Sample records for mcdonnell f-101a airplane
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2010-08-05
... Airworthiness Directives; McDonnell Douglas Corporation Model MD- 11 and MD-11F Airplanes Equipped With General... Sec. 39.13 by adding the following new AD: 2010-16-03 McDonnell Douglas Corporation: Amendment 39... applies to McDonnell Douglas Corporation Model MD-11 and MD-11F airplanes, certified in any category...
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2010-06-23
... Airworthiness Directives; McDonnell Douglas Corporation Model DC- 10-10, DC-10-10F, and MD-10-10F Airplanes... certain McDonnell Douglas Model DC-10-10, DC-10-10F, and MD-10-10F airplanes. That NPRM was published in... amends Sec. 39.13 by adding the following new AD: 2010-13-06 McDonnell Douglas Corporation: Amendment 39...
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2010-01-19
...-0043; Directorate Identifier 2009-NM-128-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas... directive (AD) for certain McDonnell Douglas Model DC-10-10, DC-10-10F, and MD-10-10F airplanes. This... adding the following new AD: McDonnell Douglas Corporation: Docket No. FAA-2010-0043; Directorate...
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75 FR 50878 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes
2010-08-18
... Airworthiness Directives; McDonnell Douglas Corporation Model MD- 90-30 Airplanes AGENCY: Federal Aviation... McDonnell Douglas Corporation: Amendment 39-16388. Docket No. FAA-2010-0433; Directorate Identifier 2009-NM..., 2010. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas Corporation Model...
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75 FR 68245 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes
2010-11-05
...-1043; Directorate Identifier 2010-NM-200-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas... McDonnell Douglas Model MD-90-30 airplanes. This proposed AD would require installing new fire handle... airworthiness directive (AD): McDonnell Douglas Corporation: Docket No. FAA-2010-1043; Directorate Identifier...
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75 FR 38056 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes
2010-07-01
...-0645; Directorate Identifier 2009-NM-200-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas..., September 9, 2008), for certain McDonnell Douglas Corporation Model MD-90-30 airplanes. That AD requires a... fasteners in the aft mount support fitting of the left and right engines on 29 McDonnell Douglas Corporation...
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2010-08-05
... Airworthiness Directives; McDonnell Douglas Corporation Model DC- 9-10 Series Airplanes, DC-9-30 Series... existing airworthiness directive (AD), which applies to all McDonnell Douglas Model DC-9-10 series..., 2010). That AD applies to all McDonnell Douglas Corporation Model DC-9-10 series airplanes, DC-9-30...
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75 FR 21528 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes
2010-04-26
...-0433; Directorate Identifier 2009-NM-117-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas... main landing gear (MLG) during gear extension, damaging the hydraulic system on McDonnell Douglas.... The retract cylinder support fittings for the MLG on McDonnell Douglas Model MD-80 series airplanes...
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75 FR 66653 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes
2010-10-29
... Airworthiness Directives; McDonnell Douglas Corporation Model MD- 90-30 Airplanes AGENCY: Federal Aviation...-15667 (73 FR 52203, September 9, 2008), and adding the following new AD: 2010-22-04 McDonnell Douglas... supersedes AD 2008-18-10, Amendment 39-15667. Applicability (c) This AD applies to McDonnell Douglas...
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2010-07-01
... Airworthiness Directives; McDonnell Douglas Corporation Model DC- 9-10 Series Airplanes, DC-9-30 Series... previously to all known U.S. owners and operators of the McDonnell Douglas Corporation airplanes identified... INFORMATION: On July 15, 2009, we issued AD 2009-15-16, which applies to all McDonnell Douglas Model DC-9-10...
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2010-10-01
... Airworthiness Directives; McDonnell Douglas Corporation Model DC- 10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10... adding the following new AD: 2010-20-14 McDonnell Douglas Corporation: Amendment 39-16449. Docket No. FAA... the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD. (1) McDonnell Douglas Corporation...
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75 FR 36577 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes
2010-06-28
... Airworthiness Directives; McDonnell Douglas Corporation Model MD- 90-30 Airplanes AGENCY: Federal Aviation... Douglas Corporation: Docket No. FAA-2010-0554; Directorate Identifier 2010-NM-082-AD. Comments Due Date (a... supersedes AD 2009-07-04, Amendment 39-15863. Applicability (c) This AD applies to McDonnell Douglas...
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75 FR 80742 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes
2010-12-23
...-1202; Directorate Identifier 2010-NM-167-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas... amends Sec. 39.13 by adding the following new airworthiness directive (AD): McDonnell Douglas Corporation... Douglas Corporation Model MD-90-30 airplanes, certificated in any category. Subject (d) Joint Aircraft...
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Kennedy, Thomas L.
1956-01-01
A flight investigation was conducted to determine the effect of jet exhaust on the drag, trim characteristics, and afterbody pressures on a 0.125-scale rocket model of the McDonnell F-101A airplance. Power-off data were obtained over a Mach number range of 1.04 to 1.9 and power-on data were obtained at a Mach number of about 1.5. The data indicated that with power-on the change in external drag coefficient was within the data accuracy and there was a decrease in trim angle of attack of 1.27 degrees with a corresponding decrease of 0.07 in lift coefficient. Correspondingly, pressure coefficients on the side and bottom of the fuselage indicated a positive increment near the jet exit. As the distance downstream of the jet exit increased, the increment on the bottom of the fuselage increased, whereas the increments on the side decreased to a negative peak.
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Flight testing a propulsion-controlled aircraft emergency flight control system on an F-15 airplane
Burcham, F. W., Jr.; Burken, John; Maine, Trindel A.
1994-01-01
Flight tests of a propulsion-controlled aircraft (PCA) system on an F-15 airplane have been conducted at the NASA Dryden Flight Research Center. The airplane was flown with all flight control surfaces locked both in the manual throttles-only mode and in an augmented system mode. In the latter mode, pilot thumbwheel commands and aircraft feedback parameters were used to position the throttles. Flight evaluation results showed that the PCA system can be used to land an airplane that has suffered a major flight control system failure safely. The PCA system was used to recover the F-15 airplane from a severe upset condition, descend, and land. Pilots from NASA, U.S. Air Force, U.S. Navy, and McDonnell Douglas Aerospace evaluated the PCA system and were favorably impressed with its capability. Manual throttles-only approaches were unsuccessful. This paper describes the PCA system operation and testing. It also presents flight test results and pilot comments.
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2010-04-21
...-0384; Directorate Identifier 2010-NM-003-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas... Douglas Corporation: Docket No. FAA-2010-0384; Directorate Identifier 2010-NM-003-AD. Comments Due Date (a... the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD. (1) McDonnell Douglas Corporation...
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2010-10-05
... Airworthiness Directives; McDonnell Douglas Corporation Model DC- 10-30, DC-10-30F, DC-10-30F (KC-10A and KDC-10...-13 McDonnell Douglas Corporation: Amendment 39-16448; Docket No. FAA-2010-0553; Directorate.... Applicability (c) This AD applies to McDonnell Douglas Corporation Model DC- 10-30, DC-10-30F, DC-10-30F (KC-10A...
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2010-12-07
... Airworthiness Directives; McDonnell Douglas Corporation Model DC- 9-30, DC-9-40, and DC-9-50 Series Airplanes...: We are adopting a new airworthiness directive (AD) for the McDonnell Douglas Corporation airplanes... to include an airworthiness directive (AD) that would apply to certain McDonnell Douglas Model DC-9...
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2010-05-04
... Airworthiness Directives; McDonnell Douglas Corporation Model DC- 10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10... amends Sec. 39.13 by adding the following new AD: 2010-09-12 McDonnell Douglas Corporation: Amendment 39... to McDonnell Douglas Corporation Model DC- 10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A...
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Crabill, Norman L.
1956-01-01
The National Advisory Committee for Aeronautics has conducted a flight test of a model approximating the McDonnell F3H-lN airplane configuration to determine its pitch-up and buffet boundaries, as well as the usual longitudinal stability derivatives obtainable from the pulsed- tail technique. The test was conducted by the freely flying rocket- boosted model technique developed at the Langley Laboratory; results were obtained at Mach numbers from 0.40 to 1.27 at corresponding Reynolds numbers of 2.6 x 10(exp 6) and 9.0 x 10(exp 6). The phenomena of pitch-up, buffet, and maximum lift were encountered at Mach numbers between 0.42 and 0.85. The lift-curve slope and wing-root bending-moment slope increased with increasing angle of attack, whereas the static stability decreased with angle of attack at subsonic speeds and increased at transonic speeds. There was little change in trim at low lift at transonic speeds.
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2010-02-08
...-0032; Directorate Identifier 2009-NM-213-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas...: McDonnell Douglas Corporation: Docket No. FAA-2010-0032; Directorate Identifier 2009-NM-213-AD. Comments Due... applies to McDonnell Douglas Corporation Model DC- 10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A...
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2010-10-14
... Airworthiness Directives; McDonnell Douglas Corporation Model DC- 10-10, DC-10-10F, DC-10-30, DC-10-30F (KDC-10... following new airworthiness directive (AD): 2010-21-13 McDonnell Douglas Corporation: Amendment 39-16473... November 18, 2010. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas...
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2010-07-07
...-0672; Directorate Identifier 2010-NM-047-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas...: McDonnell Douglas Corporation: Docket No. FAA-2010-0672; Directorate Identifier 2010-NM-047-AD. Comments Due... applies to McDonnell Douglas Corporation Model DC- 10-10, DC-10-10F, DC-10-30, DC-10-30F (KDC-10), DC-10...
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2010-10-07
... Airworthiness Directives; McDonnell Douglas Corporation Model DC- 8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and... to all of the McDonnell Douglas Corporation airplanes identified above. The existing AD currently... the following new airworthiness directive (AD): 2010-21-03 McDonnell Douglas Corporation: Amendment 39...
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2010-11-05
...-1044; Directorate Identifier 2010-NM-033-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas..., 2007) and adding the following new AD: McDonnell Douglas Corporation: Docket No. FAA-2010-1044.... Applicability (c) This AD applies to all McDonnell Douglas Corporation Model DC-10-10, DC-10-10F, DC-10-15, DC...
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78 FR 78285 - Airworthiness Directives; Airbus Airplanes
2013-12-26
...-1064; Directorate Identifier 2012-NM-101-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... A300 B4-605R and B4-622R airplanes; Model A300 F4-605R airplanes; and Model A300 C4-605R Variant F airplanes. AD 2005-23-08 required repetitive inspections to detect cracks of certain attachment holes...
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2010-05-17
... Airworthiness Directives; McDonnell Douglas Corporation Model DC- 9-30, DC-9-40, and DC-9-50 Series Airplanes... airworthiness directive (AD) for certain Model DC-9-30, DC-9-40, and DC-9-50 series airplanes. This AD requires... this AD to detect and correct the potential for an arc/spark condition to occur within the fuel boost...
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Flight Tests of a Ministick Controller in an F/A-18 Airplane
Stoliker, Patrick C.; Carter, John
2003-01-01
In March of 1999, five pilots performed flight tests to evaluate the handling qualities of an F/A-18 research airplane equipped with a small-displacement center stick (ministick) controller that had been developed for the JAS 39 Gripen airplane (a fighter/attack/ reconnaissance airplane used by the Swedish air force). For these tests, the ministick was installed in the aft cockpit (see figure) and production support flight control computers (PSFCCs) were used as interfaces between the controller hardware and the standard F/A-18 flight-control laws. The primary objective of the flight tests was to assess any changes in handling qualities of the F/A-18 airplane attributable to the mechanical characteristics of the ministick. The secondary objective was to demonstrate the capability of the PSFCCs to support flight-test experiments.
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14 CFR Appendix F to Part 135 - Airplane Flight Recorder Specification
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specification F.... F Appendix F to Part 135—Airplane Flight Recorder Specification The recorded values must meet the....125 0.004g 6. Pitch Attitude ±75% ±2° 1 or 0.25 for airplanes operated under § 135.152(j) 0.5° A...
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2010-12-30
...-1206; Directorate Identifier 2009-NM-216-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas... amends Sec. 39.13 by adding the following new AD: McDonnell Douglas Corporation: Docket No. FAA-2010-1206.... [[Page 82335
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2010-02-23
... Airworthiness Directives; Airbus Model A310-203, -221, -222 Airplanes; and Model A300 F4-605R and -622R...-222 airplanes, all serial numbers. (2) Airbus Model A300 F4-605R and A300 F4-622R airplanes, all...
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A pilot's opinion of the F-8 digital fly-by-wire airplane
Krier, G. E.
1976-01-01
The handling qualities of the F-8 digital fly by wire airplane are evaluated by using the Cooper-Harper rating scale. The reasons for the ratings are given, as well as a short description of the flying tasks. It was concluded that the handling qualities of the airplane were good in most situations, although occasional ratings of unsatisfactory were given.
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2011-05-19
... B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively... B4-605R and B4-622R airplanes; A300 F4-605R and F4-622R airplanes; A300 C4-605R Variant F airplanes...
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2011-04-08
... B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively... F4-605R and F4-622R airplanes, and Model A300 C4-605R Variant F airplanes; and Model A310-203, -204...
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76 FR 13075 - Airworthiness Directives; Airbus Model A330-243F Airplanes
2011-03-10
... Airworthiness Directives; Airbus Model A330-243F Airplanes AGENCY: Federal Aviation Administration (FAA... recent in-service event the flight crew of a Trent 700 powered A330 aircraft [[Page 13076
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Simulation model of a twin-tail, high performance airplane
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.
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Flight Test of the F/A-18 Active Aeroelastic Wing Airplane
Voracek, David
2007-01-01
A viewgraph presentation of flight tests performed on the F/A active aeroelastic wing airplane is shown. The topics include: 1) F/A-18 AAW Airplane; 2) F/A-18 AAW Control Surfaces; 3) Flight Test Background; 4) Roll Control Effectiveness Regions; 5) AAW Design Test Points; 6) AAW Phase I Test Maneuvers; 7) OBES Pitch Doublets; 8) OBES Roll Doublets; 9) AAW Aileron Flexibility; 10) Phase I - Lessons Learned; 11) Control Law Development and Verification & Validation Testing; 12) AAW Phase II RFCS Envelopes; 13) AAW 1-g Phase II Flight Test; 14) Region I - Subsonic 1-g Rolls; 15) Region I - Subsonic 1-g 360 Roll; 16) Region II - Supersonic 1-g Rolls; 17) Region II - Supersonic 1-g 360 Roll; 18) Region III - Subsonic 1-g Rolls; 19) Roll Axis HOS/LOS Comparison Region II - Supersonic (open-loop); 20) Roll Axis HOS/LOS Comparison Region II - Supersonic (closed-loop); 21) AAW Phase II Elevated-g Flight Test; 22) Region I - Subsonic 4-g RPO; and 23) Phase II - Lessons Learned
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2010-12-10
... Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R... airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; Model A300 C4...
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2011-07-06
... Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R... B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; Model A300 C4-605R Variant F...
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2011-02-07
... B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively...-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes, certificated in any category, all...
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2010-05-19
... B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively...-203, and B4-203 airplanes; Model A300 B4-601, B4- 603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4...
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2011-04-06
... B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively... July 20, 2005; have been performed in service. (2) Airbus Model A300 B4-605R, B4-622R, F4-605R, and F4... C4-600R, and A300 F4-600R series airplanes (fitted with a trim tank), all serial numbers, except...
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2011-06-29
... B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively...-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; and Model...
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2011-07-18
... Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4... A300 B4-605R and B4-622R airplanes, Model A300 F4-605R and F4-622R airplanes, and Model A300 C4- [[Page...
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Klinar, Walter J.; Lee, Henry A.
1954-01-01
A supplementary investigation was conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F9F-6 airplane. The primary purpose of the investigation was to reevaluate the spin-recovery characteristics of the airplane in view of the fact that the ailerons had been eliminated from the flaperon-aileron lateral control system of the airplane. A spin-tunnel investigation on a model of the earlier version of the F9F-6 airplane had indicated that use of ailerons with the spin (stick right in a right spin) was essential to insure recovery. The results indicate that with.ailerons eliminated, it may be difficult to obtain an erect developed spin but if a fully developed spin is obtained on the airplane, recovery therefrom may be difficult or impossible. Flaperon deflection should have little effect on spins or recoveries.
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2010-05-21
... Airworthiness Directives; Airbus Model A300 Series Airplanes; Model A300 B4-600, B4-600R, F4-600R Series..., B4-622, B4- 605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; and Model A310-203...
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Preliminary Flight Results of a Fly-by-throttle Emergency Flight Control System on an F-15 Airplane
Burcham, Frank W., Jr.; Maine, Trindel A.; Fullerton, C. Gordon; Wells, Edward A.
1993-01-01
A multi-engine aircraft, with some or all of the flight control system inoperative, may use engine thrust for control. NASA Dryden has conducted a study of the capability and techniques for this emergency flight control method for the F-15 airplane. With an augmented control system, engine thrust, along with appropriate feedback parameters, is used to control flightpath and bank angle. Extensive simulation studies were followed by flight tests. The principles of throttles only control, the F-15 airplane, the augmented system, and the flight results including actual landings with throttles-only control are discussed.
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2011-01-05
... Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R...-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes, certificated in any category...
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2010-01-15
... Conditions No. 25-401-SC] Special Conditions: Boeing Model 747-8/-8F Airplanes, Systems and Data Networks Security--Protection of Airplane Systems and Data Networks From Unauthorized External Access AGENCY... that effective electronic system security protection strategies are implemented to protect the airplane...
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2010-08-25
... Industries GmbH Models DA 40 and DA 40F Airplanes AGENCY: Federal Aviation Administration (FAA), Department... new airworthiness directive (AD) for all Diamond Aircraft Industries GmbH Models DA 40 and DA 40F... received information from Diamond Aircraft Industries GmbH that the Models DA 40 and DA 40F airplanes have...
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Emerson, Horace F.; Axelson, John A.
1949-01-01
An additional series of high-speed wind-tunnel tests of a modified 0.17-scale model of the McDonnell XF2H-1 airplane was conducted to evaluate the effects of a reduction in the thickness-to-chord ratios of the tail planes, the displacement of the horizontal tail relative to the vertical tail, and the extension of the trailing edge of the wing. Two tail-intersection fairings designed to improve the flow at the tail were also tested. The pitching-moment characteristics of the model were improved slightly by the use of the thinner tail sections. Rearward or rearward and downward displacements of the horizontal tail increased the critical Mach number at the tail intersection from 0.725 to a maximum of 0.80, but caused an excessive change in pitching-moment coefficient at the higher Mach numbers. Extending the trailing edge of the wing did not improve the static longitudinal-stability characteristics, but increased the pitching-down tendency between 0.725 and 0.825 Mach numbers prior to the pitching-up tendency. The extended wing did, however, increase the Mach numbers at which these tendencies occurred. The increase in the Mach numbers of divergence and the tuft studies indicate a probable increase in the buffet limit of the prototype airplane. No perceptible improvement of flow at the tail intersection was observed with the two fairings tested on the forward tail configuration.
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Burcham, Frank W., Jr.; Maine, Trindel A.; Fullerton, C. G.; Wells, Edward A.
1993-01-01
A multi-engine aircraft, with some or all of the flight control system inoperative, may use engine thrust for control. NASA Dryden has conducted a study of the capability and techniques for this emergency flight control method for the F-15 airplane. With an augmented control system, engine thrust, along with appropriate feedback parameters, is used to control flightpath and bank angle. Extensive simulation studies have been followed by flight tests. This paper discusses the principles of throttles-only control, the F-15 airplane, the augmented system, and the flight results including landing approaches with throttles-only control to within 10 ft of the ground.
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78 FR 70207 - Airworthiness Directives; Airbus Airplanes
2013-11-25
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes; and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was...
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2010-10-01
... Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4...; Model A300 B4-601, B4- 603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F...-- Dated-- A300 series airplanes......... A300-32A0447..... April 22, 2004. A300 B4-600, B4-600R, and F4...
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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.
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77 FR 24137 - Airworthiness Directives; Airbus Airplanes
2012-04-23
... Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule... Register. That AD applies to all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, Model... Airbus Model A300 B4-600, B4- 600R, and F4-600R series airplanes, Model A300 C4-605R Variant F airplanes...
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78 FR 9787 - Airworthiness Directives; Airbus Airplanes
2013-02-12
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes); and Airbus [[Page 9788
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78 FR 28159 - Airworthiness Directives; Airbus Airplanes
2013-05-14
...-0418; Directorate Identifier 2012-NM-200-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes...: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes...
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Design and flight experience with a digital fly-by-wire control system in an F-8 airplane
Deets, D. A.; Szalai, K. J.
1974-01-01
A digital fly-by-wire flight control system was designed, built, and for the first time flown in an airplane. The system, which uses components from the Apollo guidance system, is installed in an F-8 airplane as the primary control system. A lunar module guidance computer is the central element in the three-axis, single-channel, multimode, digital control system. A triplex electrical analog system which provides unaugmented control of the airplane is the only backup to the digital system. Flight results showed highly successful system operation, although the trim update rate was inadequate for precise trim changes, causing minor concern. The use of a digital system to implement conventional control laws proved to be practical for flight. Logic functions coded as an integral part of the control laws were found to be advantageous. Although software verification required extensive effort, confidence in the software was achieved.
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Bowman, James S., Jr.
1955-01-01
An investigation is being conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine spin and recovery characteristics and the minimum-size parachute required to satisfactorily terminate the spin in an emergency. Results obtained to date are presented herein. Test results indicate that it may be difficult to obtain an erect or inverted spin on the airplane, but, if a spin is obtained, the spin will be very oscillatory and recovery from the developed erect spin by rudder reversal may not be possible. The lateral controls will have no appreciable effect on recoveries from erect.spins. Recovery from the inverted spin by merely neutralizing the rudder will be satisfactory. After recoveries by rudder reversal and after recoveries from spins without control movement (no spins), the model oftentimes rolled very rapidly about the X-axis. Based on limited preliminary tests made in this investigation to make the model recover satisfactorily, it appears that canards near the nose of the airplane or differentially operated horizontal tails may be utilized to provide rapid recoveries. The parachute test results indicate that an 11-foot-diameter (laid-out-flat) parachute with a drag coefficient of 0.650 (based on the laid- out-flat diameter) and with a towline length equal to the wing span is the minimum-size parachute required to satisfactorily terminate an erect or inverted spin in an emergency.
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2012-08-29
... Airworthiness Directives; Hughes Helicopters, Inc., and McDonnell Douglas Helicopter Systems (Type Certificate... Airworthiness Directive (AD): Hughes Helicopters Inc., and McDonnel Douglas Helicopter Systems (Type Certificate...
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77 FR 16430 - Airworthiness Directives; Airbus Airplanes
2012-03-21
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R Variant F airplanes.../N A5231007000600. This [EASA] AD has been corrected to make clear that the use of Airbus SB A310...
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2013-03-26
... Airworthiness Directives; Hughes Helicopters, Inc., and McDonnell Douglas Helicopter Systems (Type Certificate... directive (AD): 2013-05-16 Hughes Helicopters, Inc., and McDonnell Douglas Helicopter Systems (Type...
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75 FR 8465 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes
2010-02-25
... this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood.... Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New... rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S...
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DEFF Research Database (Denmark)
Geisler, C; Plesner, T; Pallesen, G
1988-01-01
A murine monoclonal antibody (MoAb) F101.01 reacting with the T cell receptor (TCR)-T3 complex is presented. Immunohistological studies showed that F101.01 specifically stains T-zone lymphocytes in lymph nodes, tonsils, and splenic tissue. Two-colour immunofluorescence and flow cytometry...... demonstrated co-expression of the antigen defined by F101.01 and the pan-T cell antigens defined by CD2, CD3, CD5, and CD7 antibodies. Cells stained with CD4 and CD8 antibodies were both included in the F101.01-positive population, whereas CD16-positive natural killer cells (NK), B cells (CD19 and CD20......), and myeloid cells (CD13 and CD33) were excluded. The target antigen of F101.01 co-modulated with the CD3-defined antigen (T3) and the TCR recognized by the MoAb WT-31. CD3 antibody and WT-31 both blocked binding of F101.01. F101.01 precipitated the TCR-T3 complex from lysates of 125I-labelled peripheral blood...
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Assadourian, Arthur; Reeder, John P.
1948-01-01
A series of flight tests have been made at the Langley Flight Research Division at the request of the Bureau of Aeronautics, Department of the Navy, to determine the flying qualities of the Grumman F8F-1 air- plane. This paper presents the test results necessary to determine the longitudinal stability and control characteristics end the stalling characteristics. These tests were made between February and June of 1947- The range of Mach numbers covered in this investigation was approximately 0.10 to 0.62, and no attempt was made to investigate compressibility effects at higher Mach numbers. The lateral and directional stability and control characteristics of the subject airplane have already been reported (reference 1). Also presented in this paper is a discussion of the normal accelerations induced by yawing velocity and sideslip which were considered ob,jectionable by the pilot for this airplane. A discussion of the undesirable accelerations has been included with a view towards formulating some flying-qualities requirements limiting them.
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Gray, W.E.; Talmage, D.B.; Crane, H.L.
1945-01-01
The data presented have no bearing on performance characteristics of airplane, which were considered exceptionally good in previous tests. Some of the undesirable features of lateral and directional stability and control characteristics of the F-8 are listed. Directional stability, with rudder fixed, did not sufficiently restrict aileron yaw; rudder control was inadequate during take-off and landing, and was insufficient to fly airplane with one engine; in clean condition, power of ailerons was slightly below minimum value specified; it was difficult to trim airplane in rough air.
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2010-02-08
...-1213; Directorate Identifier 2009-NM-097-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas...: We propose to adopt a new airworthiness directive (AD) for certain McDonnell Douglas Corporation... [Amended] 2. The FAA amends Sec. 39.13 by adding the following new AD: McDonnell Douglas Corporation...
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78 FR 9581 - Airworthiness Directives; Airbus Airplanes
2013-02-11
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F...-03-11 Airbus: Amendment 39-17346. Docket No. FAA-2012-1002; Directorate Identifier 2012-NM-052-AD. (a...
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78 FR 15874 - Airworthiness Directives; Airbus Airplanes
2013-03-13
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F... ground threat avoidance, an Airbus A310 aeroplane experienced an uncommanded slide back of the co-pilot...
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77 FR 64701 - Airworthiness Directives; Airbus Airplanes
2012-10-23
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A300 series airplanes; Model A310 series airplanes; and Model A300 B4-600, B4-600R, and F4... that the AD be effective after Airbus completes certifying the improved design for the fuel pump half...
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78 FR 70003 - Airworthiness Directives; Airbus Airplanes
2013-11-22
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model...
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Up through the Ranks at McDonnell Douglas.
Settle, Mary
1989-01-01
Raher than bemoan the lack of leadership potential among younger employees, McDonnell Douglas Corporation has embarked on a comprehensive strategy of on-the-job development for staff members at all levels of the organization. Three types of rotational training are being used to address corporate, functional, and intracompany needs. (Author)
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2011-05-11
... Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R... applies to all Airbus Model A300 B4-601, B4-603, B4- 620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and...
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2010-06-18
...-0549; Directorate Identifier 2010-NM-109-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas... [Amended] 2. The FAA amends Sec. 39.13 by adding the following new AD: McDonnell Douglas Corporation... comments by August 2, 2010. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas...
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Design of active controls for the NASA F-8 digital fly-by-wire airplane
Gera, J.
1976-01-01
The design of a set of control laws for the NASA F-8 digital fly by wire research airplane is described. These control laws implement several active controls functions: maneuver load control, ride smoothing and departure boundary limiting. The criteria and methods which were used in the design of the control laws are also included. Results of linear analyses and nonlinear simulation are summarized.
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2011-09-23
... Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R... to Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R...
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Wing Torsional Stiffness Tests of the Active Aeroelastic Wing F/A-18 Airplane
Lokos, William A.; Olney, Candida D.; Crawford, Natalie D.; Stauf, Rick; Reichenbach, Eric Y.
2002-01-01
The left wing of the Active Aeroelastic Wing (AAW) F/A-18 airplane has been ground-load-tested to quantify its torsional stiffness. The test has been performed at the NASA Dryden Flight Research Center in November 1996, and again in April 2001 after a wing skin modification was performed. The primary objectives of these tests were to characterize the wing behavior before the first flight, and provide a before-and-after measurement of the torsional stiffness. Two streamwise load couples have been applied. The wing skin modification is shown to have more torsional flexibility than the original configuration has. Additionally, structural hysteresis is shown to be reduced by the skin modification. Data comparisons show good repeatability between the tests.
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76 FR 3854 - Airworthiness Directives; REIMS AVIATION S.A. Model F406 Airplanes
2011-01-21
... INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301... Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri...
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Spin-Tunnel Investigation of a 1/20-Scale Model of the Northrop F-5E Airplane
Scher, Stanley H.; White, William L.
1977-01-01
An investigation has been conducted in the Langley spin tunnel to determine the spin and recovery characteristics of a 1/20-scale model of the Northrop F-5E airplane. The investigation included erect and inverted spins, a range of center-of- gravity locations and moments of inertia, symmetric and asymmetric store loadings, and a determination of the parachute size required for emergency spin recovery. The effects of increased elevator trailing-edge-up deflections, of leading-edge and trailing-edge flap deflections, and of simulating the geometry of large external stores were also determined.
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Jones, Daniel S.; Ruf, Joseph H.; Bui, Trong T.; Martinez, Martel; St. John, Clinton W.
2014-01-01
The dual-bell rocket nozzle was first proposed in 1949, offering a potential improvement in rocket nozzle performance over the conventional-bell nozzle. Despite the performance advantages that have been predicted, both analytically and through static test data, the dual-bell nozzle has still not been adequately tested in a relevant flight environment. In 2013 a proposal was constructed that offered a National Aeronautics and Space Administration (NASA) F-15 airplane as the flight testbed, with the plan to operate a dual-bell rocket nozzle during captive-carried flight. If implemented, this capability will permit nozzle operation into an external flow field similar to that of a launch vehicle, and facilitate an improved understanding of dual-bell nozzle plume sensitivity to external flow-field effects. More importantly, this flight testbed can be utilized to help quantify the performance benefit with the dual-bell nozzle, as well as to advance its technology readiness level. Toward this ultimate goal, this report provides plans for future flights to quantify the external flow field of the airplane near the nozzle experiment, as well as details on the conceptual design for the dual-bell nozzle cold-flow propellant feed system integration within the NASA F-15 Propulsion Flight Test Fixture. The current study shows that this concept of flight research is feasible, and could result in valuable flight data for the dual-bell nozzle.
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Design and development experience with a digital fly-by-wire control system in an F-8C airplane
Deets, D. A.
1976-01-01
To assess the feasibility of a digital fly by wire system, the mechanical flight control system of an F-8C airplane was replaced with a digital primary system and an analog backup system. The Apollo computer was used as the heart of the primary system. This paper discusses the experience gained during the design and development of the system and relates it to active control systems that are anticipated for future civil transport applications.
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78 FR 68352 - Airworthiness Directives; Airbus Airplanes
2013-11-14
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. This AD was prompted by fatigue load... this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac...
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Davis, Simon
2017-10-23
In 1927 Michael McDonnell, a diasporic Irish Catholic, was appointed Mandatory Palestine's Chief Justice, being directed to institute firm British-style legal-judicial foundations for future self-governance. This entailed common, equal status for Arab and Jewish Palestinians, implicitly de-privileging the Jewish National Home. McDonnell was resisted in this by the British Mandate's Anglo-Jewish, pro-Zionist Attorney General, Norman Bentwich. McDonnell prevailed but only at the cost of being characterized lastingly as a pro-Arab, Catholic anti-Semite. McDonnell's continuing defence of a supreme, independent judiciary antagonized the Palestine Executive of High Commissioner Arthur Wauchope, who tried to co-opt rather than subordinate Zionist interests. Consequent frictions culminated in 1936 with McDonnell adjudicating against supra-legal British repression of Palestine's great Arab rebellion. For this he was dismissed and ostracized, subsequently publishing critiques of British policy in fringe right-wing organs. Yet McDonnell professed explicitly non-racist views, reflecting a liberal-minded, constitutional Irish nationalist equation of Palestine with Ireland, seeing comparable settler-colonial abuses and native distress as remediable only by transcendentally impartial justice. Britain reneging on these principles led McDonnell, like those Irish imperial servants noted in India, to identify with colonial subjects against colonialism. His case is one of empire as a system of domination being challenged from within, although his removal foreshadowed emerging imperial counter-insurgency's tendency not only to repress subject populations but deny civil-progressive alternatives for managing post-colonial transition. © The Author [2017]. Published by Oxford University Press. All rights reserved. For Permissions, please email: journals.permissions@oup.com.
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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.
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Fusion energy development at McDonnell Douglas: why and how
International Nuclear Information System (INIS)
Ard, W.B.
1985-01-01
The McDonnell Douglas Astronautics Company started a development program in fusion energy in 1974. This paper discusses the rationale for an industrial program in fusion energy and gives a brief account of the major activities that the company has been involved in during the course of this effort
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77 FR 40485 - Airworthiness Directives; Airbus Airplanes
2012-07-10
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... (AD) for all Airbus Model A300 series airplanes; all Model A300 B4-600, B4-600R, and F4-600R series... new AD: 2012-13-06 Airbus: Amendment 39-17108. Docket No. FAA-2012-0040; Directorate Identifier 2011...
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Burcham, Frank W., Jr.; Gatlin, Donald H.; Stewart, James F.
1995-01-01
The NASA Dryden Flight Research Center has been conducting integrated flight-propulsion control flight research using the NASA F-15 airplane for the past 12 years. The research began with the digital electronic engine control (DEEC) project, followed by the F100 Engine Model Derivative (EMD). HIDEC (Highly Integrated Digital Electronic Control) became the umbrella name for a series of experiments including: the Advanced Digital Engine Controls System (ADECS), a twin jet acoustics flight experiment, self-repairing flight control system (SRFCS), performance-seeking control (PSC), and propulsion controlled aircraft (PCA). The upcoming F-15 project is ACTIVE (Advanced Control Technology for Integrated Vehicles). This paper provides a brief summary of these activities and provides background for the PCA and PSC papers, and includes a bibliography of all papers and reports from the NASA F-15 project.
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78 FR 70851 - Airworthiness Directives; The Boeing Company Airplanes
2013-11-27
... (EICAS) message that displays ``ENG THRUST (L,R)'' (for Model 787-8 airplanes) or ``ENG (1, 2, 3, or 4... The Boeing Company Model 747-8 and 747-8F series airplanes and Model 787-8 airplanes powered by GEnx...: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground...
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Burcham, Frank W., Jr.; Maine, Trindel A.; Fullerton, C. Gordon; Webb, Lannie Dean
1996-01-01
A propulsion-controlled aircraft (PCA) system for emergency flight control of aircraft with no flight controls was developed and flight tested on an F-15 aircraft at the NASA Dryden Flight Research Center. The airplane has been flown in a throttles-only manual mode and with an augmented system called PCA in which pilot thumbwheel commands and aircraft feedback parameters were used to drive the throttles. Results from a 36-flight evaluation showed that the PCA system can be used to safety land an airplane that has suffered a major flight control system failure. The PCA system was used to recover from a severe upset condition, descend, and land. Guest pilots have also evaluated the PCA system. This paper describes the principles of throttles-only flight control; a history of loss-of-control accidents; a description of the F-15 aircraft; the PCA system operation, simulation, and flight testing; and the pilot comments.
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Bare, E. A.; Berrier, B. L.; Capone, F. J.
1981-01-01
Investigations were conducted in the Langley 16-Foot Transonic Tunnel to provide data on a 0.10-scale model of the prototype F-18 airplane and a 0.047-scale model of the F-15 three-surface configuration (canard, wing, and horizontal tails). Test data were obtained at static conditions and at Mach numbers from 0.6 to 1.2 over an angle-of-attack range from 2 deg to 15 deg. Nozzle pressure ratio was varied from jet off to about 8.0.
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Flight Test Results from the Rake Airflow Gage Experiment on the F-15B Airplane
Frederick, Michael A.; Ratnayake, Nalin A.
2011-01-01
The Rake Airflow Gage Experiment involves a flow-field survey rake that was flown on the Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center using the Dryden F-15B research test bed airplane. The objective of this flight test was to ascertain the flow-field angularity, local Mach number profile, total pressure distortion, and dynamic pressure at the aerodynamic interface plane of the Channeled Centerbody Inlet Experiment. This new mixed-compression, supersonic inlet is planned for flight test in the near term. Knowledge of the flow-field characteristics at this location underneath the airplane is essential to flight test planning and computational modeling of the new inlet, anairplane, flying at a free-stream Mach number of 1.65 and a pressure altitude of 40,000 ft, would achieve the desired local Mach number for the future inlet flight test. Interface plane distortion levels of 2 percent and a local angle of attack of -2 deg were observed at this condition. Alternative flight conditions for future testing and an exploration of certain anomalous data also are provided.
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2010-07-27
... Model Falcon 10 Airplanes; Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G Airplanes.... Since that NPRM was issued, we have determined that Model FAN JET FALCON SERIES C, D, E, F, and G..., Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes, and Model MYSTERE-FALCON 20-C5...
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2010-12-07
... Airworthiness Directives; Diamond Aircraft Industries GmbH Models DA 40 and DA 40F Airplanes AGENCY: Federal... of the Thielert Engine Owners Group commented that the Model DA 42 has the same door design and the same unsafe condition. He recommended that the AD also apply to the Model DA 42. The FAA has discussed...
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14 CFR Appendix M to Part 121 - Airplane Flight Recorder Specifications
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specifications M... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Pt. 121, App. M Appendix M to Part 121—Airplane... airplanes operated under § 121.344(f) 0.5° A sampling rate of 0.25 is recommended. 7. Roll attitude 2 ±180...
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DEFF Research Database (Denmark)
Geisler, C; Plesner, T; Pallesen, G
1988-01-01
demonstrated co-expression of the antigen defined by F101.01 and the pan-T cell antigens defined by CD2, CD3, CD5, and CD7 antibodies. Cells stained with CD4 and CD8 antibodies were both included in the F101.01-positive population, whereas CD16-positive natural killer cells (NK), B cells (CD19 and CD20...
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2010-12-23
...-1203; Directorate Identifier 2010-NM-168-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas... amends Sec. 39.13 by adding the following new airworthiness directive (AD): McDonnell Douglas Corporation... Douglas Corporation Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87) and MD-88...
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Wolhart, Walter D.; Thomas, David F., Jr.
1955-01-01
An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution.
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International Nuclear Information System (INIS)
Buragohain, Amlan; Couck, Sarah; Van Der Voort, Pascal; Denayer, Joeri F.M.; Biswas, Shyam
2016-01-01
Four existing and three new functionalized chromium terephthalates having MIL-101 topology and denoted as Cr-MIL-101-X (existing ones with X=–F, 1-F; –Cl, 2-Cl; –Br, 3-Br; –CH 3 , 4-CH 3 ; new ones with X=–C 6 H 4 , 5-C 6 H 4 ; –F 2 , 6-F 2 , –(CH 3 ) 2 , 7-(CH 3 ) 2 ) were synthesized under hydrothermal conditions. All the materials except 5-C 6 H 4 could be prepared by a general synthetic route, in which the mixtures of CrO 3 , H 2 BDC-X (BDC=1,4-benzenedicarboxylate) linkers, conc. HCl and water with a molar ratio of 1:1:3.9:222.2 were reacted at 180 °C for 144 h. Compared to the 144 h of synthesis time, three of the compounds, namely 1-Cl, 2-Br and 5-C 6 H 4 , could be prepared in much shorter reaction times (12–18 h at 180–210 °C). The materials possess high thermal stability up to 270–300 °C in an air atmosphere. The activated compounds exhibit significant porosity (S BET range: 1273–2135 m 2 g −1 ). At 0 °C and 1 bar, the CO 2 adsorption capacities of the compounds fall in the 1.7–2.9 mmol g −1 range. Compounds 1-F and 6-F 2 showed enhanced CO 2 uptake values compared to parent Cr-MIL-101. The benzene adsorption capacities of the compounds lie in the range of 66.2–139.5 molecules per unit cell at 50 °C and p/p 0 =0.35. The increased benzene uptake value of 1-F compared to un-functionalized Cr-MIL-101 and 4-CH 3 suggests that the fluorination has induced more hydrophobicity in Cr-MIL-101 as compared to the methylation. - Graphical abstract: Benzene adsorption by seven functionalized Cr-MIL-101-X metal-organic framework (MOF) materials Display Omitted - Highlights: • Seven functionalized Cr-MIL-101-X materials were synthesized solvothermally. • All Cr-MIL-101-X materials exhibited high thermal stability up to 270–300 °C in air. • All Cr-MIL-101-X compounds displayed considerable porosity towards N 2 , CO 2 and benzene. • Mono- and di-fluorinated Cr-MIL-101 materials showed enhanced CO 2 adsorption capacities.
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78 FR 52838 - Airworthiness Directives; The Boeing Company Airplanes
2013-08-27
... consequent forced landing of the airplane. DATES: This AD is effective October 1, 2013. The Director of the... to comply with this AD: Estimated Costs Cost per Cost on U.S. Action Labor cost product operators... consequent forced landing of the airplane. (f) Compliance Comply with this AD within the compliance times...
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77 FR 64704 - Airworthiness Directives; The Boeing Company Airplanes
2012-10-23
... consequent forced landing of the airplane. DATES: This AD is effective November 27, 2012. The Director of the... Labor cost product Cost on U.S. operators Operational Test 3 work hours x $85 per $255 $275,400 per..., inability to restart the engines, and consequent forced landing of the airplane. (f) Compliance Comply with...
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76 FR 15818 - Airworthiness Directives; Reims Aviation S.A. Model F406 Airplanes
2011-03-22
...-329-4148. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane... procedures found in 14 CFR 39.19. Send information to Attn: Albert Mercado, Aerospace Engineer, FAA, Small...
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Wolhart, Walter D.; Thomas, David F., Jr.
1955-01-01
An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution.
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77 FR 50644 - Airworthiness Directives; Cessna Airplane Company Airplanes
2012-08-22
... Airworthiness Directives; Cessna Airplane Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... (AD) for certain Cessna Airplane Company Model 525 airplanes equipped with certain part number (P/N... Aircraft Company (Cessna) 525, 550, and 560 airplanes, where investigation revealed brushes had worn beyond...
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77 FR 52205 - Airworthiness Directives; Univair Aircraft Corporation Airplanes
2012-08-29
... Airworthiness Directives; Univair Aircraft Corporation Airplanes AGENCY: Federal Aviation Administration (FAA... certain Univair Aircraft Corporation Models (ERCO) 415-C, 415-CD, 415-D, E, G; (Forney) F-1 and F-1A... inspection results. This new AD was prompted by a report of a Univair Aircraft Corporation Model ERCO 415-D...
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2011-06-22
... pieces unit with 3 welds (old design) as pictured in Appendix 1 of this [EASA] AD. The welding process of... pre-modification 02447.. Blue and Green. A300 airplanes post-modification 02447. Blue. A300-600 airplanes Blue. A310 airplanes Green. Table 2--Applicable service information Airbus mandatory service...
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2011-08-05
... Airworthiness Directives; Airbus Model A300 B4-600, A300 B4-600R, and A300 F4-600R Series Airplanes, and Model..., B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; and Model A310-203, -204, -221, -222...
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2011-05-04
... Airworthiness Directives; Airbus Model A300 B4-600, A300 B4-600R, and A300 F4-600R Series Airplanes, and Model...-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; and Model A310-203, -204, -221, -222...
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Flight Test Results for the F-16XL With a Digital Flight Control System
Stachowiak, Susan J.; Bosworth, John T.
2004-01-01
In the early 1980s, two F-16 airplanes were modified to extend the fuselage length and incorporate a large area delta wing planform. These two airplanes, designated the F-16XL, were designed by the General Dynamics Corporation (now Lockheed Martin Tactical Aircraft Systems) (Fort Worth, Texas) and were prototypes for a derivative fighter evaluation program conducted by the United States Air Force. Although the concept was never put into production, the F-16XL prototypes provided a unique planform for testing concepts in support of future high-speed supersonic transport aircraft. To extend the capabilities of this testbed vehicle the F-16XL ship 1 aircraft was upgraded with a digital flight control system. The added flexibility of a digital flight control system increases the versatility of this airplane as a testbed for aerodynamic research and investigation of advanced technologies. This report presents the handling qualities flight test results covering the envelope expansion of the F-16XL with the digital flight control system.
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Gardner, William N.
1951-01-01
A flight investigation of a 1/7-scale rocket-powered model of the XF10F Grumman XFl0F airplane in the swept-wing configuration has been made. The purpose of this test was to determine the static longitudinal stability, damping in pitch, and longitudinal control effectiveness of the airplane with the center of gravity at 20 percent of the wing mean aerodynamic chord. Only a small amount of data was obtained from the test because, immediately after booster separation at a Mach number of 0.88, the configuration was directionally unstable and diverged in sideslip. Simultaneous with the sideslip divergence, the model became longitudinally unstable at 3 degree angle of attack and -6 degree sideslip and diverged in pitch to a high angle of attack. During the pitch-up the free-floating horizontal tail became unstable at 5 degree angle of attack and the tail drifted against its positive deflection limit.
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78 FR 18925 - Airworthiness Directives; Airbus Airplanes
2013-03-28
...-0212; Directorate Identifier 2012-NM-116-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes...: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-223F, -223, -321...., Monday through Friday, except Federal holidays. For Airbus service information identified in this...
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76 FR 27227 - Airworthiness Directives; Airbus Model A310 Series Airplanes
2011-05-11
... program, EASA [European Aviation Safety Agency] published AD 2007-0053, which replaced DGAC France AD F... airplane configuration: Cold working of trellis boom drainage holes. Repetitive detailed or rotating probe... take about 137 work-hours per product to comply with the basic requirements of this AD. The average...
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14 CFR 36.7 - Acoustical change: Transport category large airplanes and jet airplanes.
2010-01-01
... airplanes and jet airplanes. 36.7 Section 36.7 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... § 36.7 Acoustical change: Transport category large airplanes and jet airplanes. (a) Applicability. This section applies to all transport category large airplanes and jet airplanes for which an acoustical change...
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Optimization of USMC Hornet Inventory
2016-06-01
production and procurement phase began. In 1984, the DOD contracted with McDonnell Douglas for full rate production of the aircraft and introduced it into...squadrons flying the minimum number of monthly flight hours per the F/A-18 Training and Readiness Manual and continued average pilot production at VMFAT-101...building robust operational schedules for Air Force fighter squadrons. In particular, he focused on how to mitigate the effects of absenteeism 23
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Energy Technology Data Exchange (ETDEWEB)
Buragohain, Amlan [Department of Chemistry, Indian Institute of Technology Guwahati, 781039 Assam (India); Couck, Sarah [Department of Chemical Engineering, Vrije Universiteit Brussel, Pleinlaan 2, 1050 Brussels (Belgium); Van Der Voort, Pascal [Department of Inorganic and Physical Chemistry, Ghent University, COMOC – Center for Ordered Materials, Organometallics and Catalysis, Krijgslaan 281-S3, 9000 Ghent (Belgium); Denayer, Joeri F.M. [Department of Chemical Engineering, Vrije Universiteit Brussel, Pleinlaan 2, 1050 Brussels (Belgium); Biswas, Shyam, E-mail: sbiswas@iitg.ernet.in [Department of Chemistry, Indian Institute of Technology Guwahati, 781039 Assam (India)
2016-06-15
Four existing and three new functionalized chromium terephthalates having MIL-101 topology and denoted as Cr-MIL-101-X (existing ones with X=–F, 1-F; –Cl, 2-Cl; –Br, 3-Br; –CH{sub 3}, 4-CH{sub 3}; new ones with X=–C{sub 6}H{sub 4}, 5-C{sub 6}H{sub 4}; –F{sub 2}, 6-F{sub 2}, –(CH{sub 3}){sub 2}, 7-(CH{sub 3}){sub 2}) were synthesized under hydrothermal conditions. All the materials except 5-C{sub 6}H{sub 4} could be prepared by a general synthetic route, in which the mixtures of CrO{sub 3}, H{sub 2}BDC-X (BDC=1,4-benzenedicarboxylate) linkers, conc. HCl and water with a molar ratio of 1:1:3.9:222.2 were reacted at 180 °C for 144 h. Compared to the 144 h of synthesis time, three of the compounds, namely 1-Cl, 2-Br and 5-C{sub 6}H{sub 4}, could be prepared in much shorter reaction times (12–18 h at 180–210 °C). The materials possess high thermal stability up to 270–300 °C in an air atmosphere. The activated compounds exhibit significant porosity (S{sub BET} range: 1273–2135 m{sup 2} g{sup −1}). At 0 °C and 1 bar, the CO{sub 2} adsorption capacities of the compounds fall in the 1.7–2.9 mmol g{sup −1} range. Compounds 1-F and 6-F{sub 2} showed enhanced CO{sub 2} uptake values compared to parent Cr-MIL-101. The benzene adsorption capacities of the compounds lie in the range of 66.2–139.5 molecules per unit cell at 50 °C and p/p{sub 0}=0.35. The increased benzene uptake value of 1-F compared to un-functionalized Cr-MIL-101 and 4-CH{sub 3} suggests that the fluorination has induced more hydrophobicity in Cr-MIL-101 as compared to the methylation. - Graphical abstract: Benzene adsorption by seven functionalized Cr-MIL-101-X metal-organic framework (MOF) materials Display Omitted - Highlights: • Seven functionalized Cr-MIL-101-X materials were synthesized solvothermally. • All Cr-MIL-101-X materials exhibited high thermal stability up to 270–300 °C in air. • All Cr-MIL-101-X compounds displayed considerable porosity towards N{sub 2
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77 FR 26998 - Airworthiness Directives; Airbus Airplanes
2012-05-08
...-0428; Directorate Identifier 2011-NM-078-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes...: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-243, -243F, -342..., between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information...
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Proposed Flight Research of a Dual-Bell Rocket Nozzle Using the NASA F-15 Airplane
Jones, Daniel S.; Bui, Trong T.; Ruf, Joseph H.
2013-01-01
For more than a half-century, several types of altitude-compensating rocket nozzles have been proposed and analyzed, but very few have been adequately tested in a relevant flight environment. One type of altitude-compensating nozzle is the dual-bell rocket nozzle, which was first introduced into literature in 1949. Despite the performance advantages that have been predicted, both analytically and through static test data, the dual-bell nozzle has still not been adequately tested in a relevant flight environment. This paper proposes a method for conducting testing and research with a dual-bell rocket nozzle in a flight environment. We propose to leverage the existing NASA F-15 airplane and Propulsion Flight Test Fixture as the flight testbed, with the dual-bell nozzle operating during captive-carried flights, and with the nozzle subjected to a local flow field similar to that of a launch vehicle. The primary objective of this effort is not only to advance the technology readiness level of the dual-bell nozzle, but also to gain a greater understanding of the nozzle mode transitional sensitivity to local flow-field effects, and to quantify the performance benefits with this technology. The predicted performance benefits are significant, and may result in reducing the cost of delivering payloads to low-Earth orbit.
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Simulation of Dynamics of a Flexible Miniature Airplane
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.
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2011-10-18
... F & R flight testing regardless of the airplane's systems complexity or level of automation. After... than some transport category airplanes of the 1960s and earlier. The NPRM contains more of the...
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2010-04-09
... undergo F & R flight testing regardless of the airplane's systems complexity or level of automation. After... airplanes that weigh 6,000 pounds or less to be more complex and integrated than some transport category...
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Studi Komparasi Karakter Bentuk Estetik Desain Pesawat Tempur F-16 dan SU-27
Directory of Open Access Journals (Sweden)
Larasmoyo Nugroho
2008-03-01
Full Text Available Defense and security are serious business, as they represent the integrity and dignity of a nation. It is understandable to assess military power and facilities as crucial to a nation’s defense, shown in the use of fighter airplanes. A fighter airplane serves as a window to represent nation’s values, philosophy and ideology; appeared through its design form and defense ability. The presented paper explores and compares 2 (two types of fighter airplane, F-16 of US and SU-27 of Russia, in order to observe and characterize their design forms. Having acknowledged the characteristic of their design forms as tangible aspect of analysis, it is identified that this characteristic can be split into form design and numerical design. Comparative assessment of both fighter airplanes indicates that F-16 fighter airplane of US appears smaller than the SU-27 of Russia. The smaller size of F-16 form was meant to have superior maneuver-ability for air-to-air combat, while the size of SU-27 was meant to accommodate multi-tasking aspects of fighter airplane (air-to-air combat and interceptive act. As results, both airplane forms express different views and ideological perspectives. The F-16 of US shows great and superior ability to carry special task of becoming combat airplane (thrive to perfection, coming with a hefty price and catered for great quality. On the other hand, SU-27 of Russia shows a wider purpose and not necessarily has superior ability in order to carry diverse tasks of an airplane (multi-tasking, coming with a cheaper price and catered in a great quantity. Thus, it can be deduced that the American designer of fighter airplane tends to acknowledge specialization of military purpose compare to the Russian’s generalization of military purpose.
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Guide to Canadian Aerospace-Related Industries
1990-08-01
EXPERIENCE: Present customers include Canadian Forces, Boeing Commercial Airplane Company, Boeing Helicopter Company. ADDRESS: Baskin Drive East REVISED...University Tel: (604) 946-4900 of British Columbia, Robbins Company, Lockheed Petroleum Services Fax: (604) 946-4671 and McDonnell Douglas. KEYWORDS
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Kalil, Ford
1990-01-01
NASA is considering the use of various airplanes for a Shuttle Laser Technology Experiment Facility (LTEF)-to-Airplane laser communications experiment. As supporting documentation, pertinent technical details are included about the potential use of airplanes located at Ames Research Center and Wallops Flight Facility. The effects and application of orbital mechanics considerations are also presented, including slant range, azimuth, elevation, and time. The pros and cons of an airplane equipped with a side port with a bubble window versus a top port with a dome are discussed.
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Larson, T. J.
1984-01-01
The measurement performance of a hemispherical flow-angularity probe and a fuselage-mounted pitot-static probe was evaluated at high flow angles as part of a test program on an F-14 airplane. These evaluations were performed using a calibrated pitot-static noseboom equipped with vanes for reference flow direction measurements, and another probe incorporating vanes but mounted on a pod under the fuselage nose. Data are presented for angles of attack up to 63, angles of sideslip from -22 deg to 22 deg, and for Mach numbers from approximately 0.3 to 1.3. During maneuvering flight, the hemispherical flow-angularity probe exhibited flow angle errors that exceeded 2 deg. Pressure measurements with the pitot-static probe resulted in very inaccurate data above a Mach number of 0.87 and exhibited large sensitivities with flow angle.
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McDonnell Douglas Helicopter Company independent research and development: Preparing for the future
Haggerty, Allen C.
1988-01-01
During the 1970's and 80's, research has produced the technology that is seen in aircraft such as the LHX and future models. The technology is discussed that is reaching maturity and moving into the application stage of future programs. Technology is discussed in six major areas: advanced concepts, analysis techniques, structures, systems, simulation, and research and development facilities. The partnership of McDonnell Douglas Helicopter Co. and the government in developing these technologies is illustrated in several programs.
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Oblique-wing research airplane motion simulation with decoupling control laws
Kempel, Robert W.; Mc Neill, Walter E.; Maine, Trindel A.
1988-01-01
A large piloted vertical motion simulator was used to assess the performance of a preliminary decoupling control law for an early version of the F-8 oblique wing research demonstrator airplane. Evaluations were performed for five discrete flight conditions, ranging from low-altitude subsonic Mach numbers to moderate-altitude supersonic Mach numbers. Asymmetric sideforce as a function of angle of attack was found to be the primary cause of both the lateral acceleration noted in pitch and the tendency to roll into left turns and out of right turns. The flight control system was shown to be effective in generally decoupling the airplane and reducing the lateral acceleration in pitch maneuvers.
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National Research Council Canada - National Science Library
1999-01-01
This report explains the accident involving American Airlines flight 1420, a McDonnell Douglas MD-82, which crashed after it overran the end of runway 4R during landing at Little Rock National Airport...
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2011-02-07
... Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0100, 1000, 2000, 3000, and 4000 Airplanes AGENCY.... Applicability (c) This AD applies to Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes... April 20, 2010 (for Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes); or SBF100-28-063, dated April...
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77 FR 16147 - Airworthiness Directives; The Boeing Company Airplanes
2012-03-20
... identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box... Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE... that note (f) of Figures 10 and 24 of Boeing Alert Service Bulletin 767-56A0010, Revision 1, dated...
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Gardner, William N.; Edmondson, James L.
1950-01-01
A flight test was made to determine the servoplane effectiveness and stability characteristics of the free-floating horizontal stabilizer to be used on the XF10F airplane. The results of this test indicate that servoplane effectiveness is practically constant through the speed range up to a Mach number of 1.15, and the stabilizer static stability is satisfactory. A loss of damping occurs over a narrow Mach number range near M = 1.0, resulting in dynamic instability of the stabilizer in this narrow range. Above M = 1.0 there is a gradual positive trim change of the stabilizer.
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77 FR 67561 - Airworthiness Directives; Univair Aircraft Corporation Airplanes
2012-11-13
... Airworthiness Directives; Univair Aircraft Corporation Airplanes AGENCY: Federal Aviation Administration (FAA...) that published in the Federal Register. That AD applies to certain Univair Aircraft Corporation Models... throughout the AD for Univair Aircraft Corporation Models (ERCO) 415-C, 415-CD, 415-D, E, G; (Forney) F-1 and...
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78 FR 23110 - Airworthiness Directives; The Boeing Company Airplanes
2013-04-18
... pressure, resulting in improper flow of oxygen through the passenger masks and injury to passengers if... Company Model 777-200, -200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by a report... properly flow oxygen, and that a loud noise occurred in the overhead area, which was caused by the flex...
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77 FR 37797 - Airworthiness Directives; Airbus Airplanes
2012-06-25
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-200 series airplanes; Airbus Model A330-200 Freighter series airplanes; Airbus Model A330-300 series airplanes; Airbus Model A340-200 series airplanes; and Airbus Model A340-300 series...
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78 FR 78705 - Airworthiness Directives; Airbus Airplanes
2013-12-27
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... 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...
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14 CFR 23.3 - Airplane categories.
2010-01-01
... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Airplane categories. 23.3 Section 23.3... STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES General § 23.3 Airplane categories. (a) The normal category is limited to airplanes that have a seating configuration, excluding pilot...
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78 FR 28152 - Airworthiness Directives; Airbus Airplanes
2013-05-14
...-0416; Directorate Identifier 2012-NM-144-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... A318-111 and -112 airplanes, Model A319 series airplanes, Model A320 series airplanes, and Model A321 series airplanes. The existing AD currently requires repetitive inspections of the 80VU rack lower...
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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.
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78 FR 64894 - Airworthiness Directives; B-N Group Ltd. Airplanes
2013-10-30
... INFORMATION CONTACT: Taylor Martin, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4138; fax: (816) 329-4090; email: taylor[email protected] reduced engine control with consequent loss of control. (f) Actions and Compliance Unless already done, do...
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14 CFR 125.93 - Airplane limitations.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane limitations. 125.93 Section 125.93...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements § 125.93 Airplane...
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2013-10-25
... design feature associated with the architecture and connectivity capabilities of the airplanes' computer... the comment for an association, business, labor union, etc.). DOT's complete Privacy Act Statement can... architecture for the Embraer Model EMB-550 series of airplanes is composed of several connected networks. This...
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The Airplane Cabin Microbiome.
Weiss, Howard; Hertzberg, Vicki Stover; Dupont, Chris; Espinoza, Josh L; Levy, Shawn; Nelson, Karen; Norris, Sharon
2018-06-06
Serving over three billion passengers annually, air travel serves as a conduit for infectious disease spread, including emerging infections and pandemics. Over two dozen cases of in-flight transmissions have been documented. To understand these risks, a characterization of the airplane cabin microbiome is necessary. Our study team collected 229 environmental samples on ten transcontinental US flights with subsequent 16S rRNA sequencing. We found that bacterial communities were largely derived from human skin and oral commensals, as well as environmental generalist bacteria. We identified clear signatures for air versus touch surface microbiome, but not for individual types of touch surfaces. We also found large flight-to-flight beta diversity variations with no distinguishing signatures of individual flights, rather a high between-flight diversity for all touch surfaces and particularly for air samples. There was no systematic pattern of microbial community change from pre- to post-flight. Our findings are similar to those of other recent studies of the microbiome of built environments. In summary, the airplane cabin microbiome has immense airplane to airplane variability. The vast majority of airplane-associated microbes are human commensals or non-pathogenic, and the results provide a baseline for non-crisis-level airplane microbiome conditions.
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Nonlinear analysis of a reactor building for airplane impact loadings
International Nuclear Information System (INIS)
Zimmermann, T.; Rodriguez, C.; Rebora, B.
1981-01-01
The purpose is to analyze the influence of material nonlinear behavior on the response of a reinforced concrete reactor building and on equipment response for airplane impact loadings. Two analyses are performed: first, the impact of a slow-flying commercial airplane (Boeing 707), then the impact of a fast flying military airplane (Phantom). (orig./HP)
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Variable-Structure Control of a Model Glider Airplane
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.
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41 CFR 101-30.101-1a - Item of production.
2010-07-01
... 41 Public Contracts and Property Management 2 2010-07-01 2010-07-01 true Item of production. 101-30.101-1a Section 101-30.101-1a Public Contracts and Property Management Federal Property Management....1-General § 101-30.101-1a Item of production. Item-of-production means those articles, equipment...
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Dicarlo, Daniel J.; Brown, Philip W.; Hallissy, James B.
1992-01-01
Flight tests of an F-106B aircraft equipped with a leading-edge vortex flap, which represented the culmination of a research effort to examine the effectiveness of the flap, were conducted at the NASA Langley Research Center. The purpose of the flight tests was to establish a data base on the use of a wing leading-edge vortex flap as a means to validate the design and analysis methods associated with the development of such a vortical flow-control concept. The overall experiment included: refinements of the design codes for vortex flaps; numerous wind tunnel entries to aid in verifying design codes and determining basic aerodynamic characteristics; design and fabrication of the flaps, structural modifications to the wing tip and leading edges of the test aircraft; development and installation of an aircraft research instrumentation system, including wing and flap surface pressure measurements and selected structural loads measurements; ground-based simulation to assess flying qualities; and finally, flight testing. This paper reviews the operational aspects associated with the flight experiment, which includes a description of modifications to the research airplane, the overall flight test procedures, and problems encountered. Selected research results are also presented to illustrate the accomplishments of the research effort.
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Childhood headache attributed to airplane travel: a case report.
Rogers, Kirsty; Rafiq, Nadia; Prabhakar, Prab; Ahmed, Mas
2015-05-01
Headache attributed to airplane flights is a rare form of headache disorder. This case study describes an 11-year-old girl with recurrent, severe, frontal headaches occurring during airplane travel. The episodes were associated with dizziness and facial pallor but no additional symptoms and showed spontaneous resolution on landing. Blood tests and imaging revealed no abnormalities. The present case fulfils the criteria for airplane headache recently included in the revised edition of the International Classification of Headache Disorders (ICHD-III Beta). Only a few cases of airplane headache have been reported in children. To our knowledge, this is the fourth case. We review the current literature on this rare syndrome and discuss various proposed pathophysiological mechanisms. © The Author(s) 2014.
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75 FR 74608 - Airworthiness Directives; CENTRAIR Models 101, 101A, 101P, and 101AP Gliders
2010-12-01
....societe.com . You may review copies of the referenced service information at the FAA, Small Airplane..., France; telephone: +33 (0)254 370796; fax: +33 (0)54. 374864; Internet: http://www.societe.com . (3) You...
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78 FR 27015 - Airworthiness Directives; Airbus Airplanes
2013-05-09
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-200 and A330-300 series airplanes, and Model A340-200 and A340-300 series airplanes... seal on a solenoid. This AD requires, depending on airplane configuration, modifying three flight...
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78 FR 71992 - Airworthiness Directives; Airbus Airplanes
2013-12-02
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... certain Airbus Model A318-100 and A319-100 series airplanes, A320-111 airplanes, A320-200 series airplanes... identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707...
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O'Kelly, Burke R.
1954-01-01
Free-flight tests in the transonic speed range utilizing rocketpropelled models have been made on three pairs of 0.11-scale North American F-100 airplane wings having an aspect ratio of 3.47, a taper ratio of 0.308, 45 degree sweepback at the quarter-chord line, and thickness ratios of 31 and 5 percent to investigate the possibility of flutte r. Data from tests of two other rocket-propelled models which accidentally fluttered during a drag investigation of the North American F-100 airplane are also presented. The first set of wings (5 percent thick) was tested on a model which was disturbed in pitch by a moving tail and reached a maximum Mach number of 0.85. The wings encountered mild oscillations near the first - bending frequency at high lift coefficients. The second set of wings 9 percent thick was tested up to a maximum Mach number of 0.95 at (2) angles of attack provided by small rocket motors installed in the nose of the model. No oscillations resembling flutter were encountered during the coasting flight between separation from the booster and sustainer firing (Mach numbers from 0.86 to 0.82) or during the sustainer firing at accelerations of about 8g up to the maximum Mach number of the test (0.95). The third set of wings was similar to the first set and was tested up to a maximum Mach number of 1.24. A mild flutter at frequencies near the first-bending frequency of the wings was encountered between a Mach number of 1.15 and a Mach number of 1.06 during both accelerating and coasting flight. The two drag models, which were 0.ll-scale models of the North American F-100 airplane configuration, reached a maximum Mach number of 1.77. The wings of these models had bending and torsional frequencies which were 40 and 89 percent, respectively, of the calculated scaled frequencies of the full-scale 7-percent-thick wing. Both models experienced flutter of the same type as that experienced-by the third set of wings.
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Directory of Open Access Journals (Sweden)
Sieradzki Adam
2016-09-01
Full Text Available The joined wing concept is an unconventional airplane configuration, known since the mid-twenties of the last century. It has several possible advantages, like reduction of the induced drag and weight due to the closed wing concept. The inverted joined wing variant is its rarely considered version, with the front wing being situated above the aft wing. The following paper presents a performance prediction of the recently optimized configuration of this airplane. Flight characteristics obtained numerically were compared with the performance of two classical configuration airplanes of similar category. Their computational fluid dynamics (CFD models were created basing on available documentation, photographs and some inverse engineering methods. The analysis included simulations performed for a scale of 3-meter wingspan inverted joined wing demonstrator and also for real-scale manned airplanes. Therefore, the results of CFD calculations allowed us to assess the competitiveness of the presented concept, as compared to the most technologically advanced airplanes designed and manufactured to date. At the end of the paper, the areas where the inverted joined wing is better than conventional airplane were predicted and new research possibilities were described.
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Radiated Emissions from a Remote-Controlled Airplane-Measured in a Reverberation Chamber
Ely, Jay J.; Koppen, Sandra V.; Nguyen, Truong X.; Dudley, Kenneth L.; Szatkowski, George N.; Quach, Cuong C.; Vazquez, Sixto L.; Mielnik, John J.; Hogge, Edward F.; Hill, Boyd L.;
2011-01-01
A full-vehicle, subscale all-electric model airplane was tested for radiated emissions, using a reverberation chamber. The mission of the NASA model airplane is to test in-flight airframe damage diagnosis and battery prognosis algorithms, and provide experimental data for other aviation safety research. Subscale model airplanes are economical experimental tools, but assembling their systems from hobbyist and low-cost components may lead to unforseen electromagnetic compatibility problems. This report provides a guide for accommodating the on-board radio systems, so that all model airplane systems may be operated during radiated emission testing. Radiated emission data are provided for on-board systems being operated separately and together, so that potential interferors can be isolated and mitigated. The report concludes with recommendations for EMI/EMC best practices for subscale model airplanes and airships used for research.
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78 FR 68347 - Airworthiness Directives; Airbus Airplanes
2013-11-14
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...-200, A340- 300, A340-500, and A340-600 series airplanes. AD 2009-04-07 required revising the airplane... reference unit (ADIRU) from providing erroneous data to other airplane systems. AD 2011-02-09 required...
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78 FR 65187 - Airworthiness Directives; Airbus Airplanes
2013-10-31
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-300 series airplanes and Model A340-200 and -300 series airplanes. This AD was prompted..., and possibly resulting in loss of control of the airplane. DATES: This AD becomes effective December 5...
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14 CFR 125.75 - Airplane flight manual.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane flight manual. 125.75 Section 125... OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6... Airplane flight manual. (a) Each certificate holder shall keep a current approved Airplane Flight Manual or...
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Blended Buffet-Load-Alleviation System for Fighter Airplane
Moses, Robert W.
2005-01-01
The capability of modern fighter airplanes to sustain flight at high angles of attack and/or moderate angles of sideslip often results in immersion of part of such an airplane in unsteady, separated, vortical flow emanating from its forebody or wings. The flows from these surfaces become turbulent and separated during flight under these conditions. These flows contain significant levels of energy over a frequency band coincident with that of low-order structural vibration modes of wings, fins, and control surfaces. The unsteady pressures applied to these lifting surfaces as a result of the turbulent flows are commonly denoted buffet loads, and the resulting vibrations of the affected structures are known as buffeting. Prolonged exposure to buffet loads has resulted in fatigue of structures on several airplanes. Damage to airplanes caused by buffeting has led to redesigns of airplane structures and increased support costs for the United States Air Force and Navy as well as the armed forces of other countries. Time spent inspecting, repairing, and replacing structures adversely affects availability of aircraft for missions. A blend of rudder-control and piezoelectric- actuator engineering concepts was selected as a basis for the design of a vertical-tail buffet-load-alleviation system for the F/A-18 airplane. In this system, the rudder actuator is used to control the response of the first tail vibrational mode (bending at a frequency near 15 Hz), while directional patch piezoelectric actuators are used to control the second tail vibrational mode (tip torsion at a frequency near 45 Hz). This blend of two types of actuator utilizes the most effective features of each. An analytical model of the aeroservoelastic behavior of the airplane equipped with this system was validated by good agreement with measured results from a full-scale ground test, flight-test measurement of buffet response, and an in-flight commanded rudder frequency sweep. The overall performance of the
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77 FR 6023 - Airworthiness Directives; Airbus Airplanes
2012-02-07
...-0038; Directorate Identifier 2011-NM-209-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... airplanes and Model A310-203, -204, - 221, and -222 airplanes. This proposed AD was prompted by a report of... explosion and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by March...
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Air resistance measurements on actual airplane parts
Weiselsberger, C
1923-01-01
For the calculation of the parasite resistance of an airplane, a knowledge of the resistance of the individual structural and accessory parts is necessary. The most reliable basis for this is given by tests with actual airplane parts at airspeeds which occur in practice. The data given here relate to the landing gear of a Siemanms-Schuckert DI airplane; the landing gear of a 'Luftfahrzeug-Gesellschaft' airplane (type Roland Dlla); landing gear of a 'Flugzeugbau Friedrichshafen' G airplane; a machine gun, and the exhaust manifold of a 269 HP engine.
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[A rarely known headache: Airplane travel headache].
Azman, Filiz; Erkılınç, Büşra; Çabalar, Murat; Çağırıcı, Sultan; Yayla, Vildan
2017-01-01
Recently, headache associated with airplane travel has gained importance with case reports and took its place in the classification of headache in 2013. This rare condition has different spesific characteristic from the primary headaches and its pathophysiology is not clear yet. In this case report, a 27-years-old female patient was diagnosed with the headache associated with airplane travel by history, examination and imaging findings. The possible pathophysiology and treatment were discussed.
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An Evaluation of Very Large Airplanes and Alternative Fuels: Executive Summary
1976-12-01
the AIAA/ SAE Eleventh Prop~ilsion Conference, Anaheim, Cal., September 1975. i 33 Rom, F. E., "Nuclear-Powered Airplane," Technology Heview, December...Department of Defense Directive No. 4140 -43, December 5, 1975. Scarbrough, D. R., C-5B and Austere C-5 Data Package, Lockheed-Georgia Co., Operations
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Recurring norovirus transmission on an airplane.
Thornley, Craig N; Emslie, Nicola A; Sprott, Tim W; Greening, Gail E; Rapana, Jackie P
2011-09-01
Previously reported outbreaks of norovirus gastroenteritis associated with aircraft have been limited to transmission during a single flight sector. During October 2009, an outbreak of diarrhea and vomiting occurred among different groups of flight attendants who had worked on separate flight sectors on the same airplane. We investigated the cause of the outbreak and whether the illnesses were attributable to work on the airplane. Information was obtained from flight attendants on demographic characteristics, symptoms, and possible transmission risk factors. Case patients were defined as flight attendants with diarrhea or vomiting airplane during 13-18 October 2009. Stool samples were tested for norovirus RNA. A passenger had vomited on the Boeing 777-200 airplane on the 13 October flight sector. Sixty-three (82%) of 77 flight attendants who worked on the airplane during 13-18 October provided information, and 27 (43%) met the case definition. The attack rate among flight attendants decreased significantly over successive flight sectors from 13 October onward (P airplane during successive flight sectors. Airlines should make provision for adequate disinfection of airplanes with use of products effective against norovirus and other common infectious agents after vomiting has occurred.
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2010-11-19
....V. Model F.28 Mark 0100, 1000, 2000, 3000, and 4000 Airplanes AGENCY: Federal Aviation... Fokker Services B.V. Model F28 Mark 1000, 2000, 3000, and 4000 airplanes, all serial numbers, equipped... Instructions of Fokker Service Bulletin SBF28-28-052, dated April 20, 2010 (for Model F28 Mark 1000, 2000, 3000...
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14 CFR 125.355 - Airplane equipment.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane equipment. 125.355 Section 125.355...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Release Rules § 125.355 Airplane...
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Klinar, Walter J.; Healy, Frederick M.
1955-01-01
An investigation of a 0.034-scale model of the production version of the Chance Vought F7U-3 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The inverted and erect spin and recovery characteristics of the model were determined for the combat loading with the model in the clean condition and the effect of extending slats was investigated. A brief investigation of pilot ejection was also performed. The results indicate that the inverted spin-recovery characteristics of the airplane will be satisfactory by full rudder reversal. If the rudders can only be neutralized because of high pedal forces in the inverted spins, satisfactory recovery will be obtained if the auxiliary rudders can be moved to neutral or against the spin provided the stick is held full forward. Optimum control technique for satisfactory recovery from erect spins will be full rudder reversal in conjunction with aileron movement to full with the spin (stick right in a right spin). Extension of the slats will have a slightly adverse effect on recoveries from (1 inverted spins but will have a favorable effect on recoveries from erect spins. The results of brief tests indicate that if a pilot is ejected during a spin while a spin-recovery parachute is extended and fully inflated, he will probably clear the tail parachute.
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Driver, Cornelius
1956-01-01
Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined. The results indicate that for a horizontal-tail incidence of -10 deg the trim lift coefficient varied from 0.29 at a Mach number of 1.61 to 0.23 at a Mach number of 2.01 with a corresponding decrease in lift-drag trim from 3.72 to 3.15. Stick-position instability was indicated in the low-supersonic-speed range. A photographic-type nose modification resulted in slightly higher values of minimum drag coefficient but did not significantly affect the static stability or lift-curve slope. The minimum drag coefficient for the complete model with the production nose remained essentially constant at 0.047 throughout the Mach number range investigated.
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78 FR 78694 - Airworthiness Directives; Airbus Airplanes
2013-12-27
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... all Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD... certain check valves in the [[Page 78695
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DEFF Research Database (Denmark)
Pommergaard, Hans C; Burcharth, Jakob; Fischer, Anders
2013-01-01
Flatus is natural and an invariable consequence of digestion, however at times it creates problems of social character due to sound and odour. This problem may be more significant on commercial airplanes where many people are seated in limited space and where changes in volume of intestinal gases......, due to altered cabin pressure, increase the amount of potential flatus. Holding back flatus on an airplane may cause significant discomfort and physical symptoms, whereas releasing flatus potentially presents social complications. To avoid this problem we humbly propose that active charcoal should...... airplanes, by using a methane breath test or to alter the fibre content of airline meals in order to reduce its flatulent potential. We conclude that the use of active charcoal on airlines may improve flight comfort for all passengers....
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Airplane Upset Training Evaluation Report
Gawron, Valerie J.; Jones, Patricia M. (Technical Monitor)
2002-01-01
Airplane upset accidents are a leading factor in hull losses and fatalities. This study compared five types of airplane-upset training. Each group was composed of eight, non-military pilots flying in their probationary year for airlines operating in the United States. The first group, 'No aero / no upset,' was made up of pilots without any airplane upset training or aerobatic flight experience; the second group, 'Aero/no upset,' of pilots without any airplane-upset training but with aerobatic experience; the third group, 'No aero/upset,' of pilots who had received airplane-upset training in both ground school and in the simulator; the fourth group, 'Aero/upset,' received the same training as Group Three but in addition had aerobatic flight experience; and the fifth group, 'In-flight' received in-flight airplane upset training using an instrumented in-flight simulator. Recovery performance indicated that clearly training works - specifically, all 40 pilots recovered from the windshear upset. However few pilots were trained or understood the use of bank to change the direction of the lift vector to recover from nose high upsets. Further, very few thought of, or used differential thrust to recover from rudder or aileron induced roll upsets. In addition, recovery from icing-induced stalls was inadequate.
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Ostroff, A. J.; Hueschen, R. M.
1984-01-01
The ability of a pilot to reconfigure the control surfaces on an airplane after a failure, allowing the airplane to recover to a safe condition, becomes more difficult with increasing airplane complexity. Techniques are needed to stabilize and control the airplane immediately after a failure, allowing the pilot more time to make longer range decisions. This paper presents a baseline design of a discrete multivariable control law using four controls for the longitudinal channel of a B-737. Non-reconfigured and reconfigured control laws are then evaluated, both analytically and by means of a digital airplane simulation, for three individual control element failures (stabilizer, elevator, spoilers). The simulation results are used to evaluate the effectiveness of the control reconfiguration on tracking ability during the approach and landing phase of flight with severe windshear and turbulence disturbing the airplane dynamics.
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2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Aging airplane inspections and records reviews for multiengine airplanes certificated with nine or fewer passenger seats. 135.422 Section 135.422... Maintenance, and Alterations § 135.422 Aging airplane inspections and records reviews for multiengine...
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78 FR 7261 - Airworthiness Directives; Airbus Airplanes
2013-02-01
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A310-203 airplanes. This AD was prompted by a report of an analysis that demonstrated a...-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425...
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78 FR 65173 - Airworthiness Directives; Airbus Airplanes
2013-10-31
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that... Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this...
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78 FR 53640 - Airworthiness Directives; Airbus Airplanes
2013-08-30
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-200 Freighter series airplanes; Model A330-200 and - 300 series airplanes, and Model... of the forward or aft cargo door. To address this condition, Airbus issued four separate Alert...
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Optimal back-to-front airplane boarding
Bachmat, Eitan; Khachaturov, Vassilii; Kuperman, Ran
2013-06-01
The problem of finding an optimal back-to-front airplane boarding policy is explored, using a mathematical model that is related to the 1+1 polynuclear growth model with concave boundary conditions and to causal sets in gravity. We study all airplane configurations and boarding group sizes. Optimal boarding policies for various airplane configurations are presented. Detailed calculations are provided along with simulations that support the main conclusions of the theory. We show that the effectiveness of back-to-front policies undergoes a phase transition when passing from lightly congested airplanes to heavily congested airplanes. The phase transition also affects the nature of the optimal or near-optimal policies. Under what we consider to be realistic conditions, optimal back-to-front policies lead to a modest 8-12% improvement in boarding time over random (no policy) boarding, using two boarding groups. Having more than two groups is not effective.
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Optimal back-to-front airplane boarding.
Bachmat, Eitan; Khachaturov, Vassilii; Kuperman, Ran
2013-06-01
The problem of finding an optimal back-to-front airplane boarding policy is explored, using a mathematical model that is related to the 1+1 polynuclear growth model with concave boundary conditions and to causal sets in gravity. We study all airplane configurations and boarding group sizes. Optimal boarding policies for various airplane configurations are presented. Detailed calculations are provided along with simulations that support the main conclusions of the theory. We show that the effectiveness of back-to-front policies undergoes a phase transition when passing from lightly congested airplanes to heavily congested airplanes. The phase transition also affects the nature of the optimal or near-optimal policies. Under what we consider to be realistic conditions, optimal back-to-front policies lead to a modest 8-12% improvement in boarding time over random (no policy) boarding, using two boarding groups. Having more than two groups is not effective.
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The X-15 airplane - Lessons learned
Dana, William H.
1993-01-01
The X-15 rocket research airplane flew to an altitude of 354,000 ft and reached Mach 6.70. In almost 200 flights, this airplane was used to gather aerodynamic-heating, structural loads, stability and control, and atmospheric-reentry data. This paper describes the origins, design, and operation of the X-15 airplane. In addition, lessons learned from the X-15 airplane that are applicable to designing and testing the National Aero-Space Plane are discussed.
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78 FR 41280 - Airworthiness Directives; Airbus Airplanes
2013-07-10
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A319-112, -113, and -132 airplanes; Model A320-211, -212, -214, -231, and -232 airplanes... A319 aeroplane on which Airbus modification (mod.) 22058 had been embodied in production. Airbus mod...
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78 FR 31386 - Airworthiness Directives; Airbus Airplanes
2013-05-24
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...) for all Airbus Model A330-200 and -300 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. That AD currently requires a one-time detailed inspection of both main landing gear...
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78 FR 49915 - Airworthiness Directives; Airbus Airplanes
2013-08-16
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of..., for certain Airbus Model A310 series airplanes. AD 2004-15-07 required repetitive inspections for..., International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356...
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77 FR 76228 - Airworthiness Directives; Airbus Airplanes
2012-12-27
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-300 series airplanes and Model A340-200 and -300 series airplanes. This AD was prompted... operational test. This [EASA] AD also requires reporting operational test results to Airbus. You may obtain...
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77 FR 42952 - Airworthiness Directives; Airbus Airplanes
2012-07-23
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A318-112 and -121 airplanes; Model A319-111, -112, -115, - 132, and -133 airplanes; Model... MCAI states: During structural part assembly in Airbus production line, some nuts Part Number (P/N...
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78 FR 40074 - Airworthiness Directives; Airbus Airplanes
2013-07-03
...-0465; Directorate Identifier 2012-NM-085-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... series airplanes. This proposed AD was prompted by a determination that oxygen generators installed on a... information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on...
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78 FR 47537 - Airworthiness Directives; Airbus Airplanes
2013-08-06
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... all Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD... by application of Airbus modification 49590/Service Bulletin (SB) A330-27-3085 [or SB A340-27-4089...
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78 FR 8054 - Airworthiness Directives; Airbus Airplanes
2013-02-05
...-1321; Directorate Identifier 2011-NM-147-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... A310 series airplanes. The existing AD currently requires repetitive inspections for fatigue cracking... information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on...
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Design definition study of a lift/cruise fan technology V/STOL airplane: Summary
Zabinsky, J. M.; Higgins, H. C.
1975-01-01
A two-engine three-fan V/STOL airplane was designed to fulfill naval operational requirements. A multimission airplane was developed from study of specific point designs. Based on the multimission concept, airplanes were designed to demonstrate and develop the technology and operational procedures for this class of aircraft. Use of interconnected variable pitch fans led to a good balance between high thrust with responsive control and efficient thrust at cruise speeds. The airplanes and their characteristics are presented.
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78 FR 52414 - Airworthiness Directives; Airbus Airplanes
2013-08-23
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A320-214, -232 and -233 airplanes; and Model A321-211, - 213, and -231 airplanes. This AD... Service Information Airbus requested that we revise the NPRM (77 FR 63270, October 16, 2012) to reflect...
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14 CFR 121.141 - Airplane flight manual.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane flight manual. 121.141 Section 121... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Manual Requirements § 121.141 Airplane flight manual. (a) Each certificate holder shall keep a current approved airplane flight manual for each type of...
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76 FR 61555 - Airworthiness Directives; Airbus Airplanes
2011-10-05
... pieces unit welded, instead of 4 pieces unit with 3 welds (old design) as pictured in Appendix 1 of this... pre-modification 02447. Blue and Green. A300 airplanes post-modification 02447 Blue. A300-600 airplanes Blue. A310 airplanes Green. Table 2--Applicable Service Information Airbus Mandatory Service...
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78 FR 46543 - Airworthiness Directives; Airbus Airplanes
2013-08-01
...-0665; Directorate Identifier 2012-NM-082-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes...: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-300 series airplanes and Model A340-200 and -300 series airplanes. This proposed AD was prompted by reports of corrosion...
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2010-03-16
..., a wiring change, and corrective actions if necessary. This proposed AD results from fuel system... for doing a general visual inspection of the wire assembly installation of the tail tank fuel system to detect damage of the wire assembly, changing the wiring, and doing corrective actions. Corrective...
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1990-12-03
This is our final report on the audit of Subcontract Prices on Firm-Fixed-Price Contracts Awarded to McDonnell Aircraft Company (MCAIR). The Contract Management Directorate made the audit from October 1989 through June 1990. The objective of the audit was to compare proposed and negotiated subcontract prices and determine reasons for significant variances. We also evaluated applicable internal control procedures. For a 6-month period ending December 1989, MCAIR issued 517 subcontracts valued at $679 million.
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14 CFR 125.407 - Maintenance log: Airplanes.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Maintenance log: Airplanes. 125.407 Section... OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6... Maintenance log: Airplanes. (a) Each person who takes corrective action or defers action concerning a reported...
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78 FR 40057 - Airworthiness Directives; Airbus Airplanes
2013-07-03
...-0467; Directorate Identifier 2013-NM-023-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... A321 series airplanes. This proposed AD was prompted by reports of certain sliding windows that were... from safely evacuating the airplane during an emergency. DATES: We must receive comments on this...
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1995-01-01
This November 13, 1995, photograph of the underside of the F-15 Advanced Controls Technology for Integrated Vehicles (ACTIVE) at NASA's Dryden Flight Research Center, Edwards, California, shows the thrust stand being used for ground testing of a new thrust-vectoring concept. The twin-engine F-15 research aircraft is equipped with new Pratt & Whitney nozzles that can turn up to 20 degrees in any direction. They give the aircraft thrust control in the pitch (up and down) and yaw (left and right) directions. This will reduce drag and increase fuel economy or range as compared with conventional aerodynamic controls, which increase the retarding forces (drag) acting upon the aircraft. Ground testing during the first two weeks of November 1995 went well, and flight tests began in March 1996. These tests could result in significant performance increases for military and commercial aircraft. The research program is the product of a collaborative effort by NASA, the Air Force's Wright Laboratory, Pratt & Whitney, and McDonnell Douglas Aerospace.
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77 FR 65799 - Airworthiness Directives; Airbus Airplanes
2012-10-31
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-200 freighter series airplanes, Model A330-200 and - 300 series airplanes, and Model... [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new AD: 2012-21-20 Airbus: Amendment 39...
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14 CFR 125.91 - Airplane requirements: General.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane requirements: General. 125.91... AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements...
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GRAPHIC-ANALYTICAL METHODS FOR CALCULATING THE GRAVITY CENTER OF A MODEL AIRPLANE
DIACONESCU Olivian
2012-01-01
This paper presents a stage of the realization of an airplane capable to work with low capacity motors between 2.5 cmc and 4 cmc, as it presents the gravity center calculation. Firstly for an airplane to fly properly we must calculate the gravity center, the top speed which is necessary for picking the servomotors that equip the airplane.
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78 FR 69594 - Airworthiness Directives; Airbus Airplanes
2013-11-20
...-0972; Directorate Identifier 2002-NM-009-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... airworthiness directive (AD) for all Airbus Model A330 series airplanes. The NPRM would have required... rulemaking (NPRM) for a new AD for all Airbus Model A330 series airplanes. The NPRM, FAA Docket No. FAA-2013...
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CCNA routing and switching review guide exams 100-101, 200-101, and 200-120
Lammle, Todd
2013-01-01
Todd Lammle's focused, concise review guide, updated for the latest CCNA exams CCNA is one of the most sought after certifications for IT professionals. If you're preparing for the CCNA Routing and Switching certification, this Sybex review guide offers the best quick review available. Organized by exam objective, it's the perfect supplement to other learning tools, including the Sybex CCNA Routing and Switching Study Guide (ISBN: 9781118749616). All exam topics from exams 100-101, 200-101, and 200-120 are thoroughly covered, and additional study materials including bonus exams, electronic f
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78 FR 78294 - Airworthiness Directives; Airbus Airplanes
2013-12-26
...-1031; Directorate Identifier 2013-NM-155-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... 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...
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14 CFR 121.570 - Airplane evacuation capability.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane evacuation capability. 121.570... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Operations § 121.570 Airplane evacuation capability. (a) No person may cause an airplane carrying passengers to be moved on the surface, take off, or...
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2010-11-17
... installation of hardware. Boeing stated that the original NPRM implies that only wiring changes would be required; installation of brackets and supporting hardware, however, are required in addition to the wiring... tail tank fuel system, a wiring change, and corrective actions if necessary. That NPRM was prompted by...
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Spoilers for roll control of light airplanes
Roskam, J.; Kohlman, D. L.; Wentz, W. H.
1974-01-01
The paper presents an overview of the state-of-the-art of roll control spoilers for light airplanes. Reasons for using spoilers on light airplanes are presented. Several classical objections to the use of spoilers of such airplanes are critically examined. It is shown that mechanically driven spoiler systems can be designed. Flight test results of a new mechanically driven spoiler on the Redhawk airplane are discussed. Tunnel data of spoilers on the new general aviation airfoil GA(W)-1 are presented. Finally, a bibliography on spoiler data is included.
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A Collection of Nonlinear Aircraft Simulations in MATLAB
Garza, Frederico R.; Morelli, Eugene A.
2003-01-01
Nonlinear six degree-of-freedom simulations for a variety of aircraft were created using MATLAB. Data for aircraft geometry, aerodynamic characteristics, mass / inertia properties, and engine characteristics were obtained from open literature publications documenting wind tunnel experiments and flight tests. Each nonlinear simulation was implemented within a common framework in MATLAB, and includes an interface with another commercially-available program to read pilot inputs and produce a three-dimensional (3-D) display of the simulated airplane motion. Aircraft simulations include the General Dynamics F-16 Fighting Falcon, Convair F-106B Delta Dart, Grumman F-14 Tomcat, McDonnell Douglas F-4 Phantom, NASA Langley Free-Flying Aircraft for Sub-scale Experimental Research (FASER), NASA HL-20 Lifting Body, NASA / DARPA X-31 Enhanced Fighter Maneuverability Demonstrator, and the Vought A-7 Corsair II. All nonlinear simulations and 3-D displays run in real time in response to pilot inputs, using contemporary desktop personal computer hardware. The simulations can also be run in batch mode. Each nonlinear simulation includes the full nonlinear dynamics of the bare airframe, with a scaled direct connection from pilot inputs to control surface deflections to provide adequate pilot control. Since all the nonlinear simulations are implemented entirely in MATLAB, user-defined control laws can be added in a straightforward fashion, and the simulations are portable across various computing platforms. Routines for trim, linearization, and numerical integration are included. The general nonlinear simulation framework and the specifics for each particular aircraft are documented.
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14 CFR 121.605 - Airplane equipment.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane equipment. 121.605 Section 121.605..., FLAG, AND SUPPLEMENTAL OPERATIONS Dispatching and Flight Release Rules § 121.605 Airplane equipment. No person may dispatch or release an airplane unless it is airworthy and is equipped as prescribed in § 121...
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78 FR 40069 - Airworthiness Directives; Airbus Airplanes
2013-07-03
...-0539; Directorate Identifier 2012-NM-145-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... B4-600 and Model A300 B4-600R series airplanes. That AD currently requires repetitive inspections to... information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on...
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Paper Airplanes: A Classroom Activity
Painter, Richard A.
1976-01-01
A learning experience is described for upper elementary or junior high students involving the manufacture, transportation, and marketing of a product for consumers. Steps are given and roles are assigned for students to convert raw material (paper) to a finished product (paper airplanes) and to sell it. (AV)
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Airplane headache: a further case report of a young man.
Domitrz, Izabela
2010-12-01
Headache with normal examinations and imaging, occurring during an airplane flight has been rarely reported. We present a young patient with a new type of headache that appeared during flights: take-off and landing of a plane and was not associated with other conditions. This airplane headache is rather rare in population and the pathophysiology of this type is not clear. Secondary causes must be ruled out before the diagnosis of a primary headache is made.
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76 FR 1983 - Airworthiness Directives; The Boeing Company Model MD-11 and MD-11F Airplanes
2011-01-12
... assemblies of the tail tank fuel system, a wiring change, and corrective actions if necessary. This AD also requires, for certain airplanes, a general visual inspection for correct installation of the self-adhering high-temperature electrical insulation tape; installation of a wire assembly support bracket and...
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78 FR 72834 - Airworthiness Directives; SOCATA Airplanes
2013-12-04
... Airworthiness Directives; SOCATA Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... airworthiness directive (AD) for SOCATA Model TBM 700 airplanes. This proposed AD results from mandatory... review this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas...
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14 CFR 21.5 - Airplane or Rotorcraft Flight Manual.
2010-01-01
... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Airplane or Rotorcraft Flight Manual. 21.5... CERTIFICATION PROCEDURES FOR PRODUCTS AND PARTS General § 21.5 Airplane or Rotorcraft Flight Manual. (a) With each airplane or rotorcraft that was not type certificated with an Airplane or Rotorcraft Flight Manual...
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Perturbed Motion of Airplane and Safe Store Separation
S. C. Raisinghani; S. Rao
1983-01-01
A method is presented to predict the perturbed motion of an airplane following stores jettisoning. The mass, moment of inertia, forces, and moments acting on the airplane are suitable split into contributions from the stores and the rest of the airplane parts. The seperation of stores is assumed to result in a step change of mass, moment of intertai, forces, and moments contributed by stores. The resulting set of perturbed state equations of motion are solved for two illustrative airplane str...
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Headache associated with airplane travel: a rare entity.
Cherian, Ajith; Mathew, Mini; Iype, Thomas; Sandeep, P; Jabeen, Afshan; Ayyappan, K
2013-01-01
Airplane travel headache is rare and has recently been described as a new form of headache associated with a specific situation. Of the 1,208 patients with primary headaches attending a tertiary care neurology hospital, two (0.16%) patients satisfied the criteria for headache related to airplane travel. Both the patients fulfilled the proposed diagnostic criteria for airplane travel headache. This unique headache had a mean duration of 24 minutes, localized to the medial supraorbital region described as having an intense jabbing or stabbing character that occurred exclusively and maximally during aircraft landing or take-off, following which pain intensity subsided . This rare headache felt on aircraft descent is probably due to the squeeze effect on the frontal sinus wall, when air trapped inside it contracts producing a negative pressure leading to mucosal edema, transudation and intense pain. Use of nasal decongestants either alone or in combination with naproxen sodium prior to ascent and descent abated the headache episodes. Awareness about this unique entity is essential to provide proper treatment and avoid patient suffering.
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14 CFR 121.303 - Airplane instruments and equipment.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane instruments and equipment. 121.303... Airplane instruments and equipment. (a) Unless otherwise specified, the instrument and equipment... airspeed limitation and item of related information in the Airplane Flight Manual and pertinent placards...
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Ostroff, A. J.; Hueschen, R. M.
1984-01-01
The ability of a pilot to reconfigure the control surfaces on an airplane after a failure, allowing the airplane to recover to a safe condition for landing, becomes more difficult with increasing airplane complexity. Techniques are needed to stabilize and control the airplane immediately after a failure, allowing the pilot time to make longer range decisions. This paper shows a design of a discrete multivariable control law using four controls for the longitudinal channel of a B-737. Single control element failures are allowed in three of the four controls. The four controls design and failure cases are analyzed by means of a digital airplane simulation, with regard to tracking capability and ability to overcome severe windshear and turbulence during the aproach and landing phase of flight.
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Gupta, Krishna M; Zhang, Kang; Jiang, Jianwen
2015-08-05
A molecular simulation study is reported on glucose recovery from aqueous solutions by adsorption in metal-organic framework MIL-101. The F atom of MIL-101 is identified to be the most favorable adsorption site. Among three MIL-101-X (X = H, NH2 or CH3), the parent MIL-101 exhibits the highest adsorption capacity and recovery efficacy. Upon functionalization by -NH2 or -CH3 group, the steric hindrance in MIL-101 increases; consequently, the interactions between glucose and framework become less attractive, thus reducing the capacity and mobility of glucose. The presence of ionic liquid, 1-ethyl-3-methyl-imidazolium acetate, as an impurity reduces the strength of hydrogen-bonding between glucose and MIL-101, and leads to lower capacity and mobility. Upon adding anti-solvent (ethanol or acetone), a similar adverse effect is observed. The simulation study provides useful structural and dynamic properties of glucose in MIL-101, and it suggests that MIL-101 might be a potential candidate for glucose recovery.
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29 CFR 2520.101-4 - Annual funding notice for multiemployer defined benefit pension plans.
2010-07-01
... pension plans. 2520.101-4 Section 2520.101-4 Labor Regulations Relating to Labor (Continued) EMPLOYEE... pension plans. (a) In general. (1) Except as provided in paragraph (a)(2) of this section, pursuant to section 101(f) of the Act, the administrator of a defined benefit, multiemployer pension plan shall...
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Prospect of ultralight airplanes development
Directory of Open Access Journals (Sweden)
Adam KONICZEK
2015-09-01
Full Text Available The article presents characteristic of ultralight airplanes, rules and current interest of them. The purpose is to determine prospect of ultralight airplanes development on the basis of Civil Aviation Authority statistics analysis and trend of aviation market.
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14 CFR 121.1105 - Aging airplane inspections and records reviews.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Aging airplane inspections and records... Improvements § 121.1105 Aging airplane inspections and records reviews. (a) Applicability. This section applies to all airplanes operated by a certificate holder under this part, except for those airplanes...
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14 CFR 91.605 - Transport category civil airplane weight limitations.
2010-01-01
... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Transport category civil airplane weight... civil airplane weight limitations. (a) No person may take off any transport category airplane (other than a turbine-engine-powered airplane certificated after September 30, 1958) unless— (1) The takeoff...
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2010-06-01
... harnesses of the tail tank fuel transfer pumps, and to determine if damaged wires are present; and repair... installed on wire harnesses of the tail tank fuel transfer pumps, and to determine if damaged wires are... alternate fuel pump of the tail tank, the leak detection thermal switch grounding for the number 2 engine...
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78 FR 46536 - Airworthiness Directives; Airbus Airplanes
2013-08-01
...-0668; Directorate Identifier 2013-NM-017-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... B4-600R series airplanes. This proposed AD was prompted by reports of cracks found in the bottom wing... at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the...
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76 FR 7513 - Airworthiness Directives; The Boeing Company Model 747-400 and -400F Series Airplanes
2011-02-10
... drip shields. This proposed AD was prompted by a report of a loss of bus control unit number 1 and... of a loss of bus control unit number 1 and generator control units numbers 1 and 2 while the airplane.... We are issuing this AD to prevent water penetration into the MEC, which could result in the loss of...
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Polhamus, Edward C.; King, Thomas J., Jr.
1949-01-01
An investigation was made in the Langley high-speed 7- by 10-foot tunnel to determine the high-speed lateral and directional stability characteristics of a 0.10-scale model of the Grumman XF9F-2 airplane in the Mach number range from 0.40 to 0.85. The results indicate that static lateral and directional stability is present throughout the Mach number range investigated although in the Mach number range from 0.75 to 0.85 there is an appreciable decrease in rolling moment due to sideslip. Calculations of the dynamic stability indicate that according to current flying-quality requirements the damping of the lateral oscillation, although probably satisfactory for the sea-level condition, may not be satisfactory for the majority of the altitude conditions investigated
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Gupta, Krishna M.; Zhang, Kang; Jiang, Jianwen
2015-01-01
A molecular simulation study is reported on glucose recovery from aqueous solutions by adsorption in metal-organic framework MIL-101. The F atom of MIL-101 is identified to be the most favorable adsorption site. Among three MIL-101-X (X = H, NH2 or CH3), the parent MIL-101 exhibits the highest adsorption capacity and recovery efficacy. Upon functionalization by -NH2 or -CH3 group, the steric hindrance in MIL-101 increases; consequently, the interactions between glucose and framework become less attractive, thus reducing the capacity and mobility of glucose. The presence of ionic liquid, 1-ethyl-3-methyl-imidazolium acetate, as an impurity reduces the strength of hydrogen-bonding between glucose and MIL-101, and leads to lower capacity and mobility. Upon adding anti-solvent (ethanol or acetone), a similar adverse effect is observed. The simulation study provides useful structural and dynamic properties of glucose in MIL-101, and it suggests that MIL-101 might be a potential candidate for glucose recovery. PMID:26242874
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Modeling the Aerodynamics and Performances of a Historic Airplane: the Spanish
Directory of Open Access Journals (Sweden)
A. González-Betes
2003-01-01
Full Text Available The process of modeling the aerodynamics and performances of a historic airplane is very similar to the conceptual and preliminary design phases of a new plane, with the advantage of knowing the configuration and that the airplane was airworthy; thus it is unnecessary to outline and assess many different alternatives. However, the drag polar, the real performances, stability features, etc, are still unknown. For various reasons (in particular because of two World Wars, or the Civil War in the Spanish case most details of many historical airplanes have been lost.In the present research work, the situation is as follows. In June 1933 the "Cuatro Vientos", a Spanish-built Bréguet XIX Super TR, flew non-stop from Seville to Cuba; a distance of 7500 km (about 4100 nautical miles in around 40 hours. A few days later, in a far less complicated stage between Havana and Mexico, the airplane was lost with its occupants to a storm in the Yucatan peninsula.The modeling considered in this paper starts by addressing the aerodynamic modifications introduced in the airplane for the extremely long flight. Then, with the help of old and present day aerodynamic data and methods the drag polar is estimated. The available engine data is completed and extrapolated to obtain information on power and fuel consumption. Finally, all this data is integrated to provide a reliable and technically sound reproduction of the Seville-Cuba flight.
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14 CFR 121.161 - Airplane limitations: Type of route.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane limitations: Type of route. 121... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Aircraft Requirements § 121.161 Airplane... specifications, no certificate holder may operate a turbine-engine-powered airplane over a route that contains a...
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2010-02-04
... AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H... a magnetic particle inspection (MPI) in accordance with Part 4, ``Magnetic Particle Inspection of... November 5, 2009, or MPI in accordance with Part 4, ``Magnetic Particle Inspection of the Midspar Fuse Pin...
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A digital fly-by-wire technology development program using an F-8C test aircraft
Jarvis, C. R.
1974-01-01
A digital fly-by-wire flight control system has been installed in an F-8C test airplane and has undergone extensive ground and flight testing as part of an overall program to develop digital fly-by-wire technology. This is the first airplane to fly with a digital fly-by-wire system as its primary means of control and with no mechanical reversion capability. Forty-two test flights were made for a total flight time of 57 hours. Six pilots participated in the evaluation. This paper presents an overview of the digital fly-by-wire program and discusses some of the flight-test results.
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Sieradzki Adam; Dziubiński Adam; Galiński Cezary
2016-01-01
The joined wing concept is an unconventional airplane configuration, known since the mid-twenties of the last century. It has several possible advantages, like reduction of the induced drag and weight due to the closed wing concept. The inverted joined wing variant is its rarely considered version, with the front wing being situated above the aft wing. The following paper presents a performance prediction of the recently optimized configuration of this airplane. Flight characteristics obtaine...
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14 CFR 121.503 - Flight time limitations: Pilots: airplanes.
2010-01-01
... Operations § 121.503 Flight time limitations: Pilots: airplanes. (a) A certificate holder conducting supplemental operations may schedule a pilot to fly in an airplane for eight hours or less during any 24... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Flight time limitations: Pilots: airplanes...
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Assessment of community noise for a medium-range airplane with open-rotor engines
Kopiev, V. F.; Shur, M. L.; Travin, A. K.; Belyaev, I. V.; Zamtfort, B. S.; Medvedev, Yu. V.
2017-11-01
Community noise of a hypothetical medium-range airplane equipped with open-rotor engines is assessed by numerical modeling of the aeroacoustic characteristics of an isolated open rotor with the simplest blade geometry. Various open-rotor configurations are considered at constant thrust, and the lowest-noise configuration is selected. A two-engine medium-range airplane at known thrust of bypass turbofan engines at different segments of the takeoff-landing trajectory is considered, after the replacement of those engines by the open-rotor engines. It is established that a medium-range airplane with two open-rotor engines meets the requirements of Chapter 4 of the ICAO standard with a significant margin. It is shown that airframe noise makes a significant contribution to the total noise of an airplane with open-rotor engines at landing.
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76 FR 77157 - Airworthiness Directives; The Boeing Company Airplanes
2011-12-12
... airplane. A separated T/R piece could result in a rejected takeoff (RTO) and cause asymmetric thrust and... cause structural damage to the airplane, damage to other airplanes, or injury to people on the ground... be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Rebel Nichols...
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14 CFR 23.71 - Glide: Single-engine airplanes.
2010-01-01
... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Glide: Single-engine airplanes. 23.71... AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES Flight Performance § 23.71 Glide: Single-engine airplanes. The maximum horizontal distance traveled in still air, in nautical miles...
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77 FR 57529 - Airworthiness Directives; The Boeing Company Airplanes
2012-09-18
... 737-600, -700, -700C, -800, -900, or -900ER series airplanes, a full-scale fatigue test article was... Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM...-800 series airplanes. This proposed AD was prompted by reports of early fatigue cracks at chem- mill...
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77 FR 57541 - Airworthiness Directives; The Boeing Company Airplanes
2012-09-18
... 737-600, -700, -700C, -800, -900, or -900ER series airplanes, a full-scale fatigue test article was... Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM...-600 series airplanes. This proposed AD was prompted by reports of early fatigue cracks at chem- mill...
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77 FR 57536 - Airworthiness Directives; The Boeing Company Airplanes
2012-09-18
... -900ER series airplanes, a full-scale fatigue test article was inspected for skin cracks at similar... Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM...-700 and -700C series airplanes. This proposed AD was prompted by reports of early fatigue cracks at...
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Differential equations in airplane mechanics
Carleman, M T
1922-01-01
In the following report, we will first draw some conclusions of purely theoretical interest, from the general equations of motion. At the end, we will consider the motion of an airplane, with the engine dead and with the assumption that the angle of attack remains constant. Thus we arrive at a simple result, which can be rendered practically utilizable for determining the trajectory of an airplane descending at a constant steering angle.
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14 CFR 61.159 - Aeronautical experience: Airplane category rating.
2010-01-01
... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Aeronautical experience: Airplane category... Transport Pilots § 61.159 Aeronautical experience: Airplane category rating. (a) Except as provided in... certificate with an airplane category and class rating must have at least 1,500 hours of total time as a pilot...
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75 FR 35 - Special Conditions: Airbus Model A318-112 Airplane (S/N 3886); Certification of a Cooktop
2010-01-04
... Recommended Practice 85, Rev. E, article titled, ``Air Conditioning Systems for Subsonic Airplanes,'' August 1...; Special Conditions No. 25-398-SC] Special Conditions: Airbus Model A318-112 Airplane (S/N 3886... airplane, as modified by Bizjet, a Lufthansa Technik Company, will have a novel or unusual design feature...
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77 FR 57539 - Airworthiness Directives; The Boeing Company Airplanes
2012-09-18
... 737-600, -700, -700C, -800, -900, or -900ER series airplanes, a full-scale fatigue test article was... Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM...-900 and -900ER series airplanes. This proposed AD was prompted by reports of early fatigue cracks at...
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2011-05-26
... comments were received from one commenter. Concerns With the Philosophy of Controlling Aeroelastic... reservations with the philosophy of controlling an aeroelastic instability (flutter) with an active control... throughout the service life of the airplane by: (i) Analysis to the nominal aeroelastic stability envelope...
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78 FR 51058 - Airworthiness Directives; Airbus Airplanes
2013-08-20
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... certain Airbus Model A319 and A320 series airplanes. AD 2004-13-06 required repetitive detailed... and to allow extension of the interval between two consecutive inspections, Airbus validated an Eddy...
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77 FR 7523 - Airworthiness Directives; Airbus Airplanes
2012-02-13
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... directive (AD) for all Airbus Model A340-600 series airplanes. This AD requires modifying the fire.... Relevant Service Information Airbus has issued Mandatory Service Bulletin A340-26-5020, including Appendix...
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75 FR 10696 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes
2010-03-09
... revealed that, due to their position on the aircraft, ice may form on actuators P/N 9409122 installed on... replacing the valve actuator with a serviceable part is in the Fokker 70/100 Aircraft Maintenance Manual... airplane, fuel fire shut-off valve actuators P/N [part number] 9409122 are susceptible to freezing, which...
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78 FR 21230 - Airworthiness Directives; Airbus Airplanes
2013-04-10
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by fuel system reviews conducted..., Airbus developed a modification which includes installing Ground Fault Interrupters (GFI) into the centre...
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Simple Electromagnetic Modeling of Small Airplanes: Neural Network Approach
Directory of Open Access Journals (Sweden)
P. Tobola
2009-04-01
Full Text Available The paper deals with the development of simple electromagnetic models of small airplanes, which can contain composite materials in their construction. Electromagnetic waves can penetrate through the surface of the aircraft due to the specific electromagnetic properties of the composite materials, which can increase the intensity of fields inside the airplane and can negatively influence the functionality of the sensitive avionics. The airplane is simulated by two parallel dielectric layers (the left-hand side wall and the right-hand side wall of the airplane. The layers are put into a rectangular metallic waveguide terminated by the absorber in order to simulate the illumination of the airplane by the external wave (both of the harmonic nature and pulse one. Thanks to the simplicity of the model, the parametric analysis can be performed, and the results can be used in order to train an artificial neural network. The trained networks excel in further reduction of CPU-time demands of an airplane modeling.
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A controls engineering approach for analyzing airplane input-output characteristics
Arbuckle, P. Douglas
1991-01-01
An engineering approach for analyzing airplane control and output characteristics is presented. State-space matrix equations describing the linear perturbation dynamics are transformed from physical coordinates into scaled coordinates. The scaling is accomplished by applying various transformations to the system to employ prior engineering knowledge of the airplane physics. Two different analysis techniques are then explained. Modal analysis techniques calculate the influence of each system input on each fundamental mode of motion and the distribution of each mode among the system outputs. The optimal steady state response technique computes the blending of steady state control inputs that optimize the steady state response of selected system outputs. Analysis of an example airplane model is presented to demonstrate the described engineering approach.
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77 FR 19067 - Airworthiness Directives; Airbus Airplanes
2012-03-30
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... directive (AD) for certain Airbus Model A321-131, -211, -212, and -231 airplanes. This AD requires a.... Relevant Service Information Airbus has issued Mandatory Service Bulletin A320-57-1120, Revision 01...
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Headache Attributed to Airplane Travel: A Review of Literature.
Nierenburg, Hida; Jackfert, Katelin
2018-06-14
Headaches due to airplane travel are rare but documented in the literature. We aim to provide a review of diagnostic criteria and treatment for this condition. Several cases of this syndrome have been reported since it was first described in 2004. Airplane headache is classified as unilateral, stabbing, orbito-frontal pain, lasting under 30 min, and occurs during ascent or descent of a plane. Patients with this condition can develop anxiety and fear of flying given the intensity and severity of the pain. The pathophysiology of this syndrome is unknown, but theories include suspected barotrauma given changes in barometric pressure during ascent and descent. There are no randomized controlled trials regarding treatment, but case reports suggest headache prevention with pre-treatment with naproxen, decongestants, and triptans prior to air travel. Some non-pharmacological therapies reported include Valsalva maneuvers, chewing, relaxation techniques, and pressure at the pain area. As more cases of headache attributed to airplane travel are reported, epidemiological data can be obtained to further understand the incidence and prevalence of this condition, which can lead to improved treatment options for patients.
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Headache during airplane travel ("airplane headache"): first case in Greece.
Kararizou, Evangelia; Anagnostou, Evangelos; Paraskevas, George P; Vassilopoulou, Sofia D; Naoumis, Dimitrios; Kararizos, Grigoris; Spengos, Konstantinos
2011-08-01
Headache related to airplane flights is rare. We describe a 37-year-old female patient with multiple intense, jabbing headache episodes over the last 3 years that occur exclusively during airplane flights. The pain manifests during take-off and landing, and is located always in the left retro-orbital and frontotemporal area. It is occasionally accompanied by dizziness, but no additional symptoms occur. Pain intensity diminishes and disappears after 15-20 min. Apart from occasional dizziness, no other symptoms occur. The patient has a history of tension-type headache and polycystic ovaries. Blood tests and imaging revealed no abnormalities. Here, we present the first case in Greece. We review the current literature on this rare syndrome and discuss on possible pathophysiology and the investigation of possible co-factors such as anxiety and depression.
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Fuzzy Logic Decoupled Lateral Control for General Aviation Airplanes
Duerksen, Noel
1997-01-01
It has been hypothesized that a human pilot uses the same set of generic skills to control a wide variety of aircraft. If this is true, then it should be possible to construct an electronic controller which embodies this generic skill set such that it can successfully control different airplanes without being matched to a specific airplane. In an attempt to create such a system, a fuzzy logic controller was devised to control aileron or roll spoiler position. This controller was used to control bank angle for both a piston powered single engine aileron equipped airplane simulation and a business jet simulation which used spoilers for primary roll control. Overspeed, stall and overbank protection were incorporated in the form of expert systems supervisors and weighted fuzzy rules. It was found that by using the artificial intelligence techniques of fuzzy logic and expert systems, a generic lateral controller could be successfully used on two general aviation aircraft types that have very different characteristics. These controllers worked for both airplanes over their entire flight envelopes. The controllers for both airplanes were identical except for airplane specific limits (maximum allowable airspeed, throttle ]ever travel, etc.). This research validated the fact that the same fuzzy logic based controller can control two very different general aviation airplanes. It also developed the basic controller architecture and specific control parameters required for such a general controller.
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78 FR 54377 - Airworthiness Directives; Airbus Airplanes
2013-09-04
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports that certain... accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27- 1214, including Appendix...
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78 FR 64162 - Airworthiness Directives; Airbus Airplanes
2013-10-28
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that...., Washington, DC. For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1...
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77 FR 19065 - Airworthiness Directives; Airbus Airplanes
2012-03-30
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... directive (AD) for all Airbus Model A340-600 series airplanes. This AD requires a detailed inspection for.... Relevant Service Information Airbus has issued All Operators Telex A340-25A5191, dated January 18, 2011...
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76 FR 50405 - Airworthiness Directives; SOCATA Airplanes
2011-08-15
...) 329-4148. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane...; e-mail: albert.mercado@faa.gov . SUPPLEMENTARY INFORMATION: Discussion We issued a notice of... information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301...
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78 FR 17071 - Airworthiness Directives; Airbus Airplanes
2013-03-20
... Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -300, and -200 Freighter series airplanes; and all Airbus Model A340-200 and -300 series...
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2010-07-01
... 41 Public Contracts and Property Management 2 2010-07-01 2010-07-01 true General. 101-27.101 Section 101-27.101 Public Contracts and Property Management Federal Property Management Regulations System FEDERAL PROPERTY MANAGEMENT REGULATIONS SUPPLY AND PROCUREMENT 27-INVENTORY MANAGEMENT 27.1-Stock...
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78 FR 60667 - Airworthiness Directives; Airbus Airplanes
2013-10-02
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2012- 26-51 required revising the...''), to correct an unsafe condition for the specified products. The MCAI states: Recently, an Airbus A330...
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Flying spin qualities testing of airplane
Directory of Open Access Journals (Sweden)
Kostić Čedomir J.
2015-01-01
Full Text Available In this paper is presented the theoretical analysis of origins and characteristics of spinning motion. There are precise explanation of every stage spin flight and basic meaning of notion. Personated equation of motion in spin and equitation of motion airplane in settled spin motion, analysis of them and general recommendation for pilots for recovering from spins. Introduced in valid military and civil specifications flight test demonstration requirements for departure resistance and flying stall and spin qualities testing of airplane. Special attention was given on predicting departure, stall and spin susceptibility and theoretical analysis in the name of magnify flight testing security. There are explanation of test equipment and methodology of flying qualities testing of airplanes. Like a support of this theme are described method and results of flight stall and spin qualities testing of airplane G-4(N-62 super see-gull with precise recommendation for pilots for recovering from spins, from TOC SLI VS (Technical testing center, department for fight testing Air Force of Serbia.
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78 FR 79292 - Airworthiness Directives; Airbus Airplanes
2013-12-30
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... directive (AD) 2011-24-09 which applied to certain Airbus Model A340-200 and A340-300 series airplanes. AD... AD, contact Airbus SAS-- Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac...
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77 FR 65808 - Airworthiness Directives; Airbus Airplanes
2012-10-31
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A320-214 and -232 airplanes. This AD was prompted by reports that medium-head fasteners were... installation of upper panels on Frame 35 in Airbus A320 final assembly line. Investigations revealed that...
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77 FR 19059 - Airworthiness Directives; Airbus Airplanes
2012-03-30
... Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... all Airbus Model A340-500 and Model -600 series airplanes. This AD requires performing repetitive high... Airbus has issued Mandatory Service Bulletin A340-57-5029, including Appendices 01 and 02, dated February...
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78 FR 52405 - Airworthiness Directives; Airbus Airplanes
2013-08-23
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-300, A340-200, and A340-300 series airplanes. This AD was prompted by a determination... Airbus: Amendment 39-17549. Docket No. FAA-2013-0335; Directorate Identifier 2012-NM-187-AD. [[Page 52407...
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2010-01-07
... the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs... maintenance program by incorporating new airworthiness limitations (AWLs) for fuel tank systems to satisfy... and on-airplane fuel tank system components. This AD results from a design review of the fuel tank...
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Measured Engine Installation Effects of Four Civil Transport Airplanes
Senzig, David A.; Fleming, Gregg G.; Shepherd, Kevin P.
2001-01-01
The Federal Aviation Administration's Integrated Noise Model (INM) is one of the primary tools for land use planning around airports. The INM currently calculates airplane noise lateral attenuation using the methods contained in the Society of Automotive Engineer's Aerospace Information Report No. 1751 (SAE AIR 1751). Researchers have noted that improved lateral attenuation algorithms may improve airplane noise prediction. The authors of SAE AIR 1751 based existing methods on empirical data collected from flight tests using 1960s-technology airplanes with tail-mounted engines. To determine whether the SAE AIR 1751 methods are applicable for predicting the engine installation component of lateral attenuation for airplanes with wing-mounted engines, the National Aeronautics and Space Administration (NASA) sponsored a series of flight tests during September 2000 at their Wallops Flight Facility. Four airplanes, a Boeing 767-400, a Douglas DC-9, a Dassault Falcon 2000, and a Beech KingAir, were flown through a 20 microphone array. The airplanes were flown through the array at various power settings, flap settings, and altitudes to simulate take-off and arrival configurations. This paper presents the preliminary findings of this study.
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76 FR 70042 - Airworthiness Directives; Pacific Aerospace Limited Airplanes
2011-11-10
... Airworthiness Directives; Pacific Aerospace Limited Airplanes AGENCY: Federal Aviation Administration (FAA... directive (AD) for Pacific Aerospace Limited Model FU24 Airplanes. This AD results from mandatory continuing... Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri...
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78 FR 21227 - Airworthiness Directives; Airbus Airplanes
2013-04-10
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-200, A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes; and Model... that, due to similar design, the enhanced MLG bogie pivot pin (Airbus modification 54500) could also be...
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78 FR 19085 - Airworthiness Directives; Airbus Airplanes
2013-03-29
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of oil residue... (MCAI) states: During Airbus Final Assembly Line flight tests, AoA [angle of attack] data from two...
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78 FR 14647 - Airworthiness Directives; Airbus Airplanes
2013-03-07
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... (AD) for certain Airbus Model A310-204, -222, -304, -322, and -324 airplanes. This AD was prompted by... the Airbus A310 Airworthiness Limitation Section (ALS) Part 1 and bolts must be replaced at or before...
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Modeling of terminal-area airplane fuel consumption
2009-08-01
Accurate modeling of airplane fuel consumption is necessary for air transportation policy-makers to properly : adjudicate trades between competing environmental and economic demands. Existing public models used for : computing terminal-area airplane ...
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77 FR 75825 - Airworthiness Directives; Airbus Airplanes
2012-12-26
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A330-200 and -300 series airplanes. This AD was prompted by a report of a prematurely... [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new AD: 2012-25-12 Airbus: Amendment 39...
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78 FR 64156 - Airworthiness Directives; Airbus Airplanes
2013-10-28
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... directive (AD) for all Airbus Model A340-211 -212, -213, -311, -312, -313, -541, and -642 airplanes. This AD... information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice...
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Building concepts against airplane crash
International Nuclear Information System (INIS)
Henkel, F.O.; Woelfel, H.
1984-01-01
In Germany safety related buildings of nuclear facilities as well as their equipment are to be designed against airplane crash. While the safety of the structure itself can always be guaranteed by structural means, the induced vibrations may cause severe problems for the equipment. Considerable effort was expended in recent years to comprehend the load case airplane crash in a more exact manner and to evaluate reasonable floor response spectra. Besides this analytical effort, investigations are cited to minimize the induced vibrations by new structural concepts. The present paper gives a survey concerning the development of structural concepts, culminating in the double shell structures that are state of the art today. Then the idea of spring supports, as it is known for the aseismic foundation of buildings, is further developed to a new spring concept which reduces the induced vibrations in an optimum way in the load case airplane crash and which additionally isolates earthquake vibrations. (orig.)
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78 FR 71996 - Airworthiness Directives; Airbus Airplanes
2013-12-02
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A318-112, A319-111, A319-112, A319-115, A319-132, and A319-133 airplanes. This AD was... developing this AD. We have considered the comments received. Request To Refer to Revised EASA AD Airbus...
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14 CFR 129.25 - Airplane security.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane security. 129.25 Section 129.25 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIR CARRIERS... AND FOREIGN OPERATORS OF U.S.-REGISTERED AIRCRAFT ENGAGED IN COMMON CARRIAGE General § 129.25 Airplane...
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77 FR 57003 - Airworthiness Directives; Airbus Airplanes
2012-09-17
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by a report of a torn out.... The FAA amends Sec. 39.13 by adding the following new AD: 2012-18-12 Airbus: Amendment 39-17189...
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78 FR 60798 - Airworthiness Directives; Airbus Airplanes
2013-10-02
...-0363; Directorate Identifier 2013-NM-031-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... directive (AD) for all Airbus Model A330-200, -300 and -200 Freighter series airplanes, and Model A340-200... information identified in this proposed AD, contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point...
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77 FR 19071 - Airworthiness Directives; Airbus Airplanes
2012-03-30
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... directive (AD) for certain Airbus Model A330-200, A330-300, A340-500, and A340-600 series airplanes. This AD...: During structural part assembly in Airbus production line, some nuts Part Number (P/N) ASNA2531-4 were...
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77 FR 65812 - Airworthiness Directives; Airbus Airplanes
2012-10-31
... airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by reports of ram air turbine... before delivery from production, an A330 aeroplane experienced a RAT [ram air turbine] pump failure, as a result of which, the green hydraulic system could not be fully pressurized. Investigations concluded that...
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Error Analysis of Determining Airplane Location by Global Positioning System
Hajiyev, Chingiz; Burat, Alper
1999-01-01
This paper studies the error analysis of determining airplane location by global positioning system (GPS) using statistical testing method. The Newton Rhapson method positions the airplane at the intersection point of four spheres. Absolute errors, relative errors and standard deviation have been calculated The results show that the positioning error of the airplane varies with the coordinates of GPS satellite and the airplane.
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78 FR 37437 - Airworthiness Directives; Airbus Airplanes
2013-06-21
... Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... Airbus Model A318, A319, A320, and A321 series airplanes. That AD currently requires one-time and... affected by AOT A320-55-1039 and Airbus SB A320-55-1035, A320-55- 1036 and A320-55-1037 which were not...
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1986-01-01
The airplane pictured is the new Air Shark I, a four-place amphibian that makes extensive use of composite materials and cruises at close to 200 miles per hour under power from a 200-horsepower engine. Air Shark I is a "homebuilt" airplane, assembled from a kit of parts and components furnished by Freedom Master Corporation, Satellite Beach, Florida. The airplane incorporates considerable NASA technology and its construction benefited from research assistance provided by Kennedy Space Center (KSC) In designing the Shark, company president Arthur M. Lueck was able to draw on NASA's aeronautical technology bank through KSC's computerized "recon" library. As a result of his work at KSC, the wing of the Air Shark I is a new airfoil developed by Langley Research Center for light aircraft. In addition, Lueck opted for NASA-developed "winglets," vertical extensions of the wing that reduce drag by smoothing air turbulence at the wingtips. The NASA technology bank also contributed to the hull design. Lueck is considering application of NASA laminar flow technology-means of smoothing the airflow over wing and fuselage-to later models for further improvement of the Shark's aerodynamic efficiency. A materials engineer, Lueck employed his own expertise in designing and selecting the materials for the composite segments, which include all structural members, exposed surfaces and many control components. The materials are fiber reinforced plastics, or FRP They offer a high strength-to-weight ratio, with a nominal strength rating about one and a half times that of structural steel. They provide other advantages: the materials can be easily molded into finished shapes without expensive tooling or machining, and they are highly corrosion resistant. The first homebuilt to be offered by Freedom Master, Air Shark I completed air and water testing in mid-1985 and the company launched production of kits.
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Bowman, James S., Jr.
1958-01-01
A supplementary investigation has been conducted in the langley 20-foot free-spinning tunnel on a l/24-scale model of the Grumman F11F-1 airplane to determine the spin and recovery characteristics with alternate nose configurations, the production version and the elongated APS-67 version, with and without empty and full wing tanks. When spins were obtained with either alternate nose configuration, they were oscillatory and recovery characteristics were considered unsatisfactory on the basis of the fact that very slow recoveries were indicated to be possible. The simultaneous extension of canards near the nose of the model with rudder reversal was effective in rapidly terminating the spin. The addition of empty wing tanks had little effect on the developed spin and recovery characteristics. The model did not spin erect with full wing tanks. For optimum recovery from inverted spins, the rudder should be reversed to 22O against the spin and simultaneously the flaperons should be moved with the developed spin; the stick should be held at or moved to full forward longitudinally. The minimum size parachute required to insure satisfactory recoveries in an emergency was found to be 12 feet in diameter (laid out flat) with a drag coefficient of 0.64 (based on the laid-out-flat diameter) and a towline length of 32 feet.
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77 FR 75833 - Airworthiness Directives; Airbus Airplanes
2012-12-26
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...) for certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and Model A300 B4-601, B4-603, B4... accordance with Airbus SB A300-57-6053 (Mod. 10453). Therefore and pending completion of the full analysis...
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Performance of a Fuel-Cell-Powered, Small Electric Airplane Assessed
Berton, Jeffrey J.
2004-01-01
Rapidly emerging fuel-cell-power technologies may be used to launch a new revolution of electric propulsion systems for light aircraft. Future small electric airplanes using fuel cell technologies hold the promise of high reliability, low maintenance, low noise, and - with the exception of water vapor - zero emissions. An analytical feasibility and performance assessment was conducted by NASA Glenn Research Center's Airbreathing Systems Analysis Office of a fuel-cell-powered, propeller-driven, small electric airplane based on a model of the MCR-01 two-place kitplane (Dyn'Aero, Darois, France). This assessment was conducted in parallel with an ongoing effort by the Advanced Technology Products Corporation and the Foundation for Advancing Science and Technology Education. Their project - partially funded by a NASA grant - is to design, build, and fly the first manned, continuously propelled, nongliding electric airplane. In our study, an analytical performance model of a proton exchange membrane (PEM) fuel cell propulsion system was developed and applied to a notional, two-place light airplane modeled after the MCR-01 kitplane. The PEM fuel cell stack was fed pure hydrogen fuel and humidified ambient air via a small automotive centrifugal supercharger. The fuel cell performance models were based on chemical reaction analyses calibrated with published data from the fledgling U.S. automotive fuel cell industry. Electric propeller motors, rated at two shaft power levels in separate assessments, were used to directly drive a two-bladed, variable-pitch propeller. Fuel sources considered were compressed hydrogen gas and cryogenic liquid hydrogen. Both of these fuel sources provided pure, contaminant-free hydrogen for the PEM cells.
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Structural concepts and experimental considerations for a versatile high-speed research airplane
Jackson, L. R.; Kirkham, F. S.; Weidner, J. P.
1978-01-01
Future aircraft may be hydrogen fueled and fly at hypersonic speeds. The resulting environments will require new structural concepts to satisfy performance goals. Large representative structures will have to be flight tested prior to commitment to a costly vehicle fleet. To perform flight tests, a versatile, economical, high-speed research airplane is defined. Results of this study including experimental considerations for a hypersonic research airplane are reported.
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14 CFR 135.397 - Small transport category airplane performance operating limitations.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Small transport category airplane... PERSONS ON BOARD SUCH AIRCRAFT Airplane Performance Operating Limitations § 135.397 Small transport category airplane performance operating limitations. (a) No person may operate a reciprocating engine...
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77 FR 51717 - Airworthiness Directives; Airbus Airplanes
2012-08-27
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... applies to certain Airbus Model A300 B4-2C, B4-103, and B4- 203 airplanes; and Model A300 B4-601, B4-603... information identified in this proposed AD, contact Airbus SAS--EAW (Airworthiness Office), 1 Rond Point...
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Follow-On Studies for Design Definition of a Lift/Cruise Fan Technology V/STOL Airplane, Volume 1
1977-01-01
A three engine, three fan V/STOL airplane was designed for use as a Research Technology Airplane in proof-of-concept of a candidate configuration for use as a Navy multimission airplane. Use of mechanically interconnected variable pitch fans is made to accommodate power transfer for flight control in hover and to provide flight capability in the event of a single engine failure. The airplane is a modification of a T-39A transport. Design definition is provided for high risk propulsion components and a development test program is defined.
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Planetary Airplane Extraction System Development and Subscale Testing
Teter, John E., Jr.
2006-01-01
The Aerial Regional-scale Environmental Survey (ARES) project will employ an airplane as the science platform from which to collect science data in the previously inaccessible, thin atmosphere of Mars. In order for the airplane to arrive safely in the Martian atmosphere, a number of sequences must occur. A critical element in the entry sequence at Mars is an extraction maneuver to separate the airplane quickly (in less than a second) from its protective backshell to reduce the possibility of re-contact, potentially leading to mission failure. This paper describes the development, testing, and lessons learned from building a 1/3 scale model of this airplane extraction system. This design, based on the successful Mars Exploration Rover (MER) extraction mechanism, employs a series of trucks rolling along tracks located on the surface of the central parachute can. Numerous tests using high speed video were conducted at the Langley Research Center to validate this concept. One area of concern was that that although the airplane released cleanly, a pitching moment could be introduced. While targeted for a Mars mission, this concept will enable environmental surveys by aircraft in other planetary bodies with a sensible atmosphere such as Venus or Saturn's moon, Titan.
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14 CFR 135.399 - Small nontransport category airplane performance operating limitations.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Small nontransport category airplane... PERSONS ON BOARD SUCH AIRCRAFT Airplane Performance Operating Limitations § 135.399 Small nontransport category airplane performance operating limitations. (a) No person may operate a reciprocating engine or...
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Prospect of atomic airplane and mini-reactor
International Nuclear Information System (INIS)
Shi Lei; Li Jinying; Ji Cunxing; Ma Huirou; Hou Yanli; Duan Zhihui
2012-01-01
History of R and D of atomic airplane was reviewed. inclusive of problem and actuality, principle and attaching. Prospect of R and D of atomic airplane in China is described extensively. Some suggestions to the government and establishments were made as well. (authors)
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77 FR 26937 - Airworthiness Directives; Airbus Airplanes
2012-05-08
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...) for certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes; and Model... Airbus Service Bulletins (SB) A300-57-0235 and A300-57-6088 * * *. Subsequently, new cases of cracks were...
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41 CFR 101-30.101-8 - Conversion.
2010-07-01
... classifications, stock numbers, names, and identification data to using those of the Federal Catalog System in all... 41 Public Contracts and Property Management 2 2010-07-01 2010-07-01 true Conversion. 101-30.101-8 Section 101-30.101-8 Public Contracts and Property Management Federal Property Management Regulations...
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78 FR 66861 - Airworthiness Directives; Airbus Airplanes
2013-11-07
...-0834; Directorate Identifier 2012-NM-045-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... 2004-11-08, AD 2004-13-25, AD 2004-18-14, AD 2008-06-07, and AD 2012-04-07 that apply to certain Airbus... Airbus Model A340-200, -300, -500, and -600 series airplanes from the applicability. We are proposing...
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The Integrated Mode Management Interface
Hutchins, Edwin
1996-01-01
Mode management is the processes of understanding the character and consequences of autoflight modes, planning and selecting the engagement, disengagement and transitions between modes, and anticipating automatic mode transitions made by the autoflight system itself. The state of the art is represented by the latest designs produced by each of the major airframe manufacturers, the Boeing 747-400, the Boeing 777, the McDonnell Douglas MD-11, and the Airbus A320/A340 family of airplanes. In these airplanes autoflight modes are selected by manipulating switches on the control panel. The state of the autoflight system is displayed on the flight mode annunciators. The integrated mode management interface (IMMI) is a graphical interface to autoflight mode management systems for aircraft equipped with flight management computer systems (FMCS). The interface consists of a vertical mode manager and a lateral mode manager. Autoflight modes are depicted by icons on a graphical display. Mode selection is accomplished by touching (or mousing) the appropriate icon. The IMMI provides flight crews with an integrated interface to autoflight systems for aircraft equipped with flight management computer systems (FMCS). The current version is modeled on the Boeing glass-cockpit airplanes (747-400, 757/767). It runs on the SGI Indigo workstation. A working prototype of this graphics-based crew interface to the autoflight mode management tasks of glass cockpit airplanes has been installed in the Advanced Concepts Flight Simulator of the CSSRF of NASA Ames Research Center. This IMMI replaces the devices in FMCS equipped airplanes currently known as mode control panel (Boeing), flight guidance control panel (McDonnell Douglas), and flight control unit (Airbus). It also augments the functions of the flight mode annunciators. All glass cockpit airplanes are sufficiently similar that the IMMI could be tailored to the mode management system of any modern cockpit. The IMMI does not replace the
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The Dragonfly Nearby Galaxies Survey. III. The Luminosity Function of the M101 Group
Danieli, Shany; van Dokkum, Pieter; Merritt, Allison; Abraham, Roberto; Zhang, Jielai; Karachentsev, I. D.; Makarova, L. N.
2017-03-01
We obtained follow-up HST observations of the seven low surface brightness galaxies discovered with the Dragonfly Telephoto Array in the field of the massive spiral galaxy M101. Out of the seven galaxies, only three were resolved into stars and are potentially associated with the M101 group at D = 7 Mpc. Based on HST ACS photometry in the broad F606W and F814W filters, we use a maximum likelihood algorithm to locate the Tip of the Red Giant Branch in galaxy color-magnitude diagrams. Distances are {6.38}-0.35+0.35,{6.87}-0.30+0.21 and {6.52}-0.27+0.25 {Mpc} and we confirm that they are members of the M101 group. Combining the three confirmed low-luminosity satellites with previous results for brighter group members, we find the M101 galaxy group to be a sparsely populated galaxy group consisting of seven group members, down to M V = -9.2 mag. We compare the M101 cumulative luminosity function to that of the Milky Way and M31. We find that they are remarkably similar; in fact, the cumulative luminosity function of the M101 group gets even flatter for fainter magnitudes, and we show that the M101 group might exhibit the two known small-scale flaws in the ΛCDM model, namely “the missing satellite” problem and the “too big to fail” problem. Kinematic measurements of M101's satellite galaxies are required to determine whether the “too big to fail” problem does in fact exist in the M101 group.
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76 FR 50706 - Airworthiness Directives; SOCATA Airplanes
2011-08-16
... INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; e-mail: albert.mercado@faa... Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri...
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76 FR 67341 - Airworthiness Directives; SOCATA Airplanes
2011-11-01
... INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; email: albert.mercado@faa...: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City...
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14 CFR Appendix D to Part 125 - Airplane Flight Recorder Specification
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specification D... AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD... Appendix D to Part 125—Airplane Flight Recorder Specification Parameters Range Accuracy sensor input to...
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14 CFR 125.175 - Protection of other airplane components against fire.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Protection of other airplane components... CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD... Requirements § 125.175 Protection of other airplane components against fire. (a) Except as provided in...
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14 CFR 135.393 - Large nontransport category airplanes: Landing limitations: Destination airports.
2010-01-01
... category airplane may take off that airplane at a weight that— (1) Allowing for anticipated consumption of... assumed that— (1) The airplane passes directly over the intersection of the obstruction clearance plane...
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F-15B ACTIVE with thrust vectoring nozzles on test stand at sunrise
1995-01-01
This November 13, 1995, photograph of the F-15 Advanced Controls Technology for Integrated Vehicles (ACTIVE) at NASA's Dryden Flight Research Center, Edwards, California, shows the aircraft on a test stand at sunrise. Not shown in this photograph are the aircraft's two new Pratt & Whitney nozzles that can turn up to 20 degrees in any direction. These nozzles give the aircraft thrust control in the pitch (up and down) and yaw (left and right) directions. This will reduce drag and increase fuel economy or range as compared with conventional aerodynamic controls, which increase the retarding forces (drag) acting upon the aircraft. These tests could result in significant performance increases for military and commercial aircraft. The research program is the product of a collaborative effort by NASA, the Air Force's Wright Laboratory, Pratt & Whitney, and McDonnell Douglas Aerospace. The aircraft was originally built as an F-15B (Serial #71-0290).
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Analysis of solar thermophotovoltaic test data from experiments performed at McDonnell Douglas
Energy Technology Data Exchange (ETDEWEB)
Stone, K.W.; Kusek, S.M.; Drubka, R.E. [McDonnell Douglas, 5301 Bolsa Avenue, Huntington Beach, California 92647 (United States); Fay, T.D. [21911 Bacalar, Mission Viejo, California 92692 (United States)
1995-01-05
Solar thermophotovoltaic power systems offer potentially high system efficiency for solar energy to electrical energy conversion and attractive system advantages. McDonnell Douglas Corporation (MDC) has been investigating this technology for both space and terrestrial applications for several years. A testbed prototype was designed, built, and tested on a 90 kW{sub t} dish concentrator at the MDA solar test facility. Twelve experiments were conducted with absorber temperatures in excess of 1300 {degree}C being achieved using only a fraction of the reflected power from the 90 kW{sub t} dish concentrator. This paper discusses the solar thermophotovoltaic testbed prototype unit, test data, and presents an analysis of the unit`s performance. A combination of analytical analysis and test data is used to obtain an understanding of the system and subsystem performance. The preliminary results of these tests and analysis indicate a solar thermophotovoltaic power system can achieve high system performance. Furthermore, system demonstrations are possible utilizing a combination of current off-the-shelf hardware components and components currently being tested in laboratories. {copyright} {ital 1995} {ital American} {ital Institute} {ital of} {ital Physics}.
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14 CFR 125.375 - Fuel supply: Nonturbine and turbopropeller-powered airplanes.
2010-01-01
...) Thereafter, to fly for 45 minutes at normal crusing fuel consumption. (b) If the airplane is released for any...-powered airplanes. 125.375 Section 125.375 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... AND OPERATIONS CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE...
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14 CFR Appendix E to Part 125 - Airplane Flight Recorder Specifications
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specifications E... AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD... Appendix E to Part 125—Airplane Flight Recorder Specifications The recorded values must meet the designated...
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Lateral-directional aerodynamic characteristics of light, twin-engine, propeller driven airplanes
Wolowicz, C. H.; Yancey, R. B.
1972-01-01
Analytical procedures and design data for predicting the lateral-directional static and dynamic stability and control characteristics of light, twin engine, propeller driven airplanes for propeller-off and power-on conditions are reported. Although the consideration of power effects is limited to twin engine airplanes, the propeller-off considerations are applicable to single engine airplanes as well. The procedures are applied to a twin engine, propeller driven, semi-low-wing airplane in the clean configuration through the linear lift range. The calculated derivative characteristics are compared with wind tunnel and flight data. Included in the calculated characteristics are the spiral mode, roll mode, and Dutch roll mode over the speed range of the airplane.
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2010-10-01
... 42 Public Health 1 2010-10-01 2010-10-01 false Definitions. 55a.101 Section 55a.101 Public Health PUBLIC HEALTH SERVICE, DEPARTMENT OF HEALTH AND HUMAN SERVICES GRANTS PROGRAM GRANTS FOR BLACK LUNG CLINICS General Provisions § 55a.101 Definitions. Act, as used in this part, means the Federal Mine Safety...
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A Software Defined Radio Based Airplane Communication Navigation Simulation System
He, L.; Zhong, H. T.; Song, D.
2018-01-01
Radio communication and navigation system plays important role in ensuring the safety of civil airplane in flight. Function and performance should be tested before these systems are installed on-board. Conventionally, a set of transmitter and receiver are needed for each system, thus all the equipment occupy a lot of space and are high cost. In this paper, software defined radio technology is applied to design a common hardware communication and navigation ground simulation system, which can host multiple airplane systems with different operating frequency, such as HF, VHF, VOR, ILS, ADF, etc. We use a broadband analog frontend hardware platform, universal software radio peripheral (USRP), to transmit/receive signal of different frequency band. Software is compiled by LabVIEW on computer, which interfaces with USRP through Ethernet, and is responsible for communication and navigation signal processing and system control. An integrated testing system is established to perform functional test and performance verification of the simulation signal, which demonstrate the feasibility of our design. The system is a low-cost and common hardware platform for multiple airplane systems, which provide helpful reference for integrated avionics design.
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Mainardi, F; Lisotto, C; Maggioni, F; Zanchin, G
2012-06-01
The 'headache attributed to airplane travel', also named 'airplane headache' (AH), is a recently described headache disorder that appears exclusively in relation to airplane flights, in particular during the landing phase. Based on the stereotypical nature of the attacks in all reported cases, we proposed provisional diagnostic criteria for AH in a previously published paper. Up to now 37 cases have been described in the literature. After our paper was disseminated via the Internet, we received several email messages from subjects around the world who had experienced such a peculiar headache. Their cooperation, by completing a structured questionnaire and allowing the direct observation of three subjects, enabled us to carry out a study on a total of 75 patients suffering from AH. Our survey confirmed the stereotypical nature of the attacks, in particular with regard to the short duration of the pain (lasting less than 30 minutes in up to 95% of the cases), the clear relationship with the landing phase, the unilateral pain, the male preponderance, and the absence of accompanying signs and/or symptoms. It is conceivable to consider barotrauma as one of the main mechanisms involved in the pathophysiology of AH. The observation that the pain appears inconstantly in the majority of cases, without any evident disorder affecting the paranasal sinuses, could be consistent with a multimodal pathogenesis underlying this condition, possibly resulting in the interaction between anatomic, environmental and temporary concurrent factors. This is by far the largest AH case series ever reported in the literature. The diagnostic criteria that we previously proposed proved to be valid when applied to a large number of patients suffering from this condition. We support its recognition as a new form of headache, to be included in the forthcoming update of the International Headache Society Classification, within '10. Headache attributed to disorder of homoeostasis'. Its formal
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A Hardware-in-the-Loop Simulator for Software Development for a Mars Airplane
Slagowski, Stefan E.; Vican, Justin E.; Kenney, P. Sean
2007-01-01
Draper Laboratory recently developed a Hardware-In-The-Loop Simulator (HILSIM) to provide a simulation of the Aerial Regional-scale Environmental Survey (ARES) airplane executing a mission in the Martian environment. The HILSIM was used to support risk mitigation activities under the Planetary Airplane Risk Reduction (PARR) program. PARR supported NASA Langley Research Center's (LaRC) ARES proposal efforts for the Mars Scout 2011 opportunity. The HILSIM software was a successful integration of two simulation frameworks, Draper's CSIM and NASA LaRC's Langley Standard Real-Time Simulation in C++ (LaSRS++).
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14 CFR 121.277 - Protection of other airplane components against fire.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Protection of other airplane components....277 Protection of other airplane components against fire. (a) Except as provided in paragraph (b) of this section, all airplane surfaces aft of the nacelles in the area of one nacelle diameter on both...
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14 CFR 121.193 - Airplanes: Turbine engine powered: En route limitations: Two engines inoperative.
2010-01-01
... the Airplane Flight Manual, allows the airplane to fly from the point where the two engines are...-inoperative, en route, net flight path data in the Airplane Flight Manual, allows the airplane to fly from the... Airplane Flight Manual, allows the airplane to fly from the point where the two engines are assumed to fail...
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41 CFR 101-39.101 - Notice of intention to begin a study.
2010-07-01
... VEHICLES 39-INTERAGENCY FLEET MANAGEMENT SYSTEMS 39.1-Establishment, Modification, and Discontinuance of Interagency Fleet Management Systems § 101-39.101 Notice of intention to begin a study. The Administrator, GSA... develop data and justification as to the feasibility of establishing a fleet management system. The...
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2010-08-13
... cycling and that a previous study on a Model A310 airplane had shown no reduction in stiffness due to age... considers the equipment for both inspections to be special tooling and the inspection methods to be of... of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures...
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DESIGN ASPECTS IN AIRPLANE EVOLUTION
Directory of Open Access Journals (Sweden)
ENUŞ Marilena
2013-11-01
Full Text Available The paper proposes to present a few important aspects from aerodynamics and aerospace technology. It also, presents important points regarding the improvement of airplanes as a result of research in shape modelling, materials, aerodynamics and 3d design. Several examples based on constructive structures are offered. The embodiment design of a traditional airplane is presented in order to offer directions of conceptual development for improving its performance parameters and shapes. The virtual scale models are created by computer in Catia V5, in order to provide the validation of the features and the performance of aerodynamic configuration in the wind tunnel.
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77 FR 47277 - Airworthiness Directives; Bombardier, Inc. Airplanes
2012-08-08
... Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The... airplanes, serial numbers 413, 443, 450 through 452 inclusive, 456, 458, 462 through 465 inclusive, 467 through 470 inclusive, and 473 through 588 inclusive. (2) Model DHC-8-400, -401, and -402 airplanes...
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Atmospheric electron flux at airplane altitude
International Nuclear Information System (INIS)
Enomoto, R.; Chiba, J.; Ogawa, K.; Sumiyoshi, T.; Takasaki, F.; Kifune, T.; Matsubara, Y.; Nishimura, J.
1991-01-01
We have developed a new detector to systematically measure the cosmic-ray electron flux at airplane altitudes. We loaded a lead-glass-based electron telescope onto a commercial cargo airplane. The first experiment was carried out using the air route between Narita (Japan) and Sydney (Australia); during this flight we measured the electron flux at various altitudes and latitudes. The thresholds of the electron energies were 1, 2, and 4 GeV. The results agree with a simple estimation using one-dimensional shower theory. A comparison with a Monte Carlo calculation was made
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41 CFR 101-39.101-1 - Agency cooperation.
2010-07-01
...-INTERAGENCY FLEET MANAGEMENT SYSTEMS 39.1-Establishment, Modification, and Discontinuance of Interagency Fleet... 41 Public Contracts and Property Management 2 2010-07-01 2010-07-01 true Agency cooperation. 101-39.101-1 Section 101-39.101-1 Public Contracts and Property Management Federal Property Management...
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Advances in Thrust-Based Emergency Control of an Airplane
Creech, Gray; Burken, John J.; Burcham, Bill
2003-01-01
Engineers at NASA's Dryden Flight Research Center have received a patent on an emergency flight-control method implemented by a propulsion-controlled aircraft (PCA) system. Utilizing the preexisting auto-throttle and engine-pressure-ratio trim controls of the airplane, the PCA system provides pitch and roll control for landing an airplane safely without using aerodynamic control surfaces that have ceased to function because of a primary-flight-control-system failure. The installation of the PCA does not entail any changes in pre-existing engine hardware or software. [Aspects of the method and system at previous stages of development were reported in Thrust-Control System for Emergency Control of an Airplane (DRC-96-07), NASA Tech Briefs, Vol. 25, No. 3 (March 2001), page 68 and Emergency Landing Using Thrust Control and Shift of Weight (DRC-96-55), NASA Tech Briefs, Vol. 26, No. 5 (May 2002), page 58.]. Aircraft flight-control systems are designed with extensive redundancy to ensure low probabilities of failure. During recent years, however, several airplanes have exhibited major flight-control-system failures, leaving engine thrust as the last mode of flight control. In some of these emergency situations, engine thrusts were successfully modulated by the pilots to maintain flight paths or pitch angles, but in other situations, lateral control was also needed. In the majority of such control-system failures, crashes resulted and over 1,200 people died. The challenge lay in creating a means of sufficient degree of thrust-modulation control to safely fly and land a stricken airplane. A thrust-modulation control system designed for this purpose was flight-tested in a PCA an MD-11 airplane. The results of the flight test showed that without any operational control surfaces, a pilot can land a crippled airplane (U.S. Patent 5,330,131). The installation of the original PCA system entailed modifications not only of the flight-control computer (FCC) of the airplane but
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Simple Electromagnetic Modeling of Small Airplanes: Neural Network Approach
Koudelka, V.; Raida, Zbyněk; Tobola, P.
2009-01-01
The paper deals with the development of simple electromagnetic models of small airplanes, which can contain composite materials in their construction. Electromagnetic waves can penetrate through the surface of the aircraft due to the specific electromagnetic properties of the composite materials, which can increase the intensity of fields inside the airplane and can negatively influence the functionality of the sensitive avionics. The airplane is simulated by two parallel dielectric layers (t...
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14 CFR 121.412 - Qualifications: Flight instructors (airplane) and flight instructors (simulator).
2010-01-01
... (airplane) and flight instructors (simulator). 121.412 Section 121.412 Aeronautics and Space FEDERAL... OPERATIONS Training Program § 121.412 Qualifications: Flight instructors (airplane) and flight instructors (simulator). (a) For the purposes of this section and § 121.414: (1) A flight instructor (airplane) is a...
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Airplane energy use and conservation strategies
Energy Technology Data Exchange (ETDEWEB)
Pilati, D.A.
1974-05-01
Domestic commercial airplane fuel use is examined as a function of stage length. A fuel use model is developed using the eight most popular airplanes. Short flights are very fuel inefficient; a 100-mile flight consumes 2.5 times as much fuel per passenger-mile than a 1,000-mile flight. Half of today's flights are for distances under 260 miles. Fuel consumption for purposes other than flying directly between airports is examined. Over 10% of total fuel use is for those portions of the flight in which no enroute distance is achieved. Delays account for at least 4.2% of the fuel consumption and auxiliary power units use over 1%. Fuel requirements for attempting to recover lost time and for fuel ferrying are also discussed. Airplane fuel efficiency can be increased in the short term by operational changes, particularly by increasing the load factor. A load factor increase from 50 to 60% would reduce airplane fuel use by 16% for the same traffic. Other options include reducing cruise speeds, increasing cruise altitudes, and changing ground operations. Each of these strategies offer savings of 1 to 3%. Total transportation energy use can be reduced by shifting air passengers to ground modes, especially for the inefficient short-stage traffic. Net energy savings for diverting half the flights under 200 miles to buses or trains is equivalent to 6% of the fleet fuel use. (6 tables, 6 fig., 36 references)
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Reversible cerebral vasoconstriction syndrome precipitated by airplane descent: Case report.
Hiraga, Akiyuki; Aotsuka, Yuya; Koide, Kyosuke; Kuwabara, Satoshi
2017-10-01
Background Reversible cerebral vasoconstriction syndrome (RCVS) is characterized by segmental vasospasm. Vasoactive agents and childbirth have been reported as precipitating factors for RCVS; however, RCVS induced by altitude change or air travel has rarely been reported. Case We present a case of a 74-year-old woman who presented with thunderclap headache during airplane descent. Magnetic resonance angiography demonstrated segmental vasoconstriction that improved 9 days after onset. Conclusion These findings indicate that airplane descent may be a trigger of RCVS. The time course of headache in the present case was similar to that of prolonged headache attributed to airplane travel, indicating that RCVS during air travel may have previously been overlooked and that some headache attributed to airplane travel cases may represent a milder form of RCVS.
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76 FR 73491 - Airworthiness Directives; McDonnell Douglas Corporation Airplanes
2011-11-29
... issued revised service rework drawings to clarify the repair instructions. These service rework drawings... have updated the references in paragraph (g) of this AD to include Boeing DC-10-10 Service Rework... DC-10-10 Service Rework Drawing SR10570048, Revision K, dated October 7, 2010, including Parts List...
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Airplane detection in remote sensing images using convolutional neural networks
Ouyang, Chao; Chen, Zhong; Zhang, Feng; Zhang, Yifei
2018-03-01
Airplane detection in remote sensing images remains a challenging problem and has also been taking a great interest to researchers. In this paper we propose an effective method to detect airplanes in remote sensing images using convolutional neural networks. Deep learning methods show greater advantages than the traditional methods with the rise of deep neural networks in target detection, and we give an explanation why this happens. To improve the performance on detection of airplane, we combine a region proposal algorithm with convolutional neural networks. And in the training phase, we divide the background into multi classes rather than one class, which can reduce false alarms. Our experimental results show that the proposed method is effective and robust in detecting airplane.
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Stevens, Joseph E.
1955-01-01
Low-lift drag data are presented herein for one 1/7.5-scale rocket-boosted model and three 1/45.85-scale equivalent-body models of the Grumman F9F-9 airplane, The data were obtained over a Reynolds number range of about 5 x 10(exp 6) to 10 x 10(exp 6) based on wing mean aerodynamic chord for the rocket model and total body length for the equivalent-body models. The rocket-boosted model showed a drag rise of about 0,037 (based on included wing area) between the subsonic level and the peak supersonic drag coefficient at the maximum Mach number of this test. The base drag coefficient measured on this model varied from a value of -0,0015 in the subsonic range to a maximum of about 0.0020 at a Mach number of 1.28, Drag coefficients for the equivalent-body models varied from about 0.125 (based on body maximum area) in the subsonic range to about 0.300 at a Mach number of 1.25. Increasing the total fineness ratio by a small amount raised the drag-rise Mach number slightly.
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2013-12-12
... Inc., Models BD-500-1A10 and BD- 500-1A11 Series Airplanes; Electronic Flight Control System: Control... Inc. Models BD-500-1A10 and BD-500-1A11 series airplanes. These airplanes will have a novel or unusual... comments, data, or views. The most helpful comments reference a specific portion of the special conditions...
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2012-11-20
... Aerospace, Model BD-500-1A10 and BD-500-1A11 Airplanes; Sidestick Controllers AGENCY: Federal Aviation... conditions for the Bombardier Aerospace Model BD-500-1A10 and BD-500-1A11 airplanes. These airplanes will... on the comments we receive. Background On December 10, 2009, Bombardier Aerospace applied for a type...
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The Airplane as an Open-Source Invention
Peter B. Meyer
2013-01-01
Airplanes were invented after decades of experimentation in many countries through a process we can call open-source innovation. Experimenters, inventors, and writers contributed to the airplane’s development by sharing information in publications, in clubs, by writing letters and by visiting. The hundreds of aeronautical patents before 1900 were treated like publications, not like claims to intellectual property. Inventors of modern airplanes copied earlier designs, analogously to advances i...
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Three Cases of Spine Fractures after an Airplane Crash.
Lee, Han Joo; Moon, Bong Ju; Pennant, William A; Shin, Dong Ah; Kim, Keung Nyun; Yoon, Do Heum; Ha, Yoon
2015-10-01
While injuries to the spine after an airplane crash are not rare, most crashes result in fatal injuries. As such, few studies exist that reported on spine fractures sustained during airplane accidents. In this report, we demonstrate three cases of spine fractures due to crash landing of a commercial airplane. Three passengers perished from injuries after the crash landing, yet most of the passengers and crew on board survived, with injuries ranging from minor to severe. Through evaluating our three spine fracture patients, it was determined that compression fracture of the spine was the primary injury related to the airplane accident. The first patient was a 20-year-old female who sustained a T6-8 compression fracture without neurologic deterioration. The second patient was a 33-year-old female with an L2 compression fracture, and the last patient was a 49-year-old male patient with a T8 compression fracture. All three patients were managed conservatively and required spinal orthotics. During the crash, each of these patients were subjected to direct, downward high gravity z-axis (Gz) force, which gave rise to load on the spine vertically, thereby causing compression fracture. Therefore, new safety methods should be developed to prevent excessive Gz force during airplane crash landings.
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Three Cases of Spine Fractures after an Airplane Crash
Lee, Han Joo; Moon, Bong Ju; Pennant, William A.; Shin, Dong Ah; Kim, Keung Nyun; Yoon, Do Heum
2015-01-01
While injuries to the spine after an airplane crash are not rare, most crashes result in fatal injuries. As such, few studies exist that reported on spine fractures sustained during airplane accidents. In this report, we demonstrate three cases of spine fractures due to crash landing of a commercial airplane. Three passengers perished from injuries after the crash landing, yet most of the passengers and crew on board survived, with injuries ranging from minor to severe. Through evaluating our three spine fracture patients, it was determined that compression fracture of the spine was the primary injury related to the airplane accident. The first patient was a 20-year-old female who sustained a T6-8 compression fracture without neurologic deterioration. The second patient was a 33-year-old female with an L2 compression fracture, and the last patient was a 49-year-old male patient with a T8 compression fracture. All three patients were managed conservatively and required spinal orthotics. During the crash, each of these patients were subjected to direct, downward high gravity z-axis (Gz) force, which gave rise to load on the spine vertically, thereby causing compression fracture. Therefore, new safety methods should be developed to prevent excessive Gz force during airplane crash landings. PMID:27169094
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The Bristol "Badminton" Airplane
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.
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The radiosensitivity of spermatogonial stem cells in C3H/101 F1 hybrid mice
International Nuclear Information System (INIS)
Van der Meer, Yvonne; De Rooij, Dirk G.; Cattanach, Bruce M.
1993-01-01
The radiosensitivity of spermatogonial stem cells of C3H/HeHx101/H F 1 hybrid mice was determined by counting undifferentiated spermatogonia at 10 days after X-irradiation. During the spermatogenic cycle, differences in radiosensitivity were found, which were correlated with the proliferative activity of the spermatogonial stem cells. In stage VIII irr , during quiescence, the spermatogonial stem cells were most radiosensitive with a D 0 of 1.4 Gy. In stages XI irr -V irr , when the cells were proliferatively active, the D 0 was about 2.6 Gy. Based on the D 0 values for sensitive and resistant spermatogonia and on the D 0 for the total population, a ratio of 45:55% of sensitive to resistant spermatogonial stem cells was estimated for cell killing. When the present data were compared with data on translocation induction obtained in mice of the same genotype, a close fit was obtained when the translocation yield (Y; in % abnormal cells) after a radiation dose D was described by Y=e τD , with τ=1 for the sensitive and τ=0.1 for the resistant spermatogonial stem cells, with a maximal e τD of 100
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Effect of airplane transport of donor livers on post-liver transplantation survival.
Huang, Yi; MacQuillan, Gerry; Adams, Leon A; Garas, George; Collins, Megan; Nwaba, Albert; Mou, Linjun; Bulsara, Max K; Delriviere, Luc; Jeffrey, Gary P
2016-11-07
To evaluate the effect of long haul airplane transport of donor livers on post-transplant outcomes. A retrospective cohort study of patients who received a liver transplantation was performed in Perth, Australia from 1992 to 2012. Donor and recipient characteristics information were extracted from Western Australian liver transplantation service database. Patients were followed up for a mean of six years. Patient and graft survival were evaluated and compared between patients who received a local donor liver and those who received an airplane transported donor liver. Predictors of survival were determined by univariate and multivariate analysis using cox regression. One hundred and ninety-three patients received a local donor liver and 93 patients received an airplane transported donor liver. Airplane transported livers had a significantly lower alanine transaminase (mean: 45 U/L vs 84 U/L, P = 0.035), higher donor risk index (mean: 1.88 vs 1.42, P airplane transport retained significance for graft loss (HR = 1.92, 95%CI: 1.16-3.17). One year graft survival was 0.88 for those with a local liver and was 0.71 for those with an airplane transported liver. One year graft loss was due to primary graft non-function or associated with preservation injury in 20.8% of recipients of an airplane transported liver compared with 4.6% in those with a local liver ( P = 0.027). Airplane transport of donor livers was independently associated with reduced graft survival following liver transplantation.
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78 FR 42720 - Airworthiness Directives; The Boeing Company Airplanes
2013-07-17
... airplane reaching its limit of validity (LOV) of the engineering data that support the established... receipt. FOR FURTHER INFORMATION CONTACT: Chandraduth Ramdoss, Aerospace Engineer, Airframe Branch, ANM... airplane structure. The last element of those initiatives is the requirement to establish a limit of...
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78 FR 52870 - Airworthiness Directives; Beechcraft Corporation Airplanes
2013-08-27
... Airworthiness Directives; Beechcraft Corporation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... (AD) for certain Beechcraft Corporation (type certificate previously held by Hawker Beechcraft Corporation) Models 1900, 1900C, and 1900D airplanes. This proposed AD was prompted by reports of cracking in...
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14 CFR 121.411 - Qualifications: Check airmen (airplane) and check airmen (simulator).
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Qualifications: Check airmen (airplane) and... § 121.411 Qualifications: Check airmen (airplane) and check airmen (simulator). (a) For the purposes of this section and § 121.413: (1) A check airman (airplane) is a person who is qualified, and permitted...
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77 FR 29214 - Airworthiness Directives; Hawker Beechcraft Corporation Airplanes
2012-05-17
... Airworthiness Directives; Hawker Beechcraft Corporation Airplanes AGENCY: Federal Aviation Administration (FAA... Hawker Beechcraft Corporation Models 58 and G58 airplanes. This AD was prompted by installation of... this AD, contact Hawker Beechcraft Corporation, B091-A04, 10511 E. Central Ave., Wichita, Kansas 67206...
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77 FR 12757 - Airworthiness Directives; Hawker Beechcraft Corporation Airplanes
2012-03-02
... Corporation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... Beechcraft Corporation Models 58 and G58 airplanes. This proposed AD was prompted by installation of... information identified in this proposed AD, contact Hawker Beechcraft Corporation, B091-A04, 10511 E. Central...
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International Nuclear Information System (INIS)
Brunner, P.
1975-01-01
In May, 1974, a severe airplane crash occurred near Springfield, llinois; the crew of three and a courier were killed. The plane was carrying a large container of controlled water with a slight amount of 60 Co. A survey of the crash site by Air Force detectives and the radiological assistance team from Wright--Patterson Air Force Base indicated no radioactivity. Experiences of the incident were used to develop guidelines for future emergency preparedness
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76 FR 53308 - Airworthiness Directives; Cessna Aircraft Company Airplanes
2011-08-26
... bumper, and the attachment hardware with a rudder stop modification kit. This new AD requires a change to..., Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability... acrobatic maneuvers in the airplane or replacement of the rudder stop, rudder stop bumper, and attachment...
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Stubbs, S. M.; Tanner, J. A.; Smith, E. G.
1979-01-01
The braking and cornering response of a slip velocity controlled, pressure bias modulated aircraft antiskid braking system is investigated. The investigation, conducted on dry and wet runway surfaces, utilized one main gear wheel, brake, and tire assembly of a McDonnell Douglas DC 9 series 10 airplane. The landing gear strut was replaced by a dynamometer. The parameters, which were varied, included the carriage speed, tire loading, yaw angle, tire tread condition, brake system operating pressure, and runway wetness conditions. The effects of each of these parameters on the behavior of the skid control system is presented. Comparisons between data obtained with the skid control system and data obtained from single cycle braking tests without antiskid protection are examined.
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78 FR 42900 - Airworthiness Directives; The Boeing Company Airplanes
2013-07-18
... airplane reaching its limit of validity (LOV) of the engineering data that support the established... receipt. FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM 120L... airplane structure. The last element of those initiatives is the requirement to establish a LOV of the...
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78 FR 9781 - Airworthiness Directives; Pacific Aerospace Limited Airplanes
2013-02-12
... Airworthiness Directives; Pacific Aerospace Limited Airplanes AGENCY: Federal Aviation Administration (FAA... directive (AD) for all Pacific Aerospace Limited Models FU24-954 and FU24A-954 airplanes. This AD results... Aerospace Limited, Hamilton Airport, Private Bag, 3027 Hamilton, New Zealand; telephone: +64 7 843 6144; fax...
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14 CFR Appendix D to Part 135 - Airplane Flight Recorder Specification
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specification D.... D Appendix D to Part 135—Airplane Flight Recorder Specification Parameters Range Accuracy sensor.... 3 For airplanes that can demonstrate the capability of deriving either the control input on control...
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Description of a Normal-Force In-Situ Turbulence Algorithm for Airplanes
Stewart, Eric C.
2003-01-01
A normal-force in-situ turbulence algorithm for potential use on commercial airliners is described. The algorithm can produce information that can be used to predict hazardous accelerations of airplanes or to aid meteorologists in forecasting weather patterns. The algorithm uses normal acceleration and other measures of the airplane state to approximate the vertical gust velocity. That is, the fundamental, yet simple, relationship between normal acceleration and the change in normal force coefficient is exploited to produce an estimate of the vertical gust velocity. This simple approach is robust and produces a time history of the vertical gust velocity that would be intuitively useful to pilots. With proper processing, the time history can be transformed into the eddy dissipation rate that would be useful to meteorologists. Flight data for a simplified research implementation of the algorithm are presented for a severe turbulence encounter of the NASA ARIES Boeing 757 research airplane. The results indicate that the algorithm has potential for producing accurate in-situ turbulence measurements. However, more extensive tests and analysis are needed with an operational implementation of the algorithm to make comparisons with other algorithms or methods.
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2012-10-18
... after operation of high-speed warning system by application of a load of 1.5g (0.5 acceleration... 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 airworthiness...
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International Nuclear Information System (INIS)
Wang, T.V.; Smith, K.C.
1981-01-01
The interaction of the recB21, uvrD3, lexA101, and recF143 mutations on UV radiation sensitization and genetic recombination was studied in isogenic strains containing all possible combinations of these mutations in a ΔuvrB genetic background. The relative UV radiation sensitivities of the multiply mutant strains in the ΔuvrB background were: recF recB lexA > recF recB uvrD lexA, recF recB uvrD > recA > recF uvrD lexA > recF recB, recF uvrD > recF lexA > recB uvrD lexA > recB uvrD > recB lexA, lexA uvrD > recB > lexA, uvrD > recF; three of these strains were more UV radiation sensitive than the uvrB recA strain. There was no correlation between the degree of radiation sensitivity and the degree of deficiency in genetic recombination. An analysis of the survival curves revealed that the recF mutation interacts synergistically with the recB, uvrD, and lexA mutations in UV radiation sensitization, while the recB, uvrD, and lexA mutations appear to interact additively with each other. We interpret these data to suggest that there are two major independent pathways for postreplication repair; one is dependent on the recF gene, and the other is dependent on the recB, uvrD, and lexA genes. (orig.)
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78 FR 42724 - Airworthiness Directives; Beechcraft Corporation Airplanes
2013-07-17
... Corporation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... certain Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. AD 2011-27-51 currently requires... Corporation at P.O. Box 85, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140; Internet...
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14 CFR Appendix B to Part 121 - Airplane Flight Recorder Specification
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specification B... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Pt. 121, App. B Appendix B to Part 121—Airplane... airplanes that can demonstrate the capability of deriving either the control input on control movement (one...
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41 CFR 101-30.101-3 - National stock number.
2010-07-01
... 41 Public Contracts and Property Management 2 2010-07-01 2010-07-01 true National stock number. 101-30.101-3 Section 101-30.101-3 Public Contracts and Property Management Federal Property Management Regulations System FEDERAL PROPERTY MANAGEMENT REGULATIONS SUPPLY AND PROCUREMENT 30-FEDERAL CATALOG SYSTEM 30...
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77 FR 56991 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Airplanes
2012-09-17
... FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901....mercado@faa.gov . SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed.... Send information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901...
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77 FR 20511 - Airworthiness Directives; The Boeing Company Airplanes
2012-04-05
... language regarding certain ``specific airplane(s).'' We find these comments to be addressed to EASA... with thrust reverser part number (P/N) 315A2295-003 through 315A2295-154 inclusive: Do the actions...-155 through 315A2295-174 inclusive: Do the actions within 60 months after the effective date of this...
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A knowledge-based design framework for airplane conceptual and preliminary design
Anemaat, Wilhelmus A. J.
The goal of work described herein is to develop the second generation of Advanced Aircraft Analysis (AAA) into an object-oriented structure which can be used in different environments. One such environment is the third generation of AAA with its own user interface, the other environment with the same AAA methods (i.e. the knowledge) is the AAA-AML program. AAA-AML automates the initial airplane design process using current AAA methods in combination with AMRaven methodologies for dependency tracking and knowledge management, using the TechnoSoft Adaptive Modeling Language (AML). This will lead to the following benefits: (1) Reduced design time: computer aided design methods can reduce design and development time and replace tedious hand calculations. (2) Better product through improved design: more alternative designs can be evaluated in the same time span, which can lead to improved quality. (3) Reduced design cost: due to less training and less calculation errors substantial savings in design time and related cost can be obtained. (4) Improved Efficiency: the design engineer can avoid technically correct but irrelevant calculations on incomplete or out of sync information, particularly if the process enables robust geometry earlier. Although numerous advancements in knowledge based design have been developed for detailed design, currently no such integrated knowledge based conceptual and preliminary airplane design system exists. The third generation AAA methods are tested over a ten year period on many different airplane designs. Using AAA methods will demonstrate significant time savings. The AAA-AML system will be exercised and tested using 27 existing airplanes ranging from single engine propeller, business jets, airliners, UAV's to fighters. Data for the varied sizing methods will be compared with AAA results, to validate these methods. One new design, a Light Sport Aircraft (LSA), will be developed as an exercise to use the tool for designing a new airplane
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AGT101 Advanced Gas Turbine Technology update
Energy Technology Data Exchange (ETDEWEB)
Boyd, G.L.; Kidwell, J.R.; Kreiner, D.M.
1986-01-01
The Garrett/Ford Advanced Gas Turbine Technology Development Program, designated AGT101, has made significant progress during 1985 encompassing ceramic engine and ceramic component testing. Engine testing has included full speed operation to 100,000 rpm and 1149C (2100F) turbine inlet temperature, initial baseline performance mapping and ceramic combustor start and steady state operation. Over 380 hours of test time have been accumulated on four development engines. High temperature foil bearing coatings have passed rig test and a thick precious metal foil coating selected for engine evaluation. Ceramic structures have been successfully rig tested at 1371C (2500F) for over 27 hours.
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A Study of Transport Airplane Crash-Resistant Fuel Systems
National Research Council Canada - National Science Library
Robertson, S
2002-01-01
...), of transport airplane crash-resistant fuel system (CRFS). The report covers the historical studies related to aircraft crash fires and fuel containment concepts undertaken by the FAA, NASA, and the U.S...
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77 FR 31483 - Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes
2012-05-29
... Service Change (ASC) 229 and G-1159 (aka G-II) ASC 426 installs a new three-piece box fitting on the left... result of an improper structural modification. This records search also revealed that six other Model G... similar nonconforming condition was found on a total of six airplanes. Of those, one airplane does not...
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2013-02-19
... is the first of a new family of jet airplanes designed for corporate flight, fractional, charter, and... conservative way when deriving limit loads from limit conditions. (2) The airplane must meet the strength...
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77 FR 2442 - Airworthiness Directives; The Boeing Company Airplanes
2012-01-18
... bulletin to change the concurrent requirement and provide wiring changes and an alternative installation... installation of the new panel assemblies for airplanes that have the optional water system drain plumbing and changing the interconnecting wiring between the P141 panel and the P36 and P37 panels. For airplanes with a...
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Mars Gashopper Airplane, Phase I
National Aeronautics and Space Administration — The Mars Gas Hopper Airplane, or "gashopper" is a novel concept for propulsion of a robust Mars flight and surface exploration vehicle that utilizes indigenous CO2...
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Diagnosis and management of headache attributed to airplane travel.
Mainardi, Federico; Maggioni, Ferdinando; Lisotto, Carlo; Zanchin, Giorgio
2013-03-01
The headache attributed to airplane travel, also named "airplane headache", is characterized by the sudden onset of a severe head pain exclusively in relation to airplane flights, mainly during the landing phase. Secondary causes, such as upper respiratory tract infections or acute sinusitis, must be ruled out. Although its cause is not thoroughly understood, sinus barotrauma should be reasonably involved in the pathophysiological mechanisms. Furthermore, in the current International Classification of Headache Disorders, rapid descent from high altitude is not considered as a possible cause of headache, although the onset of such pain in airplane travellers or aviators has been well known since the beginning of the aviation era. On the basis of a survey we conducted with the courteous cooperation of people who had experienced this type of headache, we proposed diagnostic criteria to be added to the forthcoming revision of the International Classification of Headache Disorders. Their formal validation would favour further studies aimed at improving knowledge of the pathophysiological mechanisms involved and at implementing preventative measures.
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14 CFR 121.409 - Training courses using airplane simulators and other training devices.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Training courses using airplane simulators... Program § 121.409 Training courses using airplane simulators and other training devices. (a) Training courses utilizing airplane simulators and other training devices may be included in the certificate holder...
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77 FR 64693 - Airworthiness Directives; Hawker Beechcraft Corporation Airplanes
2012-10-23
... Directives; Hawker Beechcraft Corporation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... Beechcraft Corporation Model G58 airplanes. This AD was prompted by notification from Hawker Beechcraft Corporation that certain affected aircraft were produced with the incorrect gauge wiring installed. This AD...
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DEFF Research Database (Denmark)
Pommergaard, Hans-Christian; Burcharth, Jakob; Fischer, Anders
2013-01-01
Flatus is natural and an invariable consequence of digestion, however at times it creates problems of social character due to sound and odour. This problem may be more significant on commercial airplanes where many people are seated in limited space and where changes in volume of intestinal gases...
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International Nuclear Information System (INIS)
Cai Hancheng; Li Zibo; Conti, Peter S.
2011-01-01
Introduction: We and others have previously reported a four-step radiosynthesis of a series of 2'-deoxy-2'-[ 18 F]fluoro-5-substituted-1-β-D-arabinofuranosyluracil derivatives including [ 18 F]FAU, [ 18 F]FEAU, [ 18 F]FFAU, [ 18 F]FCAU, [ 18 F]FBAU and [ 18 F]FIAU as thymidine derivatives for tumor proliferation and/or reporter gene expression imaging with positron emission tomography (PET). Although the radiosynthesis has been proven to be reproducible and efficient, this complicated multistep reaction is difficult to incorporate into an automated cGMP-compliant radiosynthesis module for routine production. Recently, we have developed a simple and efficient one-pot method for routine production of [ 18 F]FMAU. In this study, we studied the feasibility of radiosynthesizing [ 18 F]FAU, [ 18 F]FEAU, [ 18 F]FFAU, [ 18 F]FCAU, [ 18 F]FBAU and [ 18 F]FIAU using this newly developed method. Methods: Similar to the radiosynthesis of [ 18 F]FMAU, 5-substituted 2'-[ 18 F]fluoro-2'-deoxy-arabinofuranosyluracil derivatives ([ 18 F]FAU, [ 18 F]FEAU, [ 18 F]FFAU, [ 18 F]FCAU, [ 18 F]FBAU and [ 18 F]FIAU) were synthesized in one-pot radiosynthesis module in the presence of Friedel-Crafts catalyst TMSOTf and HMDS. Results: This one-pot radiosynthesis method could be used to produce [ 18 F]FAU, [ 18 F]FEAU, [ 18 F]FFAU, [ 18 F]FCAU, [ 18 F]FBAU and [ 18 F]FIAU. The overall radiochemical yields of these tracers varied from 4.1%±0.8% to 10.1%±1.9% (decay-corrected, n=4). The overall reaction time was reduced from 210 min to 150 min from the end of bombardment, and the radiochemical purity was >99%. Conclusions: The improved radiosyntheses of [ 18 F]FAU, [ 18 F]FEAU, [ 18 F]FFAU, [ 18 F]FCAU, [ 18 F]FBAU and [ 18 F]FIAU have been achieved with reasonable yields and high purity using a multistep one-pot method. The synthetic time has been reduced, and the reaction procedures have been significantly simplified. The success of this approach may make PET tracers [ 18 F]FAU, [ 18 F
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Tumor VEGF-R2 imaging with Tc-99m DTPA-dextran-DC101
International Nuclear Information System (INIS)
Kim, E. M.; Jeong, H. J.; Kim, S. L.; Jeong, S. J.; Lee, C. M.; Kim, D. W.; Lim, S. T.; Sohn, M. H.
2007-01-01
Vascular endothelial growth factor (VEGF) and its receptor (fetal liver kinase 1/kinase insert domain-containing receptor) play an important role in vascular permeability and tumor angiogenesis. Here, we investigated the Tc-99m DC101-dextran for VEGF-R2 imaging in tumor xenografted mice. DTPA conjugated amino-dextran was synthesized and then this was reacted with sulfo-LC-SPDP. Synthesis was identified by 1H-NMR. DTPA-dextran-SPDP was reacted with DC101. Binding affinity was checked by ELISA assay. Female athymic nude mice bearing B16F10 tumors were each injected via the tail vein with about 18.5 MBq of the Tc-99m DTPA-dextran-DC101, Tc-99m DTPA-DC101 and I-131 DC101. Biodistribution was performed at 1, 6, and 24h. DTPA-dextran-DC101 bind to FLK-1 in a dose-dependent manner. And this was blocked by significantly by free DC101. Labeling efficiency was approximately above 99% at 24 hr. Tc-99m DTPA-DC101 and I-131 DC101 showed rapid liver uptake, whereas Tc-99m DTPA-dextran-DC101 weak liver uptake and kidney elimination. In biodistribution results, Tc-99m DTPA-dextran-DC101 showed rapid renal clearance, and increased tumor uptake according to the time. Conjugation of antibody with dextran polymer is responsible for the decreased liver uptake and increased tumor uptake
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Solar-Powered Airplane with Cameras and WLAN
Higgins, Robert G.; Dunagan, Steve E.; Sullivan, Don; Slye, Robert; Brass, James; Leung, Joe G.; Gallmeyer, Bruce; Aoyagi, Michio; Wei, Mei Y.; Herwitz, Stanley R.;
2004-01-01
An experimental airborne remote sensing system includes a remotely controlled, lightweight, solar-powered airplane (see figure) that carries two digital-output electronic cameras and communicates with a nearby ground control and monitoring station via a wireless local-area network (WLAN). The speed of the airplane -- typically <50 km/h -- is low enough to enable loitering over farm fields, disaster scenes, or other areas of interest to collect high-resolution digital imagery that could be delivered to end users (e.g., farm managers or disaster-relief coordinators) in nearly real time.
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STUDY OF THE AIR FLOWS AROUND AN AIRPLANE
Directory of Open Access Journals (Sweden)
Diaconescu Olivian
2013-06-01
Full Text Available This material presents a stage of the designing of an airplane capable to work with low capacity engines of 2.5 and 4 cmc namely the simulation of the air flow around the fuselage and the wings. The study proves the correctness of the choice made in the wing’s positioning and of the horizontal stabilizer of the airplane’s axis,for the chosen airplane type namely acrobat.
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STUDY OF THE AIR FLOWS AROUND AN AIRPLANE
Diaconescu Olivian
2013-01-01
This material presents a stage of the designing of an airplane capable to work with low capacity engines of 2.5 and 4 cmc namely the simulation of the air flow around the fuselage and the wings. The study proves the correctness of the choice made in the wing’s positioning and of the horizontal stabilizer of the airplane’s axis,for the chosen airplane type namely acrobat.
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Experimental determination of airplane mass and inertial characteristics
Wolowicz, C. H.; Yancey, R. B.
1974-01-01
Current practices are evaluated for experimentally determining airplane center of gravity, moments of inertia, and products of inertia. The techniques discussed are applicable to bodies other than airplanes. In pitching- and rolling-moment-of-inertia investigations with the airplane mounted on and pivoted about knife edges, the nonlinear spring moments that occur at large amplitudes of oscillation can be eliminated by using the proper spring configuration. The single-point suspension double-pendulum technique for obtaining yawing moments of inertia, products of inertia, and the inclination of the principal axis provides accurate results from yaw-mode oscillation data, provided that the sway-mode effects are minimized by proper suspension rig design. Rocking-mode effects in the data can be isolated.
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77 FR 58970 - Special Conditions: Embraer S.A. Model EMB-550 Airplanes, Sudden Engine Stoppage
2012-09-25
... primary structure is metal with composite empennage and control surfaces. The Model EMB-550 airplane is...: Cindy Ashforth, FAA, International Branch, ANM-116, Transport Airplane Directorate, Aircraft... conditions numbers 3 and 4, below) could allow some deformation in the engine-supporting structure (ultimate...
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78 FR 72554 - Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes
2013-12-03
... Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes AGENCY: Federal Aviation Administration... Gulfstream Aerospace Corporation Model GV and GV-SP airplanes. This AD was prompted by reports of two... Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, GA 31402-2206; telephone 800...
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77 FR 64695 - Airworthiness Directives; Hawker Beechcraft Corporation Airplanes
2012-10-23
... Airworthiness Directives; Hawker Beechcraft Corporation Airplanes AGENCY: Federal Aviation Administration (FAA... Hawker Beechcraft Corporation Model C90GTi (King Air) airplanes. This AD was prompted by reports of... service information identified in this AD, contact Hawker Beechcraft Corporation, 10511 E. Central Ave...
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Transformation of Helicopter PinS Procedures for Airplanes
Directory of Open Access Journals (Sweden)
Jakub Kraus
2013-09-01
Full Text Available This article deals with the possibility to use existing helicopter Point in Space procedures with minor changes for airplanes. The basis is to find parts of PinS procedures that need to be changed, suggest these changes, and then determine whether the revised procedures could be usable and could bring the benefits for airplane operations.
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75 FR 80735 - Special Conditions: Gulfstream Model GVI Airplane; High Incidence Protection
2010-12-23
... Special Conditions No. 25-10-03-SC] Special Conditions: Gulfstream Model GVI Airplane; High Incidence... airworthiness standards for transport category airplanes associated with the use of high incidence protection... transport airplane with an executive cabin interior. The maximum takeoff weight will be 99,600 pounds, with...
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75 FR 59658 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes
2010-09-28
... INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301... found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small Airplane...
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41 CFR 101-1.101 - Federal Property Management Regulations System.
2010-07-01
... 41 Public Contracts and Property Management 2 2010-07-01 2010-07-01 true Federal Property Management Regulations System. 101-1.101 Section 101-1.101 Public Contracts and Property Management Federal Property Management Regulations System FEDERAL PROPERTY MANAGEMENT REGULATIONS GENERAL 1-INTRODUCTION 1.1...
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41 CFR 101-30.101-13 - Management data.
2010-07-01
... 41 Public Contracts and Property Management 2 2010-07-01 2010-07-01 true Management data. 101-30....1-General § 101-30.101-13 Management data. Management data means recorded data that relate an item... of supply, or inventory control. Management data do not affect the identification of an item. [41 FR...
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78 FR 42895 - Airworthiness Directives; The Boeing Company Airplanes
2013-07-18
... intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support... FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los... support initiatives that will ensure the continued airworthiness of aging airplane structure. The last...
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77 FR 3585 - Airworthiness Directives; Cirrus Design Corporation Airplanes
2012-01-25
... Airworthiness Directives; Cirrus Design Corporation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... Corporation (Cirrus) Model SR22T airplanes. This AD was prompted by reports of partial loss of engine power.... ADDRESSES: For service information identified in this AD, contact Cirrus Design Corporation, 4515 Taylor...
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78 FR 47549 - Airworthiness Directives; The Boeing Company Airplanes
2013-08-06
... Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... to certain The Boeing Company Model 737-200, -200C, -300, and -400 series airplanes. AD 2000-06-13 R1..., adds inspections and related investigative and corrective actions, revises certain inspection types...
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77 FR 33083 - Airworthiness Directives; WACO Classic Aircraft Corporation Airplanes
2012-06-05
... Airworthiness Directives; WACO Classic Aircraft Corporation Airplanes AGENCY: Federal Aviation Administration... directive (AD) for certain WACO Classic Aircraft Corporation Models 2T-1A, 2T-1A-1, and 2T-1A-2 airplanes... information identified in this AD, contact WACO Classic Aircraft Corporation; 15955 South Airport Rd., Battle...
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Smith, W H
1919-01-01
Cellulose acetate and cellulose nitrate are the important constituents of airplane dopes in use at the present time, but planes were treated with other materials in the experimental stages of flying. The above compounds belong to the class of colloids and are of value because they produce a shrinking action on the fabric when drying out of solution, rendering it drum tight. Other colloids possessing the same property have been proposed and tried. In the first stages of the development of dope, however, shrinkage was not considered. The fabric was treated merely to render it waterproof. The first airplanes constructed were covered with cotton fabric stretched as tightly as possible over the winds, fuselage, etc., and flying was possible only in fine weather. The necessity of an airplane which would fly under all weather conditions at once became apparent. Then followed experiments with rubberized fabrics, fabrics treated with glue rendered insoluble by formaldehyde or bichromate, fabrics treated with drying and nondrying oils, shellac, casein, etc. It was found that fabrics treated as above lost their tension in damp weather, and the oil from the motor penetrated the proofing material and weakened the fabric. For the most part the film of material lacked durability. Cellulose nitrate lacquers, however were found to be more satisfactory under varying weather conditions, added less weight to the planes, and were easily applied. On the other hand, they were highly inflammable, and oil from the motor penetrated the film of cellulose nitrate, causing the tension of the fabric to be relaxed.
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Predicting Tail Buffet Loads of a Fighter Airplane
Moses, Robert W.; Pototzky, Anthony S.
2006-01-01
Buffet loads on aft aerodynamic surfaces pose a recurring problem on most twin-tailed fighter airplanes: During maneuvers at high angles of attack, vortices emanating from various surfaces on the forward parts of such an airplane (engine inlets, wings, or other fuselage appendages) often burst, immersing the tails in their wakes. Although these vortices increase lift, the frequency contents of the burst vortices become so low as to cause the aft surfaces to vibrate destructively. Now, there exists a new analysis capability for predicting buffet loads during the earliest design phase of a fighter-aircraft program. In effect, buffet pressures are applied to mathematical models in the framework of a finite-element code, complete with aeroelastic properties and working knowledge of the spatiality of the buffet pressures for all flight conditions. The results of analysis performed by use of this capability illustrate those vibratory modes of a tail fin that are most likely to be affected by buffet loads. Hence, the results help in identifying the flight conditions during which to expect problems. Using this capability, an aircraft designer can make adjustments to the airframe and possibly the aerodynamics, leading to a more robust design.
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F-15B ACTIVE with thrust vectoring nozzles on test stand
1995-01-01
This November 13, 1995, photograph of the F-15 Advanced Controls Technology for Integrated Vehicles (ACTIVE) at NASA's Dryden Flight Research Center, Edwards, California, shows the thrust stand being used for ground testing of a new thrust-vectoring concept involving two new Pratt & Whitney nozzles that can turn up to 20 degrees in any direction. These nozzles give the aircraft thrust control in the pitch (up and down) and yaw (left and right) directions. This will reduce drag and increase fuel economy or range as compared with conventional aerodynamic controls, which increase the retarding forces (drag) acting upon the aircraft. These tests could lead to significant performance increases for military and commercial aircraft. The research program is the product of a collaborative effort by NASA, the Air Force's Wright Laboratory, Pratt & Whitney, and McDonnell Douglas Aerospace.
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78 FR 12256 - Airworthiness Directives; Embraer S.A. Airplanes
2013-02-22
...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 and... unit (APU) electronic starter controller (ESC) power cables and the airplane tail cone firewall. This... written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed...
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Role of Meteorology in Flights of a Solar-Powered Airplane
Donohue, Casey
2004-01-01
In the summer of 2001, the Helios prototype solar-powered uninhabited aerial vehicle (UAV) [a lightweight, remotely piloted airplane] was deployed to the Pacific Missile Range Facility (PMRF), at Kauai, Hawaii, in an attempt to fly to altitudes above 100,000 ft (30.48 km). The goal of flying a UAV to such high altitudes has been designated a level-I milestone of the NASA Environmental Research Aircraft and Sensor Technology (ERAST) program. In support of this goal, meteorologists from NASA Dryden Flight Research Center were sent to PMRF, as part of the flight crew, to provide current and forecast weather information to the pilots, mission directors, and planners. Information of this kind is needed to optimize flight conditions for peak aircraft performance and to enable avoidance of weather conditions that could adversely affect safety. In general, the primary weather data of concern for ground and flight operations are wind speeds (see Figure 1). Because of its long wing span [247 ft (.75 m)] and low weight [1,500 to 1,600 lb (about 680 to 726 kg)], the Helios airplane is sensitive to wind speeds exceeding 7 kn (3.6 m/s) at the surface. Also, clouds are of concern because they can block sunlight needed to energize an array of solar photovoltaic cells that provide power to the airplane. Vertical wind shear is very closely monitored in order to prevent damage or loss of control due to turbulence.
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An Evaluation of Automatic Control System Concepts for General Aviation Airplanes
Stewart, E. C.
1990-01-01
A piloted simulation study of automatic longitudinal control systems for general aviation airplanes has been conducted. These automatic control systems were designed to make the simulated airplane easy to fly for a beginning or infrequent pilot. Different control systems are presented and their characteristics are documented. In a conventional airplane control system each cockpit controller commands combinations of both the airspeed and the vertical speed. The best system in the present study decoupled the airspeed and vertical speed responses to cockpit controller inputs. An important feature of the automatic system was that neither changing flap position nor maneuvering in steeply banked turns affected either the airspeed or the vertical speed. All the pilots who flew the control system simulation were favorably impressed with the very low workload and the excellent handling qualities of the simulated airplane.
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2011-05-04
... Memorandum ``Side-Facing Seats on Transport Category Airplanes'' and draft Issue Paper ``Dynamic Test...; Special Conditions No. 25-425-SC] Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane... are issued for the Gulfstream Aerospace LP (GALP) model G250 airplane. This airplane will have a novel...
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11 CFR 100.93 - Travel by airplane or other means of transportation.
2010-01-01
... 11 Federal Elections 1 2010-01-01 2010-01-01 false Travel by airplane or other means of... (2 U.S.C. 431) Exceptions to Contributions § 100.93 Travel by airplane or other means of... section applies to all campaign travelers who use: (i) An airplane not licensed by the Federal Aviation...
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Proton exchange membrane fuel cells for electrical power generation on-board commercial airplanes.
Energy Technology Data Exchange (ETDEWEB)
Curgus, Dita Brigitte; Munoz-Ramos, Karina (Sandia National Laboratories, Albuquerque, NM); Pratt, Joseph William; Akhil, Abbas Ali (Sandia National Laboratories, Albuquerque, NM); Klebanoff, Leonard E.; Schenkman, Benjamin L. (Sandia National Laboratories, Albuquerque, NM)
2011-05-01
Deployed on a commercial airplane, proton exchange membrane fuel cells may offer emissions reductions, thermal efficiency gains, and enable locating the power near the point of use. This work seeks to understand whether on-board fuel cell systems are technically feasible, and, if so, if they offer a performance advantage for the airplane as a whole. Through hardware analysis and thermodynamic and electrical simulation, we found that while adding a fuel cell system using today's technology for the PEM fuel cell and hydrogen storage is technically feasible, it will not likely give the airplane a performance benefit. However, when we re-did the analysis using DOE-target technology for the PEM fuel cell and hydrogen storage, we found that the fuel cell system would provide a performance benefit to the airplane (i.e., it can save the airplane some fuel), depending on the way it is configured.
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Proton Exchange Membrane Fuel Cells for Electrical Power Generation On-Board Commercial Airplanes
Energy Technology Data Exchange (ETDEWEB)
Pratt, Joesph W. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Klebanoff, Leonard E. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Munoz-Ramos, Karina [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Akhil, Abbas A. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Curgus, Dita B. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Schenkman, Benjamin L. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)
2011-05-01
Deployed on a commercial airplane, proton exchange membrane fuel cells may offer emissions reductions, thermal efficiency gains, and enable locating the power near the point of use. This work seeks to understand whether on-board fuel cell systems are technically feasible, and, if so, if they offer a performance advantage for the airplane as a whole. Through hardware analysis and thermodynamic and electrical simulation, we found that while adding a fuel cell system using today’s technology for the PEM fuel cell and hydrogen storage is technically feasible, it will not likely give the airplane a performance benefit. However, when we re-did the analysis using DOE-target technology for the PEM fuel cell and hydrogen storage, we found that the fuel cell system would provide a performance benefit to the airplane (i.e., it can save the airplane some fuel), depending on the way it is configured.
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Proton exchange membrane fuel cells for electrical power generation on-board commercial airplanes
International Nuclear Information System (INIS)
Pratt, Joseph W.; Klebanoff, Leonard E.; Munoz-Ramos, Karina; Akhil, Abbas A.; Curgus, Dita B.; Schenkman, Benjamin L.
2013-01-01
Highlights: ► We examine proton exchange membrane fuel cells on-board commercial airplanes. ► We model the added fuel cell system’s effect on overall airplane performance. ► It is feasible to implement an on-board fuel cell system with current technology. ► Systems that maximize waste heat recovery are the best performing. ► Current PEM and H 2 storage technology results in an airplane performance penalty. -- Abstract: Deployed on a commercial airplane, proton exchange membrane (PEM) fuel cells may offer emissions reductions, thermal efficiency gains, and enable locating the power near the point of use. This work seeks to understand whether on-board fuel cell systems are technically feasible, and, if so, if they could offer a performance advantage for the airplane when using today’s off-the-shelf technology. We also examine the effects of the fuel cell system on airplane performance with (1) different electrical loads, (2) different locations on the airplane, and (3) expected advances in fuel cell and hydrogen storage technologies. Through hardware analysis and thermodynamic simulation, we found that an additional fuel cell system on a commercial airplane is technically feasible using current technology. Although applied to a Boeing 787-type airplane, the method presented is applicable to other airframes as well. Recovery and on-board use of the heat and water that is generated by the fuel cell is an important method to increase the benefit of such a system. The best performance is achieved when the fuel cell is coupled to a load that utilizes the full output of the fuel cell for the entire flight. The effects of location are small and location may be better determined by other considerations such as safety and modularity. Although the PEM fuel cell generates power more efficiently than the gas turbine generators currently used, when considering the effect of the fuel cell system on the airplane’s overall performance we found that an overall
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Munk, Max M
1925-01-01
A formula for the computation of the vertical velocity component on all sides of an airplane is deduced and discussed. The formation is of value for the interpretation of such free flight tests where two airplanes fly alongside each other to facilitate observation.
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77 FR 2238 - Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes
2012-01-17
... attachment. If not corrected, this failure could result in loss of control of the airplane. We are issuing... the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City..., Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; email: [email protected
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78 FR 33193 - Airworthiness Directives; The Boeing Company Airplanes
2013-06-04
... modifications (such as the installation of felt on Model 767 airplanes per Figure 18 of Boeing Special Attention... information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management... Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE...
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77 FR 61548 - Airworthiness Directives; The Boeing Company Airplanes
2012-10-10
...-indicating and crew-alerting system (EICAS) messages ALT DISAGREE and IAS DISAGREE displayed. The flightcrew... Special Attention Service Bulletin 727-34-0245, dated June 4, 2008 (for Model airplanes); [[Page 61549... -200C series airplanes); and Boeing Special Attention Service Bulletin 747-34-2925, dated June 4, 2008...
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2010-01-01
... in the Airplane Flight Manual, allows the airplane to fly from the point where the two engines are... the Airplane Flight Manual, allows the airplane to fly from the point where the two engines are... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Large transport category airplanes: Turbine...
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14 CFR 26.39 - Newly produced airplanes: Fuel tank flammability.
2010-01-01
... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Newly produced airplanes: Fuel tank... Tank Flammability § 26.39 Newly produced airplanes: Fuel tank flammability. (a) Applicability: This... Series 767 Series (b) Any fuel tank meeting all of the criteria stated in paragraphs (b)(1), (b)(2) and...
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2011-11-21
...; Special Conditions No. 25-452-SC] Special Conditions: Gulfstream Aerospace Corporation, Model GVI Airplane... Aerospace Corporation Model GVI airplane. This airplane will have a novel or unusual design feature(s..., Gulfstream Aerospace Corporation (GAC) applied for an FAA type certificate for its new Model GVI passenger...
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14 CFR 121.407 - Training program: Approval of airplane simulators and other training devices.
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Training program: Approval of airplane... Program § 121.407 Training program: Approval of airplane simulators and other training devices. (a) Each airplane simulator and other training device that is used in a training course permitted under § 121.409...
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78 FR 41277 - Airworthiness Directives; Piper Aircraft, Inc. Airplanes
2013-07-10
... Airworthiness Directives; Piper Aircraft, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... certain Piper Aircraft, Inc. Models PA-46-310P, PA-46-350P, PA-46R-350T, and PA-46-500TP airplanes. This... through Friday, except Federal holidays. For service information identified in this AD, contact Piper...
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DEFF Research Database (Denmark)
Mardal, Marie; Aarestrup, Frank Møller; Rasmussen, Brian Schou
2017-01-01
to difficulties in obtaining samples. The aims of the study were to test the detectability of TD and ID in airplane wastewater samples categorized according to their geographical origin. Wastewater samples (n= 17) were collected from long-distance flights and prepared with enzymatic conjugate cleaving followed...... of the airplanes with therapeutic subgroup ATC codes as variables. Airplane wastewater analysis is useful for identifying targets for WBE and toxicological analysis and explore drug use and abuse patterns....
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Sensor equipment of the German earth scientific airplane program
Seige, P.
1975-01-01
The German airplane program for earth scientific research supports the work of a vast staff of earth scientists from universities and federal agencies. Due to their fields of interest, which are in oceanography, hydrology, geology, ecology, and forestry, five test areas were selected which are spread all over Germany. The sensor package, which was designed in accordance with the requirements of this group of scientists, will be installed in a DO 28 D2 type airplane. The sensor equipment consists of a series of 70-mm cameras having different film/filter combinations, a photogrammetric camera, an infrared radiometer, an 11-channel multispectral line scanner, a LANDSAT-compatible radiometer, and a complex avionic system. Along with the airplane, a truck will be equipped with a set of radiometers and other sensor devices for extensive ground-truth measurement; this also includes a cherry picker.
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Traian Vuia – the Romanian inventor who first flew a powered airplane in 1906
Directory of Open Access Journals (Sweden)
Liviu FILIMON
2011-09-01
Full Text Available As observed the beginning of heavier than air devices started with Wright Brothers who flew in 1903 the first catapulted airplane equipped with an engine, similar to present motor gliders. In March 1906 took place the first flight of Vuia’s monoplane using on board installations. Since then a real competition between manufacturers has started to improve their airplanes as they become more efficient. Traian Vuia’s first flights and his beginnings are explained below.
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Topological estimation of aerodynamic controlled airplane system functionality of quality
Directory of Open Access Journals (Sweden)
С.В. Павлова
2005-01-01
Full Text Available It is suggested to use topological methods for stage estimation of aerodynamic airplane control in widespread range of its conditions The estimation is based on normalized stage virtual non-isotropy of configurational airplane systems calculation.
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Performance of an Electro-Hydrostatic Actuator on the F-18 Systems Research Aircraft
Navarro, Robert
1997-01-01
An electro-hydrostatic actuator was evaluated at NASA Dryden Flight Research Center, Edwards, California. The primary goal of testing this actuator system was the flight demonstration of power-by-wire technology on a primary flight control surface. The electro-hydrostatic actuator uses an electric motor to drive a hydraulic pump and relies on local hydraulics for force transmission. This actuator replaced the F-18 standard left aileron actuator on the F-18 Systems Research Aircraft and was evaluated throughout the Systems Research Aircraft flight envelope. As of July 24, 1997 the electro-hydrostatic actuator had accumulated 23.5 hours of flight time. This paper presents the electro-hydrostatic actuator system configuration and component description, ground and flight test plans, ground and flight test results, and lessons learned. This actuator performs as well as the standard actuator and has more load capability than required by aileron actuator specifications of McDonnell- Douglas Aircraft, St. Louis, Missouri. The electro-hydrostatic actuator system passed all of its ground tests with the exception of one power-off test during unloaded dynamic cycling.
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14 CFR 121.505 - Flight time limitations: Two pilot crews: airplanes.
2010-01-01
...: airplanes. 121.505 Section 121.505 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Operations § 121.505 Flight time limitations: Two pilot crews: airplanes. (a) If a certificate holder conducting supplemental operations schedules a pilot to fly more than eight hours during any 24 consecutive...
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Burk, Sanger H., Jr.; Healy, Frederick M.
1955-01-01
An investigation of a l/21-scale model of the Chance Vought F7U-3 airplane in the co&at-load- condition has been conducted in the Langley 20-foot free-spinning tunnel, The recovery characteristics of the model were determined by use of spin-recovery rockets for the erect and inverted spinning condition. The rockets were so placed as to provide either a yawing or rolling moment about the model center of gravity. Also included in the investigation were tests to determine the effect of simulated engine thrust on the recovery characteristics of the model. On the basis of model tests, recoveries from erect and inverted spins were satisfactory when a yawing moment of 22,200 foot-pounds (full scale) was provided against the spin by rockets attached to the wing tips; the anti-spin yawing moment was applied for approximately 9 seconds, (full scale). Satisfactory recoveries were obtained from erect spins when a rolling moment of 22,200 foot-pounds (full scale) was provided with the spin (rolls right wing down in right spin). Although the inverted spin was satisfactorily terminated when a rolling moment of equal magnitude was provided, a roll rocket was not considered to be an optimum spin-recovery device to effect recoveries from inverted spins for this airplane because of resulting gyrations during spin recovery. Simulation of engine thrust had no apparent effect on the spin recovery characteristics.
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77 FR 54854 - Airworthiness Directives; The Boeing Company Airplanes
2012-09-06
.... Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New... 5 p.m., Monday through Friday, except Federal holidays. Boeing Commercial Airplanes, Attention: Data... airplanes), except as specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Steps 1 through 5 of Figure...
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2013-05-28
... Model EMB-550 airplane is the first of a new family of jet airplanes designed for corporate flight... inadvertent overspeed conditions as well. Section 25.335(b)(1) is intended as a conservative enveloping... or conservative aerodynamic data are used. (a) From an initial condition of stabilized flight at V C...
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International Nuclear Information System (INIS)
Jovall, Ola
2007-01-01
Impact loads are considered in nuclear facility design as the result of the loading effects of certain design basis accidents and design basis threats made up of natural as well as man-made hazards. Also, beyond design basis accidents and threats are considered. Typical missiles include objects caused by tornado winds, aircrafts, war or terrorist activities, dropped objects, turbine fragments and other missiles resulting from failure of rotating equipment and whipping pipes and other objects of failure of pressurized fluid systems. The aim of the work is to study the potential of tools for numerical simulations to study the local load effects of airplane missiles impacting concrete structures. Two of the leading commercial computer codes for analysis of highly dynamic events, ABAQUS/Explicit and AUTODYN, have been evaluated. Numerical simulations have been carried out for rigid as well as deformable missiles with the characteristics of airplane engines. The analysis results have been compared with test results from a test program performed in the USA at Sandia National Laboratory and in Japan at Kobori Research Complex and Central Research Institute of the Electric Power industry. Finally, numerical simulations of a large passenger airliner impacting a reactor containment has been carried out using the analysis methodology developed. (author)
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2013-01-24
.... The Model EMB-550 airplane is the first of a new family of jet airplanes designed for corporate flight... inadvertent overspeed conditions as well. Section 25.335(b)(1) is intended as a conservative enveloping... or conservative aerodynamic data are used. (a) From an initial condition of stabilized flight at V C...
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Airplane radiation dose decrease during a strong Forbush decrease
Czech Academy of Sciences Publication Activity Database
Spurný, František; Kudela, K.; Dachev, T.
2004-01-01
Roč. 2, S05001 (2004), s. 1-4 ISSN 1542-7390 Grant - others:EC project(XE) FIGM-CT2000-00068 Institutional research plan: CEZ:AV0Z1048901 Keywords : airplane dose * Forbush decrease * cosmic rays Subject RIV: BG - Nuclear, Atomic and Molecular Physics, Colliders
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77 FR 66417 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Airplanes
2012-11-05
... INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 [[Page 66418...: albert.mercado@faa.gov . SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written... Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri...
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2012-10-01
... should be flown into known icing. However, the original certification basis for these airplanes did not... equipment these airplanes may be qualified to fly into known light or moderate icing condition under 14 CFR... significant alternative to prohibiting the affected airplanes from flying into known icing conditions. And...
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User Manual for the AZ-101 Data Acquisition System (AS-101 DAS)
Energy Technology Data Exchange (ETDEWEB)
BRAYTON, D.D.
2000-02-17
User manual for the TK AZ-101 Waste Retrieval System Data Acquisition System. The purpose of this document is to describe use of the AZ-101 Data Acquisition System (AZ-101 DAS). The AZ-101 DAS is provided to fulfill the requirements for data collection and monitoring as defined in Letters of Instruction (LOI) from Numatec Hanford Corporation (NHC) to Fluor Federal Services (FFS). For a complete description of the system, including design, please refer to the AZ-101 DAS System Description document, RPP-5572.
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User Manual for the AZ-101 Data Acquisition System (AS-101 DAS)
International Nuclear Information System (INIS)
BRAYTON, D.D.
2000-01-01
User manual for the TK AZ-101 Waste Retrieval System Data Acquisition System. The purpose of this document is to describe use of the AZ-101 Data Acquisition System (AZ-101 DAS). The AZ-101 DAS is provided to fulfill the requirements for data collection and monitoring as defined in Letters of Instruction (LOI) from Numatec Hanford Corporation (NHC) to Fluor Federal Services (FFS). For a complete description of the system, including design, please refer to the AZ-101 DAS System Description document, RPP-5572
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Hinson, William F.; Lee, John B.
1959-01-01
As a continuation of an investigation of the release characteristics of an MB-1 rocket carried internally by the Convair F-106A airplane, six missile-bay baffle configurations and a rocket end plate have been investigated in the 27- by 27-inch preflight jet of the NASA Wallops Station. The MB-1 rocket used had retractable fins and was ejected from a missile bay modified by the addition of six different baffle configurations. For some tests a rocket end plate was added to the model. Dynamically scaled models (0.04956 scale) were tested at a simulated altitude of 22,450 feet and Mach numbers of 0.86, 1.59, and 1.98, and at a simulated altitude of 29,450 feet and a Mach number of 1.98. The results of this investigation indicate that the missile-bay baffle configurations and the rocket end plate may be used to reduce the positive pitch amplitude of the MB-1 rocket after release. The initial negative pitching velocity applied to the MB-1 rocket might then be reduced in order to maintain a near-level-flight attitude after release. As the fuselage angle of attack is increased, the negative pitch amplitude of the rocket is decreased.
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41 CFR 101-26.505-4-101-26.505-6 - [Reserved
2010-07-01
... 41 Public Contracts and Property Management 2 2010-07-01 2010-07-01 true [Reserved] 101-26.505-4-101-26.505-6 Section 101-26.505-4-101-26.505-6 Public Contracts and Property Management Federal Property Management Regulations System FEDERAL PROPERTY MANAGEMENT REGULATIONS SUPPLY AND PROCUREMENT 26...
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Quigley, Hervey C.; Anderson, Seth B.; Innis, Robert C.
1960-01-01
A flight investigation has been conducted to study how pilots use the high lift available with blowing-type boundary-layer control applied to the leading- and trailing-edge flaps of a 45 deg. swept-wing airplane. The study includes documentation of the low-speed handling qualities as well as the pilots' evaluations of the landing-approach characteristics. All the pilots who flew the airplane considered it more comfortable to fly at low speeds than any other F-100 configuration they had flown. The major improvements noted were the reduced stall speed, the improved longitudinal stability at high lift, and the reduction in low-speed buffet. The study has shown the minimum comfortable landing-approach speeds are between 120.5 and 126.5 knots compared to 134 for the airplane with a slatted leading edge and the same trailing-edge flap. The limiting factors in the pilots' choices of landing-approach speeds were the limits of ability to control flight-path angle, lack of visibility, trim change with thrust, low static directional stability, and sluggish longitudinal control. Several of these factors were found to be associated with the high angles of attack, between 13 deg. and 15 deg., required for the low approach speeds. The angle of attack for maximum lift coefficient was 28 deg.
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77 FR 60887 - Airworthiness Directives; Alpha Aviation Concept Limited Airplanes
2012-10-05
... Airworthiness Directives; Alpha Aviation Concept Limited Airplanes AGENCY: Federal Aviation Administration (FAA... directive (AD) for Alpha Aviation Concept Limited Model R2160 Airplanes. This AD results from mandatory... and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as...
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77 FR 44511 - Airworthiness Directives; Alpha Aviation Concept Limited Airplanes
2012-07-30
... Concept Limited Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... (AD) for Alpha Aviation Concept Limited Model R2160 Airplanes. This proposed AD results from mandatory... identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as...
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Piloted simulator study of allowable time delays in large-airplane response
Grantham, William D.; Bert T.?aetingas, Stephen A.dings with ran; Bert T.?aetingas, Stephen A.dings with ran
1987-01-01
A piloted simulation was performed to determine the permissible time delay and phase shift in the flight control system of a specific large transport-type airplane. The study was conducted with a six degree of freedom ground-based simulator and a math model similar to an advanced wide-body jet transport. Time delays in discrete and lagged form were incorporated into the longitudinal, lateral, and directional control systems of the airplane. Three experienced pilots flew simulated approaches and landings with random localizer and glide slope offsets during instrument tracking as their principal evaluation task. Results of the present study suggest a level 1 (satisfactory) handling qualities limit for the effective time delay of 0.15 sec in both the pitch and roll axes, as opposed to a 0.10-sec limit of the present specification (MIL-F-8785C) for both axes. Also, the present results suggest a level 2 (acceptable but unsatisfactory) handling qualities limit for an effective time delay of 0.82 sec and 0.57 sec for the pitch and roll axes, respectively, as opposed to 0.20 sec of the present specifications for both axes. In the area of phase shift between cockpit input and control surface deflection,the results of this study, flown in turbulent air, suggest less severe phase shift limitations for the approach and landing task-approximately 50 deg. in pitch and 40 deg. in roll - as opposed to 15 deg. of the present specifications for both axes.
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Gamma rays at airplane altitudes
International Nuclear Information System (INIS)
Iwai, J.; Koss, T.; Lord, J.; Strausz, S.; Wilkes, J.; Woosley, J.
1990-01-01
An examination of the gamma ray flux above 1 TeV in the atmosphere is needed to better understand the anomalous showers from point sources. Suggestions are made for future experiments on board airplanes
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2011-06-23
... Normal Electric Power AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final special... Interface Branch, ANM-111, Transport Standards Staff, Transport Airplane Directorate, Aircraft Certification... Model GVI airplane will be an all-new, two- engine jet transport airplane. The maximum takeoff weight...
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The Paper Airplane Challenge: A Market Economy Simulation. Lesson Plan.
Owens, Kimberly
This lesson plan features a classroom simulation that helps students understand the characteristics of a market economic system. The lesson plan states a purpose; cites student objectives; suggests a time duration; lists materials needed; and details a step-by-step teaching procedure. The "Paper Airplane Challenge" handout is attached. (BT)
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The development of coastal diffusion observation method with a model airplane
International Nuclear Information System (INIS)
Yamada, Masaharu; Fukuda, Masaaki
1982-01-01
A tethered ballon system has been developed in order to take aerial photograph of dye-cloud in times of coastal diffusion experiment. The system has some weakpoints; it can not be used both under strong wind and under on-shore blowing wind. To cover these wind conditions, another method of aerial photography is developed making use of model airplane. Radio controlled airplane on the market is reconstructed to mount 35 mm camera, the shutter of which is handled through the channel ordinarily used to control wheel logs. The procedure of the new system in case of diffusion experiment is similar to that of the tethered balloon system. Observations with this system has been carried out from winter to summer this year. Some results of them are described. (author)
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2010-01-01
... operating nontransport category airplanes type certificated after December 31, 1964, to fly for 30 minutes...-powered airplanes: Supplemental operations. 121.643 Section 121.643 Aeronautics and Space FEDERAL AVIATION... Flight Release Rules § 121.643 Fuel supply: Nonturbine and turbo-propeller-powered airplanes...
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2011-06-28
... Industries GmbH Model (Diamond) DA 40 Airplanes Equipped With Certain Cabin Air Conditioning Systems AGENCY... inspections of the Diamond Model DA 40 airplanes equipped with a VCS installed per Premier Aircraft Service... GmbH Model (Diamond) DA 40 Airplanes Equipped With Certain Cabin Air Conditioning Systems: Docket No...
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Private Pilot Practical Test Standards for Airplane (SEL, MEL, SES, MES)
1995-05-01
The Private Pilot - Airplane Practical Test Standards book has been : published by the Federal Aviation Administration (FAA) to establish the : standards for the private pilot certification practical tests for the airplane : category and the single-e...
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2012-11-20
... owner operations. The aircraft has a conventional configuration with low wing and T-tail empennage. The primary structure is metal with composite empennage and control surfaces. The Model EMB-550 airplane is...: Todd Martin, FAA, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft...
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Energy Technology Data Exchange (ETDEWEB)
Van Dokkum, Pieter G.; Merritt, Allison [Department of Astronomy, Yale University, New Haven, CT 06511 (United States); Abraham, Roberto [Department of Astronomy and Astrophysics, University of Toronto, 50 St. George Street, Toronto, ON M5S 3H8 (Canada)
2014-02-20
We use a new telescope concept, the Dragonfly Telephoto Array, to study the low surface brightness outskirts of the spiral galaxy M101. The radial surface brightness profile is measured down to μ {sub g} ∼ 32 mag arcsec{sup –2}, a depth that approaches the sensitivity of star count studies in the Local Group. We convert surface brightness to surface mass density using the radial g – r color profile. The mass density profile shows no significant upturn at large radius and is well-approximated by a simple bulge + disk model out to R = 70 kpc, corresponding to 18 disk scale lengths. Fitting a bulge + disk + halo model we find that the best-fitting halo mass M{sub halo}=1.7{sub −1.7}{sup +3.4}×10{sup 8} M {sub ☉}. The total stellar mass of M101 is M{sub tot,∗}=5.3{sub −1.3}{sup +1.7}×10{sup 10} M {sub ☉}, and we infer that the halo mass fraction f{sub halo}=M{sub halo}/M{sub tot,∗}=0.003{sub −0.003}{sup +0.006}. This mass fraction is lower than that of the Milky Way (f {sub halo} ∼ 0.02) and M31 (f {sub halo} ∼ 0.04). All three galaxies fall below the f {sub halo}-M {sub tot,} {sub *} relation predicted by recent cosmological simulations that trace the light of disrupted satellites, with M101's halo mass a factor of ∼10 below the median expectation. However, the predicted scatter in this relation is large, and more galaxies are needed to better quantify this possible tension with galaxy formation models. Dragonfly is well suited for this project: as integrated-light surface brightness is independent of distance, large numbers of galaxies can be studied in a uniform way.
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Trade Study of Multiple Thruster Options for the Mars Airplane Concept
Kuhl, Christopher A.; Gayle, Steven W.; Hunter, Craig A.; Kenney, Patrick S.; Scola, Salvatore; Paddock, David A.; Wright, Henry S.; Gasbarre, Joseph F.
2009-01-01
A trade study was performed at NASA Langley Research Center under the Planetary Airplane Risk Reduction (PARR) project (2004-2005) to examine the option of using multiple, smaller thrusters in place of a single large thruster on the Mars airplane concept with the goal to reduce overall cost, schedule, and technical risk. The 5-lbf (22N) thruster is a common reaction control thruster on many satellites. Thousands of these types of thrusters have been built and flown on numerous programs, including MILSTAR and Intelsat VI. This study has examined the use of three 22N thrusters for the Mars airplane propulsion system and compared the results to those of the baseline single thruster system.
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Tuck, S F; Graham-Lorence, S; Peterson, J A; Ortiz de Montellano, P R
1993-01-05
Ferricyanide oxidation of the aryl-iron complexes formed by the reaction of cytochrome P450 enzymes with arylhydrazines causes in situ migration of the aryl group from the iron to the porphyrin nitrogen atoms. The regiochemistry of this migration, defined by the ratio of the four possible N-arylprotoporphyrin IX isomers, provides a method for mapping the topologies of cytochrome P450 active sites. The method has been validated by using it to examine the active site of cytochrome P450cam (CYP101), for which a crystal structure is available. In agreement with the crystal structure, reaction with phenylhydrazine gives a 5:25:70 ratio of the NA:NC:ND (subscript indicates pyrrole ring) N-phenylprotoporphyrin IX isomers. Naphthylhydrazine, however, yields exclusively the NC regioisomer and 4-(phenyl)phenylhydrazine the NA:NC:ND isomers in a 14:40:46 ratio. These isomer ratio differences are readily explained by topological differences between the upper and lower reaches of the active site. Having validated the aryl-iron shift as a topological probe, we used it to investigate the structural changes caused by mutation of Phe-87, a residue that provides the ceiling over pyrrole ring D in the crystal structure of cytochrome P450cam. Mutation of Phe-87 to a tryptophan causes no detectable change in the regiochemistry of camphor hydroxylation and only minor changes in the N-aryl isomer ratios. However, mutation of Phe-87 to an alanine, which was expected to open up the region above pyrrole ring D, severely decreased the proportion of the ND in favor of the NA isomer. Less rather than more space is therefore available over pyrrole ring D in the F87A mutant despite the fact that the regiochemistry of camphor hydroxylation remains unchanged. These results provide evidence for significant structural reorganization in the upper regions of the substrate binding site without alteration of the camphor hydroxylation regiospecificity in the F87A mutant.
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Rohnke, M.; Schaepe, K.; Bachmann, A.-K.; Laenger, M.; Janek, J.
2017-11-01
The modelling of electrode kinetics of solid oxide fuel cells is challenging, as the electrodes can change their composition and microstructure during operation at high temperature. Here we present results from in situ studies, applying time of flight secondary ion mass spectrometry (ToF-SIMS) to investigate compositional surface changes of lanthanum strontium manganate (LSM) model electrodes. Geometrically well-defined LSM electrodes with the composition La0.74Sr0.17Mn1.01O2.9 were deposited as thin films on yttria stabilised zirconia (YSZ) single crystals by pulsed laser deposition. As counter electrode, a porous platinum electrode was applied on the backside of the solid electrolyte. The electrochemical polarisation experiments were carried out inside the ToF-SIMS analysis chamber at 430 °C, and the ToF-SIMS measurements were performed - in contrast to former work - for the first time during electrical polarisation at elevated temperatures. By applying either a cathodic or anodic potential to the LSM cathode, enrichment or depletion of the different metallic constituents on both, the LSM and free YSZ surface, and within the LSM near surface region, were observed. After polarisation, the system relaxes towards the thermodynamic equilibrium state. Already after the first heat treatment, diffusion of manganese and strontium from the LSM electrode onto the free YSZ surface is observed. The concomitant spreading of the three-phase boundary seems to be one reason for electrode activation after polarisation.
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76 FR 17022 - Special Conditions: Gulfstream Model GVI Airplane; High Incidence Protection
2011-03-28
... Special Conditions No. 25-423-SC] Special Conditions: Gulfstream Model GVI Airplane; High Incidence... for transport category airplanes associated with the use of high incidence protection. The applicable... with an executive cabin interior. The maximum takeoff weight will be 99,600 pounds, with a maximum...
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Analysis of BmNPV orf101 disruption: orf101 is essential for mediating budded virus production.
Chen, Huiqing; Li, Mei; Mai, Weijun; Tang, Qi; Li, Guohui; Chen, Keping; Zhou, Yajing
2014-12-01
In our previous study, Orf101 (Bm101) of Bombyx mori nucleopolyhedrovirus (BmNPV) was identified as a component of the budded virions important for viral late gene expression. In this study we demonstrate that Bm101 is actually a previously unrecognized core gene and that it is essential for mediating budded virus production. To determine the role of Bm101 in the baculovirus life cycle, a Bm101 knockout bacmid containing the BmNPV genome was generated through homologous recombination in Escherichia coli. Furthermore, a Bm101 repair bacmid was constructed by transposing the Bm101 open reading frame with its native promoter region into the polyhedrin locus of the Bm101 knockout bacmid. Bacmid DNA transfection assay revealed that the Bm101 knockout bacmid was unable to produce the infectious budded virus, while the Bm101 repair bacmid rescued this defect, allowing budded-virus titers to reach wild-type levels. Real time PCR analysis indicated that the viral DNA genome in the absence of Bm101 was unaffected in the first 24 h p.t. Thus, studies of a Bm101-null BACmid indicate that Bm101 is required for viral DNA replication during the infection cycle.
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2013-12-19
... Series Airplanes; Seats With Non-Traditional, Large, Non- Metallic Panels AGENCY: Federal Aviation... airplanes will have a novel or unusual design feature associated with seats that include non-traditional... base and significant common design elements. The fuselage is aluminum alloy material, blended double...
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76 FR 41659 - Airworthiness Directives; The Boeing Company Model 747 Airplanes
2011-07-15
... sleeving; and repair or replacement of any damaged wires with new wires. For airplanes on which any burned.... For airplanes on which any burned wires are found, that NPRM also proposed to continue to require an...-28A2204 may be used. (k) If any burned wire is found, prior to further flight, perform an inspection to...
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A Conceptual Design and Analysis Method for Conventional and Unconventional Airplanes
Elmendorp, R.J.M.; Vos, R.; La Rocca, G.
2014-01-01
A design method is presented that has been implemented in a software program to investigate the merits of conventional and unconventional transport airplanes. Design and analysis methods are implemented in a design tool capable of creating a conceptual design based on a set of toplevel requirements.
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Simulated airplane headache: a proxy towards identification of underlying mechanisms.
Bui, Sebastian Bao Dinh; Petersen, Torben; Poulsen, Jeppe Nørgaard; Gazerani, Parisa
2017-12-01
Airplane Headache (AH) occurs during flights and often appears as an intense, short lasting headache during take-off or landing. Reports are limited on pathological mechanisms underlying the occurrence of this headache. Proper diagnosis and treatments would benefit from identification of potential pathways involved in AH pathogenesis. This study aimed at providing a simulated airplane headache condition as a proxy towards identification of its underlying mechanisms. Fourteen participants including 7 volunteers suffering from AH and 7 healthy matched controls were recruited after meeting the diagnostic and safety criteria based on an approved study protocol. Simulation of AH was achieved by entering a pressure chamber with similar characteristics of an airplane flight. Selected potential biomarkers including salivary prostaglandin E 2 (PGE 2 ), cortisol, facial thermo-images, blood pressure, pulse, and saturation pulse oxygen (SPO) were defined and values were collected before, during and after flight simulation in the pressure chamber. Salivary samples were analyzed with ELISA techniques, while data analysis and statistical tests were handled with SPSS version 22.0. All participants in the AH-group experienced a headache attack similar to AH experience during flight. The non-AH-group did not experience any headaches. Our data showed that the values for PGE 2 , cortisol and SPO were significantly different in the AH-group in comparison with the non-AH-group during the flight simulation in the pressure chamber. The pressure chamber proved useful not only to provoke AH-like attack but also to study potential biomarkers for AH in this study. PGE 2 , and cortisol levels together with SPO presented dysregulation during the simulated AH-attack in affected individuals compared with healthy controls. Based on these findings we propose to use pressure chamber as a model to induce AH, and thus assess new potential biomarkers for AH in future studies.
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Skoog, Richard B
1951-01-01
A theoretical analysis of the effects of aeroelasticity on the stick-fixed static longitudinal stability and elevator angle required for balance of an airplane is presented together with calculated effects for a swept-wing bomber of relatively high flexibility. Although large changes in stability due to certain parameters are indicated for the example airplane, the over-all stability change after considering all parameters was quite small, compared to the individual effects, due to the counterbalancing of wing and tail contributions. The effect of flexibility on longitudinal control for the example airplane was found to be of little real importance.
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System Description for Tank 241-AZ-101 Waste Retrieval Data Acquisition System
International Nuclear Information System (INIS)
ROMERO, S.G.
2000-01-01
The proposed activity provides the description of the Data Acquisition System for Tank 241-AZ-101. This description is documented in HNF-5572, Tank 241-AZ-101 Waste Retrieval Data Acquisition System (DAS). This activity supports the planned mixer pump tests for Tank 241-AZ-101. Tank 241-AZ-101 has been selected for the first full-scale demonstration of a mixer pump system. The tank currently holds over 960,000 gallons of neutralized current acid waste, including approximately 12.7 inches of settling solids (sludge) at the bottom of the tank. As described in Addendum 4 of the FSAR (LMHC 2000a), two 300 HP mixer pumps with associated measurement and monitoring equipment have been installed in Tank 241-AZ-101. The purpose of the Tank 241-AZ-101 retrieval system Data Acquisition System (DAS) is to provide monitoring and data acquisition of key parameters in order to confirm the effectiveness of the mixer pumps utilized for suspending solids in the tank. The suspension of solids in Tank 241-AZ-101 is necessary for pretreatment of the neutralized current acid waste and eventual disposal as glass via the Hanford Waste Vitrification Plant. HNF-5572 provides a basic description of the Tank 241-AZ-101 retrieval system DAS, including the field instrumentation and application software. The DAS is provided to fulfill requirements for data collection and monitoring. This document is not an operations procedure or is it intended to describe the mixing operation. This USQ screening provides evaluation of HNF-5572 (Revision 1) including the changes as documented on ECN 654001. The changes include (1) add information on historical trending and data backup, (2) modify DAS I/O list in Appendix E to reflect actual conditions in the field, and (3) delete IP address in Appendix F per Lockheed Martin Services, Inc. request
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Kuhl. Christopher A.
2009-01-01
The Aerial Regional-Scale Environmental Survey (ARES) is a Mars exploration mission concept with the goal of taking scientific measurements of the atmosphere, surface, and subsurface of Mars by using an airplane as the payload platform. ARES team first conducted a Phase-A study for a 2007 launch opportunity, which was completed in May 2003. Following this study, significant efforts were undertaken to reduce the risk of the atmospheric flight system, under the NASA Langley Planetary Airplane Risk Reduction Project. The concept was then proposed to the Mars Scout program in 2006 for a 2011 launch opportunity. This paper summarizes the design and development of the ARES airplane propulsion subsystem beginning with the inception of the ARES project in 2002 through the submittal of the Mars Scout proposal in July 2006.
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Comparison of portable oxygen concentrators in a simulated airplane environment.
Fischer, Rainald; Wanka, Eva R; Einhaeupl, Franziska; Voll, Klaus; Schiffl, Helmut; Lang, Susanne M; Gruss, Martin; Ferrari, Uta
2013-01-01
Portable oxygen concentrators (POC) are highly desirable for patients with lung disease traveling by airplane, as these devices allow theoretically much higher travel times if additional batteries can be used. However, it is unclear whether POCs produce enough oxygen in airplanes at cruising altitude, even if complying with aviation regulations. We evaluated five frequently used POCs (XPO2 (Invacare, USA), Freestyle (AirSep C., USA), Evergo (Philipps Healthcare, Germany), Inogen One (Inogen, USA), Eclipse 3 (Sequal, USA)) at an altitude of 2650 m (as simulated airplane environment) in 11 patients with chronic obstructive lung disease (COPD) and compared theses POCs with the standard oxygen system (WS120, EMS Ltd., Germany) used by Lufthansa. Oxygen was delivered by each POC for 30 min to each patient at rest, blood gases were then drawn from the arterialized ear lobe. All POCs were able to deliver enough oxygen to increase the PaO(2) of our subjects by at least 1.40 kPa (10 mmHg). However, to achieve this increase, the two most lightweight POCs (Freestyle and Invacare XPO2) had to be run at their maximum level. This causes a significant reduction of battery life. The three other POCs (EverGo, Inogen One, Eclipse 3) and the WS120 were able to increase the PaO(2) by more than 2.55 kPa (20 mmHg), which provides extra safety for patients with more severe basal hypoxemia. When choosing the right oxygen system for air travel in patients in COPD, not only weight, but also battery life and maximum possible oxygen output must be considered carefully. Copyright © 2012 Elsevier Ltd. All rights reserved.
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Fuel-Cell-Powered Electric Motor Drive Analyzed for a Large Airplane
Brown, Gerald V.; Choi, Benjamin B.
2005-01-01
Because of its high efficiency, fuel cell technology may be used to launch a new generation of more-electric aeropropulsion and power systems for future aircraft. Electric-motor-driven airplanes using fuel-cell powerplants would be beneficial to the environment because of fuel savings, low noise, and zero carbon-dioxide emissions. In spite of the fuel cell s efficiency benefit, to produce the same shaft drive power, a fuel cell- powered electric-drive system must be definitely heavier than a turbine-drive system. However, the fuel-cell system s overall efficiency from fuel-to-shaft power is higher than for a turbine-drive system. This means that the fuel consumption rate could be lower than for a conventional system. For heavier, fuel-laden planes for longer flights, we might achieve substantial fuel savings. In the airplane industry, in fact, an efficiency gain of even a few percentage points can make a major economic difference in operating costs.
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International Nuclear Information System (INIS)
HICKMAN, G.L.
2000-01-01
The lower temperature limit for the 241 SY-101 RAPID transfer project is currently set at 20 F Based on the analysis and recommendations in this document this limit can be lowered to 0 F. Analysis of all structures systems and components (SSCs) indicate that a reduction in operating temperature may be achieved with minor modifications to field-installed equipment. Following implementation of these changes it is recommended that the system requirements be amended to specify a temperature range for transfer or back dilute evolutions of 0 F to 100 F
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2011-10-27
... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. FAA-2011-1172: Notice No. 25-11-17-SC] Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane... Aerospace LP (GALP) Model G280 airplane. This airplane will have a novel or unusual design feature...
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Small-scale fixed wing airplane software verification flight test
Miller, Natasha R.
The increased demand for micro Unmanned Air Vehicles (UAV) driven by military requirements, commercial use, and academia is creating a need for the ability to quickly and accurately conduct low Reynolds Number aircraft design. There exist several open source software programs that are free or inexpensive that can be used for large scale aircraft design, but few software programs target the realm of low Reynolds Number flight. XFLR5 is an open source, free to download, software program that attempts to take into consideration viscous effects that occur at low Reynolds Number in airfoil design, 3D wing design, and 3D airplane design. An off the shelf, remote control airplane was used as a test bed to model in XFLR5 and then compared to flight test collected data. Flight test focused on the stability modes of the 3D plane, specifically the phugoid mode. Design and execution of the flight tests were accomplished for the RC airplane using methodology from full scale military airplane test procedures. Results from flight test were not conclusive in determining the accuracy of the XFLR5 software program. There were several sources of uncertainty that did not allow for a full analysis of the flight test results. An off the shelf drone autopilot was used as a data collection device for flight testing. The precision and accuracy of the autopilot is unknown. Potential future work should investigate flight test methods for small scale UAV flight.
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A technology development summary for the AGT101 Advanced Gas Turbine Program
Energy Technology Data Exchange (ETDEWEB)
Boyd, G.L.; Kidwell, J.R.; Kreiner, D.M.
1987-01-01
Since the program initiation in October 1979, the Garrett/Ford Advanced Gas Turbine Program, designated AGT101, has made significant progress in developing ceramic technology for gas turbine applications. Successful component development has resulted in engine tests with an all ceramic hot section to temperatures up to 2200F (1204C) and full speed operation to 100,000 rpm (turbine rotor tip speed of 2300 ft/sec (701 m/s)). An 85-hour test was performed on an all ceramic engine at 2200F (1204C) turbine inlet temperature. These engine tests represent important first steps in the development of ceramic materials and technology. Engine evaluation was preceded by important component development. Activities included aerodynamic component evaluation and development of a high temperature foil bearing to support the ceramic turbine rotor. Development of low leakage regenerator seals and static ceramic seals in this high temperature environment were critical to engine performance.
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2011-07-13
... Conditions No. 25-439-SC] Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane, Interaction... special conditions are issued for the Gulfstream Aerospace LP (GALP) Model G250 airplane. This airplane...
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Tanner, J. A.; Stubbs, S. M.; Dreher, R. C.; Smith, E. G.
1982-01-01
A computer study was performed to assess the accuracy of three brake pressure-torque mathematical models. The investigation utilized one main gear wheel, brake, and tire assembly of a McDonnell Douglas DC-9 series 10 airplane. The investigation indicates that the performance of aircraft antiskid braking systems is strongly influenced by tire characteristics, dynamic response of the antiskid control valve, and pressure-torque response of the brake. The computer study employed an average torque error criterion to assess the accuracy of the models. The results indicate that a variable nonlinear spring with hysteresis memory function models the pressure-torque response of the brake more accurately than currently used models.
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Hastings, Earl C., Jr.; Dickens, Waldo L.
1957-01-01
A flight investigation was conducted to determine the effects of inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model between Mach Numbers of 0.81 and 1.64. This paper presents the changes in trim angle of attack, trim lift coefficient, and low-lift drag caused by the modified inlets alone over a small part of the test Mach number range and by a combination of the modified inlets and extended rocket racks throughout the remainder of the test.
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Carter, John F.
1997-01-01
NASA Dryden Flight Research Center (DFRC) is working with the United States Navy to complete ground testing and initiate flight testing of a modified set of F/A-18 flight control computers. The Production Support Flight Control Computers (PSFCC) can give any fleet F/A-18 airplane an in-flight, pilot-selectable research control law capability. NASA DFRC can efficiently flight test the PSFCC for the following four reasons: (1) Six F/A-18 chase aircraft are available which could be used with the PSFCC; (2) An F/A-18 processor-in-the-loop simulation exists for validation testing; (3) The expertise has been developed in programming the research processor in the PSFCC; and (4) A well-defined process has been established for clearing flight control research projects for flight. This report presents a functional description of the PSFCC. Descriptions of the NASA DFRC facilities, PSFCC verification and validation process, and planned PSFCC projects are also provided.
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78 FR 40642 - Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes
2013-07-08
... landing gear attachment lever causes the rod end to bend at each gear retraction sequence. We are issuing... Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this... Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone...
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78 FR 59223 - Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes
2013-09-26
... safety washer and the nose landing gear attachment lever causes the rod end to bend at each gear... information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information...: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City...
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14 CFR Appendix E to Part 91 - Airplane Flight Recorder Specifications
2010-01-01
... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Airplane Flight Recorder Specifications E Appendix E to Part 91 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION... Appendix E to Part 91—Airplane Flight Recorder Specifications Parameters Range Installed system 1 minimum...
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14 CFR Appendix B to Part 135 - Airplane Flight Recorder Specifications
2010-01-01
... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specifications B Appendix B to Part 135 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION.... B Appendix B to Part 135—Airplane Flight Recorder Specifications Parameters Range Installed system 1...
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78 FR 11978 - Airworthiness Directives; Reims Aviation S.A. Airplanes
2013-02-21
... used in nose landing gear (NLG) attachment brackets could lead to failure of the NLG bracket with... referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri..., Kansas City, Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; email: [email protected]..
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78 FR 275 - Airworthiness Directives; REIMS Aviation S.A. Airplanes
2013-01-03
... INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; email: albert.mercado@faa... requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace...
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Zabinsky, J. M.; Burnham, R. W.; Flora, C. C.; Gotlieb, P.; Grande, D. L.; Gunnarson, D. W.; Howard, W. M.; Hunt, D.; Jakubowski, G. W.; Johnson, P. E.
1975-01-01
An assessment of risk, in terms of delivery delays, cost overrun, and performance achievement, associated with the V/STOL technology airplane is presented. The risk is discussed in terms of weight, structure, aerodynamics, propulsion, mechanical drive, and flight controls. The analysis ensures that risks associated with the design and development of the airplane will be eliminated in the course of the program and a useful technology airplane that meets the predicted cost, schedule, and performance can be produced.
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Modelling and Simulation of Fuel Cell Dynamics for Electrical Energy Usage of Hercules Airplanes
Directory of Open Access Journals (Sweden)
Hamid Radmanesh
2014-01-01
Full Text Available 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.
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Dorpinghaus, R.
1982-01-01
A single engine two passenger airplane, constructed completely from fiber reinforced plastic materials is introduced. The cockpit, controls, wing profile, and landing gear are discussed. Development of the airframe is also presented.
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Gouweloos, Juul; Postma, Ingri L. E.; Te Brake, Hans; Sijbrandij, Marit; Kleber, Rolf J.; Goslings, J. Carel
2016-01-01
In 2009, a commercial airplane crashed near Amsterdam. This longitudinal study aims to investigate (1) the proportion of survivors of the airplane crash showing a probable posttraumatic stress disorders (PTSD) or depressive disorder, and (2) whether symptoms of PTSD and depression were predicted by
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Gouweloos, J.; Postma, Ingri L.E.; Te Brake, Hans; Sijbrandij, E.M.; Kleber, R.J.; Goslings, J. Carel
In 2009, a commercial airplane crashed near Amsterdam. This longitudinal study aims to investigate (1) the proportion of survivors of the airplane crash showing a probable posttraumatic stress disorders (PTSD) or depressive disorder, and (2) whether symptoms of PTSD and depression were predicted by
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Gouweloos, J.; Postma, I.L.; te Brake, H.; Sijbrandij, M.; Kleber, R.; Goslings, J.C.
2016-01-01
In 2009, a commercial airplane crashed near Amsterdam. This longitudinal study aims to investigate (1) the proportion of survivors of the airplane crash showing a probable posttraumatic stress disorders (PTSD) or depressive disorder, and (2) whether symptoms of PTSD and depression were predicted by
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Velocity estimation of an airplane through a single satellite image
Institute of Scientific and Technical Information of China (English)
Zhuxin Zhao; Gongjian Wen; Bingwei Hui; Deren Li
2012-01-01
The motion information of a moving target can be recorded in a single image by a push-broom satellite. A push-broom satellite image is composed of many image lines sensed at different time instants. A method to estimate the velocity of a flying airplane from a single image based on the imagery model of the linear push-broom sensor is proposed. Some key points on the high-resolution image of the plane are chosen to determine the velocity (speed and direction). The performance of the method is tested and verified by experiments using a WorldView-1 image.%The motion information of a moving target can be recorded in a single image by a push-broom satellite.A push-broom satellite image is composed of many image lines sensed at different time instants.A method to estimate the velocity of a flying airplane from a single image based on the imagery model of the linear push-broom sensor is proposed.Some key points on the high-resolution image of the plane are chosen to determine the velocity (speed and direction).The performance of the method is tested and verified by experiments using a WorldView-1 image.
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Rapid Airplane Parametric Input Design(RAPID)
Smith, Robert E.; Bloor, Malcolm I. G.; Wilson, Michael J.; Thomas, Almuttil M.
2004-01-01
An efficient methodology is presented for defining a class of airplane configurations. Inclusive in this definition are surface grids, volume grids, and grid sensitivity. A small set of design parameters and grid control parameters govern the process. The general airplane configuration has wing, fuselage, vertical tail, horizontal tail, and canard components. The wing, tail, and canard components are manifested by solving a fourth-order partial differential equation subject to Dirichlet and Neumann boundary conditions. The design variables are incorporated into the boundary conditions, and the solution is expressed as a Fourier series. The fuselage has circular cross section, and the radius is an algebraic function of four design parameters and an independent computational variable. Volume grids are obtained through an application of the Control Point Form method. Grid sensitivity is obtained by applying the automatic differentiation precompiler ADIFOR to software for the grid generation. The computed surface grids, volume grids, and sensitivity derivatives are suitable for a wide range of Computational Fluid Dynamics simulation and configuration optimizations.
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75 FR 77793 - Airworthiness Directives; The Boeing Company Model 747 Airplanes
2010-12-14
... airplanes on which any burned wires are found, the existing AD also requires an inspection to detect damage... wires. For airplanes on which any burned wires are found, that AD also requires an inspection to detect... any burned wire is found, prior to further flight, perform an inspection to detect damage of the...
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Response of equipment in nuclear power plants to airplane crash
International Nuclear Information System (INIS)
Schalk, M.; Woelfel, H.
1976-01-01
Nuclear power plants in Germany are to be designed against airplane crash. Two problems arise: first, the local problem of penetration as well as local destruction of the building and secondly the airplane induced vibrations of the whole building which cause loadings for secondary systems (equipment). This paper deals especially with the second problem. Floor response spectra due to airplane crash are presented for two different power plant buildings. The influence of various parameters (time history of excitation, direction and location of impact, mathematical model, soil, damping, etc.) are discussed. A comparison with the results of earthquake loading is given. Suggestions are made for developing suitable floor design spectra and using them to analyse multidegree-of-freedom systems. However, the paper gives only a partial answer to the questions arising because of some important restrictions which had to be made. Studies concerning these restrictions are still being conducted and will be presented in a separate paper. (Auth.)
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75 FR 20265 - Airworthiness Directives; Liberty Aerospace Incorporated Model XL-2 Airplanes
2010-04-19
... Office, 1701 Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474-5524; facsimile: (404... Airworthiness Directives; Liberty Aerospace Incorporated Model XL-2 Airplanes AGENCY: Federal Aviation...-08- 05, which applies to certain Liberty Aerospace Incorporated Model XL-2 airplanes. AD 2009-08-05...
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Analysis of means of improving the uncontrolled lateral motions of personal airplanes
Mckinney, Marion O , Jr
1951-01-01
A theoretical analysis has been made of means of improving the uncontrolled motions of personal airplanes. The purpose of this investigation was to determine whether such airplanes could be made to fly uncontrolled for an indefinite period of time without getting into dangerous attitudes and for a reasonable period of time (1 to 3 min) without deviating excessively from their original course. The results of this analysis indicated that the uncontrolled motions of a personal airplane could be made safe as regards spiral tendencies and could be greatly improved as regards maintenance of course without resort to an autopilot. The only way to make the uncontrolled motions completely satisfactory as regards continuous maintenance of course, however, is to use a conventional type of autopilot.
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2013-10-31
... provide different levels of protection from post-crash fire threats than similar aircraft constructed from... turbofan engines. Flight controls are fly-by-wire systems with two passive/uncoupled side sticks. Avionics... models of airplanes. Maximum operating altitude is 41,000 feet for both models of airplanes. The fuselage...
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DEFF Research Database (Denmark)
Høyer, Christian Bjerre; Nielsen, Trine Skov; Nagel, Lise Loft
2012-01-01
A fatal accident is reported in which a small single-engine light airplane crashed. The airplane carried two persons in the front seats, both of whom possessed valid pilot certificates. Both victims were subject to autopsy, including post-mortem computed tomography scanning (PMCT) prior...... to the autopsy. The autopsies showed massive destruction to the bodies of the two victims but did not identify any signs of acute or chronic medical conditions that could explain loss of control of the airplane. PMCT, histological examination, and forensic chemical analysis also failed to identify an explanation...... for the crash. A detailed review of an airplane identical to the crashed airplane was performed in collaboration with the Danish Accident Investigation Board and the Danish National Police, National Centre of Forensic Services. The injuries were described using the abbreviated injury scale, the injury severity...
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76 FR 35344 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Model P2006T Airplanes
2011-06-17
... FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901.... Send information to Attn: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901...
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2010-12-21
... Airworthiness Directives; DASSAULT AVIATION Model Falcon 10 Airplanes; Model FAN JET FALCON, FAN JET FALCON.... (1) DASSAULT AVIATION Model Falcon 10 airplanes, Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E... airplanes Inspection threshold (whichever occurs later) Inspection interval Model FAN JET FALCON, FAN JET...
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75 FR 61655 - Airworthiness Directives; Piper Aircraft, Inc. Model PA-28-161 Airplanes
2010-10-06
...-1006; Directorate Identifier 2009-CE-057-AD] RIN 2120-AA64 Airworthiness Directives; Piper Aircraft... airworthiness directive (AD) for all Piper Aircraft, Inc. (Piper) Model PA-28-161 airplanes equipped with.... Piper Model PA-28-161 airplanes modified by STC No. SA03303AT have a similar unsafe design feature that...
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Effects of road traffic background noise on judgments of individual airplane noises. Ph.D. Thesis
Powell, C. A.
1979-01-01
Two laboratory experiments were conducted to investigate the effects of road-traffic background noise on judgments of individual airplane flyover noises. In the first experiment, 27 subjects judged a set of 16 airplane flyover noises in the presence of traffic-noise sessions of 30-min duration consisting of the combinations of 3 traffic-noise types and 3 noise levels. In the second experiment, 24 subjects judged the same airplane flyover noises in the presence of traffic-noise sessions of 10-min duration consisting of the combinations of 2 traffic-noise types and 4 noise levels. In both experiments the airplane noises were judged less annoying in the presence of high traffic-noise levels than in the presence of low traffic-noise levels.
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Thermal modeling of tanks 241-AW-101 and 241-AN-104 with the TEMPEST code
International Nuclear Information System (INIS)
Antoniak, Z.I.; Recknagle, K.P.
1995-07-01
The TEMPEST code was exercised in a preliminary study of double-shell Tanks 241 -AW-101 and 241-AN-104 thermal behavior. The two-dimensional model used is derived from our earlier studies on heat transfer from Tank 241-SY-101. Several changes were made to the model to simulate the waste and conditions in 241-AW-101 and 241-AN-104. The nonconvective waste layer was assumed to be 254 cm (100 in.) thick for Tank 241-AW-101, and 381 cm (150 in.) in Tank 241-AN-104. The remaining waste was assumed, for each tank, to consist of a convective layer with a 7.6-cm (3-inch) crust on top. The waste heat loads for 241-AW-101 and 241-AN-104 were taken to be 10 kW (3.4E4 Btu/hr) and 12 kW (4.0E4 Btu/hr), respectively. Present model predictions of maximum and convecting waste temperatures are within 1.7 degrees C (3 degrees F) of those measured in Tanks 241-AW-101 and 241-AN-104. The difference between the predicted and measured temperature is comparable to the uncertainty of the measurement equipment. These models, therefore, are suitable for estimating the temperatures within the tanks in the event of changing air flows, waste levels, and/or waste configurations
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Jeffrey McDonnell, an assistant professor of forest hydrology at Utah State University, Logan, received the J. Warren Nystrom Award from the Association of American Geographers for his doctoral dissertation, “The Age, Origin and Pathway of Subsurface Stormflow in a Steep Humid Headwater Catchment.” In 1987, McDonnell was awarded AGU's Horton Research Grant for his thesis proposal.McDonnell received his Ph.D. in 1989 from the University of Canterbury, Christchurch, New Zealand. His dissertation was supervised by I. F. Owens, Department of Geography, University of Canterbury and A. J. Pearce, New Zealand Forest Research Institute.
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Zhang, Xiaoxing; Chen, Qinchuan; Tang, Ju; Hu, Weihua; Zhang, Jinbin
2014-01-01
The detection of partial discharge by analyzing the components of SF6 gas in gas-insulated switchgears is important to the diagnosis and assessment of the operational state of power equipment. A gas sensor based on anatase TiO2 is used to detect decomposed gases in SF6. In this paper, first-principle density functional theory calculations are adopted to analyze the adsorption of SO2, SOF2, and SO2F2, the primary decomposition by-products of SF6 under partial discharge, on anatase (101) and (001) surfaces. Simulation results show that the perfect anatase (001) surface has a stronger interaction with the three gases than that of anatase (101), and both surfaces are more sensitive and selective to SO2 than to SOF2 and SO2F2. The selection of a defect surface to SO2, SOF2, and SO2F2 differs from that of a perfect surface. This theoretical result is corroborated by the sensing experiment using a TiO2 nanotube array (TNTA) gas sensor. The calculated values are analyzed to explain the results of the Pt-doped TNTA gas sensor sensing experiment. The results imply that the deposited Pt nanoparticles on the surface increase the active sites of the surface and the gas molecules may decompose upon adsorption on the active sites. PMID:24755845
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DEFF Research Database (Denmark)
Löfgren, Johan; Mortensen, Jann; Rasmussen, Sine H
2017-01-01
proven malignancy referred for clinical pBS were prospectively enrolled. pBS and whole-body SPECT/CT were performed followed by18F-NaF PET/CT within 9 d.18F-NaF PET/MRI was also performed in 46 patients.Results:Bone metastases were confirmed in 16 patients and excluded in 101, which was lower than......-NaF PET/CT, and PET/MRI detected additional lesions compared with pBS in 31%, 63%, and 71%, respectively.Conclusion:18F-NaF PET/CT and whole-body SPECT/CT resulted in a significant reduction of equivocal readings compared with pBS, which implies an improved diagnostic confidence. However, the clinical...
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78 FR 1723 - Airworthiness Directives; Airbus Airplanes
2013-01-09
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus... Friday, except Federal holidays. For service information identified in this AD, contact Airbus...
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Numerical simulation of RCS for carrier electronic warfare airplanes
Directory of Open Access Journals (Sweden)
Yue Kuizhi
2015-04-01
Full Text Available This paper studies the radar cross section (RCS of carrier electronic warfare airplanes. Under the typical naval operations section, the mathematical model of the radar wave’s pitch angle incidence range analysis is established. Based on the CATIA software, considering dynamic deflections of duck wing leading edge flaps, flaperons, horizontal tail, and rudder, as well as aircraft with air-to-air missile, anti-radiation missile, electronic jamming pod, and other weapons, the 3D models of carrier electronic warfare airplanes Model A and Model B with weapons were established. Based on the physical optics method and the equivalent electromagnetic flow method, by the use of the RCSAnsys software, the characteristics of carrier electronic warfare airplanes’ RCS under steady and dynamic flights were simulated under the UHF, X, and S radar bands. This paper researches the detection probability of aircraft by radars under the condition of electronic warfare, and completes the mathematical statistical analysis of the simulation results. The results show that: The Model A of carrier electronic warfare airplane is better than Model B on stealth performance and on discover probability by radar detection effectively.
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2011-11-29
... Management Branch, ACE-102A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College... Airworthiness Directives; Gulfstream Aerospace Corporation Model GV and GV-SP Airplanes AGENCY: Federal Aviation... certain Gulfstream Aerospace Corporation Model GV and GV-SP airplanes. This AD was prompted by...
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77 FR 73340 - Airworthiness Directives; Airbus Airplanes
2012-12-10
... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... earlier proposed airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series..., contact Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France...
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7 CFR 4287.101 - Introduction.
2010-01-01
... 7 Agriculture 15 2010-01-01 2010-01-01 false Introduction. 4287.101 Section 4287.101 Agriculture Regulations of the Department of Agriculture (Continued) RURAL BUSINESS-COOPERATIVE SERVICE AND RURAL... § 4287.101 Introduction. (a) This subpart supplements part 4279, subparts A and B, by providing...
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Longitudinal aerodynamic characteristics of light, twin-engine, propeller-driven airplanes
Wolowicz, C. H.; Yancey, R. B.
1972-01-01
Representative state-of-the-art analytical procedures and design data for predicting the longitudinal static and dynamic stability and control characteristics of light, propeller-driven airplanes are presented. Procedures for predicting drag characteristics are also included. The procedures are applied to a twin-engine, propeller-driven airplane in the clean configuration from zero lift to stall conditions. The calculated characteristics are compared with wind-tunnel and flight data. Included in the comparisons are level-flight trim characteristics, period and damping of the short-period oscillatory mode, and windup-turn characteristics. All calculations are documented.
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ON MODERN APPROACH TO AIRPLANE-TYPE UNMANNED AERIAL VEHICLES DESIGN WITH SHORT TAKEOFF AND LANDING
Directory of Open Access Journals (Sweden)
Oleg P. Minin
2017-11-01
Full Text Available This publication opens a series of review papers devoted to the current design problems of the next generation unmanned airplanes that are expected to appear in the period from 2025 to 2035. The series of papers considers airplanes with vertical take-off and landing, air launch of small satellites into the orbit, cargo transportation tasks, issues related to new aerodynamic forms, as well as hybrid, combined and distributed power units. The first paper of the cycle is devoted to the conceptual aerodynamic design of the airplanes with a short take-off and landing, and with technical and economic characteristics on cruise flight conditions no worse than for traditional airplane based on aerodrome with long airstrip. We consider traditional linear methods for aerodynamic scheme analysis and weight analysis, as well. The main relationships and references to the works enabling the parametric analysis of the aerodynamic configuration are given. It is concluded that one of the most promising areas in the field of airplanes with a short take-off and landing is the development of aerodynamic circuits constructed as a "flying wing" of small aspect ratio and large structural height.
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5 CFR 831.101 - Administration.
2010-01-01
... 5 Administrative Personnel 2 2010-01-01 2010-01-01 false Administration. 831.101 Section 831.101 Administrative Personnel OFFICE OF PERSONNEL MANAGEMENT (CONTINUED) CIVIL SERVICE REGULATIONS (CONTINUED) RETIREMENT Administration and General Provisions § 831.101 Administration. (a) OPM has charge of the...
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Directory of Open Access Journals (Sweden)
Xiaozhe WANG
2018-06-01
Full Text Available The preliminary phase is significant during the whole design process of a large airplane because of its enormous potential in enhancing the overall performance. However, classical sequential designs can hardly adapt to modern airplanes, due to their repeated iterations, long periods, and massive computational burdens. Multidisciplinary analysis and optimization demonstrates the capability to tackle such complex design issues. In this paper, an integrated optimization method for the preliminary design of a large airplane is proposed, accounting for aerodynamics, structure, and stability. Aeroelastic responses are computed by a rapid three-dimensional flight load analysis method combining the high-order panel method and the structural elasticity correction. The flow field is determined by the viscous/inviscid iteration method, and the cruise stability is evaluated by the linear small-disturbance theory. Parametric optimization is carried out using genetic algorithm to seek the minimal weight of a simplified plate-beam wing structure in the cruise trim condition subject to aeroelastic, aerodynamic, and stability constraints, and the optimal wing geometry shape, front/rear spar positions, and structural sizes are obtained simultaneously. To reduce the computational burden of the static aeroelasticity analysis in the optimization process, the Kriging method is employed to predict aerodynamic influence coefficient matrices of different aerodynamic shapes. The multidisciplinary analyses guarantee computational accuracy and efficiency, and the integrated optimization considers the coupling effect sufficiently between different disciplines to improve the overall performance, avoiding the limitations of sequential approaches utilized currently. Keywords: Aeroelasticity, Integrated optimization, Multidisciplinary analysis, Large airplane, Preliminary design
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78 FR 23105 - Airworthiness Directives; Airbus Airplanes
2013-04-18
... Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Model... Agency] has received a report via Airbus and Messier-Bugatti-Dowty Ltd, from a Maintenance repair...
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National Research Council Canada - National Science Library
Brown, B
1951-01-01
The longitudinal stability and control characteristics of a large airplane have been measured with a mechanical feel device in combination with a booster incorporated in the elevator-control system...
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2011-10-13
... engines manufactured for new production Eclipse Aerospace, Inc. Model EA500 airplanes will incorporate the... requires incorporating an operating limitation of a maximum operating altitude of 30,000 feet into Section 2, Limitations, of the airplane flight manual (AFM). Since we issued that AD, P&WC has developed a...
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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.
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2010-01-01
... 10 Energy 3 2010-01-01 2010-01-01 false Scope. 434.101 Section 434.101 Energy DEPARTMENT OF ENERGY ENERGY CONSERVATION ENERGY CODE FOR NEW FEDERAL COMMERCIAL AND MULTI-FAMILY HIGH RISE RESIDENTIAL BUILDINGS Administration and Enforcement-General § 434.101 Scope. 101.1 This part provides design...
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7 CFR 786.101 - Administration.
2010-01-01
... 7 Agriculture 7 2010-01-01 2010-01-01 false Administration. 786.101 Section 786.101 Agriculture Regulations of the Department of Agriculture (Continued) FARM SERVICE AGENCY, DEPARTMENT OF AGRICULTURE SPECIAL PROGRAMS DAIRY DISASTER ASSISTANCE PAYMENT PROGRAM (DDAP-III) § 786.101 Administration. (a) DDAP...