76 FR 50111 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-12

... Directives; Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes AGENCY: Federal... Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes, certificated in any category, all...

Free-Spinning-Tunnel Investigation of a 1/24-Scale Model of the Grumman F9F-6 Airplane TED No. NACA DE 364

NASA Technical Reports Server (NTRS)

Klinar, Walter J.; Healy, Frederick M.

1952-01-01

An investigation of a 1/24-scale model of the Grumman F9F-6 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The erect and inverted spin and recovery characteristics of the model were determined for the normal flight loading with the model in the clean condition. The effect of loading variations was investigated briefly. Spin-recovery parachute tests were also performed. The results indicate that erect spins obtained on the airplane in the clean condition will be satisfactorily terminated for all loading conditions provided full rudder reversal is accompanied by moving the ailerons and flaperons (lateral controls) to full with the spin (stick right in a right spin). Inverted spins should be satisfactorily terminated by full reversal of the rudder alone. The model tests indicate that an 11.4-foot (laid-out-flat diameter) tail parachute (drag coefficient approximately 0.73) should be effective as an emergency spin-recovery device during demonstration spins of the airplane provided the towline is attached above the horizontal stabilizer.

75 FR 38394 - Airworthiness Directives; The Boeing Company Model 747-100, -200B, and -200F Series Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-07-02

... Airworthiness Directives; The Boeing Company Model 747-100, - 200B, and -200F Series Airplanes AGENCY: Federal... inconsistent with the terminology used in the structural repair manual and Boeing Alert Service Bulletin 747... The Boeing Company Model 747-100, 747- 200B, and 747-200F series airplanes, certificated in any...

Electron induced ionization of plasma processing gases: C4F x (x  =  1–8) and the isomers of C4F6 and C4F8

NASA Astrophysics Data System (ADS)

Gupta, Dhanoj; Choi, Heechol; Kwon, Deuk-Chul; Yoon, Jung-Sik; Song, Mi-Young

2018-04-01

The total ionization cross section (Q ion) for C4F x (x  =  1–8) fluorocarbons and the isomers of C4F6 and C4F8 molecules are calculated from ionization threshold to 5 keV using the binary-encounter bethe method. The targets are fully optimized using the Hartree–Fock (HF) method and density function theory (DFT) for their minimum energy structure and orbital parameters. The present Q ion with HF parameters showed good agreement with the experimental data for 1,3-C4F6, 2-C4F6, 2-C4F8 and 1-C4F8. On the other hand, the Q ion with DFT parameters are in good accordance with the recent theoretical results for 1,3-C4F6 and 2-C4F6. The Q ion for c-C4F8 showed much variation among the various results. The isomer effect in Q ion is negligible for the isomers of C4F6 and C4F8 molecules. The calculation of Q ion for C4F, C4F2, C4F3, C4F4, C4F5, c-C4F6, C4F7 and iso-C4F8 is a maiden attempt. The present cross section data are important quantities for low temperature plasma modeling especially related to the fluorocarbon plasmas.

Ditching Investigation of a 1/10-Scale Model of the North American F-86 Airplane

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; McBride, Ellis E.

1954-01-01

An investigation was made of a 1/10-scale dynamically similar model of the North American F-86 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tabular form, sequence photographs, and time-history acceleration curves. From the results of the investigation it was concluded that the airplane should be ditched at the nose-high, 14 deg attitude to avoid the violent dive which occurs at the 4 deg attitude. The flaps and leading-edge slats should be fully extended to obtain the lowest possible landing speed. The wing tanks should be jettisoned to avoid the undesirable behavior which occurs with the tanks attached. In a calm-water ditching under these conditions the airplane will run smoothly for about 600 feet. Maximum longitudinal and vertical decelerations of about 3g will be encountered.

76 FR 3854 - Airworthiness Directives; REIMS AVIATION S.A. Model F406 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-01-21

... a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We... Reims Aviation S.A. Model F406 airplanes, serial numbers (SNs) 0002, 0003, 0004, 0006, 0008, 0009, 0010... the following actions: (1) For all affected SNs except F406-0091: (i) Within the next 10 hours time-in...

Jahn-Teller effect on the [TiF 4F 4F int] 6-(C 4v) and [NiF 4F 4F int] 7-(C 4v) clusters embedded into SrF 2 crystals

NASA Astrophysics Data System (ADS)

Ulanov, V. A.; Zhiteitcev, E. R.; Varlamov, A. G.

2007-07-01

By means of EPR method the associative [TiF 4F 4F int] 6-(C 4v) and [NiF 4F 4F int] 7-(C 4v) centers were revealed in the fluorite type SrF 2:Ti and SrF 2:Ni crystals grown by Bridgman method in helium atmosphere containing some amount of a fluorine gas. It was found that at low temperatures the local structures of these associative centers were exposed to a static rhombic distortion. The reasons of such distortions were accounted for by the assumption that the E ⊗ ( b1 + b2) vibronic interaction became effective due to that the ground orbital states of the [TiF 4F 4F int] 6-(C 4v) and [NiF 4F 4F int] 7-(C 4v) centers occurred to be doubly degenerated.

Precision controllability of the F-15 airplane

NASA Technical Reports Server (NTRS)

Sisk, T. R.; Matheny, N. W.

1979-01-01

A flying qualities evaluation conducted on a preproduction F-15 airplane permitted an assessment to be made of its precision controllability in the high subsonic and low transonic flight regime over the allowable angle of attack range. Precision controllability, or gunsight tracking, studies were conducted in windup turn maneuvers with the gunsight in the caged pipper mode and depressed 70 mils. This evaluation showed the F-15 airplane to experience severe buffet and mild-to-moderate wing rock at the higher angles of attack. It showed the F-15 airplane radial tracking precision to vary from approximately 6 to 20 mils over the load factor range tested. Tracking in the presence of wing rock essentially doubled the radial tracking error generated at the lower angles of attack. The stability augmentation system affected the tracking precision of the F-15 airplane more than it did that of previous aircraft studied.

Preliminary flight test results of the F100 EMD engine in an F-15 airplane

NASA Technical Reports Server (NTRS)

Myers, L. P.; Burcham, F. W., Jr.

1984-01-01

A flight evaluation of the F100 Engine Model Derivative (EMD) is conducted. The F100 EMD is an advanced version of the F100 engine that powers the F15 and F16 airplanes. The F100 EMD features a bigger fan, higher temperature turbine, a Digital Electronic Engine Control system (DEEC), and a newly designed 16 segment afterburner, all of which results in a 15 to 20 percent increase in sea level thrust. The flight evaluations consist of investigation of performance (thrust, fuel flow, and airflow) and operability (transient response and airstart) in the F-15 airplane. The performance of the F100 EMD is excellent. Aircraft acceleration time to Mach 2.0 is reduced by 23 percent with two F100 EMD engines. Several anomalies are discovered in the operability evaluations. A software change to the DEEC improved the throttle, and subsequent Cooper Harper ratings of 3 to 4 are obtained. In the extreme upper left hand corner of the flight enveloped, compressor stalls occurr when the throttle is retarded to idle power. These stalls are not predicted by altitude facility tests or stability for the compressor.

75 FR 66700 - Airworthiness Directives; Cessna Aircraft Company (Cessna) Model 402C Airplanes Modified by...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-10-29

... Company (Cessna) Model 402C Airplanes Modified by Supplemental Type Certificate (STC) SA927NW and Model... Company (Cessna) Model 402C airplanes modified by Supplemental Type Certificate (STC) SA927NW and Model... products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the...

Active Aeroelastic Wing Aerodynamic Model Development and Validation for a Modified F/A-18A Airplane

NASA Technical Reports Server (NTRS)

Cumming, Stephen B.; Diebler, Corey G.

2005-01-01

A new aerodynamic model has been developed and validated for a modified F/A-18A airplane used for the Active Aeroelastic Wing (AAW) research program. The goal of the program was to demonstrate the advantages of using the inherent flexibility of an aircraft to enhance its performance. The research airplane was an F/A-18A with wings modified to reduce stiffness and a new control system to increase control authority. There have been two flight phases. Data gathered from the first flight phase were used to create the new aerodynamic model. A maximum-likelihood output-error parameter estimation technique was used to obtain stability and control derivatives. The derivatives were incorporated into the National Aeronautics and Space Administration F-18 simulation, validated, and used to develop new AAW control laws. The second phase of flights was used to evaluate the handling qualities of the AAW airplane and the control law design process, and to further test the accuracy of the new model. The flight test envelope covered Mach numbers between 0.85 and 1.30 and dynamic pressures from 600 to 1250 pound-force per square foot. The results presented in this report demonstrate that a thorough parameter identification analysis can be used to improve upon models that were developed using other means. This report describes the parameter estimation technique used, details the validation techniques, discusses differences between previously existing F/A-18 models, and presents results from the second phase of research flights.

Tests on a model of the D.F.W. airplane T-29 of the "Deutsche Flugzeug derke" (German airplane works)

NASA Technical Reports Server (NTRS)

Molthan, Wilhelm

1924-01-01

Experiments similar to those carried out with the A.E.G (Allgemeine Elektrizitats-Gesellschaft) were made in the small wind tunnel of the Gottingen laboratory on a model of the D.F.W. airplane T-29. Three series of tests were carried out on the model with a velocity head (or dynamic pressure) of 5 kg/sq m (1.02 lb/sq ft), during which one of the movable surfaces was deflected at various angles, while both the others were retained in their central positions. Of special interest among the results of the tests is the different run of the elevating moments. The curves for the A.E.G. model, rising to the right, denote stability with the elevator locked, while the slight inclination to the left with the D.F.W model denotes a slight instability. For the maximum C(sub L) values, the stability of A.E.G. model continues to increase and the instability of the D.F.W. model is converted into stability. The rolling moments shown when the angular deflection of the ailerons is 0 degrees are due, in both series of tests, to the unequal distribution of the air velocity over the cross section of the wind tunnel, rather than to a lack of symmetry in the model.

76 FR 63159 - Airworthiness Directives; Airbus Model A330-243F Airplanes Equipped With Rolls Royce Trent 700...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-12

... Airworthiness Directives; Airbus Model A330-243F Airplanes Equipped With Rolls Royce Trent 700 Series Engines... Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057... assemblies and along the beam structure of the right and left engine thrust reversers, detailed inspection...

77 FR 64701 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-10-23

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A300 series airplanes; Model A310 series airplanes; and Model A300 B4-600, B4-600R, and F4... that the AD be effective after Airbus completes certifying the improved design for the fuel pump half...

Supplementary Investigation in the Free-Spinning Tunnel of a 1/24-Scale Model of the Grumman F9F-6 Airplane Incorporating only Flaperons for Lateral Control, TED No. NACA DE 364

NASA Technical Reports Server (NTRS)

Klinar, Walter J.; Lee, Henry A.

1954-01-01

A supplementary investigation was conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F9F-6 airplane. The primary purpose of the investigation was to reevaluate the spin-recovery characteristics of the airplane in view of the fact that the ailerons had been eliminated from the flaperon-aileron lateral control system of the airplane. A spin-tunnel investigation on a model of the earlier version of the F9F-6 airplane had indicated that use of ailerons with the spin (stick right in a right spin) was essential to insure recovery. The results indicate that with.ailerons eliminated, it may be difficult to obtain an erect developed spin but if a fully developed spin is obtained on the airplane, recovery therefrom may be difficult or impossible. Flaperon deflection should have little effect on spins or recoveries.

North American F-100 C

NASA Image and Video Library

1958-10-07

North American F-100 C airplane used in sonic boom investigation at Wallops, October 7, 1958. Photograph published in: A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 672. -- Aircraft number: NACA 42024. Side view, 3/4 view from front, 3/4 view from rear, rear view, and two front views.

78 FR 70003 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-11-22

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model...

Augmentor performance of an F100 engine model derivative engine in an F-15 airplane

NASA Technical Reports Server (NTRS)

Walton, James T.; Burcham, Frank W., Jr.

1986-01-01

The transient performance of the F100 engine model derivative (EMD) augmentor was evaluated in an F-15 airplane. The augmentor was a newly designed 16-segment augmentor. It was tested with a segment-1 sprayring with 90 deg fuel injection, and later with a modified segment-1 sprayring with centerline fuel injection. With the 90 deg injection, no-lights occurred at high altitudes with airspeeds of 175 knots or less; however, the results were better than when using the standard F100-PW-100 engine. With the centerline fuel injection, all transients were successful to an altitude of 15,500 meters and an airspeed of 150 knots: no failures to light, blowouts, or stalls occurred. For a first flight evaluation, the augmentor transient performance was excellent.

Comparison of Ion Chemistries in Octafluoro-2-butene (2-C4F8) and in Octfluorocyclobutane (c-C4F8)

NASA Astrophysics Data System (ADS)

Jiao, Charles; Dejoseph, Charles; Garscadden, Alan

2007-10-01

2-C4F8 is one of the promising candidates to replace c-C4F8 that has been widely used for dielectric etching but is not environmentally friendly. In this study we have investigated electron impact ionization and ion-molecule reactions of 2-C4F8 using Fourier transform mass spectrometry (FTMS), and compared the results with those of c-C4F8 we have studied previously. Electron impact ionization of 2-C4F8 produces 15 ionic species including C4F7,8^+, C3F3,5,6^+, C2F4^+ and CF1-3^+ as the major ions. The total ionization cross section of 2-C4F8 reaches a maximum of 1.8x10-15 cm^2 at 90 eV. The ionization is dominated by the channel forming the parent ion C4F8^+ from 12 to 18 eV, and by the channel forming C3F5^+ from 18 to 70 eV. After 70 eV, CF3^+ becomes the dominant product ion. Among the major ions generated from the electron impact ionization of 2-C4F8, only CF^+, CF2^+ and CF3^+ are found to react with 2-C4F8, via F^- abstraction or charge transfer mechanism. The charge transfer reaction of Ar^++2-C4F8 produces primarily C4F7^+.

Concluding Report on Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395

NASA Technical Reports Server (NTRS)

Bowman, James S., Jr.

1956-01-01

An investigation has been completed in the Langley 20-foot free-spinning tunnel on a l/24-scale model of the Grumman F11F-1 airplane to determine its spin and recovery characteristics. An interim report, Research Memorandum SL55G20, was published earlier and the present report concludes the presentation of results of the investigation. Primarily, the present report presents results obtained with engine gyroscopic moments simulated on the model. Also, the current results were obtained with a revised larger vertical tail recently incorporated on the airplane. It was difficult to obtain developed spins on the model when the spin direction was in the same sense as that of the engine rotation (right spin on the airplane). The developed spins obtained were very oscillatory and the recoveries were unsatisfactory. These results were similar to those previously reported for which engine rotation was not simulated. When the spin direction was in the opposite sense (left spin on the airplane), however, developed spins were readily obtainable. Recoveries from these spins also were unsatisfactory. Satisfactory recoveries were obtained on the model, however, when rudder reversal was accompanied by extension of small canards near the nose of the airplane or by deflection of the horizontal tail differentially with the spin.

Preliminary MIPCC Enhanced F-4 and F-15 Preformance Characteristics for a First Stage Reusable Launch Vehicle

NASA Technical Reports Server (NTRS)

Kloesel, Kurt J.; Clark, Casie M.

2013-01-01

Performance increases in turbojet engines can theoretically be achieved through Mass Injection Pre-Compressor Cooling (MIPCC), a process involving injecting water or oxidizer or both into an afterburning turbojet engine. The injection of water results in pre-compressor cooling, allowing the propulsion system to operate at high altitudes and Mach numbers. In this way, a MIPCC-enhanced turbojet engine could be used to power the first stage of a reusable launch vehicle or be integrated into an existing aircraft that could launch a 100-lbm payload to a reference 100-nm altitude orbit at 28 deg inclination. The two possible candidates for MIPCC flight demonstration that are evaluated in this study are the F-4 Phantom II airplane and the F-15 Eagle airplane (both of McDonnell Douglas, now The Boeing Company, Chicago, Illinois), powered by two General Electric Company (Fairfield, Connecticut) J79 engines and two Pratt & Whitney (East Hartford, Connecticut) F100-PW-100 engines, respectively. This paper presents a conceptual discussion of the theoretical performance of each of these aircraft using MIPCC propulsion techniques. Trajectory studies were completed with the Optimal Trajectories by Implicit Simulation (OTIS) software (NASA Glenn Research Center, Cleveland, Ohio) for a standard F-4 airplane and a standard F-15 airplane. Standard aircraft simulation models were constructed, and the thrust in each was altered in accordance with estimated MIPCC performance characteristics. The MIPCC and production aircraft model results were then reviewed to assess the feasibility of a MIPCC-enhanced propulsion system for use as a first-stage reusable launch vehicle; it was determined that the MIPCC-enhanced F-15 model showed a significant performance advantage over the MIPCC-enhanced F-4 model.

Preliminary MIPCC Enhanced F-4 and F-15 Performance Characteristics for a First Stage Reusable Launch Vehicle

NASA Technical Reports Server (NTRS)

Kloesel, Kurt J.

2013-01-01

Performance increases in turbojet engines can theoretically be achieved through Mass Injection Pre-Compressor Cooling (MIPCC), a process involving injecting water or oxidizer or both into an afterburning turbojet engine. The injection of water results in pre-compressor cooling, allowing the propulsion system to operate at high altitudes and Mach numbers. In this way, a MIPCC-enhanced turbojet engine could be used to power the first stage of a reusable launch vehicle or be integrated into an existing aircraft that could launch a 100-lbm payload to a reference 100-nm altitude orbit at 28 deg inclination. The two possible candidates for MIPCC flight demonstration that are evaluated in this study are the F-4 Phantom II airplane and the F-15 Eagle airplane (both of McDonnell Douglas, now The Boeing Company, Chicago, Illinois), powered by two General Electric Company (Fairfield, Connecticut) J79 engines and two Pratt & Whitney (East Hartford, Connecticut) F100-PW-100 engines, respectively. This paper presents a conceptual discussion of the theoretical performance of each of these aircraft using MIPCC propulsion techniques. Trajectory studies were completed with the Optimal Trajectories by Implicit Simulation (OTIS) software (NASA Glenn Research Center, Cleveland, Ohio) for a standard F-4 airplane and a standard F-15 airplane. Standard aircraft simulation models were constructed, and the thrust in each was altered in accordance with estimated MIPCC performance characteristics. The MIPCC and production aircraft model results were then reviewed to assess the feasibility of a MIPCC-enhanced propulsion system for use as a first-stage reusable launch vehicle; it was determined that the MIPCC-enhanced F-15 model showed a significant performance advantage over the MIPCC-enhanced F-4 model.

Buffet characteristics of the F-8 supercritical wing airplane

NASA Technical Reports Server (NTRS)

Deangelis, V. M.; Monaghan, R. C.

1977-01-01

The buffet characteristics of the F-8 supercritical wing airplane were investigated. Wing structural response was used to determine the buffet characteristics of the wing and these characteristics are compared with wind tunnel model data and the wing flow characteristics at transonic speeds. The wingtip accelerometer was used to determine the buffet onset boundary and to measure the buffet intensity characteristics of the airplane. The effects of moderate trailing edge flap deflections on the buffet onset boundary are presented. The supercritical wing flow characteristics were determined from wind tunnel and flight static pressure measurements and from a dynamic pressure sensor mounted on the flight test airplane in the vicinity of the shock wave that formed on the upper surface of the wing at transonic speeds. The comparison of the airplane's structural response data to the supercritical flow characteristics includes the effects of a leading edge vortex generator.

Wind tunnel investigation of the aerodynamic characteristics of symmetrically deflected ailerons of the F-8C airplane. [conducted in the Langley 8-foot transonic pressure tunnel

NASA Technical Reports Server (NTRS)

Gera, J.

1977-01-01

A .042-scale model of the F-8C airplane was investigated in a transonic wind tunnel at high subsonic Mach numbers and a range of angles of attack between-3 and 20 degrees. The effect of symmetrically deflected ailerons on the longitudinal aerodynamic characteristics was measured. Some data were also obtained on the lateral control effectiveness of asymmetrically deflected horizontal tail surfaces.

77 FR 49389 - Airworthiness Directives; Revo, Incorporated Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-08-16

..., Incorporated Models COLONIAL C-1, COLONIAL C-2, LAKE LA-4, LAKE LA-4A, LAKE LA-4P, and LAKE LA-4-200 airplanes... COLONIAL C-1 airplanes are identical in every other respect to those installed on the airplanes referenced... COLONIAL C-1 airplanes to the Applicability, and add an optional terminating action for the requirements...

Copper Causes Regiospecific Formation of C4F8-Containing Six-Membered Rings and their Defluorination/Aromatization to C4F4-Containing Rings in Triphenylene/1,4-C4F8I2 Reactions

DOE Office of Scientific and Technical Information (OSTI.GOV)

Rippy, Kerry C.; Bukovsky, Eric V.; Clikeman, Tyler T.

The presence of Cu in reactions of triphenylene (TRPH) and 1,4-C4F8I2 at 360 °C led to regiospecific substitution of TRPH ortho C(β) atoms to form C4F8-containing rings, completely suppressing substitution on C(α) atoms. In addition, Cu caused selective reductive-defluorination/aromatization (RD/A) to form C4F4- containing aromatic rings. Without Cu, the reactions of TRPH and 1,4- C4F8I2 were not regiospecific and no RD/A was observed. These results, supported by DFT calculations, are the first examples of Cupromoted (i) regiospecific perfluoroannulation, (ii) preparative C–F activation, and (iii) RD/A. HPLC-purified products were characterized by X-ray diffraction, low-temperature PES, and 1H/19F NMR.

Investigations of electron attachment to the perfluorocarbon molecules c-C4F8, 2-C4F8, 1,3 C4F6, and c-C5F8

NASA Astrophysics Data System (ADS)

Feil, Stefan; Märk, Tilmann D.; Mauracher, Andreas; Scheier, Paul; Mayhew, Chris A.

2008-11-01

Non-dissociative and dissociative electron attachment to a series of gas-phase perfluorocarbons (PFCs), namely octafluorocyclobutane, c-C4F8, octafluorobut-2-ene (perfluoro-2-butene), 2-C4F8, hexafluorobuta-1,3-diene (1,3 perfluorobutadiene), 1,3 C4F6, and octafluorocyclopentene (perfluorocyclopentene), c-C5F8, of importance to technological plasmas, have been investigated using two different, but complimentary, instruments available in Innsbruck over the electron energy range 0-20 eV. Anion yields as a function of electron energy have been recorded, with the positions and intensities of the electron attachment resonances being determined. One of these instruments is a double focusing sector field mass spectrometer (VG-ZAB-2SEQ), which has been used for measurements requiring high sensitivity and for obtaining accurate relative anion yields. It has also been used to determine the electron detachment lifetimes of the parent anions under various accelerating voltages, and these results are also presented. The second instrument (CELIA) is a trochoidal electron monochromator coupled to a quadrupole mass filter with a pulse counting system for detecting product anionic species. This provides a much higher energy resolution than the VG-ZAB, which makes it a better instrument to investigate narrow energy resonances close to 0 eV. The results of anion yields, peak positions and the relative intensities presented in this paper are compared with previous data of electron attachment to the above PFCs, including investigations by Professor Eugen Illenberger.

77 FR 40485 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-07-10

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... (AD) for all Airbus Model A300 series airplanes; all Model A300 B4-600, B4-600R, and F4-600R series... new AD: 2012-13-06 Airbus: Amendment 39-17108. Docket No. FAA-2012-0040; Directorate Identifier 2011...

Development and Evaluation of an Airplane Fuel Tank Ullage Composition Model. Volume 2. Experimental Determination of Airplane Fuel Tank Ullage Compositions

DTIC Science & Technology

1987-10-01

Airplane Fuel Tank Ullage Compositions ~C A. J. Roth BOEING MILITARY AIRPLANE COMPANY P. 0. Box 3707 Seattle, Washington 98124-2207 October 1987 FINAL...controlled mission simulations were made using the ModComp computer to control the Simulated Aircraft Fuel Tank Environment ( SAFTEI facility at Wright...of this report. iii PREFACE This is a final report of work conducted under F33615-84-C-2431 and submitted by the Boeing Military Airplane Company

Free-Spinning Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395

NASA Technical Reports Server (NTRS)

Bowman, James S., Jr.

1955-01-01

An investigation is being conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine spin and recovery characteristics and the minimum-size parachute required to satisfactorily terminate the spin in an emergency. Results obtained to date are presented herein. Test results indicate that it may be difficult to obtain an erect or inverted spin on the airplane, but, if a spin is obtained, the spin will be very oscillatory and recovery from the developed erect spin by rudder reversal may not be possible. The lateral controls will have no appreciable effect on recoveries from erect.spins. Recovery from the inverted spin by merely neutralizing the rudder will be satisfactory. After recoveries by rudder reversal and after recoveries from spins without control movement (no spins), the model oftentimes rolled very rapidly about the X-axis. Based on limited preliminary tests made in this investigation to make the model recover satisfactorily, it appears that canards near the nose of the airplane or differentially operated horizontal tails may be utilized to provide rapid recoveries. The parachute test results indicate that an 11-foot-diameter (laid-out-flat) parachute with a drag coefficient of 0.650 (based on the laid- out-flat diameter) and with a towline length equal to the wing span is the minimum-size parachute required to satisfactorily terminate an erect or inverted spin in an emergency.

75 FR 75868 - Airworthiness Directives; Diamond Aircraft Industries GmbH Models DA 40 and DA 40F Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-07

... Airworthiness Directives; Diamond Aircraft Industries GmbH Models DA 40 and DA 40F Airplanes AGENCY: Federal... of the Thielert Engine Owners Group commented that the Model DA 42 has the same door design and the same unsafe condition. He recommended that the AD also apply to the Model DA 42. The FAA has discussed...

Preliminary flight evaluation of F100 engine model derivative airstart capability in an F-15 airplane

NASA Technical Reports Server (NTRS)

Cho, T. K.; Burcham, F. W., Jr.

1984-01-01

A series of airstarts was conducted in an F-15 airplane with two prototype F100 engine model derivative (EMD) engines equipped with digital electronic engine control (DEEC) systems. The airstart envelope and time required for airstarts were defined. The success of an airstart is most heavily dependent on airspeed. Spooldown airstarts at 200 knots and higher were all successful. Spooldown airstart times ranged from 53 sec at 250 knots to 170 sec at 175 knots. Jet fuel starter (JFS) assisted airstarts were conducted at 175 knots at two altitudes, and airstart times were 50 and 60 sec, significantly faster than unassisted airstart. The effect of altitude on airstarts was small. In addition, the airstart characteristics of the two test engines were found to closely resemble each other. The F100 EMD airstart characteristics were very similar to the DEEC equipped F100 engine tested previously. Finally, the time required to spool down from intermediate power compressor rotor speed to a given compressor rotor speed was found to be a strong function of altitude and a weaker function of airspeed.

Subsonic stability and control derivatives for an unpowered, remotely piloted 3/8-scale F-15 airplane model obtained from flight test

NASA Technical Reports Server (NTRS)

Iliff, K. W.; Maine, R. E.; Shafer, M. F.

1976-01-01

In response to the interest in airplane configuration characteristics at high angles of attack, an unpowered remotely piloted 3/8-scale F-15 airplane model was flight tested. The subsonic stability and control characteristics of this airplane model over an angle of attack range of -20 to 53 deg are documented. The remotely piloted technique for obtaining flight test data was found to provide adequate stability and control derivatives. The remotely piloted technique provided an opportunity to test the aircraft mathematical model in an angle of attack regime not previously examined in flight test. The variation of most of the derivative estimates with angle of attack was found to be consistent, particularly when the data were supplemented by uncertainty levels.

76 FR 79560 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-12-22

...-1323; Directorate Identifier 2010-NM-212-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... airplanes; Model A330-223F and -243F airplanes; and Model A340-200, -300, -500, and -600 series airplanes... airplane flight manual. We are proposing this AD to prevent movement of the elevators to zero position...

Wind-tunnel free-flight investigation of a 0.15-scale model of the F-106B airplane with vortex flaps

NASA Technical Reports Server (NTRS)

Yip, Long P.

1987-01-01

An investigation to determine the effects of vortex flaps on the flight dynamic characteristics of the F-106B in the area of low-speed, high-angle-of-attack flight was undertaken on a 0.15-scale model of the airplane in the Langley 30- by 60-Foot Tunnel. Static force tests, dynamic forced-oscillation tests, as well as free-flight tests were conducted to obtain a data base on the flight characteristics of the F-106B airplane with vortex flaps. Vortex flap configurations tested included a full-span gothic flap, a full-span constant-chord flap, and a part-span gothic flap.

Bulk plasma fragmentation in a C4F8 inductively coupled plasma: A hybrid modeling study

NASA Astrophysics Data System (ADS)

Zhao, Shu-Xia; Zhang, Yu-Ru; Gao, Fei; Wang, You-Nian; Bogaerts, Annemie

2015-06-01

A hybrid model is used to investigate the fragmentation of C4F8 inductive discharges. Indeed, the resulting reactive species are crucial for the optimization of the Si-based etching process, since they determine the mechanisms of fluorination, polymerization, and sputtering. In this paper, we present the dissociation degree, the density ratio of F vs. CxFy (i.e., fluorocarbon (fc) neutrals), the neutral vs. positive ion density ratio, details on the neutral and ion components, and fractions of various fc neutrals (or ions) in the total fc neutral (or ion) density in a C4F8 inductively coupled plasma source, as well as the effect of pressure and power on these results. To analyze the fragmentation behavior, the electron density and temperature and electron energy probability function (EEPF) are investigated. Moreover, the main electron-impact generation sources for all considered neutrals and ions are determined from the complicated C4F8 reaction set used in the model. The C4F8 plasma fragmentation is explained, taking into account many factors, such as the EEPF characteristics, the dominance of primary and secondary processes, and the thresholds of dissociation and ionization. The simulation results are compared with experiments from literature, and reasonable agreement is obtained. Some discrepancies are observed, which can probably be attributed to the simplified polymer surface kinetics assumed in the model.

75 FR 64633 - Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-10-20

... repetitive inspections for fatigue cracking and corrosion of the upper link fuse pin of the nacelle struts... fatigue cracking or corrosion of the upper link fuse pin, which could result in failure of the fuse pin... Model 767-200, -300, and - 300F series airplanes. That AD requires repetitive inspections for fatigue...

77 FR 24829 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-04-26

... Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... and -300 series airplanes; Model A330-223F and -243F airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by a report that during the evaluation of engine failures...

Flight Test of the F/A-18 Active Aeroelastic Wing Airplane

NASA Technical Reports Server (NTRS)

Voracek, David

2007-01-01

A viewgraph presentation of flight tests performed on the F/A active aeroelastic wing airplane is shown. The topics include: 1) F/A-18 AAW Airplane; 2) F/A-18 AAW Control Surfaces; 3) Flight Test Background; 4) Roll Control Effectiveness Regions; 5) AAW Design Test Points; 6) AAW Phase I Test Maneuvers; 7) OBES Pitch Doublets; 8) OBES Roll Doublets; 9) AAW Aileron Flexibility; 10) Phase I - Lessons Learned; 11) Control Law Development and Verification & Validation Testing; 12) AAW Phase II RFCS Envelopes; 13) AAW 1-g Phase II Flight Test; 14) Region I - Subsonic 1-g Rolls; 15) Region I - Subsonic 1-g 360 Roll; 16) Region II - Supersonic 1-g Rolls; 17) Region II - Supersonic 1-g 360 Roll; 18) Region III - Subsonic 1-g Rolls; 19) Roll Axis HOS/LOS Comparison Region II - Supersonic (open-loop); 20) Roll Axis HOS/LOS Comparison Region II - Supersonic (closed-loop); 21) AAW Phase II Elevated-g Flight Test; 22) Region I - Subsonic 4-g RPO; and 23) Phase II - Lessons Learned

Ditching Investigation of a 1/10-Scale Model of the Grumman F9F-2 Airplane, TED No. NACA DE 335

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; McBride, Ellis E.

1955-01-01

An investigation was made of a 1/10-scale dynamically similar model of the Grumman FgF-2 airplane to study its behavior when ditched. The model was landed in calm water at the Langley Tank No. 2 monorail. Various landing attitudes, speeds, and configurations were investigated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tabular form, sequence photographs, time-history acceleration curves, and plots of attitude and speed against distance after contact.

77 FR 26937 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-05-08

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...) for certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes; and Model... Airbus Service Bulletins (SB) A300-57-0235 and A300-57-6088 * * *. Subsequently, new cases of cracks were...

Flight Tests of a Ministick Controller in an F/A-18 Airplane

NASA Technical Reports Server (NTRS)

Stoliker, Patrick C.; Carter, John

2003-01-01

In March of 1999, five pilots performed flight tests to evaluate the handling qualities of an F/A-18 research airplane equipped with a small-displacement center stick (ministick) controller that had been developed for the JAS 39 Gripen airplane (a fighter/attack/ reconnaissance airplane used by the Swedish air force). For these tests, the ministick was installed in the aft cockpit (see figure) and production support flight control computers (PSFCCs) were used as interfaces between the controller hardware and the standard F/A-18 flight-control laws. The primary objective of the flight tests was to assess any changes in handling qualities of the F/A-18 airplane attributable to the mechanical characteristics of the ministick. The secondary objective was to demonstrate the capability of the PSFCCs to support flight-test experiments.

Spin Tests of 1/20-Scale Models of the Chance Vought Revised XF6U-1 and F6U-1 Airplanes, TED No. NACA 2390

NASA Technical Reports Server (NTRS)

Klinar, Walter J.; Berman, Theodore

1948-01-01

An investigation has been conducted in the Langley 20-foot free-spinning tunnel on the 1/20-scale model of the Chance Vought XF6U-1 airplane altered to represent the XF6U-1 airplane as it will be spin-tested in flight, and also altered to represent the F6U-1 airplane as it will be produced for service use. Spin tests were made to determine the effects of control settings and movements at the normal loading. The results show that the spins obtained on the revised XF6U-1 airplane will be oscillatory in roll and yaw and that recoveries by rudder reversal will be rapid. Model test results indicate that the F6U-1 airplane will probably not spin. Inasmuch as the results of this investigation show that the new designs are as good as or better than the original XF6U-1 design in regard to spin recovery, it is felt that the conclusions and recommendations reached for the original design can be applied to the new designs for all loading conditions.

Flight testing and simulation of an F-15 airplane using throttles for flight control

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Maine, Trindel; Wolf, Thomas

1992-01-01

Flight tests and simulation studies using the throttles of an F-15 airplane for emergency flight control have been conducted at the NASA Dryden Flight Research Facility. The airplane and the simulation are capable of extended up-and-away flight, using only throttles for flight path control. Initial simulation results showed that runway landings using manual throttles-only control were difficult, but possible with practice. Manual approaches flown in the airplane were much more difficult, indicating a significant discrepancy between flight and simulation. Analysis of flight data and development of improved simulation models that resolve the discrepancy are discussed. An augmented throttle-only control system that controls bank angle and flight path with appropriate feedback parameters has also been developed, evaluated in simulations, and is planned for flight in the F-15.

77 FR 2439 - Airworthiness Directives; Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-01-18

... down position (control column forward), the link must form an angle between the link attachment point... Airworthiness Directives; Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D Airplanes AGENCY: Federal... new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Models 1900, 1900C, and...

75 FR 47245 - Airworthiness Directives; The Boeing Company Model 747-400, 747-400D, and 747-400F Series...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-05

... Model 747-400, 747- 400D, and 747-400F Series Airplanes Equipped With General Electric CF6- 80C2 or Pratt & Whitney PW4000 Series Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice... certain Model 747-400, 747-400D, and 747-400F series airplanes. This proposed AD would require modifying...

77 FR 46343 - Airworthiness Directives; The Boeing Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-08-03

... certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes; and certain Model 757-200, -200PF, and... applies to The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300...

Ditching Investigation of a 1/12-Scale Model of the Douglas F3D-2 Airplane, TED No. NACA DE 381

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; Thompson, William C.

1955-01-01

An investigation of a 1/12- scale dynamically similar model of the Douglas F3D-2 airplane was made in calm water to observe the ditching behavior and to determine the safest procedure for making an emergency water landing. Various conditions of damage were simulated to determine the behavior which probably would occur in a full-scale ditching. The behavior of the model was determined from motion-picture records, time- history acceleration records, and visual observations. It was concluded that the airplane should be ditched at a medium high attitude of about 8 degrees with the landing flaps down 40 degrees. In calm water the airplane will probably make a smooth run of about 550 feet and will have a maximum longitudinal deceleration of about 3g. The fuselage bottom will probably be damaged enough to allow the fuselage to fill with water very rapidly.

The value of early flight evaluation of propulsion concepts using the NASA F-15 research airplane

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Ray, Ronald J.

1987-01-01

The value of early flight evaluation of propulsion and propulsion control concepts was demonstrated on the NASA F-15 airplane in programs such as highly integrated digital electronic control (HIDEC), the F100 engine model derivative (EMD), and digital electronic engine control (DEEC). (In each case, the value of flight demonstration was conclusively demonstrated). This paper described these programs, and discusses the results that were not expected, based on ground test or analytical prediction. The role of flight demonstration in facilitating transfer of technology from the laboratory to operational airplanes is discussed.

77 FR 51717 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-08-27

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... applies to certain Airbus Model A300 B4-2C, B4-103, and B4- 203 airplanes; and Model A300 B4-601, B4-603... information identified in this proposed AD, contact Airbus SAS--EAW (Airworthiness Office), 1 Rond Point...

Effect of simulated in-flight thrust reversing on vertical-tail loads of F-18 and F-15 airplane models. [conducted in the Langley 16-foot transonic tunnel

NASA Technical Reports Server (NTRS)

Bare, E. A.; Berrier, B. L.; Capone, F. J.

1981-01-01

Investigations were conducted in the Langley 16-Foot Transonic Tunnel to provide data on a 0.10-scale model of the prototype F-18 airplane and a 0.047-scale model of the F-15 three-surface configuration (canard, wing, and horizontal tails). Test data were obtained at static conditions and at Mach numbers from 0.6 to 1.2 over an angle-of-attack range from 2 deg to 15 deg. Nozzle pressure ratio was varied from jet off to about 8.0.

Wind-Tunnel Tests of a 1/8-Scale Powered Model of the XTB3F-1 Airplane, TED No. NACA 2382

NASA Technical Reports Server (NTRS)

McKee, John W.; Vogler, Raymond D.

1947-01-01

A 1/8 scale model of the Grumman XTB3F-1 airplane was tested in the Langley 7- by 10-foot tunnel to determine the stability and control characteristics and to provide data for estimating the airplane handling qualities. The report includes longitudinal and lateral stability and control characteristics of the complete model, the characteristics of the isolated horizontal tail, the effects of various flow conditions through the jet duct, tests with external stores attached to the underside of the wing, ana tests simulating landing and take-off conditions with a ground board. The handling characteristics of the airplane have not been computed but some conclusions were indicated by the data. An improvement in the longitudinal stability was obtained by tilting the thrust line down. It is shown that if the wing flap is spring loaded so that the flap deflection varies with airspeed, the airplanes will be less stable than with the flap retracted or fully deflected. An increase in size of the vertical tail and of the dorsal fin gave more desirable yawing-moment characteristics than the original vertical tail and dorsal fin. Preventing air flow through the jet duct system or simulating jet operation with unheated air produced only small changes in the model characteristics. The external stores on the underside of the wing had only small effects on the model characteristics. After completion of the investigation, the model was returned to the contractor for modifications indicated by the test results.

Electron impact elastic and excitation cross-sections of the isomers of C4F6 molecule for plasma modeling

NASA Astrophysics Data System (ADS)

Gupta, Dhanoj; Song, Mi-Young; Baluja, K. L.; Choi, Heechol; Yoon, Jung-Sik

2018-06-01

We report the calculations of elastic (along with its symmetry components) and electronic excitation cross sections by electron impact of the three isomers of C4F6, namely, hexafluoro-1,3-butadiene (1,3-C4F6), hexafluoro-2-butyne (2-C4F6), and hexafluorocyclobutene (c-C4F6) belonging to the point groups C2, D3d, and C2v, respectively, using the R-matrix approach. The electron energy range is from 0.01 eV to 12 eV. We have employed the cc-pVTZ basis set for C and F atoms to generate self-consistent field molecular orbitals to construct the target states for all the isomers included in our calculations. All the target states are constructed by including correlation effects in a configuration interaction (CI) approach. The target properties such as vertical excitation energies and dipole moment of all the isomers are in reasonable agreement with the literature values. Differences in the cross sections of these isomers are strongly influenced by the effect of correlation and polarization effects and their geometrical extent. We have included the ground state and many excited states of each isomer in the trial wave function of the entire scattering system. The resulting elastic cross sections are compared with the available experimental results. The agreement is reasonably good for energies above 5 eV. The shape resonances detected at 2.57, 2.95, and 3.20 eV for c-C4F6, 1,3-C4F6, and 2-C4F6 isomers are associated with the negative anion formation of C3F3- as observed in the mass spectrometry experiments. We have also performed 1-state CI calculation for all the isomers that include only the correlated ground state. The position of resonances shifts to lower energies as the number of target states is increased compared to 1-state calculation for all the isomers. The elastic cross section for 2-C4F6 isomer is larger than the other isomers because of its larger spatial extent. The present cross section data are important for plasma simulation and modeling, especially

Spin-Tunnel Investigation of a 1/20-Scale Model of the Northrop F-5E Airplane

NASA Technical Reports Server (NTRS)

Scher, Stanley H.; White, William L.

1977-01-01

An investigation has been conducted in the Langley spin tunnel to determine the spin and recovery characteristics of a 1/20-scale model of the Northrop F-5E airplane. The investigation included erect and inverted spins, a range of center-of- gravity locations and moments of inertia, symmetric and asymmetric store loadings, and a determination of the parachute size required for emergency spin recovery. The effects of increased elevator trailing-edge-up deflections, of leading-edge and trailing-edge flap deflections, and of simulating the geometry of large external stores were also determined.

Long-term tropospheric trend of octafluorocyclobutane (c-C4F8 or PFC-318)

NASA Astrophysics Data System (ADS)

Oram, D. E.; Mani, F. S.; Laube, J. C.; Newland, M. J.; Reeves, C. E.; Sturges, W. T.; Penkett, S. A.; Brenninkmeijer, C. A. M.; Röckmann, T.; Fraser, P. J.

2011-07-01

Air samples collected at Cape Grim, Tasmania between 1978 and 2008 and during a series of more recent aircraft sampling programmes have been analysed to determine the atmospheric abundance and trend of octafluorocyclobutane (-C4F8 or PFC-318). c-C4F8 has an atmospheric lifetime in excess of 3000 yr and a global warming potential (GWP) of 10 300 (100 yr time horizon), making it one of the most potent greenhouse gases detected in the atmosphere to date. The abundance of c-C4F8 in the Southern Hemisphere has risen from 0.35 ppt in 1978 to 1.2 ppt in 2010, and is currently increasing at a rate of around 0.03 ppt yr-1. It is the third most abundant perfluorocarbon (PFC) in the present day atmosphere, behind CF4 (~75 ppt) and C2F6 (~4 ppt). The origin of c-C4F8 is unclear. Using a 2-D global model to derive top-down global emissions based on the Cape Grim measurements yields a recent (2007) emission rate of around 1.1 Gg yr-1 and a cumulative emission up to and including 2007 of 38.1 Gg. Emissions reported on the EDGAR emissions database for the period 1986-2005 represent less than 1 % of the top-down emissions for the same period, which suggests there is a large unaccounted for source of this compound. It is also apparent that the magnitude of this source has varied considerably over the past 30 yr, declining sharply in the late 1980s before increasing again in the mid-1990s.

75 FR 6849 - Airworthiness Directives; Airbus Model A310-221, -222, -322, -324, and -325 Airplanes, and Model...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-02-12

... Airworthiness Directives; Airbus Model A310-221, -222, -322, - 324, and -325 Airplanes, and Model A300 B4-620... applies to Airbus Model A310-221, -222, -322, -324, and -325 airplanes, and Model A300 B4-620, B4-622, B4... Model A310-221, - 222, -322, -324, and -325 airplanes), both including Appendix 1, both dated October 3...

Flight and wind-tunnel comparisons of the inlet-airframe interaction of the F-15 airplane

NASA Technical Reports Server (NTRS)

Webb, L. D.; Andriyich-Varda, D.; Whitmore, S. A.

1984-01-01

The design of inlets and nozzles and their interactions with the airplane which may account for a large percentage of the total drag of modern high performance aircraft is discussed. The inlet/airframe interactions program and the flight tests conducted is described. Inlet drag and lift data from a 7.5% wind-tunnel model are compared with data from an F-15 airplane with instrumentation to match the model. Pressure coefficient variations with variable cowl angles, capture ratios, examples of flow interactions and angles of attack are for Mach numbers of 0.6, 0.9, 1.2, and 1.5 are presented.

Long-term tropospheric trend of octafluorocyclobutane (c-C4F8 or PFC-318)

NASA Astrophysics Data System (ADS)

Oram, D. E.; Mani, F. S.; Laube, J. C.; Newland, M. J.; Reeves, C. E.; Sturges, W. T.; Penkett, S. A.; Brenninkmeijer, C. A. M.; Röckmann, T.; Fraser, P. J.

2012-01-01

Air samples collected at Cape Grim, Tasmania between 1978 and 2008 and during a series of more recent aircraft sampling programmes have been analysed to determine the atmospheric abundance and trend of octafluorocyclobutane (c-C4F8 or PFC-318). c-C4F8 has an atmospheric lifetime in excess of 3000 yr and a global warming potential (GWP) of 10 300 (100 yr time horizon), making it one of the most potent greenhouse gases detected in the atmosphere to date. The abundance of c-C4F8 in the Southern Hemisphere has risen from 0.35 ppt in 1978 to 1.2 ppt in 2010, and is currently increasing at a rate of around 0.03 ppt yr-1. It is the third most abundant perfluorocarbon (PFC) in the present day atmosphere, behind CF4 (~75 ppt) and C2F6 (~4 ppt). Although a number of potential sources of c-C4F8 have been reported, including the electronics and semi-conductor industries, there remains a large discrepancy in the atmospheric budget. Using a 2-D global model to derive top-down global emissions based on the Cape Grim measurements yields a recent (2007) emission rate of around 1.1 Gg yr-1 and a cumulative emission up to and including 2007 of 38.1 Gg. Emissions reported on the EDGAR emissions database for the period 1986-2005 represent less than 1% of the top-down emissions for the same period, which suggests there is a large unaccounted for source of this compound. It is also apparent that the magnitude of this source has varied considerably over the past 30 yr, declining sharply in the late 1980s before increasing again in the mid-1990s.

Ditching Investigation of a 1/11-Scale Model of the Chance Vought F7U-3 Airplane, TED NO. NACA DE 360

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; Windham, John O.

1955-01-01

An investigation was made of a 1/11-scale dynamically similar model of the Chance Vought F7U-3 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and configurations were investigated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tabular form, sequence photographs, time-history acceleration curves, and plots of attitude change against time after contact. From the results of the investigation, it was concluded that the airplane should be ditched at the lowest speed and highest attitude consistent with adequate control. The aft part of the fuselage and the main landing-gear doors will probably be damaged. In a calm-water ditching under these conditions the airplane will probably skip slightly and then porpoise for the remainder of the run. Maximum longitudinal decelerations will be about 3 1/2g and maximum normal accelerations will be about 7g in a landing run of about 500 feet.

Static Longitudinal and Lateral Stability and Control Characteristics of a 1/15-Scale Model of the Grumman F9F-9 Airplane at a Mach Number of 1.41

NASA Technical Reports Server (NTRS)

Palazzo, Edward B.; Spearman, M. Leroy

1954-01-01

An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.41 to determine the static stability and control and drag characteristics of a l/l5-scale model of the Grunman F9F-9 airplane. The effects of alternate fuselage shapes, wing camber, wing fences, and fuselage dive brakes on the aerodynamic characteristics were also investigated. These tests were made at a Reynolds number of 1.96 x l0 (exp 6) based on the wing mean aerodynamic chord of 0.545 foot. The basic configuration had a static margin of stability of 38.4 percent of the mean aerodynamic chord and a minimum drag coefficient of 0.049. For the maximum horizontal tail deflection investigated (-l0 deg), the maximum trim lift coefficient was 0.338. The basic configuration had positive static lateral stability at zero angle of attack and positive directional control throughout the angle-of-attack range investigated up to ll deg.

Flight Research Using F100 Engine P680063 in the NASA F-15 Airplane

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Conners, Timothy R.; Maxwell, Michael D.

1994-01-01

The value of flight research in developing and evaluating gas turbine engines is high. NASA Dryden Flight Research Center has been conducting flight research on propulsion systems for many years. The F100 engine has been tested in the NASA F-15 research airplane in the last three decades. One engine in particular, S/N P680063, has been used for the entire program and has been flown in many pioneering propulsion flight research activities. Included are detailed flight-to-ground facility tests; tests of the first production digital engine control system, the first active stall margin control system, the first performance-seeking control system; and the first use of computer-controlled engine thrust for emergency flight control. The flight research has been supplemented with altitude facility tests at key times. This paper presents a review of the tests of engine P680063, the F-15 airplanes in which it flew, and the role of the flight test in maturing propulsion technology.

Effect of control logic modifications on airstart performance of F100 engine model derivative engines in an F-15 airplane

NASA Technical Reports Server (NTRS)

Crawford, D. B.; Burcham, F. W., Jr.

1984-01-01

A series of airstarts were conducted in an F-15 airplane with two prototype Pratt and Whitney F100 Engine Model Derivative engines equipped with Digital Electronic Engine Control (DEEC) systems. The airstart envelope and the time required for airstarts were defined. Comparisons were made between the original airstart logic, and modified logic which was designed to improve the airstart capability. Spooldown airstarts with the modified logic were more successful at lower altitudes than were those with the original logic. Spooldown airstart times ranged from 33 seconds at 250 knots to 83 seconds at 175 knots. The modified logic improved the airstart time from 31% to 53%, with the most improved times at slower airspeeds. Jet fuel starter (JFS)-assisted airstarts were conducted at 7000 m and airstart times were significantly faster than unassisted airstarts. The effect of altitude on airstart times was small.

14 CFR Appendix F to Part 36 - Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter...

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter Category Airplane Certification Tests Prior to.... F Appendix F to Part 36—Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller...

14 CFR Appendix F to Part 36 - Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter...

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter Category Airplane Certification Tests Prior to.... F Appendix F to Part 36—Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller...

14 CFR Appendix F to Part 36 - Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter...

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter Category Airplane Certification Tests Prior to.... F Appendix F to Part 36—Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller...

14 CFR Appendix F to Part 36 - Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter...

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter Category Airplane Certification Tests Prior to.... F Appendix F to Part 36—Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller...

14 CFR Appendix F to Part 36 - Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter...

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter Category Airplane Certification Tests Prior to.... F Appendix F to Part 36—Flyover Noise Requirements for Propeller-Driven Small Airplane and Propeller...

75 FR 79952 - Airworthiness Directives; DASSAULT AVIATION Model Falcon 10 Airplanes; Model FAN JET FALCON, FAN...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-21

... Airworthiness Directives; DASSAULT AVIATION Model Falcon 10 Airplanes; Model FAN JET FALCON, FAN JET FALCON.... List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of.... (1) DASSAULT AVIATION Model Falcon 10 airplanes, Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E...

77 FR 70366 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-11-26

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-243, -243F, -341, -342, and -343 airplanes equipped with Rolls-Royce Trent 700 engines...: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA...

78 FR 4051 - Airworthiness Directives; The Boeing Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-01-18

...-400D, 747-400F, 747SR, and 747SP series airplanes; and certain Model 757-200, -200PF, and -300 series... Model 757 series airplanes. This new AD adds airplanes to the applicability and revises the initial compliance times for those airplanes. This AD was prompted by reports of problems associated with the...

Measurements in Flight of the Flying Qualities of a Chance Vought F4U-4 Airplane: TED No. NACA 2388

NASA Technical Reports Server (NTRS)

Liddell, Charles J., Jr.; Reynolds, Robert M.; Christofferson, Frank E.

1947-01-01

The results of flight tests to determine flying qualities of a Chance Vought F4U-4 airplane are presented and discussed herein. In addition to comprehensive measurements at low altitude (about 8000 ft), tests of limited scope were made at high altitude (about 25,000 ft). The more important characteristics, based on a comparison of the test results and opinions of the pilots with the Navy requirements, can be summarized as follows: 1. The short-period control-free oscillations of the elevator angle and the normal acceleration were satisfactorily damped. 2. The most rearward center-of-gravity locations for satisfactory static longitudinal stability with power on, as determined by the control-force variations, were approximately 30 and 27 percent M.A.C. with flaps and gear up and down, respectively. 3. In maneuvering flight the conditions for which control-force gradients of satisfactory magnitude were obtained were seriously limited by sizable changes in the gradient with center-of-gravity location, airspeed, altitude, acceleration factor, and direction of turn. 4. The elevator and rudder controls were satisfactory for landings and take-offs. 5. The trim tabs were sufficiently effective for all controls. 6. The directional and lateral dynamic stability was positive, but the rudder oscillation did not damp within one cycle. The airplane oscillation damped sufficiently at low altitude but not at high altitude. 7. Both rudder-fixed and rudder-free static directional stability were positive over a sideslip range of +/-15 deg. However, the rudder force tended to reverse at high angles of right sideslip with flaps and gear up, power on, at low speeds. 8. The stick-fixed static lateral stability (dihedral effect) was positive in all conditions, but the stick-free dihedral effect was neutral at low speeds with flap and gear down, power on. 9. The yaw due to abrupt full aileron deflection at low speed was mot excessive, and the rudder control was adequate to hold trim

Comparison of 4'-[methyl-(11)C]thiothymidine ((11)C-4DST) and 3'-deoxy-3'-[(18)F]fluorothymidine ((18)F-FLT) PET/CT in human brain glioma imaging.

PubMed

Toyota, Yasunori; Miyake, Keisuke; Kawai, Nobuyuki; Hatakeyama, Tetsuhiro; Yamamoto, Yuka; Toyohara, Jun; Nishiyama, Yoshihiro; Tamiya, Takashi

2015-01-01

3'-deoxy-3'-[(18)F]fluorothymidine ((18)F-FLT) has been used to evaluate tumor malignancy and cell proliferation in human brain gliomas. However, (18)F-FLT has several limitations in clinical use. Recently, (11)C-labeled thymidine analogue, 4'-[methyl-(11)C]thiothymidine ((11)C-4DST), became available as an in vivo cell proliferation positron emission tomography (PET) tracer. The present study was conducted to evaluate the usefulness of (11)C-4DST PET in the diagnosis of human brain gliomas by comparing with the images of (18)F-FLT PET. Twenty patients with primary and recurrent brain gliomas underwent (18)F-FLT and (11)C-4DST PET scans. The uptake values in the tumors were evaluated using the maximum standardized uptake value (SUVmax), the tumor-to-normal tissue uptake (T/N) ratio, and the tumor-to-blood uptake (T/B) ratio. These values were compared among different glioma grades. Correlation between the Ki-67 labeling index and the uptake values of (11)C-4DST and (18)F-FLT in the tumor was evaluated using linear regression analysis. The relationship between the individual (18)F-FLT and (11)C-4DST uptake values in the tumors was also examined. (11)C-4DST uptake was significantly higher than that of (18)F-FLT in the normal brain. The uptake values of (11)C-4DST in the tumor were similar to those of (18)F-FLT resulting in better visualization with (18)F-FLT. No significant differences in the uptake values of (18)F-FLT and (11)C-4DST were noted among different glioma grades. Linear regression analysis showed a significant correlation between the Ki-67 labeling index and the T/N ratio of (11)C-4DST (r = 0.50, P < 0.05) and (18)F-FLT (r = 0.50, P < 0.05). Significant correlations were also found between the Ki-67 labeling index and the T/B ratio of (11)C-4DST (r = 0.52, P < 0.05) and (18)F-FLT (r = 0.55, P < 0.05). A highly significant correlation was observed between the individual T/N ratio of (11)C-4DST and (18)F-FLT in the tumor (r�

Highly integrated digital engine control system on an F-15 airplane

NASA Technical Reports Server (NTRS)

Burcham, F. W., Jr.; Haering, E. A., Jr.

1984-01-01

The Highly Integrated Digital Electronic Control (HIDEC) program will demonstrate and evaluate the improvements in performance and mission effectiveness that result from integrated engine/airframe control systems. This system is being used on the F-15 airplane. An integrated flightpath management mode and an integrated adaptive engine stall margin mode are implemented into the system. The adaptive stall margin mode is a highly integrated mode in which the airplane flight conditions, the resulting inlet distortion, and the engine stall margin are continuously computed; the excess stall margin is used to uptrim the engine for more thrust. The integrated flightpath management mode optimizes the flightpath and throttle setting to reach a desired flight condition. The increase in thrust and the improvement in airplane performance is discussed.

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109

NASA Technical Reports Server (NTRS)

Wolhart, Walter D.; Thomas, David F., Jr.

1955-01-01

An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution.

Time-History Data of Maneuvers Performed by a Republic F84G Airplane During Squadron Operational Training

NASA Technical Reports Server (NTRS)

Hamer, Harold A.; Mayo, Alton P.

1953-01-01

Preliminary results of one phase of a control-motion study program involving several jet fighter-type airplanes are presented in time-history form and are summarized as maximum measured quantities plotted against indicated airspeed. The results pertain to approximately 1,000 maneuvers performed by a Republic F-84G jet-fighter airplane during squadron operational training. The data include most tactical maneuvers of which the F-84G airplane is capable. Maneuvers were performed at pressure altitudes of 0 to 30,000 feet with indicated airspeeds ranging from the stalling speed to approximately 515 knots.

Flight testing a propulsion-controlled aircraft emergency flight control system on an F-15 airplane

NASA Technical Reports Server (NTRS)

Burcham, F. W., Jr.; Burken, John; Maine, Trindel A.

1994-01-01

Flight tests of a propulsion-controlled aircraft (PCA) system on an F-15 airplane have been conducted at the NASA Dryden Flight Research Center. The airplane was flown with all flight control surfaces locked both in the manual throttles-only mode and in an augmented system mode. In the latter mode, pilot thumbwheel commands and aircraft feedback parameters were used to position the throttles. Flight evaluation results showed that the PCA system can be used to land an airplane that has suffered a major flight control system failure safely. The PCA system was used to recover the F-15 airplane from a severe upset condition, descend, and land. Pilots from NASA, U.S. Air Force, U.S. Navy, and McDonnell Douglas Aerospace evaluated the PCA system and were favorably impressed with its capability. Manual throttles-only approaches were unsuccessful. This paper describes the PCA system operation and testing. It also presents flight test results and pilot comments.

Highly integrated digital engine control system on an F-15 airplane

NASA Technical Reports Server (NTRS)

Burcham, F. W., Jr.; Haering, E. A., Jr.

1984-01-01

The highly integrated digital electronic control (HIDEC) program will demonstrate and evaluate the improvements in performance and mission effectiveness that result from integrated engine-airframe control systems. This system is being used on the F-15 airplane at the Dryden Flight Research Facility of NASA Ames Research Center. An integrated flightpath management mode and an integrated adaptive engine stall margin mode are being implemented into the system. The adaptive stall margin mode is a highly integrated mode in which the airplane flight conditions, the resulting inlet distortion, and the engine stall margin are continuously computed; the excess stall margin is used to uptrim the engine for more thrust. The integrated flightpath management mode optimizes the flightpath and throttle setting to reach a desired flight condition. The increase in thrust and the improvement in airplane performance is discussed in this paper.

Effects of installation of F101 DFE exhaust nozzles on the afterbody-nozzle characteristics of the F-14 airplane

NASA Technical Reports Server (NTRS)

Reubush, D. E.; Carlson, J. R.

1982-01-01

A wind-tunnel investigation was conducted to determine the effects of F101 DFE (derivative fighter engine) nozzle axial positioning on the afterbody-nozzle longitudinal aerodynamic characteristics of the F-14 airplane. The model was tested in the Langley 16-Foot Transonic Tunnel at Mach numbers from 0.7 to 1.25 and angles of attack from about -2 to 6 degrees. Compressed air was used to simulate nozzle exhaust flow at jet total-pressure ratios from 1 (jet off) to about 8. The results of the investigation show that for subsonic Mach numbers the intermediate cruise nozzle position of the three positions tested resulted in the lowest drag.

Aerodynamic Effects of a 24-Foot, Multisegmented Telescoping Nose Boom on an F-15B Airplane

NASA Technical Reports Server (NTRS)

Cumming, Stephen B.; Smith, Mark S.; Frederick, Michael A.

2007-01-01

An experimental multisegmented telescoping nose boom has been installed on an F-15B airplane to be tested in a flight environment. The experimental nose boom is representative of one that could be used to tailor the sonic boom signature of an airplane such as a supersonic business jet. The nose boom consists of multiple sections and could be extended during flight to a length of 24 ft. The preliminary analyses indicated that the addition of the experimental nose boom could adversely affect vehicle flight characteristics and air data systems. Before the boom was added, a series of flights was flown to update the aerodynamic model and characterize the air data systems of the baseline airplane. The baseline results have been used in conjunction with estimates of the nose boom s influence to prepare for a series of research flights conducted with the nose boom installed. Data from these flights indicate that the presence of the experimental boom reduced the static pitch and yaw stability of the airplane. The boom also adversely affected the static-position error of the airplane but did not significantly affect angle-of-attack or angle-of-sideslip measurements. The research flight series has been successfully completed.

Aerodynamic Effects of a 24-foot Multisegmented Telescoping Nose Boom on an F-15B Airplane

NASA Technical Reports Server (NTRS)

Cumming, Stephen B.; Smith, Mark S.; Frederick, Michael A.

2008-01-01

An experimental multisegmented telescoping nose boom has been installed on an F-15B airplane to be tested in a flight environment. The experimental nose boom is representative of one that could be used to tailor the sonic boom signature of an airplane such as a supersonic business jet. The nose boom consists of multiple sections and could be extended during flight to a length of 24 ft. The preliminary analyses indicate that the addition of the experimental nose boom could adversely affect vehicle flight characteristics and air data systems. Before the boom was added, a series of flights was conducted to update the aerodynamic model and characterize the air data systems of the baseline airplane. The baseline results have been used in conjunction with estimates of the nose boom's influence to prepare for a series of research flights conducted with the nose boom installed. Data from these flights indicate that the presence of the experimental boom reduced the static pitch and yaw stability of the airplane. The boom also adversely affected the static-position error of the airplane but did not significantly affect angle-of-attack or angle-of-sideslip measurements. The research flight series has been successfully completed.

Flight test experience with high-alpha control system techniques on the F-14 airplane

NASA Technical Reports Server (NTRS)

Gera, J.; Wilson, R. J.; Enevoldson, E. K.; Nguyen, L. T.

1981-01-01

Improved handling qualities of fighter aircraft at high angles of attack can be provided by various stability and control augmentation techniques. NASA and the U.S. Navy are conducting a joint flight demonstration of these techniques on an F-14 airplane. This paper reports on the flight test experience with a newly designed lateral-directional control system which suppresses such high angle of attack handling qualities problems as roll reversal, wing rock, and directional divergence while simultaneously improving departure/spin resistance. The technique of integrating a piloted simulation into the flight program was used extensively in this program. This technique had not been applied previously to high angle of attack testing and required the development of a valid model to simulate the test airplane at extremely high angles of attack.

78 FR 68352 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-11-14

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. This AD was prompted by fatigue load... this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac...

Modeling of terminal-area airplane fuel consumption

DOT National Transportation Integrated Search

2009-08-01

Accurate modeling of airplane fuel consumption is necessary for air transportation policy-makers to properly : adjudicate trades between competing environmental and economic demands. Existing public models used for : computing terminal-area airplane ...

Free-Spinning Tunnel Tests of a 1/24-Scale Model of the Grumman XTB3F-1 Airplane, TED No. NACA DE304

NASA Technical Reports Server (NTRS)

Berman, Theodore

1947-01-01

In accordance with a request of the Bureau of Aeronautics, Navy Department, tests were performed in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 1/24 scale model of the Grumman XTB3F-1 airplane. The airplane is a two-place, midwing torpedo bomber equipped with a tractor propeller and an auxiliary jet engine. The effect of control setting and movement on the erect and inverted spin and recovery characteristics of the model were determined for the normal loading. Brief tests with mass extended slightly along the fuselage were also made, however, in order to determine the effect of such a mass variation on elevator effectiveness. Tests were performed to determine the size of emergency spin-recovery tail and wing-tip parachutes required for satisfactory recovery by parachute action alone. The investigation also included emergency pilot-escape tests and tests to determine the rudder pedal and elevator stick forces necessary to move the rudder and elevator for recovery.

78 FR 53638 - Airworthiness Directives; Bombardier, Inc. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-30

.... Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of erratic pitch movement and...

77 FR 67267 - Airworthiness Directives; Bombardier, Inc. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-11-09

... (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report...

Substituent effects in a series of 1,7-C[subscript 60](R[subscript F])[subscript 2] compounds (R[subscript F] = CF[subscript 3], C[subscript 2]F[subscript 5], n-C[subscrip 3]F[subscript 7], i-C[subscript 3]F[subscript 7], n-C[subscript 4]F[subscript 9], s-C[subscript 4]F[subscript 9], n-C[subscript 8]F[subscript 17]): electron affinities, reduction potentials and E(LUMO) values are not always correlated

DOE Office of Scientific and Technical Information (OSTI.GOV)

Kuvychko, Igor V.; Whitaker, James B.; Larson, Bryon W.

2013-04-08

A series of seven structurally-similar compounds with different pairs of R{sub F} groups were prepared, characterized spectroscopically, and studied by electrochemical methods (cyclic and square-wave voltammetry), low-temperature anion photoelectron spectroscopy, and DFT calculations (five of the compounds are reported here for the first time). This is the first time that a set of seven R{sub F} groups have been compared with respect to their relative effects on E{sub 1/2}(0/-), electron affinity (EA), and the DFT-calculated LUMO energy. The compounds, 1,7-C{sub 60}(R{sub F}){sub 2} (R{sub F} = CF{sub 3}, C{sub 2}F{sub 5}, i-C{sub 3}F{sub 7}, n-C{sub 3}F{sub 7}, s-C{sub 4}F{sub 9},more » n-C{sub 4}F{sub 9} and n-C{sub 8}F{sub 21}), were found to have statistically different electron affinities (EA), at the {+-}10 meV level of uncertainty, but virtually identical first reduction potentials, at the {+-}10 mV level of uncertainty. The lack of a correlation between EA and E{sub 1/2}(0/-), and between E(LUMO) and E{sub 1/2}(0/-), for such similar compounds is unprecedented and suggests that explanations for differences in figures of merit for materials and/or devices that are based on equating easily measurable E{sub 1/2}(0/-) values with EAs or E(LUMO) values should be viewed with caution. The solubilities of the seven compounds in toluene varied by nearly a factor of six, but in an unpredictable way, with the C{sub 2}F{sub 5} and s-C{sub 4}F{sub 9} compounds being the most soluble and the i-C{sub 3}F{sub 7} compound being the least soluble. The effects of the different R{sub F} groups on EAs, E(LUMO) values, and solubilities should help fluorine chemists choose the right R{sub F} group to design new materials with improved morphological, electronic, optical, and/or magnetic properties.« less

Free-Spinning and Recovery Characteristics of a 1/19-Scale Model of the North American T-28C Airplane, TED No. NACA AD 3127

NASA Technical Reports Server (NTRS)

Bowman, James S., Jr.

1956-01-01

An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/19-scale model of the North American T-28C airplane to determine the spin and recovery characteristics. The T-28C airplane is similar to the T-28B airplane except for slight modifications for the arresting hook. The lower rear section of the fuselage was cut out and, consequently, the lower part of the rudder was removed to make a smooth fairing with the fuselage. The T-28B airplane had good recovery characteristics; but these modifications, along with the addition of gun packages on the wings, led to poor and unsatisfactory spin-recovery characteristics during demonstration spins of the T-28C airplane. Model test results indicated that without the gun packages installed, satisfactory recoveries could be obtained if the elevators were held full back while the rudder was fully reversed and the ailerons were held neutral. However, with the addition of gun packages to the wings and the corresponding change in loading, recoveries were considered unsatisfactory. Recoveries attempted by using a larger chord or larger span rudder were improved very slightly, but were still considered marginal or unsatisfactory. Strakes placed on the nose of the model were effective in slowing the spin rotation slightly and, in most instances, decreased the turns for recovery slightly. Recovery characteristics were slightly marginal for the full fuel loading when strakes and the extended-chord rudder were installed; but with the wing fuel partly used, recovery characteristics were again considered unsatisfactory or, at least, definitely on the marginal side. The optimum control technique for recovery is movement of the rudder to full against the spin with the stick held full back (elevators full up) and the ailerons held neutral, followed by forward movement of the stick only after the spin rotation ceases. Inverted-spin test results indicate that the airplane will spin steep and fast and that recovery

Wind-Tunnel Investigation at Low Speed of the Yawing, Pitching, and Static Stability Characteristics of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109

NASA Technical Reports Server (NTRS)

Wolhart, Walter D.; Thomas, David F., Jr.

1955-01-01

An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution.

Stability and Controls Analysis and Flight Test Results of a 24-Foot Telescoping Nose Boom on an F-15B Airplane

NASA Technical Reports Server (NTRS)

Moua, Cheng M.; Cox, Timothy H.; McWherter, Shaun C.

2008-01-01

The Quiet Spike(TradeMark) F-15B flight research program investigated supersonic shock reduction using a 24-ft telescoping nose boom on an F-15B airplane. The program goal was to collect flight data for model validation up to 1.8 Mach. In the area of stability and controls, the primary concerns were to assess the potential destabilizing effect of the oversized nose boom on the stability, controllability, and handling qualities of the airplane and to ensure adequate stability margins across the entire research flight envelope. This paper reports on the stability and control analytical methods, flight envelope clearance approach, and flight test results of the F-15B telescoping nose boom configuration. Also discussed are brief pilot commentary on typical piloting tasks and refueling tasks.

Investigation at near-sonic speed of some effects of humidity on the longitudinal aerodynamic characteristics of an NASA supercritical wing research airplane model

NASA Technical Reports Server (NTRS)

Jordan, F. L., Jr.

1972-01-01

The Langley 8-foot transonic pressure tunnel was used in an effort to determine the effects of humidity at near-sonic speed on the longitudinal aerodynamic characteristics and wing pressure distributions of an area-rule research airplane model with an NASA supercritical wing. Effects of dewpoint at the normal tunnel operating stagnation temperature of 48.9 C (120 F) and effects of stagnation temperature at a relatively high dewpoint of 15.6 C (60 F) were investigated. The test tunnel stagnation pressure was 101 325 N/sq m (1 atmosphere).

76 FR 18664 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-04-05

... apply to The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. That NPRM published... time have changed the text of AWLs No. 28-AWL-27 and No. 28-AWL- 28. Therefore, either of the revisions..., may be used. Request To Extend Compliance Time CAL had no technical objection to the original NPRM...

Flight and Static Exhaust Flow Properties of an F110-GE-129 Engine in an F-16XL Airplane During Acoustic Tests

NASA Technical Reports Server (NTRS)

Holzman, Jon K.; Webb, Lannie D.; Burcham, Frank W., Jr.

1996-01-01

The exhaust flow properties (mass flow, pressure, temperature, velocity, and Mach number) of the F110-GE-129 engine in an F-16XL airplane were determined from a series of flight tests flown at NASA Dryden Flight Research Center, Edwards, California. These tests were performed in conjunction with NASA Langley Research Center, Hampton, Virginia (LARC) as part of a study to investigate the acoustic characteristics of jet engines operating at high nozzle pressure conditions. The range of interest for both objectives was from Mach 0.3 to Mach 0.9. NASA Dryden flew the airplane and acquired and analyzed the engine data to determine the exhaust characteristics. NASA Langley collected the flyover acoustic measurements and correlated these results with their current predictive codes. This paper describes the airplane, tests, and methods used to determine the exhaust flow properties and presents the exhaust flow properties. No acoustics results are presented.

Ditching Tests of Two Models of the Army B-36 Airplane

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; Cederborg, Gibson, A.

1948-01-01

The ditching characteristics of the Army B-36 airplane were determined by testing 1/20- and 1/30-scale dynamic models in calm water in Langley tank no. 2 and at the outdoor catapult. The scope of the tests consisted of ditching the models at various conditions of simulated damage, landing attitudes, and speeds, with various flap settings using several degrees of restraint of the flap hinges. The ditching behavior was evaluated from recordings of deceleration, length of run, and motions of the models. The results showed that the airplane should be ditched at an attitude of about 9 deg with flaps full down. The probable ditching behavior will be a smooth run with a maximum longitudinal deceleration of 3g to 4g and a landing run of 4 to 5 fuselage lengths. Structural failure of the underside of the fuselage will not seriously affect the behavior of the airplane.

75 FR 68688 - Airworthiness Directives; The Boeing Company Model 757 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-11-09

...We are adopting a new airworthiness directive (AD) for all Model 757 airplanes. This AD requires changing the lower fixed leading edge panel assemblies immediately outboard of the nacelles at slats 4 and 7. This AD results from reports of Model 757 airplanes in service that have drain holes and unsealed panel assemblies in the fixed leading edge adjacent to the inboard end of slats 4 and 7 that are too close to the hot portion of the engines. We are issuing this AD to prevent fuel leaking onto an engine and a consequent fire.

Flight Test Results from the Rake Airflow Gage Experiment on the F-15B Airplane

NASA Technical Reports Server (NTRS)

Frederick, Michael A.; Ratnayake, Nalin A.

2010-01-01

The Rake Airflow Gage Experiment involves a flow-field survey rake that was flown on the Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center using the Dryden F-15B research test bed airplane. The objective of this flight test was to ascertain the flow-field angularity, local Mach number profile, total pressure distortion, and dynamic pressure at the aerodynamic interface plane of the Channeled Centerbody Inlet Experiment. This new mixed-compression, supersonic inlet is planned for flight test in the near term. Knowledge of the flow-field characteristics at this location underneath the airplane is essential to flight test planning and computational modeling of the new inlet, and it is also applicable for future propulsion systems research that may use the Propulsion Flight Test Fixture. This report describes the flight test preparation and execution, and the local flowfield properties calculated from pressure measurements of the rake. Data from the two Rake Airflow Gage Experiment research flights demonstrate that the F-15B airplane, flying at a free-stream Mach number of 1.65 and a pressure altitude of 40,000 ft, would achieve the desired local Mach number for the future inlet flight test. Interface plane distortion levels of 2 percent and a local angle of attack of 2 were observed at this condition. Alternative flight conditions for future testing and an exploration of certain anomalous data also are provided.

Flight Test Results from the Rake Airflow Gage Experiment on the F-15B Airplane

NASA Technical Reports Server (NTRS)

Frederick, Michael A.; Ratnayake, Nalin A.

2011-01-01

The Rake Airflow Gage Experiment involves a flow-field survey rake that was flown on the Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center using the Dryden F-15B research test bed airplane. The objective of this flight test was to ascertain the flow-field angularity, local Mach number profile, total pressure distortion, and dynamic pressure at the aerodynamic interface plane of the Channeled Centerbody Inlet Experiment. This new mixed-compression, supersonic inlet is planned for flight test in the near term. Knowledge of the flow-field characteristics at this location underneath the airplane is essential to flight test planning and computational modeling of the new inlet, an< it is also applicable for future propulsion systems research that may use the Propulsion Flight Test Fixture. This report describes the flight test preparation and execution, and the local flow-field properties calculated from pressure measurements of the rake. Data from the two Rake Airflow Gage Experiment research flights demonstrate that the F-15B airplane, flying at a free-stream Mach number of 1.65 and a pressure altitude of 40,000 ft, would achieve the desired local Mach number for the future inlet flight test. Interface plane distortion levels of 2 percent and a local angle of attack of -2 deg were observed at this condition. Alternative flight conditions for future testing and an exploration of certain anomalous data also are provided.

75 FR 30272 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-06-01

... economic impact, positive or negative, on a substantial number of small entities under the criteria of the.... Applicability (c) This AD applies to Model TBM 700 airplanes, all serial numbers (SNs), that: (1) are...

76 FR 58722 - Airworthiness Directives; the Boeing Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-22

...- 200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP series airplanes, without a stretched upper deck or stretched upper deck modification. The existing AD currently requires repetitive inspections for...

The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390

NASA Technical Reports Server (NTRS)

Driver, Cornelius

1956-01-01

Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined. The results indicate that for a horizontal-tail incidence of -10 deg the trim lift coefficient varied from 0.29 at a Mach number of 1.61 to 0.23 at a Mach number of 2.01 with a corresponding decrease in lift-drag trim from 3.72 to 3.15. Stick-position instability was indicated in the low-supersonic-speed range. A photographic-type nose modification resulted in slightly higher values of minimum drag coefficient but did not significantly affect the static stability or lift-curve slope. The minimum drag coefficient for the complete model with the production nose remained essentially constant at 0.047 throughout the Mach number range investigated.

Free-Spinning-Tunnel Investigation of a 1/25-Scale Model of the McDonnell F3H-1N Airplane, TED No. NACA AD 3100

NASA Technical Reports Server (NTRS)

Lee, Henry A.; Wilkes, L. Faye

1954-01-01

An investigation was conducted in the Langley 20-foot free-spinning tunnel on a 1/23-scale model of the McDonnell F3H-1N airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the clean condition. Spin-recovery parachute tests were also performed. The results indicated that erect spins obtained on the airplane for the take-off or combat loadings should be satisfactorily terminated if full rudder reversal is accompanied by moving the ailerons to full with the spin (stick full right in a right spin). The spins obtained should be oscillatory in pitch, roll, and yaw. Recoveries from inverted spins should be satisfactory by full reversal of the rudder. A 16.7-foot- diameter tail parachute with a towline length of 30 feet and a drag coefficient of 0.734 should be adequate for emergency recovery from demonstration spins.

Minimum time and fuel flight profiles for an F-15 airplane with a Highly Integrated Digital Electronic Control (HIDEC) system

NASA Technical Reports Server (NTRS)

Haering, E. A., Jr.; Burcham, F. W., Jr.

1984-01-01

A simulation study was conducted to optimize minimum time and fuel consumption paths for an F-15 airplane powered by two F100 Engine Model Derivative (EMD) engines. The benefits of using variable stall margin (uptrim) to increase performance were also determined. This study supports the NASA Highly Integrated Digital Electronic Control (HIDEC) program. The basis for this comparison was minimum time and fuel used to reach Mach 2 at 13,716 m (45,000 ft) from the initial conditions of Mach 0.15 at 1524 m (5000 ft). Results were also compared to a pilot's estimated minimum time and fuel trajectory determined from the F-15 flight manual and previous experience. The minimum time trajectory took 15 percent less time than the pilot's estimate for the standard EMD engines, while the minimum fuel trajectory used 1 percent less fuel than the pilot's estimate for the minimum fuel trajectory. The F-15 airplane with EMD engines and uptrim, was 23 percent faster than the pilot's estimate. The minimum fuel used was 5 percent less than the estimate.

Loads Model Development and Analysis for the F/A-18 Active Aeroelastic Wing Airplane

NASA Technical Reports Server (NTRS)

Allen, Michael J.; Lizotte, Andrew M.; Dibley, Ryan P.; Clarke, Robert

2005-01-01

The Active Aeroelastic Wing airplane was successfully flight-tested in March 2005. During phase 1 of the two-phase program, an onboard excitation system provided independent control surface movements that were used to develop a loads model for the wing structure and wing control surfaces. The resulting loads model, which was used to develop the control laws for phase 2, is described. The loads model was developed from flight data through the use of a multiple linear regression technique. The loads model input consisted of aircraft states and control surface positions, in addition to nonlinear inputs that were calculated from flight-measured parameters. The loads model output for each wing consisted of wing-root bending moment and torque, wing-fold bending moment and torque, inboard and outboard leading-edge flap hinge moment, trailing-edge flap hinge moment, and aileron hinge moment. The development of the Active Aeroelastic Wing loads model is described, and the ability of the model to predict loads during phase 2 research maneuvers is demonstrated. Results show a good match to phase 2 flight data for all loads except inboard and outboard leading-edge flap hinge moments at certain flight conditions. The average load prediction errors for all loads at all flight conditions are 9.1 percent for maximum stick-deflection rolls, 4.4 percent for 5-g windup turns, and 7.7 percent for 4-g rolling pullouts.

14 CFR Appendix F to Part 135 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Airplane Flight Recorder Specification F... from the air data computer when practicable. 3. Indicated airspeed or Calibrated airspeed 50 KIAS or minimum value to Max Vso≢ and Vso to 1.2 V.D ±5% and ±3% 1 1 kt Data should be obtained from the air data...

14 CFR Appendix F to Part 135 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Airplane Flight Recorder Specification F... from the air data computer when practicable. 3. Indicated airspeed or Calibrated airspeed 50 KIAS or minimum value to Max Vso≢ and Vso to 1.2 V.D ±5% and ±3% 1 1 kt Data should be obtained from the air data...

14 CFR Appendix F to Part 135 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Airplane Flight Recorder Specification F... from the air data computer when practicable. 3. Indicated airspeed or Calibrated airspeed 50 KIAS or minimum value to Max Vso≢ and Vso to 1.2 V.D ±5% and ±3% 1 1 kt Data should be obtained from the air data...

14 CFR Appendix F to Part 135 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Airplane Flight Recorder Specification F... from the air data computer when practicable. 3. Indicated airspeed or Calibrated airspeed 50 KIAS or minimum value to Max Vso≢ and Vso to 1.2 V.D ±5% and ±3% 1 1 kt Data should be obtained from the air data...

75 FR 52482 - Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-26

..., check the airplane maintenance records to determine if the left and/or right aileron outboard bearing... an entry is found during the airplane maintenance records check required in paragraph (f)(1) of this...-0849; Directorate Identifier 2010-CE-043-AD] RIN 2120-AA64 Airworthiness Directives; PILATUS Aircraft...

C20H4(C4F8)3: a fluorine-containing annulated corannulene that is a better electron acceptor than C60.

PubMed

Kuvychko, Igor V; Dubceac, Cristina; Deng, Shihu H M; Wang, Xue-Bin; Granovsky, Alexander A; Popov, Alexey A; Petrukhina, Marina A; Strauss, Steven H; Boltalina, Olga V

2013-07-15

At sixes and sevens: The reaction of corannulene with 35 equivalents of 1,4-C4F8I2 is an efficient and a relatively selective process that yields two main products in which six H atoms are substituted with three C4F8 moieties that form six- and seven-membered rings. Low-temperature photoelectron spectroscopy showed the electron affinity of the major isomer (shown) exceeds that of C60 (2.74±0.02 and 2.689±0.008 eV, respectively). Copyright © 2013 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

78 FR 11978 - Airworthiness Directives; Reims Aviation S.A. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-02-21

... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2012... Airworthiness Directives; Reims Aviation S.A. Airplanes AGENCY: Federal Aviation Administration (FAA... directive (AD) for Reims Aviation S.A. Model F406 airplanes. This AD results from mandatory continuing...

Thrust stand evaluation of engine performance improvement algorithms in an F-15 airplane

NASA Technical Reports Server (NTRS)

Conners, Timothy R.

1992-01-01

An investigation is underway to determine the benefits of a new propulsion system optimization algorithm in an F-15 airplane. The performance seeking control (PSC) algorithm optimizes the quasi-steady-state performance of an F100 derivative turbofan engine for several modes of operation. The PSC algorithm uses an onboard software engine model that calculates thrust, stall margin, and other unmeasured variables for use in the optimization. As part of the PSC test program, the F-15 aircraft was operated on a horizontal thrust stand. Thrust was measured with highly accurate load cells. The measured thrust was compared to onboard model estimates and to results from posttest performance programs. Thrust changes using the various PSC modes were recorded. Those results were compared to benefits using the less complex highly integrated digital electronic control (HIDEC) algorithm. The PSC maximum thrust mode increased intermediate power thrust by 10 percent. The PSC engine model did very well at estimating measured thrust and closely followed the transients during optimization. Quantitative results from the evaluation of the algorithms and performance calculation models are included with emphasis on measured thrust results. The report presents a description of the PSC system and a discussion of factors affecting the accuracy of the thrust stand load measurements.

Preliminary Flight Results of a Fly-by-throttle Emergency Flight Control System on an F-15 Airplane

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Maine, Trindel A.; Fullerton, C. Gordon; Wells, Edward A.

1993-01-01

A multi-engine aircraft, with some or all of the flight control system inoperative, may use engine thrust for control. NASA Dryden has conducted a study of the capability and techniques for this emergency flight control method for the F-15 airplane. With an augmented control system, engine thrust, along with appropriate feedback parameters, is used to control flightpath and bank angle. Extensive simulation studies were followed by flight tests. The principles of throttles only control, the F-15 airplane, the augmented system, and the flight results including actual landings with throttles-only control are discussed.

75 FR 82335 - Airworthiness Directives; APEX Aircraft Model CAP 10 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-30

... Model CAP 10 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... accident occurred to a CAP 10C, in which the pilot lost control of the aeroplane. The following... condition for the specified products. The MCAI states: A fatal accident occurred to a CAP 10C, in which the...

77 FR 16490 - Airworthiness Directives; Bombardier, Inc. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-03-21

...-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900) airplanes. This proposed AD was prompted by... and fuel tubes, and protective shields on the rudder quadrant support-beam in the aft equipment...

Preliminary Results Obtained from Flight Test of a 1/7-Scale Rocket-Powered Model of the Grumman XF10F Airplane Configuration in the Swept-Wing Condition, TED No. NACA DE 354

NASA Technical Reports Server (NTRS)

Gardner, William N.

1951-01-01

A flight investigation of a 1/7-scale rocket-powered model of the XF10F Grumman XFl0F airplane in the swept-wing configuration has been made. The purpose of this test was to determine the static longitudinal stability, damping in pitch, and longitudinal control effectiveness of the airplane with the center of gravity at 20 percent of the wing mean aerodynamic chord. Only a small amount of data was obtained from the test because, immediately after booster separation at a Mach number of 0.88, the configuration was directionally unstable and diverged in sideslip. Simultaneous with the sideslip divergence, the model became longitudinally unstable at 3 degree angle of attack and -6 degree sideslip and diverged in pitch to a high angle of attack. During the pitch-up the free-floating horizontal tail became unstable at 5 degree angle of attack and the tail drifted against its positive deflection limit.

75 FR 66655 - Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-10-29

... December 3, 2010 (the effective date of this AD), check the airplane maintenance records to determine if... of the airplane. Do this check following paragraph 3.A. of Pilatus Aircraft Ltd. PC-7 Service... maintenance records check required in paragraph (f)(1) of this AD or it is unclear whether or not the left and...

75 FR 49370 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-13

.... American Airlines states that this will allow for more efficient planning and will relieve the burden of obtaining special flight permits to move re-activated airplanes to facilities where the inspections are to.... We have added a compliance time of within 840 flight hours after the effective date of this AD to...

78 FR 75511 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-12

... Design Features The C-series airplanes will incorporate the following novel or unusual design features: A.... Conclusion This action affects only certain novel or unusual design features on two model series of airplanes... Inc., Models BD-500-1A10 and BD- 500-1A11 Series Airplanes; Electronic Flight Control System: Control...

Rate coefficients for the reaction of O(1D) with the atmospherically long-lived greenhouse gases NF3, SF5CF3, CHF3, C2F6, c-C4F8, n-C5F12, and n-C6F14

NASA Astrophysics Data System (ADS)

Baasandorj, M.; Hall, B. D.; Burkholder, J. B.

2012-12-01

The contribution of atmospherically persistent (long-lived) greenhouse gases to the radiative forcing of Earth has increased over the past several decades. The impact of highly fluorinated, saturated compounds, in particular perfluorinated compounds, on climate change is a concern because of their long atmospheric lifetimes, which are primarily determined by stratospheric loss processes, as well as their strong absorption in the infrared "window" region. A potentially key stratospheric loss process for these compounds is their gas-phase reaction with electronically excited oxygen atoms, O(1D). Therefore, accurate reaction rate coefficient data is desired for input to climate change models. In this work, rate coefficients, k, were measured for the reaction of O(1D) with several key long-lived greenhouse gases, namely NF3, SF5CF3, CHF3 (HFC-23), C2F6, c-C4F8, n-C5F12, and n-C6F14. Room temperature rate coefficients for the total reaction, kTot, corresponding to loss of O(1D), and reactive channel, kR, corresponding to the loss of the reactant compound, were measured for NF3 and SF5CF3 using competitive reaction and relative rate methods, respectively. kR was measured for the CHF3 reaction and improved upper-limits were determined for the perfluorinated compounds included in this study. For NF3, kTot was determined to be (2.55 ± 0.38) × 10-11 cm3 molecule-1 s-1 and kR, which was measured using CF3Cl, N2O, CF2ClCF2Cl (CFC-114), and CF3CFCl2 (CFC-114a) as reference compounds, was determined to be (2.21 ± 0.33) × 10-11 cm3 molecule-1 s-1. For SF5CF3, kTot = (3.24 ± 0.50) × 10-13 cm3 molecule-1 s-1 and kR < 5.8 × 10×14 cm3 molecule-1 s-1 were measured, where kR is a factor of three lower than the current recommendation of kTot for use in atmospheric modeling. For CHF3 kR was determined to be (2.35 ± 0.35) × 10-12 cm3 molecule-1 s-1, which corresponds to a reactive channel yield of 0.26 ± 0.04, and resolves a large discrepancy among previously reported values

28 CFR 55.8 - Relationship between section 4(f)(4) and section 203(c).

Code of Federal Regulations, 2014 CFR

2014-07-01

... the 1975 Amendments to the Act. (c) Although the coverage formulas applicable to section 4(f)(4) and section 203(c) are different, a political subdivision may be included within both of the coverage formulas. Under these circumstances, a judgment terminating coverage of the jurisdiction under one provision would...

28 CFR 55.8 - Relationship between section 4(f)(4) and section 203(c).

Code of Federal Regulations, 2013 CFR

2013-07-01

... the 1975 Amendments to the Act. (c) Although the coverage formulas applicable to section 4(f)(4) and section 203(c) are different, a political subdivision may be included within both of the coverage formulas. Under these circumstances, a judgment terminating coverage of the jurisdiction under one provision would...

An overview of integrated flight-propulsion controls flight research on the NASA F-15 research airplane

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Gatlin, Donald H.; Stewart, James F.

1995-01-01

The NASA Dryden Flight Research Center has been conducting integrated flight-propulsion control flight research using the NASA F-15 airplane for the past 12 years. The research began with the digital electronic engine control (DEEC) project, followed by the F100 Engine Model Derivative (EMD). HIDEC (Highly Integrated Digital Electronic Control) became the umbrella name for a series of experiments including: the Advanced Digital Engine Controls System (ADECS), a twin jet acoustics flight experiment, self-repairing flight control system (SRFCS), performance-seeking control (PSC), and propulsion controlled aircraft (PCA). The upcoming F-15 project is ACTIVE (Advanced Control Technology for Integrated Vehicles). This paper provides a brief summary of these activities and provides background for the PCA and PSC papers, and includes a bibliography of all papers and reports from the NASA F-15 project.

77 FR 2437 - Special Conditions: Gulfstream Aerospace Corporation, Model GVI Airplane; Rechargeable Lithium...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-01-18

..., transport-category airplanes were derived from Civil Air Regulations (CAR) Part 4b.625(d) as part of the re-codification of CAR 4b that established 14 CFR part 25 in February 1965. The new battery requirements, Sec. 25.1353(c) (1) through (c)(4), basically reworded the CAR requirements. Increased use of nickel-cadmium...

78 FR 42724 - Airworthiness Directives; Beechcraft Corporation Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-07-17

... certain Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. AD 2011-27-51 currently requires... deformation to the weight and/or weight bracket with corrective action as necessary. Since we issued AD 2011..., January 18, 2012), for certain Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. AD...

CLEC4F Is an Inducible C-Type Lectin in F4/80-Positive Cells and Is Involved in Alpha-Galactosylceramide Presentation in Liver

PubMed Central

Yang, Chih-Ya; Chen, Jiun-Bo; Tsai, Ting-Fen; Tsai, Yi-Chen; Tsai, Ching-Yen; Liang, Pi-Hui; Hsu, Tsui-Ling; Wu, Chung-Yi; Netea, Mihai G.; Wong, Chi-Huey; Hsieh, Shie-Liang

2013-01-01

CLEC4F, a member of C-type lectin, was first purified from rat liver extract with high binding affinity to fucose, galactose (Gal), N-acetylgalactosamine (GalNAc), and un-sialylated glucosphingolipids with GalNAc or Gal terminus. However, the biological functions of CLEC4F have not been elucidated. To address this question, we examined the expression and distribution of murine CLEC4F, determined its binding specificity by glycan array, and investigated its function using CLEC4F knockout (Clec4f−/−) mice. We found that CLEC4F is a heavily glycosylated membrane protein co-expressed with F4/80 on Kupffer cells. In contrast to F4/80, CLEC4F is detectable in fetal livers at embryonic day 11.5 (E11.5) but not in yolk sac, suggesting the expression of CLEC4F is induced as cells migrate from yolk cells to the liver. Even though CLEC4F is not detectable in tissues outside liver, both residential Kupffer cells and infiltrating mononuclear cells surrounding liver abscesses are CLEC4F-positive upon Listeria monocytogenes (L. monocytogenes) infection. While CLEC4F has strong binding to Gal and GalNAc, terminal fucosylation inhibits CLEC4F recognition to several glycans such as Fucosyl GM1, Globo H, Bb3∼4 and other fucosyl-glycans. Moreover, CLEC4F interacts with alpha-galactosylceramide (α-GalCer) in a calcium-dependent manner and participates in the presentation of α-GalCer to natural killer T (NKT) cells. This suggests that CLEC4F is a C-type lectin with diverse binding specificity expressed on residential Kupffer cells and infiltrating monocytes in the liver, and may play an important role to modulate glycolipids presentation on Kupffer cells. PMID:23762286

26 CFR 5c.168(f)(8)-4 - Minimum investment of lessor.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 26 Internal Revenue 14 2010-04-01 2010-04-01 false Minimum investment of lessor. 5c.168(f)(8)-4....168(f)(8)-4 Minimum investment of lessor. (a) Minimum investment. Under section 168(f)(8)(B)(ii), an... has a minimum at risk investment which, at the time the property is placed in service under the lease...

26 CFR 5c.168(f)(8)-4 - Minimum investment of lessor.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 26 Internal Revenue 14 2011-04-01 2010-04-01 true Minimum investment of lessor. 5c.168(f)(8)-4....168(f)(8)-4 Minimum investment of lessor. (a) Minimum investment. Under section 168(f)(8)(B)(ii), an... has a minimum at risk investment which, at the time the property is placed in service under the lease...

Effect of the Surface Condition of a Wing on the Aerodynamic Characteristics of an Airplane

NASA Technical Reports Server (NTRS)

Defrance, S J

1934-01-01

In order to determine the effect of the surface conditions of a wing on the aerodynamic characteristics of an airplane, tests were conducted in the N.A.C.A. full-scale wind tunnel on the Fairchild F-22 airplane first with normal commercial finish of wing surface and later with the same wing polished. Comparison of the characteristics of the airplane with the two surface conditions shows that the polish caused a negligible change in the lift curve, but reduced the minimum drag coefficient by 0.001. This reduction in drag if applied to an airplane with a given speed of 200 miles per hour and a minimum drag coefficient of 0.025 would increase the speed only 2.9 miles per hour, but if the speed remained the same, the power would be reduced 4 percent.

76 FR 12845 - Airworthiness Directives; APEX Aircraft Model CAP 10 B Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-09

... Airworthiness Directives; APEX Aircraft Model CAP 10 B Airplanes AGENCY: Federal Aviation Administration (FAA... CAP 10C, in which the pilot lost control of the aeroplane. The following investigation has revealed... a CAP 10C, in which the pilot lost control of the aeroplane. The following investigation has...

Effects of feedstock availability on the negative ion behavior in a C{sub 4}F{sub 8} inductively coupled plasma

DOE Office of Scientific and Technical Information (OSTI.GOV)

Zhao, Shu-Xia; Research group PLASMANT, Dept. Chemistry, University of Antwerp, Universiteitsplein 1, B-2610 Antwerp; Gao, Fei

2015-07-21

In this paper, the negative ion behavior in a C{sub 4}F{sub 8} inductively coupled plasma (ICP) is investigated using a hybrid model. The model predicts a non-monotonic variation of the total negative ion density with power at low pressure (10–30 mTorr), and this trend agrees well with experiments that were carried out in many fluorocarbon (fc) ICP sources, like C{sub 2}F{sub 6}, CHF{sub 3}, and C{sub 4}F{sub 8}. This behavior is explained by the availability of feedstock C{sub 4}F{sub 8} gas as a source of the negative ions, as well as by the presence of low energy electrons due tomore » vibrational excitation at low power. The maximum of the negative ion density shifts to low power values upon decreasing pressure, because of the more pronounced depletion of C{sub 4}F{sub 8} molecules, and at high pressure (∼50 mTorr), the anion density continuously increases with power, which is similar to fc CCP sources. Furthermore, the negative ion composition is identified in this paper. Our work demonstrates that for a clear understanding of the negative ion behavior in radio frequency C{sub 4}F{sub 8} plasma sources, one needs to take into account many factors, like the attachment characteristics, the anion composition, the spatial profiles, and the reactor configuration. Finally, a detailed comparison of our simulation results with experiments is conducted.« less

Inhibition of c-Myc by 10058-F4 induces growth arrest and chemosensitivity in pancreatic ductal adenocarcinoma.

PubMed

Zhang, Meng; Fan, Hai-Yan; Li, Sheng-Chao

2015-07-01

Pancreatic ductal adenocarcinoma (PDAC) is a formidable medical challenge due to its malignancies and the absence of effective treatment. c-Myc, as an important transcription factor, plays crucial roles in cell cycle progression, apoptosis and cellular transformation. The c-Myc inhibitor, 10058-F4, has been reported act as a tumor suppressor in several different tumors. In current study, the tumor-suppressive roles of 10058-F4 was observed in human pancreatic cancer cells in vitro as demonstrated by decreased cell viability, cell cycle arrest at the G1/S transition and increased caspase3/7 activity. And tumor responses to gemcitabine were also significantly enhanced by 10058-F4 in PANC-1 and SW1990 cells. In a subcutaneous xenograft model, however, 10058-F4 showed no significant influence on pancreatic tumorigenesis. When combined with gemcitabine, tumorigenesis was drastically attenuated compared with gemcitabine group or 10058-F4 group; this synergistic effect was accompanied with decreased PCNA-positive cells and reduced TUNEL-positive cells in the combined treated group. Subsequent studies revealed that decreased glycolysis may be involved in the inhibitory effect of 10058-F4 on PDAC. Taken together, this study demonstrates the roles of 10058-F4 in PDAC and provides evidence that 10058-F4 in combination with gemcitabine showed significant clinical benefit over the usage of gemcitabine alone. Copyright © 2015. Published by Elsevier Masson SAS.

Photographer; NACA North American F-100A NASA-200 Super Sabre airplane - wing leading edge deflected

NASA Technical Reports Server (NTRS)

1958-01-01

Photographer; NACA North American F-100A NASA-200 Super Sabre airplane - wing leading edge deflected 60 degrees for increased lift with boundary=layer control; takeoff preformance was improved 10% (mar 1960)

78 FR 72568 - Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-03

... Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes AGENCY: Federal Aviation Administration... airworthiness directive (AD) for Diamond Aircraft Industries GmbH Models DA40 and DA40F airplanes. This AD..., contact Diamond Aircraft Industries GmbH, N.A. Otto-Str.5, A-2700 Wiener Neustadt, Austria; telephone: +43...

Emissions of Tetrafluoromethane (CF4) and Hexafluoroethane (C2F6) from East Asian Aluminum and Semiconductor Industries

NASA Astrophysics Data System (ADS)

Kim, J.; Li, S.; Muhle, J.; Fang, X.; Manning, A. J.; Arnold, T.; Park, S.; Park, M.; Saito, T.; Yokouchi, Y.; Stohl, A.; Weiss, R. F.; Kim, K.

2013-12-01

Tetrafluoromethane (CF4) and Hexafluoroethane (C2F6) are among the most potent greenhouse gases (GHGs), with atmospheric lifetimes of 50,000 and 10,000 years and 100-year Global Warming Potentials of 7,490 and 12,200, respectively. The Chinese aluminum smelting (AL) industry, accounting for 39% of the global aluminum production in 2010, has become a significant emitter of these compounds to the atmosphere, . The AL industry has estimated its Chinese emissions averaged over 2008-2010 at 1.4 Gg/yr of CF4 and 0.06 Gg/yr of C2F6. In this study we combine East Asian measurements of C2F6 at Gosan (Jeju Island, Korea), Hateruma, and Ochi-Ishi (Japan) and of CF4 at Gosan, using inversion techniques and two Lagrangian particle dispersion models (FLEXPART and NAME), to estimate the emissions of these two compounds from China and East Asia. Our results yield total emissions from China for the 2008-2010 period of approximately 4 × 0.5 Gg/yr for CF4 and 0.8 × 0.1 Gg/yr for C2F6. These results may be reconciled if emissions of these compounds from China's semiconductor (SC) industry are larger than currently estimated. However, evidence presented in the analysis of the inversion results and in the C2F6/CF4 emission ratios observed for China suggest that China's AL industry emissions are likely to be the dominant source of the discrepancy between reported emissions and those inferred from atmospheric measurements. As the AL and SC industries evolve toward new manufacturing technologies that reduce GHG emissions, continued and improved atmospheric measurements and modeling in this region will be useful in assessing the effectiveness of these changes.

75 FR 7942 - Airworthiness Directives; Airbus Model A310-203, -221, -222 Airplanes; and Model A300 F4-605R and...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-02-23

... gear retraction. * * * * * The unsafe condition is potential loss of control of the airplane during... when the speed of the aeroplane is greater than 100 knots and until landing gear retraction. To prevent... greater than 100 knots and until landing gear retraction. To prevent further incidents of inadvertent...

Preliminary flight test results of a fly-by-throttle emergency flight control system on an F-15 airplane

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Maine, Trindel A.; Fullerton, C. G.; Wells, Edward A.

1993-01-01

A multi-engine aircraft, with some or all of the flight control system inoperative, may use engine thrust for control. NASA Dryden has conducted a study of the capability and techniques for this emergency flight control method for the F-15 airplane. With an augmented control system, engine thrust, along with appropriate feedback parameters, is used to control flightpath and bank angle. Extensive simulation studies have been followed by flight tests. This paper discusses the principles of throttles-only control, the F-15 airplane, the augmented system, and the flight results including landing approaches with throttles-only control to within 10 ft of the ground.

77 FR 50644 - Airworthiness Directives; Cessna Airplane Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-08-22

... airplanes that have P/N 1134104-1 or 1134104-5 A/C compressor motor installed; an aircraft logbook check for... following: (1) Inspect the number of hours on the A/C compressor hour meter; and (2) Check the aircraft.... Do the replacement following Cessna Aircraft Company Model 525 Maintenance Manual, Revision 23, dated...

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms September 4, 1947 to September 5, 1947 at Clinton County Army Air Field, Ohio

NASA Technical Reports Server (NTRS)

Funk, Jack

1948-01-01

The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from September 4, 1947 to September 5, 1947 are presented.

78 FR 63847 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Airplane Electronic System Security...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-10-25

... design feature associated with the architecture and connectivity capabilities of the airplanes' computer... the comment for an association, business, labor union, etc.). DOT's complete Privacy Act Statement can... architecture for the Embraer Model EMB-550 series of airplanes is composed of several connected networks. This...

Generic Airplane Model Concept and Four Specific Models Developed for Use in Piloted Simulation Studies

NASA Technical Reports Server (NTRS)

Hoffler, Keith D.; Fears, Scott P.; Carzoo, Susan W.

1997-01-01

A generic airplane model concept was developed to allow configurations with various agility, performance, handling qualities, and pilot vehicle interface to be generated rapidly for piloted simulation studies. The simple concept allows stick shaping and various stick command types or modes to drive an airplane with both linear and nonlinear components. Output from the stick shaping goes to linear models or a series of linear models that can represent an entire flight envelope. The generic model also has provisions for control power limitations, a nonlinear feature. Therefore, departures from controlled flight are possible. Note that only loss of control is modeled, the generic airplane does not accurately model post departure phenomenon. The model concept is presented herein, along with four example airplanes. Agility was varied across the four example airplanes without altering specific excess energy or significantly altering handling qualities. A new feedback scheme to provide angle-of-attack cueing to the pilot, while using a pitch rate command system, was implemented and tested.

Noise exposure levels from model airplane engines.

PubMed

Pearlman, R C; Miller, M

1985-01-01

Previous research indicates that noise levels from unmuffled model airplane engines produce sufficient noise to cause TTS. The present study explored SPLs of smaller engines under 3.25 cc (.19 cu. in.) and the effectiveness of engine mufflers. Results showed that model airplanes can exceed a widely used damage risk criterion (DRC) but that engine mufflers can reduce levels below DRC. Handling model gasoline engines should be added to the list of recreational activities such as snow-mobile and motorcycle riding, shooting, etc. in which the participant's hearing may be in jeopardy. Suggestions are presented to the model engine enthusiast for avoiding damage to hearing.

Flight Measurements of the Longitudinal Stability and Control Characteristics of the Grumman F8F-1 Airplane, TED No. NACA 2379

NASA Technical Reports Server (NTRS)

Assadourian, Arthur; Reeder, John P.

1948-01-01

A series of flight tests have been made at the Langley Flight Research Division at the request of the Bureau of Aeronautics, Department of the Navy, to determine the flying qualities of the Grumman F8F-1 air- plane. This paper presents the test results necessary to determine the longitudinal stability and control characteristics end the stalling characteristics. These tests were made between February and June of 1947- The range of Mach numbers covered in this investigation was approximately 0.10 to 0.62, and no attempt was made to investigate compressibility effects at higher Mach numbers. The lateral and directional stability and control characteristics of the subject airplane have already been reported (reference 1). Also presented in this paper is a discussion of the normal accelerations induced by yawing velocity and sideslip which were considered ob,jectionable by the pilot for this airplane. A discussion of the undesirable accelerations has been included with a view towards formulating some flying-qualities requirements limiting them.

Variable-Structure Control of a Model Glider Airplane

NASA Technical Reports Server (NTRS)

Waszak, Martin R.; Anderson, Mark R.

2008-01-01

A variable-structure control system designed to enable a fuselage-heavy airplane to recover from spin has been demonstrated in a hand-launched, instrumented model glider airplane. Variable-structure control is a high-speed switching feedback control technique that has been developed for control of nonlinear dynamic systems.

76 FR 1985 - Airworthiness Directives; Short Brothers PLC Model SD3 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-01-12

... Airworthiness Directives; Short Brothers PLC Model SD3 Airplanes AGENCY: Federal Aviation Administration (FAA..., June 16, 2006) and adding the following new AD: 2010-24-06 Short Brothers PLC: Amendment 39-16525..., Amendment 39-14644. Applicability (c) This AD applies to all Short Brothers PLC Model SD3-60 SHERPA, SD3...

f57f4.4p::gfp as a fluorescent reporter for analysis of the C. elegans response to bacterial infection.

PubMed

Julien-Gau, Ingrid; Schmidt, Marion; Kurz, C Léopold

2014-02-01

Host defense mechanisms are multi-layered and involve constitutive as well as inducible components. The dissection of these complex processes can be greatly facilitated using a reporter gene strategy with a transparent animal. In this study, we use Caenorhabditis elegans as a model host and introduce a new pathogen-inducible fluorescent reporter involving the promoter of f57f4.4, a gene encoding a putative component of the glycocalyx. We show that this reporter construct does not respond to heavy metal or hypertonic environments, but is specifically and locally induced in the intestine upon Photorhabus luminescens and Pseudomonas aeruginosa infections. We further demonstrate that its upregulation requires live pathogens as well as elements of the nematode p38 MAP kinase and TGF-beta pathways. In addition to introducing a new tool for the study of the interactions between C. elegans and a pathogen, our results suggest a role for the glycocalyx in gut immunity. Copyright © 2013 Elsevier Ltd. All rights reserved.

Vanguard 2C VTOL Airplane Tested in the Ames 40x80 Foot Wind Tunnel.

NASA Image and Video Library

1960-02-01

Vanguard 2C vertical take-off and landing (VTOL) airplane, wind tunnel test. Front view from below, model 14 1/2 feet high disk off. Nasa Ames engineer Ralph Maki in photo. Variable height struts and ground plane, low pressure ratio, fan in wing. 02/01/1960.

Tests on Models of Three British Airplanes in the Variable Density Wind Tunnel

NASA Technical Reports Server (NTRS)

Higgins, George J; Defoe, George L; Diehl, W S

1928-01-01

This report contains the results of tests made in the National Advisory Committee for Aeronautics variable density wind tunnel on three airplane models supplied by the British Aeronautical Research Committee. These models, the BE-2E with R.A.F. 19 wings, the British Fighter with R.A.F. 15 wings, and the Bristol Fighter with R.A.F. 30 wings, were tested over a wide range in Reynolds numbers in order to supply data desired by the Aeronautical Research Committee for scale effect studies. The maximum lifts obtained in these tests are in excellent agreement with the published results of British tests, both model and full scale. No attempt is made to compare drag data, owing to the emission of tail surfaces, radiator, etc., from the model, but is shown that the scale effect observed on the drag coefficients in these tests is due to a large extent to the parts of the models other than the wings. (author)

76 FR 56286 - Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, and -243 Airplanes, Model A330...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-13

... Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes AGENCY: Federal Aviation... A340-200/-300 aeroplanes. An extended de-bonding, if not detected and corrected, may degrade the...

Evaluation of the Impact of Towing DC-9 Transport Airplanes at Boston-Logan Airport.

DTIC Science & Technology

1980-05-01

42- 22’ 71’ 02’ 12 1617 [t6 -96 F6p olt ln, slotr ADHA ,- r ’ C is on 11 f / 1 -3 . P o s.Nt Ofic /29/3 / 06/64 70 0 ftj. SE 42- 21’ 71’ W1 20 360 337 336...34A-A8 $64 DOUGLAS AIRCRAFT CO LONG BEACH CA PIG/ 1 /2 GG EVALUATION OF THE IMPACT OF TOWING DC-9 TRANSPORT AIRPLANES AT -ETC(U) MAY G0 E A HOOVER DOT...a -ib’f t0 tie U S. pubic through the Nat onj T, r ,ca, h -nrrmatior Ser\\ice, St 1 ’ o c: a q~nii 22161 - - ,.......~ - r’) C 2 TAINKD A ,4

Transonic wind-tunnel tests of an F-8 airplane model equipped with 12 and 14-percent thick oblique wings

NASA Technical Reports Server (NTRS)

Smith, R. C.; Jones, R. T.; Summers, J. L.

1975-01-01

An experimental investigation was conducted in the Ames 14-foot transonic wind tunnel to study the aerodynamic performance and stability characteristics of a 0.087-scale model of an F-8 airplane fitted with an oblique wing. Two elliptical planform (axis ratio = 8:1) wings, each having a maximum thickness of 12 and 14 percent, were tested. Longitudinal stability data were obtained with no wing and with each of the two wings set at sweep angles of 0, 45, and 60 deg. Lateral directional stability data were obtained for the 12 percent wing only. Test Mach numbers ranged from 0.6 to 1.2 in the unit Reynolds number range from 11.2 to 13.1 million per meter. Angles of attack were between -6 and 22 deg at zero sideslip. Angles of sideslip were between -6 and +6 deg for two angles of attack, depending upon the wing configuration.

77 FR 36129 - Airworthiness Directives; Bombardier, Inc. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-18

... (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900... the wing box and fuel tubes, and protective shields on the rudder quadrant support-beam in the aft...

78 FR 42417 - Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-07-16

... certain Pilatus Aircraft Ltd. Model PC-6/B2-H4 airplanes. This AD results from mandatory continuing... Aircraft Ltd. Model PC-6/B2-H4 airplanes, serial numbers 735, 863, 909, 923, 948, 956, 958, 977, 978, 979...

78 FR 20229 - Airworthiness Directives; The Boeing Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-04-04

... Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. That AD currently... 20231

Synthesis and structure resolution of RbLaF4.

PubMed

Rollet, Anne-Laure; Allix, Mathieu; Veron, Emmanuel; Deschamps, Michael; Montouillout, Valérie; Suchomel, Matthew R; Suard, Emmanuelle; Barre, Maud; Ocaña, Manuel; Sadoc, Aymeric; Boucher, Florent; Bessada, Catherine; Massiot, Dominique; Fayon, Franck

2012-02-20

The synthesis and structure resolution of RbLaF(4) are described. RbLaF(4) is synthesized by solid-state reaction between RbF and LaF(3) at 425 °C under a nonoxidizing atmosphere. Its crystal structure has been resolved by combining neutron and synchrotron powder diffraction data refinements (Pnma,a = 6.46281(2) Å, b = 3.86498(1) Å, c = 16.17629(4) Å, Z = 4). One-dimensional (87)Rb, (139)La, and (19)F MAS NMR spectra have been recorded and are in agreement with the proposed structural model. Assignment of the (19)F resonances is performed on the basis of both (19)F-(139)La J-coupling multiplet patterns observed in a heteronuclear DQ-filtered J-resolved spectrum and (19)F-(87)Rb HMQC MAS experiments. DFT calculations of both the (19)F isotropic chemical shieldings and the (87)Rb, (139)La electric field gradient tensors using the GIPAW and PAW methods implemented in the CASTEP code are in good agreement with the experimental values and support the proposed structural model. Finally, the conductivity of RbLaF(4) and luminescence properties of Eu-doped LaRbF(4) are investigated.

Investigation of Incipient Spin Characteristics of a 1/35-Scale Model of the Convair F-102A Airplane, Coord. No. AF-AM-79

NASA Technical Reports Server (NTRS)

Healy, Frederick M.

1958-01-01

Incipient spin characteristics have been investigated on a l/35-scale dynamic model of the Convair F-10% airplane. The model was launched by a catapult apparatus into free flight with various control settings, and the motions obtained were photographed. The model was ballasted for the combat loading. All tests were made with the speed brakes and landing gear retracted, and engine effects were not simulated. The results of the investigation indicated that the model would enter motions apparently simulating entry phases of spins when the elevators were deflected full up. Deflecting the rudder had little effect on the direction of the motion obtained, but when ailerons were deflected the model always rotated in a direction opposite to the aileron setting (that is, the model entered a right spin with the stick to the left). The ailerons were very influential in initiating spin entry, and the pilot should avoid, as far as possible, the use of ailerons in low-speed flight.

77 FR 69742 - Airworthiness Directives; Cessna Aircraft Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-11-21

... Company (Cessna) Model 402C airplanes modified by Supplemental Type Certificate (STC) SA927NW and Model... Airworthiness Directives; Cessna Aircraft Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... new airworthiness directive (AD): 2012-23-01 Cessna Aircraft Company: Amendment 39-17257; Docket No...

Research on the F/A-18E/F Using a 22%-Dynamically-Scaled Drop Model

NASA Technical Reports Server (NTRS)

Croom, M.; Kenney, H.; Murri, D.; Lawson, K.

2000-01-01

Research on the F/A-18E/F configuration was conducted using a 22%-dynamically-scaled drop model to study flight dynamics in the subsonic regime. Several topics were investigated including longitudinal response, departure/spin resistance, developed spins and recoveries, and the failing leaf mode. Comparisons to full-scale flight test results were made and show the drop model strongly correlates to the airplane even under very dynamic conditions. The capability to use the drop model to expand on the information gained from full-scale flight testing is also discussed. Finally, a preliminary analysis of an unusual inclined spinning motion, dubbed the "cartwheel", is presented here for the first time.

Comparison of wind velocity in thunderstorms determined from measurements by a ground-based Doppler radar and an F-106B airplane

NASA Technical Reports Server (NTRS)

Usry, J. W.; Dunham, R. E., Jr.; Lee, J. T.

1985-01-01

As a part of the NASA Storm Hazards Program, the wind velocity in several thunderstorms was measured by an F-106B instrumented airplane and a ground-based Doppler radar. The results of five airplane penetrations of two storms in 1980 and six penetrations of one storm in 1981 are given. Comparisons were made between the radial wind velocity components measured by the radar and the airplane. The correlation coefficients for the 1980 data and part of the 1981 data were 0.88 and 0.78, respectively. It is suggested that larger values for these coefficients may be obtained by improving the experimental technique and in particular by slaving the radar to track the airplane during such tests.

Ground vibration test of F-16 airplane with initial decoupler pylon

NASA Technical Reports Server (NTRS)

Cazier, F. W., Jr.; Kehoe, M. W.

1984-01-01

A ground vibration test was conducted on an F-16 airplane loaded on each wing with a 370-gal tank mounted on a standard pylon, a GBU-8 store mounted on a decoupler pylon, and an AIM-9J missile mounted on a wing-tip launcher. The decoupler pylon is a passive wing/store flutter-suppression device. The test was conducted prior to initial flight tests to determine the modal frequencies, mode shapes, and structural damping coefficients. The data presented include frequency response plots, force effect plots, and limited mode shape data.

Properties of C4F7N–CO2 thermal plasmas: thermodynamic properties, transport coefficients and emission coefficients

NASA Astrophysics Data System (ADS)

Wu, Yi; Wang, Chunlin; Sun, Hao; Murphy, Anthony B.; Rong, Mingzhe; Yang, Fei; Chen, Zhexin; Niu, Chunpin; Wang, Xiaohua

2018-04-01

The thermophysical properties, including composition, thermodynamic properties, transport coefficients and net emission coefficients, of thermal plasmas formed from pure iso-C4 perfluoronitrile C4F7N and C4F7N–CO2 mixtures are calculated for temperatures from 300 to 30 000 K and pressures from 0.1 to 20 atm. These gases have received much attention as alternatives to SF6 for use in circuit breakers, due to the low global warming potential and good dielectric properties of C4F7N. Since the parameters of the large molecules formed in the dissociation of C4F7N are unavailable, the partition function and enthalpy of formation were calculated using computational chemistry methods. From the equilibrium composition calculations, it was found that when C4F7N is mixed with CO2, CO2 can capture C atoms from C4F7N, producing CO, since the system consisting of small molecules such as CF4 and CO has lower energy at room temperature. This is in agreement with previous experimental results, which show that CO dominates the decomposition products of C4F7N–CO2 mixtures; it could limit the repeated breaking performance of C4F7N. From the point of view of chemical stability, the mixing ratio of CO2 should therefore be chosen carefully. Through comparison with common arc quenching gases (including SF6, CF3I and C5F10O), it is found that for the temperature range for which electrical conductivity remains low, pure C4F7N has similar ρC p (product of mass density and specific heat) properties to SF6, and higher radiative emission coefficient, properties that are correlated with good arc extinguishing capability. For C4F7N–CO2 mixtures, the electrical conductivity is very close to that of SF6 while the ρC p peak at 7000 K caused by decomposition of CO implies inferior interruption capability to that of SF6. The calculated properties will be useful in arc simulations.

Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; Morris, Garland J.

1948-01-01

Tests were made of a 1/18-scale dynamically similar model of the Lockheed Constellation airplane to investigate its ditching characteristics and proper ditching technique. Scale-strength bottoms were used to reproduce probable damage to the fuselage. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and fuselage configuration were simulated. The behavior of the model was determined from visual observations, by recording the longitudinal decelerations, and by taking motion pictures of the ditchings. Data are presented in tabular form, sequence photographs, and time-history deceleration curves. It was concluded that the airplane should be ditched at a medium nose-high landing attitude with the landing flaps full down. The airplane will probably make a deep run with heavy spray and may even dive slightly. The fuselage will be damaged and leak substantially but in calm water probably will not flood rapidly. Maximum longitudinal decelerations in a calm-water ditching will be about 4g.

Predicted performance benefits of an adaptive digital engine control system of an F-15 airplane

NASA Technical Reports Server (NTRS)

Burcham, F. W., Jr.; Myers, L. P.; Ray, R. J.

1985-01-01

The highly integrated digital electronic control (HIDEC) program will demonstrate and evaluate the improvements in performance and mission effectiveness that result from integrating engine-airframe control systems. Currently this is accomplished on the NASA Ames Research Center's F-15 airplane. The two control modes used to implement the systems are an integrated flightpath management mode and in integrated adaptive engine control system (ADECS) mode. The ADECS mode is a highly integrated mode in which the airplane flight conditions, the resulting inlet distortion, and the available engine stall margin are continually computed. The excess stall margin is traded for thrust. The predicted increase in engine performance due to the ADECS mode is presented in this report.

High alpha feedback control for agile half-loop maneuvers of the F-18 airplane

NASA Technical Reports Server (NTRS)

Stalford, Harold

1988-01-01

A nonlinear feedback control law for the F/A-18 airplane that provides time-optimal or agile maneuvering of the half-loop maneuver at high angles of attack is given. The feedback control law was developed using the mathematical approach of singular perturbations, in which the control devices considered were conventional aerodynamic control surfaces and thrusting. The derived nonlinear control law was used to simulate F/A-18 half-loop maneuvers. The simulated results at Mach 0.6 and 0.9 compared well with pilot simulations conducted at NASA.

77 FR 16143 - Airworthiness Directives; The Boeing Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-03-20

...We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by a design review following a ground fire incident and reports of flammable fluid leaks from the wing leading edge area onto the engine exhaust area. This AD requires modifying the fluid drain path in the leading edge area of the wing. We are issuing this AD to prevent flammable fluid from leaking onto the engine exhaust nozzle, which could result in a fire.

Zoom-climb altitude maximization of the F-4C and F-15 aircraft for stratospheric sampling missions

NASA Technical Reports Server (NTRS)

Hague, D. S.; Merz, A. W.; Page, W. A.

1976-01-01

Some predictions indicate that byproducts of aerosol containers may lead to a modification of the ultraviolet-radiation shielding properties of the upper atmosphere. NASA currently monitors atmospheric properties to 70,000 feet using U-2 aircraft. Testing is needed at about 100,000 feet for adequate monitoring of possible aerosol contaminants during the next decade. To study this problem the F-4C and F-15 aircraft were analyzed to determine their maximum altitude ability in zoom-climb maneuvers. These trajectories must satisfy realistic dynamic pressure and Mach number constraints. Maximum altitudes obtained for the F4-C are above 90,000 feet, and for the F-15 above 100,000 feet. Sensitivities of the zoom-climb altitudes were found with respect to several variables including vehicle thrust, initial weight, stratospheric winds and the constraints. A final decision on aircraft selection must be based on mission modification costs and operational considerations balanced against their respective zoom altitude performance capabilities.

20. FOUR 4B17Gs BEING CONVERTED TO F9Cs. Photographic copy of ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

20. FOUR 4B-17Gs BEING CONVERTED TO F-9Cs. Photographic copy of historic photograph. Jan.-June 1947 OAMA (original print located at Ogden Air Logistics Center, Hill Air Force Base, Utah). Photographer unknown. - Hill Field, Airplane Repair Hangars No. 1-No. 4, 5875 Southgate Avenue, Layton, Davis County, UT

75 FR 66659 - Airworthiness Directives; Airbus Model A310 Series Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-10-29

.... Applicability (c) This AD applies to all Airbus Model A310-203, -204, -221, - 222, -304, -322, [[Page 66661... first. (ii) For A310-304, -322, -324, and -325 short range airplanes: Within 700 flight cycles or 1,900 flight hours after the effective date of this AD, whichever occurs first. (iii) For A310-304, -322, -324...

Analysis of rotary balance data for the F-15 airplane including the effect of conformal fuel tanks

NASA Technical Reports Server (NTRS)

Barnhart, B.

1982-01-01

F-15 rotary balance data was analyzed, and the influence of control deflections, Reynolds number and airplane components, i.e., body, wing, horizontal and vertical tails, as well as conformal tanks, on the aerodynamics up to 90 degrees angle of attack are discussed. Steady state spin mode predictions using these data are presented, which show excellent correlation with spin tunnel and flight test results. Generally, the data shows damped yawing moment slopes with rotation at all angles of attack, and good control effectiveness. Differences in the rotary aerodynamics due to the addition of conformal tanks are minimal. The small differences in the region of the flat spin do, however, indicate that the resulting spin mode would be slightly flatter and faster for a conformal tank equipped airplane. The addition of conformal tanks make the airplane more departure susceptible.

Design Oriented Structural Modeling for Airplane Conceptual Design Optimization

NASA Technical Reports Server (NTRS)

Livne, Eli

1999-01-01

The main goal for research conducted with the support of this grant was to develop design oriented structural optimization methods for the conceptual design of airplanes. Traditionally in conceptual design airframe weight is estimated based on statistical equations developed over years of fitting airplane weight data in data bases of similar existing air- planes. Utilization of such regression equations for the design of new airplanes can be justified only if the new air-planes use structural technology similar to the technology on the airplanes in those weight data bases. If any new structural technology is to be pursued or any new unconventional configurations designed the statistical weight equations cannot be used. In such cases any structural weight estimation must be based on rigorous "physics based" structural analysis and optimization of the airframes under consideration. Work under this grant progressed to explore airframe design-oriented structural optimization techniques along two lines of research: methods based on "fast" design oriented finite element technology and methods based on equivalent plate / equivalent shell models of airframes, in which the vehicle is modelled as an assembly of plate and shell components, each simulating a lifting surface or nacelle / fuselage pieces. Since response to changes in geometry are essential in conceptual design of airplanes, as well as the capability to optimize the shape itself, research supported by this grant sought to develop efficient techniques for parametrization of airplane shape and sensitivity analysis with respect to shape design variables. Towards the end of the grant period a prototype automated structural analysis code designed to work with the NASA Aircraft Synthesis conceptual design code ACS= was delivered to NASA Ames.

Laser-induced fluorescence studies of excited Sr reactions: II. Sr(3P1)+CH3F, C2H5F, C2H4F2

NASA Astrophysics Data System (ADS)

Teule, J. M.; Janssen, M. H. M.; Bulthuis, J.; Stolte, S.

1999-06-01

The vibrational and rotational energy distributions of ground state SrF(X 2Σ) formed in the reactions of electronically excited Sr(3P1) with methylfluoride, ethylfluoride, and 1,1-difluoroethane have been studied by laser-induced fluorescence. Although the reactions of ground state Sr with these reactants are exothermic, no SrF products are observed for those reactions in this study. The fraction of available energy disposed into the sum of rotational and vibrational energy of the SrF(X 2Σ) product is approximately the same for all three reactions, i.e., 40%. The reaction of Sr(3P1) with CH3F results in very low vibrational excitation in the SrF reaction product. The product vibration increases in going to C2H5F and C2H4F2. It is concluded that the alkyl group influences the energy disposal mechanism in these reactions, and some suggestions are given for a partial explanation of the observations.

Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE 317

NASA Technical Reports Server (NTRS)

Berman, Theodore

1948-01-01

An investigation of the spin and recovery characteristics of a scale model of the Grumman XF9F-2 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model in the flight loading were determined. The investigation also included spin-recovery-parachute, pilot-escape, and rudder-pedal- . force tests. The recovery characteristics of the model were satisfactory for all configurations tested. Spins for the normal control configuration were oscillatory in roll and yaw. Deflecting the leading-edge flaps or the dive brakes did not change the spin and recovery characteristics of the model noticeably. A 10.0-foot tail parachute or a 6.0-foot wing-tip parachute (drag coefficient of 0.75) was found to be effective for recoveries from demonstration spins. The rudder forces in the spin appeared to be within the capabilities of the pilot.

Ditching Tests of a 1/18-Scale Model of the Navy XP4M-1 Airplane in Langley Tank No. 2 and on an Outdoor Catapult, TED No. NACA 2362

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; Hoffman, Edward L.

1947-01-01

Tests with a dynamically similar model of the Navy XP4M-1 airplane were made to determine the best way to land the airplane in calm and rough water, to determine its probable ditching performance, and to determine practicable modifications which could be incorporated in the design of the airplane that would improve its ditching characteristics. The results were obtained by making visual observations, by recording longitudinal decelerations,a nd by taking motion pictures of the landings. A list of conclusions from the test results is included.

76 FR 71865 - Special Conditions: Gulfstream Aerospace Corporation, Model GVI Airplane; Windshield Coating in...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-11-21

...; Special Conditions No. 25-452-SC] Special Conditions: Gulfstream Aerospace Corporation, Model GVI Airplane... Aerospace Corporation Model GVI airplane. This airplane will have a novel or unusual design feature(s..., Gulfstream Aerospace Corporation (GAC) applied for an FAA type certificate for its new Model GVI passenger...

Thermodynamic assessment of the LiF-ThF4-PuF3-UF4 system

NASA Astrophysics Data System (ADS)

Capelli, E.; Beneš, O.; Konings, R. J. M.

2015-07-01

The LiF-ThF4-PuF3-UF4 system is the reference salt mixture considered for the Molten Salt Fast Reactor (MSFR) concept started with PuF3. In order to obtain the complete thermodynamic description of this quaternary system, two binary systems (ThF4-PuF3 and UF4-PuF3) and two ternary systems (LiF-ThF4-PuF3 and LiF-UF4-PuF3) have been assessed for the first time. The similarities between CeF3/PuF3 and ThF4/UF4 compounds have been taken into account for the presented optimization as well as in the experimental measurements performed, which have confirmed the temperatures predicted by the model. Moreover, the experimental results and the thermodynamic database developed have been used to identify potential compositions for the MSFR fuel and to evaluate the influence of partial substitution of ThF4 by UF4 in the salt.

78 FR 18925 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-03-28

...-0212; Directorate Identifier 2012-NM-116-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes...: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-223F, -223, -321...., Monday through Friday, except Federal holidays. For Airbus service information identified in this...

78 FR 65190 - Airworthiness Directives; Bombardier, Inc. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-10-31

... altitude indications, and consequent loss of control of the airplane. DATES: This AD becomes effective... result in erroneous airspeed and altitude indications [and consequent loss of control of the airplane... indications, and consequent loss of control of the airplane. (f) Compliance You are responsible for having the...

An Evaluation of Very Large Airplanes and Alternative Fuels: Executive Summary

DTIC Science & Technology

1976-12-01

the AIAA/ SAE Eleventh Prop~ilsion Conference, Anaheim, Cal., September 1975. i 33 Rom, F. E., "Nuclear-Powered Airplane," Technology Heview, December...Department of Defense Directive No. 4140 -43, December 5, 1975. Scarbrough, D. R., C-5B and Austere C-5 Data Package, Lockheed-Georgia Co., Operations

Simulation model of a twin-tail, high performance airplane

NASA Technical Reports Server (NTRS)

Buttrill, Carey S.; Arbuckle, P. Douglas; Hoffler, Keith D.

1992-01-01

The mathematical model and associated computer program to simulate a twin-tailed high performance fighter airplane (McDonnell Douglas F/A-18) are described. The simulation program is written in the Advanced Continuous Simulation Language. The simulation math model includes the nonlinear six degree-of-freedom rigid-body equations, an engine model, sensors, and first order actuators with rate and position limiting. A simplified form of the F/A-18 digital control laws (version 8.3.3) are implemented. The simulated control law includes only inner loop augmentation in the up and away flight mode. The aerodynamic forces and moments are calculated from a wind-tunnel-derived database using table look-ups with linear interpolation. The aerodynamic database has an angle-of-attack range of -10 to +90 and a sideslip range of -20 to +20 degrees. The effects of elastic deformation are incorporated in a quasi-static-elastic manner. Elastic degrees of freedom are not actively simulated. In the engine model, the throttle-commanded steady-state thrust level and the dynamic response characteristics of the engine are based on airflow rate as determined from a table look-up. Afterburner dynamics are switched in at a threshold based on the engine airflow and commanded thrust.

Biotransformation of ginsenosides F4 and Rg6 in zebrafish.

PubMed

Shen, Wen-Wen; Zhang, Hai-Xia; Qiu, Shou-Bei; Wei, Ying-Jie; Zhu, Fen-Xia; Wang, Jing; Wang, Dan-Dan; Jia, Xiao-Bin; Tang, Dao-Quan; Chen, Bin

2017-03-28

Ginsenosides F 4 and Rg 6 (GF 4 and GRg 6 ), two main active components of steamed notoginseng or red ginseng, are dehydrated disaccharide saponins. In this work, biotransformation of ginsenosides F 4 and Rg 6 in zebrafish was investigated by qualitatively identifying their metabolites and then proposing their possible metabolic pathways. The prediction of possible metabolism of ginsenosides F 4 and Rg 6 using zebrafish model which can effectively simulate existing mammals model was early and quickly performed. Metabolites of ginsenosides F 4 and Rg 6 after exposing to zebrafish for 24 h were identified by Ultraperformance Liquid Chromatography/Quadrupole-Time-of-Flight Mass Spectrometry. A total of 8 and 6 metabolites of ginsenosides F 4 and Rg 6 were identified in zebrafish, respectively. Of these, 7 and 5, including M1, M3-M5, M7-M9 and N1 (N5), N2, N4 (N9), N7-N8 were reported for the first time as far as we know. The mechanisms of their biotransformation involved were further deduced to be desugarization, glucuronidation, sulfation, dehydroxylation, loss of C-17 and/or C-23 residue pathways. It was concluded that loss of rhamnose at position C-6 and glucuronidation at position C-3 in zebrafish were considered as the main physiologic and metabolic processes of ginsenosides F 4 and ginsenosides Rg 6 , respectively.

An Investigation of the Drag Characteristics of a Tailless Delta-Wing Airplane in Flight, Including Comparison with Wind-Tunnel Data

NASA Technical Reports Server (NTRS)

Rolls, L. Stewart; Wingrove, Rodney C.

1958-01-01

A series of flight tests were conducted to determine the lift and drag characteristics of an F4D-1 airplane over a Mach number range of 0.80 to 1.10 at an altitude of 40,000 feet. Apparently satisfactory agreement was obtained between the flight data and results from wind-tunnel tests of an 0.055-scale model of the airplane. Further tests show the apparent agreement was a consequence of the altitude at which the first tests were made.

Cyclo-octafluorobutane (PFC-318, c-C4F8) in the global atmosphere

NASA Astrophysics Data System (ADS)

Muhle, J.; Vollmer, M. K.; Ivy, D. J.; Fraser, P.; Arnold, T.; Harth, C. M.; Salameh, P.; O'Doherty, S.; Young, D.; Steele, P.; Krummel, P. B.; Leist, M.; Rhee, T. S.; Schmidbauer, N.; Lunder, C.; Kim, J.; Kim, K.; Reimann, S.; Simmonds, P.; Prinn, R. G.; Weiss, R. F.

2011-12-01

The perfluorocarbon (PFC) cyclo-octafluorobutane (PFC-318, c-C4F8) is a very long-lived (up to 3,200 years) and potent greenhouse gas (100-year global warming potential up to 10,300) with a wide range of industrial uses. We present an update of our PFC-318 archived air and in situ measurements from remote and urban AGAGE (Advanced Global Atmospheric Gases Experiment) sites and affiliated stations in both hemispheres. Most importantly, we have significantly improved our Southern Hemisphere (SH) data density by measuring the Cape Grim Air Archive (1970s-2010). Combined with our previously presented measurements of archived Northern Hemisphere (NH) flasks (1973-2009), we provide thirty year spanning records for both hemispheres. We have also further extended our in situ records by continuing our measurements at all remote stations, with the longest hemispheric records starting in November 2007 at Jungfraujoch (NH) and in June 2010 at Cape Grim (SH). We compare our data with those of Oram (1999) and Oram et al. (2011), who focus on SH data alone, and with other previous data sets. From our measurements, we derive emission estimates using a chemical transport model and inverse method, and compare our results to previous measurement based emission estimates (top-down) and to the EDGAR emission database (bottom-up). As stated previously (Mühle et al., 2010), we find emissions of ~1 Gg/yr in recent years while EDGAR estimates only 0.02 Gg/yr for 2005, similar to what Oram et al. (2011) find. We conclude that PFC-318 is the third most important PFC in terms of abundance and CO2-equivalent emissions. We continue to observe mostly baseline concentrations at remote AGAGE stations and urban sites in the USA, Europe, and Australia, in contrast to frequent pollution episodes measured at sites in East Asia, indicating significant regional emissions in East Asia, as found by Saito et al. (2010). EDGAR, Emission Database for Global Atmospheric Research, release version 4.1. http

North American Aviation F-100 in the Ames 40x80 Foot Wind Tunnel.

NASA Image and Video Library

1959-02-12

North American F-100-F airplane, equipped with thrust reversers, full scale wind tunnel test. 3/4 front view of F-100-F airplane with North American Aviation thrust reverser. On standard 40x80 struts landing gear down. Mark Kelly, branch chief in photo.

76 FR 36387 - Airworthiness Directives; Airbus Model A300 Series Airplanes; Model A310 Series Airplanes; and...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-06-22

... Original August 12, 2010. A300-29-6064 Original August 12, 2010. A310-29-2099, including Appendix 01... (for Model A300- Original....... August 12, 2010. 600 airplanes). A310-29-2099 (for Model A310 Original..., 2010. A310-29-2099 Original........ August 12, 2010. A310-29-2100 Original........ August 12, 2010...

77 FR 24831 - Airworthiness Directives; The Boeing Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-04-26

... Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes equipped with analog transient suppression devices (ATSDs) installed in accordance with Supplemental Type Certificate ST00146BO. This AD was...

78 FR 47549 - Airworthiness Directives; The Boeing Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-06

... Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... to certain The Boeing Company Model 737-200, -200C, -300, and -400 series airplanes. AD 2000-06-13 R1..., adds inspections and related investigative and corrective actions, revises certain inspection types...

Measurement of Flying Qualities of a Dehavilland Mosquito F-8 Airplane (AAF No. 43-334960) I: Lateral and Directional Stability and Control Characteristics

NASA Technical Reports Server (NTRS)

Gray, W.E.; Talmage, D.B.; Crane, H.L.

1945-01-01

The data presented have no bearing on performance characteristics of airplane, which were considered exceptionally good in previous tests. Some of the undesirable features of lateral and directional stability and control characteristics of the F-8 are listed. Directional stability, with rudder fixed, did not sufficiently restrict aileron yaw; rudder control was inadequate during take-off and landing, and was insufficient to fly airplane with one engine; in clean condition, power of ailerons was slightly below minimum value specified; it was difficult to trim airplane in rough air.

77 FR 37797 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-25

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-200 series airplanes; Airbus Model A330-200 Freighter series airplanes; Airbus Model A330-300 series airplanes; Airbus Model A340-200 series airplanes; and Airbus Model A340-300 series...

Kinetic Modelling of Infection Tracers [18F]FDG, [68Ga]Ga-Citrate, [11C]Methionine, and [11C]Donepezil in a Porcine Osteomyelitis Model.

PubMed

Jødal, Lars; Jensen, Svend B; Nielsen, Ole L; Afzelius, Pia; Borghammer, Per; Alstrup, Aage K O; Hansen, Søren B

2017-01-01

Positron emission tomography (PET) is increasingly applied for infection imaging using [ 18 F]FDG as tracer, but uptake is unspecific. The present study compares the kinetics of [ 18 F]FDG and three other PET tracers with relevance for infection imaging. A juvenile porcine osteomyelitis model was used. Eleven pigs underwent PET/CT with 60-minute dynamic PET imaging of [ 18 F]FDG, [ 68 Ga]Ga-citrate, [ 11 C]methionine, and/or [ 11 C]donepezil, along with blood sampling. For infectious lesions, kinetic modelling with one- and two-tissue-compartment models was conducted for each tracer. Irreversible uptake was found for [ 18 F]FDG and [ 68 Ga]Ga-citrate; reversible uptake was found for [ 11 C]methionine (two-tissue model) and [ 11 C]donepezil (one-tissue model). The uptake rate for [ 68 Ga]Ga-citrate was slow and diffusion-limited. For the other tracers, the uptake rate was primarily determined by perfusion (flow-limited uptake). Net uptake rate for [ 18 F]FDG and distribution volume for [ 11 C]methionine were significantly higher for infectious lesions than for correspondingly noninfected tissue. For [ 11 C]donepezil in pigs, labelled metabolite products appeared to be important for the analysis. The kinetics of the four studied tracers in infection was characterized. For clinical applications, [ 18 F]FDG remains the first-choice PET tracer. [ 11 C]methionine may have a potential for detecting soft tissue infections. [ 68 Ga]Ga-citrate and [ 11 C]donepezil were not found useful for imaging of osteomyelitis.

C_7F_16/He rf plasma CVD of a-C:F films

NASA Astrophysics Data System (ADS)

Hokoi, Kohji; Akazawa, Masamichi; Sugawara, Hirotake; Sakai, Yosuke

2000-10-01

Fluorinated carbon is one of the most promissing materials with low dielectric constant ɛr and high dielectric strength V_b. We have deposited a-C:F films by rf (13.56 MHz) plasma enhanced CVD method using the following liquid materials; C_7F_16, (C_3F_7)_3N/(C_4F_9)_3N and C_8F_18/C_8F_16O.(C. P. Lungu et al.), Jpn. J. Appl. Phys. 38, L1544--6 (1999) The films showed ɛr values in a range of 1.9--3.0 and V_b>2 MV/cm. In this work, we added He (3 Pa) to C_7F_16 (60 Pa) plasmas, expecting that He atoms in the metastable excited state (He*, 19.8 eV) would promote C_7F_16 decomposition in gas phase or activation of the film surface during deposition. The films with the thickness up to 2300 nm were deposited on unheated Si substrate with an rf power of 100 W. The deposition rate derived from the film thickness measurement by SEM and ellipsometry was about 230 nm/min. This value is roughly two times as large as that of the films deposited by C_7F_16 (60 Pa) plasmas without He. We discuss the mechanism that leads to such a significant increase in the deposition rate.

Wind-tunnel tests of a 1/4 scale model of the Bell XS-1 transonic airplane. 1: Longitudinal stability and control characteristics

NASA Technical Reports Server (NTRS)

Donlan, C. J.; Kemp, W. B., Jr.; Polhamus, E. C.

1976-01-01

A 1/4 scale model of the Bell XS-1 transonic aircraft was tested in the Langley 300 mile-per-hour 7 by 10 foot tunnel to determine its low speed longitudinal stability and control characteristics. Pertinent longitudinal flying qualities expected of the XS-1 research airplane were estimated from the results of these tests including the effects of compressibility likely to be encountered at speeds below the force break. It appears that the static longitudinal stability and elevator control power will be adequate, but that the elevator control force gradient in steady flight will be undesirably low for all configurations. It is suggested that a centering spring be incorporated in the elevator control system of the airplane in order to increase the control force gradient in steady flight and in maneuvers.

Phase 2 program on ground test of refanned JT8D turbofan engines and nacelles for the 727 airplane. Volume 4: Airplane evaluation and analysis

NASA Technical Reports Server (NTRS)

1975-01-01

The retrofit of JT8D-109 (refan) engines are evaluated on a 727-200 airplane in terms of airworthiness, performance, and noise. Design of certifiable hardware, manufacture, and ground testing of the essential nacelle components is included along with analysis of the certifiable airplane design to ensure airworthiness compliance and to predict the in-flight performance and noise characteristics of the modified airplane. The analyses confirm that the 727 refan airplane is certifiable. The refan airplane range would be 15% less that of the baseline airplane and block fuel would be increased by 1.5% to 3%. However, with this particular 727-200 model, with a brake release gross weight of 172,500 lb (78,245 kg), it is possible to operate the airplane (with minor structural modifications) at higher gross weights and increase the range up to 15% over the 727-200 (baseline) airplane. The refan airplane FAR Part 36 noise levels would be 6 to 8 EPNdB (effective perceived noise in decibels) below the baseline. Noise footprint studies showed that approach noise contour areas are small compared to takeoff areas. The 727 refan realizes a 68% to 83% reduction in annoyance-weighted area when compared to the 727-200 over a range of gross weights and operational procedures.

75 FR 20265 - Airworthiness Directives; Liberty Aerospace Incorporated Model XL-2 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-04-19

... Airworthiness Directives; Liberty Aerospace Incorporated Model XL-2 Airplanes AGENCY: Federal Aviation...-08- 05, which applies to certain Liberty Aerospace Incorporated Model XL-2 airplanes. AD 2009-08-05...), the Director of the Federal Register approved the incorporation by reference of Liberty Aerospace, Inc...

77 FR 70941 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Interaction of Systems and Structures

Federal Register 2010, 2011, 2012, 2013, 2014

2012-11-28

... primary structure is metal with composite empennage and control surfaces. The Model EMB-550 airplane is...., Model EMB-550 Airplane; Interaction of Systems and Structures AGENCY: Federal Aviation Administration... conditions for the Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design...

77 FR 26998 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-05-08

...-0428; Directorate Identifier 2011-NM-078-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes...: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-243, -243F, -342..., between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information...

Comparison of (11)C-4'-thiothymidine, (11)C-methionine, and (18)F-FDG PET/CT for the detection of active lesions of multiple myeloma.

PubMed

Okasaki, Momoko; Kubota, Kazuo; Minamimoto, Ryogo; Miyata, Yoko; Morooka, Miyako; Ito, Kimiteru; Ishiwata, Kiichi; Toyohara, Jun; Inoue, Tomio; Hirai, Risen; Hagiwara, Shotaro; Miwa, Akiyoshi

2015-04-01

The aims of this study were to evaluate the possibility of using (11)C-methionine ((11)C-MET) and (11)C-4'-thiothymidine ((11)C-4DST) whole-body PET/CT for the imaging of amino acid metabolism and DNA synthesis, respectively, when searching for bone marrow involvement in patients with multiple myeloma (MM) and to compare these findings with those for (18)F-FDG PET/CT and aspiration cytology. A total of 64 patients with MM, solitary plasmacytoma, monoclonal gammopathy of undetermined significance, or an unspecified diagnosis were prospectively enrolled. All the patients underwent three whole-body PET/CT examinations within a period of 1 week. First, the tracer accumulation was visually evaluated as positive, equivocal, or negative for 55 focal lytic lesions visualized using CT in 24 patients. Second, the percentages of marrow plasma cells as calculated using a bone marrow aspiration smear and tracer accumulation were evaluated in the posterior iliac crests of 36 patients. Among the 55 lytic lesions, the (11)C-MET and (11)C-4DST findings tended to reveal more positive findings than the (18)F-FDG findings. Based on the standard criteria for the diagnosis of active myeloma using the percentage of marrow plasma cells, significant differences were found between the (18)F-FDG and (11)C-MET findings and between the (18)F-FDG and (11)C-4DST findings, but no significant difference was observed between the (11)C-MET and (11)C-4DST findings. The addition of (11)C-MET and (11)C-4DST to (18)F-FDG when performing PET/CT enabled clearer evaluations of equivocal lesions. Based on cytological diagnostic criteria, (11)C-MET and (11)C-4DST were more sensitive than (18)F-FDG for the detection of active lesions. (11)C-MET and (11)C-4DST were more useful than (18)F-FDG for the detection of active lesions, especially during the early stage of disease.

Calculated Drag of an Aerial Refueling Assembly Through Airplane Performance Analysis

NASA Technical Reports Server (NTRS)

Vachon, Michael Jacob; Ray, Ronald J.

2004-01-01

The aerodynamic drag of an aerial refueling assembly was calculated during the Automated Aerial Refueling project at the NASA Dryden Flight Research Center. An F/A-18A airplane was specially instrumented to obtain accurate fuel flow measurements and to determine engine thrust. A standard Navy air refueling store with a retractable refueling hose and paradrogue was mounted to the centerline pylon of the F/A-18A airplane. As the paradrogue assembly was deployed and stowed, changes in the calculated thrust of the airplane occurred and were equated to changes in vehicle drag. These drag changes were attributable to the drag of the paradrogue assembly. The drag of the paradrogue assembly was determined to range from 200 to 450 lbf at airspeeds from 170 to 250 KIAS. Analysis of the drag data resulted in a single drag coefficient of 0.0056 for the paradrogue assembly that adequately matched the calculated drag for all flight conditions. The drag relief provided to the tanker airplane when a receiver airplane engaged the paradrogue is also documented from 35 to 270 lbf at the various flight conditions tested. The results support the development of accurate aerodynamic models to be used in refueling simulations and control laws for fully autonomous refueling.

Report on Tests of Metal Model Propellers in Combination with a Model VE-7 Airplane

NASA Technical Reports Server (NTRS)

Lesley, E P

1926-01-01

This report, prepared at the request of the NACA, describes tests of three metal model propellers, in a free air stream and in front of a model of a VE-7 airplane. The effect of introducing the model airplane is shown to be an increase in thrust and power coefficients and efficiency at small slip, and a decrease in the same at large slip.

Ditching Tests of a 1/20-Scale Model of the Northrop B-35 Airplane

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.

1948-01-01

Tests of a 1/20-scale dynamically similar model of the Northrop B-35 airplane were made to study its ditching characteristics. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds,and conditions of damage were simulated during the investigation. The ditching characteristics were determined by visual observation and from motion-picture records and time-history acceleration records. Both longitudinal and lateral accelerations were measured. Results are given in tabular form and time-history acceleration curves and sequence photographs are presented. Conclusions based on the model investigation are as follows: 1. The best ditching of the B-35 airplane probably can be made by contacting the water in a near normal landing attitude of about 9 deg with the landing flaps full down so as to have a low horizontal speed. 2. The airplane usually will turn or yaw but the motion will not be violent. The maximum lateral acceleration will be about 2g. 3. If the airplane does not turn or yaw immediately after landing, it probably will trim up and then make a smooth run or porpoise slightly. The maximum longitudinal decelerations that will be encountered are about 6g or 7g. 4. Although the decelerations are not indicated to be especially large, the construction of the airplane is such that extensive damage is to be expected, and it probably will be difficult to find ditching stations where crew members can adequately brace themselves and be reasonably sure of avoiding a large inrush of water.

75 FR 57664 - Airworthiness Directives; G ROB-WERKE Model G120A Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-09-22

... Airworthiness Directives; G ROB-WERKE Model G120A Airplanes AGENCY: Federal Aviation Administration (FAA), DOT.... The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113..., PART B, dated May 18, 2010. (g) You may at any time complete GROB Aircraft AG Repair Instruction No. RI...

78 FR 14005 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: Pitch and...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-03-04

...-1211; Special Conditions No. 25-486-SC] Special Conditions: Embraer S.A., Model EMB-550 Airplanes... Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design feature associated...: Background On May 14, 2009, Embraer S.A. applied for a type certificate for their new Model EMB-550 airplane...

76 FR 63177 - Airworthiness Directives; Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-12

... available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2011... B4-2C Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT...

76 FR 27239 - Airworthiness Directives; Cessna Aircraft Company (Cessna) Model 172 Airplanes Modified by...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-05-11

... Airworthiness Directives; Cessna Aircraft Company (Cessna) Model 172 Airplanes Modified by Supplemental Type... months for Cessna Aircraft Company (Cessna) Model 172 Airplanes modified by Supplemental Type Certificate...

Flight evaluation of an extended engine life mode on an F-15 airplane

NASA Technical Reports Server (NTRS)

Myers, Lawrence P.; Conners, Timothy R.

1992-01-01

An integrated flight and propulsion control system designed to reduce the rate of engine deterioration was developed and evaluated in flight on the NASA Dryden F-15 research aircraft. The extended engine life mode increases engine pressure ratio while reducing engine airflow to lower the turbine temperature at constant thrust. The engine pressure ratio uptrim is modulated in real time based on airplane maneuver requirements, flight conditions, and engine information. The extended engine life mode logic performed well, significantly reducing turbine operating temperature. Reductions in fan turbine inlet temperature of up to 80 F were obtained at intermediate power and up to 170 F at maximum augmented power with no appreciable loss in thrust. A secondary benefit was the considerable reduction in thrust-specific fuel consumption. The success of the extended engine life mode is one example of the advantages gained from integrating aircraft flight and propulsion control systems.

Dynamic Ground Effect for a Cranked Arrow Wing Airplane

NASA Technical Reports Server (NTRS)

Curry, Robert E.

1997-01-01

Flight-determined ground effect characteristics for an F-16XL airplane are presented and correlated with wind tunnel predictions and similar flight results from other aircraft. Maneuvers were conducted at a variety of flightpath angles. Conventional ground effect flight test methods were used, with the exception that space positioning data were obtained using the differential global positioning system (DGPS). Accuracy of the DGPS was similar to that of optical tracking methods, but it was operationally more attractive. The dynamic flight determined lift and drag coefficient increments were measurably lower than steady-state wind-tunnel predictions. This relationship is consistent with the results of other aircraft for which similar data are available. Trends in the flight measured lift increments caused by ground effect as a function of flightpath angle were evident but weakly correlated. An engineering model of dynamic ground effect was developed based on linear aerodynamic theory and super-positioning of flows. This model was applied to the F-16XL data set and to previously published data for an F-15 airplane. In both cases, the model provided an engineering estimate of the ratio between the steady-state and dynamic data sets.

Time-History Data of Maneuvers Performed by an F-86A Airplane During Squadron Operational Training

NASA Technical Reports Server (NTRS)

Henderson, Campbell; Thornton, James; Mayo, Alton

1952-01-01

Preliminary results of one phase of a control-motion study program are presented in the form of plots of load factor.and angular acceleration against indicated airspeed and of time histories of several measured quantities. The results were obtained from 197 maneuvers performed by an F-86A jet-fighter airplane during normal squadron operational training. Most of the tactical maneuver8 of which the F-86A is capable were performed at pressure altitudes ranging from 0 to 32,000 feet and at indicated airspeeds ranging from 95 to 650 miles per hour.

Joint Research Centre Copernicus Climate Change Service (C3S) Fitness-for-Purpose (F4P) Platform

NASA Astrophysics Data System (ADS)

Gobron, N.; Adams, J. S.; Cappucci, F.; Lanconelli, C.; Mota, B.; Melin, F.

2016-08-01

This paper presents the concept and first results of the Copernicus Climate Change Service Fitness-for-Purpose (C3S F4P) project. The main goal aims at evaluating the efficiency and overall performance of the service, mainly with regard to users information needs and high level requirements. This project will also assess the fitness- for-purpose of the C3S with a specific emphasis on the needs of European Union (EU) Policies and translate these recommendations into programmatic and technical requirements. The C3S Climate Data Records (CDS) include various Essential Climate Variables (ECVs) that are derived from space sensors, including from Copernicus Sentinels sensors. One module of the F4P platform focuses on the benchmarking of data sets and algorithms, in addition to radiative transfer models used towards understanding potential discrepancies between CDS records. Methods and preliminary results of the benchmark platform are presented in this contribution.

Calculations of total electron-impact ionization cross sections for Fluoroketone C5F10O and Fluoronitrile C4F7N using modified Deutsch-Märk formula

NASA Astrophysics Data System (ADS)

Xiong, Jiayu; Li, Xingwen; Wu, Jian; Guo, Xiaoxue; Zhao, Hu

2017-11-01

Both fluoroketone C5F10O and fluoronitrile C4F7N are promising substitute gases for SF6. The electron-impact ionization cross sections for these two gases are calculated using the Deutsch-Märk (DM) formula and its modified method. The necessary molecular geometry optimization and electron population were determined by ab initio calculation, which was performed with quantum chemistry code. The level of calculation, including the theoretical method and basis-set, are carefully determined. To eliminate the drawbacks of the DM formula, a modified DM formula is set in this paper. The modified DM formula, of which the weighting factors are changed, has a better agreement with the experimental data on both the peak and shape of the cross-section curves. The results calculated by DM formula and modified DM formula are given as references to fill in gaps in further research into C5F10O and C4F7N.

Ditching Investigation of a 1/15-Scale Model of the Convair-Liner Airplane

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; Thompson, William C.

1950-01-01

A ditching investigation of a model of the Convair-Liner airplane was made to observe the behavior and determine the safest procedure for making an emergency water landing. The ditching model was designed and constructed by the National Advisory Committee for Aeronautics. Design information on the airplane was furnished by the Consolidated Vultee Aircraft Corporation. A three-view drawing of the airplane is shown. The investigation was made in calm water at the Langley tank no. 2 monorail.

75 FR 8554 - Airworthiness Directives; The Boeing Company Model 747-100, -200B, and -200F Series Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-02-25

... AD results from reports of fatigue cracking on modified airplanes. We are proposing this AD to detect and correct fatigue cracking in the longitudinal lap joints of the fuselage lower lobe, which could... reports of incidents involving fatigue cracking and corrosion of transport category airplanes that are...

Simulator study of stall/post-stall characteristics of a fighter airplane with relaxed longitudinal static stability. [F-16

NASA Technical Reports Server (NTRS)

Nguyen, L. T.; Ogburn, M. E.; Gilbert, W. P.; Kibler, K. S.; Brown, P. W.; Deal, P. L.

1979-01-01

A real-time piloted simulation was conducted to evaluate the high-angle-of-attack characteristics of a fighter configuration based on wind-tunnel testing of the F-16, with particular emphasis on the effects of various levels of relaxed longitudinal static stability. The aerodynamic data used in the simulation was conducted on the Langley differential maneuvering simulator, and the evaluation involved representative low-speed combat maneuvering. Results of the investigation show that the airplane with the basic control system was resistant to the classical yaw departure; however, it was susceptible to pitch departures induced by inertia coupling during rapid, large-amplitude rolls at low airspeed. The airplane also exhibited a deep-stall trim which could be flown into and from which it was difficult to recover. Control-system modifications were developed which greatly decreased the airplane susceptibility to the inertia-coupling departure and which provided a reliable means for recovering from the deep stall.

77 FR 19071 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-03-30

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... directive (AD) for certain Airbus Model A330-200, A330-300, A340-500, and A340-600 series airplanes. This AD...: During structural part assembly in Airbus production line, some nuts Part Number (P/N) ASNA2531-4 were...

78 FR 76248 - Special Conditions: Airbus, Model A350-900 Series Airplane; Side Stick Controller

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-17

... control columns and wheels. This kind of controller is designed for only one-hand operation. The... same subject: For the Airbus Model A350-900 series airplane equipped with stick controls designed for... Airbus Model A350-900 series airplanes. These airplanes will have a novel or unusual design feature...

Free-Spinning-Tunnel Investigation of a 0.034-Scale Model of the Production Version of the Chance Vought F7U-3 Airplane, TED No. NACA AD 3103

NASA Technical Reports Server (NTRS)

Klinar, Walter J.; Healy, Frederick M.

1955-01-01

An investigation of a 0.034-scale model of the production version of the Chance Vought F7U-3 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The inverted and erect spin and recovery characteristics of the model were determined for the combat loading with the model in the clean condition and the effect of extending slats was investigated. A brief investigation of pilot ejection was also performed. The results indicate that the inverted spin-recovery characteristics of the airplane will be satisfactory by full rudder reversal. If the rudders can only be neutralized because of high pedal forces in the inverted spins, satisfactory recovery will be obtained if the auxiliary rudders can be moved to neutral or against the spin provided the stick is held full forward. Optimum control technique for satisfactory recovery from erect spins will be full rudder reversal in conjunction with aileron movement to full with the spin (stick right in a right spin). Extension of the slats will have a slightly adverse effect on recoveries from (1 inverted spins but will have a favorable effect on recoveries from erect spins. The results of brief tests indicate that if a pilot is ejected during a spin while a spin-recovery parachute is extended and fully inflated, he will probably clear the tail parachute.

Ditching Tests with a 1/16-Size Model of the Navy XP2V-1 Airplane at the Langley Tank No. 2 Monorail

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; Tarshis, Robert P.

1947-01-01

Tests were made with a 1/16 size dynamically similar model of the Navy XP2V-1 airplane to study its performance when ditched. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated. The performance of the node1 was determined and recorded from visual observations, by recording time histories of the longitudinal decelerations, and by taking motion pictures of the ditchings From the results of the tests with the model the following conclusions were drawn: 1. The airplane should be ditched at the normal landing attitude. The flaps should be fully extended to obtain the lowest possible landing speed; 2. Extensive damage will occur in a ditching and the airplane probably will dive violently after a run of about 2 fuselage lengths. Maximum longitudinal decelerations up to about 4g will be encountered; and 3. If a trapezoidal hydroflap 4 feet by 2 feet by 1 foot is attached to the airplane at station 192.4, diving will be prevented and the airplane will probably porpoise in a run of about 4 fuselage lengths with a maximum longitudinal deceleration of less than 3.5g.

75 FR 78594 - Airworthiness Directives; The Boeing Company Model 777-200 Series Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-16

... which a T/R is installed with a design change known as ``Commonality T/R,'' which is common to Model 777... Airworthiness Directives; The Boeing Company Model 777-200 Series Airplanes AGENCY: Federal Aviation... certain Model 777-200 series airplanes. This AD requires installing a new insulation blanket on the latch...

78 FR 31835 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Landing Pitchover Condition

Federal Register 2010, 2011, 2012, 2013, 2014

2013-05-28

... Model EMB-550 airplane. The Model EMB-550 airplane is the first of a new family of jet airplanes... the fuel vent and exhaust emission requirements of 14 CFR part 34 and the noise certification... condition from which ultimate loads must also be determined. Loads must be determined for critical fuel and...

Flight Test of the F/A-18 Active Aeroelastic Wing Airplane

NASA Technical Reports Server (NTRS)

Clarke, Robert; Allen, Michael J.; Dibley, Ryan P.; Gera, Joseph; Hodgkinson, John

2005-01-01

Successful flight-testing of the Active Aeroelastic Wing airplane was completed in March 2005. This program, which started in 1996, was a joint activity sponsored by NASA, Air Force Research Laboratory, and industry contractors. The test program contained two flight test phases conducted in early 2003 and early 2005. During the first phase of flight test, aerodynamic models and load models of the wing control surfaces and wing structure were developed. Design teams built new research control laws for the Active Aeroelastic Wing airplane using these flight-validated models; and throughout the final phase of flight test, these new control laws were demonstrated. The control laws were designed to optimize strategies for moving the wing control surfaces to maximize roll rates in the transonic and supersonic flight regimes. Control surface hinge moments and wing loads were constrained to remain within hydraulic and load limits. This paper describes briefly the flight control system architecture as well as the design approach used by Active Aeroelastic Wing project engineers to develop flight control system gains. Additionally, this paper presents flight test techniques and comparison between flight test results and predictions.

Measurement of Small Molecular Dopant F4TCNQ and C 60F 36 Diffusion in Organic Bilayer Architectures

DOE Office of Scientific and Technical Information (OSTI.GOV)

Li, Jun; Rochester, Chris W.; Jacobs, Ian E.

2015-12-03

The diffusion of molecules through and between organic layers is a serious stability concern in organic electronic devices. In this paper, the temperature-dependent diffusion of molecular dopants through small molecule hole transport layers is observed. Specifically we investigate bilayer stacks of small molecules used for hole transport (MeO-TPD) and p-type dopants (F4TCNQ and C 60F 36) used in hole injection layers for organic light emitting diodes and hole collection electrodes for organic photovoltaics. With the use of absorbance spectroscopy, photoluminescence spectroscopy, neutron reflectometry, and near-edge X-ray absorption fine structure spectroscopy, we are able to obtain a comprehensive picture of themore » diffusion of fluorinated small molecules through MeO-TPD layers. F4TCNQ spontaneously diffuses into the MeO-TPD material even at room temperature, while C 60F 36, a much bulkier molecule, is shown to have a substantially higher morphological stability. Finally, this study highlights that the differences in size/geometry and thermal properties of small molecular dopants can have a significant impact on their diffusion in organic device architectures.« less

Airstart performance of a digital electronic engine control system in an F-15 airplane

NASA Technical Reports Server (NTRS)

Licata, S. J.; Burcham, F. W., Jr.

1983-01-01

The airstart performance of the F100 engine equipped with a digital electronic engine control (DEEC) system was evaluated in an F-15 airplane. The DEEC system incorporates closed-loop airstart logic for improved capability. Spooldown and jet fuel starter-assisted airstarts were made over a range of airspeeds and altitudes. All jet fuel starter-assisted airstarts were successful, with airstart time varying from 35 to 60 sec. All spooldown airstarts at airspeeds of 200 knots and higher were successful; airstart times ranged from 45 sec at 250 knots to 135 sec at 200 knots. The effects of altitude on airstart success and time were small. The flight results agreed closely with previous altitude facility test results. The DEEC system provided successful airstarts at airspeeds at least 50 knots lower than the standard F100 engine control system.

Application of trajectory optimization techniques to upper atmosphere sampling flights using the F4-C Phantom aircraft

NASA Technical Reports Server (NTRS)

Hague, D. S.; Merz, A. W.

1975-01-01

Altitude potential of an off-the-shelf F4-C aircraft is examined. It is shown that the standard F4-C has a maximum altitude capability in the region from 85000 to 95000 ft, depending on the minimum dynamic pressures deemed acceptable for adequate flight control. By using engine overspeed capability and by making use of prevailing winds in the stratosphere, it is suggested that the maximum altitude achievable by an F4-C should be in the vicinity of 95000 ft for routine flight operation. This altitude is well in excess of the minimum altitudes which must be achieved for monitoring the possible growth of suspected aerosol contaminants.

75 FR 12468 - Airworthiness Directives; Quartz Mountain Aerospace, Inc. Model 11E Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-03-16

... Aerospace, Inc. Model 11E Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... airworthiness directive (AD) for all Quartz Mountain Aerospace, Inc. Model 11E airplanes. This proposed AD would... 5 p.m., Monday through Friday, except Federal holidays. Quartz Mountain Aerospace, Inc. is in...

75 FR 30282 - Airworthiness Directives; Quartz Mountain Aerospace, Inc. Model 11E Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-06-01

... Airworthiness Directives; Quartz Mountain Aerospace, Inc. Model 11E Airplanes AGENCY: Federal Aviation... airworthiness directive (AD) for all Quartz Mountain Aerospace, Inc. Model 11E airplanes. This AD requires you... reference of certain publications listed in this AD. ADDRESSES: Quartz Mountain Aerospace, Inc. is in...

Evaluation of the antitumor effects of c-Myc-Max heterodimerization inhibitor 100258-F4 in ovarian cancer cells.

PubMed

Wang, Jiandong; Ma, Xiaoli; Jones, Hannah M; Chan, Leo Li-Ying; Song, Fang; Zhang, Weiyuan; Bae-Jump, Victoria L; Zhou, Chunxiao

2014-08-21

Epithelial ovarian carcinoma is the most lethal gynecological cancer due to its silent onset and recurrence with resistance to chemotherapy. Overexpression of oncogene c-Myc is one of the most frequently encountered events present in ovarian carcinoma. Disrupting the function of c-Myc and its downstream target genes is a promising strategy for cancer therapy. Our objective was to evaluate the potential effects of small-molecule c-Myc inhibitor, 10058-F4, on ovarian carcinoma cells and the underlying mechanisms by which 10058-F4 exerts its actions. Using MTT assay, colony formation, flow cytometry and Annexin V FITC assays, we found that 10058-F4 significantly inhibited cell proliferation of both SKOV3 and Hey ovarian cancer cells in a dose dependent manner through induction of apoptosis and cell cycle G1 arrest. Treatment with 10058-F4 reduced cellular ATP production and ROS levels in SKOV3 and Hey cells. Consistently, primary cultures of ovarian cancer treated with 10058-F4 showed induction of caspase-3 activity and inhibition of cell proliferation in 15 of 18 cases. The response to 10058-F4 was independent the level of c-Myc protein over-expression in primary cultures of ovarian carcinoma. These novel findings suggest that the growth of ovarian cancer cells is dependent upon c-MYC activity and that targeting c-Myc-Max heterodimerization could be a potential therapeutic strategy for ovarian cancer.

Decomposed Fragment Identification in C_8F_18 RF Plasma for a-C:F Film Production

NASA Astrophysics Data System (ADS)

Sakai, Yosuke; Tazawa, Shota; Bratescu, Maria; Suda, Yoshiyuki; Sugawara, Hirotake

2004-09-01

Amorphous fluorocarbon polymer (a-C:F) film shows excellent insulation properties such as low dielectric constant (<2.5), high dielectric strength (>2 MV/cm), low surface energy, and chemical inertness. Therefore, we have studied this film for a purpose of an additional insulator to enhance the breakdown voltage in an alternative to a SF6 gas insulation system. The films are prepared using a C_8F_18 vapor RF plasma. When per-fluorocarbon, such as C_8F_18 as source gases, then the deposition rate becomes roughly two orders of magnitude higher than that obtained from conventional low molecular-weight source monomers (CF_4, C_2F_6, C_3F_6, and C_4F_8) [1]. The breakdown voltage (V_s) of N_2, Ar and He gases between the a-C:F film coated Al sphere-sphere electrodes for a gas pressure (p) times gap length (d), pd=0.1-100 Torr¥cm, was studied as well. Then, Vs between the a-C:F film coated electrodes was a several times higher than that between the Al electrodes in the present pd range[2]. In this work, the decomposed species of C_8F_18 in the plasma were identified using emission spectra from the plasma and Quadra-pole mass spectrograph, and the reason why the high deposition rate was obtained was discussed. The physical and chemical properties of a-C:F film was analyzed. [1] C.P.Lungu, et.al., Jpn. J. Appl. Phys. 38 (12B) L1544 - L1546 (1999) [2] C.Biloiu, et.al., Jpn. J. Appl. Phys. 42 (2B) L 201- L203 (2003) Work supported by Grant-in-Aid for Scientific Research (B), JSPS.

76 FR 67346 - Airworthiness Directives; Cessna Aircraft Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-11-01

... one of the affected airplanes equipped with a lithium-ion battery as the main aircraft battery. We are... replacing the lithium-ion main aircraft battery, Cessna part number (P/N) 9914788-1, with a Ni-Cad or a lead... power unit was connected to a Cessna Model 525C airplane equipped with a lithium-ion battery, Cessna P/N...

76 FR 53308 - Airworthiness Directives; Cessna Aircraft Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-26

... Airworthiness Directives; Cessna Aircraft Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... (AD) for certain Cessna Aircraft Company (Cessna) Models 150F, 150G, 150H, 150J, 150K, 150L, 150M... Friday, except Federal holidays. For service information identified in this AD, contact Cessna Aircraft...

Testing a Windmill Airplane ("autogiro")

NASA Technical Reports Server (NTRS)

Seiferth, R

1927-01-01

In order to clear up the matter ( In the Spanish report it was stated that the reference surface for the calculation of the coefficients c(sub a) and c(sub w) was the area of all four wings, instead of a single wing), the model of a windwill airplane was tested in the Gottingen wind tunnel.

75 FR 38019 - Airworthiness Directives; Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700 & 701...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-07-01

... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2009... Directives; Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700 & 701) Airplanes, Model CL-600-2D15 (Regional Jet Series 705) Airplanes, and Model CL-600-2D24 (Regional Jet Series 900) Airplanes Correction In...

75 FR 20518 - Special Conditions: Cirrus Design Corporation Model SF50 Airplane; Full Authority Digital Engine...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-04-20

...; Special Conditions No. 23-246-SC] Special Conditions: Cirrus Design Corporation Model SF50 Airplane; Full Authority Digital Engine Control (FADEC) System AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... Cirrus Design Corporation model SF50 airplane. This airplane will have a novel or unusual design feature...

78 FR 11553 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Electronic Flight Control System...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-02-19

... metal with composite empennage and control surfaces. The Model EMB-550 airplane is designed for 8...; Electronic Flight Control System: Control Surface Awareness and Mode Annunciation AGENCY: Federal Aviation... Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design feature(s...

JRC Copernicus Climate Change Service (C3S) F4P platform.

NASA Astrophysics Data System (ADS)

Mota, Bernardo; Cappucci, Fabrizio; Gobron, Nadine

2016-04-01

With the increasing number of Earth Observation satellites and derived land surface products, concerns of quality assurance led the Global Climate Observing System (GCOS) to establish accuracy criteria and standards. In this context, the Climate Change Copernicus Service (C3S) fitness-for-purpose (F4P) platform, developed at the Joint Research Centre, aims assessing the quality of land Essential Climate Variables (ECVs) in compliance with GCOS criteria. In this paper, we first summarize the JRC C3S FP4 goals and secondly present the automatic review platform to assess multi-mission physical consistencies and physical coherence of and between various land products, at global and regional scales. We propose new metrics, such as Gamma Index and Triple Collocation Error Model, for multi-mission product inter-comparison and stability assessment, and resource selection statistical methods to assess physical coherence with other related ECV products. Examples concern the consistency of five global albedo products (GlobAlbedo, GLASS, MCD43C3, GIO and MISR), between 2000 And 2011, and their coherence with four burnt area products (MCD45A1, MCD64A1, Fire_CCI and GIO) for the overlapping period (2006 to 2008). Preliminary results show reasonable agreement with the inherent limitations of each product algorithm and sensor resolution.

76 FR 63823 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane Pilot-Compartment View...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-14

... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. NM457; Notice No. 25-449-SC] Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane Pilot... Gulfstream Aerospace LP (GALP) Model G280 airplane. This airplane will have a novel or unusual design feature...

76 FR 30294 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane Pilot Compartment View...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-05-25

... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. NM457; Notice No. 25-11-14-SC] Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane Pilot... conditions for the Gulfstream Aerospace LP (GALP) Model G250 airplane. This airplane will have a novel or...

Low-Lift Drag of the Grumman F9F-9 Airplane as Obtained by a 1/7.5-Scale Rocket-Boosted Model and by Three 1/45.85-Scale Equivalent-Body Models between Mach Numbers of 0.8 and 1.3, TED No. NACA DE 391

NASA Technical Reports Server (NTRS)

Stevens, Joseph E.

1955-01-01

Low-lift drag data are presented herein for one 1/7.5-scale rocket-boosted model and three 1/45.85-scale equivalent-body models of the Grumman F9F-9 airplane, The data were obtained over a Reynolds number range of about 5 x 10(exp 6) to 10 x 10(exp 6) based on wing mean aerodynamic chord for the rocket model and total body length for the equivalent-body models. The rocket-boosted model showed a drag rise of about 0,037 (based on included wing area) between the subsonic level and the peak supersonic drag coefficient at the maximum Mach number of this test. The base drag coefficient measured on this model varied from a value of -0,0015 in the subsonic range to a maximum of about 0.0020 at a Mach number of 1.28, Drag coefficients for the equivalent-body models varied from about 0.125 (based on body maximum area) in the subsonic range to about 0.300 at a Mach number of 1.25. Increasing the total fineness ratio by a small amount raised the drag-rise Mach number slightly.

Theoretical and experimental studies of the Nd3+ 4f3<-->4f25d transitions in monoclinic Nd:BaY2F8 crystal

NASA Astrophysics Data System (ADS)

Collombet, Annabelle; Guyot, Yannick; Joubert, Marie-France; Margerie, Jean; Moncorgé, Richard; Tkachuk, Alexandra

2004-11-01

Experimental spectroscopic results related to Nd3+-doped BaY2F8, are presented that include vacuum-ultraviolet ground-state absorption and excitation spectra as well as polarized emission and excited-state absorption spectra recorded in the near-ultraviolet spectral range at room and low temperatures. Calculations were performed to determine the positions of the 4f25d sublevels and the intensities and polarizations of the 4f3<-->4f25d optical transitions of the Nd3+ ions in the C2 symmetry sites of the biaxial host crystal. The simulated spectra agree well with the experimental spectra; in particular, the model that was used successfully reproduced the differences between the polarized spectra on one hand and between the spectra recorded at low and room temperatures on the other hand.

78 FR 36084 - Special Conditions: The Boeing Company, Model 717-200 Series Airplanes; Seats With Inflatable...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-06-17

... 717- 200 series airplanes. These airplanes will have a novel or unusual design feature [[Page 36085... series airplanes will incorporate the following novel or unusual design features: inflatable lapbelts on... certain novel or unusual design features on one model series of airplanes. It is not a rule of general...

Flight evaluation results for a digital electronic engine control in an F-15 airplane

NASA Technical Reports Server (NTRS)

Burcham, F. W., Jr.; Myers, L. P.; Walsh, K. R.

1983-01-01

A digital electronic engine control (DEEC) system on an F100 engine in an F-15 airplane was evaluated in flight. Thirty flights were flown in a four-phase program from June 1981 to February 1983. Significant improvements in the operability and performance of the F100 engine were developed as a result of the flight evaluation: the augmentor envelope was increased by 15,000 ft, the airstart envelope was improved by 75 knots, and the need to periodically trim the engine was eliminated. The hydromechanical backup control performance was evaluated and was found to be satisfactory. Two system failures were encountered in the test program; both were detected and accommodated successfully. No transfers to the backup control system were required, and no automatic transfers occurred. As a result of the successful DEEC flight evaluation, the DEEC system has entered the full-scale development phase.

76 FR 77934 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-12-15

...-1321; Directorate Identifier 2011-NM-045-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes...: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A319 series airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321 series airplanes that would...

75 FR 69030 - Airworthiness Directives; Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-11-10

.... Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) Airplanes, Model CL-600-2D15 (Regional Jet Series 705) Airplanes, and Model CL-600-2D24 (Regional Jet Series 900) Airplanes AGENCY: Federal Aviation... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2010...

77 FR 2442 - Airworthiness Directives; The Boeing Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-01-18

... removed for any alternative designs (e.g., TDG Aerospace UFI). Japan Airlines (JAL) noted that the... or concurrently with the installation of the ground fault interrupt relays, a dual crossfeed valve is...) Applicability This AD applies to The Boeing Company Model 767-200, -300, - 300F, and -400ER series airplanes...

78 FR 68775 - Special Conditions: Airbus, Model A350-900 Series Airplane; Composite Fuselage In-Flight Fire...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-11-15

... Model A350-900 series airplanes. This airplane will have a novel or unusual design features associated... Model A350-900 series because of a novel or unusual design feature, special conditions are prescribed... Airbus Model A350-900 series airplane will incorporate the following novel or unusual design features...

76 FR 38550 - Special Conditions: Boeing, Model 747-8 Series Airplanes; Door 1 Extendable Length Escape Slide

Federal Register 2010, 2011, 2012, 2013, 2014

2011-07-01

...; Special Conditions No. 25-438-SC] Special Conditions: Boeing, Model 747-8 Series Airplanes; Door 1... conditions. SUMMARY: These special conditions are issued for Boeing Model 747-8 airplanes. These airplanes... Federal Regulations (14 CFR) 21.101, Boeing must show that the Model 747-8 (hereafter referred as 747-8...

75 FR 10658 - Airworthiness Directives; The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-03-09

... Airworthiness Directives; The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes..., -200, -200C, -300, -400, and - 500 series airplanes. That AD currently requires a one-time inspection... 16211, March 31, 2006). The existing AD applies to all Model 737-100, -200, -200C, -300, -400, and -500...

76 FR 63818 - Special Conditions: Boeing Model 767-400ER Series Airplanes; Seats With Inflatable Lapbelts

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-14

... appropriate safety standards for the 767-400ER series airplanes because of a novel or unusual design feature...-1106; Special Conditions No. 25-448-SC] Special Conditions: Boeing Model 767-400ER Series Airplanes...- 400ER series airplane. These airplanes, as modified by Continental Airlines, will have a novel or...

Enhanced electrochemical properties of F-doped Li2MnSiO4/C for lithium ion batteries

NASA Astrophysics Data System (ADS)

Wang, Chao; Xu, Youlong; Sun, Xiaofei; Zhang, Baofeng; Chen, Yanjun; He, Shengnan

2018-02-01

The Li2MnSiO4 as a novel cathode material for lithium ion batteries, performs high specific capacity, high thermal stability, low cost and etc. However, it suffers from relatively low electronic conductivity and lithium ion diffusion rate. Herein, we successfully introduce fluorine to Li2MnSiO4 (Li2MnSiO4-xFx, x = 0.00, 0.01, 0.03 and 0.05) to overcome these obstacles. The results show that F doping not only enlarges the lattice parameters but also decreases the particle size, synergistically improving the lithium ion diffusion of Li2MnSiO4. Moreover, F doping increase electronic conductivity of Li2MnSiO4/C by inhibiting the formation of C-O bonds in the carbon layers. Meanwhile, F doping improves the crystallinity and stabilizes the crystal structure of Li2MnSiO4. Finally, the Li2MnSiO3.97F0.03/C with the best electrochemical performances delivers the initial specific discharge capacity of 279 mA h g-1 at 25mA g-1 current density from 1.5 V to 4.8 V. Also, it maintains a higher capacity (201 mA h g-1) than F-free Li2MnSiO4 (145 mA h g-1) after 50 cycles.

77 FR 37788 - Airworthiness Directives; Fokker Services B.V. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-25

... Model F.28 Mark 0100 airplane. This AD requires repetitive low frequency eddy current inspections of the... described above, this [EASA] AD requires repetitive [low frequency eddy current] inspections of the forward... eddy current inspection of the forward fuselage butt-joints for cracks, in accordance with the...

Summary of Low-Lift Drag and Directional Stability Data from Rocket Models of the Douglas XF4D-1 Airplane with and without External Stores and Rocket Packets at Mach Numbers from 0.8 to 1.38 TED No. NACA DE-349

NASA Technical Reports Server (NTRS)

Mitcham, Grady L.; Blanchard, Willard S.; Hastings, Earl C., Jr.

1952-01-01

At the request of the Bureau of Aeronautics, Department of the Navy, an investigation at transonic and low supersonic speeds of the drag and longitudinal trim characteristics of the Douglas XF4D-1 airplane is being conducted by the Langley Pilotless Aircraft Research Division. The Douglas XF4D-1 is a jet-propelled, low-aspect-ratio, swept-wing, tailless, interceptor-type airplane designed to fly at low supersonic speeds. As a part of this investigation, flight tests were made using rocket- propelled 1/10- scale models to determine the effect of the addition of 10 external stores and rocket packets on the drag at low lift coefficients. In addition to these data, some qualitative values of the directional stability parameter C(sub n beta) and duct total-pressure recovery are also presented.

Role of C-Terminal Cysteine Residues of Aspergillus fumigatus Allergen Asp f 4 in Immunoglobulin E Binding

PubMed Central

Ramachandran, Harikrishnan; Banerjee, Banani; Greenberger, Paul A.; Kelly, Kevin J.; Fink, Jordan N.; Kurup, Viswanath P.

2004-01-01

Among the several allergens cloned and expressed from Aspergillus fumigatus, Asp f 4 is a major one associated with allergic bronchopulmonary aspergillosis (ABPA). The structure-function relationship of allergens is important in understanding the immunopathogenesis, diagnosis, and treatment of allergic diseases. These include the epitopes, conformational or linear, deletion of the N or C terminus or both N and C termini, and glycosylation or nonglycosylation, all of which affect immune responses. Similarly, the role of cysteine residues present in allergens may yield useful information regarding the conformational structure of allergens and the immunoglobulin E (IgE) epitope interaction. Such information may help in developing new strategies towards immunotherapy. In order to define the role of cysteine in the interaction of the antibody with Asp f 4, we have constructed mutants by selectively deleting cysteine residues from the C-terminal region of the Asp f 4. Immunological evaluation of these engineered recombinant constructs was conducted by using sera from patients with ABPA, Aspergillus skin test-positive asthmatics, and healthy controls. The results demonstrate strong IgE binding with Asp f 4 and two truncated mutants, Asp f 41-234 (amino acids [aa] 1 to 234) and Asp f 41-241 (aa 1 to 241), while another mutant, Asp f 41-196 (aa 1 to 196), showed reactivity with fewer patients. The result suggests that deletion of cysteines and the alteration of IgE epitopes at the C-terminal end resulted in conformational changes, which may have a potential role in the immunomodulation of the disease. PMID:15013973

Rate coefficients for the reaction of O(1D) with the atmospherically long-lived greenhouse gases NF3, SF3CF3, CHF3, C2F6, c-C3F8, n-C5F12, and n-C6F14

NASA Astrophysics Data System (ADS)

Baasandorj, M.; Hall, B. D.; Burkholder, J. B.

2012-09-01

The contribution of atmospherically persistent (long-lived) greenhouse gases to the radiative forcing of Earth has increased over the past several decades. The impact of highly fluorinated saturated compounds, in particular perfluorinated compounds, on climate change is a concern because of their long atmospheric lifetimes, which are primarily determined by stratospheric loss processes, as well as their strong absorption in the infrared "window" region. A potentially key stratospheric loss process for these compounds is their gas-phase reaction with electronically excited oxygen atoms, O(1D). Therefore, accurate reaction rate coefficient data is desired for input to climate change models. In this work, rate coefficients, k, were measured for the reaction of O(1D) with several key long-lived greenhouse gases, namely NF3, SF5CF3, CHF3 (HFC-23), C2F6, c-C4F8, n-C5F12, and n-C6F14. Room temperature rate coefficients for the total reaction, kTot, corresponding to loss of O(1D), and reactive channel, kR, corresponding to the loss of the reactant compound, were measured for NF3 and SF5CF3 using competitive reaction and relative rate methods, respectively. kR was measured for the CHF3 reaction and improved upper-limits were determined for the perfluorinated compounds included in this study. For NF3, kTot was determined to be (2.55 ± 0.38) × 10-11 cm3 molecule-1 s-1 and kR, which was measured using CF3Cl, N2O, CF2ClCF2Cl (CFC-114), and CF3CFCl2 (CFC-114a) as reference compounds, was determined to be (2.21 ± 0.33) × 10-11 cm3 molecule-1 s-1 corresponding to a reactive branching ratio of 0.87 ± 0.13. For SF5CF3, kTot = (3.24 ± 0.50) × 10-13 cm3 molecule-1 s-1 and kR < 5.8 × 10-14 cm3 molecule-1 s-1 were measured, where kR is a factor of three lower than the current recommendation of kTot for use in atmospheric modeling. For CHF3, kR was determined to be (2.35 ± 0.35) × 10-12 cm3 molecule-1 s-1, which corresponds to a reactive channel yield of 0.26 ± 0.04, and

78 FR 22806 - Airworthiness Directives; Bombardier, Inc. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-04-17

... indications, and consequent loss of control of the airplane. DATES: We must receive comments on this proposed... corrected, may result in erroneous airspeed and altitude indications [and consequent loss of control of the... consequent loss of control of the airplane. (f) Compliance You are responsible for having the actions...

76 FR 65103 - Special Conditions: Gulfstream Aerospace Corporation, Model GIV-X Airplane; Aircraft Electronic...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-20

... interior design configuration in the Gulfstream Model GIV-X passenger airplane. The Gulfstream Model GIV-X.... This airplane will have novel or unusual design features associated with the architecture and... appropriate safety standards for these design features. These special conditions contain the additional safety...

Free-Flight Tests of 0.11-Scale North American F-100 Airplane Wings to Investigate the Possibility of Flutter in Transonic Speed Range at Varying Angles of Attack

NASA Technical Reports Server (NTRS)

O'Kelly, Burke R.

1954-01-01

Free-flight tests in the transonic speed range utilizing rocketpropelled models have been made on three pairs of 0.11-scale North American F-100 airplane wings having an aspect ratio of 3.47, a taper ratio of 0.308, 45 degree sweepback at the quarter-chord line, and thickness ratios of 31 and 5 percent to investigate the possibility of flutte r. Data from tests of two other rocket-propelled models which accidentally fluttered during a drag investigation of the North American F-100 airplane are also presented. The first set of wings (5 percent thick) was tested on a model which was disturbed in pitch by a moving tail and reached a maximum Mach number of 0.85. The wings encountered mild oscillations near the first - bending frequency at high lift coefficients. The second set of wings 9 percent thick was tested up to a maximum Mach number of 0.95 at (2) angles of attack provided by small rocket motors installed in the nose of the model. No oscillations resembling flutter were encountered during the coasting flight between separation from the booster and sustainer firing (Mach numbers from 0.86 to 0.82) or during the sustainer firing at accelerations of about 8g up to the maximum Mach number of the test (0.95). The third set of wings was similar to the first set and was tested up to a maximum Mach number of 1.24. A mild flutter at frequencies near the first-bending frequency of the wings was encountered between a Mach number of 1.15 and a Mach number of 1.06 during both accelerating and coasting flight. The two drag models, which were 0.ll-scale models of the North American F-100 airplane configuration, reached a maximum Mach number of 1.77. The wings of these models had bending and torsional frequencies which were 40 and 89 percent, respectively, of the calculated scaled frequencies of the full-scale 7-percent-thick wing. Both models experienced flutter of the same type as that experienced-by the third set of wings.

Free-to-Roll Testing of Airplane Models in Wind Tunnels

NASA Technical Reports Server (NTRS)

Capone, Francis J.; Owens, D. Bruce; Hall, Robert M.

2007-01-01

head rigidly to the stationary head. Switching between the static and FTR test modes takes only about 30 minutes. The FTR test rig was originally mounted in a 16-ft (approximately 4.0-m) transonic wind tunnel, but could just as well be adapted to use in any large wind tunnel. In one series of tests on the FTR rig, static and dynamic characteristics of models of four different fighter airplanes were measured. Two of the models exhibited uncommanded lateral motions; the other two did not. A figure of merit was developed to discern the severity of lateral motions. Using this figure of merit, it was shown that the FTR test technique enabled identification of conditions under which the uncommanded lateral motions occurred. The wind-tunnel conditions thus identified were found to be correlated with flight conditions under which the corresponding full-size airplanes exhibited uncommanded lateral motions.

78 FR 27015 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-05-09

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-200 and A330-300 series airplanes, and Model A340-200 and A340-300 series airplanes... seal on a solenoid. This AD requires, depending on airplane configuration, modifying three flight...

The selective activation of a C-F bond with an auxiliary strong Lewis acid: a method to change the activation preference of C-F and C-H bonds.

PubMed

Wang, Lin; Sun, Hongjian; Li, Xiaoyan; Fuhr, Olaf; Fenske, Dieter

2016-11-15

The selective activation of the C-F bonds in substituted (2,6-difluorophenyl)phenylimines (2,6-F 2 H 3 C 6 -(C[double bond, length as m-dash]NH)-n'-R-C 6 H 4 (n' = 2, R = H (1); n' = 2, R = Me (2); n' = 4, R = tBu (3))) by Fe(PMe 3 ) 4 with an auxiliary strong Lewis acid (LiBr, LiI, or ZnCl 2 ) was explored. As a result, iron(ii) halides ((H 5 C 6 -(C[double bond, length as m-dash]NH)-2-FH 3 C 6 )FeX(PMe 3 ) 3 (X = Br (8); Cl (9)) and (n-RH 4 C 6 -(C[double bond, length as m-dash]NH)-2'-FH 3 C 6 )FeX(PMe 3 ) 3 (n = 2, R = Me, X = Br (11); n = 4, R = tBu, X = I (12))) were obtained. Under similar reaction conditions, using LiBF 4 instead of LiBr or ZnCl 2 , the reaction of (2,6-difluorophenyl)phenylimine with Fe(PMe 3 ) 4 afforded an ionic complex [(2,6-F 2 H 3 C 6 -(C[double bond, length as m-dash]NH)-H 4 C 6 )Fe(PMe 3 ) 4 ](BF 4 ) (10) via the activation of a C-H bond. The method of C-F bond activation with an auxiliary strong Lewis acid is appropriate for monofluoroarylmethanimines. Without the Lewis acid, iron(ii) hydrides ((2-RH 4 C 6 -(C[double bond, length as m-dash]NH)-2'-FH 3 C 6 )FeH(PMe 3 ) 3 (R = H (13); Me (14))) were generated from the reactions of Fe(PMe 3 ) 4 with the monofluoroarylmethanimines (2-FH 4 C 6 -(C[double bond, length as m-dash]NH)-2'-RC 6 H 4 (R = H (4); Me (5))); however, in the presence of ZnCl 2 or LiBr, iron(ii) halides ((2-RH 4 C 6 -(C[double bond, length as m-dash]NH)-H 4 C 6 )FeX(PMe 3 ) 3 (R = H, X = Cl (15); R = Me, X = Br (16))) could be obtained through the activation of a C-F bond. Furthermore, a C-F bond activation with good regioselectivity in (pentafluorophenyl)arylmethanimines (F 5 C 6 -(C[double bond, length as m-dash]NH)-2,6-Y 2 C 6 H 3 (Y = F (6); H (7))) could be realized in the presence of ZnCl 2 to produce iron(ii) chlorides ((2,6-Y 2 H 3 C 6 -(C[double bond, length as m-dash]NH)-F 4 C 6 )FeCl(PMe 3 ) 3 (Y = F (17); H (18))). This series of iron(ii) halides could be used to catalyze the hydrosilylation reaction of

78 FR 17865 - Airworthiness Directives; PILATUS AIRCRAFT LTD. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-03-25

... TBO were moved from Chapter 5: Time Limits/Maintenance Checks, to Chapter 4: Structural, Component and... Directives; PILATUS AIRCRAFT LTD. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final... all PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, and PC-12/47 airplanes. This AD results from...

Evaluation in Monkey of Two Candidate PET Radioligands, [11C]RX-1 and [18F]RX-2, for Imaging Brain 5-HT4 Receptors

PubMed Central

LOHITH, TALAKAD G.; XU, RONG; TSUJIKAWA, TETSUYA; MORSE, CHERYL L.; ANDERSON, KACEY B.; GLADDING, ROBERT L.; ZOGHBI, SAMI S.; FUJITA, MASAHIRO; INNIS, ROBERT B.; PIKE, VICTOR W.

2014-01-01

The serotonin subtype-4 (5-HT4) receptor, which is known to be involved physiologically in learning and memory, and pathologically in Alzheimer’s disease, anxiety and other neuropsychiatric disorders – has few radioligands readily available for imaging in vivo. We have previously reported two novel 5-HT4 receptor radioligands, namely [methoxy-11C](1-butylpiperidin-4-yl)methyl 4-amino-3-methoxybenzoate; [11C]RX-1) and the [18F]3-fluoromethoxy analog ([18F]RX-2), and in this study we evaluated them by PET in rhesus monkey. Brain scans were performed at baseline, receptor preblock or displacement conditions using SB 207710, a 5-HT4 receptor antagonist, on the same day for [11C]RX-1 and on different days for [18F]RX-2. Specific-to-nondisplaceable ratio (BPND) was measured with the simplified reference tissue model from all baseline scans. To determine specific binding, total distribution volume (VT) was also measured in some monkeys by radiometabolite-corrected arterial input function after ex vivo inhibition of esterases from baseline and blocked scans. Both radioligands showed moderate to high peak brain uptake of radioactivity (2–6 SUV). Regional BPND values were in the rank order of known 5-HT4 receptor distribution with a trend for higher BPND values from [18F]RX-2. One-tissue compartmental model provided good fits with well identified VT values for both radioligands. In the highest 5-HT4 receptor density region, striatum, 50–60% of total binding was specific. The VT in receptor-poor cerebellum reached stable values by about 60 min for both radioligands indicating little influence of radiometabolites on brain signal. In conclusion, both [11C]RX-1 and [18F]RX-2 showed positive attributes for PET imaging of brain 5-HT4 receptors, validating the radioligand design strategy. PMID:25088028

High-Speed Wind-Tunnel Investigation of the Longitudinal Stability and Control Characteristics of a 0.10-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE301

NASA Technical Reports Server (NTRS)

Polhamus, Edward C.; King, Thomas J., Jr.

1948-01-01

An investigation was made in the Langley high-speed 7-by 10-foot tunnel to determine the high-speed longitudinal stability end con&o1 characteristics of a 0.01-scale model of the Grumman XF9F-2 airplane in the Mach number range from 0.40 to 0.85. The results indicated that the lift and drag force breaks occurred at a Mach number of about 0.76. The aerodynamic-center position moved rearward after the force break and control position stability was present for all Mach numbers up to a Mach number of 0.80.

77 FR 69739 - Airworthiness Directives; The Boeing Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-11-21

... Company Model 747-400, -400D, and -400F series airplanes. This AD was prompted by reports of crown frame... to prevent complete fracture of the crown frame assembly, and consequent damage to the skin and in... frame web. Request To Provide Credit for Prior Actions Boeing requested that we allow credit for work...

76 FR 6578 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-02-07

...-200 and -300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Supplemental... apply to certain Model A330-200 and -300 series airplanes. That supplemental NPRM was published in the...

Development and Flight Evaluation of an Emergency Digital Flight Control System Using Only Engine Thrust on an F-15 Airplane

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Maine, Trindel A.; Fullerton, C. Gordon; Webb, Lannie Dean

1996-01-01

A propulsion-controlled aircraft (PCA) system for emergency flight control of aircraft with no flight controls was developed and flight tested on an F-15 aircraft at the NASA Dryden Flight Research Center. The airplane has been flown in a throttles-only manual mode and with an augmented system called PCA in which pilot thumbwheel commands and aircraft feedback parameters were used to drive the throttles. Results from a 36-flight evaluation showed that the PCA system can be used to safety land an airplane that has suffered a major flight control system failure. The PCA system was used to recover from a severe upset condition, descend, and land. Guest pilots have also evaluated the PCA system. This paper describes the principles of throttles-only flight control; a history of loss-of-control accidents; a description of the F-15 aircraft; the PCA system operation, simulation, and flight testing; and the pilot comments.

The effect of lateral controls in producing motion of an airplane as computed from wind-tunnel data

NASA Technical Reports Server (NTRS)

Weick, F. E.; Jones, R. T.

1976-01-01

An analytical study of the lateral controllability of an airplane has been made in which both the static rolling and yawing moments supplied by the controls and the reactions due to the inherent stability of the airplane have been taken into account. A hypothetical average airplane, embodying the essential characteristics of both the wind tunnel models and the full size test airplanes, was assumed for the study. Computations made of forced rolling and yawing motions of an F-22 airplane caused by a sudden deflection of the ailerons were found to agree well with actual measurements of these motions. The conditions following instantaneous full deflections of the lateral control have been studied, and some attention has been devoted to the controlling of complete turn maneuvers.

78 FR 11562 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: High Speed...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-02-19

... control surfaces. The Model EMB-550 airplane is designed for 8 passengers, with a maximum of 12 passengers... the pilot or copilot sidestick. The longitudinal control law design of the Embraer S.A. Model EMB- 550... EMB-550 airplane. This airplane will have a novel or unusual design feature, specifically an...

Flight Characteristics of a 1/4-Scale Model of the XFV-1 Airplane (TED No. NACA DE-378)

NASA Technical Reports Server (NTRS)

Kelly, Mark W.; Smaus, Louis H.

1952-01-01

A l/4-scale dynamically similar model of the XFV-1 airplane has been flown in the Ames 40- by 80-foot wind tunnel, using the trailing flight-cable technique. This investigation was devoted to establishing the flight characteristics of the model in forward flight from hovering to wing stall, and in yawed flight (wing span alined with the relative wind) from hovering to the maximum speed at which controlled flight could be maintained. Landings, take-offs, and hovering characteristics in flights close to the ground were also investigated.. Since the remote control system for the model was rather complicated and provided artificial damping about the pitch, roll, and yaw axes, sufficient data from the control-system calibration tests are included in this report to specify the performance of the control system in relation to both the model flight tests and the design of an automatic control system for the full-scale airplane. The model in hovering flight appeared to be neutrally stable. The response of the model to the controls was very rapid, and it was always necessary to provide some amount of artificial damping to maintain control. The model could be landed with little difficulty by hovering approximately a foot above the floor and then cutting the power. Take-offs were more difficult to perform, primarily because the rate of change in power to the model motors was limited by the characteristics of the available power source. The model was,capable of controlled yawed flight at translational velocities up to and including 20 feet per second. The effectiveness of the controls decreased with increasing speed, however, and at 25 fps control in pitch, and probably roll, was lost completely. The model was flown in controlled forward flight from hovering up to 70 fps. During these flights the model appeared to be more difficult to control in yaw than it was in pitch or roll. The flights of the model were recorded by motion picture cameras. These motion pictures are

Thermophysical and radiation properties of high-temperature C4F8-CO2 mixtures to replace SF6 in high-voltage circuit breakers

NASA Astrophysics Data System (ADS)

Zhong, Linlin; Cressault, Yann; Teulet, Philippe

2018-03-01

C4F8-CO2 mixtures are one of the potential substitutes to SF6 in high-voltage circuit breakers. However, the arc quenching ability of C4F8-CO2 mixtures is still unknown. In order to provide the necessary basic data for the further investigation of arc quenching performance, the compositions, thermodynamic properties, transport coefficients, and net emission coefficients (NEC) of various C4F8-CO2 mixtures are calculated at temperatures of 300-30 000 K in this work. The thermodynamic properties are presented as the product of mass density and specific heat, i.e., ρCp. The transport coefficients include electrical conductivity, viscosity, and thermal conductivity. The atomic and molecular radiation are both taken into account in the calculation of NEC. The comparison of the properties between SF6 and C4F8-CO2 mixtures is also discussed to find their differences. The results of compositions show that C4F8-CO2 mixtures have a distinctive advantage over other alternative gases e.g., CF3I and C3F8, because the dissociative product (i.e., C4F6) of C4F8 at low temperatures has a very high dielectric strength. This is good for an arc quenching medium to endure the arc recovery phase. Compared with SF6, C4F8-CO2 mixtures present lower ρCp at temperatures below 2800 K and larger thermal conductivity above 2800 K. Based on the position of peaks in thermal conductivity, we predict that the cooling of C4F8-CO2 arc will be slowed down at higher temperatures than that of SF6 arc. It is also found that the mixing of CO2 shows slight effects on the electrical conductivity and NEC of C4F8-CO2 mixtures.

77 FR 4699 - Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-01-31

... Register. That NPRM applies to certain Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC- 6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes. The Docket Number in the heading, in the Supplementary Information...

Water production in comets C/2011 L4 (PanSTARRS) and C/2012 F6 (Lemmon) from observations with Soho/Swan

DOE Office of Scientific and Technical Information (OSTI.GOV)

Combi, M. R.; Aptekar, G.; Bertaux, J.-L.

2014-06-01

Comets C/2011 L4 (PanSTARRS) and C/2012 F6 (Lemmon) were observed throughout their 2012-2013 apparitions with the Solar Wind Anisotropies (SWAN) all-sky hydrogen Lyα camera on board the Solar and Heliosphere Observatory (SOHO) satellite. SOHO has been in a halo orbit around the L1 Earth-Sun Lagrange point since early 1996 and has been observing the interplanetary medium and comets beginning with C/1996 B2 (Hyakutake). The global water production from these comets was determined from an analysis of the SWAN Lyα camera observations. Comet C/2011 L4 (PanSTARRS), which reached its perihelion distance of 0.302 AU on 2013 March 10.17, was observed onmore » 50 days between 2013 January 29 and April 30. Comet C/2012 F6 (Lemmon), which reached its perihelion distance of 0.731 AU on 2013 March 24.51, was observed on 109 days between 2012 November 29 and 2013 June 31. The maximum water production rates were ∼1 × 10{sup 30} molecules s{sup –1} for both comets. The activities of both comets were asymmetric about perihelion. C/2011 L4 (PanSTARRS) was more active before perihelion than after, but C/2012 F6 (Lemmon) was more active after perihelion than before.« less

Fluorine-substitution induced switching of dissociation patterns of C6H4*+ produced by photoelimination of MgF2 from the complexes of mg*+ (multifluorobenzene).

PubMed

Liu, Hai-Chuan; Zhang, Xin-Hao; Wu, Yun-Dong; Yang, Shihe

2005-03-07

Complexes of fluorinated benzenes (o-C6H4-nF2+n) and Mg*+ are subjected to ultraviolet photodissociation (260-340 nm), producing efficiently benzyne radical cations (C6H4-nFn*+) besides Mg*+ and MgF+. We show that the consecutive dissociation of C6H4-nFn*+ follows the [C4(+) + C2] pattern exclusively for n < or = 2 after the parent complexes absorb one or two photons. However, the dissociation pattern is switched to [C5(+) + C1] and [C1 + C5] for n > or = 3. In particular, upon two-photon absorption at 340 nm by the complexes of Mg*+ (C6HF5) (1) and Mg*+ (C6F6) (2), photoproducts of CF+, C5H+, and C5HF*+ from C6HF3*+ and CF+, C5F+, C5F2*+, and C5F3+ from C6F4*+ are detected, respectively. Theoretical calculations are used to explain the switching of the dissociation patterns induced by the fluorine substitutions. It was found that the formation of C5+ + C1 is energetically more favorable than that of C4(+) + C2 from C6HF3*+ and C6F4*+ and of C1(+) + C5. Except for C5H2F(+) + CF, all the channels of [C5(+) + C1] and [C1(+) + C5] are energetically less favorable than those of [C4(+) + C2] from C6H3F*+ and C6H2F2*+. In most cases, the calculated results agree well with the experimental observations.

78 FR 36084 - Special Conditions: Cirrus Design Corporation Model SF50 Airplane; Function and Reliability...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-06-17

...; Special Conditions No. 23-248-SC] Special Conditions: Cirrus Design Corporation Model SF50 Airplane... granting special conditions for the Cirrus Design Corporation model SF50 airplane. We are withdrawing... Special Condition No. 23-248- SC for the Cirrus Design Corporation new model SF50 ``Vision'' Jet. The SF50...

75 FR 23572 - Airworthiness Directives; Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-05-04

... cycles 6,700 flight 80A3 or Pratt & Whitney engines. flight cycles \\1\\. flight cycles or \\2\\. cycles or...-200 airplanes with GE CF6- 18,000 total 19,500 total 250 flight cycles 5,800 flight 80C2 engines... flight cycles 6,700 flight Pratt & Whitney JT9D engines. flight cycles \\1\\. flight cycles or \\2\\. cycles...

78 FR 53640 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-30

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-200 Freighter series airplanes; Model A330-200 and - 300 series airplanes, and Model... of the forward or aft cargo door. To address this condition, Airbus issued four separate Alert...

Abelian F-theory models with charge-3 and charge-4 matter

NASA Astrophysics Data System (ADS)

Raghuram, Nikhil

2018-05-01

This paper analyzes U(1) F-theory models admitting matter with charges q = 3 and 4. First, we systematically derive a q = 3 construction that generalizes the previous q = 3 examples. We argue that U(1) symmetries can be tuned through a procedure reminiscent of the SU( N ) and Sp( N ) tuning process. For models with q = 3 matter, the components of the generating section vanish to orders higher than 1 at the charge-3 matter loci. As a result, the Weierstrass models can contain non-UFD structure and thereby deviate from the standard Morrison-Park form. Techniques used to tune SU( N ) models on singular divisors allow us to determine the non-UFD structures and derive the q = 3 tuning from scratch. We also obtain a class of a q=4 models by deforming a prior U(1) × U(1) construction. To the author's knowledge, this is the first published F-theory example with charge-4 matter. Finally, we discuss some conjectures regarding models with charges larger than 4.

Depletion of kidney CD11c+ F4/80+ cells impairs the recovery process in ischaemia/reperfusion-induced acute kidney injury.

PubMed

Kim, Myung-Gyu; Boo, Chang Su; Ko, Yoon Sook; Lee, Hee Young; Cho, Won Yong; Kim, Hyoung Kyu; Jo, Sang-Kyung

2010-09-01

Recent studies provided evidence of the potential role of CD11c(+) F4/80(+) dendritic subset in mediating injury and repair. The purpose of this study was to examine the role of kidney CD11c(+) F4/80(+) dendritic subset in the recovery phase of ischaemia/reperfusion injury (IRI). Following ischaemia/reperfusion (I/R), liposome clodronate or phosphate buffered saline (PBS) was administered, and on day 7 biochemical and histologic kidney damage was assessed. Activation and depletion of CD11c(+) F4/80(+) dendritic subset were confirmed by flow cytometry. Isolation of kidney CD11c(+) cells on days 1 and 7 with in vitro culture for measuring cytokines was performed to define functional characteristics of these cells, and adoptive transfer of CD11c(+) cells was also done. Following kidney IRI, the percentage of CD11c(+) F4/80(+) kidney dendritic cell subset that co-expresses maturation marker increased. Liposome clodronate injection after I/R resulted in preferential depletion of CD11c(+) F4/80(+) kidney dendritic subset, and depletion of these cells was associated with persistent kidney injury, more apoptosis, inflammation and impaired tubular cell proliferation. CD11c(+) F4/80(+) cell depletion was also associated with higher tissue levels of pro-inflammatory cytokines and lower level of IL-10, indicating the persistence of inflammatory milieu. Isolated kidney CD11c(+) cells on day 7 showed different phenotype with increased production of IL-10 compared with those on day 1. Adoptive transfer of CD11c(+) cells partially reversed impaired tissue recovery. Our results suggest that kidney CD11c(+) F4/80(+) dendritic subset might contribute to the recovery process by dynamic phenotypic change from pro-inflammatory to anti-inflammatory with modulation of immune response.

78 FR 75287 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Flight...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-11

... appropriate safety standards for the C-series airplanes because of a novel or unusual design feature, special... Features The C-series airplanes will incorporate the following novel or unusual design features: new... Series Airplanes; Flight Envelope Protection: General Limiting Requirements AGENCY: Federal Aviation...

Evaluation of Gust and Draft Velocities from Flights of F-61C Airplanes within Thunderstorms August 7, 1947 to August 13, 1947 at Clinton County Army Air Field, Ohio

NASA Technical Reports Server (NTRS)

Funk, Jack

1948-01-01

The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air FIeld, Ohio, from August 7, 1947 to August 13, 1947 are presented.

77 FR 42952 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-07-23

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A318-112 and -121 airplanes; Model A319-111, -112, -115, - 132, and -133 airplanes; Model... MCAI states: During structural part assembly in Airbus production line, some nuts Part Number (P/N...

An Experimental Investigation of Effects of Fluxes (Na3AlF6 and K2TiF6), Element Alloys (Mg), and Composite Powders ((Al + TiC)CP and (Al + B4C)CP) on Distribution of Particles and Phases in Al-B4C and Al-TiC Composites

NASA Astrophysics Data System (ADS)

Mazaheri, Younes; Emadi, Rahmatollah; Meratian, Mahmood; Zarchi, Mehdi Karimi

2017-04-01

The wettability, incorporation, and gravity segregation of TiC and B4C particles into molten aluminum are important problems in the production of Al-TiC and Al-B4C composites by the casting techniques. In order to solve these problems, different methods consisting of adding the Na3AlF6 and K2TiF6 fluxes and Mg (as the alloying element) into the molten aluminum and injection of the (Al + TiC)CP and (Al + B4C)CP composite powders instead of B4C and TiC particles are evaluated. In this work, the conditions of sample preparation, such as particle addition temperature, stirring speed, and stirring time, are determined after many studies and tests. Microstructural characterizations of samples are investigated by scanning electron microscopy equipped with energy dispersive spectroscopy (EDS) and X-ray diffractometry. The results show better distribution and incorporation of TiCp and B4Cp in aluminum matrix when the fluxes are used, as well as EDS analysis of the interface between the matrix and reinforcement-strengthened formation of the different phases such as Al4C3 in the Al-TiC composites and Al3BC, TiB2 in the Al-B4C composites.

76 FR 62673 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-11

...-1066; Directorate Identifier 2011-NM-050-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes...: We propose to adopt a new airworthiness directive (AD), for certain Airbus Model A300 B2-1C, B2K-3C... Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus...

75 FR 38017 - Airworthiness Directives; McDonnell Douglas Corporation Model DC-9-10 Series Airplanes, DC-9-30...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-07-01

... Airworthiness Directives; McDonnell Douglas Corporation Model DC- 9-10 Series Airplanes, DC-9-30 Series Airplanes, DC-9-81 (MD-81) Airplanes, DC-9-82 (MD-82) Airplanes, DC-9-83 (MD-83) Airplanes, DC-9- 87 (MD-87... Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and...

A Monte Carlo Sensitivity Analysis of CF2 and CF Radical Densities in a c-C4F8 Plasma

NASA Technical Reports Server (NTRS)

Bose, Deepak; Rauf, Shahid; Hash, D. B.; Govindan, T. R.; Meyyappan, M.

2004-01-01

A Monte Carlo sensitivity analysis is used to build a plasma chemistry model for octacyclofluorobutane (c-C4F8) which is commonly used in dielectric etch. Experimental data are used both quantitatively and quantitatively to analyze the gas phase and gas surface reactions for neutral radical chemistry. The sensitivity data of the resulting model identifies a few critical gas phase and surface aided reactions that account for most of the uncertainty in the CF2 and CF radical densities. Electron impact dissociation of small radicals (CF2 and CF) and their surface recombination reactions are found to be the rate-limiting steps in the neutral radical chemistry. The relative rates for these electron impact dissociation and surface recombination reactions are also suggested. The resulting mechanism is able to explain the measurements of CF2 and CF densities available in the literature and also their hollow spatial density profiles.

Atmospheric abundance and global emissions of perfluorocarbons CF4, C2F6 and C3F8 since 1800 inferred from ice core, firn, air archive and in situ measurements

NASA Astrophysics Data System (ADS)

Trudinger, Cathy M.; Fraser, Paul J.; Etheridge, David M.; Sturges, William T.; Vollmer, Martin K.; Rigby, Matt; Martinerie, Patricia; Mühle, Jens; Worton, David R.; Krummel, Paul B.; Steele, L. Paul; Miller, Benjamin R.; Laube, Johannes; Mani, Francis S.; Rayner, Peter J.; Harth, Christina M.; Witrant, Emmanuel; Blunier, Thomas; Schwander, Jakob; O'Doherty, Simon; Battle, Mark

2016-09-01

Perfluorocarbons (PFCs) are very potent and long-lived greenhouse gases in the atmosphere, released predominantly during aluminium production and semiconductor manufacture. They have been targeted for emission controls under the United Nations Framework Convention on Climate Change. Here we present the first continuous records of the atmospheric abundance of CF4 (PFC-14), C2F6 (PFC-116) and C3F8 (PFC-218) from 1800 to 2014. The records are derived from high-precision measurements of PFCs in air extracted from polar firn or ice at six sites (DE08, DE08-2, DSSW20K, EDML, NEEM and South Pole) and air archive tanks and atmospheric air sampled from both hemispheres. We take account of the age characteristics of the firn and ice core air samples and demonstrate excellent consistency between the ice core, firn and atmospheric measurements. We present an inversion for global emissions from 1900 to 2014. We also formulate the inversion to directly infer emission factors for PFC emissions due to aluminium production prior to the 1980s. We show that 19th century atmospheric levels, before significant anthropogenic influence, were stable at 34.1 ± 0.3 ppt for CF4 and below detection limits of 0.002 and 0.01 ppt for C2F6 and C3F8, respectively. We find a significant peak in CF4 and C2F6 emissions around 1940, most likely due to the high demand for aluminium during World War II, for example for construction of aircraft, but these emissions were nevertheless much lower than in recent years. The PFC emission factors for aluminium production in the early 20th century were significantly higher than today but have decreased since then due to improvements and better control of the smelting process. Mitigation efforts have led to decreases in emissions from peaks in 1980 (CF4) or early-to-mid-2000s (C2F6 and C3F8) despite the continued increase in global aluminium production; however, these decreases in emissions appear to have recently halted. We see a temporary reduction of around

Gas-phase reactivity of lanthanide cations with fluorocarbons: C-F versus C-H and C-C bond activation

DOE Office of Scientific and Technical Information (OSTI.GOV)

Cornehl, H.H.; Hornung, G.; Schwarz, H.

1996-10-16

The gas-phase reactivity of the fluorinated hydrocarbons CF{sub 4}, CHF{sub 3}, CH{sub 3}F, C{sub 2}F{sub 6}, 1,1-C{sub 2}H{sub 4}F{sub 2}, and C{sub 6}F{sub 6} with the lanthanide cations Ce{sup +}, Pr{sup +}, Sm{sup +}, Ho{sup +}, Tm{sup +}, and Yb{sup +} and the reactivity of C{sub 6}H{sub 5}F with all lanthanide cations Ln{sup +} (Ln = La-Lu, with the exception of Pm{sup +}) have been examined by Fourier-transform ion cyclotron resonance mass spectrometry. The perfluorinated compounds tetrafluoromethane and hexafluoroethane as well as trifluoromethane do not react with any lanthanide cation. Selective activation of the strong C-F bonds in fluoromethane, 1,1-difluoroethane,more » hexafluorobenzene, and fluorobenzene appears as a general reaction scheme along the 4f row. Experimental evidence is given for a `harpoon`-like mechanism for the F atom abstraction process which operates via an initial electron transfer from the lanthanide cation to the fluorinated substrate in the encounter complex Ln{sup +}RF. The most reactive lanthanides La{sup +}, Ce{sup +}, Gd{sup +}, and Tb{sup +} and also the formal closed-shell species Lu{sup +} exhibit additional C-H and C-C bond activation pathways in the reaction with fluorobenzene, namely dehydrohalogenation as well as loss of a neutral acetylene molecule. In the case of Tm{sup +} and Yb{sup +} the formation of neutral LnF{sub 3} is observed in a multistep process via C-C coupling and charge transfer. 17 refs., 2 figs., 2 tabs.« less

77 FR 65799 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-10-31

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-200 freighter series airplanes, Model A330-200 and - 300 series airplanes, and Model... [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new AD: 2012-21-20 Airbus: Amendment 39...

Effects of flaps on buffet characteristics and wind-rock onset of an F-8C airplane at subsonic and transonic speeds

NASA Technical Reports Server (NTRS)

Monaghan, R. C.; Friend, E. L.

1973-01-01

Wind-up-turn maneuvers were performed to establish the values of airplane normal force coefficient for buffet onset, wing-rock onset, and buffet loads with various combinations of leading- and trailing-edge flap deflections. Data were gathered at both subsonic and transonic speeds covering a range from Mach 0.64 to Mach 0.92. Buffet onset and buffet loads were obtained from wingtip acceleration and wing-root bending-moment data, and wing-rock onset was obtained from airplane roll rate data. Buffet onset, wing-rock onset, and buffet loads were similarly affected by the various combinations of leading- and training-edge flaps. Subsonically, the 12 deg leading-edge-flap and trailing-edge-flap combination was most effective in delaying buffet onset, wing-rock onset, and equivalent values of buffet loads to a higher value of airplane normal force coefficient. This was the maximum flap deflection investigated. Transonically, however, the optimum leading-edge flap position was generally less than 12 deg.

Setaria viridis: A Model for C4 Photosynthesis[C][W

PubMed Central

Brutnell, Thomas P.; Wang, Lin; Swartwood, Kerry; Goldschmidt, Alexander; Jackson, David; Zhu, Xin-Guang; Kellogg, Elizabeth; Van Eck, Joyce

2010-01-01

C4 photosynthesis drives productivity in several major food crops and bioenergy grasses, including maize (Zea mays), sugarcane (Saccharum officinarum), sorghum (Sorghum bicolor), Miscanthus x giganteus, and switchgrass (Panicum virgatum). Gains in productivity associated with C4 photosynthesis include improved water and nitrogen use efficiencies. Thus, engineering C4 traits into C3 crops is an attractive target for crop improvement. However, the lack of a small, rapid cycling genetic model system to study C4 photosynthesis has limited progress in dissecting the regulatory networks underlying the C4 syndrome. Setaria viridis is a member of the Panicoideae clade and is a close relative of several major feed, fuel, and bioenergy grasses. It is a true diploid with a relatively small genome of ~510 Mb. Its short stature, simple growth requirements, and rapid life cycle will greatly facilitate genetic studies of the C4 grasses. Importantly, S. viridis uses an NADP-malic enzyme subtype C4 photosynthetic system to fix carbon and therefore is a potentially powerful model system for dissecting C4 photosynthesis. Here, we summarize some of the recent advances that promise greatly to accelerate the use of S. viridis as a genetic system. These include our recent successful efforts at regenerating plants from seed callus, establishing a transient transformation system, and developing stable transformation. PMID:20693355

Heats of Formation for Cyclic C4Fn, n=4-8, and their Cations

NASA Technical Reports Server (NTRS)

Bauschlicher, Charles W., Jr.; Ricca, Alessandra; Arnold, James (Technical Monitor)

2000-01-01

Heats of formation for cyclic C4F8 and C4F8+ are determined at the G3MP2 level. The several decomposition pathways are investigated. The calculations confirm that C4F8+ rearranges and its decomposition is responsible for both the C2F4+ and C3F5+ species observed in experiment. The heats of formation are presented for C4Fn and C4Fn+, n = 4-8.

Both flagella and F4 fimbriae from F4ac+ enterotoxigenic Escherichia coli contribute to attachment to IPEC-J2 cells in vitro.

PubMed

Zhou, Mingxu; Duan, Qiangde; Zhu, Xiaofang; Guo, Zhiyan; Li, Yinchau; Hardwidge, Philip R; Zhu, Guoqiang

2013-05-13

The role of flagella in the pathogenesis of F4ac+ Enterotoxigenic Escherichia coli (ETEC) mediated neonatal and post-weaning diarrhea (PWD) is not currently understood. We targeted the reference C83902 ETEC strain (O8:H19:F4ac+ LT+ STa+ STb+), to construct isogenic mutants in the fliC (encoding the major flagellin protein), motA (encoding the flagella motor), and faeG (encoding the major subunit of F4 fimbriae) genes. Both the ΔfliC and ΔfaeG mutants had a reduced ability to adhere to porcine intestinal epithelial IPEC-J2 cells. F4 fimbriae expression was significantly down-regulated after deleting fliC, which revealed that co-regulation exists between flagella and F4 fimbriae. However, there was no difference in adhesion between the ΔmotA mutant and its parent strain. These data demonstrate that both flagella and F4 fimbriae are required for efficient F4ac+ ETEC adhesion in vitro.

Longitudinal Trim and Tumble Characteristics of a 0.057-Scale Model of the Chance Vought XF7U-1 Airplane, TED NO. NACA DE311

NASA Technical Reports Server (NTRS)

Bryant, Robert L.

1948-01-01

Based on results of longitudinal trim and tumble tests of a 0.057-scale model of the Chance Vought XF7U-1 airplane, the following conclusions regarding the trim and tumble characteristics of the airplane have been drawn: 1. The airplane will not trim at any unusual or uncontrolled angles of attack. 2. The airplane will not tumble with the center of gravity located forward of 24 percent of the mean aerodynamic chord. When the center of gravity is located at 24 percent of the mean aerodynamic chord and slats are extended and elevators are deflected full up, the airplane may tumble if given an external positive pitching moment. 3. The tumbling motion obtained will be readily terminated by deflecting the elevators full down so as to oppose the rotation. 4. The accelerations encountered during an established tumble may be dangerous to the pilot and, therefore, action should be taken to terminate a tumble immediately upon its inception. 5. Simultaneous opening of two wing-tip parachutes having diameters of 4 feet or larger and having drag coefficients of approximately 0.7 will effectively terminate the tumble. 6. Model results indicate that the pilot will not be struck by the airplane if it becomes necessary to leave the airplane during a tumble. The pilot may require aid from an ejection-seat arrangement.

C4GEM, a Genome-Scale Metabolic Model to Study C4 Plant Metabolism1[W][OA

PubMed Central

de Oliveira Dal’Molin, Cristiana Gomes; Quek, Lake-Ee; Palfreyman, Robin William; Brumbley, Stevens Michael; Nielsen, Lars Keld

2010-01-01

Leaves of C4 grasses (such as maize [Zea mays], sugarcane [Saccharum officinarum], and sorghum [Sorghum bicolor]) form a classical Kranz leaf anatomy. Unlike C3 plants, where photosynthetic CO2 fixation proceeds in the mesophyll (M), the fixation process in C4 plants is distributed between two cell types, the M cell and the bundle sheath (BS) cell. Here, we develop a C4 genome-scale model (C4GEM) for the investigation of flux distribution in M and BS cells during C4 photosynthesis. C4GEM, to our knowledge, is the first large-scale metabolic model that encapsulates metabolic interactions between two different cell types. C4GEM is based on the Arabidopsis (Arabidopsis thaliana) model (AraGEM) but has been extended by adding reactions and transporters responsible to represent three different C4 subtypes (NADP-ME [for malic enzyme], NAD-ME, and phosphoenolpyruvate carboxykinase). C4GEM has been validated for its ability to synthesize 47 biomass components and consists of 1,588 unique reactions, 1,755 metabolites, 83 interorganelle transporters, and 29 external transporters (including transport through plasmodesmata). Reactions in the common C4 model have been associated with well-annotated C4 species (NADP-ME subtypes): 3,557 genes in sorghum, 11,623 genes in maize, and 3,881 genes in sugarcane. The number of essential reactions not assigned to genes is 131, 135, and 156 in sorghum, maize, and sugarcane, respectively. Flux balance analysis was used to assess the metabolic activity in M and BS cells during C4 photosynthesis. Our simulations were consistent with chloroplast proteomic studies, and C4GEM predicted the classical C4 photosynthesis pathway and its major effect in organelle function in M and BS. The model also highlights differences in metabolic activities around photosystem I and photosystem II for three different C4 subtypes. Effects of CO2 leakage were also explored. C4GEM is a viable framework for in silico analysis of cell cooperation between M and BS

76 FR 8314 - Special Conditions: Gulfstream Model GVI Airplane; Operation Without Normal Electric Power

Federal Register 2010, 2011, 2012, 2013, 2014

2011-02-14

... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. NM444 Special Conditions No. 25-11-03-SC] Special Conditions: Gulfstream Model GVI Airplane; Operation Without... Aviation Administration, Transport Airplane Directorate, Attn: Rules Docket (ANM-113), Docket No. NM444...

76 FR 9265 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System: Control...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-02-17

... for transport category airplanes. These design features include an electronic flight control system... Design Features The GVI has an electronic flight control system and no direct coupling from the cockpit...: Gulfstream Model GVI Airplane; Electronic Flight Control System: Control Surface Position Awareness AGENCY...

Analysis of Structural MtrC Models Based on Homology with the Crystal Structure of MtrF

DOE Office of Scientific and Technical Information (OSTI.GOV)

Edwards, Marcus; Fredrickson, Jim K.; Zachara, John M.

2012-12-01

The outer-membrane decahaem cytochrome MtrC is part of the transmembrane MtrCAB complex required for mineral respiration by Shewanella oneidensis. MtrC has significant sequence similarity to the paralogous decahaem cytochrome MtrF, which has been structurally solved through X-ray crystallography. This now allows for homology-based models of MtrC to be generated. The structure of these MtrC homology models contain ten bis-histidine-co-ordinated c-type haems arranged in a staggered cross through a four-domain structure. This model is consistent with current spectroscopic data and shows that the areas around haem 5 and haem 10, at the termini of an octahaem chain, are likely to havemore » functions similar to those of the corresponding haems in MtrF. The electrostatic surfaces around haem 7, close to the β-barrels, are different in MtrF and MtrC, indicating that these haems may have different potentials and interact with substrates differently.« less

78 FR 31386 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-05-24

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...) for all Airbus Model A330-200 and -300 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. That AD currently requires a one-time detailed inspection of both main landing gear...

Configuration development study of the X-24C hypersonic research airplane, phase 3

NASA Technical Reports Server (NTRS)

Combs, H. G.

1977-01-01

The conclusion evolved from the three phased study on the configuration development of the X-24C Hypersonic Research Airplane makes it evident that it is practical to design and build the high performance National Hypersonic Flight Research Facility airplane with today's state of the art within the cost and operational constraints established by NASA. The vehicle launched at 31.75 Mg from the B-52 can cruise for 40 seconds at Mach 6.78 on scramjets. Without scramjets it can approach Mach 8 with a 453.6 Kg payload or do 70 seconds of cruise at Mach 6 with a 2.27 Mg payload. Reduction in cost is possible with a vehicle scaled to a lesser mass and capability.

Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane with Speedpak Attached

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; Thompson, William C.

1949-01-01

Results of previous model ditching tests of the Lockheed Constellation airplane are reported. Further model tests have been made to determine the probable ditching characteristics and the proper ditching technique for the airplane with the Speedpak attached. This paper presents the results of these tests. Design information was furnished by the Lockheed Aircraft Corporation. A three-vies drawing of the airplane with the Speedpak attached is shown. The tests were made in calm water at the Langley tank no.2 monorail.

Transonic wing DFVLR-F4 as European test model

NASA Technical Reports Server (NTRS)

Redeker, G.; Schmidt, N.

1980-01-01

A transonic wing, the DFVLR-F4 was designed and tested as a model in European transonic wind tunnels and was found to give performance improvements over conventional wings. One reason for the improvement was the reduction of compression shocks in the transonic region as the result of improved wing design.

Reconstructing the atmospheric concentration and emissions of CF4, C2F6 and C3F8 prior to direct atmospheric measurements, using air from polar firn and ice

NASA Astrophysics Data System (ADS)

Trudinger, Cathy; Etheridge, David; Sturges, William; Vollmer, Martin; Miller, Benjamin; Worton, David; Rigby, Matt; Krummel, Paul; Martinerie, Patricia; Witrant, Emmanuel; Rayner, Peter; Battle, Mark; Blunier, Thomas; Fraser, Paul; Laube, Johannes; Mani, Frances; Mühle, Jens; O'Doherty, Simon; Schwander, Jakob; Steele, Paul

2015-04-01

Perfluorocarbons are very potent and long-lived greenhouse gases in the atmosphere, released predominantly during aluminium production, electronic chip manufacture and refrigeration. Mühle et al. (2010) presented records of the concentration and inferred emissions of CF4 (PFC-14), C2F6 (PFC-116) and C3F8 (PFC-218) from the 1970s up to 2008, using measurements from the Cape Grim Air Archive and a suite of tanks with old Northern Hemisphere air, and the AGAGE in situ network. Mühle et al. (2010) also estimated pre-industrial concentrations of these compounds from a small number of polar firn and ice core samples. Here we present measurements of air from polar firn at four sites (DSSW20K, EDML, NEEM and South Pole) and from air bubbles trapped in ice at two sites (DE08 and DE08-2), along with recent atmospheric measurements to give a continuous record of concentration from preindustrial levels up to the present. We estimate global emissions (with uncertainties) consistent with the concentration records. The uncertainty analysis takes into account uncertainties in characterisation of the age of air in firn and ice by the use of two different (independently-calibrated) firn models (the CSIRO and LGGE-GIPSA firn models). References Mühle, J., A.L. Ganesan, B.R. Miller, P.K. Salameh, C.M. Harth, B.R. Greally, M. Rigby, L.W. Porter, L. P. Steele, C.M. Trudinger, P.B. Krummel, S. O'Doherty, P.J. Fraser, P.G. Simmonds, R.G. Prinn, and R.F. Weiss, Perfluorocarbons in the global atmosphere: tetrafluoromethane, hexafluoroethane, and octafluoropropane, Atmos. Chem. Phys., 10, 5145-5164, doi:10.5194/acp-10-5145-2010, 2010.

78 FR 52414 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-23

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A320-214, -232 and -233 airplanes; and Model A321-211, - 213, and -231 airplanes. This AD... Service Information Airbus requested that we revise the NPRM (77 FR 63270, October 16, 2012) to reflect...

Initial events during the evolution of C4 photosynthesis in C3 species of Flaveria.

PubMed

Sage, Tammy L; Busch, Florian A; Johnson, Daniel C; Friesen, Patrick C; Stinson, Corey R; Stata, Matt; Sultmanis, Stefanie; Rahman, Beshar A; Rawsthorne, Stephen; Sage, Rowan F

2013-11-01

The evolution of C4 photosynthesis in many taxa involves the establishment of a two-celled photorespiratory CO2 pump, termed C2 photosynthesis. How C3 species evolved C2 metabolism is critical to understanding the initial phases of C4 plant evolution. To evaluate early events in C4 evolution, we compared leaf anatomy, ultrastructure, and gas-exchange responses of closely related C3 and C2 species of Flaveria, a model genus for C4 evolution. We hypothesized that Flaveria pringlei and Flaveria robusta, two C3 species that are most closely related to the C2 Flaveria species, would show rudimentary characteristics of C2 physiology. Compared with less-related C3 species, bundle sheath (BS) cells of F. pringlei and F. robusta had more mitochondria and chloroplasts, larger mitochondria, and proportionally more of these organelles located along the inner cell periphery. These patterns were similar, although generally less in magnitude, than those observed in the C2 species Flaveria angustifolia and Flaveria sonorensis. In F. pringlei and F. robusta, the CO2 compensation point of photosynthesis was slightly lower than in the less-related C3 species, indicating an increase in photosynthetic efficiency. This could occur because of enhanced refixation of photorespired CO2 by the centripetally positioned organelles in the BS cells. If the phylogenetic positions of F. pringlei and F. robusta reflect ancestral states, these results support a hypothesis that increased numbers of centripetally located organelles initiated a metabolic scavenging of photorespired CO2 within the BS. This could have facilitated the formation of a glycine shuttle between mesophyll and BS cells that characterizes C2 photosynthesis.

An analysis of the dissipation of heat in conditions of icing from a section of the wing of the C-46 airplane

NASA Technical Reports Server (NTRS)

Hardy, J K

1945-01-01

A method is given for calculating the temperature that a surface, heated internally by air, will assume in specified conditions of icing. The method can be applied generally to predict the performance, under conditions of icing, of the thermal system for protecting aircraft. Calculations have been made for a section of the wing of the C-46 airplane, and the results agree closely with the temperature measured. The limit of protection when the temperature of the surface reaches 32 degrees F., has been predicted for the leading edge. The temperature of the surface in conditions of icing with air at 0 degree F. also has been calculated. The effect of kinetic heating and the effect of the concentration of free water and size of droplet in the cloud are demonstrated.

77 FR 48469 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-08-14

...-0808; Directorate Identifier 2010-NM-170-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... airplanes, and Model A340-200 and A340-300 series airplanes. This proposed AD was prompted by reports of an... require, depending on airplane configuration, modifying three flight control primary computers (FCPCs...

78 FR 65187 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-10-31

.... (c) Applicability This AD applies to Airbus Model A330-301, -302, -303, -321, - 322, -323, -341, -342..., - 321, -322, -323, -341, -342, and -343 airplanes); or A340-27-4175, Revision 01, dated June 13, 2013...-3179, Revision 01, dated June 13, 2013 (for Model A330-301, -302, -303, -321, -322, -323, -341, -342...

Free-Spinning-Tunnel Tests of a 1/27-Scale Model of the Douglas XF3D-1 Airplane, TED No. NACA DE 312

NASA Technical Reports Server (NTRS)

Scher, Stanley H.

1947-01-01

Free-spinning-tunnel tests have been made on a 1/27-scale model of the Douglas XF3D-1 airplane to confirm a preliminary evaluation made of the airplane spin and recovery characteristics and previously reported. Recovery characteristics were satisfactory for erect and inverted spins when the model was in the clean condition. When the slow-down brakes were open, recoveries were slow. The pedal force necessary to reverse the airplane rudder during a spin will be within the physical capabilities of the pilot. A 10-foot-diameter parachute attached to the tail of the airplane (laid-out-flat diameter, drag coefficient 0.7) or a 4.5-foot-diameter parachute attached to the outboard wing tip will be satisfactory for emergency spin recovery from demonstration spins. If it becomes necessary for the crew to abandon the airplane during a spin, they should leave from the outboard side of the cockpit. The test results indicated spin and recovery characteristics generally similar to those indicated in the preliminary evaluation.

78 FR 47529 - Airworthiness Directives; Bombardier, Inc. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-06

... (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD... To Shorten Compliance Time The Airline Pilots Association International stated it supports the NPRM.... (c) Applicability This AD applies to Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100...

Wing Torsional Stiffness Tests of the Active Aeroelastic Wing F/A-18 Airplane

NASA Technical Reports Server (NTRS)

Lokos, William A.; Olney, Candida D.; Crawford, Natalie D.; Stauf, Rick; Reichenbach, Eric Y.

2002-01-01

The left wing of the Active Aeroelastic Wing (AAW) F/A-18 airplane has been ground-load-tested to quantify its torsional stiffness. The test has been performed at the NASA Dryden Flight Research Center in November 1996, and again in April 2001 after a wing skin modification was performed. The primary objectives of these tests were to characterize the wing behavior before the first flight, and provide a before-and-after measurement of the torsional stiffness. Two streamwise load couples have been applied. The wing skin modification is shown to have more torsional flexibility than the original configuration has. Additionally, structural hysteresis is shown to be reduced by the skin modification. Data comparisons show good repeatability between the tests.

76 FR 44246 - Special Conditions: Boeing Model 747-8 Series Airplanes; Overhead Flight Attendant Rest Compartment

Federal Register 2010, 2011, 2012, 2013, 2014

2011-07-25

...; Special Conditions No. 25-442-SC] Special Conditions: Boeing Model 747-8 Series Airplanes; Overhead Flight... conditions. SUMMARY: These special conditions are issued for Boeing Model 747-8 series airplanes. These... applied for, and was granted, an extension of time for the amended type certificate, which changed the...

NACA Photographer North American F-100A (NACA-200) Super Sabre Airplane take-off. The blowing-tupe

NASA Technical Reports Server (NTRS)

1957-01-01

NACA Photographer North American F-100A (NACA-200) Super Sabre Airplane take-off. The blowing-tupe boundary-layer control on the leading- and trailing-edge provided large reductions in takeoff and landing approach speeds. Approach speeds were reduced by about 10 knots (Mar 1960). Note: Used in publication in Flight Research at Ames; 57 Years of Development and Validation of Aeronautical Technology NASA SP-1998-3300 fig. 102 and and Memoirs of a Flight Test Engneer NASA SP-2002-4525

77 FR 5195 - Airworthiness Directives; The Boeing Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-02-02

... 747-400D series airplanes; and Model 747-200B series airplanes having a stretched upper deck. The...; and Model 747-200B series airplanes having a stretched upper deck. The original NPRM was published in... having a stretched upper deck; certificated in any category; excluding airplanes that have been converted...

Renal F4/80+CD11c+ Mononuclear Phagocytes Display Phenotypic and Functional Characteristics of Macrophages in Health and in Adriamycin Nephropathy

PubMed Central

Wang, Yiping; Wang, Xin Maggie; Lu, Junyu; Lee, Vincent W.S.; Ye, Qianling; Nguyen, Hanh; Zheng, Guoping; Zhao, Ye; Alexander, Stephen I.; Harris, David C.H.

2015-01-01

Conventional markers of macrophages (Mфs) and dendritic cells (DCs) lack specificity and often overlap, leading to confusion and controversy regarding the precise function of these cells in kidney and other diseases. This study aimed to identify the phenotype and function of renal mononuclear phagocytes (rMPs) expressing key markers of both Mфs and DCs. F4/80+CD11c+ cells accounted for 45% of total rMPs in normal kidneys and in those from mice with Adriamycin nephropathy (AN). Despite expression of the DC marker CD11c, these double-positive rMPs displayed the features of Mфs, including Mф-like morphology, high expression of CD68, CD204, and CD206, and high phagocytic ability but low antigen-presenting ability. F4/80+CD11c+ cells were found in the cortex but not in the medulla of the kidney. In AN, F4/80+CD11c+ cells displayed an M1 Mф phenotype with high expression of inflammatory mediators and costimulatory factors. Adoptive transfer of F4/80+CD11c+ cells separated from diseased kidney aggravated renal injury in AN mice. Furthermore, adoptive transfer of common progenitors revealed that kidney F4/80+CD11c+ cells were derived predominantly from monocytes, but not from pre-DCs. In conclusion, renal F4/80+CD11c+ cells are a major subset of rMPs and display Mф-like phenotypic and functional characteristics in health and in AN. PMID:25012165

77 FR 70362 - Airworthiness Directives; The Boeing Company Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-11-26

..., 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by reports of cracks in the main entry door number 1 upper main sill outer chord, along the bend radius of the chord on several airplanes...) repairs of the upper main sill outer chord of the left and right side main entry door number 1, repetitive...

78 FR 11560 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Electronic Flight Control System...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-02-19

... or unusual design feature(s) associated with an electronic flight control system with respect to... control surfaces. The Model EMB-550 airplane is designed for 8 passengers, with a maximum of 12 passengers... the pilot or copilot sidestick. The Embraer S.A. Model EMB-550 airplane has a flight control design...

A fuel-efficient cruise performance model for general aviation piston engine airplanes. Ph.D. Thesis. Final Report

NASA Technical Reports Server (NTRS)

Parkinson, R. C. H.

1983-01-01

A fuel-efficient cruise performance model which facilitates maximizing the specific range of General Aviation airplanes powered by spark-ignition piston engines and propellers is presented. Airplanes of fixed design only are considered. The uses and limitations of typical Pilot Operating Handbook cruise performance data, for constructing cruise performance models suitable for maximizing specific range, are first examined. These data are found to be inadequate for constructing such models. A new model of General Aviation piston-prop airplane cruise performance is then developed. This model consists of two subsystem models: the airframe-propeller-atmosphere subsystem model; and the engine-atmosphere subsystem model. The new model facilitates maximizing specific range; and by virtue of its implicity and low volume data storge requirements, appears suitable for airborne microprocessor implementation.

77 FR 64025 - Special Conditions: Airbus Model A318, A319, A320, and A321 Series Airplanes; Interaction of...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-10-18

... series airplanes with modification 160023 (Sharklet). These airplanes will have novel or unusual design... novel or unusual design features on the model series of airplanes listed above. It is not a rule of... Series Airplanes; Interaction of Systems and Structures AGENCY: Federal Aviation Administration (FAA...

76 FR 26957 - Special Conditions: Boeing, Model 747-8 Series Airplanes; Door 1 Extendable Length Escape Slide

Federal Register 2010, 2011, 2012, 2013, 2014

2011-05-10

...; Notice No. 25-11-12-SC] Special Conditions: Boeing, Model 747-8 Series Airplanes; Door 1 Extendable... special conditions. SUMMARY: This action proposes special conditions for the Boeing Model 747-8 airplane... Boeing Company applied for an amendment to Type Certificate Number A20WE to include the Model 747-8...

14 CFR 91.853 - Final compliance: Civil subsonic airplanes.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Final compliance: Civil subsonic airplanes... Noise Limits § 91.853 Final compliance: Civil subsonic airplanes. Except as provided in § 91.873, after... airplane subject to § 91.801(c) of this subpart, unless that airplane has been shown to comply with Stage 3...

14 CFR 91.853 - Final compliance: Civil subsonic airplanes.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Final compliance: Civil subsonic airplanes... Noise Limits § 91.853 Final compliance: Civil subsonic airplanes. Except as provided in § 91.873, after... airplane subject to § 91.801(c) of this subpart, unless that airplane has been shown to comply with Stage 3...

14 CFR 91.853 - Final compliance: Civil subsonic airplanes.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Final compliance: Civil subsonic airplanes... Noise Limits § 91.853 Final compliance: Civil subsonic airplanes. Except as provided in § 91.873, after... airplane subject to § 91.801(c) of this subpart, unless that airplane has been shown to comply with Stage 3...

14 CFR 91.853 - Final compliance: Civil subsonic airplanes.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Final compliance: Civil subsonic airplanes... Noise Limits § 91.853 Final compliance: Civil subsonic airplanes. Except as provided in § 91.873, after... airplane subject to § 91.801(c) of this subpart, unless that airplane has been shown to comply with Stage 3...

14 CFR 91.853 - Final compliance: Civil subsonic airplanes.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Final compliance: Civil subsonic airplanes... Noise Limits § 91.853 Final compliance: Civil subsonic airplanes. Except as provided in § 91.873, after... airplane subject to § 91.801(c) of this subpart, unless that airplane has been shown to comply with Stage 3...

Synthesis of Organotitanium(IV) Fluoride Phosphates and the Crystal Structure of [(C5Me4Et)TiF(µ-F){µ-O2P(OSiMe3)2}]2.

PubMed

Pevec, Andrej; Demšar, Alojz; Pinkas, Jiri; Necas, Marek

2012-03-01

The complexes [(C5Me4R)TiF(µ-F)µ-O2P(OSiMe3)2]2 [R = Me (1), Et (2)] were prepared from [(C5Me4R)TiF3]2, (R = Me, Et) and OP(OSiMe3)3. The molecular structure of 2 has been determined by single-crystal X-ray diffraction analysis. An eight-membered Ti2O4P2 metallacycle bridged by two fluorine ligands between two titanium centers is observed.

Estimated Flying Qualities of the Martin Model 202 Airplane

NASA Technical Reports Server (NTRS)

Weil, Joseph; Spear, Margaret

1947-01-01

The flying qualities of the Martin model 202 airplane have been estimated chiefly from the results of tests of an 0.0875-scale complete model with power made in the Wright Brothers tunnel at the Massachusetts Institute of Technology and from partial span wing and isolated vertical tail tests made in the Georgia Tech Nine-Foot Tunnel. These estimated handling qualities have been compared with existing Army-Navy and CAA requirements for stability and control. The results of the analysis indicate that the Martin model 202 airplane will possess satisfactory handling qualities in all respects except possibly in the following: The amount of elevator control available for landing or maneuvering in the landing condition is either marginal or insufficient when using the adjustable stabilizer linked to the flaps . Moreover, indications are that the longitudinal trim changes will be neither large nor appreciably worse with a fixed stabilizer than with the contemplated arrangement utilizing the adjustable stabilizer in an attempt to reduce the magnitude of the trim changes caused by flap deflection.

77 FR 64023 - Special Conditions: Airbus Model A318, A319, A320, and A321 Series Airplanes; Design Roll...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-10-18

... airplanes with modification 160023 (Sharklet). These airplanes will have novel or unusual design features..., A320, and A321 series airplanes because of a novel or unusual design feature, special conditions are... model that incorporates the same novel or unusual design feature, or should any other model already...

76 FR 1983 - Airworthiness Directives; The Boeing Company Model MD-11 and MD-11F Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-01-12

... assemblies of the tail tank fuel system, a wiring change, and corrective actions if necessary. This AD also requires, for certain airplanes, a general visual inspection for correct installation of the self-adhering high-temperature electrical insulation tape; installation of a wire assembly support bracket and...

Disruption of Mouse Cytochrome P450 4f14 (Cyp4f14 Gene) Causes Severe Perturbations in Vitamin E Metabolism*

PubMed Central

Bardowell, Sabrina A.; Duan, Faping; Manor, Danny; Swanson, Joy E.; Parker, Robert S.

2012-01-01

Vitamin E is a family of naturally occurring and structurally related lipophilic antioxidants, one of which, α-tocopherol (α-TOH), selectively accumulates in vertebrate tissues. The ω-hydroxylase cytochrome P450–4F2 (CYP4F2) is the only human enzyme shown to metabolize vitamin E. Using cDNA cloning, cell culture expression, and activity assays, we identified Cyp4f14 as a functional murine ortholog of CYP4F2. We then investigated the effect of Cyp4f14 deletion on vitamin E metabolism and status in vivo. Cyp4f14-null mice exhibited substrate-specific reductions in liver microsomal vitamin E-ω-hydroxylase activity ranging from 93% (γ-TOH) to 48% (γ-tocotrienol). In vivo data obtained from metabolic cage studies showed whole-body reductions in metabolism of γ-TOH of 90% and of 68% for δ- and α-TOH. This metabolic deficit in Cyp4f14−/− mice was partially offset by increased fecal excretion of nonmetabolized tocopherols and of novel ω-1- and ω-2-hydroxytocopherols. 12′-OH-γ-TOH represented 41% of whole-body production of γ-TOH metabolites in Cyp4f14−/− mice fed a soybean oil diet. Despite these counterbalancing mechanisms, Cyp4f14-null mice fed this diet for 6 weeks hyper-accumulated γ-TOH (2-fold increase over wild-type littermates) in all tissues and appeared normal. We conclude that CYP4F14 is the major but not the only vitamin E-ω-hydroxylase in mice. Its disruption significantly impairs whole-body vitamin E metabolism and alters the widely conserved phenotype of preferential tissue deposition of α-TOH. This model animal and its derivatives will be valuable in determining the biological actions of specific tocopherols and tocotrienols in vivo. PMID:22665481

Centrosymmetric [N(CH3)4]2TiF6 vs. noncentrosymmetric polar [C(NH2)3]2TiF6: A hydrogen-bonding effect on the out-of-center distortion of TiF6 octahedra

NASA Astrophysics Data System (ADS)

Kim, Eun-ah; Lee, Dong Woo; Ok, Kang Min

2012-11-01

The syntheses, structures, and characterization of organically templated zero-dimensional titanium fluoride materials, A2TiF6 (A[N(CH3)4] or [C(NH2)3]), are reported. Phase pure samples of A2TiF6 were synthesized by either solvothermal reaction method or a simple mixing method. While [N(CH3)4]2TiF6 crystallizes in a centrosymmetric space group, R-3, [C(NH2)3]2TiF6 crystallizes in a noncentrosymmetric polar space group, Cm. The asymmetric out-of-center distortion of TiF6 octahedra in polar [C(NH2)3]2TiF6 are attributable to the hydrogen-bonding interactions between the fluorine atoms in TiF6 octahedra and the nitrogen atoms in the [C(NH2)3]+ cation. Powder second-harmonic generation (SHG) measurements on the [C(NH2)3]2TiF6, using 1064 nm radiation, indicate the material has SHG efficiency of 25× that of α-SiO2, which indicates an average nonlinear optical susceptibility, exp of 2.8 pm/V. Additional SHG measurements reveal that the material is not phase-matchable (Type 1). The magnitudes of out-of-center distortions and dipole moment calculations for TiF6 octahedra will be also reported.

76 FR 65105 - Special Conditions: Gulfstream Aerospace Corporation, Model GIV-X Airplane; Isolation or Aircraft...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-20

... supplemental type certificate to install a new interior design configuration in the Gulfstream Model GIV-X... airplane. This airplane will have novel or unusual design features associated with connectivity of the... airworthiness regulations do not contain adequate or appropriate safety standards for these design features...

Development and Efficacy Assessment of an Enteric Coated Porous Tablet Loaded With F4 Fimbriae for Oral Vaccination of Piglets against F4+ Escherichia coli Infections.

PubMed

Srivastava, Atul; Gowda, D V; Madhunapantula, SubbaRao V; Siddaramaiah

2016-01-01

Enterotoxigenic Escherichia coli (ETEC) infection is one of the major causes contributing to the development of diarrhoea and mortality in new born, suckling and newly weaned piglets. To date, no preventive/treatment strategy showed promising results, which could be due to the lack of potent vaccines, and/or due to the development of resistance of ETEC to antibiotics. Therefore, in the present investigation, a novel porous sodium alginate (SA) tablet formulation loaded with F4 fimbriae antigen was developed and tested for efficacy against ETEC infections in piglet models. Precompression parameters of the powder mixes and post compression parameters of tablets have been evaluated and results were found to be satisfactory. Loading of F4 fimbrial antigens into the tablets was achieved by inducing pores in the tablets via the sublimation of camphor followed by incubation with purified F4 fimbriae. The loaded tablets have been coated with Eudragit L100 to protect the F4 fimbriae from (a) highly acidic gastric environment; (b) proteolytic cleavage by pepsin; and (c) to promote subsequent release in the intestine. Evaluation of developed F4 fimbrial tablets in a Pig model demonstrated induction of mucosal immunity, and a significant reduction of F4+ E. coli in faeces. Therefore, F4 fimbriae loaded porous tablets could be a novel oral vaccination candidate to induce mucosal and systemic immunity against ETEC infections.

Hydrothermal Syntheses and Structures of Three-Dimensional Oxo-fluorovanadium Phosphates: [H 2N(C 2H 4) 2NH 2] 0.5[(VO) 4V(HPO 4) 2(PO 4) 2F 2(H 2O) 4] · 2H 2O and K 2[(VO) 3(PO 4) 2F 2(H 2O)] · H 2O

NASA Astrophysics Data System (ADS)

Bonavia, Grant; Haushalter, R. C.; Zubieta, Jon

1996-11-01

The hydrothermal reactions of FPO3H2with vanadium oxides result in the incorporation of fluoride into V-P-O frameworks as a consequence of metal-mediated hydrolysis of the fluorophosphoric acid to produce F-and PO3-4. By exploiting this convenient source of F-, two 3-dimensional oxo-fluorovanadium phosphate phases were isolated, [H2N(C2H4)2NH2]0.5[(VO)4V(HOP4)2(PO4)2F2(H2O)4) · 2H2O (1 · 2H2O) and K2[(VO)3(PO4)2F2(H2O)] · H2O (2 · H2O). Both anionic frameworks contain (VIVO)-F--phosphate layers, with confacial bioctahedral {(VIVO)2FO6} units as the fundamental motif. In the case of 1, the layers are linked through {VIIIO6} octahedra, while for 2 the interlayer connectivity is provided by edge-sharing {(VIVO)2F2O6} units. Crystal data are 1 · 2H2O, CH10FN0.5O13P2V2.5, monoclinicC2/m,a= 18.425(4) Å,c= 8.954(2) Å, β = 93.69(2)0,V= 1221.1(4) Å3,Z= 4,Dcalc= 2.423 g cm-3; 2 · H2O, H4F2K2O13P2V3, triclinicPoverline1,a= 7.298(1) Å,b= 8.929(2) Å,c = 10.090(2) Å, α = 104.50(2)0, β = 100.39(2)0, δ = 92.13(2)0,V= 623.8(3) Å3,Z= 2,Dcalc= 2.891 g cm-3.

Blended Buffet-Load-Alleviation System for Fighter Airplane

NASA Technical Reports Server (NTRS)

Moses, Robert W.

2005-01-01

The capability of modern fighter airplanes to sustain flight at high angles of attack and/or moderate angles of sideslip often results in immersion of part of such an airplane in unsteady, separated, vortical flow emanating from its forebody or wings. The flows from these surfaces become turbulent and separated during flight under these conditions. These flows contain significant levels of energy over a frequency band coincident with that of low-order structural vibration modes of wings, fins, and control surfaces. The unsteady pressures applied to these lifting surfaces as a result of the turbulent flows are commonly denoted buffet loads, and the resulting vibrations of the affected structures are known as buffeting. Prolonged exposure to buffet loads has resulted in fatigue of structures on several airplanes. Damage to airplanes caused by buffeting has led to redesigns of airplane structures and increased support costs for the United States Air Force and Navy as well as the armed forces of other countries. Time spent inspecting, repairing, and replacing structures adversely affects availability of aircraft for missions. A blend of rudder-control and piezoelectric- actuator engineering concepts was selected as a basis for the design of a vertical-tail buffet-load-alleviation system for the F/A-18 airplane. In this system, the rudder actuator is used to control the response of the first tail vibrational mode (bending at a frequency near 15 Hz), while directional patch piezoelectric actuators are used to control the second tail vibrational mode (tip torsion at a frequency near 45 Hz). This blend of two types of actuator utilizes the most effective features of each. An analytical model of the aeroservoelastic behavior of the airplane equipped with this system was validated by good agreement with measured results from a full-scale ground test, flight-test measurement of buffet response, and an in-flight commanded rudder frequency sweep. The overall performance of the

Ditching Investigation of a 1/24-Scale Model of the Boeing B-47 Airplane

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; Windham, John O.

1950-01-01

An investigation of a 1/24-scale dynamically similar model of the Boeing B-47 airplane was made to determine the ditching characteristics and proper ditching technique for the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion-picture records, and time-history deceleration records. The results of the investigation are presented in table form, photographs, and curves. The airplane should be ditched at the lowest speed and highest attitude consistent with adequate control; the flaps should be full down. The airplane will probably make a deep but fairly smooth run. The fuselage bottom will be damaged and partially filled with water; consequently, crew members should be assigned ditching stations near an exit in the upper or forward part of the fuselage. The nacelles may be expected to be torn away from the wing. In calm water the maximum decelerations will be about 3g and the landing run will be about 6 fuselage lengths.

75 FR 81430 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-28

... skin and the skin splice plate; for certain airplanes, an inspection for steel cross-shaped doublers on... body skin and the skin splice plate; for certain airplanes, an inspection for steel cross- shaped... done on these 14 airplanes can be unique to each airplane and are different from the repair...

Full-Scale Hydrodynamic Evaluation of a Modified Navy J4F-2 Amphibian with a 0.425-Scale XP5M-1 Hull Bottom. TED No. NACA DE325

NASA Technical Reports Server (NTRS)

Land, Norman S.; Elliott, John M.; Christopher, Kenneth W.

1949-01-01

An investigation was made to evaluate the hydrodynamic qualities of a 0.425-scale model of the Navy XP5M-1 hull, which was installed on a modified Navy J4F-2 amphibian. Longitudinal and directional stability during take-off and landing, low-speed maneuverability, spray characteristics, and take-off performance were investigated. The behavior of the airplane in moderately rough water was also observed. The opinions of three pilots have been correlated with the data.

High-Speed Wind-Tunnel Investigation of the Lateral Stability Characteristics of a 0.10-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE 301

NASA Technical Reports Server (NTRS)

Polhamus, Edward C.; King, Thomas J., Jr.

1949-01-01

An investigation was made in the Langley high-speed 7- by 10-foot tunnel to determine the high-speed lateral and directional stability characteristics of a 0.10-scale model of the Grumman XF9F-2 airplane in the Mach number range from 0.40 to 0.85. The results indicate that static lateral and directional stability is present throughout the Mach number range investigated although in the Mach number range from 0.75 to 0.85 there is an appreciable decrease in rolling moment due to sideslip. Calculations of the dynamic stability indicate that according to current flying-quality requirements the damping of the lateral oscillation, although probably satisfactory for the sea-level condition, may not be satisfactory for the majority of the altitude conditions investigated

Renal F4/80+ CD11c+ mononuclear phagocytes display phenotypic and functional characteristics of macrophages in health and in adriamycin nephropathy.

PubMed

Cao, Qi; Wang, Yiping; Wang, Xin Maggie; Lu, Junyu; Lee, Vincent W S; Ye, Qianling; Nguyen, Hanh; Zheng, Guoping; Zhao, Ye; Alexander, Stephen I; Harris, David C H

2015-02-01

Conventional markers of macrophages (Mфs) and dendritic cells (DCs) lack specificity and often overlap, leading to confusion and controversy regarding the precise function of these cells in kidney and other diseases. This study aimed to identify the phenotype and function of renal mononuclear phagocytes (rMPs) expressing key markers of both Mфs and DCs. F4/80(+)CD11c(+) cells accounted for 45% of total rMPs in normal kidneys and in those from mice with Adriamycin nephropathy (AN). Despite expression of the DC marker CD11c, these double-positive rMPs displayed the features of Mфs, including Mф-like morphology, high expression of CD68, CD204, and CD206, and high phagocytic ability but low antigen-presenting ability. F4/80(+)CD11c(+) cells were found in the cortex but not in the medulla of the kidney. In AN, F4/80(+)CD11c(+) cells displayed an M1 Mф phenotype with high expression of inflammatory mediators and costimulatory factors. Adoptive transfer of F4/80(+)CD11c(+) cells separated from diseased kidney aggravated renal injury in AN mice. Furthermore, adoptive transfer of common progenitors revealed that kidney F4/80(+)CD11c(+) cells were derived predominantly from monocytes, but not from pre-DCs. In conclusion, renal F4/80(+)CD11c(+) cells are a major subset of rMPs and display Mф-like phenotypic and functional characteristics in health and in AN. Copyright © 2015 by the American Society of Nephrology.

76 FR 10482 - Special Conditions: Boeing Model 787-8 Airplane; Overhead Flightcrew-Rest Compartment Occupiable...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-02-25

... Boeing Model 787-8 airplane. This airplane will have novel or unusual design features associated with an... standards for this design feature. These special conditions contain the additional safety standards that the... airworthiness standards. Additional special conditions will be issued for other novel or unusual design features...

78 FR 69597 - Airworthiness Directives; Piaggio Aero Industries S.p.A Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-11-20

... Industries S.p.A Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... (AD) for Piaggio Aero Industries S.p.A Model P-180 airplanes that would supersede an existing AD. This... proposed AD, contact Piaggio Aero Industries S.p.A-Airworthiness Office, Via Luigi Cibrario, 4-16154 Genova...

76 FR 47427 - Airworthiness Directives; The Boeing Company Model 747-400 and -400F Series Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-05

... the products listed above. This AD requires a general visual inspection for cracks and holes of the... Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle... published in the Federal Register on February 10, 2011 (76 FR 7513). The NPRM proposed a general visual...

Solvothermal indium fluoride chemistry: Syntheses and crystal structures of K{sub 5}In{sub 3}F{sub 14}, beta-(NH{sub 4}){sub 3}InF{sub 6} and [NH{sub 4}]{sub 3}[C{sub 6}H{sub 21}N{sub 4}]{sub 2}[In{sub 4}F{sub 21}

DOE Office of Scientific and Technical Information (OSTI.GOV)

Jayasundera, Anil C.A.; Goff, Richard J.; Li Yang

2010-02-15

The solvothermal syntheses and crystal structures of three indium fluorides are presented. K{sub 5}In{sub 3}F{sub 14} (1) and beta-(NH{sub 4}){sub 3}InF{sub 6} (2) are variants on known inorganic structure types chiolite and cryolite, respectively, with the latter exhibiting a complex and apparently novel structural distortion. [NH{sub 4}]{sub 3}[C{sub 6}H{sub 21}N{sub 4}]{sub 2}[In{sub 4}F{sub 21}] (3) represents a new hybrid composition displaying a unique trimeric metal fluoride building unit. - Graphical abstract: Solvothermal synthesis has been used to prepare three indium fluorides, including a novel hybrid material containing a unique [In{sub 3}F{sub 15}] trimer templated by tren.