Browse Topic: Pitot-static instruments

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IAQG-03282025-1 IAQG-03282025-1 (Current)04/02/2025
IAQG-03282025-1
IAQG-1 Standards Committee
Experimental and Numerical Investigations of Sprays in Crossflow in Aftertreatment Systems2021-01-059604/06/2021
Selective catalytic reduction (SCR) of oxides of nitrogen (NOx) with gaseous ammonia is the leading technology used to meet on- and off-highway NOx emission standards across the world. In typical SCR systems, a low-pressure injector introduces a solution of urea and water (UWS) into hot exhaust gases leading to atomization and subsequent spray processes that finally lead to production of gaseous ammonia. Through their synergetic effect, the UWS injector and mixing enhancement devices (such as static mixers or baffles) help deliver a uniform mixture of ammonia and NOx to the SCR catalyst with minimal urea-derived solid deposits. To develop an efficient and robust aftertreatment system, it is essential to have experimental and simulation capabilities to assess the behavior of sprays under flow conditions representative of engine exhaust. The experimental part of the present work uses an optically accessible, cold- or hot-flow capable test section (called Insitu test section) that allows
Munnannur, Achuth, Blessinger, Matthew, Liu, Z. Gerald
Flight Test Procedures for Static Pressure Systems Installed in Subsonic Transport AircraftARP921B (Current)12/22/2020
This SAE Aerospace Recommended Practice (ARP) covers the test procedures and equipment for performing flight testing on pitot-static systems installed in subsonic transport type aircraft.
A-4 Aircraft Instruments Committee
Maximum-Allowable-Airspeed Instruments (Turbine Powered Subsonic Aircraft)AS437B (Current)12/22/2020
This SAE Aerospace Standard (AS) covers one type of maximum-allowable-airspeed instrument which gives a continuous indication of both indicated airspeed and maximum allowable airspeed not exceeding 650 knots.
A-4 Aircraft Instruments Committee
Maximum-Allowable-Airspeed Instruments (Turbine Powered Subsonic Aircraft)AS437B-TEST-REC (Historical)12/22/2020
This SAE Aerospace Standard (AS) covers one type of maximum-allowable-airspeed instrument which gives a continuous indication of both indicated airspeed and maximum allowable airspeed not exceeding 650 knots.
A-4 Aircraft Instruments Committee
Air Data Computer – Minimum Performance StandardAS8002B (Current)04/28/2020
This SAE Aerospace Standard (AS) covers air data computer equipment (hereinafter designated the computer) which when connected to sources of aircraft electrical power, static pressure, total pressure, outside air temperature, and others specified by the manufacturer (singly or in combination) provides some or all of the following computed air data output signals (in analog and/or digital form) which may supply primary and/or standby flight instruments: Pressure Altitude Pressure Altitude, Baro-Corrected Vertical Speed Calibrated Airspeed Mach Number Maximum Allowable Airspeed Over-speed Warning Total Air Temperature
A-4 Air Data Subcommittee
Barometry for Altimeter CalibrationAIR1075B (Current)02/20/2020
This SAE Aerospace Information Report (AIR) is concerned only with aspects directly relating to available accuracy. While well-designed photoelectric, inductive or capacitive readers and pressure regulators, and other accessories are highly desirable for convenience and production rate, they are considered to be outside the scope of this AIR.
A-4 Aircraft Instruments Committee
Maintenance of Pitot-Static Systems of Transport AircraftAIR975B (Current)02/20/2020
In efforts to increase the accuracy and reliability of altimetry, speed measurement and other aspects of air data, a great deal of attention and money have been expended on new and refined pressure transducing and computing systems and on the standards by which they are calibrated. So much progress has been made in this that the limiting factor is, or may soon be, the sensing and transmitting in the aircraft of the pressures to be transduced. Until the appearance of References 1-13 and 18 there was little guidance available on the maintenance of pitot and static systems. This report presents what information is available, suggests limits, and lists the principal original papers on the subject.
A-4 Aircraft Instruments Committee
Collins Aerospace provides avionics for C-130H modernization programSAE-MA-0000209/03/2019
The Lockheed C-130H Hercules fleet operated by the Air National Guard and U.S. Air Force Reserve is getting new Collins Aerospace Systems avionics that will help extend the life of the legacy aircraft by 20 years.
Kucinski, William
ADAPTORS AND SEALS FOR PIPE CONNECTIONS TO AIRCRAFT PITOT/STATIC INSTRUMENTS AND ASSOCIATED EQUIPMENTTSC47-017_0104/19/2018
No Scope available.
Training and Qualification Program for Deicing/Anti-icing of Aircraft on the GroundAS6286 (Historical)11/29/2016
This document establishes the minimum training and qualification requirements for ground based aircraft deicing/anti-icing methods and procedures. All guidelines referred to herein are applicable only in conjunction with the applicable documents. Due to aerodynamic and other concerns, the application of deicing/anti-icing fluids shall be carried out in compliance with engine and aircraft manufacturers’ recommendations. The scope of training should be adjusted according to local demands. There are a wide variety of winter seasons and differences of the involvement between deicing operators and the level and length of training should therefore be adjusted accordingly. However, the minimum level of training shall be covered in all cases. As a rule of thumb, each hour of classroom training should at least equal the same amount (or include more) of practical training wherever this is relevant. Both basic and recurrent practical training shall be performed and documented periodically.
G-12T Training and Quality Programs Committee
Pressure Altimeter SystemsAS8009C (Current)05/24/2016
This SAE Aerospace Standard (AS) specifies minimum performance requirements for pressure altimeter systems other than air data computers. This document covers altimeter systems that measure and display altitude as a function of atmospheric pressure. The pressure transducer may be contained within the instrument display case or located remotely. Requirements for air data computers are specified in AS8002. Some requirements for nontransducing servoed altitude indicators are included in AS791. This document does not address RVSM requirements because general RVSM requirements cannot be independently detailed at the component level. The instrument system specified herein does not include aircraft pressure lines. Unless otherwise specified, whenever the term “instrument” is used, it is to be understood to be the complete system of pressure transducer components, any auxiliary equipment, and display components. The test procedures specified herein apply specifically to mechanical type
A-4 Air Data Subcommittee
SOFIA Closed- and Open-Door Aerodynamic AnalysesTBMG-1264701/01/2012
Work to evaluate the aerodynamic characteristics and the cavity acoustic environment of the SOFIA (Stratospheric Observatory for Infrared Astronomy) airplane has been completed. The airplane has been evaluated in its closed-door configuration, as well as several open-door configurations (see figure). Work performed included: acoustic analysis tool development, cavity acoustic evaluation, stability and control parameter estimation, air data calibration, and external flow evaluation.
FLIGHT TEST PROCEDURES FOR STATIC PRESSURE SYSTEMS INSTALLED IN SUBSONIC TRANSPORT AIRCRAFTARP921 (Historical)08/10/2011
This Aerospace Recommended Practice covers the test procedures and equipment for performing flight testing on pitot-static systems installed in subsonic transport type aircraft.
A-4 Aircraft Instruments Committee
Aircraft Damage Caused by Ground Support EquipmentAIR1589A (Historical)12/09/2009
Only those incidents where a piece of ground support equipment directly associated with the "turnaround" servicing of an aircraft was involved are reviewed. Specifically excluded are those incidents that occurred during heavy maintenance, overhaul activity, or aircraft taxiing.
AGE-3 Aircraft Ground Support Equipment Committee
MINIMUM SAFE PERFORMANCE OVER SPEED WARNING INSTRUMENTSAS8007 (Current)02/16/2008
This AS defines instruments which use inputs of static and pitot pressure equal to those which are utilized to establish the pressure altitude and speed of that aircraft. These pressures are applied to the instrument ports to provide means for generation of an aural warning whenever the aircraft reaches or exceeds the maximum operating limit speed. This Over Speed Warning Instrument function may be incorporated as part of an Air Data Computer, or an Air Speed Indicator, or an Air Speed/Mach Number Indicator, or other instruments. In those cases where the Over Speed Warning Instrument is part of another instrument, the standards contained herein apply only to the Over Speed Warning Instrument function. Each aircraft type and model has a defined maximum operating limit speed curve or curves which are a part of the airframe manufacturer's type certification approval data; this limit speed data shall be available from the subject airframe manufacturer as published in the operating manual
A-4 Air Data Subcommittee
Experimental Investigation into the Temperature and Heat Transfer Distribution around Air-Cooled Cylinders2006-32-003911/13/2006
This paper describes an experimental investigation into the surface heat transfer coefficient of finned metal cylinders in a free air stream. Ten cylinders were tested with four different fin pitches and five different fin lengths. The cylinders and their fins were designed to be representative of those found on a motorcycle engine with an external cylinder diameter of 100mm and fin lengths of 10 to 50mm. The fins of each cylinder were gravity die cast in aluminium alloy. Each cylinder was electrically heated and mounted in a wind tunnel which subjected it to a range of air speeds between 2 and 20 m/s. The surface heat transfer coefficient, h, was found primarily to be a function of the air speed and the fin separation, with fin length having a lesser effect. In addition to the determination of an overall heat transfer coefficient, the distribution of cooling around the circumference of each cylinder was also studied. Not surprisingly, the cooling was found to be greatest on the front
Thornhill, D., Stewart, A., Cuningham, G., Troxler, P., Meyer, R., Price, B.
RVSM (Reduced Vertical Separation Minimum): Applications News to Flight Levels2005-01-402011/22/2005
The imprecision of altimeter system in higher altitudes, utilized by aircrafts in past decades, although adequate for lower levels, imposed that minimum separation between flights levels FL290 (29000 feet) and above had to be 2000 feet. This higher separation limits aircraft capacity on these levels where jets are more efficient and, therefore, is undesirable to airline companies, taking account, principally, the fuel economy. The advance of electronic technology in altimetry system has permitted to obtain a better precision of altitude measurements and, thus, reducing the minimum vertical separation between these levels to 1000 feet became safer, showed by figure 1. This process is called RVSM (reduced vertical separation minimum) and presents some characteristics such as introduction of 6 news flight levels. This process defines special requirements related to airspace and it was implemented in North America and Europe in last years. In Latin America (including Brazil), the RVSM
Cristofani, Nivaldo, Baldacim, Sandro Aparecido, Lautenschlager, José Rui
Pressure Altimeter SystemsAS8009B (Historical)09/21/2005
This SAE Aerospace Standard (AS) specifies minimum performance requirements for primary pressure altimeter systems other than air data computers. This document covers altimeter systems that measure and display altitude as a function of atmospheric pressure. The pressure transducer may be contained within the instrument display case or located remotely. Requirements for air data computers are specified in AS8002. Some requirements for nontransducing servoed altitude indicators are included in AS791. The instrument system specified herein does not include aircraft pressure lines. Unless otherwise specified, whenever the term “instrument” is used, it is to be understood to be the complete system of pressure transducer components, any auxiliary equipment, and display components. The test procedures specified herein apply specifically to analog type instruments. Digital instruments or automatic test instrumentation may require other test procedures. Such differing procedures shall be
A-4 Air Data Subcommittee
Experimental Investigation into the Free Air-Cooling of Air-Cooled Cylinders2003-32-003409/16/2003
This paper describes an experimental investigation into the surface heat transfer coefficient of finned metal cylinders in a free air stream. Eight cast aluminium alloy cylinders were tested with four different fin pitches and five different fin lengths. The cylinders and their fins were designed to be representative of those found on a motorcycle engine. Each electrically heated cylinder was mounted in a wind tunnel and subjected to a range of air speeds between 2 and 20 m/s. The surface heat transfer coefficient, h, was found primarily to be a function of the air speed and the fin separation, with fin length having a lesser effect. The coefficient increases with airspeed and as the fins are separated or shortened. It was also noted that a limiting value of coefficient exists, influenced only by airspeed. Above the limiting value the surface heat transfer could not be increased by further separation of the fins or reduction in their length.
Thornhill, D., Graham, A., Cunnigham, G., Troxler, P., Meyer, R.
Safety — An Essential Ingredient for Profitability, Managing Safety and Profitability in Airline Operations2000-01-212404/11/2000
Accidents and serious incidents are major cost factors in companies that have high consequence operations. Aviation, though having a very favorable safety level, still faces huge liabilities when accidents or serious incidents occur. This paper will argue that safety should be regarded by management as a core production value, just as other products of the company are. Examples will be drawn from the worldwide industry that show the value of low accident operation. The FSF’s ICARUS committee’s work will also be described that presents persuasive arguments for establishing aviation company cultures that place high value on accident avoidance and reduction of risk. Returns in passenger confidence and respect for the air company that translate into ridership are only part of the profit picture. Reductions of employee injuries and fatalities, reduced damage to aircraft during ground operations have heavy positive leverage on the company’s profitability. Investments by management in
Matthews, Stuart
Boundary-Layer Rake of Pitot Tubes for Flight TestingTBMG-2981912/01/1999
A boundary-layer rake of pitot tubes has been designed and built for installation on a flight-test fixture (FTF) on the NASA Dryden F-15B, which is a two-seat version of the F-15 high-performance, supersonic, all-weather fighter airplane. This boundary-layer rake will be used in flight-research projects in which there are requirements for detailed surveys of the turbulent boundary layer. A design feature unique to this rake is a curved rake body; this feature makes it possible to cluster the pitot tubes in the near-wall region more densely than they can be clustered in conventional rakes. Results of tests have shown that this rake exhibits good aerodynamic performance and that it is operationally rugged.
Improving AC-130H Gunship Performance Through Drag Reduction - A Wind Tunnel and Flight Test Partnership1999-01-550610/19/1999
Approximately 120 hours of wind tunnel testing were accomplished to determine the drag contributions of various external protuberances on the AC-130H Gunship and to recommend modifications to achieve optimal drag reduction potential. Also, the operational impact of the recommended configuration was quantified using a performance modeling code. The overall objective of this effort was to establish a solid foundation via experimental and computational ground efforts to support flight test of drag reduction modifications to an aircraft. Thirteen basic AC-130H protuberances were evaluated to determine their incremental drag. A recommended reduced-drag configuration was developed which provided a drag reduction potential of 58.2 counts. An Air Force Research Laboratory performance modeling code (CASP) predicted that the H-model gunship could save 1,630 lbs of fuel, increase its radius 57.4 nmi, or increase its loiter time by 30.0 minutes in a typical combat mission with the recommended
Yechout, Thomas R., Dowty, Jonathan C.
Advanced Measurement of Angle of Attack and SideslipTBMG-3229711/01/1998
Nearly every military and commercial aircraft in the United States today uses pitot-static probes for accurate, repeatable airdata measurements. Recently, local angle-of-attack- and sideslip-sensing capabilities have been added to these probes to satisfy requirements for advanced aircraft with extended maneuvering envelopes. Probes made in advanced shapes to satisfy these requirements have been evaluated in wind-tunnel tests at angles of attack up to 90°, with favorable results. Flight tests of the Advanced L-probe Air Data Integration (ALADIN) program, directed toward evaluating the performances of these probes, were recently concluded at NASA Dryden Flight Research Center.
Teaching Aircraft Flight Performance in Aeronautical Engineering Using PC-Based Flight Simulation98553009/28/1998
This paper describes some ways in which PC-based flight simulation can be used to teach aircraft flight performance and flight testing to aeronautical engineering students. Two PC-based flight simulation programs are used here for this purpose: the Jeppesen FS200 PCATD and Microsoft Flight Simulator 98. Examples of student flight test assignments using these programs are given for cruise (straight and level, unaccelerated) flight, climbs, descents (power off glide), and for (level) maneuvering flight. Simulation flight test data from these assignments are presented and compared to theory. It is concluded that PC-based flight simulation can be a valuable tool for illustrating flight performance and flight testing to aeronautical engineering students and can be challenging, interesting and fun for students.
Baughn, James, Wolf, Jason
DESIGN AND INSTALLATION OF PITOT-STATIC SYSTEMS FOR TRANSPORT AIRCRAFTARP920A (Current)10/01/1996
This SAE Aerospace Recommended Practice (ARP) covers the design and installation requirements for pitot-static systems.
A-4 Aircraft Instruments Committee
BAROMETRY FOR ALTIMETER CALIBRATIONAIR1075A (Historical)09/01/1996
This SAE Aerospace Information Report (AIR) is concerned only with aspects directly relating to available accuracy. While well-designed photoelectric, inductive or capacitive readers and pressure regulators, and other accessories are highly desirable for convenience and production rate, they are considered to be outside the scope of this AIR.
A-4 Aircraft Instruments Committee
AIR DATA COMPUTER - MINIMUM PERFORMANCE STANDARDAS8002A (Historical)09/01/1996
This SAE Aerospace Standard (AS) covers air data computer equipment (hereinafter designated the computer) which when connected to sources of aircraft electrical power, static pressure, total pressure, outside air temperature, and others specified by the manufacturer (singly or in combination) provides some or all of the following computed air data output signals (in analog and/or digital form) which may supply primary flight instruments: Pressure Altitude Pressure Altitude, Baro-Corrected Vertical Speed Calibrated Airspeed Mach Number Maximum Allowable Airspeed Overspeed Warning Total Air Temperature In addition, the computer may supply one or more of the following signals: Pressure Altitude, Digitized Equivalent Airspeed True Airspeed Static Air Temperature Altitude Hold Airspeed Hold Mach Hold Angle of Attack Flight Control Gain Scheduling Others
A-4 Air Data Subcommittee
FLIGHT TEST PROCEDURES FOR STATIC PRESSURE SYSTEMS INSTALLED IN SUBSONIC TRANSPORT AIRCRAFTARP921A (Historical)09/01/1996
This SAE Aerospace Recommended Practice (ARP) covers the test procedures and equipment for performing flight testing on pitot-static systems installed in subsonic transport type aircraft.
A-4 Aircraft Instruments Committee
MAINTENANCE OF PITOT-STATIC SYSTEMS OF TRANSPORT AIRCRAFTAIR975A (Historical)09/01/1996
In efforts to increase the accuracy and reliability of altimetry, speed measurement and other aspects of air data, a great deal of attention and money have been expended on new and refined pressure transducing and computing systems and on the standards by which they are calibrated. So much progress has been made in this that the limiting factor is, or may soon be, the sensing and transmitting in the aircraft of the pressures to be transduced. Until the appearance of References 1-13 and 18 there was little guidance available on the maintenance of pitot and static systems. This report presents what information is available, suggests limits, and lists the principal original papers on the subject.
A-4 Aircraft Instruments Committee
Magnesium Heat Sink Evaluations93041503/01/1993
A system has been constructed to estimate heat dissipated from geometrically identical heat sinks and pinfins extruded from magnesium (M1A) and aluminum (6063-T5)alloys. Two longitudinal fins of circular cross sectional area, machined from aluminum and magnesium, are used to calibrate the equipment. Thermocouples were mounted on an aluminum connecting cylinder between a heater and the pin fins or heat sinks. Insulation around this same cylinder and the heater keeps most of the heat flowing axially to be dissipated by the pin fins and heat sinks. Thermocouples were also mounted on the longitudinal fins to measure temperature distribution. Measured temperature distributions on the aluminum and magnesium pin fins were in good agreement with theoretical models. After calibration of the measuring equipment, the heat dissipated through actual aluminum and magnesium heat sinks was measured as a function of air velocity over the heat sinks. Aluminum and magnesium heat sinks were then tested at
Brown, James F., Riopelle, Lisabeth
Altitude Measurement Capability as Related to Altitude Measurement Performance90197209/01/1990
Height-keeping capability is defined as an aircraft's capability to measure altitude and to hold that altitude while flying. This paper examines the difference between altitude measurement capability as designed into an aircraft and actual altitude measurement performance as measured through operational flight testing for various types of aircraft. It defines an altimetry system error model that can be used to develop system standards for both airframe error measurements and altimetry instrument errors. The paper addresses airframe-related questions of static source sensor tolerances, manufacturing tolerances, production line tolerances, calibration accuracy, and calibration repeatability. It also addresses questions of in-service use effects, such as static pressure sensing degradation for both static probe systems and flush static port systems. The information presented in this paper is being used to develop altimetry system requirements that could allow vertical separation standards
Schust, Alex P.
Second Generation Airliner Dry Stripping (PMB) Following Boeing's Specifications90097104/01/1990
On May 3, 1985, Republic Airlines (now Northwest Airlines) dry stripped with plastic media blast (PMB) their first DC-9 aircraft in Atlanta, Georgia. Four days later, Hill Air Force Base began production in their new facility designed to dry strip F-4 fighter aircraft in Ogden, Utah. These two important steps initiated the first generation of airline and military production PMB dry stripping. After this inception of the PMB process, numberable questions were raised pertaining to structural safety after being subjected to dry stripping. In the intervening four years, process improvements have been made and test data accumulated to verify safety of the PMB process. Boeing, with approval by the Federal Aviation Administration (FAA), has issued their specification for plastic media (PMB) dry stripping of airframes, Document D6-54705, PLASTIC MEDIA ABRASIVE STRIPPING OF ORGANIC FINISHES. We consider this to be the start of the second generation airliner dry stripping program. In this paper
Pauli, Robert, Taylor, William
The Current Status of the Flight Test of the ASKA88143310/01/1988
The four engined Upper Surface Blowing (USB) STOL research aircraft ASKA was developed by National Aerospace Laboratory of Japan and has been in the flight test phase to provide various kinds of flight data. The position error in airspeed and angle of attack is discussed, and the low speed performance demonstrated in the flight test is provided by the figures of lift/drag coefficient curves and V-Gamma plot. Several indications of powered lift and dynamic stability derivatives obtained from the V-Gamma plot are discussed. The flight measured pitching moment shows the distinctive features such as pitch up tendency. The wing-body pitching moment and the downwash angle are analyzed from the flight load measurments of the horizontal tail. The ground effect of the ASKA is also presented quantitatively in this paper. THE QUIET SHORT TAKE-OFF AND LANDING (STOL) capability is very beneficial for the Japanese domestic aviation, since airports have short runways in the vicinity of the
Okada, Noriaki, Masui, Kazuya, Yamato, Hiroyuki, Kuriyama, Masamichi, Tobinaga, Yoshinari
BAROMETRY FOR ALTIMETER CALIBRATIONAIR1075 (Historical)10/01/1984
This AIR is concerned only with aspects directly relating to available accuracy. While well-designed photoelectric, inductive or capacitive readers and pressure regulators, and other accessories are highly desirable for convenience and production rate, they are considered to be outside the scope of this AIR.
A-4 Aircraft Instruments Committee
MAINTENANCE OF PITOT-STATIC SYSTEMS OF TRANSPORT AIRCRAFTAIR975 (Historical)10/01/1984
In efforts to increase the accuracy and reliability of altimetry, speed measurement and other aspects of air data, a great deal of attention and money have been expended on new and refined pressure transducing and computing systems and on the standards by which they are calibrated. So much progress has been made in this that the limiting factor is, or may soon be, the sensing and transmitting in the aircraft of the pressures to be transduced. Until the appearance of References 1-13 and 18 there was little guidance available on the maintenance of pitot and static systems. This report presents what information is available, suggests limits, and lists the principal original papers on the subject.
A-4 Aircraft Instruments Committee
Development and Flight Test of a Two-Place Night/Adverse Weather A-10 for the Close-Air Support and Battlefield Attack Mission79106902/01/1979
Recognizing a critical void in battlefield support tactical air capability in night and adverse weather, a Fairchild sponsored activity was undertaken to develop, build and critically evaluate a near term, cost-effective solution consisting of an enhancement of the highly effective A-10 system. The objective was to incorporate an effective integration of proven avionics with appropriate displays and presentations into a modified A-10, and to demonstrate night/adverse weather tactical effectiveness using this system to exploit the A-10's tactics and munitions. The N/AW A-10 has been demonstrated to be a formidable and viable night-low level penetrator with outstanding lethality.
Williamson, John M., Shawler, Wendell
System Integration in Business Aircraft Avionics74034602/01/1974
There is an increasing need for improved efficiency in flight operations of business aircraft while preserving the operational flexibility that is essential to the business aircraft mission. The growing complexity of the air traffic control environment coupled with new regulatory demands has spawned the development of new avionic devices to meet the new requirements. These devices must be integrated into the avionic equipment complex in a manner that fits the normal pattern of pilot activity and does not increase his workload. The operational integration will result in less overall avionic system complexity, fewer interface compatibility problems, improved reliability and lower cost of ownership.
Wohlers, A.K.
A Fluidically-Augmented Artificial Feel System for High Performance Aircraft70078502/01/1970
Of the several types of pitch axis artificial feel systems currently in use in fighter and attack aircraft the most common is the bobweight, spring, and viscous damper type, and variations on it. The current project of NAVAIRDEVCEN is to augment and improve this type of feel system through the use of fluidic devises. Such augmentation will improve the handling qualities of aircraft by reducing variations in stick force for a given maneuvering response; will reduce the weight and inertia of the feel system; will permit tailoring of the feel system performance over the flight envelope.
Jansen, Tor W., Kaniuka, Walter W.
Engine Performance for the Business Jets70020902/01/1970
The pilot flying one of today's business jets has a high precision tool at his command. Some of the same basic principles of flying piston-powered airplanes still apply; however, with the jet engine he is faced with revising some of his operating and handling techniques. These changes in techniques have been brought about by increased engine thrusts, increased speeds, longer range, and higher altitudes. It is the purpose of this paper to explain some of these new characteristics associated with the high performing jet engine, such as, engine ratings, installation effects, operating limitations, thrust setting procedure, engine performance, engine check-out and testing, airplane range. The interrelationship of these characteristics are discussed to show the importance of proper engine operation so the operator can gain maximum performance from the business jet.
Smith, Lawrence D.
DESIGN AND INSTALLATION OF PITOT-STATIC SYSTEMS FOR TRANSPORT AIRCRAFTARP920 (Historical)10/01/1968
This Aerospace Recommended Practice covers the design and installation requirements for pitot-static systems.
A-4 Aircraft Instruments Committee
AS8679 Arrangement of Banjo Fittings, Pitot Static SystemsAS8679-2 (Current)10/11/1967
No scope available.
Engine and Airframe Technical Standards Committee (TSC)
C-5A Flight Control System67057402/01/1967
The C-5A flight control system is explained with individual schematics illustrating each subsystem. Several mechanical failure situations and necessary pilot actions are described. The distribution of hydraulic power and its importance on an airplane which uses fully powered hydraulic flight controls is explained. The handling quality requirements and some results of ground based simulation studies are presented.
Jamison, Gene S.
AS8681 Banjo Body, Static. Pitot Static SystemAS8681-2 (Current)12/12/1966
No scope available.
Engine and Airframe Technical Standards Committee (TSC)
AS8683 Banjo Bolt, Static. Pitot Static SystemAS8683-1 (Current)10/11/1966
No scope available.
Engine and Airframe Technical Standards Committee (TSC)
AS8680 Banjo Bolt, Pitot. Pitot Static SystemAS8680-1 (Current)10/11/1966
No scope available.
Engine and Airframe Technical Standards Committee (TSC)
AS8682 Banjo Bolt, Pitot. Pitot Static SystemAS8682-1 (Current)10/11/1966
No scope available.
Engine and Airframe Technical Standards Committee (TSC)
AIR DATA COMPUTERAS417 (Historical)02/01/1965
This Aerospace Standard covers an air data computer characterized by the concept of transducing and computing the majority of air data requirements for an aircraft. The display instruments and other using subsystems are not considered in this scope except where they perform computing operations for output parameters as covered by this specification. The computer may accept the inputs and provide the outputs listed in paragraphs 2.1 and 2.2 respectively. The computer may also provide an altitude encoder output for IFF Mark X ¯ ¯ (SIF)/Air Traffic Control Radar Beacon System SIF/ATCRBS; in which case AS 855* "Altitude Device Providing Outputs for Automatic Pressure Altitude Reporting" shall be referred to for applicable minimum standards. (Note - Reference to air data computer in subsequent paragraphs will be designated as "instrument".)
A-4 Aircraft Instruments Committee
Angle of Attack as an Aid to Flying65025002/01/1965
Application of the early ideas of Wilbur and Orville Wright, in regards to angle of incidence, has provided the Navy with an effective method of controlling airplane approach and landing speeds. The current Navy angle-of-attack systems have commercial applications for use in landing, clear air turbulence, stall warning and other flight regimes. The most important application of the angle-of-attack, to date, has been its use with automatic throttle for control of speed in approaches and landings. The angle-of-attack system provides optimum reference for auto-throttle operation regardless of aircraft weight, bank angle, flap settings, “g” loading and engines in operation.
Tuomela, Commander C. H.
DISCUSSION OF SOME DESIGN PROBLEMS ASSOCIATED WITH ARTIFICIAL FEEL SYSTEMS OF AIRPLANES WITH IRREVERSIBLE POWERED FLIGHT CONTROLS60026001/01/1960
A basic study was conducted on the longitudinal stick free static and dynamic stability for airplanes with irreversible power control. Methods of improving the airplane flying and handling qualities are presented. With regard to the stick free static stability, trim reversal was apparently eliminated by means of a Mach compensation device which improved the characteristics of stick force speed stability. Stick forces per airplane normal acceleration in steady-state maneuvering flight were tailored to meet the requirements of the military specification by incorporating a Q-bellows bleed air subsystem into the artificial feel system. In the stick free dynamic analysis, residual oscillations of airplane normal acceleration following a step stick force input and control forces in sudden pull-ups have been studied for various feel systems. The system exhibiting the most satisfactory performance was the one which comprised a Q-bellows with Mach and dynamic pressure compensation devices, very
FENG, TSUN-YING, NEIL, DONALD C.
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