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Sample records for f4c airplane model

  1. 75 FR 39804 - Airworthiness Directives; The Boeing Company Model 757 Airplanes, Model 767 Airplanes, and Model...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-13

    ... Model 757 Airplanes, Model 767 Airplanes, and Model 777-200 and -300 Series Airplanes AGENCY: Federal... directive (AD) for certain Model 757 airplanes, Model 767 airplanes, and Model 777-200 and -300 series...) that would apply to certain Model 757 airplanes, Model 767 airplanes, and Model 777-200 and -300...

  2. MLS: Airplane system modeling

    NASA Technical Reports Server (NTRS)

    Thompson, A. D.; Stapleton, B. P.; Walen, D. B.; Rieder, P. F.; Moss, D. G.

    1981-01-01

    Analysis, modeling, and simulations were conducted as part of a multiyear investigation of the more important airplane-system-related items of the microwave landing system (MLS). Particular emphasis was placed upon the airplane RF system, including the antenna radiation distribution, the cabling options from the antenna to the receiver, and the overall impact of the airborne system gains and losses upon the direct-path signal structure. In addition, effort was expended toward determining the impact of the MLS upon the airplane flight management system and developing the initial stages of a fast-time MLS automatic control system simulation model. Results ot these studies are presented.

  3. 76 FR 61645 - Airworthiness Directives; Airbus Model A330-200 Series Airplanes; Model A330-300 Series Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-05

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Model A330-200 Series Airplanes; Model A330-300 Series Airplanes; Model A340-200 Series Airplanes; and Model A340... November 21, 2011. ADDRESSES: You may send comments by any of the following methods: Federal...

  4. 76 FR 4219 - Airworthiness Directives; Airbus Model A330-200 Series Airplanes; Model A330-300 Series Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-25

    ...-279-AD; Amendment 39-16583; AD 2011-02-09] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330-200 Series Airplanes; Model A330-300 Series Airplanes; Model A340-200 Series Airplanes; and Model A340... comments on this AD by March 11, 2011. ADDRESSES: You may send comments by any of the following...

  5. 75 FR 28463 - Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model BAe 146 Airplanes and Model Avro...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-21

    ...-16301; AD 2010-10-22] RIN 2120-AA64 Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model BAe 146 Airplanes and Model Avro 146-RJ Airplanes AGENCY: Federal Aviation Administration (FAA... airworthiness directive (AD), which applies to Model BAe 146 airplanes and Model Avro 146-RJ airplanes. That...

  6. 75 FR 10701 - Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model BAe 146 Airplanes and Model Avro...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-09

    ... (Operations) Limited Model BAe 146 Airplanes and Model Avro 146-RJ Airplanes AGENCY: Federal Aviation... directive (AD) that applies to all Model BAe 146 airplanes and Model Avro 146-RJ airplanes. The original.... ADDRESSES: You may send comments by any of the following methods: Federal eRulemaking Portal: Go to...

  7. 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.

  8. F-16XL Basic Airplane Model in the BART

    NASA Technical Reports Server (NTRS)

    1994-01-01

    4% F-16XL model in BART. Model configuration is the basic airplane, with air dams and missiles. Tests in the tunnel included surface pressures, 5 hole probe, and on and off surface flow visualization.

  9. Mathematical model of induced flow on the airplane vertical tail

    NASA Astrophysics Data System (ADS)

    Rotaru, Constantin; Cîrciu, Ionicǎ; Edu, Raluca Ioana

    2016-06-01

    In this paper is presented a mathematical model of the flow around the vertical tail of an airplane, based on the general elements of the aerodynamic design, with details leading to the separate formulation of the Fourier coefficients in the series solution of the Prandtl's lifting-line equation. Numerical results are obtained in Maple soft environment, for a standard configuration of an airplane geometry. The results include the discussion of the vortex model for the sidewash gradient on the vertical stabilizer.

  10. 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.

  11. 78 FR 73993 - Special Conditions: Cessna Model 680 Series Airplanes; Aircraft Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-10

    ...These special conditions are issued for the Cessna Model 680 Series airplanes. These airplanes will have a novel or unusual design feature associated with the architecture and connectivity capabilities of the airplanes' computer systems and networks. Connectivity to, or access by, external systems and networks may result in security vulnerabilities to the airplanes' systems. The proposed......

  12. An evaluation of aerodynamics modeling of spinning light airplanes

    NASA Technical Reports Server (NTRS)

    Pamadi, B. N.; Taylor, L. W., Jr.

    1983-01-01

    This paper extends the application of the modified strip theory for wing body combination of a spinning light airplane reported earlier. In addition, to account for the contribution of the tail plane, the shielding effect on vertical tail under steady state spin condition is modeled from basic aerodynamic considerations. The results of this combined analysis, presented for some light airplane configurations, are shown to be in good agreement with spin tunnel rotary balance test data.

  13. 78 FR 63845 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Isolation or Airplane Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-25

    ..., 2000 (65 FR 19477-19478), as well as at http://DocketsInfo.dot.gov/ . Docket: Background documents or...; Isolation or Airplane Electronic System Security Protection From Unauthorized Internal Access AGENCY... control surfaces. The Model EMB-550 airplane is designed for 8 passengers, with a maximum of 12...

  14. 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.

  15. 76 FR 28683 - Airworthiness Directives; Airbus Model A330 and A340 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-18

    ... was published on March 22, 2011 (76 FR 15872) for Model A330-200 and -300 series airplanes. That NPRM..., 2011 (76 FR 8612) for Model A340-200, -300, -500, and -600 series airplanes. That AD requires revising... Directives; Airbus Model A330 and A340 Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  16. 75 FR 6092 - Special Conditions: Model C-27J Airplane; Class E Cargo Compartment Lavatory

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-08

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Model C-27J Airplane; Class E Cargo.... SUMMARY: These special conditions are issued for the Alenia Model C-27J airplane. This airplane has novel... certification of a twin-engine, commercial transport designated as the Model C-27J. The C-27J is a...

  17. 75 FR 60667 - Airworthiness Directives; Learjet Inc. Model 45 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-01

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Learjet Inc. Model... rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Model 45 airplanes... AD by November 15, 2010. ADDRESSES: You may send comments by any of the following methods: Federal...

  18. 75 FR 32255 - Airworthiness Directives; Learjet Inc. Model 60 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-08

    ... Register on May 29, 2009 (74 FR 25682). That NPRM proposed to require revising the Tire-Servicing section... higher gross weight and tire pressure than the Model 55 airplane. In addition, a review of the hydraulic... 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR...

  19. 78 FR 76248 - Special Conditions: Airbus, Model A350-900 Series Airplane; Side Stick Controller

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-17

    ..., 2000 (65 FR 19477-19478), as well as at http:// DocketsInfo.dot.gov/ . Docket: Background documents or... A350-900 Series Airplane; Side Stick Controller AGENCY: Federal Aviation Administration (FAA), DOT... Airbus Model A350-900 series airplanes. These airplanes will have a novel or unusual design...

  20. 78 FR 73995 - Special Conditions: Cessna Model 680 Series Airplanes; Aircraft Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-10

    ...These special conditions are issued for the Cessna Model 680 series airplanes. These airplanes will have novel or unusual design features associated with connectivity of the passenger service computer systems to the airplane critical systems and data networks. The network architecture is composed of several connected networks including the following: 1. Flight-Safety related control and......

  1. 76 FR 53348 - Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model BAe 146 Airplanes and Model Avro...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-26

    ... (Operations) Limited Model BAe 146 Airplanes and Model Avro 146-RJ Airplanes AGENCY: Federal Aviation... send comments by any of the following methods: Federal eRulemaking Portal: Go to http://www.regulations... proposed AD. Discussion On May 3, 2010, we issued AD 2010-10-22, Amendment 39-16301 (75 FR 28463, May...

  2. 76 FR 2281 - Airworthiness Directives; BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 Airplanes, and Model...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-13

    ... (OPERATIONS) LIMITED Model BAe 146 Airplanes, and Model Avro 146-RJ Airplanes AGENCY: Federal Aviation... comments by any of the following methods: Federal eRulemaking Portal: Go to http://www.regulations.gov... this proposed AD. Discussion On June 14, 2005, we issued AD 2005-13-19, Amendment 39-14156 (70 FR...

  3. 78 FR 14007 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Electrical/Electronic Equipment Bay...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-04

    ...These special conditions are issued for the Embraer S.A. Model EMB-550 airplane. This airplane will have novel or unusual design features, specifically distributed electrical and electronic equipment bays in pressurized areas of the airplane. Older transport category airplane electrical/electronic equipment bay installations are located in the lower lobe where the flight crew could determine......

  4. 75 FR 46868 - Airworthiness Directives; The Boeing Company Model 747 Airplanes and Model 767 Airplanes Equipped...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-04

    ... airplanes. That original NPRM was published in the Federal Register on April 7, 2008 (73 FR 18721). That... Relevant Rulemaking Related NPRM, Docket FAA-2008-0403, Directorate Identifier 2007-NM- 166-AD (73 FR 18719... Global Supply Systems (Global) requests that we revise AD 2007-12- 07, Amendment 39-15085 (72 FR...

  5. 76 FR 27872 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-13

    ... INDUSTRIES S.p.A Model P- 180 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ] ACTION: Final... known U.S. owners and operators of PIAGGIO AERO INDUSTRIES S.p.A (Piaggio) Model PIAGGIO P-180 airplanes... fuselage on a number of Piaggio Model P.180 aeroplanes, which resulted in jamming of the flight...

  6. 76 FR 68368 - Airworthiness Directives; DASSAULT AVIATION Model MYSTERE-FALCON 900 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-04

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will... Model MYSTERE-FALCON 900 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... DASSAULT AVIATION Model MYSTERE-FALCON 900 airplanes. This proposed AD results from mandatory...

  7. 76 FR 68366 - Airworthiness Directives; The Boeing Company Model 777-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-04

    ... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will... Directives; The Boeing Company Model 777-200 and - 300 Series Airplanes AGENCY: Federal Aviation... airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes....

  8. 75 FR 21528 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-26

    ... Policies and Procedures (44 FR 11034, February 26, 1979), and 3. Will not have a significant economic... Douglas Corporation Model MD- 90-30 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... certain Model MD-90-30 airplanes. This proposed AD would require inspecting for corrosion of the...

  9. 76 FR 54093 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-31

    ... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or.... Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of.... Applicability (c) This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes, certificated...

  10. 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.

  11. 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.

  12. 77 FR 75071 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Electrical/Electronic Equipment Bay...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-12-19

    ... Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478... Model EMB-550 airplane. The Model EMB-550 airplane is the first of a new family of jet airplanes... mounted on aft fuselage pylons. Each engine produces approximately 6,540 pounds of thrust for...

  13. 78 FR 76254 - Special Conditions: Airbus, Model A350-900 Series Airplane; Control Surface Awareness and Mode...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-17

    ..., 2000 (65 FR 19477-19478), as well as at http://DocketsInfo.dot.gov/ . Docket: Background documents or... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Airbus, Model A350-900 Series Airplane... Model A350-900 series airplanes. These airplanes will have a novel or unusual design...

  14. 76 FR 9265 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System: Control...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-17

    ... Model GVI Airplane; Electronic Flight Control System: Control Surface Position Awareness AGENCY: Federal... transport category airplanes. These design features include an electronic flight control system. The..., include with your comments a self-addressed, stamped postcard on which you have written the docket...

  15. Transonic Flutter Investigation of Models of T-Tail of Blackburn NA-39 Airplane

    NASA Technical Reports Server (NTRS)

    Jones, George W., Jr.; Farmer, Moses G.

    1959-01-01

    A transonic flutter investigation has been made of models of the T-tail of the Blackburn NA-39 airplane. The models were dynamically and elastically scaled from measured airplane data in accordance with criteria which include a flutter safety margin. The investigation was made in the Langley transonic blowdown tunnel and covered a Mach number range from 0.73 to 1.09 at simulated altitudes extending to below sea level. The results of the investigation indicated that, if differences between the measured model and scaled airplane properties are disregarded, the airplane with the normal value of stabilizer pitching stiffness should have a stiffness margin of safety of at least 32 percent at all Mach numbers and altitudes within the flight boundary. However, the airplane with the emergency value of stabilizer pitching stiffness would not have the required margin of safety from symmetrical flutter at Mach numbers greater than about 0.85 at low altitudes. First-order corrections for some differences between the measured model and scaled airplane properties indicated that the airplane with the normal value of stabilizer pitching stiffness would still have an adequate margin of safety from flutter and that the flutter safety margin for the airplane with the emergency value of stabilizer pitching stiffness would be changed from inadequate to adequate. However, the validity of the corrections is questionable.

  16. 76 FR 35736 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane Automatic Power Reserve...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-20

    .... This airplane will have a novel or unusual design feature associated with go-around performance credit... you wish to review the docket in person, go to the address in the ADDRESSES section of this preamble... regulations. Discussion GALP is proposing to use the APR function of the Model G250 airplane during...

  17. 78 FR 11609 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Landing Pitchover Condition

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-19

    ...This action proposes special conditions for the Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design feature(s) associated with landing loads due to the automatic braking system. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These proposed special conditions contain the additional......

  18. 76 FR 35324 - Special Conditions: Boeing Model 787 Series Airplanes; Seats With Inflatable Lapbelts

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-17

    ...These special conditions are issued for the Boeing Model 787 series airplane. These airplanes will have a novel or unusual design feature(s) associated with seats with inflatable lapbelts. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the......

  19. 75 FR 8465 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-25

    ... Model MD-90-30 airplanes. That NPRM was published in the Federal Register on September 4, 2009 (74 FR... ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), and (3) Will... airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal...

  20. 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.

  1. Application of a performance modeling technique to an airplane with variable sweep wings

    NASA Technical Reports Server (NTRS)

    Redin, P. C.

    1981-01-01

    A performance modeling concept previously applied to an F-104F G and a YF-12C airplane was applied to an F-111A airplane. This application extended the concept to an airplane with variable sweep wings. The performance model adequately matched flight test data for maneuvers flown at different wing sweep angles at maximum afterburning and intermediate power settings. For maneuvers flown at less than intermediate power, including dynamic maneuvers, the performance model was not validated because the method used to correlate model and in-flight power setting was not adequate. Individual dynamic maneuvers were matched sucessfully by using adjustments unique to each maneuver.

  2. 76 FR 14819 - Special Conditions: Boeing Model 747-8 Series Airplanes; Stairway Between the Main Deck and Upper...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-18

    ... provided so, when measured along the center lines of each tread and landing, the illumination is not less... conditions for the Boeing Model 747-8 airplane. This airplane will have novel or unusual design features when... airplanes. These design features include a stairway between the main deck and upper deck. These...

  3. 76 FR 31451 - Special Conditions: Boeing Model 747-8 Airplanes; Stairway Between the Main Deck and Upper Deck

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-01

    ...These special conditions are issued for Boeing Model 747-8 airplanes. This airplane will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. These design features include a stairway between the main deck and upper deck. These special conditions contain the additional safety standards that the......

  4. Modeling and analyzing characteristics of self-infrared radiation on airplane-skin

    NASA Astrophysics Data System (ADS)

    Li, Zhaozhao; Wu, Wenyuan; Wu, Chengguo; Yang, Yuntao; Huang, Yanhua; Sunxiaobo, Zhuan

    2016-01-01

    The characteristic of the self-infrared radiation of airplane-skin is very important for the stealth performance of airplane. Based on the theory of the airplane-skin temperature field, the distribution of the atmospheric temperature field and the principle of the black-body radiation function the self-infrared radiation model was established. In specified flight conditions, the influence of the atmospheric temperature, the speed of flight, the emissivity and the sight angle detection on the self-infrared radiation of the airplane skin were analyzed. Through the simulation of infrared radiation, some results under different flight states are obtained. The simulation results show that skin infrared radiation energy mainly concentrate on the far infrared wavebands, and various factors have different effects on the infrared radiation of skin. This conclusion can help reduce the infrared radiation and improve the stealth performance of airplane in the engineering design and the selection of flight conditions.

  5. Evaluation of an aeroelastic model technique for predicting airplane buffet loads

    NASA Technical Reports Server (NTRS)

    Hanson, P. W.

    1973-01-01

    A wind-tunnel technique which makes use of a dynamically scaled aeroelastic model to predict full-scale airplane buffet loads during buffet boundary penetration is evaluated. A 1/8-scale flutter model of a fighter airplane with remotely controllable variable-sweep wings and trimming surfaces was used for the evaluation. The model was flown on a cable-mount system which permitted high lift forces comparable to those in maneuvering flight. Bending moments and accelerations due to buffet were measured on the flutter model and compared with those measured on the full-scale airplane in an independent flight buffet research study. It is concluded that the technique can provide valuable information on airplane buffet load characteristics not available from any other source except flight test.

  6. 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.

  7. 76 FR 37251 - Airworthiness Directives; Dassault Aviation Model FALCON 7X Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-27

    ...We are adopting a new airworthiness directive (AD) for the products listed above. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires that, as of the effective date of the AD, operation of Model FALCON 7X airplanes is prohibited. This AD was prompted by a report of an uncontrolled pitch trim runaway during descent. We are issuing......

  8. 76 FR 17334 - Special Conditions: Boeing Model 747-2G4B Airplane; Certification of Cooktops

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-29

    ...These special conditions are issued for the Boeing Model 747- 2G4B series airplane. This airplane, as modified by Greenpoint Technologies, Inc., will have a novel or unusual design feature associated with the replacement and re-certification of existing cooktops with advanced technology induction coil cooktops in the main deck galleys on two Boeing Model 747-2G4B airplanes. The proposed......

  9. 77 FR 69573 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Electronic Flight Control System...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-20

    ... Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as...-135 (76 FR 74654, December 1, 2011), effective January 30, 2012. (This amendment is not in the Model... Model EMB-550 airplane. The Model EMB-550 airplane is the first of a new family of jet...

  10. Scaling behavior of an airplane-boarding model.

    PubMed

    Brics, Martins; Kaupužs, Jevgenijs; Mahnke, Reinhard

    2013-04-01

    An airplane-boarding model, introduced earlier by Frette and Hemmer [Phys. Rev. E 85, 011130 (2012)], is studied with the aim of determining precisely its asymptotic power-law scaling behavior for a large number of passengers N. Based on Monte Carlo simulation data for very large system sizes up to N=2(16)=65536, we have analyzed numerically the scaling behavior of the mean boarding time and other related quantities. In analogy with critical phenomena, we have used appropriate scaling Ansätze, which include the leading term as some power of N (e.g., [proportionality]N(α) for ), as well as power-law corrections to scaling. Our results clearly show that α=1/2 holds with a very high numerical accuracy (α=0.5001±0.0001). This value deviates essentially from α=/~0.69, obtained earlier by Frette and Hemmer from data within the range 2≤N≤16. Our results confirm the convergence of the effective exponent α(eff)(N) to 1/2 at large N as observed by Bernstein. Our analysis explains this effect. Namely, the effective exponent α(eff)(N) varies from values about 0.7 for small system sizes to the true asymptotic value 1/2 at N→∞ almost linearly in N(-1/3) for large N. This means that the variation is caused by corrections to scaling, the leading correction-to-scaling exponent being θ≈1/3. We have estimated also other exponents: ν=1/2 for the mean number of passengers taking seats simultaneously in one time step, β=1 for the second moment of t(b), and γ≈1/3 for its variance. PMID:23679383

  11. 75 FR 64963 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-21

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic.... Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes, certificated in any category, equipped...

  12. 75 FR 35624 - Airworthiness Directives; Fokker Services B.V. Model F.27 Mark 500 and 600 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-23

    ... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or.... Model F.27 Mark 500 and 600 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of.... Applicability (c) This AD applies to Fokker Services B.V. Model F.27 Mark 500 and 600 airplanes; certified...

  13. 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.

  14. 76 FR 19724 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-08

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will... B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively... A300 B4-605R and B4-622R airplanes, Model A300 F4-605R and F4-622R airplanes, and Model A300...

  15. 76 FR 53305 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-26

    ... (76 FR 8610, February 15, 2011), addresses Model A340-200, -300, -500, and -600 series airplanes. (2...-211-AD; Amendment 39-16773; AD 2011-17-09] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330... reference of a certain other publication listed in this AD as of June 7, 2006 (71 FR 25919, May 3,...

  16. 76 FR 27220 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-11

    ...-091-AD; Amendment 39-16688; AD 2011-10-07] RIN 2120-AA64 Airworthiness Directives; Airbus Model A310..., 2011 (76 FR 34). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI... Model A310-203 and A310-222 airplanes: Repetitive detailed inspections for cracking of the leading...

  17. 76 FR 34918 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-15

    ... Model 757 and Model 747 airplanes. We have issued AD 2010-23-13, Amendment 39-16502 (75 FR 68688... 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... proposing this AD to prevent flammable fluid from leaking onto the engine exhaust nozzle which could...

  18. 76 FR 15872 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-22

    ... issued AD 2006-09-07, Amendment 39-14577 (71 FR 25919, May 3, 2006), that applies to Airbus Model A330... FR 8610, February 15, 2011), for Airbus Model A340-200, -300, -500, and -600 series airplanes, to... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3....

  19. 75 FR 38950 - Airworthiness Directives; The Boeing Company Model 727 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-07

    ..., Amendment 39-16223 (75 FR 13225, March 19, 2010), applies to Boeing Model 737-100, -200, -200C, -300, -400, and, -500 series airplanes. AD 2007-19-07, Amendment 39-15198 (72 FR 60244, October 24, 2007), applies...-16096 (74 FR 62217, November 27, 2009) applies to certain Boeing Model 777-200, -200LR, -300,...

  20. Tests on an airplane model, AEG D I of the Allgemeine Elektricitats Gesellschft, A-G, airplane construction section conducted at the Gottingen Model Testing Laboratory for Aerodynamics

    NASA Technical Reports Server (NTRS)

    Munk, Max; Molthan, Wilhelm

    1923-01-01

    Tests were carried out in the small wind tunnel of the Gottingen establishment on a complete model of the AEG D I airplane. The agreement between the model and the complete airplane applies particularly to the wings, which have ribs cut out of sheet metal and built up in exactly the same manner as in the actual airplane. Various series of tests were carried out with this model in which one or the other of the control surfaces were adjusted to various angles, while the others remained in their neutral positions. During the first three series of tests, the stabilizer was set at a positive angle of 3 degrees, 45' relative to the axis of the engine crankshaft, after which further tests at a 6 degree 30' we made. Finally, the model was tested with the tail group removed. With the elevators set in the prescribed positions, the lift, the drag, and the moments about an axis passing through the center of gravity and perpendicular to the plane of symmetry were measured. All three sets of readings are given as absolute coefficients. Where one of the other control surfaces was deflected from its normal position, the moment produced by that adjustment of the surface was also measured.

  1. 78 FR 66317 - Special Conditions: Learjet Inc. Model LJ-200-1A10; Airplane Fuselage Post-Crash Fire Survivability

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-05

    ... Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478.... Model LJ-200-1A10; Airplane Fuselage Post-Crash Fire Survivability AGENCY: Federal Aviation... conditions for the Learjet Inc. Model LJ-200-1A10 airplane. This airplane will have a novel or unusual...

  2. 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

    ...-SC for the GALP Model G280 airplane was published in the Federal Register on May 25, 2011 (76 FR... G280 Airplane Pilot-Compartment View--Hydrophobic Coatings in Lieu of Windshield Wipers AGENCY: Federal... unusual design feature associated with the pilot-compartment view through a hydrophobic windshield...

  3. 77 FR 5990 - Special Conditions: Learjet Inc., Model LJ-200-1A10 Airplane, Pilot-Compartment View Through...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-02-07

    ... Learjet Model LJ-200-1A10 airplane was published in the Federal Register on October 14, 2011 (76 FR 63851... Airplane, Pilot-Compartment View Through Hydrophobic Windshield Coatings in Lieu of Windshield Wipers... or unusual design feature associated with hydrophobic windshield coatings in lieu of...

  4. 76 FR 41667 - Airworthiness Directives; Hawker Beechcraft Corporation Models B300 and B300C (C-12W) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-15

    ... Corporation Models B300 and B300C (C-12W) airplanes. This AD was prompted by an error found in the take-off... decision speed (V 1 ). This could result in the airplane running out of runway before take-off can be... runway before take-off can be accomplished. We are issuing this AD to correct the unsafe condition...

  5. 78 FR 76731 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Rechargeable Lithium...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-19

    ... battery systems special conditions adopted for the Boeing Model 787 (72 FR 57842; October 11, 2007..., -300, and -300ER series airplanes, was published in the Federal Register on August 22, 2013 (78 FR... Series Airplanes; Rechargeable Lithium Ion Batteries and Battery Systems AGENCY: Federal...

  6. 78 FR 6198 - Special Conditions: Airbus, Model A318-112 Airplane (S/N 3238); Certification of Cooktops

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-01-30

    ...These special conditions are issued for the Airbus Model A318- 112 airplane, serial number (S/N) 3238. This airplane, as modified by Fokker Services B.V., will have a novel or unusual design feature associated with a cooktop installation. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain......

  7. 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

    ...These special conditions are issued for Boeing Model 747-8 airplanes. These airplanes will have a novel or unusual design feature associated with an extendable length escape slide. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator......

  8. 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

    ...-243F Airplanes Equipped With Rolls Royce Trent 700 Series Engines AGENCY: Federal Aviation... AD applies to Airbus Model A330-243F airplanes; certificated in any category; equipped with Rolls... 39-12221 (66 FR 23838, May 10, 2001] * * * is issued to extend the applicability to the...

  9. 75 FR 2433 - Special Conditions: Boeing Model 747-8/-8F Airplanes, Systems and Data Networks Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-15

    ... Federal Register on October 2, 2009 (74 FR 50926). No comments were received. Applicability As discussed... Administration 14 CFR Part 25 Special Conditions: Boeing Model 747-8/-8F Airplanes, Systems and Data Networks Security--Protection of Airplane Systems and Data Networks From Unauthorized External Access...

  10. 76 FR 5061 - Special Conditions: TTF Aerospace, LLC, Modification to Boeing Model 767-300 Series Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-28

    ...These special conditions are issued for the Boeing Model 767- 300 series airplane. This airplane, as modified by TTF Aerospace, LLC, will have a novel or unusual design features associated with the pilot lower lobe crew rest module (CRM). The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain......

  11. 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

    ...These special conditions are issued for the Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design feature(s) associated with the control surface awareness and mode annunciation of the electronic flight control system. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special......

  12. 76 FR 14794 - Special Conditions: Boeing Model 747-8 Airplanes, Systems and Data Networks Security-Isolation or...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-18

    ... Boeing Model 747-8 airplane was published in the Federal Register on December 9, 2010 (75 FR 76647). No... design features associated with connectivity of the passenger domain computer systems to the airplane... connected networks. The network architecture would be used for a diverse set of functions, including:...

  13. 78 FR 70848 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-27

    ... the EFB architecture and existing airplane network systems. The applicable airworthiness regulations... interface to existing aircraft systems. The proposed network architecture is used for a diverse set of... architecture and network configuration in the Boeing Model 777- 200, -300, and -300ER series airplanes...

  14. 75 FR 70090 - Special Conditions: Bombardier Inc. Model CL-600-2E25 Airplane, Operation Without Normal...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-17

    ... (APU)-generated electrical power. Service experience on other airplane models with similar electrical... engine generators or APU, is not extremely improbable. Thus, it must be demonstrated that the airplane... landing with inoperative normal engine- and APU-generated electrical power (for example,...

  15. 78 FR 11554 - Special Conditions: Embraer S.A., Model EMB-550 Airplane, Limit Pilot Forces for Sidestick Control

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-19

    ...These special conditions for the Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design feature, specifically sidestick controllers designed to be operated with only one hand. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards......

  16. 78 FR 5146 - Special Conditions: Embraer S.A., Model EMB-550 Airplane, Dive Speed Definition With Speed...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-01-24

    ... Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477 19478), as well as...., Model EMB-550 Airplane, Dive Speed Definition With Speed Protection System AGENCY: Federal Aviation... category airplanes. These design features include a high-speed protection system. The...

  17. 77 FR 16910 - Special Conditions: Boeing Model 787 Series Airplanes; Single-place Side-facing Seats With...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-03-23

    ...These special conditions are issued for the Boeing Model 787 series airplanes. These airplanes have a novel or unusual design feature associated with single-place side-facing seats with inflatable lapbelts. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards......

  18. 76 FR 24358 - Airworthiness Directives; Dassault-Aviation Model FALCON 7X Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-02

    ... Model FALCON 7X Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation... December 30, 2010 (75 FR 82327). That NPRM proposed to correct an unsafe condition for the specified... of civil aircraft in air commerce by prescribing regulations for practices, methods, and...

  19. 76 FR 64847 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-19

    .... Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of..., 2011. ADDRESSES: You may send comments by any of the following methods: Federal eRulemaking Portal: Go... of civil aircraft in air commerce by prescribing regulations for practices, methods, and...

  20. 76 FR 64788 - Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model 4101 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-19

    ... (Operations) Limited Model 4101 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... by reference of certain other publications listed in this AD as of June 11, 2009 (74 FR 21246, May 7... April 8, 2011 (76 FR 19716), and proposed to supersede AD 2009-10-02, Amendment 39-15897 (74 FR...

  1. 75 FR 52652 - Airworthiness Directives; Airbus Model A300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-27

    ... Directives; Airbus Model A300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... proposed AD by October 12, 2010. ADDRESSES: You may send comments by any of the following methods: Federal... air commerce by prescribing regulations for practices, methods, and procedures the Administrator...

  2. 75 FR 39863 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-13

    ... Directives; Airbus Model A310 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION..., 2010. ADDRESSES: You may send comments by any of the following methods: Federal eRulemaking Portal: Go... proposed AD. Discussion On April 20, 2006, we issued AD 2006-09-05, Amendment 39-14575 (71 FR 25921, May...

  3. 76 FR 64849 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-19

    .... Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... comments by any of the following methods: ] Federal eRulemaking Portal: Go to http://www.regulations.gov... flight of civil aircraft in air commerce by prescribing regulations for practices, methods,...

  4. 76 FR 28639 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-18

    .... Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... was published in the Federal Register on February 23, 2011 (76 FR 9982). The MCAI states: During... practices, methods, and procedures the Administrator finds necessary for safety in air commerce....

  5. 75 FR 82327 - Airworthiness Directives; Dassault-Aviation Model FALCON 7X Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-30

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Dassault-Aviation Model FALCON 7X Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of...

  6. 76 FR 67633 - Airworthiness Directives; Dassault Aviation Model Mystere-Falcon 50 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-02

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Dassault Aviation Model Mystere-Falcon 50 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice...

  7. 75 FR 38064 - Airworthiness Directives; Bombardier, Inc. Model DHC-8 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-01

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will.... Model DHC-8 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... will be no charge for these costs. As we do not control warranty coverage for affected parties,...

  8. 76 FR 27615 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-12

    ... Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR... Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA... coverage for affected parties, some parties may incur costs higher than estimated here. Based on...

  9. 76 FR 50403 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-15

    ... products. That NPRM was published in the Federal Register on May 12, 2011 (76 FR 27615). That NPRM proposed... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant...; Bombardier, Inc. Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA),...

  10. 76 FR 19719 - Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-08

    ... Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR... Aerosystems Model SAAB 2000 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... charge for these parts. As we do not control warranty coverage for affected parties, some parties...

  11. 76 FR 41665 - Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-15

    ... specified products. That NPRM was published in the Federal Register on April 8, 2011 (76 FR 19719). That... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... Aerosystems Model SAAB 2000 Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  12. 75 FR 61987 - Airworthiness Directives; Bombardier, Inc. Model DHC-8 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-07

    ... was published in the Federal Register on July 1, 2010 (75 FR 38064). That NPRM proposed to correct an... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or.... Model DHC-8 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation...

  13. 75 FR 12710 - Airworthiness Directives; Bombardier, Inc., Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-17

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will...., Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... costs. As we do not control warranty coverage for affected parties, some parties may incur costs...

  14. 75 FR 66655 - Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-29

    ... Register on August 26, 2010 (75 FR 52482). That NPRM proposed to correct an unsafe condition for the...'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a... Ltd. Model PC-7 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...

  15. 75 FR 32863 - Airworthiness Directives; PILATUS AIRCRAFT LTD. Model PC-12/47E Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-10

    ... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... Directives; PILATUS AIRCRAFT LTD. Model PC-12/47E Airplanes AGENCY: Federal Aviation Administration (FAA... receive comments by July 26, 2010. Affected ADs (b) None. Applicability (c) This AD applies to...

  16. 75 FR 50869 - Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-12/47E Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-18

    ... Register on June 10, 2010 (75 FR 32863). That NPRM proposed to correct an unsafe condition for the... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant... Ltd. Model PC-12/47E Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  17. 75 FR 12150 - Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-15

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... Ltd. Model PC-7 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation.... Relevant Service Information PILATUS Aircraft Ltd. has issued PILATUS PC-7 Service Bulletin No....

  18. 75 FR 52482 - Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-26

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Ltd. Model PC-7 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation... Pilatus Aircraft Ltd. has issued PC-7 Service Bulletin No. 57-015, Rev. No. 1, date July 23, 2010....

  19. 75 FR 17879 - Airworthiness Directives; The Cessna Aircraft Company Model 750 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-08

    ...-14817 (71 FR 65047, November 7, 2006), for all The Cessna Aircraft Company Model 750 airplanes. That AD...'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have... Amendment 39-14817 (71 FR 65047, November 7, 2006) and adding the following new AD: The Cessna...

  20. 75 FR 77790 - Airworthiness Directives; The Boeing Company Model 767 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-14

    ... 23, 2000, we issued AD 2000-11-06, amendment 39-11754 (65 FR 34928, June 1, 2000), for all Model 767 airplanes. (A correction of the rule was published in the Federal Register on August 1, 2000 (65 FR 46862...'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not...

  1. 75 FR 5690 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A. Model P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-04

    ...'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a... INDUSTRIES S.p.A. Model P- 180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... specified products. That NPRM was published in the Federal Register on November 19, 2009 (74 FR 59941)....

  2. 75 FR 3660 - Airworthiness Directives; The Boeing Company Model 757 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-22

    ...We propose to adopt a new airworthiness directive (AD) for all Model 757 airplanes. This proposed AD would require repetitive inspections for corrosion and cracking in the front spar lower chord at the four fastener locations common to the side link support fitting at wing station (WS) 292, and corrective actions if necessary. This proposed AD results from reports that several operators have......

  3. 75 FR 77793 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-14

    ...-26-07, Amendment 39-10250 (62 FR 65352, December 12, 1997), for all Model 747 airplanes. That AD... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3... Amendment 39-10250 (62 FR 65352, December 12, 1997) and adding the following new AD: The Boeing...

  4. 76 FR 39256 - Airworthiness Directives; Dassault Aviation Model FALCON 7X Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-06

    ... to the specified products. That NPRM was published in the Federal Register on March 8, 2011 (76 FR... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3... Model FALCON 7X Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...

  5. 75 FR 32263 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-08

    ... in the Federal Register on December 30, 2009 (74 FR 69038). That NPRM proposed to correct an unsafe... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant.... Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  6. 75 FR 28465 - Airworthiness Directives; Dassault-Aviation Model FALCON 2000 and FALCON 2000EX Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-21

    ... September 24, 2009 (74 FR 48668). That NPRM proposed to correct an unsafe condition for the specified... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... Model FALCON 2000 and FALCON 2000EX Airplanes AGENCY: Federal Aviation Administration (FAA),...

  7. 76 FR 30043 - Airworthiness Directives; The Boeing Company Model 757 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-24

    ..., we issued AD 2006-23-15, Amendment 39-14827 (71 FR 66657, November 16, 2006). That AD applies to the... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will... Model 757 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of...

  8. 76 FR 18964 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Model P2006T Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-06

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Aeronautiche Tecnam srl Model P2006T Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... the nose landing gear hydraulic actuator cap. The manufacturer has identified the root cause of...

  9. 75 FR 61999 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-07

    ..., amendment 39-12330 (66 FR 38350, July 24, 2001), for certain Boeing Model 767 airplanes. That AD requires... AD 2001-14-19). Drain tube replacement (new Between 7 and 11, 1,117 Between $1,712 356 Between $609... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and...

  10. 75 FR 8279 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-24

    ...-06, amendment 39-14503 (71 FR 12125, March 9, 2006). The original NPRM applied to certain Model 747 airplanes. The original NPRM was published in the Federal Register on September 23, 2008 (73 FR 54751). The...) amends Sec. 39.13 by removing amendment 39-14503 (71 FR 12125, March 9, 2006) and adding the...

  11. 76 FR 9495 - Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-18

    ..., amendment 39-16412 (75 FR 52255, August 25, 2010), for all Air Tractor Models AT-802 and AT- 802A airplanes... statutes, to fit regulatory and informational requirements to the scale of the businesses, organizations... actions. The RFA covers a wide range of small entities, including small businesses,...

  12. 76 FR 19710 - Airworthiness Directives; The Boeing Company Model 757 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-08

    ...-10-11, amendment 39-15517 (73 FR 25974, May 8, 2008), for all Model 757 series airplanes. That AD... a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26...), 40113, 44701. Sec. 39.13 2. The FAA amends Sec. 39.13 by removing amendment 39-15517 (73 FR 25974, May...

  13. 78 FR 6195 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-01-30

    ... Embraer S.A. Model EMB-550 airplanes was published in the Federal Register on November 9, 2012, (77 FR... Protection: Performance Credit for Automatic Takeoff Thrust Control System (ATTCS) During Go-Around AGENCY... design feature associated with the use of an Automatic Takeoff Thrust Control System (ATTCS) during...

  14. 76 FR 20501 - Airworthiness Directives; Fokker Services B.V. Model F.27 Mark 050 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-13

    ... and Maintenance and Inspection Requirements'' (66 FR 23086, May 7, 2001). In addition to new... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... Services B.V. Model F.27 Mark 050 Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  15. 76 FR 18031 - Airworthiness Directives; Dassault Aviation Model Mystere-Falcon 50 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-01

    ... Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska... Model Mystere-Falcon 50 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...-Falcon 50 aeroplanes in service, it was detected that two pipes had been swapped in maintenance at...

  16. 76 FR 13924 - Airworthiness Directives; Dassault-Aviation Model FALCON 7X Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-15

    ... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... Model FALCON 7X Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... is set at 1 000 flight hours (FH) in the airworthiness limitations section of the Falcon 7X...

  17. 75 FR 71530 - Airworthiness Directives; DASSAULT AVIATION Model MYSTERE-FALCON 50 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-24

    ... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... Model MYSTERE-FALCON 50 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...-Falcon 50 aeroplanes in service, it was detected that two pipes of the emergency brake system 2...

  18. 76 FR 21815 - Airworthiness Directives; The Boeing Company Model 737 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-19

    ...We are revising an earlier proposed airworthiness directive (AD) for certain Model 737 airplanes. The original NPRM would have required repetitive inspections, lubrications, and repetitive repairs/ overhauls of the ball nut and ballscrew and attachment (Gimbal) fittings for the trim actuator of the horizontal stabilizer; various installation(s); and corrective actions if necessary; as......

  19. 75 FR 35616 - Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-23

    ... airplane. DATES: This AD becomes effective on July 28, 2010. As of April 21, 2006 (71 FR 19994, April 19... (74 FR 39243). The NPRM proposed to supersede AD 2006-08-09 to clarify the SNs of the Models AT-802... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a...

  20. 76 FR 13080 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-10

    ... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant.... Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... examining the MCAI in the AD docket. Relevant Service Information Bombardier has issued Repair Drawing...

  1. 75 FR 36577 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-28

    ...-07-04, Amendment 39-15863 (74 FR 14460, March 31, 2009), for certain Model MD-90-30 airplanes. That... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3... Amendment 39-15863 (74 FR 14460, March 31, 2009) and adding the following new AD: McDonnell...

  2. 75 FR 15328 - Airworthiness Directives; The Boeing Company Model 757 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-29

    ... certain Model 757 airplanes. That NPRM was published in the Federal Register on September 29, 2009 (74 FR... ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), and (3) Will... oxygen system installed under the oxygen mask stowage box at a flightcrew and supernumerary oxygen...

  3. 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

    ...-135 (76 FR 74654, December 1, 2011), effective January 30, 2012. (This amendment is not in the Model.... Model EMB-550 airplanes was published in the Federal Register on November 20, 2012 (77 FR 69573)....

  4. 75 FR 9515 - Airworthiness Directives; Airbus Model A330-200 Series Airplanes and Model A340-200 and -300...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-03

    ...-16202; AD 2010-04-09] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330-200 Series Airplanes and Model A340-200 and -300 Series Airplanes Correction In rule document 2010-3119 beginning on page 7940 in..., under the header ``Applicability,'' item (1) should read: ``(1) Airbus Model A330-201, - 202, -203,...

  5. Rubber airplane: Constraint-based component-modeling for knowledge representation in computer-aided conceptual design

    NASA Technical Reports Server (NTRS)

    Kolb, Mark A.

    1990-01-01

    Viewgraphs on Rubber Airplane: Constraint-based Component-Modeling for Knowledge Representation in Computer Aided Conceptual Design are presented. Topics covered include: computer aided design; object oriented programming; airfoil design; surveillance aircraft; commercial aircraft; aircraft design; and launch vehicles.

  6. High-Speed Tests of a Model Twin-Engine Low-Wing Transport Airplane

    NASA Technical Reports Server (NTRS)

    Becker, John V; LEONARD LLOYD H

    1942-01-01

    Report presents the results of force tests made of a 1/8-scale model of a twin-engine low-wing transport airplane in the NACA 8-foot high-speed tunnel to investigate compressibility and interference effects of speeds up to 450 miles per hour. In addition to tests of the standard arrangement of the model, tests were made with several modifications designed to reduce the drag and to increase the critical speed.

  7. 75 FR 28475 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes, and Model A340-300...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-21

    ...-122-AD; Amendment 39-16304; AD 2010-10-25] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes, and Model A340-300 Series Airplanes AGENCY: Federal Aviation... products. That NPRM was published in the Federal Register on October 19, 2009 (74 FR 53440). That...

  8. 75 FR 7940 - Airworthiness Directives; Airbus Model A330-200 Series Airplanes and Model A340-200 and -300...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-23

    ...-138-AD; Amendment 39-16202; AD 2010-04-09] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330-200 Series Airplanes and Model A340-200 and -300 Series Airplanes AGENCY: Federal Aviation... products. That NPRM was published in the Federal Register on December 1, 2009 (74 FR 62713). That...

  9. 75 FR 32266 - Airworthiness Directives; Airbus Model A300 Series Airplanes; Airbus Model A300 B4-600, B4-600R...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-08

    ... Register on February 25, 2010 (75 FR 8549). That NPRM proposed to correct an unsafe condition for the... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant... Series Airplanes; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model...

  10. Fuel-efficient cruise performance model for general aviation piston engine airplanes

    SciTech Connect

    Parkinson, R.C.H.

    1982-01-01

    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 simplicity and low volume data storage requirements, appears suitable for airborne microprocessor implementation.

  11. Recent Dynamic Measurements and Considerations for Aerodynamic Modeling of Fighter Airplane Configurations

    NASA Technical Reports Server (NTRS)

    Brandon, Jay M.; Foster, John V.

    1998-01-01

    As airplane designs have trended toward the expansion of flight envelopes into the high angle of attack and high angular rate regimes, concerns regarding modeling the complex unsteady aerodynamics for simulation have arisen. Most current modeling methods still rely on traditional body axis damping coefficients that are measured using techniques which were intended for relatively benign flight conditions. This paper presents recent wind tunnel results obtained during large-amplitude pitch, roll and yaw testing of several fighter airplane configurations. A review of the similitude requirements for applying sub-scale test results to full-scale conditions is presented. Data is then shown to be a strong function of Strouhal number - both the traditional damping terms, but also the associated static stability terms. Additionally, large effects of sideslip are seen in the damping parameter that should be included in simulation math models. Finally, an example of the inclusion of frequency effects on the data in a simulation is shown.

  12. 76 FR 22059 - Airworthiness Directives; The Boeing Company Model 757 Airplanes, and Model 767-200, 767-300, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-20

    ...-09-07, Amendment 39-15488 (73 FR 21811, April 23, 2008), for all Boeing Model 757 airplanes and Model... a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26...-07, Amendment 39-15488 (73 FR 21811, April 23, 2008), and adding the following new AD: The...

  13. 77 FR 15291 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-03-15

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not... B4-622R airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-600R series airplanes... B4-603, B4-605R, and B4- 622R airplanes; Model A300 C4-605R Variant F airplanes; and Model A300...

  14. 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

    ... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http... design feature associated with the architecture and connectivity capabilities of the airplanes' computer systems and networks, which may allow access to or by external computer systems and networks....

  15. 76 FR 69685 - Airworthiness Directives; The Boeing Company Model 767-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-09

    ...We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 767-200 and -300 series airplanes. This proposed AD was prompted by reports of cracks in the inner chords at both left-side and right-side stations 859.5, 883.5, and 903.5. This proposed AD would require repetitive inspections of the frame inner chord transition radius for cracks, and related investigative......

  16. 75 FR 75878 - Airworthiness Directives; Airbus Model A318-111 and A318-112 Airplanes and Model A319, A320, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-07

    ... Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2008-0670; Directorate Identifier 2007-NM...-111 and A318-112 Airplanes and Model A319, A320, and A321 Series Airplanes AGENCY: Federal Aviation... airworthiness information (MCAI) originated by an aviation authority of another country to identify and...

  17. 78 FR 49655 - Special Conditions: Embraer, S.A., Model EMB-550 Airplane; Side-Facing Seats; Installation of...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-15

    ...These special conditions are issued for the Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design feature associated with multiple-place and single-place side-facing seats and the installation of airbag systems in the shoulder belts. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These......

  18. 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

    ... July 16, 2009 (74 FR 34516). That NPRM proposed to correct an unsafe condition for the specified... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or...-221, -222, -322, - 324, and -325 Airplanes, and Model A300 B4-620, B4-622, B4-622R, and...

  19. 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.

  20. Determination of airplane model structure from flight data by using modified stepwise regression

    NASA Technical Reports Server (NTRS)

    Klein, V.; Batterson, J. G.; Murphy, P. C.

    1981-01-01

    The linear and stepwise regressions are briefly introduced, then the problem of determining airplane model structure is addressed. The MSR was constructed to force a linear model for the aerodynamic coefficient first, then add significant nonlinear terms and delete nonsignificant terms from the model. In addition to the statistical criteria in the stepwise regression, the prediction sum of squares (PRESS) criterion and the analysis of residuals were examined for the selection of an adequate model. The procedure is used in examples with simulated and real flight data. It is shown that the MSR performs better than the ordinary stepwise regression and that the technique can also be applied to the large amplitude maneuvers.

  1. 76 FR 38069 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-29

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively...-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; and Model A310-203,...

  2. Determination of airplane model structure from flight data using splines and stepwise regression

    NASA Technical Reports Server (NTRS)

    Klein, V.; Batterson, J. G.

    1983-01-01

    A procedure for the determination of airplane model structure from flight data is presented. The model is based on a polynomial spline representation of the aerodynamic coefficients, and the procedure is implemented by use of a stepwise regression. First, a form of the aerodynamic force and moment coefficients amenable to the utilization of splines is developed. Next, expressions for the splines in one and two variables are introduced. Then the steps in the determination of an aerodynamic model structure and the estimation of parameters are discussed briefly. The focus is on the application to flight data of the techniques developed.

  3. 75 FR 51698 - Airworthiness Directives; Airbus Model A310 Series Airplanes; and Model A300 B4-600, A300 B4-600R...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-23

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... Series Airplanes; and Model A300 B4-600, A300 B4-600R, A300 F4-600R Series Airplanes, and Model A300 C4... B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R airplanes; Model A300...

  4. 76 FR 441 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-05

    ... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant... B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively..., B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes, certificated in any category, all...

  5. 76 FR 8319 - Special Conditions: Gulfstream Model GVI Airplane; Design Roll Maneuver Requirement for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-14

    ... Roll Maneuver Requirement for Electronic Flight Controls AGENCY: Federal Aviation Administration (FAA... airplanes. These design features include an electronic flight control system that provides roll control of the airplane through pilot inputs to the flight ] computers. These proposed special conditions...

  6. 76 FR 17022 - Special Conditions: Gulfstream Model GVI Airplane; High Incidence Protection

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-28

    ...These special conditions are issued for the Gulfstream GVI airplane. This airplane will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes associated with the use of high incidence protection. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for......

  7. 76 FR 41142 - Special Conditions; Cessna Aircraft Company Model M680 Airplane; Lithium-ion Battery Installations

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-13

    ... Aircraft Company Model M680 Airplane; Lithium-ion Battery Installations AGENCY: Federal Aviation... design feature associated with Lithium-ion batteries. The applicable airworthiness regulations do not...) T00012WI for installation of Lithium-ion batteries in the Model 680. The Model 680 is a twin-engine,...

  8. Subsonic wind tunnel investigation of a twin-engine attack airplane model having nonmetric powered nacelles

    NASA Technical Reports Server (NTRS)

    Lockwood, V. E.; Matarazzo, A.

    1974-01-01

    A 1/10-scale powered model of a twin-engine attack airplane was investigated in the Langley high-speed 7- by 10-foot tunnel. The study was made at several Mach numbers between 0.225 and 0.75 which correspond to Reynolds numbers, based on the mean aerodynamic chord, of 1.35 million and 3.34 million. Unheated compressed air was used for jet simulation in the nonmetric engine nacelles which were located ahead of and above the horizontal stabilizer.

  9. A statistical mechanics model for free-for-all airplane passenger boarding

    SciTech Connect

    Steffen, Jason H.; /Fermilab

    2008-08-01

    I discuss a model for free-for-all passenger boarding which is employed by some discount air carriers. The model is based on the principles of statistical mechanics where each seat in the aircraft has an associated energy which reflects the preferences of travelers. As each passenger enters the airplane they select their seats using Boltzmann statistics, proceed to that location, load their luggage, sit down, and the partition function seen by remaining passengers is modified to reflect this fact. I discuss the various model parameters and make qualitative comparisons of this passenger boarding model with those that involve assigned seats. The model can be used to predict the probability that certain seats will be occupied at different times during the boarding process. These results might provide a useful description of this boarding method. The model is a relatively unusual application of undergraduate level physics and describes a situation familiar to many students and faculty.

  10. Longitudinal Stability and Stalling Characteristics of a 1/8.33-Scale Model of the Republic XF-12 Airplane

    NASA Technical Reports Server (NTRS)

    Pepper, Edward; Foster, Gerald V.

    1946-01-01

    The XF-12 airplane is a high performance, photo-reconnaissance aircraft designed by the Republic Aviation Corporation for Army Air Forces. A series of tests of a 1/8.33-scale powered model was conducted in the Langley 9-foot pressure tunnel to obtain information relative to the aerodynamic design of the airplane. This report presents the results of tests to determine the static longitudinal stability and stalling characteristics of the model. From this investigation it was indicated that the airplane will possess a positive static margin for all probable flight conditions. The stalling characteristics are considered satisfactory in that the stall initiates near the root section and progresses toward the tips. Early root section stalling occurs, with the flaps retracted and may cause undesirable tail buffeting and erratic elevator control in the normal flight range. From considerations of sinking speed landing flap deflections of 40 degrees may be preferable to 55 degrees of 65 degrees.

  11. 75 FR 904 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-07

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Directive (AD) 2009-21-08, which applies to PIAGGIO AERO INDUSTRIES S.p.A. (Piaggio) Model PIAGGIO P-180... as AD 2009-21-08. As of December 14, 2009 (74 FR 57561, November 9, 2009), the Director of...

  12. 75 FR 10696 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-09

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will.... Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION...) None. Applicability (c) This AD applies to Fokker Services B.V. Model F.28 Mark 0070 and Mark...

  13. 75 FR 16660 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-02

    ...-064-AD; Amendment 39-16252; AD 2010-07-07] RIN 2120-AA64 Airworthiness Directives; SOCATA Model TBM..., 2010 (75 FR 89). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI... air commerce by prescribing regulations for practices, methods, and procedures the Administrator...

  14. 75 FR 13239 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-19

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; SOCATA Model TBM... methods: Federal eRulemaking Portal: Go to http://www.regulations.gov . Follow the instructions for... practices, methods, and procedures the Administrator finds necessary for safety in air commerce....

  15. 76 FR 30295 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-25

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; SOCATA Model TBM... proposed AD by July 11, 2011. ADDRESSES: You may send comments by any of the following methods: Federal e... air commerce by prescribing regulations for practices, methods, and procedures the Administrator...

  16. 76 FR 4216 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-25

    ...-041-AD; Amendment 39-16575; AD 2011-02-02] RIN 2120-AA64 Airworthiness Directives; SOCATA Model TBM... (73 FR 54067, September 18, 2008), the Director of the Federal Register approved the incorporation by... September 28, 2010 (75 FR 59658), and proposed to supersede AD 2008-19-06, Amendment 39- 15673 (73 FR...

  17. 75 FR 59658 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-28

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; SOCATA Model TBM... may send comments by any of the following methods: Federal eRulemaking Portal: Go to http://www... proposed AD. Discussion On September 8, 2008, we issued AD 2008-19-06, Amendment 39-15673 (73 FR...

  18. 75 FR 89 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-04

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; SOCATA Model TBM... following methods: Federal eRulemaking Portal: Go to http://www.regulations.gov . Follow the instructions..., methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation...

  19. 76 FR 39248 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-06

    ... products. That NPRM was published in the Federal Register on December 10, 2010 (75 FR 76926). That NPRM... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes...

  20. 76 FR 28914 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-19

    ... Order 12866, 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR... of the rudder system design. Rudder pedal sensitivity on Model A300-600 and A310 series airplanes is greater than that of other transport category airplane designs. Such rudder control sensitivity...

  1. Ditching Investigation of a 1/18-Scale Model of the North American B-45 Airplane

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; Thompson, William C.

    1949-01-01

    An investigation of a 1/18-scale dynamically similar model of the North American B-45 airplane was made to observe the ditching behavior and determine the proper landing technique to be used in 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 high-speed motion-picture records, time-history acceleration records, and visual observations. It was concluded that the airplane should be ditched at the maximum nose-high attitude with the landing flaps full down for minimum landing speed. During the ditching, the nose-wheel and bomb-bay doors probably will be torn away and the rear of the fuselage flooded. A violent dive will very likely occur. Longitudinal decelerations of approximately 5g and vertical accelerations of approximately -6g (including gravity) will be experienced near the pilots' compartment. Ditching braces installed in the bomb bay will tend to improve the behavior slightly but will be torn away along with the bomb-bay doors. A hydroflap installed ahead of the nose-wheel doors will eliminate the dive and failure of the nose-wheel doors, and substantially reduce the motions and accelerations.

  2. 78 FR 78705 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-27

    ...We are superseding Airworthiness Directive (AD) 2010-24-07 for all Airbus Model A318 series airplanes, Model A319 series airplanes, Model A320 series airplanes, and Model A321 series airplanes. AD 2010- 24-07 required repetitive inspections of the 80VU rack lower lateral fittings for damage, repetitive inspections of the 80VU rack lower central support for cracking, and corrective action if......

  3. 77 FR 12989 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-03-05

    ...We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 series airplanes; Model A330-300 series airplanes; Model A340-200 series airplanes; and Model A340-300 series airplanes. This AD was prompted by a report that three failures of the retraction bracket occurred during fatigue testing before the calculated life limit of the main landing gear (MLG). This AD......

  4. 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

    A free-to-roll (FTR) test technique and test rig make it possible to evaluate both the transonic performance and the wingdrop/ rock behavior of a high-strength airplane model in a single wind-tunnel entry. The free-to-roll test technique is a single degree-of-motion method in which the model is free to roll about the longitudinal axis. The rolling motion is observed, recorded, and analyzed to gain insight into wing-drop/rock behavior. Wing-drop/rock is one of several phenomena symptomatic of abrupt wing stall. FTR testing was developed as part of the NASA/Navy Abrupt Wing Stall Program, which was established for the purposes of understanding and preventing significant unexpected and uncommanded (thus, highly undesirable) lateral-directional motions associated with wing-drop/rock, which have been observed mostly in fighter airplanes under high-subsonic and transonic maneuvering conditions. Before FTR testing became available, wingrock/ drop behavior of high-performance airplanes undergoing development was not recognized until flight testing. FTR testing is a reliable means of detecting, and evaluating design modifications for reducing or preventing, very complex abrupt wing stall phenomena in a ground facility prior to flight testing. The FTR test rig was designed to replace an older sting attachment butt, such that a model with its force balance and support sting could freely rotate about the longitudinal axis. The rig (see figure) includes a rotary head supported in a stationary head with a forward spherical roller bearing and an aft needle bearing. Rotation is amplified by a set of gears and measured by a shaft-angle resolver; the roll angle can be resolved to within 0.067 degrees at a rotational speed up to 1,000 degrees/s. An assembly of electrically actuated brakes between the rotary and stationary heads can be used to hold the model against a rolling torque at a commanded roll angle. When static testing is required, a locking bar is used to fix the rotating

  5. Spin-Tunnel Investigation of a 1/28-Scale Model of a Subsonic Attack Airplane

    NASA Technical Reports Server (NTRS)

    Lee, Henry A.; Healy, Frederick M.

    1964-01-01

    An investigation has been made of a 1/28-scale model of the Grumman A-6A airplane in the Langley spin tunnel. The erect spin and recovery characteristics of the model were determined for the flight design gross weight loading and for a loading with full internal fuel and empty external wing fuel tanks. The effects of extending slats and deflecting flaps were investigated. Inverted-spin and recovery characteristics of the model were determined for the flight design gross weight loading. The size of the spin-recovery tail parachute necessary to insure satisfactory spin-recovery was determined, and the effect of firing wing-mounded rockets during spins was investigated.

  6. 76 FR 16582 - Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-24

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... continuing airworthiness information (MCAI) originated by an aviation authority of another country...

  7. 76 FR 40286 - Airworthiness Directives; Empresa Brasileira de Aeronáutica S.A. (EMBRAER) Model EMB-505 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-08

    ... not control warranty coverage for affected individuals. As a result, we have included all costs in our... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... de Aeron utica S.A. (EMBRAER) Model EMB-505 Airplanes AGENCY: Federal Aviation Administration...

  8. 75 FR 53609 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-01

    ... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes AGENCY: Federal Aviation... docket. Relevant Service Information Empresa Brasileira de Aeron utica S.A. (EMBRAER) has issued...

  9. 75 FR 2060 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-14

    ... Register on July 15, 2009 (74 FR 34276). That NPRM proposed to correct an unsafe condition for the... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes AGENCY: Federal Aviation Administration...

  10. 75 FR 7409 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-19

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of..., Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,...

  11. 75 FR 22512 - Airworthiness Directives; Piaggio Aero Industries S.p.A. Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-29

    ... Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or... Industries S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... ] Register on February 19, 2010 (75 FR 7409). That NPRM proposed to correct an unsafe condition for...

  12. 75 FR 43095 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A. Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-23

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... INDUSTRIES S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of..., Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,...

  13. 75 FR 67639 - Airworthiness Directives; Piaggio Aero Industries S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-03

    ... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... Industries S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... maintenance requirements and/or airworthiness limitations developed by Piaggio Aero Industries S.p.A....

  14. 76 FR 10224 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-24

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... this AD, contact Piaggio Aero Industries S.p.A., Via Cibrario, 4-16154 Genoa, Italy; phone: +39 010... NPRM was published in the Federal Register on November 3, 2010 (75 FR 67639). That NPRM proposed...

  15. 76 FR 7694 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-11

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The..., amendment 39-16582 (76 FR 4056, January 24, 2011), currently requires an immediate functional test of...

  16. 76 FR 36980 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-24

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... . SUPPLEMENTARY INFORMATION: Airworthiness Directive 2011-09-51, Amendment 39-16697 (76 FR 27872, May 13, 2011... Internet at http://www.regulations.gov ; or in person at the Docket Management Facility between 9 a.m....

  17. 75 FR 43101 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-23

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except....regulations.gov ; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday...

  18. 75 FR 68172 - Airworthiness Directives; Piaggio Aero Industries S.p.A. Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-05

    ...'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a... Industries S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... identified in this AD, contact Piaggio Aero Industries S.p.a., Via Cibrario, 4-16154 Genoa, Italy; phone:...

  19. 75 FR 63060 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A. Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-14

    ... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant... INDUSTRIES S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Register on July 23, 2010 (75 FR 43095). That NPRM proposed to correct an unsafe condition for...

  20. 75 FR 47734 - Airworthiness Directives; Piaggio Aero Industries S.p.A. Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-09

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... Industries S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday...

  1. 76 FR 54403 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-09-01

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday,...

  2. 75 FR 43105 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-23

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday...

  3. 75 FR 63062 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-14

    ... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... (75 FR 43101). That NPRM proposed to correct an unsafe condition for the specified products. The...

  4. Investigations of Tumbling Characteristics of a 1/20-Scale Model of the Northrop N-9M Airplane

    NASA Technical Reports Server (NTRS)

    MacDougall, George F., Jr.

    1947-01-01

    The tumbling characteristics of a 1/20-scale model of the Northrop N-9M airplane have been determined in the Langley 20-foot free-spinning tunnel for various configurations and loading conditions of the model. The investigation included tests to determine whether recovery from a tumble could be effected by the use of parachutes. An estimation of the forces due to acceleration acting on the pilot during a tumble was made. The tests were performed at an equivalent test altitude of 15,000 feet. The results of the model tests indicate that if the airplane is stalled with its nose up and near the vertical, or if an appreciable amount of pitching rotation is imparted to the airplane as through the action of a strong gust, the airplane will either tumble or oscillate in pitch through a range of angles of the order of +/-120 deg. The normal flying controls will probably be ineffective in preventing or in terminating the tumbling motion. The results of the model tests indicate that deflection of the landing flaps full down immediately upon the initiation of pitching rotation will tend to prevent the development of a state of tumbling equilibrium. The simultaneous opening of two-7-foot diameter parachutes having drag coefficients of 0.7, one parachute attached to the rear portion of each wing tip with a towline between 10 and 30 feet long, will provide recovery from a tumble. The accelerations acting on the pilot during a tumble will be dangerous.

  5. 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

    ... Embraer S.A. Model EMB-550 airplanes was published in the Federal Register on November 20, 2012 (77 FR... electronic flight control system which contains fly-by-wire control laws, including envelope protections, for... controls consist of hydraulically powered fly-by-wire elevators, aileron and rudder, controlled by...

  6. 76 FR 42607 - Airworthiness Directives; The Boeing Company Model 767-200, -300, and -400ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-19

    ...-15818 (74 FR 8717, February 26, 2009), for certain Model 767-200, -300, and - 400ER series airplanes...'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect... FR 8717, February 26, 2009), and adding the following new AD: The Boeing Company: Docket No....

  7. 75 FR 27966 - Airworthiness Directives; The Boeing Company Model 747-400 and 747-400D Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-19

    ... 12866, 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... certain Model 747-400 and 747-400D series airplanes. This proposed AD would ] require installing aluminum... November 4, 2009. The service bulletin describes procedures for installing aluminum gutter...

  8. 75 FR 27668 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-18

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will... Services B.V. Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... cause of the MLG extension problem was the (partially) blocked hydraulic return line from the...

  9. 76 FR 4056 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-24

    ...-15281 (72 FR 67843, December 3, 2007). AD 2007-24-15 requires correcting the fuselage drain system and... 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034... Model PIAGGIO P-180 airplanes. AD 2007-24-15, Amendment 39-15281 (72 FR 67843, December 3, 2007)...

  10. 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

    ... Register on August 25, 2010 (75 FR 52292). That NPRM proposed to require a retrofit of the rear passenger... 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034... Aircraft Industries GmbH Models DA 40 and DA 40F Airplanes AGENCY: Federal Aviation Administration,...

  11. 75 FR 2434 - Special Conditions: Boeing Model 747-8/-8F Series Airplanes; Design Roll Maneuver Requirement

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-15

    ... airplanes was published in the Federal Register on October 8, 2009 (74 FR 51813). No comments were received... appropriate safety standards for the 747-8/-8F because of a novel or unusual design feature, special... that incorporates the same or similar novel or unusual design feature, or should any other model...

  12. 76 FR 13921 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-15

    ... and Maintenance and Inspection Requirements'' (66 FR 23086, May 7, 2001). In addition to new... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will.... Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT....

  13. 75 FR 4485 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-28

    ... Register on September 28, 2009 (74 FR 49349). That NPRM proposed to correct an unsafe condition for the... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or.... Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  14. Spin tests of a 1/20-scale model of the XP-39 airplane, 15 March 1939

    NASA Technical Reports Server (NTRS)

    Donlan, C. J.

    1976-01-01

    The tests were performed to determine the spinning characteristics of a 1/20-scale model of the Bell XP-39 airplane. Effects of loading changes and of various control dispositions were studied. Subsequent tests were performed to determine the effect of a change in wing dihedral.

  15. 75 FR 71346 - Special Conditions: Boeing Model 787-8 Airplane; Lightning Protection of Fuel Tank Structure To...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-23

    ..., 2009 (74 FR 52698). Several comments were received from two commenters (Cessna and NATCA). Cessna 1.... The Boeing Model 787-8 airplane will incorporate a fuel tank nitrogen generation system (NGS) that... Features The 787 will have a fuel tank NGS that is intended to control fuel tank flammability. This NGS...

  16. 75 FR 6865 - Airworthiness Directives; The Boeing Company Model 737-700 (IGW) Series Airplanes Equipped With...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-12

    ... Review, Flammability Reduction and Maintenance and Inspection Requirements'' (66 FR 23086, May 7, 2001... Policies and Procedures (44 FR 11034, February 26, 1979), and 3. Will not have a significant economic... Model 737-700 (IGW) Series Airplanes Equipped With Auxiliary Fuel Tanks Installed in Accordance...

  17. 75 FR 76926 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-10

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will... Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F... B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; Model A300 C4-605R Variant...

  18. Tank Investigation of the EDO Model 142 Hydro-Ski Research Airplane

    NASA Technical Reports Server (NTRS)

    Ramsen, John A.; Wadlin, Kenneth L.; Gray, George R.

    1951-01-01

    A tank investigation has been conducted of a 1/10-size powered-dynamic model of the Edo model 142 hydra-ski research airplane. The results of tests of two configurations are presented: One included a large ski and a ski well; the other, a small ski without a well. Water take-offs would be possible with the available thrust for either configuration: however, the configuration with the large ski emerged sooner and had less resistance from ski emergence until take-off. Longitudinal stability and landing behavior in smooth water were satisfactory for both configurations. Some alteration to the design of the tail would be desirable in order to reduce the spray loads.

  19. The 727 airplane target thrust reverser static performance model test for refanned JT8D engines

    NASA Technical Reports Server (NTRS)

    Chow, C. T. P.; Atkey, E. N.

    1974-01-01

    The results of a scale model static performance test of target thrust reverser configurations for the Pratt and Whitney Aircraft JT8D-100 series engine are presented. The objective of the test was to select a series of suitable candidate reverser configurations for the subsequent airplane model wind tunnel ingestion and flight controls tests. Test results indicate that adequate reverse thrust performance with compatible engine airflow match is achievable for the selected configurations. Tapering of the lips results in loss of performance and only minimal flow directivity. Door pressure surveys were conducted on a selected number of lip and fence configurations to obtain data to support the design of the thrust reverser system.

  20. Dynamics Modeling and Simulation of Large Transport Airplanes in Upset Conditions

    NASA Technical Reports Server (NTRS)

    Foster, John V.; Cunningham, Kevin; Fremaux, Charles M.; Shah, Gautam H.; Stewart, Eric C.; Rivers, Robert A.; Wilborn, James E.; Gato, William

    2005-01-01

    As part of NASA's Aviation Safety and Security Program, research has been in progress to develop aerodynamic modeling methods for simulations that accurately predict the flight dynamics characteristics of large transport airplanes in upset conditions. The motivation for this research stems from the recognition that simulation is a vital tool for addressing loss-of-control accidents, including applications to pilot training, accident reconstruction, and advanced control system analysis. The ultimate goal of this effort is to contribute to the reduction of the fatal accident rate due to loss-of-control. Research activities have involved accident analyses, wind tunnel testing, and piloted simulation. Results have shown that significant improvements in simulation fidelity for upset conditions, compared to current training simulations, can be achieved using state-of-the-art wind tunnel testing and aerodynamic modeling methods. This paper provides a summary of research completed to date and includes discussion on key technical results, lessons learned, and future research needs.

  1. 78 FR 68347 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-14

    ... (74 FR 7549, February 18, 2009). Airbus also stated that for Model A340-541 and A340-642 airplanes.... Airbus stated that this requirement for Model A330 MRTT airplanes is equivalent to one in the NPRM (78 FR... (f) of AD 2009-04-07, Amendment 39-15813 (74 FR 7549, February 18, 2009). For all airplanes...

  2. 76 FR 79560 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-22

    ... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... airplanes; Model A330-223F and -243F airplanes; and Model A340-200, -300, -500, and -600 series...

  3. 78 FR 70003 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-22

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... series airplanes; Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300...

  4. 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.

  5. 76 FR 8316 - Special Conditions: Gulfstream Model GVI Airplane; Interaction of Systems and Structures

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-14

    ... systems that affect the structural capability of the airplane. The applicable airworthiness regulations do... are systems that may affect the airplane's structural performance, either directly or as a result of... conditions, and thereby affect its structural capability. These systems may also affect the...

  6. 76 FR 36865 - Special Conditions: Gulfstream Model GVI Airplane; Interaction of Systems and Structures

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-23

    ... Federal Register on February 14, 2011 (76 FR 8316). Only one comment was received. Clarification of GVI... that affect the structural capability of the airplane. The applicable airworthiness regulations do not... unusual design features. These features are systems that may affect the airplane's structural...

  7. 75 FR 39189 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-08

    ... Policies and Procedures (44 FR 11034, February 26, 1979), and 3. Will not have a significant economic... airplanes. This proposed AD would require repetitive inspections for cracking in the body skin around the... cracking in the body skin and the skin splice plate; for certain airplanes, an inspection for steel...

  8. 75 FR 29962 - Special Conditions: Cirrus Design Corporation Model SF50 Airplane; Function and Reliability Testing

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-28

    ... Design Corporation SF50 airplane. This airplane will have a novel or unusual design feature(s) associated... airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These... for the SF 50 because of a novel or unusual design feature, special conditions are prescribed...

  9. 76 FR 36863 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Systems Security Protection From...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-23

    ... airplanes was published in the Federal Register on February 25, 2011 (76 FR 10529). Only one comment was... architecture and connectivity capabilities of the airplane's computer systems and networks, which may allow access by external computer systems and networks. Connectivity by external systems and networks...

  10. 76 FR 36861 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Systems Security Isolation or...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-23

    ... Gulfstream GVI airplanes was published in the Federal Register on February 25, 2011 (76 FR 10528). Only one... features associated with connectivity of the passenger domain computer systems to the airplane ] critical... connected networks. The proposed architecture and network configuration may be used for, or interfaced...

  11. 78 FR 65155 - Special Conditions: Learjet Model 45 Series Airplanes; Isolation or Security Protection of the...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-31

    ... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http... associated with connectivity of the passenger service computer systems to the airplane critical systems and... perform functions required for the safe operation of the airplane. This proposed data network and...

  12. 75 FR 27956 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-19

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will... B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively... airplanes; Model A300 B4-601, B4- 603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and...

  13. 77 FR 50644 - Airworthiness Directives; Cessna Airplane Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-22

    ... 1134104-5 air conditioning (A/C) compressor motor; and (2) are certificated in any category. (d) Subject... certain Cessna Airplane Company Model 525 airplanes equipped with certain part number (P/N) air conditioning (A/C) compressor motors. This proposed AD was prompted by reports of smoke and/or fire in...

  14. 78 FR 28152 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-14

    ..., Amendment 39-16526 (75 FR 75878, December 7, 2010), exempted airplanes on which Airbus Modification 34804..., Amendment 39-16526 (75 FR 75878, December 7, 2010). Except for Model A318-121 and -122 airplanes, and except...) of AD 2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). Except for airplanes on...

  15. Geometric Model for a Parametric Study of the Blended-Wing-Body Airplane

    NASA Technical Reports Server (NTRS)

    Mastin, C. Wayne; Smith, Robert E.; Sadrehaghighi, Ideen; Wiese, Micharl R.

    1996-01-01

    A parametric model is presented for the blended-wing-body airplane, one concept being proposed for the next generation of large subsonic transports. The model is defined in terms of a small set of parameters which facilitates analysis and optimization during the conceptual design process. The model is generated from a preliminary CAD geometry. From this geometry, airfoil cross sections are cut at selected locations and fitted with analytic curves. The airfoils are then used as boundaries for surfaces defined as the solution of partial differential equations. Both the airfoil curves and the surfaces are generated with free parameters selected to give a good representation of the original geometry. The original surface is compared with the parametric model, and solutions of the Euler equations for compressible flow are computed for both geometries. The parametric model is a good approximation of the CAD model and the computed solutions are qualitatively similar. An optimal NURBS approximation is constructed and can be used by a CAD model for further refinement or modification of the original geometry.

  16. 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.

  17. 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.

  18. Compilation of Test Data on 111 Free-Spinning Airplane Models Tested in the Langley 15-Foot and 20-Foot Free-Spinning Tunnels

    NASA Technical Reports Server (NTRS)

    Malvestuto, Frank S.; Gale, Lawrence J.; Wood, John H.

    1947-01-01

    A compilation of free-spinning-airplane model data on the spin and recovery characteristics of 111 airplanes is presented. These data were previously published in separate memorandum reports and were obtained from free-spinning tests in the Langley 15-foot and the Langley 20-foot free-spinning tunnels. The model test data presented include the steady-spin and recovery characteristics of each model for various combinations of aileron and elevator deflections and for various loadings and dimensional configurations. Dimensional data, mass data, and a three-view drawing of the corresponding free-spinning tunnel model are also presented for each airplane. The data presented should be of value to designers and should facilitate the design of airplanes incorporating satisfactory spin-recovery characteristics.

  19. 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.

  20. 75 FR 77569 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System Mode...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-13

    ...; Electronic Flight Control System Mode Annunciation AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... design features include an electronic flight control system. The applicable airworthiness regulations do... INFORMATION CONTACT: Joe Jacobsen, FAA, Airplane and Flight Crew Interface Branch, ANM-111,...

  1. 76 FR 10529 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Systems Security Protection From...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-25

    ... associated with the architecture and connectivity capabilities of the airplane's computer systems and networks, which may allow access by external computer systems and networks. Connectivity by external... architecture composed of several connected networks. The proposed architecture and network configuration may...

  2. 75 FR 60010 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes and Model A340-200...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-29

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will... Directives; Airbus Model A330-200 and -300 Series Airplanes and Model A340-200, -300, -500, and -600 Series... connector internal arcing and hydraulic system malfunction. In addition, as the connectors are located...

  3. Free-Spinning-Tunnel Investigation of a 1/40-Scale Model of the McConnell F-101A Airplane

    NASA Technical Reports Server (NTRS)

    Bowman, James S., Jr.; Healy, Frederick M.

    1959-01-01

    An investigation has been made in the Langley 20-foot free-spinning tunnel of a 1/40-scale model of the McDonnell F-101A airplane to alleviate the unfavorable spinning characteristics encountered with the airplane. The model results indicate that a suitable strake extended on the inboard side of the nose of the airplane (right side in a right spin) in conjunction with the use of optimum control recovery technique will terminate spin rotation of the airplane. It may be difficult to recover from subsequent high angle-of-attack trimmed flight attitudes even by forward stick movement. The optimum spin-recovery control technique for the McDonnell F-101A is simultaneous full rudder reversal to against the spin and aileron movement to full with the spin (stick full right in a right erect spin) and forward movement of the stick immediately after rotation stops.

  4. 77 FR 26663 - Airworthiness Directives; The Boeing Company Model 767-200, -300, -300F, and -400ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-05-07

    ...We are superseding an existing airworthiness directive (AD) that applies to The Boeing Company Model 767-200, -300, and -300F series airplanes. That AD currently requires inspections to detect cracking or corrosion of the fail-safe straps between the side fitting of the rear spar bulkhead at body station 955 and the skin; and follow- on and corrective actions. This new AD expands the......

  5. 78 FR 65233 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-31

    ...This action proposes special conditions for the Bombardier Inc. Models BD-500-1A10 and BD-500-1A11 series airplanes. These airplanes will have a novel or unusual design feature associated with aluminum-lithium fuselage construction that may provide different levels of protection from post-crash fire threats than similar aircraft constructed from traditional aluminum structure. The applicable......

  6. Revalidation of the NASA Ames 11-by 11-Foot Transonic Wind Tunnel with a Commercial Airplane Model

    NASA Technical Reports Server (NTRS)

    Kmak, Frank J.; Hudgins, M.; Hergert, D.; George, Michael W. (Technical Monitor)

    2001-01-01

    The 11-By 11-Foot Transonic leg of the Unitary Plan Wind Tunnel (UPWT) was modernized to improve tunnel performance, capability, productivity, and reliability. Wind tunnel tests to demonstrate the readiness of the tunnel for a return to production operations included an Integrated Systems Test (IST), calibration tests, and airplane validation tests. One of the two validation tests was a 0.037-scale Boeing 777 model that was previously tested in the 11-By 11-Foot tunnel in 1991. The objective of the validation tests was to compare pre-modernization and post-modernization results from the same airplane model in order to substantiate the operational readiness of the facility. Evaluation of within-test, test-to-test, and tunnel-to-tunnel data repeatability were made to study the effects of the tunnel modifications. Tunnel productivity was also evaluated to determine the readiness of the facility for production operations. The operation of the facility, including model installation, tunnel operations, and the performance of tunnel systems, was observed and facility deficiency findings generated. The data repeatability studies and tunnel-to-tunnel comparisons demonstrated outstanding data repeatability and a high overall level of data quality. Despite some operational and facility problems, the validation test was successful in demonstrating the readiness of the facility to perform production airplane wind tunnel%, tests.

  7. Ditching Tests of a 1/10-Scale Model of the North American XFJ-1 Airplane Ted No. NACA 314

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; McBride, Ellis E.

    1948-01-01

    Tests were made of a 1/10-scale dynamically similar model of the North American XFJ-1 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, by recording the accelerations, and by taking motion pictures of the ditchings. Data are presented in tabular form, sequence photographs, and time-history acceleration curves. From the results of the tests it was concluded that the airplane should be ditched at the near-stall, tail-down landing attitude of 12 deg. The flaps should be fully extended to obtain the lowest possible landing speed. The wing-tip tanks should be jettisoned if any appreciable load of fuel remains; if empty, they should be retained for additional buoyancy. In a calm-water ditching the airplane will probably run about 600 feet Maximum longitudinal decelerations of about 2.5g and maximum vertical acceleration of about 2g will be encountered. The nose-intake duct will be clear of the water until practically all forward motion has stopped.

  8. Effects of several factors on theoretical predictions of airplane spin characteristics. [dynamic models

    NASA Technical Reports Server (NTRS)

    Bihrle, W., Jr.; Barnhart, B.

    1974-01-01

    The influence of different mathematical and aerodynamic models on computed spin motion was investigated along with the importance of some of the aerodynamic and nonaerodynamic quantities defined in these models. An analytical technique was used which included the aerodynamic forces and moments acting on a spinning aircraft due to steady rotational flow and the contribution of the rotary derivatives to the oscillatory component of the total angular rates. It was shown that (1) during experimental-analytical correlation studies, the flight-recorded control time histories must be faithfully duplicated since the spinning motion can be sensitive to a small change in the application of the spin entry controls; (2) an error in the assumed inertias, yawing moments at high angle of attack, and initial spin entry bank angle do not influence the developed spin significantly; (3) damping in pitch derivatives and the center of gravity location play a role in the spinning motion; and (4) the experimental spin investigations conducted in a constant atmospheric density environment duplicate the Froude number only at the initial full-scale spin altitude (since the full-scale airplane at high altitudes experiences large density changes during the spin.)

  9. Lateral Stability Characteristics of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

    NASA Technical Reports Server (NTRS)

    Pepper, Edward; Foster, Gerald V.

    1947-01-01

    The XF-12 airplane is a high-performance photo-reconnaissance aircraft designed for the Army Air Forces by the Republic Aviation Corporation. An investigation of a 1/8.33 - scale powered model was made in the Langley l9-foot pressure tunnel to obtain information relative to the aerodynamic design of the airplane. The model was tested with and without the original vertical tail. and with two revised tails. For the revised tail no. 1, the span of the original vertical .tail was increased about 15 percent and the portion of the vertical tail between the stabilizer and fuselage behind the rudder hinge line was allowed to deflect simultaneously with the main rudder. Revision no. 2 incorporated the increased span, but the lower rudder was locked in the neutral position. For all the tail arrangements investigated it was indicated that the airplane will possess positive effective dihedral and will be directionally stable regardless of flap or power condition. The rudder effectiveness is greater for the revised tails than for the original tail, but this is offset by the increase in directional stability caused by the revised tail. All the rudder arrangements appear inadequate in trimming out the resultant yawing moments at zero yaw in a take - off condition with the left-hand outboard propeller windmilling and the remaining engines developing take-off power.

  10. Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363

    NASA Technical Reports Server (NTRS)

    Hoffman, Edward L.; Fisher, Lloyd J.

    1950-01-01

    A model of the Convair Y2-2 airplane was tested in Langley tank no. 2 to determine whether satisfactory stability in yawed landings was possible with a certain ventral fin. Free-body landings were made in smooth and rough water at two speeds and two rates of descent with the model yawed 15deg. The behavior of the model was determined by visual observations and from motion-picture re.cords. It was concluded that satisfactory stability was possible with the ventral fin as tested but that the characteristics of the model shock absorbers and the settings of the elevon control surfaces had an appreciable influence on behavior.

  11. 75 FR 47207 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes, and Model A340-200...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-05

    ...- 19, Amendment 39-16364 (75 FR 39814, July 13, 2010), for certain Airbus Model A330-200 and -300... A340-200, -300, -500 and -600 series airplanes. A certain service bulletin number in Note 3 of the regulatory section is incorrect. This document corrects that service bulletin number. In all other...

  12. 75 FR 11435 - Airworthiness Directives; Airbus Model A300 B4-2C, B4-103, and B4-203 Airplanes; and Model A300...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-11

    ... October 28, 2009 (74 FR 55485). That NPRM proposed to correct an unsafe condition for the specified... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant...-53-0268, Revision 06, dated January 7, 2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes);...

  13. Experimental study of noise reduction for an unstiffened cylindrical model of an airplane fuselage

    NASA Technical Reports Server (NTRS)

    Willis, C. M.; Daniels, E. F.

    1981-01-01

    Noise reduction measurements were made for a simplified model of an airplane fuselage consisting of an unstiffened aluminum cylinder 0.5 m in diameter by 1.2 m long with a 1.6-mm-thick wall. Noise reduction was first measured with a reverberant field pink-noise load on the cylinder exterior. Next, noise reduction was measured by using a propeller to provide a more realistic noise load on the cylinder. Structural resonance frequencies and acoustic reverberation times for the cylinder interior volume were also measured. Comparison of data from the relatively simple test using reverberant-field noise with data from the more complex propeller-noise tests indicates some similarity in both the overall noise reduction and the spectral distribution. However, all of the test parameters investigated (propeller speed, blade pitch, and tip clearance) had some effect on the noise-reduction spectra. Thus, the amount of noise reduction achieved appears to be somewhat dependent upon the spectral and spatial characteristics of the flight conditions. Information is also presented on cyclinder resonance frequencies, damping, and characteristics of propeller-noise loads.

  14. 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.

  15. Wind-Tunnel Investigation of a 1/5-Scale Model of the Ryan XF2R Airplane

    NASA Technical Reports Server (NTRS)

    Wong, Park Y.

    1947-01-01

    Wind-tunnel tests on a 1/5-scale model of the Ryan XF2R airplane were conducted to determine the aerodynamic characteristics of the air intake for the front power plant, a General Electric TG-100 gas turbine, and to determine the stability and control characteristics of the airplane. The results indicated low-dynamic-pressure recover3- for the air intake to the TG-100 gas turbine rith the standard propeller in operation. Propeller cuffs were designed and tested for the purpose of impoving the dynamic-pressure recovery. Data obtained with the cuffs installed and the gap between the spinner an& the cuff sealed indicated a substantial gain in dynamic pressure recovery over that obtained with the standard propeller and with the cuffed propeller unsealed. Stability and control tests were conducted with the sealed cuffs installed on the propeller. The data from these tests indicated the following unsatisfactory characteristics for the airplane: 1. Marginal static longitudinal stability. 2. Inadequate directional stability and control. 3. Rudder-pedal-force reversal in the climb condition. 4. Negative dihedral effect in the power-on approach and wave-off conditions.

  16. Modelling and simulation of fuel cell dynamics for electrical energy usage of Hercules airplanes.

    PubMed

    Radmanesh, Hamid; Heidari Yazdi, Seyed Saeid; Gharehpetian, G B; Fathi, S H

    2014-01-01

    Dynamics of proton exchange membrane fuel cells (PEMFC) with hydrogen storage system for generating part of Hercules airplanes electrical energy is presented. Feasibility of using fuel cell (FC) for this airplane is evaluated by means of simulations. Temperature change and dual layer capacity effect are considered in all simulations. Using a three-level 3-phase inverter, FC's output voltage is connected to the essential bus of the airplane. Moreover, it is possible to connect FC's output voltage to airplane DC bus alternatively. PID controller is presented to control flow of hydrogen and oxygen to FC and improve transient and steady state responses of the output voltage to load disturbances. FC's output voltage is regulated via an ultracapacitor. Simulations are carried out via MATLAB/SIMULINK and results show that the load tracking and output voltage regulation are acceptable. The proposed system utilizes an electrolyser to generate hydrogen and a tank for storage. Therefore, there is no need for batteries. Moreover, the generated oxygen could be used in other applications in airplane. PMID:24782664

  17. Modelling and Simulation of Fuel Cell Dynamics for Electrical Energy Usage of Hercules Airplanes

    PubMed Central

    Radmanesh, Hamid; Heidari Yazdi, Seyed Saeid; Gharehpetian, G. B.; Fathi, S. H.

    2014-01-01

    Dynamics of proton exchange membrane fuel cells (PEMFC) with hydrogen storage system for generating part of Hercules airplanes electrical energy is presented. Feasibility of using fuel cell (FC) for this airplane is evaluated by means of simulations. Temperature change and dual layer capacity effect are considered in all simulations. Using a three-level 3-phase inverter, FC's output voltage is connected to the essential bus of the airplane. Moreover, it is possible to connect FC's output voltage to airplane DC bus alternatively. PID controller is presented to control flow of hydrogen and oxygen to FC and improve transient and steady state responses of the output voltage to load disturbances. FC's output voltage is regulated via an ultracapacitor. Simulations are carried out via MATLAB/SIMULINK and results show that the load tracking and output voltage regulation are acceptable. The proposed system utilizes an electrolyser to generate hydrogen and a tank for storage. Therefore, there is no need for batteries. Moreover, the generated oxygen could be used in other applications in airplane. PMID:24782664

  18. An Estimation of the Flying Qualities of the Kaiser Fleetwing All-Wing Airplane from Tests of a 1/7-Scale Model, TED No. NACA 2340

    NASA Technical Reports Server (NTRS)

    Brewer, Gerald W.

    1946-01-01

    An investigation of a 1/7-scale powered model of the Kaiser Fleetwing all-wing airplane was made in the Langley full-scale tunnel to provide data for an estimation of the flying qualities of the airplane. The analysis of the stability and control characteristics of the airplane has been made as closely as possible in accordance with the requirements of the Bureau of Aeronautics, Navy Department's specifications, and a summary of the more significant conclusions is presented as follows. With the normal center of gravity located at 20 percent of the mean aerodynamic chord, the airplane will have adequate static longitudinal stability, elevator fixed, for all flight conditions except for low-power operation at low speeds where the stability will be about neutral. There will not be sufficient down-elevator deflection available for trim above speeds of about 130 miles per hour. It is probable that the reduction in the up-elevator deflections required for trim will be accompanied by reduced elevator hinge moments for low-power operation at low flight speeds. The static directional stability for this airplane will be low for all rudder-fixed or rudder-free flight conditions. The maximum rudder deflection of 30 deg will trim only about 15 deg yaw for most flight conditions and only 10 deg yaw for the condition with low power at low speeds. Also, at low powers and low speeds, it is estimated that the rudders will not trim the total adverse yaw resulting from an abrupt aileron roll using maximum aileron deflection. The airplane will meet the requirements for stability and control for asymmetric power operation with one outboard engine inoperative. The airplane would have no tendency for directional divergence but would probably be spirally unstable, with rudders fixed. The static lateral stability of the airplane will probably be about neutral for the high-speed flight conditions and will be only slightly increased for the low-power operation in low-speed flight. The

  19. 78 FR 29666 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-21

    ...We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes; Model A340-200 and -300 series airplanes; and Model A340-541 and -642 airplanes. This proposed AD was prompted by reports of wing tip brakes (WTBs) losing their braking function in service due to heavy wear on the brake discs. WTBs are designed to stop and hold the mechanical......

  20. 77 FR 65812 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-31

    ...We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 freighter series airplanes; Model A330-200 and - 300 series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by reports of ram air turbine (RAT) pump failure. This AD requires inspecting the RAT pump anti-stall valve for correct setting, re-identifying the RAT pump, performing a......

  1. 77 FR 40830 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-11

    ...We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-200 freighter series airplanes; Model A330-200 and - 300 series airplanes; and Model A340-200 and -300 series airplanes. This proposed AD was prompted by reports of ram air turbine (RAT) pump failure. This proposed AD would require inspecting the RAT pump anti- stall valve for correct setting, re-identifying the......

  2. Correlation Tests of the Ditching Behavior of an Army B-24D Airplane and a 1/16-size Model

    NASA Technical Reports Server (NTRS)

    Jarvis, George A.; Fisher, Lloyd J.

    1946-01-01

    Behaviors of both model and full-scale airplanes were ascertained by making visual observations, by recording time histories of decelerations, and by taking motion picture records of ditchings. Results are presented in form of sequence photographs and time-history curves for attitudes, vertical and horizontal displacements, and longitudinal decelerations. Time-history curves for attitudes and horizontal and vertical displacements for model and full-scale tests were in agreement; maximum longitudinal decelerations for both ditchings did not occur at same part of run; full-scale maximum deceleration was 50 percent greater.

  3. Vapor-Liquid Equilibrium in the Mixture 1,1,1,2-Tetrafluoroethane C2H2F4 + C4H10O2 2,5-Dioxahexane (EVLM1111, LB5748_E)

    NASA Astrophysics Data System (ADS)

    Cibulka, I.; Fontaine, J.-C.; Sosnkowska-Kehiaian, K.; Kehiaian, H. V.

    This document is part of Subvolume C 'Binary Liquid Systems of Nonelectrolytes III' of Volume 26 'Heats of Mixing, Vapor-Liquid Equilibrium, and Volumetric Properties of Mixtures and Solutions' of Landolt-Börnstein Group IV 'Physical Chemistry'. It contains the Chapter 'vapor-Liquid Equilibrium in the Mixture 1,1,1,2-Tetrafluoroethane C2H2F4 + C4H10O2 2,5-Dioxahexane (EVLM1111, LB5748_E)' providing data from direct measurement of pressure at variable mole fraction in liquid phase and constant temperature.

  4. Ditching Tests of a 1/9-Size Model of the Army P-38 Airplane in Langley Tank No. 2 and at the Outdoor Catapult

    NASA Technical Reports Server (NTRS)

    Jarvis, George A.; Cederborg, Gibson A.

    1946-01-01

    A dynamically similar model of the Army P-38 airplane was tested to determine the best way to land this airplane on the water and to determine its probable ditching performance. The tests consisted of ditching the model at various landing attitudes, flap settings, speeds, weights, and conditions of simulated damage. The model was ditched in calm water from the tank towing carriage and a few ditching were made in both calm and rough water at the outdoor catapult. The performance of the model was determined by making visual observations, by recording lengths of run and time histories of decelerations, and by taking motion pictures of the ditchings.

  5. Wind-tunnel Tests of a 2-engine Airplane Model as a Preliminary Study of Flight Conditions Arising on the Failure of the Engine

    NASA Technical Reports Server (NTRS)

    Hartman, Edwin P

    1938-01-01

    Wind tunnel tests of a 15-foot-span model of a two-engine low wing transport airplane were made as a preliminary study of the emergency arising from the failure of one engine in flight. Two methods of reducing the initial yawing moment resulting from the failure of one engine were investigated and the equilibrium conditions were explored for two basic modes on one engine, one with zero angle of sideslip and the other with several degrees of sideslip. The added drag resulting from the unsymmetrical attitudes required for flight on one engine was determined for the model airplane. The effects of the application of power upon the stability, controllability, lift, and drag of the model airplane were measured. A dynamic pressure survey of the propeller slipstream was made in the neighborhood of the tail surfaces at three angles of attack. The added parasite drag of the model airplane resulting from the unfavorable conditions of flight on one engine was estimated. From 35 to 50 percent of this added drag was due to the drag of the dead engine propeller and the other 50 to 65 percent was due to the unsymmetrical attitude of the airplane. The mode of flight on one engine in which the angle of sideslip was zero was found to require less power than the mode in which the angle of sideslip was several degrees.

  6. 76 FR 12845 - Airworthiness Directives; APEX Aircraft Model CAP 10 B Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-09

    ... Register on December 30, 2010 (75 FR 82335). That NPRM proposed to correct an unsafe condition for the... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant... CAP 10 B Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation...

  7. 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

    ... G250 Airplane Pilot Compartment View--Hydrophobic Coatings in Lieu of Windshield Wipers AGENCY: Federal... windshield coating, in lieu of windshield wipers. The applicable airworthiness regulations do not contain... window coatings in lieu of windshield wipers. Type Certification Basis Under the provisions of 14 CFR...

  8. 76 FR 35336 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-17

    ... other publications listed in this AD as of August 28, 2001 (66 FR 38350, July 24, 2001). ADDRESSES: For... (NPRM) to amend 14 CFR part 39 to supersede AD 2001-14-19, amendment 39-12330 (66 FR 38350, July 24... October 7, 2010 (75 FR 61999). That NPRM proposed to continue to require, for certain airplanes,...

  9. 75 FR 11439 - Airworthiness Directives; Airbus Model A319, A320, and A321 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-11

    ... Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2009-0649; Directorate Identifier 2008-NM..., A320, and A321 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...) originated by an aviation authority of another country to identify and correct an unsafe condition on...

  10. 76 FR 25648 - Special Conditions: Gulfstream Model GVI Airplane; Limit Engine Torque Loads for Sudden Engine...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-05

    .... These proposed special conditions pertain to their effects on the structural performance of the airplane... load imposed by sudden engine stoppage due to malfunction or structural failure.'' Limit loads are... structures be able to support limit loads without detrimental permanent deformation, meaning that...

  11. 76 FR 44245 - Special Conditions: Gulfstream Model GVI Airplane; Limit Engine Torque Loads for Sudden Engine...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-25

    ... FR 25648). One supportive comment was received and the special conditions are adopted as proposed... structural performance of the airplane. The applicable airworthiness regulations do not contain adequate or... imposed by sudden engine stoppage due to malfunction or structural failure.'' Limit loads are expected...

  12. 76 FR 41041 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane, Interaction of Systems...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-13

    ... effects on structural ] performance of this system and its failures. Discussion Active flight control... controls and are given sufficient control authority to maneuver the airplane to its structural design.... Therefore, it is necessary to determine the structural factors of safety and operating margins such that...

  13. 76 FR 25229 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane, Dynamic Test Requirements...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-04

    ... G250 Airplane, Dynamic Test Requirements for Side-Facing, Single-Occupant Seats AGENCY: Federal... will have a novel or unusual design feature associated with dynamic test requirements for side-facing... dynamic testing of all seats approved for occupancy during takeoff and landing. The intent of Amendment...

  14. 75 FR 15629 - Airworthiness Directives; Cessna Aircraft Company Model 525A Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-30

    ... airplanes caused us to issue AD 2009-24-13, Amendment 39-16105 (74 FR 62479, November 30, 2009). AD 2009-24... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3... Airworthiness Directive (AD) 2009-24-13, Amendment 39-16105 (74 FR 62479, November 30, 2009), and adding...

  15. 78 FR 63848 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Sidestick Controllers

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-25

    ... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http... a new family of jet airplanes designed for corporate flight, fractional, charter, and private owner... bypass ratio turbofan engines mounted on aft fuselage pylons. Each engine produces approximately...

  16. 76 FR 8615 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-15

    ... Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR... airplanes. That NPRM was published in the Federal Register on April 8, 2010 (75 FR 17887). That NPRM... installation procedures for the stop fitting(s) for access purposes. AAL reported that Boeing does plan to...

  17. 75 FR 15357 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-29

    ... Procedures (44 FR 11034, February 26, 1979), and 3. Will not have a significant economic impact, positive or...-to-wing upper link load path and possible separation of a strut and engine from the airplane during... not detected and corrected, could result in the loss of the strut-to-wing upper link load path...

  18. 75 FR 46861 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-04

    ... 29, 2010 (75 FR 4710). That earlier NPRM proposed to supersede AD 2007-05-08, Amendment 39-14969 (72 FR 96580, March 5, 2007), to require actions intended to address the unsafe condition for the..., -500, and -600 series airplanes. We have issued AD 2010-01-07, Amendment 39-16165 (75 FR 1538,...

  19. 75 FR 53843 - Airworthiness Directives; The Boeing Company Model 737-100 and -200 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-02

    ... published in the Federal Register on May 19, 2010 (75 FR 27969). That NPRM proposed to require repetitive... Policies and Procedures (44 FR 11034, February 26, 1979), and (3) Will not have a significant economic... at body station 639, stringer S-16, and corrective actions if necessary. For certain airplanes,...

  20. 75 FR 60665 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-01

    ... MD-90-30 airplanes. This proposed AD would require repetitive high frequency eddy current inspections... 17, 2010, describes procedures for doing repetitive high frequency eddy current (HFEC) inspections... Order 12866, 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44...

  1. 75 FR 80742 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-23

    ... proposed AD by February 7, 2011. ADDRESSES: You may send comments by any of the following methods: Federal... stabilizer in accordance with AD 2007-10-04, Amendment 39-15045 (72 FR 25960, May 8, 2007). That airplane had..., Amendment 39-15947 (74 FR 30922, June 29, 2009). Uncorrected cracking could result in loss of the...

  2. 76 FR 36870 - Special Conditions: Gulfstream Model GVI Airplane; Design Roll Maneuver Requirement for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-23

    ..., 2011 (76 FR 8319). Only one comment was received, which was supportive, so these special conditions are...; Design Roll Maneuver Requirement for Electronic Flight Controls AGENCY: Federal Aviation Administration... electronic flight control system that provides roll control of the airplane through pilot inputs to...

  3. 76 FR 37684 - Airworthiness Directives; Diamond Aircraft Industries GmbH Model (Diamond) DA 40 Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-28

    ... Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will... the airplane weight and balance. This proposed AD was prompted by reports of damage around the VCS... balance. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority...

  4. 75 FR 52255 - Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-25

    ... FR 19994, April 19, 2006), the Director of the Federal Register approved the incorporation by..., AT-600, and AT- 800 series airplanes. In 2001, we issued AD 2001-10-04, Amendment 39-12230 (66 FR... full-time firefighting. In 2002, we issued AD 2002-11-05, Amendment 39-12766 (67 FR 37967, May 31,...

  5. 75 FR 12468 - Airworthiness Directives; Quartz Mountain Aerospace, Inc. Model 11E Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-16

    ... invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD... airplane painting with the rod ends exposed. Production procedures were changed to prevent further...'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not...

  6. 76 FR 65103 - Special Conditions: Gulfstream Aerospace Corporation, Model GIV-X Airplane; Aircraft Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-20

    ... Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478... connectivity capabilities of the airplane's computer systems and networks, which may allow access by external computer systems and networks. Connectivity by external systems and networks may result in...

  7. 77 FR 38467 - Special Conditions: Gulfstream Aerospace LP (GALP), Model Gulfstream G280 Airplane; Isolation or...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-06-28

    ... the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo... connectivity of the passenger service computer systems to the airplane critical systems and data networks. The.... The proposed architecture and network configuration may be used for, or interfaced with, a diverse...

  8. 77 FR 36123 - Special Conditions: Gulfstream Aerospace LP (GALP), Model Gulfstream G280 Airplane; Aircraft...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-06-18

    ... the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http://govDockets... architecture and connectivity capabilities of the airplane's computer systems and networks, which may allow access to or by external computer systems and networks. Connectivity to, or access by, external...

  9. 78 FR 65153 - Special Conditions: Learjet Model 45 Series Airplanes; Aircraft Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-31

    ... Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478... design feature associated with the architecture and connectivity capabilities of the airplanes' computer... systems architecture composed of several connected networks. The proposed architecture and...

  10. 78 FR 75451 - Special Conditions: Cessna Model 750 Series Airplanes; Aircraft Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-12

    ... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http... design feature associated with the architecture and connectivity capabilities of the airplanes' computer...; facsimile 425-227-1149. SUPPLEMENTARY INFORMATION: The proposed network architecture includes the...

  11. 76 FR 22828 - Airworthiness Directives; The Boeing Company Model 737-700 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-25

    ... 12866, 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... airplanes, replacing the seat track pivot link assemblies, seat track sections, and floor panels. For... plunger is installed across the seat track pivot joint at approximately STA 521. The existing...

  12. 75 FR 78177 - Airworthiness Directives; Cessna Aircraft Company (Cessna) Model 172 Airplanes Modified by...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-15

    ... 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... battery, replacing the supplement pilot's operating handbook and FAA approved airplane flight manual, and replacing the FADEC backup battery every 12 calendar months. This proposed AD was prompted by an...

  13. 75 FR 61655 - Airworthiness Directives; Piper Aircraft, Inc. Model PA-28-161 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-06

    ... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3... battery, replacing the supplement pilot's operating handbook and FAA approved airplane flight manual, and... can allow the FADEC to shut down or reset if the main battery is depleted and the electrical...

  14. 75 FR 81417 - Airworthiness Directives; Piper Aircraft, Inc. Model PA-28-161 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-28

    ..., 2010 (75 FR 61655). That NPRM proposed to require installation of a FADEC backup battery, replacement... Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034...) backup battery, replacing the supplement pilot's operating handbook and FAA approved airplane...

  15. 75 FR 80735 - Special Conditions: Gulfstream Model GVI Airplane; High Incidence Protection

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-23

    ... required performance standard. (5) The most unfavorable center of gravity allowable. (6) The airplane... with a required performance standard. (4) The center of gravity position that results in the highest... traditional sense at forward and aft center of gravity in straight and turning flight at IDLE power. (g) If...

  16. 76 FR 81360 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane, Operation Without Normal...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-28

    ... 27, 2011 (76 FR 66660). No comments were received, and the special conditions are adopted as proposed... generation and distribution architecture is equipped with an auxiliary power unit (APU) and is not equipped... power, which is generated by the airplane's engine generators or APU is not extremely improbable....

  17. 78 FR 41684 - Special Conditions: Embraer S.A. Model EMB-550 Airplanes, Sudden Engine Stoppage

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-11

    ... airplane, was published in the Federal Register on September 25, 2012 (77 FR 58970). No comments were... auxiliary power unit (APU) installations, the APU mounts and adjacent supporting airframe structure must be... imposed by each of the following: (a) Sudden APU deceleration due to malfunction or structural...

  18. 76 FR 8314 - Special Conditions: Gulfstream Model GVI Airplane; Operation Without Normal Electric Power

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-14

    ... power unit (APU) generated electrical power inoperative. Service experience has shown that loss of all electrical power from the airplane's engine and APU driven generators is not extremely improbable. Thus... failure must be made. 4. Availability of APU operation should not be considered in establishing...

  19. 76 FR 36864 - Special Conditions: Gulfstream Model GVI Airplane; Operation Without Normal Electric Power

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-23

    ... published in the Federal Register on February 14, 2011 (76 FR 8314). Only one comment was received, which... normal sources of engine and auxiliary power unit (APU) generated electrical power inoperative. Service experience has shown that loss of all electrical power from the airplane's engine and APU driven...

  20. 78 FR 75453 - Special Conditions: Cessna Model 750 Series Airplanes; Aircraft Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-12

    ... Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478... Airplanes; Aircraft Electronic System Security Isolation or Protection From Internal Access AGENCY: Federal... control and navigation systems, 2. Operator business and administrative support, and 3....

  1. 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

    ... the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo... GIV-X Airplane; Isolation or Aircraft Electronic System Security Protection From Unauthorized Internal..., a diverse set of functions, including: 1. Flight-safety related control, communication,...

  2. 76 FR 31454 - Special Conditions: Gulfstream Model GVI Airplane; Automatic Speed Protection for Design Dive Speed

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-01

    ... for Gulfstream GVI airplanes was published in the Federal Register on February 16, 2011 (76 FR 8917...; Automatic Speed Protection for Design Dive Speed AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... high speed protection system. These special conditions contain the additional safety standards that...

  3. 76 FR 1979 - Airworthiness Directives; The Boeing Company Model 757 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-12

    ... airplanes. That supplemental NPRM was published in the Federal Register on October 19, 2009 (74 FR 53430... Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic..., 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Steve...

  4. 75 FR 12464 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-11 and MD-11F Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-16

    ...'' (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new... may review copies of the referenced service information at the FAA, Transport Airplane Directorate... fuel tank explosions on several large transport airplanes, including the adequacy of...

  5. 75 FR 15322 - Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-29

    ... series airplanes. That NPRM was published in the Federal Register on July 2, 2009 (74 FR 31640). For...'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), and (3) Will not have a..., -300, and -300F series airplanes. For certain airplanes, this AD requires installing support...

  6. 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.

  7. Free-spinning-tunnel Investigation of a 1/30 Scale Model of a Twin-jet-swept-wing Fighter Airplane

    NASA Technical Reports Server (NTRS)

    Bowman, James S., Jr.; Healy, Frederick M.

    1960-01-01

    An investigation has been made in the Langley 20-foot free-spinning tunnel to determine the erect and inverted spin and recovery characteristics of a 1/30-scale dynamic model of a twin-jet swept-wing fighter airplane. The model results indicate that the optimum erect spin recovery technique determined (simultaneous rudder reversal to full against the spin and aileron deflection to full with the spin) will provide satisfactory recovery from steep-type spins obtained on the airplane. It is considered that the air-plane will not readily enter flat-type spins, also indicated as possible by the model tests, but developed-spin conditions should be avoided in as much as the optimum recovery procedure may not provide satisfactory recovery if the airplane encounters a flat-type developed spin. Satisfactory recovery from inverted spins will be obtained on the airplane by neutralization of all controls. A 30-foot- diameter (laid-out-flat) stable tail parachute having a drag coefficient of 0.67 and a towline length of 27.5 feet will be satisfactory for emergency spin recovery.

  8. Tabulated pressure measurements on a large subsonic transport model airplane with high bypass ratio, powered, fan jet engines

    NASA Technical Reports Server (NTRS)

    Flechner, S. G.; Patterson, J. C., Jr.

    1972-01-01

    An experimental wind-tunnel investigation to determine the aerodynamic interference and the jet-wake interference associated with the wing, pylon, and high-bypass-ratio, powered, fan-jet model engines has been conducted on a typical high-wing logistics transport airplane configuration. Pressures were measured on the wing and pylons and on the surfaces of the engine fan cowl, turbine cowl, and plug. Combinations of wing, pylons, engines, and flow-through nacelles were tested, and the pressure coefficients are presented in tabular form. Tests were conducted at Mach numbers from 0.700 to 0.825 and angles of attack from -2 to 4 deg.

  9. Spin Tunnel Investigation of a 1/30 Scale Model of the North American A-5A Airplane

    NASA Technical Reports Server (NTRS)

    Lee, Henry A.

    1964-01-01

    An investigation has been made in the Langley spin tunnel to determine the erect and inverted spin and recovery characteristics of a 1/30-scale dynamic model of the North American A-5A airplane. Tests were made for the basic flight design loading with the center of gravity at 30-percent mean aerodynamic chord and also for a forward position and a rearward position with the center of gravity at 26-percent and 40-percent mean aerodynamic chord, respectively. Tests were also made to determine the effect of full external wing tanks on both wings, and of an asymmetrical condition when only one full tank is carried.

  10. Spin-Tunnel Investigation of a 1/30-Scale Model of the North American A-5 Airplane

    NASA Technical Reports Server (NTRS)

    Lee, Henry A.

    1964-01-01

    An investigation has been made to determine the erect and. inverted spin and recovery characteristics of a 1/30-scale dynamic model of the North American A-5A airplane. Tests were made for the basic flight design loading with the center of gravity at 30-percent mean aerodynamic chord and also for a forward position and a rearward position with the center of gravity at 26-percent and 40-percent mean aerodynamic chord, respectively. Tests were also made to determine the effect of full external wing tanks on both wings, and of an asymmetrical condition when only one full tank is carried.

  11. 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.

  12. The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-flight Tunnel

    NASA Technical Reports Server (NTRS)

    Campbell, John P; Seacord, Charles L , Jr

    1943-01-01

    The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing moments of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the model were correlated with calculated stability and control characteristics and, in general, good agreement was obtained.

  13. Free-Spinning-Tunnel Tests of a 1/16-Scale Model of the Chance Vought XF5U-1 Airplane, TED No. NACA 2349

    NASA Technical Reports Server (NTRS)

    White, Richard P.

    1947-01-01

    Spin tests of a 1/16-scale model of the Chance Vought XF5U-1 airplane have been performed in the Langley 20-foot free-spinning tunnel. The effect of control position and movement upon the erect and inverted spin and recovery characteristics ae well as the effects of propellers, of stability flaps, and of various revisions to the design configuration have been determined for the normal fighter loading. The investigation also included spin recovery parachute, tumbling, and pilot-escape tests. For the original design configuration, with or without windmilling propellers, the recovery characteristics of the model were considered unsatisfactory. Increasing the maximum upward deflection of the ailavators from 45 deg to 65 deg resulted in greatly improved recovery characteristics. Dimensional revisions to the original airplane configuration, which satisfactorily improved the general spin and recovery characteristics of the model, consisted of: (1) a supplementary vertical tail 34 inches by 59 inches (full-scale) attached to a boom 80 inches aft of the trailing edge of the airplane in the plane of symmetry, (2) a large semispan undersurface spoiler placed along the airplane quarter-chord line and opened on the outboard side in a spin, or (3) two additional vertical tails 64 inches by 52 inches (full-scale) located at the tips of the ailavators. A satisfactory parachute arrangement for emergency spin recovery from demonstration spins was found to be an arrangement consisting of a 13.3-foot parachute attached by a 30-foot towline to the arresting gear mast on the airplane and opened simultaneously with an 8-foot parachute on the outboard end of the wing attached by a 3-foot towline. Tests indicated that pilot escape from a spin would be extremely hazardous unless the pilot is mechanically ejected from the cockpit. Model tumbling tests indicated that the airplane would not tumble.

  14. Aerodynamic Characteristics and Flying Qualities of a Tailless Triangular-wing Airplane Configuration as Obtained from Flights of Rocket-propelled Models at Transonic and Supersonic Speeds

    NASA Technical Reports Server (NTRS)

    Mitcham, Grady L; Stevens, Joseph E; Norris, Harry P

    1956-01-01

    A flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented.

  15. Determination of model structure and parameters of an airplane from pre- and post-stall flight data

    NASA Technical Reports Server (NTRS)

    Klein, V.; Batterson, J. G.; Murphy, P. C.

    1981-01-01

    A procedure for airplane model structure determination from flight data based on modified stepwise regression (MSR), several decision criteria and postulated aerodynamic model equations is presented. The MSR is constructed to force a linear model for the aerodynamic coefficient first, then select significant nonlinear terms and reject nonsignificant terms from the model. In addition to the statistical criteria in the stepwise regression, the prediction sum of squares (PRESS) criterion and analysis of residuals are examined for the selection of an adequate model. The procedure is used in examples with simulated and real flight data. It is shown that the MSR performs better than the ordinary stepwise regression and that the technique can be also applied to the large amplitude maneuvers.

  16. Supplementary Ditching Investigation of a 1/18-Scale Model of the North American B-45 Airplane

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; Thompson, William C.

    1949-01-01

    A supplementary investigation of a 1/18-scale dynamically similar model of the North American B-45 airplane was made in calm water to observe the ditching behavior and to determine the effect of further conditions of simulated damage. The behavior of the model was determined from motion-picture records, time-history deceleration records, and visual observations. It was concluded that, during a ditching, the nose-wheel doors, bomb-bay doors, under surface of the aft fuselage and lower part of the bomb-bay aft bulkhead will be torn away. When such damage occurs, the diving found in the previous tests will not occur and the airplane will porpoise during the first third of the landing run and then run smoothly. Because of the extensive damage which occurs, the fuselage aft of the pilots' compartment will fill with water very rapidly and is, therefore, an undesirable ditching station. No change in the previously recommended ditching attitude and flap setting (6 deg attitude, flaps down) is indicated by these supplementary tests.

  17. Wind-tunnel static and free-flight investigation of high-angle-of-attack stability and control characteristics of a model of the EA-6B airplane

    NASA Technical Reports Server (NTRS)

    Jordan, Frank L., Jr.; Hahne, David E.

    1992-01-01

    An investigation was conducted in the Langley 30- by 60-Foot Tunnel and the Langley 12-Foot Low-Speed Tunnel to identify factors contributing to a directional divergence at high angles of attack for the EA-6B airplane. The study consisted of static wind-tunnel tests, smoke and tuft flow-visualization tests, and free-flight tests of a 1/8.5-scale model of the airplane. The results of the investigation indicate that the directional divergence of the airplane is brought about by a loss of directional stability and effective dihedral at high angles of attack. Several modifications were tested that significantly alleviate the stability problem. The results of the free-flight study show that the modified configuration exhibits good dynamic stability characteristics and could be flown at angles of attack significantly higher than those of the unmodified configuration.

  18. Force Tests of a 1/5-Scale Model of the McDonnell XP-85 Airplane with Conventional Tail Assembly in the Langley Free-Flight Tunnel

    NASA Technical Reports Server (NTRS)

    Paulson, John W.; Johnson, Joseph L.

    1947-01-01

    At the request of the Air Materiel Command, Army Air Forces an investigation of the low-speed, power-off stability and control characteristics of the McDonnell XP-85 airplane is being conducted in the Langley free-flight tunnel. The XP-85 airplane is a parasite fighter carried in a bomb bay of the B-36 airplane. As a part of the investigation a few force tests were made of a 1/5 scale model of the XP-85 with a conventional tail assembly installed in place of the original design five-unit tail assembly. The total area of the conventional assembly was approximately 80 percent of the area of the five-unit assembly. The results of this investigation showed that the conventional tail assembly gave about the same longitudinal stability characteristics as the original configuration and improved the directional and lateral stability.

  19. 77 FR 73343 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-12-10

    ... 39-16634 (76 FR 15805, March 22, 2011)] had been accomplished on this seat, but due to seizure, the... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not... F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model...

  20. 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.

  1. 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.

  2. A 727 airplane center duct inlet low speed performance confirmation model test for refanned JT8D engines, phase 2

    NASA Technical Reports Server (NTRS)

    Kaldschmidt, G.; Syltebo, B. E.; Ting, C. T.

    1973-01-01

    The results from testing of a 0.3 scale model center duct inlet (S duct) for the Pratt and Whitney Aircraft JT8D-100 engines are presented. The objective of this test was to demonstrate that the required airflow of the JT8D-100 engine (480 lb/sec as compared to 334 lb/sec for JT8D-15) can be achieved with minimum modifications to the existing 727 airplane structure at acceptable levels of total pressure recovery and distortion. Steady-state pressure recovery, steady-state pressure distortion, and dynamic pressure measurements were taken at the engine face station. Surface static pressure measurements were taken along the duct. Test results indicated that the required airflow was achieved with acceptable pressure recovery (comparable to the current 727-200 S duct). Inlet inflow angle variation within the 727 airplane operating regime (minus 5 to 5 degrees) had no effect on the inlet performance. Pressure distortion at static and forward speed at takeoff airflow conditions are within P and WA limits for the Phase II duct when equipped with vortex generators. Static crosswind operation between 10 knots and 25 knots appears feasible at full takeoff power.

  3. Recent NASA Research on Aerodynamic Modeling of Post-Stall and Spin Dynamics of Large Transport Airplanes

    NASA Technical Reports Server (NTRS)

    Murch, Austin M.; Foster, John V.

    2007-01-01

    A simulation study was conducted to investigate aerodynamic modeling methods for prediction of post-stall flight dynamics of large transport airplanes. The research approach involved integrating dynamic wind tunnel data from rotary balance and forced oscillation testing with static wind tunnel data to predict aerodynamic forces and moments during highly dynamic departure and spin motions. Several state-of-the-art aerodynamic modeling methods were evaluated and predicted flight dynamics using these various approaches were compared. Results showed the different modeling methods had varying effects on the predicted flight dynamics and the differences were most significant during uncoordinated maneuvers. Preliminary wind tunnel validation data indicated the potential of the various methods for predicting steady spin motions.

  4. An Investigation of a Full-Scale Model of the Republic XF-91 Airplane in the Ames 40- By 80-Foot Wind Tunnel: Pressure Data

    NASA Technical Reports Server (NTRS)

    Hunton, Lynn W.; Dew, Joseph K.

    1949-01-01

    Wind-tunnel tests of a full-scale model of the Republic XF-91 airplane were conducted to determine the distribution of pressure over the external wing fuel tank installation and over the vee tail and ventral fin. The data were obtained for a range of angles of attack and sideslip and elerudder deflection angles; the presentation is in tabular form.

  5. Spin-Tunnel Investigation of A 1/40-Scale Model of the F-111A Airplane with Store Loadings and with Supplementary Spin-Recovery Devices

    NASA Technical Reports Server (NTRS)

    Bowman, James S., Jr.; White, William L.

    1974-01-01

    An investigation has been made in the Langley spin tunnel to determine the spin and spin-recovery characteristics of the F-111A airplane in the symmetric and asymmetric stores loading conditions. Tests were also made with the model in the clean condition to determine whether the spin-recovery characteristics could be improved by the use of supplementary devices.

  6. 76 FR 66198 - Airworthiness Directives; Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-26

    ... parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... Directives; Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 Airplanes AGENCY: Federal...

  7. 76 FR 42029 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-18

    ... products. That NPRM was published in the Federal Register on April 8, 2011 (76 FR 19724). That NPRM... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant... B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F...

  8. 76 FR 47520 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Model ATR42 and ATR72 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-05

    ... continued.airworthiness@atr.fr ; Internet http://www.aerochain.com . You may review copies of the referenced... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Transport R gional Model ATR42 and ATR72 Airplanes AGENCY: Federal Aviation Administration (FAA),...

  9. 75 FR 8476 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Model ATR42 and ATR72 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-25

    ..., amendment 39-16159 (75 FR 221, January 5, 2010), on December 28, 2009. That AD applies to certain portable...'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have... Transport R gional Model ATR42 and ATR72 Airplanes AGENCY: Federal Aviation Administration (FAA),...

  10. 76 FR 428 - Airworthiness Directives; Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-05

    ..., 2010 (75 FR 63420). That NPRM proposed to correct an unsafe condition for the specified products. The... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant.... Model BD-700-1A10 and BD-700-1A11 Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  11. 75 FR 63420 - Airworthiness Directives; Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-15

    ... Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR.... Model BD-700-1A10 and BD-700-1A11 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... damage to No. 2 and No. 3 hydraulic system lines in the wing auxiliary spar area on the left side of...

  12. 75 FR 7407 - Airworthiness Directives; Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-19

    ... caused us to issue the following ADs: AD 2004-23-17, Amendment 39-13872 (69 FR 67809, November 22, 2004... FR 34941, June 1, 2000), applicable to Commander Aircraft Company Model 114TC airplanes. A newer and... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and...

  13. 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

    ... to the specified products. That NPRM was published in the Federal Register on April 2, 2010 (75 FR... cycling and that a previous study on a Model A310 airplane had shown no reduction in stiffness due to age...'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not...

  14. Airplane Balance

    NASA Technical Reports Server (NTRS)

    Huguet, L

    1921-01-01

    The authors argue that the center of gravity has a preponderating influence on the longitudinal stability of an airplane in flight, but that manufacturers, although aware of this influence, are still content to apply empirical rules to the balancing of their airplanes instead of conducting wind tunnel tests. The author examines the following points: 1) longitudinal stability, in flight, of a glider with coinciding centers; 2) the influence exercised on the stability of flight by the position of the axis of thrust with respect to the center of gravity and the whole of the glider; 3) the stability on the ground before taking off, and the influence of the position of the landing gear. 4) the influence of the elements of the glider on the balance, the possibility of sometimes correcting defective balance, and the valuable information given on this point by wind tunnel tests; 5) and a brief examination of the equilibrium of power in horizontal flight, where the conditions of stability peculiar to this kind of flight are added to previously existing conditions of the stability of the glider, and interfere in fixing the safety limits of certain evolutions.

  15. 78 FR 72834 - Airworthiness Directives; SOCATA Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-04

    ... 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Directives; SOCATA Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... (AD) for SOCATA Model TBM 700 airplanes. This proposed AD results from mandatory...

  16. Noise reduction studies for the Cessna model 337 (0-2) airplane

    NASA Technical Reports Server (NTRS)

    Hilton, D. A.; Connor, A. B.; Dingeldein, R. C.

    1975-01-01

    A study was undertaken to determine the noise reduction potential of the 0-2 airplane in order to reduce its aural detection distance. Static and flyover noise measurements were made to document the noise signature of the unmodified airplane. The results show that significant reductions in aural detection distance can be achieved by the combination of propeller geometry changes and the addition of engine exhaust mufflers. The best results were estimated for the aircraft equipped with a six-blade propeller operating at 3/4 engine speed in combination with a 3.49 cubic foot exhaust muffler installed on each engine. Detection distance for the modified aircraft is estimated to be reduced from about 4-1/4 miles to about 1-1/2 miles when the aircraft is operating at an altitude of 1,000 ft over grassy terrain. Reducing the altitude to 300 ft over a leafy jungle ground cover should reduce the aural detection distance to 0.9 miles. Reduced aural detection distances were also indicated for a modification utilizing a direct-drive six-blade propeller of reduced radius along with smaller exhaust mufflers.

  17. A Transonic Wind-Tunnel Investigation of the Longitudinal Aerodynamic Characteristics of a Model of the Lockheed XF-104 Airplane

    NASA Technical Reports Server (NTRS)

    Hieser, Gerald; Reid, Charles F.

    1954-01-01

    The transonic longitudinal aerodynamic characteristics of a 0.0858-scale model of the Lockheed XF-104 airplane have been obtained from tests at the Langley 16-foot transonic tunnel. The results of the investigation provide some general information applicable to the transonic properties of thin, low-aspect-ratio, unswept wing configurations utilizing a high horizontal tail . The model employs a horizontal tail mounted at the top of the vertical tail and a wing with an aspect ratio of 2.5, a taper ratio of 0.385, and 3.4-percent-thick airfoil sections. The lift, drag, and static longitudinal pitching moment were measured at Mach numbers from 0.80 t o 1.09 and angles of attack from -2.5 deg to 22.5 deg. Some of the dynamic longitudinal stability properties of the airplane have been predicted from the test results. In addition, some visual flow studies on the wing surfaces obtained at Mach numbers of 0.80 and 1.00 are included. Results of the investigation show that the transonic rise in drag coefficient at zero lift is about 0.030. At high angles of attack, the model becomes longitudinally unstable at Mach numbers from 0.80 t o 0.90, whereas a reduction in static stability is experienced when very high angles of attack are reached at Mach numbers above 0.90. Longitudinal dynamic stability calculations show that the longitudinal control is good at angles of attack below the unstable break in the static pitching-moment curves, but a typical corrective control applied after the occurrence of neutral stability has little effect in averting pitch-up.

  18. 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.

  19. 76 FR 63851 - Special Conditions: Learjet Inc., Model LJ-200-1A10 Airplane, Pilot-Compartment View Through...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-14

    ... Airplane, Pilot-Compartment View Through Hydrophobic Windshield Coatings In Lieu of Windshield Wipers... will have a novel or unusual design feature associated with hydrophobic windshield coatings in lieu of... airplane uses a hydrophobic windshield coating, in lieu of windshield wipers, for an unobstructed...

  20. 76 FR 3561 - Airworthiness Directives; The Boeing Company Model 777-200 and -300 Series Airplanes Equipped...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-20

    ... Policies and Procedures (44 FR 11034, February 26, 1979), and 3. Will not have a significant economic... structural damage to the airplane, damage to other airplanes, or possible injury to people on the ground... thrust operation. If a thrust reverser inner wall overheats, separated components could cause...

  1. 75 FR 70092 - Special Conditions: Bombardier Inc. Model CL-600-2E25 Airplane, Interaction of Systems and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-17

    ...-2D24. The CL-600-2E25 will have a CBW rudder-control system that will affect the structural performance... effects of this system and its failures on structural performance. The special conditions defined herein... that will affect the structural performance of the airplane. The airplane will use a CBW Rudder...

  2. 78 FR 8961 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Hydrophobic Coatings in Lieu of...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-07

    ...-550 airplanes was published in the Federal Register on November 9, 2012, (77 FR 67308). No comments... jet airplanes designed for corporate flight, fractional, charter, and private owner operations. The... turbofan engines mounted on aft fuselage pylons. Each engine produces approximately 6,540 pounds of...

  3. 78 FR 68986 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-18

    ... and connectivity capabilities of the airplane's onboard network computer systems, which may allow access to or by external computer systems and networks. This onboard network system will be composed of a... airplane's onboard network system. The applicable airworthiness regulations do not contain adequate...

  4. 75 FR 34663 - Airworthiness Directives; The Boeing Company Model 777-200, -300, and -300ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-18

    ... series airplanes. That original NPRM was published in the Federal Register on January 29, 2007 (72 FR... Policies and Procedures (44 FR 11034, February 26, 1979), and 3. Will not have a significant economic... series airplanes. The original NPRM would have required installing Teflon sleeving under the clamps...

  5. 75 FR 9811 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-04

    ... Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic... 170 airplane full scale fatigue test, cracks were found in some structural components of the airplane... timely detection of fatigue cracks. Undetected fatigue cracks in these areas could adversely affect...

  6. 76 FR 36398 - Airworthiness Directives; BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 and Avro 146-RJ Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-22

    ... review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind..., Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425... Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44...

  7. Tests of a Full-Scale Model of the Republic XF-91 Airplane in the Ames 40- by 80-Foot Wind Tunnel. Force and Moment Data

    NASA Technical Reports Server (NTRS)

    Hunten, Lynn W.; Dew, Joseph K.

    1949-01-01

    Wind-tunnel tests of a full-scale model of the Republic XF-91 airplane having swept-back wings and a vee tail were conducted to determine both the stability and control characteristics of the model longitudinally, laterally, and directionally. Configurations of the model were investigated involving such variables as external fuel tanks, a landing gear, trailing-edge flaps, leading-edge slats, and a range of wing incidences and tail incidences.

  8. 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

  9. Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the North American XP-86 Airplane

    NASA Technical Reports Server (NTRS)

    Berman, Theodore

    1948-01-01

    A spin investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the North American XP-86 airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the design gross weight loading. The long-range loading was also investigated and the effects of extending slats and dive flaps were determined. In addition, the investigation included the determination of the size of spin-recovery parachute required for emergency recovery from demonstration spins, the rudder force required to move the rudder for recovery, and the best method for the pilot to escape if it should become necessary to do so during a spin. The results of the investigation indicated that the XP-86 airplane will probably recover satisfactorily from erect and inverted spins for all possible loadings. It was found that fully extending both slats would be beneficial but that extending the dive brakes would cause unsatisfactory recoveries. It was determined that a 10.0-foot-diameter tail parachute with a drag coefficient of 0.7 and with a towline 30.0 feet long attached below the jet exit or a 6.0-foot-diameter wingtip parachute opened on the outer wing tip with a towline 6.0 feet long would insure recoveries from any spins obtainable. The rudder-pedal force necessary to move the rudder for satisfactory recovery was found to be within the physical capabilities of the pilot.

  10. Wind-Tunnel Tests of a 0.182-Scale Model of an F4U-1 Airplane with External Stores

    NASA Technical Reports Server (NTRS)

    Silvers, H. Norman; Spreemann, Kenneth P.

    1947-01-01

    Tests were made in the Langley 7- by 10-foot tunnel on a 0.182-scale model of an F4U-1 airplane with external stores. This paper is concerned mainly with presenting the data obtained in this investigation and with a comparison of some of these data with flight-test results determining the feasibility of estimating flight buffet Mach number from tunnel data. The results of this investigation indicate that the incremental drag coefficient due to external stores may be used to estimate the maximum Mach number that the F4U-1 airplane may reach in flight when it is equipped with external stores. This estimation is conservative for the five configurations investigated by mounts varying from 0 to 10 percent of the flight limit Mach number. The free-stream tunnel Mach number corresponding to sonic flow over the lower surface of the wing in the region of the store is a good indication of the lower limit of buffet in flight of the F4U-1 airplane when equipped with external stores. The fluctuations of total pressure over the horizontal tail are not sufficiently large (maximum of 1 percent q(sub o) to cause buffeting of the airplane.

  11. Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120

    NASA Technical Reports Server (NTRS)

    Osborne, Robert S.

    1957-01-01

    The basic aerodynamic characteristics of a 0.04956-scale model of the Convair TF-102A airplane with controls undeflected have been determined at Mach numbers from 0.60 to 1.135 for angles of attack up to approximately 22 deg in the Langley 8-foot transonic tunnel. In addition, comparisons have been made with data obtained from a previous investigation of a 0.04956-scale model of the Convair F-102A airplane. The results indicated the TF-102A airplane was longitudinally stable for all conditions tested. An increase in lift-curve slope from 0.045 to 0.059 and an 11-percent rearward shift in aerodynamic-center location occurred with increases in Mach number from 0.60 to approximately 1.05. The zero-lift drag coefficient for the TF-102A airplane increased 145 percent between the Mach numbers of 0.85 and 1.075; the maximum lift-drag ratio decreased from 9.5 at a Mach number of 0.60 to 5.0 at Mach numbers above 1.025. There was little difference in the lift and pitching-moment characteristics and drag due to life between the TF-102A and F-102A configurations. However, as compared with the F-102A airplane, the zero-lift drag-rise Mach number for the TF-102A was reduced by at least 0.06, the zero-lift peak wave drag was increased 50 percent, and the maximum lift-drag ratio was reduced as much as 20 percent.

  12. Pitch Controllability Based on Airplane Model without Short-Period Approximation—Flight Simulator Experiment—

    NASA Astrophysics Data System (ADS)

    Sato, Osamu; Kobayashi, Osamu

    Pitch controllability of an airplane is very important for longitudinal flying qualities, therefore, much research has been conducted. However, it has not been clarified why pitch handling qualities degrades in the low speed, e.g. take-off and landing flight phases. On this topic, this paper investigates the effect of several parameters of the short-period mode and phugoid mode using a flight simulator. The results show the following conclusions: The difference between the initial phase angles in two modal components in the pitch attitude response to elevator step input plays the most important role in the pitch handling qualities among modal parameters; and the difference of the two modal natural frequencies has small effect on the pitch controllability even when flight speed decreases.

  13. Distribution of Pressure Over Model of the Upper Wing and Aileron of a Fokker D-VII Airplane

    NASA Technical Reports Server (NTRS)

    Fairbanks, A J

    1927-01-01

    This report describes tests made for the purpose of determining the distribution of pressure over a model of the tapered portion of the upper wing and the aileron of a Fokker D-VII Airplane. Normal pressures were measured simultaneously at 74 points distributed over the wing and aileron. Tests were made throughout the useful range of angles of attack with aileron setting ranging from -20 degrees to +20 degrees. The results are presented graphically. It was found that the pressure distribution along the chord is in general similar to that of thick tapered airfoils previously tested. The maximum resultant pressure recorded was five times the dynamic pressure. The distribution of the air load along the span may be assumed to be uniform for design purposes. Aileron displacements affect the pressures forward to the leading edge of the wing and may increase the air load on the outer portion of the wing by a considerable amount. With the wing at large angles of attack, the overhanging portion of the aileron creates usually a burble flow and therefore a large drag. The balance reduces the control stick forces at small angles of attack for all aileron displacements. At large angles of attack it does this for small displacements only. With the airplane at its maximum speed, an angle of attack of 18 degrees, and a down aileron displacement of 20 degrees, the bending moment tending to break off the overhanging portion of the aileron will be greater than that caused by a uniform static load of 35 pounds per square foot.

  14. The Light Airplane

    NASA Technical Reports Server (NTRS)

    Driggs, Ivan H.

    1925-01-01

    This report begins with a review and analysis of the work being done to develop light airplanes in the U.S. and abroad. A technical discussion of the construction and innovations in light airplanes is then presented.

  15. Transition-flight Tests of a Model of a Low-wing Transport Vertical-take-off Airplane with Tilting Wing and Propellers

    NASA Technical Reports Server (NTRS)

    Lovell, Powell M , Jr; Parlett, Lysle P

    1956-01-01

    An investigation of the stability and control of a low-wing four-engine transport vertical-take-off airplane during the transition from hovering to normal forward flight has been conducted with a remotely controlled free-flight model. The model had four propellers distributed along the wing with the thrust axes in the wing-chord plane. The wing could be rotated to 90 degrees incidence so that the propeller thrust axes were vertical for hovering flight.

  16. Initial results from flight testing a large, remotely piloted airplane model. [flight tests of remotely controlled scale model of F-15 aircraft

    NASA Technical Reports Server (NTRS)

    Holleman, E. C. (Compiler)

    1974-01-01

    The first four flights of a remotely piloted airplane model showed that a flight envelope can be expanded rapidly and that hazardous flight tests can be conducted safely with good results. The flights also showed that aerodynamic data can be obtained quickly and effectively over a wide range of flight conditions, clear and useful impressions of handling and controllability of configurations can be obtained, and present computer and electronic technology provide the capability to close flight control loops on the ground, thus providing a new method of design and flight test for advanced aircraft.

  17. Summary of flight tests to determine the spin and controllability characteristics of a remotely piloted, large-scale (3/8) fighter airplane model

    NASA Technical Reports Server (NTRS)

    Holleman, E. C.

    1976-01-01

    An unpowered, large, dynamically scaled airplane model was test flown by remote pilot to investigate the stability and controllability of the configuration at high angles of attack. The configuration proved to be departure/spin resistant; however, spins were obtained by using techniques developed on a flight support simulator. Spin modes at high and medium high angles of attack were identified, and recovery techniques were investigated. A flight support simulation of the airplane model mechanized with low speed wind tunnel data over an angle of attack range of + or - 90 deg. and an angle of sideslip range of + or - 40 deg. provided insight into the effects of altitude, stability, aerodynamic damping, and the operation of the augmented flight control system on spins. Aerodynamic derivatives determined from flight maneuvers were used to correlate model controllability with two proposed departure/spin design criteria.

  18. Rotary balance data for a typical single-engine general aviation design for an angle-of-attack range of 8 deg to 90 deg. 1: Influence of airplane components for model D. [Langley spin tunnel tests

    NASA Technical Reports Server (NTRS)

    Ralston, J.

    1983-01-01

    The influence of airplane components, as well as wing location and tail length, on the rotational flow aerodynamics is discussed for a 1/6 scale general aviation airplane model. The airplane was tested in a built-up fashion (i.e., body, body-wing, body-wing-vertical, etc.) in the presence of two wing locations and two body lengths. Data were measured, using a rotary balance, over an angle-of-attack range of 8 deg to 90 deg, and for clockwise and counter-clockwise rotations covering an omega b/2V range of 0 to 0.9.

  19. High Speed Stability and Control Characteristics of a 0.17-Scale Model of the McDonnell XF2H-1 Airplane (TED No. NACA DE 318)

    NASA Technical Reports Server (NTRS)

    Axelson, John A.; Emerson, Horace F.

    1949-01-01

    High-speed wind-tunnel tests were conducted of two versions of a 0.17-scale model of the McDonnell XF2H-1 airplane to ascertain the high-speed stability and control characteristics and to study means for raising the high-speed buffet limit of the airplane, The results for the revised model, employing a thinner wing and tail than the original model, revealed a mild diving tendency from 0.75 to 0.80 Mach number, followed by a marked climbing tendency from 0.80 to 0.875 Mach number. The high-speed climbing tendency was caused principally by the pitching-moment characteristics of the wing. At 0.875 Mach number the results for the revised model indicated stick-fixed directional instability over a limited range of yaw angles, apparently caused by separated flow over the vertical tail. The test results indicate that the high-speed buffet limit of the airplane can probably be raised by reducing the thickness and changing the relative location of the horizontal and vertical tails, and by revising the inner portion of the wing to have a lower thickness-to-chord ratio and reduced trailing-edge angle. The addition of the wing-tip tanks to the revised model resulted in a forward shift in the neutral point below 0.82 Mach number.

  20. 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

  1. Experimental and analytical study on the flutter and gust response characteristics of a torsion-free-wing airplane model. [in the Langley transonic dynamics tunnel

    NASA Technical Reports Server (NTRS)

    Murphy, A. C.

    1981-01-01

    Experimental data and correlative analytical results on the flutter and gust response characteristics of a torsion-free-wing (TFW) fighter airplane model are presented. TFW consists of a combined wing/boom/canard surface and was tested with the TFW free to pivot in pitch and with the TFW locked to the fuselage. Flutter and gust response characteristics were measured in the Langley Transonic Dynamics Tunnel with the complete airplane model mounted on a cable mount system that provided a near free flying condition. Although the lowest flutter dynamic pressure was measured for the wing free configuration, it was only about 20 deg less than that for the wing locked configuration. However, no appreciable alleviation of the gust response was measured by freeing the wing.

  2. Free-Spinning-Tunnel Tests of a 1/29-Scale Model of the Republic XP-91 Airplane with a Vee Tail Installed

    NASA Technical Reports Server (NTRS)

    Snyder, Thomas L.

    1948-01-01

    A spin investigation has been conducted in the Langley 20 -foot free-spinning tunnel on a 1/29 - scale model of the Republic XP-91 airplane with vee tail installed. The effects cf control settings and movements upon the effect spin and recovery characteristics of the model were determined for the clean condition (wing tanks removed, landing gear and flaps retracted). The tests were made at a loading simulating that following cruise at altitude and at a time when nearly all fuel was expended. The results indicated that the airplane might not spin at normal spinning-control configuration, but if a spin were obtained, recovery therefrom by full rudder reversal would be satisfactory. It was also indicated that aileron-against settings would lead to violent oscillatory motions and should be avoided.

  3. 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.

  4. 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

    ... safety standards that the Administrator considers necessary to establish a level of safety equivalent to... four-engine jet transport airplane that will have a maximum takeoff weight of 975,000 pounds,...

  5. 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.

  6. 75 FR 60611 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-01

    ... products. That NPRM was published in the Federal Register on May 19, 2010 (75 FR 27956). That NPRM proposed... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F...

  7. High-Speed Load Distribution on the Wing of a 3/16-Scale Model of a Scout-Bomber Airplane with Flaps Deflected

    NASA Technical Reports Server (NTRS)

    Barnes, Robert H.

    1947-01-01

    The tests reported herein were made for the purpose of determining the high-speed load distribution on the wing of a 3/16 scale model of a scout-bomber airplane. Comparisons are made between the root bending-moment and section torsional-moment coefficients as obtained experimentally and derived analytically. The results show good correlation for the bending-moment coefficients but considerable disagreement for the torsional-moment coefficients.

  8. General problem of the airplane

    NASA Technical Reports Server (NTRS)

    Richard, Maurice; Richard, Paul

    1922-01-01

    A series of equations relating to airplanes are given and examples listed. Some of the equations listed include: the speed, altitude and carrying capacity of various airplanes; weight of an airplane; weight of various parts of an airplane; the polars of the wings; speeds of airplanes; radius of action.

  9. Ditching Tests of a 1/8-Scale Model of the Chance Vought XF6U-1 Airplane, TED No. NACA DE319

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J., Jr.; McBride, Ellis E.

    1953-01-01

    Tests were made with a 1/8-scale dynamically similar model of the Chance Vought XF6U-1 airplane to study its behavior 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 behavior of the model was determined from visual observations, by recording time histories of the accelerations, and by taking motion pictures of the ditchings. From the results of the tests it was concluded that the airplane should be ditched at the near-stall, tail-down attitude (12 deg). The flaps should be fully extended to obtain the lowest possible landing speed. The wing-tip tanks should be jettisoned. The underside of the fuselage will be critically damaged in a ditching and the airplane will dive violently after a run of about three fuselage lengths. Maximum longitudinal decelerations up to about 7g and maximum vertical accelerations up to about 5g will be encountered.

  10. 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.

  11. 77 FR 58787 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-24

    ...We propose to supersede an existing airworthiness directive (AD) that applies to 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) airplanes. The existing AD currently requires repetitive inspections of the rudder travel limiter (RTL) return springs......

  12. 77 FR 55159 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-07

    ...We are revising an earlier proposed airworthiness directive (AD) for certain The Boeing Company Model 737-700, -700C, -800, and - 900ER series airplanes, Model 747-400F series airplanes, and Model 767- 200 and -300 series airplanes. That NPRM proposed to require an inspection for affected serial numbers of the crew oxygen mask stowage box units; and replacement of the crew oxygen mask stowage......

  13. Free-Spinning-Tunnel Investigation of a 1/24-Scale Model of the Grumman AF-2S, -2W Airplane

    NASA Technical Reports Server (NTRS)

    Klinar, Walter J.; Wilson, Jack H.

    1950-01-01

    An investigation of the spin and recovery characteristics of a 1/24-scale model of the Grumman AF-2S, -2W airplane was conducted in the Langley 20-foot free-spinning tunnel. The effects of controls on the erect and inverted spin and recovery characteristics for a range of possible loadings of the.airplane were determined. The effect of a revised-tail installation (small dual fins added to the stabilizer of the original tail and the vertical-tail height of the original tail increased) and the effect of various ventral-fin and antispin-fillet installations were determined. The investigation also included spin-recovery parachute tests.

  14. Transonic flutter and gust-response tests and analyses of a wind-tunnel model of a torsion free wing airplane

    NASA Technical Reports Server (NTRS)

    Ruhlin, C. L.; Murphy, A. C.

    1981-01-01

    An exploratory study of a 1/5.5 size, complete airplane version of a torsion free wing (TFW) fighter aircraft was conducted. The TFW consisted of a wing/boom/canard assembly on each fuselage side that was interconnected by a common pivot shaft so that the TFW could rotate freely in pitch. The effect of the TFW was evaluated by comparing data obtained with the TFW free and the TFW locked to the fuselage. With the model mounted on cables to simulate an airplane free flying condition, flutter boundaries were measured at Mach number (M) from 0.85 to 1.0 and gust responses at M = 0.65 and 0.90. The critical flutter mode for the TFW free configuration was found experimentally to occur at M = 0.95 and had the rigid TFW pitch mode as its apparent aerodynamic driver.

  15. Determination of Longitudinal Stability and Control Characteristics from Free-Flight Model Tests with Results at Transonic Speeds for Three Airplane Configurations

    NASA Technical Reports Server (NTRS)

    Gillis, Clarence L; Mitchell, Jesse L

    1957-01-01

    A test technique and data analysis method has been developed for determining the longitudinal aerodynamic characteristics from free-flight tests of rocket-propelled models. The technique makes use of accelerometers and an angle-of-attack indicator to permit instantaneous measurements of lift, drag, and pitching moments. The data, obtained during transient oscillations resulting from control-surface disturbances, are analyzed by essentially nonlinear direct methods (such as cross plots of the variation of lift coefficient with angle of attack) and by linear indirect methods by using the equations of motion for a transient oscillation. The analysis procedure has been set forth in some detail and the feasibility of the method has been demonstrated by data measured through the transonic speed range on several airplane configurations. It was shown that the flight conditions and dynamic similitude factors for the tests described were reasonably close to typical full-scale airplane conditions.

  16. 78 FR 78294 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-26

    ...We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-200, A340-300, A340-500, and A340-600 series airplanes. This proposed AD was prompted by the failure of the generator control unit-constant speed motor/generator (GCU-CSM/G) during a final assembly operational test. This proposed AD would......

  17. 78 FR 64156 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-28

    ... ADs for Model A340 airplanes. AD 2003-14-11, Amendment 39-13230 (68 FR 41521, July 14, 2003). AD 2004-11-08, Amendment 39-13654 (69 FR 31874, June 8, 2004). AD 2004-13-25, Amendment 39-13707 (69 FR 41394...) through (i)(7) of this AD for Model A340 airplanes only. (1) AD 2003-14-11, Amendment 39-13230 (68...

  18. Free-Spinning-Tunnel Investigation of a 1/20-Scale Model of the North American T2J-1 Airplane

    NASA Technical Reports Server (NTRS)

    Bowman, James S., Jr.; Healy, Frederick M.

    1959-01-01

    An investigation has been made in the Langley 20-foot free-spinning tunnel to determine the erect and inverted spin and recovery characteristics of a 1/20-scale dynamic model of the North American T2J-1 airplane. The model results indicate that the optimum technique for recovery from erect spins of the airplane will be dependent on the distribution of the disposable load. The recommended recovery procedure for spins encountered at the flight design gross weight is simultaneous rudder reversal to against the spin and aileron movement to with the spin. With full wingtip tanks plus rocket installation and full internal fuel load, rudder reversal should be followed by a downward movement of the elevator. For the flight design gross weight plus partially full wingtip tanks, recovery should be attempted by simultaneous rudder reversal to against the spin, movement of ailerons to with the spin, and ejection of the wing-tip tanks. The optimum recovery technique for airplane-inverted spins is rudder reversal to against the spin with the stick maintained longitudinally and laterally neutral.

  19. Free-Spinning-Tunnel Investigation of a 1/25-Scale Model of the Chance Vought F8U-1P Airplane

    NASA Technical Reports Server (NTRS)

    Browman, James S., Jr.; Healy, Frederick M.

    1959-01-01

    An investigation has been made in the Langley 20-foot free-spinning tunnel on a 1/25-scale dynamic model to determine the spin and recovery characteristics of the Chance Vought F8U-1P airplane. Results indicated that the F8U-IP airplane would have spin-recovery characteristics similar to the XF8U-1 design, a model of which was tested and the results of the tests reported in NACA Research Memorandum SL56L31b. The results indicate that some modification in the design, or some special technique for recovery, is required in order to insure satisfactory recovery from fully developed erect spins. The recommended recovery technique for the F8U-lP will be full rudder reversal and movement of ailerons full with the spin (stick right in a right spin) with full deflection of the wing leading- edge flap. Inverted spins will be difficult to obtain and any inverted spin obtained should be readily terminated by full rudder reversal to oppose the yawing rotation and neutralization of the longitudinal and lateral controls. In an emergency, the same size parachute recommended for the XFBU-1 airplane will be adequate for termination of the spin: a stable parachute 17.7 feet in diameter (projected) with a drag coefficient of 1.14 (based on projected diameter) and a towline length of 36.5 feet.

  20. Longitudinal Control Characteristics of a 1/20-Scale Model of the Convair F-102 Airplane at Transonic Speeds

    NASA Technical Reports Server (NTRS)

    Osborne, Robert S.; Tempelmeyer, Kenneth E.

    1954-01-01

    The effects of elevator deflections from 0deg to -20deg on the force and moment characteristics of a 1/20-scale model of the Convair F-102 airplane with chordwise fences have been determined a t Mach numbers from 0.6 to 1.1 for angles of attack up to 20deg in the Langley 8-foot transonic tunnel. The configuration exhibited static longitudinal stability throughout the range tested, although a mild pitch-up tendency was indicated a t Mach numbers from 0.85 to 0.95. Elevator pitch effectiveness decreased rapidly between the Mach numbers of 0.9 and 1.0, however, no complete loss or reversal was indicated for all conditions tested. Because of the type of longitudinal control used, trimming the configuration from the zero elevator condition resulted in substantial decreases in lift-curve slope and maximum lift-drag ratio and increases in drag due to lift. The drag at zero lift, drag due to lift, and trim drag were high for this configuration.

  1. Effects of Fuselage Modifications on the Drag Characteristics of a 1/20-Scale Model of the Convair F-102 Airplane at Transonic Speeds

    NASA Technical Reports Server (NTRS)

    Kelly, Thomas C.; Osborne, Robert S.

    1954-01-01

    An investigation has been conducted in the Langley 8-foot transonic tunnel to determine the effects of several fuselage modifications on the transonic drag-rise characteristics of a 1/20-scale model of the Convair F-102 airplane. Tests covered an angle-of-attack range from 0deg to about 10deg and a Mach number range from 0.60 to 1.14. Results indicated that the transonic drag rise .for the basic F-102 airplane could be substantially reduced by extending the fuselage after-body approximately 8 percent of the fuselage length. Tests of other bodies indicated that a shorter (4-percent) afterbody extension may have a similar effect on the drag rise. Further improvement of the axial cross-sectional-area distribution of the 8-percent extended configuration through the addition of fuselage volume resulted in additional reductions in the drag rise at a Mach number of 1.0 and caused no or only slight drag penalties at the higher Mach numbers. The results of the present tests generally substantiate the area-rule concept with respect to the prediction of the transonic drag rise through the use of an equivalent-area body of revolution for a practical delta-wing airplane configuration.

  2. Wind Tunnel Testing of a 120th Scale Large Civil Tilt-Rotor Model in Airplane and Helicopter Modes

    NASA Technical Reports Server (NTRS)

    Theodore, Colin R.; Willink, Gina C.; Russell, Carl R.; Amy, Alexander R.; Pete, Ashley E.

    2014-01-01

    In April 2012 and October 2013, NASA and the U.S. Army jointly conducted a wind tunnel test program examining two notional large tilt rotor designs: NASA's Large Civil Tilt Rotor and the Army's High Efficiency Tilt Rotor. The approximately 6%-scale airframe models (unpowered) were tested without rotors in the U.S. Army 7- by 10-foot wind tunnel at NASA Ames Research Center. Measurements of all six forces and moments acting on the airframe were taken using the wind tunnel scale system. In addition to force and moment measurements, flow visualization using tufts, infrared thermography and oil flow were used to identify flow trajectories, boundary layer transition and areas of flow separation. The purpose of this test was to collect data for the validation of computational fluid dynamics tools, for the development of flight dynamics simulation models, and to validate performance predictions made during conceptual design. This paper focuses on the results for the Large Civil Tilt Rotor model in an airplane mode configuration up to 200 knots of wind tunnel speed. Results are presented with the full airframe model with various wing tip and nacelle configurations, and for a wing-only case also with various wing tip and nacelle configurations. Key results show that the addition of a wing extension outboard of the nacelles produces a significant increase in the lift-to-drag ratio, and interestingly decreases the drag compared to the case where the wing extension is not present. The drag decrease is likely due to complex aerodynamic interactions between the nacelle and wing extension that results in a significant drag benefit.

  3. Landing performance of an air cushion landing system installed on a 1/10-scale dynamic model on the C-8 Buffalo airplane

    NASA Technical Reports Server (NTRS)

    Thompson, W. C.

    1973-01-01

    An experimental study was conducted to evaluate the landing behavior of a 1/10-scale dynamic model of the C-8 Buffalo airplane equipped with an air-cushion landing system (ACLS) on a variety of surfaces including both calm and rough water and a smooth hard surface. Taxi runs were made on the hard surface over several obstacles. Landings were made with the model at various pitch and roll attitudes and vertical velocities and at one nominal horizontal velocity. Data from the landings include time histories of the trunk and air-cushion pressures and accelerations at selected locations on the model.

  4. 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.

  5. Langley Full-Scale Tunnel Investigation of a 1/3-Scale Model of the Chance Vought XF5U-1 Airplane

    NASA Technical Reports Server (NTRS)

    Lange, Roy H.; Cocke, Bennie W., Jr.; Proterra, Anthony J.

    1946-01-01

    The results of an investigation of a 1/3-scale model of the Chance Vought XF5U-1 airplane in the Langley full-scale tunnel are presented in this report. The maximum lift and stalling characteristics of several model configurations, the longitudinal stability characteristics of the model, and the effectiveness of the control surfaces were determined with the propellers removed. The propulsive characteristics, the effect of propeller operation on the lift, and the static thrust of the model propellers were determined at several propeller-blade angles. The results with the propellers removed showed that the maximum lift coefficient of the complete model configuration was only 0.97 was compared with the value of 1.31 for the model configuration in which the engine-air ducts and canopy are removed. The model with the propellers removed (normal center-of-gravity position) has a positive static margin, stick fixed, varying from 5 to 13 percent of the mean aerodynamic chord throughout the unstalled range of lift coefficients. The unit horizontal tail is sufficiently powerful to trim the airplane with the propellers removed throughout the unstalled range of lift coefficients. The peak propulsive efficiencies for beta = 20 degrees and beta = 30 degrees were increased 7 percent at C(sub L) congruent to 0.67 and 20 percent at C(sub L) congruent to 0.74, respectively, with the propellers rotating upward in the center than with the propellers rotating downward in the center. Indications are that the minimum forward-flight speed of the airplane for full-power operation at sea level will be about 90 miles per hour. Decreasing the weight and increasing the power reduced this value of minimum speed and there were no indications from the results of a lower limit to the minimum speed.

  6. 78 FR 39633 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-02

    ..., Amendment 39-6794 (55 FR 46499, November 5, 1990). (1) For Model 757 series airplanes, line numbers 001... 90-23-06, Amendment 39-6794 (55 FR 46499, November 5, 1990). (2) For Model 757 series airplanes, line...-23-06, Amendment 39-6794 (55 FR 46499, November 5, 1990), for certain Boeing Model 757...

  7. Wind-tunnel investigation at low speeds of a model of the Kestrel (XV-6A) vectored-trust V/STOL airplane

    NASA Technical Reports Server (NTRS)

    Margason, R. J.; Vogler, R. D.; Winston, M. M.

    1972-01-01

    Longitudinal and lateral stability data were obtained with the model out of and in ground effect over a moving ground plane for a range of model angles of attack and sideslip at various thrust coefficients. These data were taken primarily at thrust coefficients which simulate transition speeds on the airplane between hover and 200 knots. Some data, however, represent the effect of thrust deflection at speeds up to 350 knots. Also presented are the effects of control-surface deflections and interference between the jets and free stream.

  8. 76 FR 22302 - Airworthiness Directives; Airbus Model A310 Series Airplanes; and Model A300 B4-600, A300 B4-600R...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-21

    ... products. That NPRM was published in the Federal Register on August 23, 2010 (75 FR 51698). That NPRM...'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have... A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes) AGENCY:...

  9. Free-Spinning Tunnel Tests of a 1/20-Scale Model of the Chance Vought XF6U-1 Airplane, TED No. NACA 2390

    NASA Technical Reports Server (NTRS)

    Klinar, Walter J.

    1946-01-01

    A spin investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/20-scale model of the Chance Vought XF6U-1 airplane, The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the normal-fighter condition. The investigation also included tests for the take-off fighter condition (wing-tip tanks plus fuel added) spin-recovery parachutes, and simulated pilot escape. In general, for the normal-fighter condition, the model was extremely oscillatory in roll, pitch, and yaw. The angles of the fuselage varied from extremely flat to inverted attitudes, and the model rotated with the rudder in a series of short turns and glides. Recoveries by rudder reversal were rapid but the model would immediately go into a spin in the other direction. Recoveries by merely neutralizing the rudder were satisfactory when the elevator and ailerons were set to neutral, the ensuing flight path being a steep glide. Thus, it is recommended that all controls be neutralized for safe recovery from spins obtained on the airplane. With the external wing-tip tanks installed, the spins were somewhat less oscillatory in roll but recovery could not be obtained unless full-down elevator was used in conjunction with the rudder. If a spin is entered inadvertently with the full-scale airplane with external wing-tip tanks installed and if recovery is not imminent after a recovery attempt is made, it is recommended that the tanks be jettisoned and the controls neutralized.

  10. Measurements of the Buffeting Loads on the Wing and Horizontal Tail of a 1/4-scale Model of the X-1E Airplane

    NASA Technical Reports Server (NTRS)

    Rainey, A Gerald; Igoe, William B

    1958-01-01

    The buffeting loads acting on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane have been measured in the Langley 16-foot transonic tunnel in the Mach number range from 0.40 to 0.90. When the buffeting loads were reduced to a nondimensional aerodynamic coefficient of buffeting intensity, it was found that the maximum buffeting intensity of the horizontal tail was about twice as large as that of the wing. Comparison of power spectra of buffeting loads acting on the horizontal tail of the airplaneand of the model indicated that the model horizontal tail, which was of conventional force-test-model design, responded in an entirely different mode than did the airplane.This result implied that if quantitative extrapolation of model data to flight conditions were desired a dynamically scaled model of the rearward portion of the fuselage and empennage would be required. A study of the sources of horizontal-tail buffeting of the model indicated that the wing wake contributed a large part of the total buffeting load. At one condition it was found that removal of the wing wake would reduce the buffeting loads on the horizontal tail to about one-third of the original value.

  11. 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.

  12. 75 FR 82337 - Airworthiness Directives; The Boeing Company Model 777-200, -300, and -300ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-30

    ...; installing airplane information management system 2 (AIMS-2) software in the AIMS-2 hardware; and making... (AIMS-2) software in the AIMS-2 hardware, in accordance with the Accomplishment Instructions of Boeing... ] override/jettison and main jettison fuel pumps. This proposed AD would also require installing new...

  13. 76 FR 42024 - Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-18

    ... Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2011-0257; Directorate Identifier 2010-NM..., A319, A320, and A321 Series Airplanes AGENCY: Department of Transportation (DOT), Federal Aviation... information (MCAI) originated by an aviation authority of another country to identify and correct an...

  14. 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

    ... Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478... structural performance of the airplane. The applicable airworthiness regulations do not contain adequate or..., affect structural performance. These systems include flight control systems, autopilots,...

  15. 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

    ... the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo..., affect its structural performance. Current regulations do not take into account loads for the airplane due to the effects of systems on structural performance including normal operation and...

  16. 78 FR 11556 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Interaction of Systems and Structures

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-19

    ... was published in the Federal Register on November 28, 2012, (77 FR 70941). No comments were received..., affect its structural performance. Current regulations do not take into account loads for the airplane due to the effects of systems on structural performance including normal operation and...

  17. 76 FR 41045 - Special Conditions; Gulfstream Aerospace LP (GALP) Model G250 Airplane, Design Roll-Maneuver...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-13

    ... Administrator considers necessary to establish a level of safety equivalent to that established by the existing... 20.8-foot tail height. Maximum takeoff weight is 39,600 pounds and maximum landing weight 32,700... airplanes with engines or other weight concentrations outboard of the fuselage. For the...

  18. 76 FR 57627 - Special Conditions: Cessna Aircraft Company Model M680 Airplane; Rechargeable Lithium-Ion Battery...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-09-16

    ... published in the Federal Register on July 1, 2011 (76 FR 41142). No comments were received, and the special... Airplane; Rechargeable Lithium-Ion Battery Installations AGENCY: Federal Aviation Administration (FAA), DOT... lithium-ion batteries. The applicable airworthiness regulations do not contain adequate or...

  19. 78 FR 52107 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Rechargeable Lithium...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-22

    ... April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo.dot.gov/ gov/. Docket: Background... Series Airplanes; Rechargeable Lithium Ion Batteries and Battery Systems AGENCY: Federal Aviation... lithium ion batteries and battery system that will be used on an International Communications Group...

  20. 76 FR 57625 - Special Conditions: Boeing Model 737-600, -700, -700C, -800, -900, and -900ER Series Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-09-16

    ... Series Airplanes; Rechargeable Lithium-Ion Battery Installations AGENCY: Federal Aviation Administration... rechargeable lithium-ion batteries. The applicable airworthiness regulations do not contain adequate or... Specialists, Inc., proposes to use rechargeable lithium-ion batteries in a dual Class 3 EFB system on...

  1. 78 FR 62495 - Special Conditions: Learjet Model 35, 35A, 36, and 36A Airplanes; Rechargeable Lithium-Ion...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-22

    ..., 2000 (65 FR 19477-19478), as well as at http://DocketsInfo.dot.gov/ . Docket: Background documents or... Airplanes; Rechargeable Lithium-Ion Batteries and Battery Systems AGENCY: Federal Aviation Administration... associated with rechargeable lithium-ion batteries and battery systems. These batteries have certain...

  2. 75 FR 27406 - Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10 (Challenger 300) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-17

    ... Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or... airplanes, insulation near the safety valve opening, and foam in the area surrounding the safety valves..., removing discrepant material, cleaning the surfaces of the valves, and securing insulation are required,...

  3. 77 FR 67308 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Hydrophobic Coatings in Lieu of...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-09

    ... April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo.dot.gov/ . Docket: Background... jet airplanes designed for corporate flight, fractional, charter, and private owner operations. The... turbofan engines mounted on aft fuselage pylons. Each engine produces approximately 6,540 pounds of...

  4. 77 FR 70384 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Design Roll Maneuver for Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-26

    ... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http... first of a new family of jet airplanes designed for corporate flight, fractional, charter, and private... medium bypass ratio turbofan engines mounted on aft fuselage pylons. Each engine produces approximately...

  5. 77 FR 69571 - Special Conditions: Embraer S.A., Model EMB-550 Airplane, Limit Pilot Forces for Sidestick Control

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-20

    ... the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo... first of a new family of jet airplanes designed for corporate flight, fractional, charter, and private... medium bypass ratio turbofan engines mounted on aft fuselage pylons. Each engine produces approximately...

  6. 78 FR 63902 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: Normal...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-25

    ... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http... of a new family of jet airplanes designed for corporate flight, fractional, charter, and private... medium bypass ratio turbofan engines mounted on aft fuselage pylons. Each engine produces approximately...

  7. 75 FR 47203 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-11 and MD-11F Airplanes Equipped...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-05

    ... airplanes. That NPRM was published in the Federal Register on April 7, 2008 (73 FR 18719). That NPRM.... FAA-2008-0402, Directorate Identifier 2007-NM-165- AD (73 FR 18721, April 7, 2008), proposes to... (Directorate Identifier 2007-NM-165-AD, Docket FAA- 2008-0402 (73 FR 18721, April 7, 2008)), which...

  8. 78 FR 68985 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-18

    ... and data networks. This onboard network system will be composed of a network file server, a network... installation of an onboard network system, associated line replaceable units (LRUs) and additional software..., -300ER series airplanes will incorporate the following novel or unusual design features: An...

  9. 75 FR 35 - Special Conditions: Airbus Model A318-112 Airplane (S/N 3886); Certification of a Cooktop

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-04

    ... be a novel or unusual design feature. Discussion Currently, ovens are the prevailing means of heating food on airplanes. Ovens are characterized by an enclosure that contains both the heat source and the food being heated. The hazards presented by ovens are thus inherently limited, and are well...

  10. 75 FR 9756 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-100 and DHC-8-200 Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-04

    .... That NPRM was published in the Federal Register on August 13, 2009 (74 FR 40778). That NPRM proposed to... Policies and Procedures (44 FR 11034, February 26, 1979), and (3) Will not have a significant economic..., and -315 airplanes. This AD requires implementing a corrosion prevention and control program...

  11. 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

    ... February 10, 2011 (76 FR 7513). The NPRM proposed a general visual inspection for cracks and holes of the... actions be done in accordance with Boeing Alert Service Bulletin 747-25A3588, Revision 1, dated April 7... 747-25A3588, Revision 1, dated April 7, 2011, removes airplane RT101 from this service...

  12. 78 FR 11555 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Design Roll Maneuver for Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-19

    ... Embraer S.A. EMB-550 airplanes was published in the Federal Register on November 26, 2012 (77 FR 70384...; Design Roll Maneuver for Electronic Flight Controls AGENCY: Federal Aviation Administration (FAA), DOT... design roll maneuver for electronic flight controls, specifically an electronic flight control...

  13. 76 FR 1351 - Airworthiness Directives; The Boeing Company Model 757-200, -200CB, and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-10

    ... the lap joint at stringer 4L (left) of the chem-milled step. The airplane had accumulated 24,631 total... interior surface along the chem-milled step edges above the stringer 4L or 4R (right) lap splices of the... Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44...

  14. 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

    ... April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo.dot.gov/ . Docket: Background... regulations do not contain adequate or appropriate safety standards for this design feature. These special..., A319, A320, and A321 series airplanes because of a novel or unusual design feature, special...

  15. 75 FR 76647 - Special Conditions: Boeing Model 747-8 Airplanes, Systems and Data Networks Security-Isolation or...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-09

    ... passenger domain computer systems to the airplane critical systems and data networks. The applicable...: Digital systems architecture composed of several connected networks. The proposed network architecture... Domain), and 4. The capability to allow access to or by external network sources. Discussion The...

  16. 76 FR 23921 - Airworthiness Directives; Hawker Beechcraft Corporation Models B300 and B300C (C-12W) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-29

    ... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will... charts in the FAA-approved airplane flight manual and the pilot's operating handbook, part number (P/N... This proposed AD would require inserting an update to the performance charts in the...

  17. 78 FR 70849 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-27

    ... Series Airplanes; Aircraft Electronic System Security Protection from Unauthorized Internal Access... regulatory adequacy under Sec. 611 of Public Law 92-574, the ``Noise Control Act of 1972.'' The FAA issues... between systems, including: 1. Flight-safety related control and navigation systems, 2. Operator...

  18. The Airplane Experiment.

    ERIC Educational Resources Information Center

    Larson, Lee; Grant, Roderick

    1991-01-01

    Presents an experiment to investigate centripetal force and acceleration that utilizes an airplane suspended on a string from a spring balance. Investigates the possibility that lift on the wings of the airplane accounts for the differences between calculated tension and measured tension on the string. (MDH)

  19. Metal Airplane Construction

    NASA Technical Reports Server (NTRS)

    1926-01-01

    It has long been thought that metal construction of airplanes would involve an increase in weight as compared with wood construction. Recent experience has shown that such is not the case. This report describes the materials used, treatment of, and characteristics of metal airplane construction.

  20. Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds

    NASA Technical Reports Server (NTRS)

    Tempelmeyer, Kenneth E.; Osborne, Robert S.

    1955-01-01

    Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 . In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose section with a smooth area distribution. Fuselage modifications employed on the F-102A were responsible for a 25.percent reduction in the minimum drag-coefficient rise between the Mach numbers of 0.85 and 1.075 when compared with that for the earlier versions of the F-102. Although the wing modifications increased the F-102A subsonic minimum drag-coefficient level approximately 0.0020, they produced large decreases in drag at lifting conditions over that for the original (plane-wing) F-102. The F-102A had 15 to 25 percent higher maximum lift-drag ratios than did the original F-102. The F-102A had about 15 percent lower maximum lift-drag ratios at Mach numbers below 0.95 and slightly higher maximum lift-drag ratios at supersonic speeds when compared with those ratios for sn earlier modified-wing version of the F-102. Chordwise wing fences which provided suitable longitudinal stability for the original F-102 were not adequate for the cambered-wing F-102A The pitching-moment curves indicated a region of near neutral stability with possible pitch-up tendencies for the F-102A at high subsonic Mach numbers for lift coefficients between about 0.4 and 0.5.

  1. 78 FR 76736 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Side...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-19

    ... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http... BD- 500-1A11 Series Airplanes; Side Stick Controllers: Pilot Strength, Pilot Control Authority, and...-1A10 and BD-500-1A11 series airplanes. These airplanes will have a novel or unusual design...

  2. 78 FR 41882 - Airworthiness Directives; Dassault Aviation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-12

    ... 2002-23-19, Amendment 39-12963 (67 FR 71452, December 2, 2002), for all Dassault Aviation Model Falcon 2000 airplanes. (That AD superseded AD 99-14-07, Amendment 39-11218 (64 FR 36561, July 7, 1999)). AD... (75 FR 79952, December 21, 2010), for all Dassault Aviation Model FALCON 2000 airplanes. (l)...

  3. 77 FR 31762 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-05-30

    ... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... directive (AD) for all The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes....

  4. 76 FR 59590 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-09-27

    ... 28, 2005 (70 FR 12119, March 11, 2005). Applicability (c) This AD applies to The Boeing Company Model... Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice... FR 10917, March 9, 2004), for certain Model 767-200 and -300 series airplanes. That AD...

  5. Ground effects and control effectiveness tests of a .095 scale powered model of a modified T-39 lift/cruise fan V/STOL research airplane

    NASA Technical Reports Server (NTRS)

    Dawson, C. R.; Omar, E.

    1977-01-01

    Wind tunnel test data are analysed to determine ground effects and the effectiveness of the aerodynamic control surfaces to provide a technology base for a Navy type A V/STOL airplane. Three 14CM (5.5 inch) turbopowered simulators were used to power the model which was tested primarily in the following configurations: (1) VTOL with flaps deployed, gear down, and engines tilted to 80 deg, 90 deg, and 95 deg, (2) STOL with flap and gear down and engines tilted to 50 deg; and (3) Loiter with flaps and gear up and L/C nacelles off. Data acquired during the tests are included as an appendix.

  6. High-attitude low-speed static aerodynamic characteristics of an F-4D fighter airplane model with leading edge slats

    NASA Technical Reports Server (NTRS)

    Monfort, J. C.; Whitcomb, W. M.

    1975-01-01

    An investigation was conducted to determine the effects of two-position leading edge slats on the low speed aerodynamic characteristics of a swept wing twin-jet supersonic fighter airplane model at high angle of attack and various Reynolds numbers. The investigation was performed at a Mach number of 0.20 over a range of angle of attack from 19 deg to 90 deg and angles of slideslip from -10 deg to 30 deg and Reynolds numbers from 1.97 to 13.12 million per meter.

  7. Effect of Reynolds number and engine nacelles on the stalling characteristics of a model of a twin-engine light airplane

    NASA Technical Reports Server (NTRS)

    Lockwood, V. E.

    1972-01-01

    The investigation was made on a 1/18-scale model of a twin-engine light airplane. Static longitudinal, lateral, and directional characteristics were obtained at 0 deg and plus or minus 5 deg sideslip at a Mach number of about 0.2. The angle of attack varied from about 20 deg at a Reynolds number of 0.39 times one million to 13 deg at a Reynolds number of 3.7 times one million, based on the reference chord. The effect of fixed transition, vertical and horizontal tails, and nacelle fillets was studied.

  8. Dynamic stability characteristics in pitch, yaw, and roll of a supercritical-wing research airplane model. [langley 8-foot transonic tunnel tests

    NASA Technical Reports Server (NTRS)

    Boyden, R. P.

    1974-01-01

    The aerodynamic damping in pitch, yaw, and roll and the oscillatory stability in pitch and yaw of a supercritical-wing research airplane model were determined for Mach numbers of 0.25 to 1.20 by using the small-amplitude forced-oscillation technique. The angle-of-attack range was from -2 deg to 20 deg. The effects of the underwing leading-edge vortex generators and the contributions of the wing, vertical tail, and horizontal tail to the appropriate damping and stability were measured.

  9. The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel

    NASA Technical Reports Server (NTRS)

    Seacord, Charles L; Campbell, John P.

    1943-01-01

    The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing movements of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the model were correlated with calculated stability and control characteristics and, in general, good agreement was obtained. The tests showed the following effects of increased rolling and yawing moments of inertia: no appreciable change in spiral stability; reductions in oscillatory stability that were serious at high values of dihedral; a reduction in the sensitivity of the model to gust disturbances; and a reduction in rolling acceleration provided by the ailerons, which caused a marked increase in time to reach a given angle of bank. The general flight behavior of the model became worse with increasing moments of inertia but, with combinations of small effective dihedral and large vertical-tail area, satisfactory flight characteristics were obtained at all moment-of-inertia conditions.

  10. 76 FR 34 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-03

    ... March 6, 1991, we issued AD 91-06-18, amendment 39-6940 (56 FR 10796), for all Airbus Model A310-200... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Model A310... proposed AD by February 17, 2011. ADDRESSES: You may send comments by any of the following methods:...

  11. 76 FR 62653 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-11

    ...-15330 (73 FR 2795, January 16, 2008). Applicability (c) This AD applies to Airbus Model A310-203, -204... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Model A310... 25, 2011. ADDRESSES: You may send comments by any of the following methods: Federal...

  12. 76 FR 13075 - Airworthiness Directives; Airbus Model A330-243F Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-10

    ...-231-AD; Amendment 39-16628; AD 2011-06-04] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330.... ADDRESSES: You may send comments by any of the following methods: Federal eRulemaking Portal: Go to http... AD * * * is issued to extend the applicability to the newly certified model A330-243F. This AD...

  13. High Altitude Long Endurance UAV Analysis Model Development and Application Study Comparing Solar Powered Airplane and Airship Station-Keeping Capabilities

    NASA Technical Reports Server (NTRS)

    Ozoroski, Thomas A.; Nickol, Craig L.; Guynn, Mark D.

    2015-01-01

    There have been ongoing efforts in the Aeronautics Systems Analysis Branch at NASA Langley Research Center to develop a suite of integrated physics-based computational utilities suitable for modeling and analyzing extended-duration missions carried out using solar powered aircraft. From these efforts, SolFlyte has emerged as a state-of-the-art vehicle analysis and mission simulation tool capable of modeling both heavier-than-air (HTA) and lighter-than-air (LTA) vehicle concepts. This study compares solar powered airplane and airship station-keeping capability during a variety of high altitude missions, using SolFlyte as the primary analysis component. Three Unmanned Aerial Vehicle (UAV) concepts were designed for this study: an airplane (Operating Empty Weight (OEW) = 3285 kilograms, span = 127 meters, array area = 450 square meters), a small airship (OEW = 3790 kilograms, length = 115 meters, array area = 570 square meters), and a large airship (OEW = 6250 kilograms, length = 135 meters, array area = 1080 square meters). All the vehicles were sized for payload weight and power requirements of 454 kilograms and 5 kilowatts, respectively. Seven mission sites distributed throughout the United States were selected to provide a basis for assessing the vehicle energy budgets and site-persistent operational availability. Seasonal, 30-day duration missions were simulated at each of the sites during March, June, September, and December; one-year duration missions were simulated at three of the sites. Atmospheric conditions during the simulated missions were correlated to National Climatic Data Center (NCDC) historical data measurements at each mission site, at four flight levels. Unique features of the SolFlyte model are described, including methods for calculating recoverable and energy-optimal flight trajectories and the effects of shadows on solar energy collection. Results of this study indicate that: 1) the airplane concept attained longer periods of on

  14. Pilot Transition Courses for Complex Single-Engine and Light Twin-Engine Airplanes.

    ERIC Educational Resources Information Center

    Federal Aviation Administration (DOT), Washington, DC.

    This publication is intended for use by certificated airplane pilots and provides transitional knowledge and skills for more complex single-engine or light twin-engine airplanes. The training should be conducted by a competent flight instructor certified in the class of airplane and familiar with the make and model. A syllabus outline of ground…

  15. 75 FR 50853 - Special Conditions: Cirrus Design Corporation Model SF50 Airplane; Function and Reliability Testing

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-18

    ..., 2010, 75 FR 29962. No comments were received, and the special conditions are adopted as proposed... products, the SF50 includes a ballistically deployed airframe parachute. The model SF50 has a...

  16. 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.

  17. 75 FR 39798 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400, -401, and -402 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-13

    ... Model 401 PSM 1-84-1A. 13 3 June 9, 2008 Model 402 PSM 1-84-1A. (3) On July 10, 2007 (72 FR 30968, June... incorporation by reference of certain publications listed in this AD as of September 2, 2008 (73 FR 47818... other publications listed in this AD as of July 10, 2007 (72 FR 30968, June 5, 2007). ADDRESSES: You...

  18. Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the Grumman XF9F-2 Airplane with Wing-Tip Tanks Installed

    NASA Technical Reports Server (NTRS)

    Berman, Theodore; Wilson, Jack H.

    1948-01-01

    An investigation of the spin and recovery characteristics of a 1/24-scale model of the Grumman XF9F-2 airplane with wing-tip tanks installed has been conducted-in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect spin and recovery characteristics of the model for a range of possible loadings of the tip tanks were determined. Spin and recovery characteristics without tanks were determined in a previous investigation. The model results indicated that the airplane spins will generally be oscillatory and that recoveries will be satisfactory for all loadings by normal recovery technique (full rudder reversal followed approximately one-half turn later by moving the elevator down). The rudder force necessary for recovery should be within the physical capability of the pilot but the elevator force may be excessive so that some type of balance or booster might be necessary, or it might be necessary to jettison the wing-tip tanks.

  19. Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XP-85 Airplane While Attached to the Trapeze

    NASA Technical Reports Server (NTRS)

    Johnson, Joseph L.

    1947-01-01

    At the request of the Air Materiel Command, Army Air Forces, an investigation of the low-speed, power-off, stability and control characteristics of the McDonnell XP-85 airplane has been conducted in the Langley free-flight tunnel. The results of the portion of the investigation consisting of tests of a 1/10-scale model to study the stability of the XP-85 when attached to the trapeze and during retraction into the B-36 bomb bay are presented herein. In the power-off condition the stability was satisfactory with all oscillations well damped and the nose-restraining collar could be placed in position without difficulty. In a simulated power-on condition the model had a constant-amplitude rolling and sidewise motion and when the collar was layered, a violent motion resulted if the collar struck the model but failed to hold it in the proper manner. Folding of the wings and retraction into the bomb bay offered no problem once the airplane was properly held by the collar. It is recommended that the power be cut immediately after hooking on and that a restricting mechanism be incorporated in the center of the trapeze to eliminate the sidewise motion. It also appears desirable to have the retracting procedure controlled by the XP-85 pilot or an observer in the mother ship to insure that the parasite is in proper position after hooking up before bringing the collar down.

  20. The Aerodynamic Forces and Moments on a Spinning Model of the F4B-2 Airplane as Measured by the Spinning Balance

    NASA Technical Reports Server (NTRS)

    Bamber, M J; Zimmerman, C H

    1935-01-01

    The aerodynamic forces and moments on a 1/12-scale model of the F4B-2 airplane were measured with the spinning balance in nine spinning attitudes with three sets of tail surfaces, namely, F4B-2 surfaces; F4B-4 fin and rudder with rectangular stabilizer; and with all tail surfaces removed. In one of these attitudes measurements were made to determine the effect upon the forces and moments of independent and of simultaneous displacement of the rudder and elevator for two of the sets of tail surfaces. Additional measurements were made for a comparison of model and full-scale data for six attitudes that were determined from flight tests with various control settings. The characteristics were found to vary in the usual manner with angle of attack and sideslip. The F4B-2 surfaces were quite ineffective as a source of yawing moments. The F4B-4 fin and F4B-2 stabilizer gave a greater damping yawing moment when controls were against the spin than did the F4B-2 surfaces but otherwise there was little difference. Substitution of a rectangular stabilizer for the F4B-2 stabilizer made no appreciable difference in the coefficient. Further comparisons with other airplane types are necessary before final conclusions can be drawn as to the relations between model and full-scale spin measurements.

  1. Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the McDonnell XP-88 Airplane with a Conventional Tail

    NASA Technical Reports Server (NTRS)

    Berman, Theodore

    1947-01-01

    An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 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 normal loading were determined. Tests of the model in the long-range loading also were made. The investigation included tail-modification, spin-recovery parachute, pilot-escape, and rudder-pedal-force tests. Recoveries were generally satisfactory for spins in the normal loading provided the ailerons were not held against the spin. Satisfactory recoveries were obtained regardless of the aileron setting when the leading-edge flaps were deflected and normal recovery technique was used or when the horizontal tail was raised 70 inches, full scale. Recoveries were rapid from all inverted spins obtained. In the long-range loading with tanks on, it may be necessary to jettison the tanks in order to obtain recovery. A 12.0-foot spin-recovery parachute at the tail or a 4.0-foot parachute opened on the outer wing tip (drag coefficient of 0.66) was found to be effective for recoveries from demonstration spins. Test results showed that in an emergency the pilot should attempt to escape from the outboard side of the spinning airplane. The rudder-pedal forces in a spin were indicated to be within the capabilities of the pilot.

  2. Free-Spinning-Tunnel Tests of a 0.057-Scale Model of the Chance Vought XF7U-1 Airplane

    NASA Technical Reports Server (NTRS)

    Daughtridge, Lee T., Jr.

    1948-01-01

    An investigation of the spin and recovery characteristics of a 0.057-scale model of the Chance Vought XF7U-1 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 were determined, as were also the effects of extending the wing slats, of center-of-gravity movement, and-of variation in the mass distribution. The investigation also included wing-tip spin-recovery-parachute tests, pilot-escape tests, and rudder-control-force tests. The investigation indicated that the spin and recovery characteristics of the airplane will be satisfactory for all conditions. It was found that a single 4.24-foot (full-scale) parachute when opened alone from the outboard wing tip or two 8.77-foot (full-scale) parachutes when opened simultaneously, one from each wing tip, would effect satisfactory emergency recoveries (the drag coefficients of the parachutes, based on the surface area of the parachute, were 0.83 and 0.70 for the 4.24- and 8.77-foot parachutes, respectively). The towline length in both cases was 25 feet (full scale). Tests results showed that, if the pilot should have to leave the airplane during a spin, he should jump from the outboard side (left side in a right spin) of the cockpit. The rudder-control force necessary for recovery from a spin was found to be rather high but appeared to be within the upper limits of a pilot's capabilities.

  3. Estimation of the Spin and Recovery Characteristics of the North American XSN2J-1 Airplane

    NASA Technical Reports Server (NTRS)

    Snyder, Thomas L.

    1947-01-01

    The probable spin and recovery characteristics of the XSN2J-1 air-plane have been estimated on the basis of the results of brief test a performed on a model of an airplane of somewhat similar design. The spin-recovery tail-parachute requirements for the airplane were also determined end, in addition, an analysis was made to determine the best method of emergency pilot escape during a spin. The results of the investigation indicate that the recovery characteristics of the airplane will be satisfactory for all probable loading conditions of the airplane. A 6-foot-diameter tall parachute attached to a 30-foot tow-line will be satisfactory as a spin-recovery device for emergency recovery from demonstration spins. If the occupants of the airplane decide to abandon the airplane in a spin, they should leave the airplane from the outboard side of the cockpit and as far rearward as possible.

  4. Investigation of Spinning and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultee XFY-1 Airplane in the Free-Spinning Tunnel, TED No. NACA DE 370

    NASA Technical Reports Server (NTRS)

    Lee, Henry A.

    1952-01-01

    An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/20-scale model of the Consolidated Vultee XFY-1 airplane with a windmilling propeller simulated to determine the effects of control setting and movements upon the erect spin and recovery characteristics for a range of airplane-loading conditions. The effects on the model's spin-recovery characteristics of removing the lower vertical tail, removing the gun pods, and fixing the rudders at neutral were also investigated briefly. The investigation included determination of the size parachute required for emergency recovery from demonstration spins. The tumbling tendencies of the model were also investigated. Brief static force tests were made to determine the aerodynamic characteristics in pitch at high angles of attack. The investigation indicated that the spin and recovery characteristics of the airplane with propeller windmilling will be satisfactory for all loading conditions if recovery is attempted by full rudder reversal accompanied by simultaneous movement of the stick laterally to full with the spin (stick right in a right spin) and longitudinally to neutral. Inverted spins should be satisfactorily terminated by fully reversing the rudder followed immediately by moving the stick laterally towards the forward rudder pedal and longitudinally to neutral. Removal of the gun pods or fixing the rudders at neutral will not adversely affect the airplane's spin-recovery characteristics, but removal of the lower vertical tail will result in unsatisfactory spin-recovery characteristics. The model-test results showed that a 13.3-foot wing-tip conventional parachute (drag coefficient approximately 0.7) should be effective as an emergency spin-recovery device during demonstration spins of the airplane. It was indicated that the airplane should not tumble and that no unusual longitudinal-trim characteristics should be obtained for the center-of-gravity positions investigated.

  5. Subsonic Flight Tests of a 1/7-Scale Radio-Controlled Model of the North American X-15 Airplane with Particular Reference to High Angel-of-Attack Conditions

    NASA Technical Reports Server (NTRS)

    Hewes, Donald E.; Hassell, James L., Jr.

    1960-01-01

    An investigation of the subsonic stability and control characteristics of an unpowered 1/7-scale model based on the North American X-15 airplane was conducted by using a radio-controlled model launched from a helicopter and flown in free-gliding flight. At angles of attack below about 20 deg. where the model motions represent those of the X-15 airplane, the model was found to be both longitudinally and laterally stable, and the all-movable tail surfaces were found to be very effective. The model could also be flown at much higher angles of attack where the model motions did not necessarily represent those of the airplane because of slight geometrical differences and Reynolds number effects, but these test results are useful in evaluating the effectiveness at these angles of the type of lateral control system used in the X-15 airplane. In some cases, the model was flown to angles of attack as high as 60 or 70 deg. without encountering divergent or uncontrollable conditions. For some flights in which the model was subjected to rapid maneuvers, spinning motions were generated by application of corrective controls to oppose the direction of rotation. Rapid recoveries from this type of motion were achieved by applying roll control in the direction of rotation.

  6. Gordon Bennett Airplane Cup

    NASA Technical Reports Server (NTRS)

    Margoulis, W

    1921-01-01

    The characteristics of the airplanes built for the Gordon Bennet Airplane Cup race that took place on September 28, 1920 are described. The airplanes are discussed from a aerodynamical point of view, with a number of new details concerning the French machines. Also discussed is the regulation of future races. The author argues that there should be no limitations on the power of the aircraft engines. He reasons that in the present state of things, liberty with regard to engine power does not lead to a search for the most powerful engine, but for one which is reliable and light, thus leading to progress.

  7. 75 FR 6852 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-12

    ... 2009-NM-002-AD; Amendment 39-16196; AD 2010-04-03] RIN 2120-AA64 Airworthiness Directives; Airbus Model... products. That NPRM was published in the Federal Register on August 25, 2009 (74 FR 42804). That NPRM... air commerce by prescribing regulations for practices, methods, and procedures the Administrator...

  8. 76 FR 39035 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-05

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Model A310.... ADDRESSES: You may send comments by any of the following methods: Federal eRulemaking Portal: Go to http... Requirements'' (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport...

  9. 76 FR 53301 - Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-26

    ...-16787; AD 2011-18-05] RIN 2120-AA64 Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000... specified products. That NPRM was published in the Federal Register on June 1, 2011 (76 FR 31508). That NPRM... air commerce by prescribing regulations for practices, methods, and procedures the Administrator...

  10. 76 FR 20496 - Airworthiness Directives; Airbus Model A340-541 and -642 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-13

    ...-105-AD; Amendment 39-16653; AD 2011-08-03] RIN 2120-AA64 Airworthiness Directives; Airbus Model A340..., 2011. ADDRESSES: You may send comments by any of the following methods: Federal eRulemaking Portal: Go... air commerce by prescribing regulations for practices, methods, and procedures the Administrator...

  11. 76 FR 421 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-05

    ...-261-AD; Amendment 39-16559; AD 2011-01-06] RIN 2120-AA64 Airworthiness Directives; Airbus Model A310... Register on September 23, 2010 (75 FR 57880), and proposed to supersede AD 2007-02-22, Amendment 39- 14909 (72 FR 3708, January 26, 2007). That NPRM proposed to correct an unsafe condition for the...

  12. 75 FR 66659 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-29

    ...-195-AD; Amendment 39-16482; AD 2010-22-03] RIN 2120-AA64 Airworthiness Directives; Airbus Model A310... products. That NPRM was published in the Federal Register on July 13, 2010 (75 FR 39863), and proposed to supersede AD 2006-09-05, Amendment 39-14575 (71 FR 25921, May 3, 2006). That NPRM proposed to correct...

  13. 76 FR 50 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-03

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Model A310.... ADDRESSES: You may send comments by any of the following methods: Federal eRulemaking Portal: Go to http... proposes to supersede AD 98-26-01, amendment 39-10942 (63 FR 69179, December 16, 1998), to continue...

  14. 76 FR 65938 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-25

    ...-257-AD; Amendment 39-16846; AD 2011-22-04] RIN 2120-AA64 Airworthiness Directives; Airbus Model A310... (76 FR 39035). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI... developing this AD. We received no comments on the NPRM (76 FR 39035, July 5, 2011) or on the...

  15. 76 FR 27227 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-11

    ...-090-AD; Amendment 39-16687; AD 2011-10-06] RIN 2120-AA64 Airworthiness Directives; Airbus Model A310... products. That NPRM was published in the Federal Register on January 3, 2011 (76 FR 50). That NPRM proposed... regulations for practices, methods, and procedures the Administrator finds necessary for safety in...

  16. 76 FR 41657 - Airworthiness Directives; Airbus Model A330-342 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-15

    ...-249-AD; Amendment 39-16745; AD 2011-14-10] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330... may send comments by any of the following methods: Federal eRulemaking Portal: Go to http://www... in this AD. The corrective action is repairing any cracks in accordance with a method approved by...

  17. 75 FR 57880 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-23

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Model A310... of the following methods: Federal eRulemaking Portal: Go to http://www.regulations.gov . Follow the..., we issued AD 2007-02-22, Amendment 39-14909 (72 FR 3708, January 26, 2007). That AD required...

  18. 75 FR 75870 - Airworthiness Directives; Airbus Model A300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-07

    ...-076-AD; Amendment 39-16536; AD 2010-25-03] RIN 2120-AA64 Airworthiness Directives; Airbus Model A300... to the specified products. That NPRM was published in the Federal Register on August 27, 2010 (75 FR... air commerce by prescribing regulations for practices, methods, and procedures the Administrator...

  19. 76 FR 53303 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-26

    ...-210-AD; Amendment 39-16772; AD 2011-17-08] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330... reference of a certain other publication listed in this AD as of June 7, 2006 (71 FR 25919, May 3, 2006... (76 FR 15867), and proposed to supersede AD 2006-09-07, Amendment 39-14577 (71 FR 25919, May 3,...

  20. 76 FR 15867 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-22

    ...-09-07, Amendment 39-14577 (71 FR 25919, May 3, 2006). That AD requires actions intended to address an... 39-16605 (76 FR 8612, February 15, 2011), for Airbus Model A340-200, -300, -500, and -600 series... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR...

  1. 75 FR 39787 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-13

    ... published in the Federal Register on March 17, 2010 (75 FR 12710). That NPRM proposed to correct an unsafe... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3...-16356; AD 2010-14-11] RIN 2120-AA64 Airworthiness Directives; Bombardier, Inc. Model DHC-8-400...

  2. 78 FR 76772 - Special Conditions: Airbus Model A350-900 Airplanes; Permanently Installed Rechargeable Lithium...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-19

    ... the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo... the Boeing Model 787 (72 FR 57842; October 11, 2007). Applicability As discussed above, these special...; Permanently Installed Rechargeable Lithium-Ion Batteries and Battery Systems AGENCY: Federal...

  3. 75 FR 32251 - Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-08

    ... products. That NPRM was published in the Federal Register on March 15, 2010 (75 FR 12150). That NPRM... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant...; AD 2010-12-04] RIN 2120-AA64 Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7...

  4. 76 FR 10528 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Systems Security Isolation or...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-25

    ... unusual design features associated with connectivity of the passenger domain computer systems to the... and network configuration may be used for, or interfaced with, a diverse set of functions, including... sources. Discussion of Proposed Special Conditions The proposed Model GVI integrated network...

  5. 75 FR 45075 - Airworthiness Directives; Eclipse Aerospace, Inc. Model EA500 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-02

    ... Register on July 9, 2010 (75 FR 39472), and applies to certain Eclipse Aerospace, Inc. (Eclipse) Model...-5960. SUPPLEMENTARY INFORMATION: Discussion On July 1, 2010, the FAA issued an NPRM (75 FR 39472, July... created. Correction of Publication Accordingly, the publication of July 9, 2010 (75 FR 39472), of...

  6. 78 FR 58973 - Airworthiness Directives; Dassault Aviation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-25

    ... Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska... 39-16544 (75 FR 79952, December 21, 2010), for Dassault Aviation Model FALCON 2000EX Airplanes. (i...-05, Amendment 39-16544 (75 FR 79952, December 21, 2010), for the airplanes identified in paragraph...

  7. 77 FR 49396 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-16

    ...-20, Amendment 39-15583 (73 FR 37786, July 2, 2008), for certain Model 757 airplanes equipped with... of AD 2008-13-20, Amendment 39-15583 (73 FR 37786, July 2, 2008). For certain airplanes, this... Since we issued AD 2008-13-20, Amendment 39-15583 (73 FR 37786, July 2, 2008), we have received...

  8. 78 FR 78701 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-27

    ...We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires, depending on airplane configuration, replacing fuel pump power control relays with new relays having a ground fault interrupter (GFI) feature, installing ground studs and a......

  9. 77 FR 65613 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-30

    ...We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200LR and -300ER series airplanes. This AD requires reviewing the airplane's maintenance records for each rudder power control unit (PCU) to identify the condition of its related reaction link assembly, and replacing the rudder PCU and its related reaction link assembly if necessary. This AD was......

  10. 77 FR 47277 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-08

    ...We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8 series airplanes. This AD was prompted by reports that various pushrods had been manufactured with tubes having the incorrect heat treatment. This AD requires replacing the affected pushrod assembly. We are issuing this AD to prevent loss of rudder control, reduced directional control of the airplane on......

  11. 78 FR 27010 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-09

    ...We are superseding two existing airworthiness directives (AD) that apply to certain The Boeing Company Model 737-100, -200, -200C, - 300, -400, and -500 series airplanes. Those ADs, for certain airplanes, currently require repetitive inspections of the flap track of the wing outboard flap, and corrective actions if necessary; and eventual rework of the flap track assembly and rear spar......

  12. 78 FR 42727 - Airworthiness Directives; the Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-17

    ... Boeing Company Model 777-200 and -300 series airplanes: We have issued an NPRM (78 FR 27310, May 10, 2013..., Amendment 39-15151 (72 FR 44740, August 9, 2007), requires changes to existing wiring; installation of new... series airplanes: AD 2008-23-15, Amendment 39-15736 (73 FR 70267, November 20, 2008), requires...

  13. 77 FR 66417 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-05

    ... 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Aeronautiche Tecnam srl Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation... directive (AD) for Costruzioni Aeronautiche Tecnam srl Model P2006T airplanes. This proposed AD results...

  14. 78 FR 14722 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-07

    ... 777 airplanes. That NPRM published in the Federal Register on June 6, 2008 (73 FR 32253). That NPRM... revealed on the Model 737-400 airplanes. Actions Since Previous NPRM (73 FR 32253, June 6, 2008) Was Issued Since we issued the previous NPRM (73 FR 32253, June 6, 2008), we have received comments from...

  15. 77 FR 32064 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-05-31

    ... gear beam. ] Actions Since Existing AD Was Issued Since we issued AD 89-15-07, amendment 39-6267 (54 FR... 7, 1989, we issued AD 89-15-07, amendment 39-6267 (54 FR 30009, July 18, 1989), for certain Model... Information Since the issuance of AD 89-15-07, amendment 39-6267 (54 FR 30009, July 18, 1989), Boeing...

  16. 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.

  17. Low-Speed Longitudinal Stability Characteristics of a 1/6-Scale Model of the Republic XF-84H Airplane with the Propeller Operating

    NASA Technical Reports Server (NTRS)

    Sleeman, William C.; Byrnes, Andrew L.

    1953-01-01

    A low-speed investigation was made of a 1/6-scale model of the Republic XF-84H airplane. The model had a single tractor propeller and a 40deg swept wing of aspect ratio 3.45. This investigation was undertaken to provide information on the effects of propeller operation on longitudinal stability characteristics for the XF -84H airplane and to provide an indication of slipstream effects that might be encountered on similar swept-wing configurations. Effects of propeller operation were generally destabilizing for all conditions investigated; however, the over-all stability characteristics with power on were greatly dependent on the power-off characteristics. With flaps and slats retracted, longitudinal instability was present at moderate angles of attack both with the propeller off and with power on. The longitudinal stability with flaps and slats deflected, which was satisfactory without power, was decreased by propeller operation, but no marked pitch-up tendency was indicated. Significant improvement in the power-on stability with flaps retracted was achieved by use of either a wing fence at 75 percent semispan, a leading-edge chord-extension from 65 to 94 percent semispan, or a raised horizontal tail located 65 percent semispan above the thrust line.

  18. Supersonic airplane study and design

    NASA Technical Reports Server (NTRS)

    Cheung, Samson

    1993-01-01

    A supersonic airplane creates shocks which coalesce and form a classical N-wave on the ground, forming a double bang noise termed sonic boom. A recent supersonic commercial transport (the Concorde) has a loud sonic boom (over 100 PLdB) and low aerodynamic performance (cruise lift-drag ratio 7). To enhance the U.S. market share in supersonic transport, an airframer's market risk for a low-boom airplane has to be reduced. Computational fluid dynamics (CFD) is used to design airplanes to meet the dual constraints of low sonic boom and high aerodynamic performance. During the past year, a research effort was focused on three main topics. The first was to use the existing design tools, developed in past years, to design one of the low-boom wind-tunnel configurations (Ames Model 3) for testing at Ames Research Center in April 1993. The second was to use a Navier-Stokes code (Overflow) to support the Oblique-All-Wing (OAW) study at Ames. The third was to study an optimization technique applied on a Haack-Adams body to reduce aerodynamic drag.

  19. Wind tunnel and ground static tests of a .094 scale powered model of a modified T-39 lift/cruise fan V/STOL research airplane

    NASA Technical Reports Server (NTRS)

    Hunt, D.; Clinglan, J.; Salemann, V.; Omar, E.

    1977-01-01

    Ground static and wind tunnel test of a scale model modified T-39 airplane are reported. The configuration in the nose and replacement of the existing nacelles with tilting lift/cruise fans. The model was powered with three 14 cm diameter tip driven turbopowered simulators. Forces and moments were measured by an internal strain guage balance. Engine simulator thrust and mass flow were measured by calibrated pressure and temperature instrumentation mounted downstream of the fans. The low speed handling qualities and general aerodynamic characteristics of the modified T-39 were defined. Test variables include thrust level and thrust balance, forward speed, model pitch and sideslip angle at forward speeds, model pitch, roll, and ground height during static tests, lift/cruise fan tilt angle, flap and aileron deflection angle, and horizonal stabilizer angle. The effects of removing the landing gear, the lift/cruise fans, and the tail surfaces were also investigated.

  20. General airplane performance

    NASA Technical Reports Server (NTRS)

    Rockfeller, W C

    1939-01-01

    Equations have been developed for the analysis of the performance of the ideal airplane, leading to an approximate physical interpretation of the performance problem. The basic sea-level airplane parameters have been generalized to altitude parameters and a new parameter has been introduced and physically interpreted. The performance analysis for actual airplanes has been obtained in terms of the equivalent ideal airplane in order that the charts developed for use in practical calculations will for the most part apply to any type of engine-propeller combination and system of control, the only additional material required consisting of the actual engine and propeller curves for propulsion unit. Finally, a more exact method for the calculation of the climb characteristics for the constant-speed controllable propeller is presented in the appendix.

  1. English airplane construction

    NASA Technical Reports Server (NTRS)

    Schwencke, D

    1930-01-01

    English airplane construction is presented with a particular emphasis on metal construction techniques. Steel rib and fuselage construction are discussed as well as the use of duralumin in construction.

  2. The Bristol "Badminton" Airplane

    NASA Technical Reports Server (NTRS)

    1926-01-01

    The Bristol Badminton, Type 99 airplane has a radial aircooled engine (a Bristol Jupiter 9 cylinder 450 HP.) and three fuel tanks. It is a single seat biplane weighing 1,840 lbs. empty and 2,460 lbs. loaded.

  3. Airplane Stress Analysis

    NASA Technical Reports Server (NTRS)

    Zahm, A F; Crook, L H

    1918-01-01

    Report presents stress analysis of individual components of an airplane. Normal and abnormal loads, sudden loads, simple stresses, indirect simple stresses, resultant unit stress, repetitive and equivalent stress, maximum steady load and stress are considered.

  4. Quantifying and scaling airplane performance in turbulence

    NASA Astrophysics Data System (ADS)

    Richardson, Johnhenri R.

    This dissertation studies the effects of turbulent wind on airplane airspeed and normal load factor, determining how these effects scale with airplane size and developing envelopes to account for them. The results have applications in design and control of aircraft, especially small scale aircraft, for robustness with respect to turbulence. Using linearized airplane dynamics and the Dryden gust model, this dissertation presents analytical and numerical scaling laws for airplane performance in gusts, safety margins that guarantee, with specified probability, that steady flight can be maintained when stochastic wind gusts act upon an airplane, and envelopes to visualize these safety margins. Presented here for the first time are scaling laws for the phugoid natural frequency, phugoid damping ratio, airspeed variance in turbulence, and flight path angle variance in turbulence. The results show that small aircraft are more susceptible to high frequency gusts, that the phugoid damping ratio does not depend directly on airplane size, that the airspeed and flight path angle variances can be parameterized by the ratio of the phugoid natural frequency to a characteristic turbulence frequency, and that the coefficient of variation of the airspeed decreases with increasing airplane size. Accompanying numerical examples validate the results using eleven different airplanes models, focusing on NASA's hypothetical Boeing 757 analog the Generic Transport Model and its operational 5.5% scale model, the NASA T2. Also presented here for the first time are stationary flight, where the flight state is a stationary random process, and the stationary flight envelope, an adjusted steady flight envelope to visualize safety margins for stationary flight. The dissertation shows that driving the linearized airplane equations of motion with stationary, stochastic gusts results in stationary flight. It also shows how feedback control can enlarge the stationary flight envelope by alleviating

  5. Hovering and Transition Flight Tests of a 1/5-Scale Model of a Jet-Powered Vertical-Attitude VTOL Research Airplane

    NASA Technical Reports Server (NTRS)

    Smith, Charles C., Jr.

    1961-01-01

    An experimental investigation has been made to determine the dynamic stability and control characteristics of a 1/5-scale flying model of a jet-powered vertical-attitude VTOL research airplane in hovering and transition flight. The model was powered with either a hydrogen peroxide rocket motor or a compressed-air jet exhausting through an ejector tube to simulate the turbojet engine of the airplane. The gyroscopic effects of the engine were simulated by a flywheel driven by compressed-air jets. In hovering flight the model was controlled by jet-reaction controls which consisted of a swiveling nozzle on the main jet and a movable nozzle on each wing tip; and in forward flight the model was controlled by elevons and a rudder. If the gyroscopic effects of the jet engine were not represented, the model could be flown satisfactorily in hovering flight without any automatic stabilization devices. When the gyroscopic effects of the jet engine were represented, however, the model could not be controlled without the aid of artificial stabilizing devices because of the gyroscopic coupling of the yawing and pitching motions. The use of pitch and yaw dampers made these motions completely stable and the model could then be controlled very easily. In the transition flight tests, which were performed only with the automatic pitch and yaw dampers operating, it was found that the transition was very easy to perform either with or without the engine gyroscopic effects simulated, although the model had a tendency to fly in a rolled and sideslipped attitude at angles of attack between approximately 25 deg and 45 deg because of static directional instability in this range.

  6. Hovering and Transition Flight Tests of a 1/5-Scale Model of a Jet-Powered Vertical-Attitude VTOL Research Airplane

    NASA Technical Reports Server (NTRS)

    Smith, Charles C., Jr.

    1958-01-01

    An experimental investigation has been made to determine the dynamic stability and control characteristics of a 1/5-scale flying model of a jet-powered vertical-attitude VTOL research airplane in hovering and transition flight. The model was powered with either a hydrogen peroxide rocket motor or a compressed-air jet exhausting through an ejector tube to simulate the turbojet engine of the airplane. The gyroscopic effects of the engine were simulated by a flywheel driven by compressed-air jets. In hovering flight the model was controlled by jet-reaction controls which consisted of a swiveling nozzle on the main jet and a movable nozzle on each wing tip; and in forward flight the model was controlled by elevons and a rudder. If the gyroscopic effects of the jet engine were not represented, the model could be flown satisfactorily in hovering flight without any automatic stabilization devices. When the gyroscopic effects of the jet engine were represented, however, the model could not be controlled without the aid of artificial stabilizing devices because of the gyroscopic coupling of the yawing and pitching motions. The use of pitch and yaw dampers made these motions completely stable and the model could then be controlled very easily. In the transition flight tests, which were performed only with the automatic pitch and yaw dampers operating, it was found that the transition was very easy to perform either with or without the engine gyroscopic effects simulated, although the model had a tendency to fly in a rolled and sideslipped attitude at angles of attack between approximately 25 and 45 deg because of static directional instability in this range.

  7. Stall-proof Airplanes

    NASA Technical Reports Server (NTRS)

    Lachmann, G

    1927-01-01

    My lecture has to do with the following questions. Is the danger of stalling necessarily inherent in the airplane in its present form and structure, or can it be diminished or eliminated by suitable means? Do we possess such means or devices and how must they operate? In this connection I will devote special attention to the exhibition of stall-proof airplanes by Fokker under the auspices of the English Air Ministry, which took place in Croyden last April.

  8. Experimental Verification of the Rudder-Free Stability Theory for an Airplane Model Equipped with Rudders Having Negative Floating Tendency and Negligible Friction

    NASA Technical Reports Server (NTRS)

    McKinney, Marion O.; Maggin, Bernard

    1944-01-01

    An investigation has been made in the Langley free-flight tunnel to obtain an experimental verification of the theoretical rudder-free stability characteristics of an airplane model equipped with conventional rudders having negative floating tendencies and negligible friction. The model used in the tests was equipped with a conventional single vertical tail having rudder area 40 percent of the vertical tail area. The model was tested both in free flight and mounted on a strut that allowed freedom only in yaw. Tests were made with three different amounts of rudder aerodynamic balance and with various values of mass, moment of inertia, and center-of-gravity location of the rudder. Most of the stability derivatives required for the theoretical calculations were determined from forced and free-oscillation tests of the particular model tested. The theoretical analysis showed that the rudder-free motions of an airplane consist largely of two oscillatory modes - a long-period oscillation somewhat similar to the normal rudder-fixed oscillation and a short-period oscillation introduced only when the rudder is set free. It was found possible in the tests to create lateral instability of the rudder-free short-period mode by large values of rudder mass parameters even though the rudder-fixed condition was highly stable. The results of the tests and calculation indicated that for most present-day airplanes having rudders of negative floating tendency, the rudder-free stability characteristics may be examined by simply considering the dynamic lateral stability using the value of the directional-stability parameter Cn(sub p) for the rudder-free condition in the conventional controls-fixed lateral-stability equations. For very large airplanes having relatively high values of the rudder mass parameters with respect to the rudder aerodynamic parameters, however, analysis of the rudder-free stability should be made with the complete equations of motion. Good agreement between

  9. Hydrodynamic Investigation of the the Take-Off Characteristics of a 1/10-Scale Dynamic Model of the Convair XF2Y-1 Airplane

    NASA Technical Reports Server (NTRS)

    McBridge, Ellis E.; Fisher, Lloyd J.

    1954-01-01

    An investigation was made of the take-off characteristics of a 1/10-scale dynamic model of the Convair XF2Y-1 airplane. This airplane is a water-based, jet-propelled, delta-wing fighter incorporating a hydro-ski landing gear. Tests were made with the original configuration, with the beaching wheels removed, and with the wheels installed and fairings added in front of the wheels. Each configuration was tested at weight and balance conditions simulating 17,000 pounds gross weight with the moment due t o 7,600 pounds of thrust, 17,300 pounds gross weight with a 9,500-pound thrust condition, and 23,000 pounds gross weight with a 9,300-pound thrust condition. Constant-speed runs were made at various elevon settings and vertical ski-strut positions; and trim, rise, and resistance were measured. Accelerated runs were made with controlled elevons and scale shock struts which could be extended as desired, and the longitudinal stability and spray characteristics were observed and photographed.

  10. Wind-Tunnel Investigation of Effects of Unsymmetrical Horizontal-Tail Arrangements on Power-on Static Longitudinal Stability of a Single-Engine Airplane Model

    NASA Technical Reports Server (NTRS)

    Purser, Paul E.; Spear, Margaret F.

    1947-01-01

    A wind-tunnel investigation has been made to determine the effects of unsymmetrical horizontal-tail arrangements on the power-on static longitudinal stability of a single-engine single-rotation airplane model. Although the tests and analyses showed that extreme asymmetry in the horizontal tail indicated a reduction in power effects on longitudinal stability for single-engine single-rotation airplanes, the particular "practical" arrangement tested did not show marked improvement. Differences in average downwash between the normal tail arrangement and various other tail arrangements estimated from computed values of propeller-slipstream rotation agreed with values estimated from pitching-moment test data for the flaps-up condition (low thrust and torque) and disagreed for the flaps-down condition (high thrust and torque). This disagreement indicated the necessity for continued research to determine the characteristics of the slip-stream behind various propeller-fuselage-wing combinations. Out-of-trim lateral forces and moments of the unsymmetrical tail arrangements that were best from consideration of longitudinal stability were no greater than those of the normal tail arrangement.

  11. Preliminary Tests of a Buffet Stall-Warning Device on a 1/5-Scale Model of the Republic XP-84 Airplane

    NASA Technical Reports Server (NTRS)

    Tucker, Warren A.; Comisarow, Paul

    1946-01-01

    During the first flight tests of the Republic XP-84 airplane it was discovered that there was a complete lack of stall warning. A short series of development tests of a suitable stall-warning device for the airplane was therefore made on a 1/5-scale model in the Langley 300 MPH 7- by 10-foot tunnel. Two similar stall-warning devices, each designed to produce early root stall which would provide a buffet warning, were tested. It appeared that either device would give a satisfactory buffet warning in the flap-up configuration, at the cost of an increase of 8 or 10 miles per hour in minimum speed. Although neither device seemed to give a true buffet warning in the flaps-down configuration, it appeared that either device would improve the flaps-down stalling characteristics by lessening the severity of the stall and by maintaining better control at the stall. The flaps-down minimum-speed increase caused by the devices was only 1 or 2 miles per hour.

  12. Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane with External Fuel Tanks, TED No. NACA AD 3112

    NASA Technical Reports Server (NTRS)

    Healy, Frederick M.

    1958-01-01

    A supplementary investigation to determine the effect of external fuel tanks on the spin and recovery characteristics of a l/28-scale model of the North American FJ-4 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The model had been extensively tested previously (NACA Research Memorandum SL38A29) and therefore only brief tests were made to evaluate the effect of tank installation. Erect spin tests of the model indicate that flat-type spins-are more prevalent with 200-gallon external fuel tanks than with tanks not installed. The recovery technique determined for spins without tanks, rudder reversal to full against the spin accompanied by simultaneous movement of ailerons to full with the spin, is recommended for spins encountered with external tanks installed. If inverted spins are encountered with external tanks installed, the tanks should be jettisoned and recovery attempted by rudder reversal to full against the spin with ailerons maintained at neutral.

  13. Free-Spinning and Recovery Characteristics of a 1/18-Scale Model of the Ryan X-13 Airplane as Determined from Tests in the Langley 20-Foot Free-Spinning Tunnel

    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 l/18 scale model of the Ryan X-13 airplane to determine its spin and recovery characteristics. The spin and recovery characteristics determined to date are presented in this report.

  14. 77 FR 63716 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-17

    ..., Amendment 39-16097 (74 FR 62219, November 27, 2009). For Model A318-111 and -112 airplanes, and Model A319... this AD as of December 14, 2009 (74 FR 62219, November 27, 2009). The Director of the Federal Register..., 2007 (72 FR 40222, July 24, 2007). ADDRESSES: You may examine the AD docket on the Internet at...

  15. 78 FR 71992 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-02

    ..., Amendment 39-14523 (71 FR 15023, March 27, 2006). For Model A318-111 and -112 airplanes; Model ] A319-111... as of May 1, 2006 (71 FR 15023, March 27, 2006). ADDRESSES: You may examine the AD docket on the... published in the Federal Register on August 20, 2013 (78 FR 51117), and proposed to supersede AD...

  16. 78 FR 51117 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-20

    ...-06-14, Amendment 39-14523 (71 FR 15023, March 27, 2006). For Model A318-111 and -112 airplanes; Model...-06-14, Amendment 39-14523 (71 FR 15023, March 27, 2006), (``AD 2006-06-14''). That AD required... $680. Amendment 39-14523 (71 FR per hour = Between 15023, March 27, 2006)]. $85 and $680....

  17. Concluding Report of Free-Spinning, Tumbling, and Recovery Characteristics of a 1/18-Scale Model of the Ryan X-13 Airplane, Coord. No. AF-199

    NASA Technical Reports Server (NTRS)

    Bowman, James S., Jr.

    1957-01-01

    An investigation has been completed in the Langley 20-foot free-spinning tunnel on a l/18-scale model of the Ryan X-13 airplane to determine its spin, recovery, and tumbling characteristics, and to determine the minimum altitude from which a belly landing could be made in case of power failure in hovering flight. Model spin tests were conducted with and without simulated engine rotation. Tests without simulated engine rotation indicated two types of spins: one, a slightly oscillatory flat spin; and the other, a violently oscillatory spin. Tests with simulated engine rotation indicated that spins to the left were fast rotating and steep and those to the right were slow rotating and flat. The optimum technique for recovery is reversal of the rudder to against the spin and simultaneous movement of the ailerons to full with the spin followed by movement of the elevators to neutral after the spin rotation ceases. Tumbling tests made on the model indicated that although the Ryan X-13 airplane will not tumble in the ordinary sense (end-over-end pitching motion), it may instead tend to enter a wild gyrating'motion. Tests made to simulate power failure in hovering flight by dropping the model indicated that the model entered what appeared to be a right spin. An attempt should be made to stop this motion immediately by moving the rudder to oppose the rotation (left pedal), moving the ailerons to with the spin (stick right), and moving the stick forward after the spin rotation ceases to obtain flying speed for pullout. The minimum altitude required for a belly landing in case of power failure in hovering flight was indicated to be about 4,200 feet.

  18. Exhaust-nozzle characterisitcs for a twin-jet variable-wing-sweep fighter airplane model at Mach numbers to 2.2

    NASA Technical Reports Server (NTRS)

    Reubush, D. E.; Mercer, C. E.

    1974-01-01

    A wind-tunnel investigation has been conducted to determine the exhaust-nozzle aerodynamic and propulsive characteristics for a twin-jet variable-wing-sweep fighter airplane model. The powered model was tested in the Langley 16-foot transonic tunnel and in the Langley 4-foot supersonic pressure tunnel at Mach numbers to 2.2 and at angles of attack from about minus 2 to 6 deg. Compressed air was used to simulate the nozzle exhaust flow at values of jet total-pressure ratio from approximately 1 (jet off) to about 21. Effects of configuration variables such as speed-brake deflection, store installation, and boundary-layer thickness on the the nozzle characteristics were also investigated.

  19. 78 FR 3363 - Airworthiness Directives; the Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-01-16

    ...-13269 (68 FR 51439, August 27, 2003), for Model 747-400 series airplanes equipped with GE Model CF6-80C2...-04, Amendment 39-11833 (65 FR 47252, August 2, 2000), for Model 747-200 and -300 series airplanes..., we issued AD 2000-09-04, Amendment 39-11712 (65 FR 25833, May 4, 2000), for Model 767...

  20. 77 FR 59149 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-26

    ... rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not..., and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called A300-600... B4-601, B4-603, B4-620, B4- 622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F...

  1. Effect of Ground Proximity on Aerodynamic Characteristics of Two Horizontal-Attitude Jet Vertical-Take-Off-and-Landing Airplane Models

    NASA Technical Reports Server (NTRS)

    Newsom, William A., Jr.

    1960-01-01

    An investigation has been made to study the effect of ground proximity on the aerodynamic characteristics of two jet vertical-take-off-and-landing airplane models in which the fuselage remains in a horizontal attitude for the take-off and landing. The first model (called the tilt-wing model) had a tilting wing-engine assembly which was set at 90 deg incidence for the take-off and landing. The second model, called the deflected-jet model) had a cascade of retractable turning vanes to deflect the exhaust of the horizontally mounted jet engines downward for vertical take-off and landing while the entire model remained in a horizontal attitude. With the models at various heights above the ground in the take-off and landing configuration, the lift, drag, and pitching moment were measured and tuft surveys were made to determine the flow field caused by the jet exhaust. The tilt-wing model experienced a loss of lift of less than 3 percent near the ground. The deflected-jet model, however, suffered losses in lift as high as 45 percent near the ground because of a low pressure region under the model caused by the entrainment of air by the jet exhaust as it spread out along the ground. This loss in lift for the deflected-jet configuration could probably be reduced to less than 5 percent by the use of a longer landing gear and a high wing location.

  2. Investigation of axisymmetric and nonaxisymmetric nozzles installed on a 0.10 scale F-18 prototype airplane model. [wind tunnel tests

    NASA Technical Reports Server (NTRS)

    Capone, F. J.; Berrier, B. L.

    1980-01-01

    The Langley 16 foot transonic tunnel was used to investigate the afterbody/nozzle longitudinal aerodynamic characteristics of three different two dimensional nozzles and a base-line axisymmetric nozzle installed on a 0.10 scale model of the F-18 airplane. The effects of thrust vectoring and in-flight thrust reversing were also studied. Horizontal-tail deflections of 0 deg, -2 deg, and -5 deg were tested. Test data were obtained at static conditions and at Mach numbers from 0.60 to 1.20 over an angle-of-attack range from -2 deg to 10 deg. Nozzle pressure ratio was varied from jet off to about 10.

  3. Investigation of the Stability and Control Characteristics of a 1/20-Scale Model of the Consolidated Vultee XB-53 Airplane in the Langley Free-Flight Tunnel

    NASA Technical Reports Server (NTRS)

    Bennett, Charles V.

    1947-01-01

    An investigation of the low-speed, power-off stability and control characteristics of a 1/20-scale model of the Consolidated Vultee XB-53 airplane has been conducted in the Langley free-flight tunnel. In the investigation it was found that with flaps neutral satisfactory flight behavior at low speeds was obtainable with an increase in height of the vertical tail and with the inboard slats opened. In the flap-down slat-open condition the longitudinal stability was satisfactory, but it was impossible to obtain satisfactory lateral-flight characteristics even with the increase in height of the vertical tail because of the negative effective dihedral, low directional stability, and large-adverse yawing moments of the ailerons.

  4. Wind-tunnel investigation of the effect of power and flaps on the static lateral characteristics of a single-engine low-wing airplane model

    NASA Technical Reports Server (NTRS)

    Tamburello, Vito; Weil, Joseph

    1947-01-01

    Tests were made in the Langley 7- by 10-foot tunnel to determine the lateral-stability characteristics with and without power of a model of a typical low-wing single-engine airplane with flaps neutral, with a full-span single slotted flap, and with a full-span double slotted flap. Power decreased the dihedral effect regardless of flap condition, and the double-slotted flap configuration showed the most marked decrease. The usual effect of power in increasing the directional stability was also shown. Deflection of the single slotted flap produced negative dihedral effect, but increased the directional stability. The effects of deflecting the double slotted flap were erratic and marked changes in both effective dihedral and directional stability occurred. The addition of the tail surfaces always contributed directional stability and generally produced positive dihedral effect.

  5. Static aerodynamic characteristics of a 0.035-scale model of a modified NKC-135 airplane at a Mach number of 0.28

    NASA Technical Reports Server (NTRS)

    Hedstrom, E.; Whitcomb, W. M.

    1977-01-01

    A 0.035-scale model fo a modified NKC-135 airplane was tested in 12-foot pressure wind tunnel to determine the effects on the static aerodynamic characteristics of modifications to the basic aircraft. Modifications investigated included: nose, lower fuselage, and upper fuselage radomes; wing pylons and pods; overwing probe; and air conditioning inlets. The investigation was performed at a Mach number of 0.28 over a Reynolds number range from 6.6 to 26.2 million per meter. Angles of attack and sideslip varied from -8 deg to 20 deg and from -18 deg to 8 deg, respectively, for various combinations of flap, aileron, and rudder deflections. A limited analysis of the test results indicates that the addition of the radomes reduces lateral-directional stability and control effectiveness of the basic aircraft.

  6. 77 FR 64029 - Special Conditions: Airbus Model A318, A319, A320, and A321 Series Airplanes; Design Dive Speed

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-18

    ... April 11, 2000 (65 FR 19477-19478), as well as at http: DocketsInfo.dot.gov/. Docket: Background... Series Airplanes; Design Dive Speed AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final... airplanes. These design features include a high-speed protection system. The applicable...

  7. Free-Spinning, Longitudinal-Trim, and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultke MX-813 (Prototype of XP-92) Airplane as Determined in the Langley 20-Foot Free-Spinning Tunnel

    NASA Technical Reports Server (NTRS)

    Stone, Ralph W., Jr.; White, Richard P.

    1948-01-01

    An investigation has been conducted in the Langley 20-foot free-spinning tunnel to evaluate the spin, longitudinal-trim, and tumbling characteristics of a 1/20-scale model of the Consolidated Vultee MX-813 airplane. The effects of control position were determined for the model ballasted to represent the airplane in its design gross weight loading. The model, in general, would not spin but demonstrated a tendency to trim at very high stalled angles of attack. Static tests substantiated the dynamic tests as regards the trim characteristics. Movement of the elevator, however, from up to slightly down was effective in pitching the model from stalled to normal trim attitudes. The model would not tumble.

  8. 77 FR 19071 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-03-30

    ..., dated October 7, 2010 (for Model A340-500 and -600 series airplanes). The actions described in this... Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will... Mandatory Service Bulletin A340-53-5056, excluding Appendices 01 and 02, dated October 7, 2010 (for...

  9. 77 FR 60653 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-04

    ... and AFT lower deck cargo holds, as applicable to aeroplane configuration, in accordance with Airbus SB...-14974 (72 FR 10348, March 8, 2007), and retained in this proposed AD take about 4 work-hours per product...; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in...

  10. Take-Off and Landing Characteristics of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane in Steady Winds, TED No. NACA DE 368

    NASA Technical Reports Server (NTRS)

    Schade, Robert O.; Smith, Charles C., Jr.; Lovell, P. M., Jr.

    1954-01-01

    An experimental investigation has been conducted to determine the stability and control characteristics of a 0.13-scale free-flight model of the Convair XFY-1 airplane during take-offs and landings in steady winds. The tests indicated that take-offs in headwinds up to at least 20 knots (full scale) will be fairly easy to perform although the airplane may be blown downstream as much as 3 spans before a trim condition can be established. The distance that the airplane will be blown down-stream can be reduced by restraining the upwind landing gear until the instant of take-off. The tests also indicated that spot landings in headwinds up to at least 30 knots (full scale) and in crosswinds up to at least 20 knots (full scale) can be accomplished with reasonable accuracy although, during the landing approach, there will probably be an undesirable nosing-up tendency caused by ground effect and by the change in angle of attack resulting from vertical descent. Some form of arresting gear will probably be required to prevent the airplane from rolling downwind or tipping over after contact. This rolling and tipping can be prevented by a snubbing line attached to the tip of the upwind' wing or tail or by an arresting gear consisting of a wire mesh on the ground and hooks on the landing gear to engage the mesh.

  11. Longitudinal Aerodynamic Modeling of the Adaptive Compliant Trailing Edge Flaps on a GIII Airplane and Comparisons to Flight Data

    NASA Technical Reports Server (NTRS)

    Smith, Mark S.; Bui, Trong T.; Garcia, Christian A.; Cumming, Stephen B.

    2016-01-01

    A pair of compliant trailing edge flaps was flown on a modified GIII airplane. Prior to flight test, multiple analysis tools of various levels of complexity were used to predict the aerodynamic effects of the flaps. Vortex lattice, full potential flow, and full Navier-Stokes aerodynamic analysis software programs were used for prediction, in addition to another program that used empirical data. After the flight-test series, lift and pitching moment coefficient increments due to the flaps were estimated from flight data and compared to the results of the predictive tools. The predicted lift increments matched flight data well for all predictive tools for small flap deflections. All tools over-predicted lift increments for large flap deflections. The potential flow and Navier-Stokes programs predicted pitching moment coefficient increments better than the other tools.

  12. Simulation of Dynamics of a Flexible Miniature Airplane

    NASA Technical Reports Server (NTRS)

    Waszak, Martin R.

    2005-01-01

    A short report discusses selected aspects of the development of the University of Florida micro-aerial vehicle (UFMAV) basically, a miniature airplane that has a flexible wing and is representative of a new class of airplanes that would operate autonomously or under remote control and be used for surveillance and/or scientific observation. The flexibility of the wing is to be optimized such that passive deformation of the wing in the presence of aerodynamic disturbances would reduce the overall response of the airplane to disturbances, thereby rendering the airplane more stable as an observation platform. The aspect of the development emphasized in the report is that of computational simulation of dynamics of the UFMAV in flight, for the purpose of generating mathematical models for use in designing control systems for the airplane. The simulations are performed by use of data from a wind-tunnel test of the airplane in combination with commercial software, in which are codified a standard set of equations of motion of an airplane, and a set of mathematical routines to compute trim conditions and extract linear state space models.

  13. 78 FR 57104 - Airworthiness Directives; Diamond Aircraft Industries Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-17

    ... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation... Model DA 40 airplanes, serial numbers 40.006 through 40.009, 40.011 through 40.1071, and 40.1073...

  14. 78 FR 14719 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-07

    ...We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 747SP series airplanes, and certain The Boeing Company Model 747-100B SUD and 747-300 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage skin just above certain lap splice locations is subject to widespread fatigue damage (WFD).......

  15. 77 FR 5195 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-02-02

    ...We are revising an earlier proposed airworthiness directive (AD) for all Model 747-100B SUD, 747-300, 747-400, and 747-400D series airplanes; and Model 747-200B series airplanes having a stretched upper deck. The original NPRM would have superseded an existing AD that currently requires repetitively inspecting for cracking or discrepancies of the fasteners in the tension ties, shear webs, and......

  16. The evolution of airplanes

    NASA Astrophysics Data System (ADS)

    Bejan, A.; Charles, J. D.; Lorente, S.

    2014-07-01

    The prevailing view is that we cannot witness biological evolution because it occurred on a time scale immensely greater than our lifetime. Here, we show that we can witness evolution in our lifetime by watching the evolution of the flying human-and-machine species: the airplane. We document this evolution, and we also predict it based on a physics principle: the constructal law. We show that the airplanes must obey theoretical allometric rules that unite them with the birds and other animals. For example, the larger airplanes are faster, more efficient as vehicles, and have greater range. The engine mass is proportional to the body size: this scaling is analogous to animal design, where the mass of the motive organs (muscle, heart, lung) is proportional to the body size. Large or small, airplanes exhibit a proportionality between wing span and fuselage length, and between fuel load and body size. The animal-design counterparts of these features are evident. The view that emerges is that the evolution phenomenon is broader than biological evolution. The evolution of technology, river basins, and animal design is one phenomenon, and it belongs in physics.

  17. Summary of the Aerodynamic Characteristics and Flying Qualities Obtained from Flights of Rocket-Propelled Models of an Airplane Configuration Incorporating a Sweptback Inversely Tapered Wing at Transonic and Low-Supersonic Speeds

    NASA Technical Reports Server (NTRS)

    Mitcham, Grady L.; Blanchard, Willard S., Jr.

    1950-01-01

    Flight tests have been conducted on rocket-propelled models of an airplane configuration incorporating a sweptback wing with inverse taper to investigate the drag, stability, and control characteristics at transonic and supersonic speeds. The models were tested with a conventional tail arrangement in the Mach number range from 0.55 to 1.2. In addition to the various aerodynamic parameters obtained, the flying qualities were computed for a full-scale airplane with the center-of-gravity location at 18 percent of the mean aerodynamic chord. Also, included in this investigation are drag measurements made on relatively simple fixed-control models tested with both conventional and V-tail arrangements.

  18. Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the McDonnell XP-88 Airplane with a VEE Tail

    NASA Technical Reports Server (NTRS)

    Berman, Theodore

    1947-01-01

    An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 airplane has been conducted in the Langley 20-ft free-spinning tunnel. Results of tests with a conventional tail have been previously reported; the results presented herein are for the model with a vee tail installed. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model. In the normal loading were determined. Tests of the model in the long-range loading also were made. The investigation included leading-edge-flap, spin-recovery-parachute, and rudder-pedal-force tests. The recovery characteristics of the model were satisfactory for the normal loading. Deflecting the leading-edge flaps improved recoveries. The results indicated that with the external wing tanks installed (long-range loading) recoveries may be poor and, therefore, if a spin is inadvertently entered in this condition the tanks should be jettisoned if recovery does not appear imminent immediately after it is attempted. A 10-foot spin-recovery tail parachute with a towline 40 feet long and a drag coefficient of 0.63 was found to be effective for spin recovery. The rudder pedal force required for spin recovery was indicated to be within the capabilities of the pilot.

  19. Preliminary Evaluation of the Low-Speed Stability and Control Characteristics of the McDonnell XP-85 Airplane from Tests of an Unballasted 1/5-Scale Model in the Langley Free-Flight Tunnel

    NASA Technical Reports Server (NTRS)

    Paulson, John W.; Johnson, Joseph L.

    1947-01-01

    At the request of the Air Material Command, Army Air Forces an investigation of the low-speed, power-off stability and control characteristics of the McDonnell XP-85 airplane is being conducted in the Langley free-flight tunnel. The XP-85 airplane is a jet propelled, parasite fighter with a 34 deg sweepback at the wing quarter chord. It was designed to be carried in a bomb bay of the B-36 air plane. The first portion of the investigation consists of a preliminary evaluation of the stability and control characteristics of the airplane from force and fight tests of an unballasted 1/5-scale model. The second portion of the investigation consists of test of a properly balasted 1/10-scale model which will include a study of the stability of the Xp-85 when attached to the trapeze for retraction into the B-36 bomb bay. The results of the preliminary test with the 1/5-scale model are presented herein. This portion fo the investigation included tests of the model with various center fin arrangements. Both the design nose flap and a stall control vane were investigated.

  20. 77 FR 54848 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-06

    ...We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, -500, -600, -700, - 700C, -800, -900, and -900ER series airplanes. This proposed AD was prompted by a review of the tail strobe light installation, which revealed that the tail strobe light is not electrically bonded to primary structure of the airplane. This proposed AD would require......