2001
The views and opinions expressed in this paper are solely those of the authors. They do not necessarily represent the positions or policies of any private, public or governmental organizations. Over the past 8 years, the authors have been developing a training-oriented paradigm for operational decision-making in the cockpit. While our emphasis has been on the civil aviation side, the model can easily adapted for the business aviation venue. The paradigm began to form at an aeronautical decision-making workshop in 1992 (Lofaro, Adams and Adams; 1992) around an expanding set of interrelated concepts. The set expansion resulted from the authors continuing to wrestle with identifying and explicating the critical components and processes for real-time operational decision-making, as well as the relationships among decision-making, crew resource management (CRM) and situation awareness (SA). The first paradigm component was the “rising risk continuum” (Lofaro and Smith, 1993), as embedded in
Smith, Kevin M., Lofaro, Ronald John
Building a familyAEROAPR01_0401/01/2001
Fairchild Dornier takes the family approach to developing its various regional jet aircraft. To remain competitive as well as meet the market demands of regional airlines, Fairchild Dornier has adopted the strategy of developing a family of aircraft. The latest series of aircraft under development by the company begins with the 70-passenger 728JET, which is scheduled to enter service in 2003. This aircraft will be followed by the 50-passenger 528JET in 2004 and the 100-passenger 928JET in 2005. Strong cost competition has forced major airlines to form global alliances so they could achieve control of the regional air transport systems. Airlines now also play an important role in the decision-making processes of regional aircraft manufacturers. They require comfort equivalent to large aircraft standard, the same level of reliability, all-weather capability, and a turn-around time less than 20 min-but at a lower cost than today's turboprops.
Solution of an Engine Inlet Compatibility Problem During C-17 Low Cost N/EAT Nacelle Thrust Reverser Development2000-01-557910/10/2000
The C-17 transport aircraft is established in military service with unique capabilities to ground maneuver using thrust reversers. Recently, the C-17 has undergone fan thrust reverser re-design to reduce cost. The new Nacelle/Engine Affordability Team (N/EAT) nacelles are now fully qualified but had, during the flight test program, revealed an engine inlet compatibility problem. Flight tests, engineering analyses and practical applications that led to a successful N/EAT fan reverser cascade design modification are discussed. Fabrication methods that enabled timely implementation of the solution and flight test results showing successful resolution of the problem are presented.
Johns, Christopher J.
Defining the Operational Structural Loading of Commercial Transport Systems by Airborne Data Monitoring98120004/06/1998
The application of individual airplane structures and systems tracking to commercial transports has been slow. This paper discusses a procedure by which data collected on a representative sample of a commercial transport fleet can be used to understand aircraft loading cycles on systems and structures.
Barnes, Terence J., Hempe, David W.
Guidelines for Time-Limited-Dispatch (TLD) Analysis for Electronic Engine Control SystemsARP5107 (Historical)06/01/1997
This SAE Aerospace Recommended Practice (ARP) provides methodologies and approaches which have been used for conducting and documenting the analyses associated with the application of Time Limited Dispatch (TLD) to the thrust control reliability of Full Authority Digital Electronic Control (FADEC) systems. The TLD concept is one wherein a redundant system is allowed to operate for a predetermined length of time with faults present in the redundant elements of the system, before repairs are required. This document includes the background of the development of TLD, the structure of TLD that was developed and implemented on present generation commercial transports, and the analysis methods used to validate the application of TLD on present day FADEC equipped aircraft. Although this document is specific to TLD analyses (for FADEC systems) of the loss of thrust control, the techniques and processes discussed in this document are considered applicable to other FADEC system failure effects or
E-36 Electronic Engine Controls Committee
Condition Monitoring and Diagnostics Increase Safety and Reduce Operating Costs96560310/01/1996
Accurate information derived from monitoring the contamination level of the hydraulic fluid in an aircraft allows the development of a diagnostic system. Using this approach, maintenance can be based on actual condition of the aircraft's Fluid Power System. Servicing the system and its components based on known condition rather than on arbitrary service, or time intervals reduces unscheduled maintenance and has a major impact on reducing operating costs. Safety, reliability, and predictable availability of the aircraft are significant benefits of this approach to maintenance.
Juhasz, Charles, Bybee, Jim
Hydraulic System Simulator Model For Boeing 77796560610/01/1996
To optimize the hydraulic system design and evaluate the system performance at the airplane level, a complete dynamic integrated hydraulic model is needed. This paper describes the development and usage of a dynamic model for the Boeing 777 hydraulic system. This model dynamically simulates the hydraulic power available as a function of the airplane events. This not only allows the designers to test their design prior to building the hardware but it also serves as a tool to evaluate the hydraulic system performance at the airplane level.
Wang, David S.
Development of the McDonnell Douglas MD-9095205209/01/1995
Douglas developed the MD-90, an IAE V2500-powered derivative of the MD-80, to satisfy a customer need for a more environmentally - friendly 150-seat, short/medium range jet transport. The program was launched in late 1989 with requirements to: significantly reduce community noise and engine emissions improve aircraft fuel efficiency make other technical improvements where cost effective for the customer. The aircraft was certificated in November 1994 and entered airline service in April 1995. The MD-90 meets all of its technical requirements.
Kressly, Arthur E., Parker, Anthony C.
The 3x Jet Engine Configuration95117305/01/1995
An advanced, unconventional two-engine jet configuration shows considerable promise of significantly reducing operating costs, dramatically improving two-engine climb performance, extending range and increasing safety.
Bacon, Richard, Roskam, Jan
Pilot and Controller Communications: Incidents Reported to the NASA Aviation Safety Reporting System94213710/01/1994
The NASA Aviation Safety Reporting System (ASRS) receives voluntarily submitted aviation incident reports from pilots, air traffic controllers, and other participants within the National Airspace System. The incident reports are evaluated and categorized into categories describing the incident event. One of the many areas that are evaluated in these reports is communication or information transfer issues. Information transfer issues represent one of the largest categories of problems contained in these reports. The present paper describes ASRS 1993 data on eleven communication problems areas. The communication problem areas of Readback/Hearback and Phraseology were further evaluated for (1) the types of reported incident anomalies associated with these problems, (2) the evaluation of who was the original reporter, (3) who attributed to the primary problem, and (4) the phase of flight where the incident occurred.
Connell, Linda J.
High Bypass Separate Flow Exhaust System Improved Thrust Efficiency By Modifying the Aft Centerbody93262209/01/1993
Scale model data indicated a performance dip in nozzle thrust efficiency at the cruise design conditions for a high bypass separate flow derivative exhaust system. A performance improvement program was implemented to determine the cause of the reduction in thrust efficiency and to identify viable redesigns. Data analysis indicated the performance loss to be a result of high Mach number fan and core exhaust interactions adversely affecting the pressure force on the exhaust system centerbody. Scale model testing confirmed the cause of performance loss and demonstrated that modifying the aft centerbody to reduce the plume Mach number recovers the loss in exhaust system thrust efficiency.
Babbitt, Bob
Nacelle Automatic Riveting92241910/01/1992
Increasing world competition is forcing U.S. industry to find new ways to not only survive, but excel, in the rapidly expanding global economy. The production side of manufacturing currently faces pressure to keep down cost and, at the same time, improve quality. The use of increasingly powerful, yet flexible, part-handling/positioning systems, along with their associated automatic riveting machines, can help. A semirobotic part-positioning system and elevated automatic riveter used for the assembly of aircraft engine nacelles and extremely contoured panels including control schemes, applications, and implementation are discussed.
Pekar, Gary W.
A Study of Decision Making and Performance in Rejected Takeoffs92113407/01/1992
A study was conducted in a B-737 full flight simulator at the Boeing Customer Training facility to evaluate pilot decision making and performance under various situations in which decisions on whether or not to reject a take off had to be made and executed. A total of eight (8) situations were defined in which Go/NoGo decisions had to be made near V1 speed. Subjects included 24 Boeing instructor pilots and 24 line pilots from five different airlines. The sequence in which pilots encountered the situations was carefully balanced across subjects to control for learning effects. The results of the study are reported as quantitative data on RTO decisions, stopping performance, and procedure accomplishment plus a summary of data derived from post-run debriefings of the airline pilots. Lessons learned, conclusions, and recommendations for RTO training are presented.
Roberson, William C., Shontz, William D.
The C-17: Modern Airlift Technology91196709/01/1991
Three SAE technical papers in recent years have addressed the C-17 program: “C-17 Technical Description” by Robert van't Riet, presented 8 March 1989, and “C-17 Flight Control System” by Alex Brown, and “Meeting the C-17 Reverse Thrust Requirements” by Frank Junkermann, both presented 3 October 1988. This paper provides an update of these previous presentations by members of the McDonnell Douglas C-17 team. The paper discusses technology adapted from commercial aircraft for military airlift; the military requirement to move large cargo items long distances and land on short runways, which drove C-17 design; and significant design alternatives and the solutions selected.
Tavernetti, Leonard R.
Results and Lessons Learned from the STOL & Maneuver Demonstration Program91200509/01/1991
The STOL and Maneuver Technology Demonstrator (S/MTD) Program has validated a set of technologies that give a supersonic fighter all-weather Short Takeoff and Landing (STOL) performance while also enhancing up-and-away maneuverability. Significant reductions in both takeoff and landing distances, compared with the unmodified F-15, have been measured. The additional pitch control power of thrust vectoring has been demonstrated up to 30° angle of attack. The effectiveness of up-and-away reversing has been identified. First, major flight test results are presented and then lessons learned from this integration program are discussed.
Moorhouse, David J., Laughrey, James A.
Use of Thrust Vectoring and Reversing on the S/MTD91117304/01/1991
A main objective of the STOL and Maneuver Technology Demonstrator, (S/MTD) Program was to evaluate the operability and performance of its unique engine/nozzle configuration which can deliver thrust in three different modes; conventional, vectored and through variable vanes which give the option of going from forward to reverse thrust. The two-dimensional nozzle and the modified engine were extensively tested during sea level and altitude testing to satisfy all flight clearance requirements. This paper concentrates on the flight test results of the various modes of vectoring and reversing ending with a compilation of the actual usage of the propulsive controls that could be used by designers of similar advanced propulsion systems.
Laughrey, J. A.
Factors Affecting Pilot Decision-Making in Rejected Takeoffs90234412/01/1990
Runway overruns following high speed rejected takeoffs (RTOs) have resulted and continue to result in airplane incidents and accidents. Although most high speed RTOs are executed without incident, the potential for an incident or an accident remains high. Since 1988 for example, four high speed RTO incidents and accidents occurred, two of which resulted in destroyed airplanes and one of those, fatalities. In response to the RTO incidents and accidents, the National Transportation Safety Board issued a Special Investigation Report which examined training and procedures used in the recognition of the need for and the execution of high speed RTOs. This report examines the pilot decision-making aspects of initiating and executing an RTO that were found in the Special Investigation. It discusses the deficiencies found in pilot training and procedures as well as recommendations offered to address those deficiencies.
Strauch, Barry
Advanced Materials and the Pivoting Door Reverser90198609/01/1990
HUREL-DUBOIS patented a new concept of thrust reverser in 1981 known as “the door forward reverser”. It gives numerous advantages over the conventional cascade reverser, and in particular is inherently lighter. The extensive use of advanced materials has allowed a highly competitive weight to be achieved. This paper describes the work currently under way for the pivoting door reverser for the ROLLS-ROYCE Trent engine and covers: Thrust Reverser door structure predominantly in composite. Acoustic treatment with composite sandwich. IFS design with carbon bismaleimide material This reverser will be used on MD11 and Airbus A330 aircraft.
Fourrier, Alain, Jouan, Jean-Alain
Carbon Epoxy Perforated Skin for Nacelle Acoustic Treatment90198209/01/1990
The acoustic treatment requirement for jet engine nacelle inner flowpath leads to using perforated skin. Formerly in light alloy these skins are now composite and new techniques have been developped to achieve the perforation. After reviewing different possible techniques (mandrel tool, abrasion, stamping, mechanical drilling,…) one process is chosen and described in terms of skin mechanical properties, cost, and production facilities.
Hersen, R., Vigneron, D.
Fire Barrier Coatings and Their Uses90095704/01/1990
Fire barrier coatings are being used to protect nacelle and cowling components by insulating the surfaces from excessive heat exposure during normal flight operations and to provide a fire barrier in the event of an engine fire. Design criteria, formulating, considerations, application methods, and typical performance characteristics for such systems will be discussed.
Brannfors, J. E.
The Ergonomie Integrated Flight Deck89261212/01/1989
A coordinated flight deck design concept is presented, which takes into account human capabilities and limitations such as fit and function, seating, internal and external vision, reach, and safety. In addition to incorporating operational requirements, the concept covers amenities such as coffee cup holders, footrests, provisions for food service, storage of personal items such as suitcases and clothing, and maps, flight manuals, and charts. The design is brought together with computer-aided drafting procedures as well as sophisticated human modeling techniques, enabling a step-by-step assessment of the resulting configuration.
Stone, Gerald
Propulsion Integration for Military Aircraft89223409/01/1989
ABSTRACT The transonic aerodynamic characteristics for high-performance aircraft are significantly affected by shock induced flow interactions as well as other local flow interference effects which usually occur at transonic speeds. These adverse interactions can not only cause high drag, but can cause unusual aerodynamic loadings and/or severe stability and control problems. Many new programs are underway to develop methods for reducing the adverse effects, as well as to develop an understanding of the basic flow conditions which are the primary contributors. It is anticipated that these new programs will result in technologies which can reduce the aircraft cruise drag through improved integration as well as increased aircraft maneuverability through the application of thrust vectoring. This paper will identify some of the primary propulsion integration problems for high performance aircraft at transonic speeds, and demonstrate several methods for reducing or eliminating the
Henderson, William P.
A Status Report on the FAA Low Visibility Simulation88077502/01/1988
Oliver, Joseph G.
RB211 Developments87240911/13/1987
This paper examines briefly the growth prospects of long haul civil air transportation in the Pacific basin and the contribution made by the RB211-524 in the Boeing 747. The development of the latest committed version of this engine giving over 60,0001b static thrust is described as well as the design of the proposed 65,0.001b static thrust RB211-524L powerplant. Finally the prospects for new Ultra High Bypass Ratio cowled turbofans for long haul operation in the next century are reviewed.
Pickerell, D. J.
Commercial Supersonic Operations - Ten Years of Experience With Concorde86168310/01/1986
This paper is intended to give a brief overview of Concorde development and in-service operations to date. It identifies the features peculiar to Concorde as a supersonic transport and the various problems and major incidents encountered during development and service flying. Finally it covers in-service experience and identifies the most troublesome items.
Swadling, S.J.
Faulty Cockpit Communication as a Factor in the Failure of Flight 9085185910/14/1985
Through transcript analysis of Air Florida's flight 90 it was determined the crash might have been prevented if proper flight deck procedures had been followed. This paper examines various facets that come into play when cockpit communications break down or become inefficient for the task at hand. Aspects dealt with include: casualness on the flight deck; lack of decisive command; improper implementation of problem solving strategies; and the concept of role differentiation, specifically as it relates to the captain acting as copilot when the first officer is handling the controls. Complacency as a result of cockpit automation, and diminishing vigilance due to technological advances are considered as problem areas. The increase in safety and reduction of operational complexity, as a result of technological innovations, is offered as a potential area of concern for flight crew alertness. A conclusion drawn from research indicates the need exists for more effective crew training in the
Couchman, Darlene A.
STOL and Maneuver Technology85115807/01/1985
This paper describes the Short Takeoff and Landing (STOL) and Maneuver Technology Demonstrator. It relates government requirements for performance and for specific technology to be developed. The two-dimensional, thrust vectoring and reversing engine exhaust nozzle and its integration with the control system are described. The use of modern control system design techniques to meet evolving criteria for aircraft handling during the STOL task is discussed. Use of on-board sensors to substitute for ground-based approach aids used in weather is outlined. Expected performance improvements in takeoff and landing and in maneuvering flight are related to the technology being demonstrated. The paper closes with a discussion of the potential tactical and strategic impact of the technology.
Borowski, Richard A.
Integration of the PW2037 Engine Electronic Control System in the Boeing 757 Airplane84155410/01/1984
A full authority, dual channel, digital electronic control system on the PW2037 engine has been integrated into the 757 airplane that is scheduled for delivery late in 1984. The system allows optimizing engine performance without sacrificing engine stability and also integrates with the digital avionics system in the airplane, permitting simplified propulsion system operation and unprecedented availability of operating and maintenance information to the flight and ground crews.
Kuhlberg, J.F., Newirth, D.M., Kniat, J.
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