WorldWideScience

Sample records for airplanes

  1. Mars Gashopper Airplane Project

    Data.gov (United States)

    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...

  2. 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.

  3. Flatulence on airplanes

    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...... 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....

  4. Unmanned Airplane Autopilot Tuning

    OpenAIRE

    Petar Getsov; Dimitar Yordanov

    2014-01-01

    This article considers different approaches for autopilot controller gain values adjustment. The correct autopilot performance is tested using modeling methods. A variant of land-based autopilot is considered. Examined are scenarios of UAV airplanes in level flight. The latter are applicable to tasks such as remote sensing, controlled area surveillance, etc.

  5. Unmanned Airplane Autopilot Tuning

    Directory of Open Access Journals (Sweden)

    Petar Getsov

    2014-07-01

    Full Text Available This article considers different approaches for autopilot controller gain values adjustment. The correct autopilot performance is tested using modeling methods. A variant of land-based autopilot is considered. Examined are scenarios of UAV airplanes in level flight. The latter are applicable to tasks such as remote sensing, controlled area surveillance, etc.

  6. Flatulence on airplanes

    DEFF Research Database (Denmark)

    Pommergaard, Hans-Christian; Burcharth, Jakob; Fischer, Anders;

    2013-01-01

    , 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...... be embedded in the seat cushion, since this material is able to neutralise the odour. Moreover active charcoal may be used in trousers and blankets to emphasise this effect. Other less practical or politically correct solutions to overcome this problem may be to restrict access of flatus-prone persons from...... 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....

  7. Headache attributed to airplane travel ("airplane headache"): first Italian case.

    Science.gov (United States)

    Mainardi, Federico; Lisotto, Carlo; Palestini, Claudia; Sarchielli, Paola; Maggioni, Ferdinando; Zanchin, Giorgio

    2007-06-01

    A new form of headache, whose attacks seem to be stereotyped, has been recently reported; because of the peculiarity of its onset, strictly related to airplane travel, the name of "Airplane headache" was proposed. A total of 7 cases have been published. Here we present the first Italian one. Furthermore the revision of the clinical characteristics of each patient leads us to propose provisional diagnostic criteria.

  8. Simulated airplane headache

    DEFF Research Database (Denmark)

    Bui, Sebastian Bao Dinh; Petersen, Torben; Poulsen, Jeppe Nørgaard;

    2017-01-01

    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 E2 (PGE2), cortisol, facial thermo-images, blood...... 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 PGE2, 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. CONCLUSION: The pressure chamber proved useful not only to provoke AH-like attack but also to study potential biomarkers for AH in this study. PGE2, and cortisol levels together with SPO presented dysregulation during the simulated AH-attack in affected individuals...

  9. 78 FR 48286 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-08-08

    ... A318, A319, A320, and ] A321 series airplanes. This AD requires an inspection to determine airplane... 37241, June 27, 2011)] to require an amendment of the applicable Airplane Flight Manual (AFM... Airbus Service Bulletin (SB) A320-32-1409), in combination with certain LGCIUs and MLG door...

  10. 78 FR 60667 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-10-02

    .../A319/A320/A321 Airplane Flight Manual. (ii) Reserved. (5) For service information identified in this AD.... SUMMARY: We are superseding airworthiness directive (AD) 2012-26-51 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2012- 26-51 required revising the airplane flight manual (AFM) to...

  11. Controllability and Maneuverability of Airplanes

    Science.gov (United States)

    Norton, F H; Brown, W G

    1923-01-01

    This investigation was conducted for the purpose of studying the behavior of the JN4H airplane in free flight under the action of its controls and from this to arrive at satisfactory definitions and coefficients for controllability and maneuverability. The method consisted in recording the angular velocity about the three axes, together with the air speed, control positions, and acceleration. (author)

  12. 77 FR 1622 - Airworthiness Directives; Socata Airplanes

    Science.gov (United States)

    2012-01-11

    ... 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... information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room...

  13. 78 FR 60798 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-10-02

    ... directive (AD) for all Airbus Model A330-200, -300 and -200 Freighter series airplanes, and Model A340-200... prompted by a report that an airplane equipped with AOA sensors installed with conic plates recently... information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket...

  14. 76 FR 73496 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2011-11-29

    ..., -312, and -313 airplanes on which the repair specified in Airbus Repair Drawing R57115053, R57115051..., -311, -312, and -313 airplanes on which the repair specified in Airbus Repair Drawing R57115053... Technical Disposition F57D03012810, Issue B, dated August 18, 2003; or Airbus A330/A340...

  15. 77 FR 28238 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-05-14

    ... -132 airplanes; Model A320-111, -211, -212, -214 and -232 airplanes; and Model A321-111, -211, -212.... ] Request That the FAA Accept Published Service Repair Manual (SRM) Repairs as an FAA-Approved Corrective... specified to comply with the NPRM. United Airlines stated that Airbus Service Bulletin A320-57-1152,...

  16. 77 FR 49386 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-08-16

    ...-111 and -112 airplanes, and Model A319, A320, and A321 series airplanes. This proposed AD was prompted... of the manual mask release and corrective actions if necessary. We are proposing this AD to detect... operational check of the manual mask release and corrective actions if necessary. You may obtain...

  17. 78 FR 25666 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-05-02

    ... Flight Manual (AFM) by inserting Airbus A318/A319/A320/A321 Temporary Revision (TR) TR286, Issue 1.0... A318, A319, A320, and A321 series airplanes. The existing AD currently requires revising the airplane flight manual (AFM) to advise the flightcrew of emergency procedures for addressing angle of attack...

  18. 77 FR 60653 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-10-04

    ... A319, A320, and A321 airplanes. The existing AD currently requires installing spacer assemblies at the... conversion manual. This proposed AD would require modifying the attachment points of fixed YZ-latches of the... address an unsafe condition on certain Airbus Model A319, A320, and A321 series airplanes. Since we...

  19. 14 CFR 21.5 - Airplane or Rotorcraft Flight Manual.

    Science.gov (United States)

    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...

  20. 76 FR 78524 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2011-12-19

    ... airplanes only), as applicable, in accordance with the instructions of Airbus All Operators Telex (AOT) A330.... 552(a) and 1 CFR part 51: (1) Airbus All Operators Telex (AOT) A330-26A3052, dated April 19,...

  1. 78 FR 22432 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-04-16

    ... provide appropriate operational procedures to prevent the airplane flight directors (FDs), autopilot (AP... computers (FCPCs) are necessary to inhibit autopilot re-engagement under unreliable airspeed conditions... this AD to prevent autopilot engagement under unreliable airspeed conditions, which could result...

  2. 77 FR 10691 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-02-23

    ... Operators Telex A330-52A3084, dated December 20, 2010 (for Model A330-200 and A330-300 series airplanes); All Operators Telex A330-52A3085, dated December 20, 2010 (for Model A330-200 and A330-300 series airplanes); All Operators Telex A340-52A4091, dated December 20, 2010 (for Model A340-200 and...

  3. 77 FR 75833 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-12-26

    ... with Airbus All Operator Telex A300-53A0391, dated August 9, 2011 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or Airbus All Operator Telex A300-57A6111, dated August 9, 2011 (for Model A300 B4-601... the airplane, in accordance with Airbus All Operator Telex A300- 53A0391, dated August 9, 2011...

  4. 77 FR 32060 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-05-31

    .... Note 2 to paragraph (g)(4) of this AD: Airbus A318/A319/A320/ A321 Maintenance Manual Task 47-10-43-920... and -112 airplanes; and all Model A319, A320, and A321 series airplanes. The existing AD currently..., Amendment 39-16097 (74 FR 62219, November 27, 2009), Airbus has issued A318/A319/A320/A321...

  5. 77 FR 46929 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-08-07

    ... existing airworthiness directive (AD) that applies to all Airbus Model A318, A319, A320, and A321 series airplanes. The existing AD currently requires revising the airplane flight manual (AFM) to include a..., A320-111, A320-211, A320-212, A320-214, A320-231, A320-232, A320-233, A321-111, A321-112,...

  6. Factors of airplane engine performance

    Science.gov (United States)

    Gage, Victor R

    1921-01-01

    This report is based upon an analysis of a large number of airplane-engine tests. It contains the results of a search for fundamental relations between many variables of engine operation. The data used came from over 100 groups of tests made upon several engines, primarily for military information. The types of engines were the Liberty 12 and three models of the Hispano-Suiza. The tests were made in the altitude chamber, where conditions simulated altitudes up to about 30,000 feet, with engine speeds ranging from 1,200 to 2,200 r.p.m. The compression ratios of the different engines ranged from under 5 to over 8 to 1. The data taken on the tests were exceptionally complete, including variations of pressure and temperature, besides the brake and friction torques, rates of fuel and air consumption, the jacket and exhaust heat losses.

  7. 77 FR 65642 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-30

    ... (FMEA) be done for the fuel system on Model 757 airplanes. AAL stated that the fuel system, while... and FMEA; specifically, all the wing fuel pump relays of the Model 757 airplane are powered by one...

  8. 78 FR 41882 - Airworthiness Directives; Dassault Aviation Airplanes

    Science.gov (United States)

    2013-07-12

    ...). SUMMARY: We propose to supersede airworthiness directive (AD) 2002-23- 19, which applies to all Dassault... manufacturer revised the airplane maintenance manual (AMM) maintenance requirements and airworthiness... Rodriguez, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601...

  9. 14 CFR 121.141 - Airplane flight manual.

    Science.gov (United States)

    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...

  10. 14 CFR 125.75 - Airplane flight manual.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane flight manual. 125.75 Section 125...,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Manual Requirements § 125.75 Airplane flight manual. (a) Each certificate holder shall keep a current approved Airplane Flight Manual...

  11. 77 FR 50054 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Science.gov (United States)

    2012-08-20

    ... Directives; Cessna Aircraft Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... certain Cessna Aircraft Company Models 172R and 172S airplanes. This proposed AD was prompted by reports... tube assembly and the airplane structure; and adjustment as necessary. We are proposing this AD...

  12. 14 CFR 125.407 - Maintenance log: Airplanes.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Maintenance log: Airplanes. 125.407 Section... Maintenance log: Airplanes. (a) Each person who takes corrective action or defers action concerning a reported... record the action taken in the airplane maintenance log in accordance with part 43 of this chapter....

  13. 77 FR 65501 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-29

    ... certain The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. The existing AD... Boeing Company Model 707-100 long body, - 200, -100B long body, and -100B short body series airplanes... TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The...

  14. Performance Comparison of the Optimized Inverted Joined Wing Airplane Concept and Classical Configuration Airplanes

    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.

  15. 76 FR 67341 - Airworthiness Directives; SOCATA Airplanes

    Science.gov (United States)

    2011-11-01

    ... availability of this material at the FAA, call (816) 329-4148. FOR FURTHER INFORMATION CONTACT: Albert Mercado...; telephone: (816) 329-4119; fax: (816) 329-4090; email: albert.mercado@faa.gov . SUPPLEMENTARY INFORMATION...: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas...

  16. 76 FR 65419 - Airworthiness Directives; SOCATA Airplanes

    Science.gov (United States)

    2011-10-21

    .... ] FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate...-mail: albert.mercado@faa.go v. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any... the procedures found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace...

  17. 76 FR 50706 - Airworthiness Directives; SOCATA Airplanes

    Science.gov (United States)

    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... the procedures found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace...

  18. 77 FR 36125 - Airworthiness Directives; SOCATA Airplanes

    Science.gov (United States)

    2012-06-18

    ... 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.gov... 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small...

  19. 76 FR 50405 - Airworthiness Directives; SOCATA Airplanes

    Science.gov (United States)

    2011-08-15

    ...: 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.gov... the procedures found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace...

  20. 77 FR 67256 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-11-09

    ... rudder has been certified, and its robust FOQA program coupled with a review of maximum lateral loading... that it has monitored and recorded events of lateral G exceedences at FedEx as a result of FAA AD 2002... excessive pedal input, thinking he was actually correcting an airplane malfunction. Even with...

  1. 77 FR 48427 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-08-14

    ... procurement will allow the work to be performed during a heavy maintenance check for all FedEx airplanes. We... product. Where the service information lists required parts costs that are covered under warranty, we have... between the national government and the States, or on the distribution of power and responsibilities...

  2. A study of airplane engine tests

    Science.gov (United States)

    Gage, Victor R

    1920-01-01

    This report is a study of the results obtained from a large number of test of an Hispano-Suiza airplane engine in the altitude laboratory of the Bureau of Standards. It was originally undertaken to determine the heat distribution in such an engine, but many other factors are also considered as bearing on this matter.

  3. 77 FR 26154 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-05-03

    ... time. This AD requires installing three secondary retention plates for the gimbal bearings on the THSA... CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate... been identified by analysis. Primary load path failure can be caused by bearing migration from...

  4. 77 FR 14314 - Airworthiness Directives; SOCATA Airplanes

    Science.gov (United States)

    2012-03-09

    ... receipt. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane... that this rupture could have been caused by the installation of a bolt bearing incorrect Part Number (P... 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small...

  5. 78 FR 65173 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-10-31

    ... bearing installation of the retraction jack anchorage fitting in the main landing gear (MLG) were incorrectly manufactured. This AD requires an inspection of the left-hand (LH) and right-hand (RH) bearing... CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane...

  6. 78 FR 78294 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-12-26

    ... airplanes. This proposed AD was prompted by the failure of the generator control unit-constant speed motor... with an emergency electrical configuration loss of the main electrical system or total engine flame out... INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport...

  7. 14 CFR 129.25 - Airplane security.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane security. 129.25 Section 129.25... security. Foreign air carriers conducting operations under this part must comply with the applicable security requirements in 49 CFR chapter XII....

  8. 78 FR 78705 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-12-27

    ... compliance time for the corrective actions specified in paragraphs (m), (o), and (p) of the NPRM (78 FR 28152.... The commenter has not provided sufficient substantiation for revising the corrective action compliance... result in reduced control of the airplane. (f) Compliance You are responsible for having the...

  9. Two-stroke-cycle engines for airplanes

    Science.gov (United States)

    Jalbert, J

    1926-01-01

    Now that the two-stroke-cycle engine has begun to make its appearance in automobiles, it is important to know what services we have a right to expect of it in aeronautics, what conditions must be met by engines of this type for use on airplanes and what has been accomplished.

  10. 77 FR 51729 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-08-27

    ... examining the MCAI in the AD docket. Relevant Service Information Airbus has issued All Operator Telex A330... series airplanes); and All Operator Telex A340-32A4292, dated August 24, 2011, including Appendix 1..., dated August 23, 2011, of Airbus All Operator Telex A330-32A3256, dated August 24, 2011 (for Model...

  11. 77 FR 24833 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-04-26

    ... accordance with the ] instructions in Airbus All Operators Telex A310-29A2101, Revision 01, dated April 12... Telex A310-29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic... with the instructions in Airbus All Operators Telex A310- 29A2101, Revision 01, dated April 12,...

  12. 78 FR 39190 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-07-01

    ..., of Chapter 57, Wings, of the Airbus A318/A319/A320/A321 Aircraft Maintenance Manual (AMM), Revision.../A320/A321 Aircraft Maintenance Manual (AMM), Revision 50, dated November 1, 2012. (2) Task 57-26-13-400..., A319, A320, and A321 series airplanes. This proposed AD was prompted by a determination that...

  13. 78 FR 21230 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-04-10

    .../A320 Aircraft Maintenance Manual. Request To Correct Typographical Error Virgin America noted an error.../A320 Aircraft Maintenance Manual. Note 2 to paragraph (i) of this AD: Guidance on the fuel pump... A320 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer,...

  14. 78 FR 9341 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2013-02-08

    ...). Chapter 32 of the Airbus A318/ A319/A320/A321 Aircraft Maintenance Manual (AMM) is one approved method for... A318, A319, A320, and A321 series airplanes. The existing AD currently requires repetitive inspections...''), to correct an unsafe condition for the specified products. The MCAI states: In 2005, an...

  15. 77 FR 15636 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-03-16

    ..., A319, and A320 series airplanes. This proposed AD was prompted by reports of unsuccessful slide... manual mode. As a result, the aspirator will not ingest sufficient ambient air for slide inflation. This... correct the unsafe condition identified in the MCAI. Airbus Service Bulletin A320-28-1118, Revision...

  16. 77 FR 14679 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-03-13

    ... service information was approved for IBR on IBR June 24, 2002 (67 FR 35425, May 20, 2002). (i) Airbus... asymmetry during landing, with controllability and deceleration consequences. We are issuing this AD to prevent thrust asymmetry conditions which could result in loss of control of the airplane during...

  17. Safety and design in airplane construction

    Science.gov (United States)

    Teichmann, Alfred

    1934-01-01

    The author gives a survey of the principles of stress analysis and design of airplane structures, and discusses the fundamental strength specifications and their effect on the stress analysis as compared with the safety factors used in other branches of engineering.

  18. Developing aircraft photonic networks for airplane systems

    DEFF Research Database (Denmark)

    White, Henry J.; Brownjohn, Nick; Baptista, João;

    2013-01-01

    Achieving affordable high speed fiber optic communication networks for airplane systems has proved to be challenging. In this paper we describe a summary of the EU Framework 7 project DAPHNE (Developing Aircraft Photonic Networks). DAPHNE aimed to exploit photonic technology from terrestrial comm...

  19. 75 FR 39798 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400, -401, and -402 Airplanes

    Science.gov (United States)

    2010-07-13

    ... 8 Q400 Airplane amendment-- Flight Manual-- DHC-8-400 airplanes 13 1 July 14, 2005 PSM 1-84-1A. DHC-8-401 airplanes 13 1 July 14, 2005 PSM 1-84-1A. DHC-8-402 airplanes 13 1 July 14, 2005 PSM 1-84-1A... amendment-- Flight Manual-- DHC-8-400 airplanes 13 3 June 9, 2008 PSM 1-84-1A. DHC-8-401 airplanes 13 3...

  20. Perturbed Motion of Airplane and Safe Store Separation

    Directory of Open Access Journals (Sweden)

    S. C. Raisinghani

    1984-07-01

    Full Text Available 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 stroes combination. A criterion is evolved to qualitatively indicate locations for safe store separation. It is suggested that the present method be used to predict airplane perturbed motion following stores separation for a given airplane store combination and results be used in conjunction with store trajectory analysis for finally declaring a store location as safe unsafe.

  1. 76 FR 3854 - Airworthiness Directives; REIMS AVIATION S.A. Model F406 Airplanes

    Science.gov (United States)

    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,...

  2. Experimental test of airplane boarding methods

    CERN Document Server

    Steffen, Jason H

    2011-01-01

    We report the results of an experimental comparison of different airplane boarding methods. This test was conducted in a mock 757 fuselage, located on a Southern California soundstage, with 12 rows of six seats and a single aisle. Five methods were tested using 72 passengers of various ages. We found a significant reduction in the boarding times of optimized methods over traditional methods. These improved methods, if properly implemented, could result in a significant savings to airline companies.

  3. Autonomous Deicing System For Airplane Wing

    Science.gov (United States)

    Hickman, G. A.; Gerardi, J. J.

    1993-01-01

    Prototype autonomous deicing system for airplane includes network of electronic and electromechanical modules at various locations in wings and connected to central data-processing unit. Small, integrated solid-state device, using long coils installed under leading edge, exciting small vibrations to detect ice and larger vibrations to knock ice off. In extension of concept, outputs of vibration sensors and other sensors used to detect rivet-line fractures, fatigue cracks, and other potentially dangerous defects.

  4. 77 FR 51717 - Airworthiness Directives; Airbus Airplanes

    Science.gov (United States)

    2012-08-27

    ... Information Airbus has issued All Operator Telex A300-53A0391, dated August 9, 2011 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); and All Operator Telex A300-57A6111, dated August 9, 2011 (for Model A300... accordance with Airbus All Operator Telex A300-53A0391, dated August 9, 2011 (for Model A300 B4-2C,...

  5. 77 FR 56991 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Airplanes

    Science.gov (United States)

    2012-09-17

    ...: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; phone: (816) 329-4119; fax: (816) 329-4090; email: albert.mercado@faa.gov . SUPPLEMENTARY... information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room...

  6. 78 FR 30243 - Airworthiness Directives; Eclipse Aerospace, Inc. Airplanes

    Science.gov (United States)

    2013-05-22

    ... Directives; Eclipse Aerospace, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... all Eclipse Aerospace, Inc. Model EA500 airplanes equipped with Avio, Avio with ETT, or Avio NG 1.0... identified in this proposed AD, contact Eclipse Aerospace, Inc. 26 East Palatine Road, Wheeling,...

  7. 77 FR 21426 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-04-10

    ...-020-AD; Amendment 39-17013; AD 2012-07-07] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for all The Boeing Company Model 747 airplanes. This AD was prompted..., contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC...

  8. 78 FR 49217 - Airworthiness Directives; the Boeing Company Airplanes

    Science.gov (United States)

    2013-08-13

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; the Boeing Company... directive (AD), for all The Boeing Company Model 727 airplanes, which proposed to supersede an existing AD... information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services...

  9. 78 FR 58962 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-09-25

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... Boeing Company Model 747 series airplanes. ] AD 89-12-10 currently requires replacement of certain... information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data &...

  10. 77 FR 21429 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-04-10

    ...-208-AD; Amendment 39-17012; AD 2012-07-06] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was...: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention:...

  11. 77 FR 24835 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-04-26

    ...-217-AD; Amendment 39-17031; AD 2012-08-14] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was... this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707,...

  12. 78 FR 22439 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-04-16

    ... Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The existing... around the galley service doorway hinge cutouts, add inspections of certain repaired structure at...

  13. 77 FR 45518 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-08-01

    ... Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC- 9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes... the wing structure not supporting the limit load condition, which could lead to loss of...

  14. 78 FR 49906 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-08-16

    ...-026-AD; Amendment 39-17527; AD 2013-15-11] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD was prompted... structure and result in loss of airplane control due to lack of horizontal stabilizer support. DATES:...

  15. 78 FR 46301 - Airworthiness Directives; BAE Systems (Operations) Limited Airplanes

    Science.gov (United States)

    2013-07-31

    ..., which could result in the engine pylon separating from the wing, with consequent damage to the airplane... in the engine pylon separating from the wing, with consequent damage to the airplane and reduced... of a cracked pick- up bracket of the forward outboard pylon of the number 1 engine due to...

  16. 77 FR 37795 - Airworthiness Directives; Dassault Aviation Airplanes

    Science.gov (United States)

    2012-06-25

    ... combination with other system failures, could lead to loss of controllability of the airplane. DATES: This AD... failure mode of TVS diodes used on PDCU or GCU cards in the PPDB, which, in combination with other system... combination with other system failures, could lead to loss of controllability of the airplane. (f)...

  17. 77 FR 72250 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Science.gov (United States)

    2012-12-05

    ... between the fuel return line assembly and the airplane structure; and, if any damage is found, replace the... personal information you provide. We will also post a report summarizing each substantive verbal contact we... and the airplane structure; and adjustment as necessary. The ADs resulted from reports of chafed...

  18. 78 FR 54561 - Airworthiness Directives; Piper Aircraft, Inc. Airplanes

    Science.gov (United States)

    2013-09-05

    ...-17457; AD 2013-10-04] RIN 2120-AA64 Airworthiness Directives; Piper Aircraft, Inc. Airplanes AGENCY... an airworthiness directive (AD) that published in the Federal Register. That AD applies to all Piper... airplane exhaust system, and repair or replacement of parts as necessary for all Piper Aircraft,...

  19. 78 FR 53078 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-08-28

    ... Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice... certain The Boeing Company Model 747-200B, -200C, -200F, -300, and 747SR series airplanes. This proposed... directive (AD): The Boeing Company: Docket No. FAA-2013-0704; Directorate Identifier 2013-NM-074-AD....

  20. 78 FR 13463 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-02-28

    ...-042-AD; Amendment 39-17284; AD 2012-25-03] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... applies to certain The Boeing Company Model 757 airplanes. That AD incorrectly identified certain actions... windshield. For certain The Boeing Company Model 757 airplanes, AD 2012-25-03 also specifies...

  1. 78 FR 25898 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-03

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... Boeing Company Model 747 series airplanes. The existing AD currently requires inspection of the fuselage... Boeing Company Model 747 series airplanes. AD 90-23-14 superseded AD 85-17-05, Amendment 39-5123...

  2. 76 FR 78574 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2011-12-19

    ... Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice... all The Boeing Company Model 767 airplanes. This proposed AD was prompted by reports of cracks of the... fitting, and contacting The Boeing Company for repair instructions and doing the repair. The...

  3. 77 FR 71723 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-12-04

    ... Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice... (AD) that applies to certain The Boeing Company Model 737-200, -200C, - 300, and -400 series airplanes...-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001), for certain The Boeing Company Model...

  4. 78 FR 57542 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-09-19

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... Boeing Company Model 777-200 and -300 series airplanes. AD 2012-12-08 requires an inspection for the part..., 2012) (``AD 2012-12-08''), for certain The Boeing Company Model 777-200 and -300 series airplanes....

  5. 78 FR 73739 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-12-09

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... all The Boeing Company Model MD-90- 30 airplanes. AD 97-11-07 and AD 99-18-23 currently require..., 1997), for all The Boeing Company Model MD-90-30 airplanes. AD 97-11-07 requires revising...

  6. 77 FR 55159 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-09-07

    ... Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... earlier proposed airworthiness directive (AD) for certain The Boeing Company Model 737-700, -700C, -800... certain The Boeing Company Model 737-700, -700C, -800, and -900ER series airplanes, Model 747-400F...

  7. 78 FR 21854 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-04-12

    ... Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice... certain The Boeing Company Model 747-400 and -400F series airplanes. This proposed AD was prompted by a... FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): The Boeing...

  8. 77 FR 31167 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-05-25

    ...-17059; AD 2012-10-10] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY... airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports... airworthiness directive (AD): 2012-10-10 The Boeing Company: Amendment 39-17059; Docket No. FAA-...

  9. 78 FR 15332 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-03-11

    ... Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice... (AD) that applies to all The Boeing Company Model 737-300, -400, and - 500 series airplanes. The... (73 FR 15397, March 24, 2008), for all The Boeing Company Model 737-300, - 400, and -500...

  10. Future Propulsion Opportunities for Commuter Airplanes

    Science.gov (United States)

    Strack, W. C.

    1982-01-01

    Commuter airplane propulsion opportunities are summarized. Consideration is given to advanced technology conventional turboprop engines, advanced propellers, and several unconventional alternatives: regenerative turboprops, rotaries, and diesels. Advanced versions of conventional turboprops (including propellers) offer 15-20 percent savings in fuel and 10-15 percent in DOC compared to the new crop of 1500-2000 SHP engines currently in development. Unconventional engines could boost the fuel savings to 30-40 percent. The conclusion is that several important opportunities exist and, therefore, powerplant technology need not plateau.

  11. Rapid Airplane Parametric Input Design (RAPID)

    Science.gov (United States)

    Smith, Robert E.

    1995-01-01

    RAPID is a methodology and software system to define a class of airplane configurations and directly evaluate surface grids, volume grids, and grid sensitivity on and about the configurations. A distinguishing characteristic which separates RAPID from other airplane surface modellers is that the output grids and grid sensitivity are directly applicable in CFD analysis. A small set of design parameters and grid control parameters govern the process which is incorporated into interactive software for 'real time' visual analysis and into batch software for the application of optimization technology. The computed surface grids and volume grids are suitable for a wide range of Computational Fluid Dynamics (CFD) simulation. The general airplane configuration has wing, fuselage, horizontal tail, and vertical tail components. The double-delta wing and tail components are manifested by solving a fourth order partial differential equation (PDE) subject to Dirichlet and Neumann boundary conditions. The design parameters are incorporated into the boundary conditions and therefore govern the shapes of the surfaces. The PDE solution yields a smooth transition between boundaries. Surface grids suitable for CFD calculation are created by establishing an H-type topology about the configuration and incorporating grid spacing functions in the PDE equation for the lifting components and the fuselage definition equations. User specified grid parameters govern the location and degree of grid concentration. A two-block volume grid about a configuration is calculated using the Control Point Form (CPF) technique. The interactive software, which runs on Silicon Graphics IRIS workstations, allows design parameters to be continuously varied and the resulting surface grid to be observed in real time. The batch software computes both the surface and volume grids and also computes the sensitivity of the output grid with respect to the input design parameters by applying the precompiler tool

  12. Fuzzy Logic Decoupled Lateral Control for General Aviation Airplanes

    Science.gov (United States)

    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.

  13. Fuzzy Logic Decoupled Longitudinal Control for General Aviation Airplanes

    Science.gov (United States)

    Duerksen, Noel

    1996-01-01

    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 difference airplanes without being matched to a specific airplane. In an attempt to create such a system, a fuzzy logic controller was devised to control throttle position and another to control elevator position. These two controllers were used to control flight path angle and airspeed for both a piston powered single engine airplane simulation and a business jet simulation. Overspeed protection and stall protection were incorporated in the form of expert systems supervisors. It was found that by using the artificial intelligence techniques of fuzzy logic and expert systems, a generic longitudinal controller could be successfully used on two general aviation aircraft types that have very difference characteristics. These controllers worked for both airplanes over their entire flight envelopes including configuration changes. The controllers for both airplanes were identical except for airplane specific limits (maximum allowable airspeed, throttle lever travel, etc.). The controllers also handled configuration changes without mode switching or knowledge of the current configuration. 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.

  14. 75 FR 47199 - Airworthiness Directives; McDonnell Douglas Corporation Model DC-9-10 Series Airplanes, DC-9-30...

    Science.gov (United States)

    2010-08-05

    ... Douglas Corporation Model DC- 9-10 Series Airplanes, DC-9-30 Series Airplanes, DC-9-81 (MD-81) Airplanes, DC-9-82 (MD-82) Airplanes, DC-9-83 (MD-83) Airplanes, DC-9- 87 (MD-87) Airplanes, MD-88 Airplanes... directive (AD), which applies to all McDonnell Douglas Model DC-9-10 series airplanes, DC-9-30...

  15. 75 FR 89 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Science.gov (United States)

    2010-01-04

    ... after receipt. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane... found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small...

  16. 75 FR 71536 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Science.gov (United States)

    2010-11-24

    ... material at the FAA, call 816-329-4148. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer... Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,...

  17. 76 FR 30295 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Science.gov (United States)

    2011-05-25

    ... Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri... procedures found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace Engineer, FAA,...

  18. 75 FR 59658 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Science.gov (United States)

    2010-09-28

    ... Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri... the procedures found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace...

  19. 75 FR 30272 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Science.gov (United States)

    2010-06-01

    ...: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City... the procedures found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace...

  20. 75 FR 16660 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Science.gov (United States)

    2010-04-02

    ... CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas... requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Albert Mercado,...

  1. 75 FR 13239 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Science.gov (United States)

    2010-03-19

    ... receipt. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane... found in 14 CFR 39.19. Send information to Attn: Albert Mercado, Aerospace Engineer, FAA, Small...

  2. 75 FR 52480 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Science.gov (United States)

    2010-08-26

    ... after receipt. 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,...

  3. 76 FR 4216 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Science.gov (United States)

    2011-01-25

    ... CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, ACE... found in 14 CFR 39.19. Send information to Attn: Albert Mercado, Aerospace Engineer, FAA, Small...

  4. 75 FR 60667 - Airworthiness Directives; Learjet Inc. Model 45 Airplanes

    Science.gov (United States)

    2010-10-01

    ... burning of wires have been reported on four Model 45 airplanes. In all four incidents, the wire damage was... from within touching distance unless otherwise specified. A mirror may be necessary to ensure...

  5. 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.

  6. Revolution in airplane construction? Grob G110: The first modern fiber glass composition airplane shortly before its maiden flight

    Science.gov (United States)

    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.

  7. Application of Feedback Linearization Method in Airplane Automatic Landing Control System

    Institute of Scientific and Technical Information of China (English)

    Wang Xiaoyan; Feng Jiang; Feng Xiujuan; Wu Junqin

    2004-01-01

    Summarizes the I/O feedback linearization about MIMO system, and applies it to nonlinear control equation of airplane. And also designs the tracing control laws for airplane longitudinal automatic landing control system.

  8. Design Oriented Structural Modeling for Airplane Conceptual Design Optimization

    Science.gov (United States)

    Livne, Eli

    1999-01-01

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

  9. 75 FR 20787 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400, -401, and -402 Airplanes

    Science.gov (United States)

    2010-04-21

    ...-- Dated-- Q400 Airplane Flight Amendment-- Manual-- DHC-8-400 airplanes 13 1 July 14, 2005...... PSM 1-84-1A. DHC-8-401 airplanes 13 1 July 14, 2005...... PSM 1-84-1A. DHC-8-402 airplanes 13 1 July 14, 2005...... PSM 1-84-1A. Note 1: This may be done by inserting a copy of the applicable temporary amendment...

  10. Patterns of measles transmission among airplane travelers.

    Science.gov (United States)

    Edelson, Paul J

    2012-09-01

    With advanced air handling systems on modern aircraft and the high level of measles immunity in many countries, measles infection in air travelers may be considered a low-risk event. However, introduction of measles into countries where transmission has been controlled or eliminated can have substantial consequences both for the use of public health resources and for those still susceptible. In an effort to balance the relatively low likelihood of disease transmission among largely immune travelers and the risk to the public health of the occurrence of secondary cases resulting from importations, criteria in the United States for contact investigations for measles exposures consider contacts to be those passengers who are seated within 2 rows of the index case. However, recent work has shown that cabin air flow may not be as reliable a barrier to the spread of measles virus as previously believed. Along with these new studies, several reports have described measles developing after travel in passengers seated some distance from the index case. To understand better the potential for measles virus to spread on an airplane, reports of apparent secondary cases occurring in co-travelers of passengers with infectious cases of measles were reviewed. Medline™ was searched for articles in all languages from 1946 to week 1 of March 2012, using the search terms "measles [human] or rubeola" and ("aircraft" or "airplane" or "aeroplane" or "aviation" or "travel" or "traveler" or "traveller"); 45 citations were returned. Embase™ was searched from 1988 to week 11 2012, using the same search strategy; 95 citations were returned. Papers were included in this review if they reported secondary cases of measles occurring in persons traveling on an airplane on which a person or persons with measles also flew, and which included the seating location of both the index case(s) and the secondary case(s) on the plane. Nine reports, including 13 index cases and 23 apparent secondary cases

  11. 78 FR 65153 - Special Conditions: Learjet Model 45 Series Airplanes; Aircraft Electronic System Security...

    Science.gov (United States)

    2013-10-31

    ... Learjet Model 45 series airplanes. The Model 45 series airplanes are swept-wing aircraft equipped with two... type certification basis for Learjet Model 45 series airplanes. System Security Protection for Aircraft... ensure that continued airworthiness of the aircraft is maintained, including all...

  12. 76 FR 30294 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane Pilot Compartment View...

    Science.gov (United States)

    2011-05-25

    ... INFORMATION CONTACT: Loran Haworth, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind... type certificate for their new Model G250 airplane. The G250 is an 8-10 passenger (19 maximum), twin... nautical miles. Airplane dimensions are 61.69-foot wing span, 66.6-foot overall length, and 20.8-foot...

  13. 14 CFR Appendix F to Part 135 - Airplane Flight Recorder Specification

    Science.gov (United States)

    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... voice recorder. 31. Air/ground sensor (primary airplane system reference nose or main gear)...

  14. LAUNCH : an innovation concept for loading and unloading narrow-body airplanes

    NARCIS (Netherlands)

    Grinten, M.P. van der; Bronkhorst, R.E.; Delleman, N.J.

    2000-01-01

    In wide-body airplanes containers are used for handling luggage in and out the airplane. In narrow-body airplanes loading and unloading still is done manually causing heavy loads in awkward postures due to the limited height in the belly. Incidence rates of musculoskeletal health problems are high i

  15. 14 CFR 121.195 - Airplanes: Turbine engine powered: Landing limitations: Destination airports.

    Science.gov (United States)

    2010-01-01

    ... limitations: Destination airports. 121.195 Section 121.195 Aeronautics and Space FEDERAL AVIATION...: Destination airports. (a) No person operating a turbine engine powered airplane may take off that airplane at... alternate airport) the weight of the airplane on arrival would exceed the landing weight set forth in...

  16. 14 CFR 135.395 - Large nontransport category airplanes: Landing limitations: Alternate airports.

    Science.gov (United States)

    2010-01-01

    ...: Landing limitations: Alternate airports. 135.395 Section 135.395 Aeronautics and Space FEDERAL AVIATION... category airplanes: Landing limitations: Alternate airports. No person may select an airport as an alternate airport for a large nontransport category airplane unless that airplane (at the weight...

  17. 75 FR 38017 - Airworthiness Directives; McDonnell Douglas Corporation Model DC-9-10 Series Airplanes, DC-9-30...

    Science.gov (United States)

    2010-07-01

    ... Corporation Model DC- 9-10 Series Airplanes, DC-9-30 Series Airplanes, DC-9-81 (MD-81) Airplanes, DC-9-82 (MD-82) Airplanes, DC-9-83 (MD-83) Airplanes, DC-9- 87 (MD-87) Airplanes, MD-88 Airplanes, and MD-90-30..., Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590. Hand Delivery: U.S. Department...

  18. 78 FR 70848 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Science.gov (United States)

    2013-11-27

    .... The Boeing Model 777-200 airplanes are long-range, wide-body, twin-engine jet airplanes with a maximum... networks connected to systems that perform functions required for the safe operation of the airplane. This... allow increased connectivity to, or access by, external airplane sources, airline operations,...

  19. Flight test results for several light, canard-configured airplanes

    Science.gov (United States)

    Brown, Philip W.

    1987-01-01

    Brief flight evaluations of two different, light, composite constructed, canard and winglet configured airplanes were performed to assess their handling qualities; one airplane was a single engine, pusher design and the other a twin engine, push-pull configuration. An emphasis was placed on the slow speed/high angle of attack region for both airplanes and on the engine-out regime for the twin. Mission suitability assessment included cockpit and control layout, ground and airborne handling qualities, and turbulence response. Very limited performance data was taken. Stall/spin tests and the effects of laminar flow loss on performance and handling qualities were assessed on an extended range, single engine pusher design.

  20. Design of the ARES Mars Airplane and Mission Architecture

    Science.gov (United States)

    Braun, Robert D.; Wright, Henry S.; Croom, Mark A.; Levine, Joel S.; Spencer, David A.

    2006-01-01

    Significant technology advances have enabled planetary aircraft to be considered as viable science platforms. Such systems fill a unique planetary science measurement gap, that of regional-scale, near-surface observation, while providing a fresh perspective for potential discovery. Recent efforts have produced mature mission and flight system concepts, ready for flight project implementation. This paper summarizes the development of a Mars airplane mission architecture that balances science, implementation risk and cost. Airplane mission performance, flight system design and technology maturation are described. The design, analysis and testing completed demonstrates the readiness of this science platform for use in a Mars flight project.

  1. 77 FR 66417 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Airplanes

    Science.gov (United States)

    2012-11-05

    ... INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 ] Locust, Room....mercado@faa.gov . SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant... procedures found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace Engineer, FAA,...

  2. 77 FR 21420 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Science.gov (United States)

    2012-04-10

    ... adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Model 680 airplanes. This..., 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the... refer to certain applicable AFM TCs, and incorrectly addresses the procedure change in the recently...

  3. 78 FR 49908 - Airworthiness Directives; Eclipse Aerospace, Inc. Airplanes

    Science.gov (United States)

    2013-08-16

    ...-007-AD; Amendment 39-17542; AD 2013-16-04] RIN 2120-AA64 Airworthiness Directives; Eclipse Aerospace... adopting a new airworthiness directive (AD) for all Eclipse Aerospace, Inc. Model EA500 airplanes equipped... service information identified in this AD, contact Eclipse Aerospace, Inc., 26 East Palatine...

  4. 77 FR 36206 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-06-18

    ... Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will... proposing this AD to prevent contactor failures, which could result in uncontained hot debris flow due to ELMS contactor breakdown, consequent smoke and heat damage to airplane structure and equipment...

  5. A Study of Transport Airplane Crash-Resistant Fuel Systems

    Science.gov (United States)

    Jones, Lisa (Technical Monitor); Robertson, S. H.; Johnson, N. B.; Hall, D. S.; Rimson, I. J.

    2002-01-01

    This report presents the results of a study, funded by the Federal Aviation Administration (FAA), 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. Army, which ultimately led to the current state of the art in CRFS technology. It describes the basic research, testing, field investigations and production efforts which have led to the highly successful military CRFS, which has saved many lives and reduced costs of accidents. Current CRFS technology used in transport category airplanes is defined and compared to the available state-of-the-art technology. The report provides information to the FAA and other government organizations which can help them plan their efforts to improve the state of crash fire protection in the transport airplane fleet. The report provides guidance to designers looking for information about CRFS design problems, analysis tools to use for product improvement, and a summary of current and proposed regulations for transport category airplane fuel systems.

  6. 77 FR 61731 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-11

    ..., evidence of electrical arcing, or arc-through of the conduit wall, and applicable corrective action; and... electrical arcing between the wiring and the surrounding conduit, which could result in arc-through of the... Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA...

  7. 77 FR 12166 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-02-29

    ... number six auxiliary slat track, causing electrical wires in the bundle to arc, which damaged both the..., contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65... wires in the bundle to arc, which damaged both the auxiliary slat track and power feeder wires....

  8. 78 FR 72791 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-12-04

    ... result in arc-through of the conduit, and consequent fire or explosion of the fuel tank. DATES: This AD..., contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65... result in arc-through of the conduit, and consequent fire or explosion of the fuel tank. (f)...

  9. 76 FR 10215 - Airworthiness Directives; Learjet Inc. Model 45 Airplanes

    Science.gov (United States)

    2011-02-24

    ... pilot and copilot circuit breaker panels caused by a short circuit between chafed wires.'' We agree with.... Model 45 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We... breaker panels caused by a short circuit between chafed wiring and the circuit breaker panel...

  10. Diagnosis and management of headache attributed to airplane travel.

    Science.gov (United States)

    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.

  11. 78 FR 12256 - Airworthiness Directives; Embraer S.A. Airplanes

    Science.gov (United States)

    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...

  12. 77 FR 45979 - Airworthiness Directives; Piper Aircraft, Inc. Airplanes

    Science.gov (United States)

    2012-08-02

    ... regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments... had reports of cracks, corrosion, failure of the turnbuckle, control cable fraying, the cable swage... (g)(1), (g)(2) and (g)(3) of this AD: To assist in determining the age of the airplane, you...

  13. 78 FR 52875 - Airworthiness Directives; the Boeing Company Airplanes

    Science.gov (United States)

    2013-08-27

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; the Boeing Company...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for all the Boeing Company Model 727.... For service information identified in this proposed AD, contact Boeing Commercial Airplanes,...

  14. 78 FR 73457 - Airworthiness Directives; the Boeing Company Airplanes

    Science.gov (United States)

    2013-12-06

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; the Boeing Company... Boeing Company Model 747-100, 747-200B, 747-200F series airplanes. AD 84-19-01 requires repetitive... Friday, except Federal holidays. For service information identified in this proposed AD, contact...

  15. 78 FR 58982 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-09-25

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company...). SUMMARY: We propose to supersede airworthiness directive (AD) 2013-07- 07, which applies to all The Boeing... information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services...

  16. 78 FR 49229 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-08-13

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... Boeing Company Model 737-600, -700, - 700C, and -800 series airplanes. AD 2009-24-07 currently requires... holidays. For service information identified in this proposed AD, contact Boeing Commercial...

  17. 77 FR 12170 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-02-29

    ...-135-AD; Amendment 39-16940; AD 2012-02-17] RIN 2120-AA64 Airworthiness Directives; The Boeing Company.... ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention...-5000, extension 1; fax 206-766-5680; email me.boecom@boeing.com ; Internet...

  18. 78 FR 3365 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-01-16

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Airplanes... holidays. For service information identified in this proposed AD, contact Boeing Commercial...

  19. 78 FR 52838 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-08-27

    ...-354-AD; Amendment 39-17533; AD 2013-15-17] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900... information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services...

  20. 78 FR 52836 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-08-27

    ...-352-AD; Amendment 39-17529; AD 2013-15-13] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted... October 1, 2013. ADDRESSES: For service information identified in this AD, contact Boeing...

  1. 77 FR 731 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-01-06

    ...-256-AD; Amendment 39-16904; AD 2011-27-03] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... publications listed in the AD as of February 10, 2012. ADDRESSES: For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707,...

  2. 78 FR 60676 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-10-02

    ... reports of worn or incorrectly assembled latches on main deck escape slides installed on airplane doors... (78 FR 9346). The NPRM proposed to require determining if the latches on main deck escape slides... after the effective date of this AD: Determine if the latches in the main deck escape slide/rafts...

  3. 78 FR 21079 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2013-04-09

    .... Discussion Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued..., New York Aircraft Certification Office (ACO), ANE-170, Transport Airplane Directorate, FAA; or TCCA... either the Manager, New York ACO, ANE- 170, FAA; or Transport Canada Civil Aviation (TCCA) (or...

  4. 76 FR 69166 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2011-11-08

    ...-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This proposed AD results... unsafe condition as: t was found that the * * * ADG GCU transformer primary winding can break due...

  5. 77 FR 24364 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2012-04-24

    ...-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by... ADG GCU transformer primary winding can break due to thermal fatigue. Broken transformer...

  6. 77 FR 37770 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-06-25

    .... Request To Clarify the Applicability Regarding the Installation of Winglets American Airlines (American... for airplanes covered by the applicability of the NPRM are affected by the installation of winglets... winglets. Aviation Partners Boeing (APB) stated it has reviewed Boeing Alert Service Bulletin...

  7. Nieuport-Delage Pursuit Airplane 48 C. 1. : "jockey" type

    Science.gov (United States)

    1927-01-01

    This is a light single-seat pursuit airplane with a tractor propeller actuated by a 12 cylinder V-type Hispano-Suiza engine giving 400 HP at 2000 R.P.M. This is a single winged aircraft capable of 273 km/h.

  8. 77 FR 26158 - Airworthiness Directives; Saab AB, Saab Aerosystems Airplanes

    Science.gov (United States)

    2012-05-03

    ... AD requires replacing certain hydraulic accumulators with stainless steel hydraulic accumulators, and... accumulators, which may result in damage to the airplane and injury to occupants. DATES: This AD becomes... by corrosion. This condition, if not detected and corrected, may lead to fatigue failure of...

  9. 76 FR 81889 - Airworthiness Directives; Saab AB, Saab Aerosystems Airplanes

    Science.gov (United States)

    2011-12-29

    ... corrected, may lead to fatigue failure of a hydraulic accumulator, possibly resulting in damage to the... failure. This proposed AD would require replacing certain hydraulic accumulators with stainless steel... to prevent failure of hydraulic accumulators, which may result in damage to the airplane and...

  10. 77 FR 63714 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-17

    ... airplanes. This AD was prompted by a report of elevator vibration and bearing swage failures. This AD... Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Kelly McGuckin, Aerospace... Controls. (e) Unsafe Condition This AD was prompted by a report of elevator vibration and bearing...

  11. Experiments on the resistance of airplane wheels and radiators

    Science.gov (United States)

    1924-01-01

    Experiments were made on the resistance of four airplane wheels of different sizes and coverings and two Lamblin radiators. The results show the important influence of the wheel coverings. The closing of a shutter, which was fitted to one of the radiators, considerably lessened the resistance.

  12. 78 FR 25374 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-01

    ... economic impact, positive or negative, on a substantial number of small entities under the criteria of the... AD was prompted by a report that certain airplanes might not have reinforcement straps installed on the center overhead stowage bins in the passenger compartment, and some installed reinforcement...

  13. 77 FR 63266 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-16

    ... not have a significant economic impact, positive or negative, on a substantial number of small..., reinforcement straps were not bonded to the center overhead stowage bins in the passenger compartment. For certain airplanes, this proposed AD would require performing an inspection of reinforcement straps...

  14. 78 FR 33010 - Airworthiness Directives; Saab AB, Saab Aerosystems Airplanes

    Science.gov (United States)

    2013-06-03

    ... in an aircraft maintenance manual is incorrect for Saab 340B airplane. This proposed AD would require... information identified in this proposed AD, contact Saab AB, Saab Aeronautics, SE-581 88, Link ping, Sweden... Aircraft Maintenance Manual (AMM), which quotes an elevator position of 4 degrees trailing edge down...

  15. 78 FR 77615 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2013-12-24

    ... Bombardier, Inc. Model DHC-8-400 series airplanes. AD 2010-13-04 requires modifying the nose landing gear... landing gear (NLG) trailing arm pivot pin retention bolt (part number NAS6204-13D) was damaged. One... excessive frictional torque on the pivot pin and an adverse tolerance condition at the retention...

  16. 78 FR 22802 - Airworthiness Directives; the Boeing Company Airplanes

    Science.gov (United States)

    2013-04-17

    ... in-flight resulting in decreased airplane control and performance, possible runway excursions, and... Tran, Aerospace Engineer, Propulsion Branch, ANM-140S, Seattle Aircraft Certification Office (ACO), FAA... motor switcher or shutoff solenoid valves because of overheating. This let the air motor shutoff...

  17. 78 FR 61164 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-10-03

    ... bushings, and inner cylinder bushings. For all airplanes, this AD requires a maintenance program revision... proposed to require a maintenance program revision, one-time inspections of the MLG truck beam, and related..., 2013) to specify the repetitive interval for the lubrication schedule (as referenced in Boeing...

  18. 77 FR 60285 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-03

    ... including the repetitive lubrication in the airplane maintenance program. We agree that accomplishment of.... This AD requires repetitive lubrication of the MLG pivot joints; repetitive detailed inspections of the... Register on May 1, 2012 (77 FR 25647). That NPRM proposed to require repetitive lubrication of the...

  19. 78 FR 47543 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2013-08-06

    .... Model DHC-8-100, -200, and -300 series airplanes. AD 2012-14-04 required replacing certain parking brake... around the parking brake accumulator end caps. We are issuing this AD to prevent failure of a parking...-002 (Parking Brake Accumulator), are installed on the aeroplanes listed in the Applicability...

  20. 77 FR 65617 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2012-10-30

    ... parking brake hydraulic accumulator, and relocating the parking brake accumulator, on the subject airplanes. We are issuing this AD to prevent failure of the screw caps and/or end caps of the parking brake... the CL-600- 2B19, Part Number (P/N) 08-60197-001 (Parking Brake Accumulator), are installed on...

  1. 78 FR 60679 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-10-02

    ...-273-AD; Amendment 39-17604; AD 2013-19-22] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes. This AD was... result in damage to the adjacent structure and consequent loss of structural integrity of the...

  2. 77 FR 54848 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-09-06

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737... not electrically bonded to primary structure of the airplane. This proposed AD would...

  3. 78 FR 17290 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-03-21

    ...-056-AD; Amendment 39-17375; AD 2013-05-03] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and... measuring the electrical resistance of the bond from the adapter plate to the airplane structure, and...

  4. 77 FR 50414 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-08-21

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737... structure, which could result in uncontrolled decompression of the airplane. DATES: We must receive...

  5. 77 FR 37793 - Airworthiness Directives; the Boeing Company Airplanes

    Science.gov (United States)

    2012-06-25

    ...-124-AD; Amendment 39-17099; AD 2012-12-19] RIN 2120-AA64 Airworthiness Directives; the Boeing Company... new airworthiness directive (AD) for certain the Boeing Company Model 777-200, -200LR, and -300ER... ceiling support structure of Section 41, in airplanes incorporating the overhead space utilization...

  6. 78 FR 9796 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Science.gov (United States)

    2013-02-12

    ... Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Models 172R and 172S... structure; and, if any damage is found, replace the fuel return line assembly. We are issuing this AD...

  7. 77 FR 65803 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-31

    ...-050-AD; Amendment 39-17234; AD 2012-21-18] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model MD-90-30 airplanes. This AD was... AD to detect and correct such cracking, which could result in the wing structure not supporting...

  8. 77 FR 65611 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-30

    ...-17229; AD 2012-21-13] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY... airworthiness directive (AD) for certain The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD... result in the wing structure not supporting the limit load condition, which could lead to loss...

  9. 78 FR 17294 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-03-21

    ...-054-AD; Amendment 39-17377; AD 2013-05-05] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and... smoke and heat damage to airplane structure and equipment during ground operations, and...

  10. 77 FR 5730 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2012-02-06

    ... necessary; and, for certain MLG shock strut assemblies, replacement or rework of the apex nut. Since we...) Replacement or Rework of the Apex Nut for Model CL-600-2C10 Airplanes For any MLG shock strut assembly... hours after May 18, 2011, replace or rework the apex nut, in accordance with Part B of...

  11. 78 FR 27010 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-09

    ... necessary; and eventual rework of the flap track assembly and rear spar attachments. For certain airplanes... rework of the flap track assembly and rear spar attachments. The NPRM published in the Federal Register... data to support the rework requirements of paragraphs (s) and (t) of the NPRM (77 FR 61542, October...

  12. 77 FR 71357 - Airworthiness Directives; Pacific Aerospace Limited Airplanes

    Science.gov (United States)

    2012-11-30

    ... On September 21, 2010, we issued AD 2010-20-18, Amendment 39-16453 (75 FR 59606, September 28, 2010... issued AD 2010-20-18, Amendment 39-16453 (75 FR 59606, September 28, 2010), information has been received... airplanes. This proposed AD also retains all actions in AD 2010-20-18, Amendment 39-16453 (75 FR...

  13. 76 FR 55614 - Airworthiness Directives; Pacific Aerospace Limited Airplanes

    Science.gov (United States)

    2011-09-08

    ... Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Pacific Aerospace... (AD) for Pacific Aerospace Limited Models FU24-954 and FU24A-954 airplanes modified with an...

  14. 78 FR 9781 - Airworthiness Directives; Pacific Aerospace Limited Airplanes

    Science.gov (United States)

    2013-02-12

    ... November 30, 2012 (77 FR 71357), and proposed to supersede AD 2010-20-18, Amendment 39- 16453 (75 FR 59606, September 28, 2010). Since we issued AD 2010-20-18, Amendment 39-16453 (75 FR 59606, September 28, 2010... airplanes. This AD also retains all actions in AD 2010-20-18, Amendment 39-16453 (75 FR 59606, September...

  15. 78 FR 65204 - Airworthiness Directives; BAE Systems (Operations) Limited Airplanes

    Science.gov (United States)

    2013-10-31

    ... in the engine pylon separating from the wing, with consequent damage to the airplane and reduced... report of a cracked pick-up bracket of the forward outboard pylon of the number 1 engine due to stress corrosion. This AD requires repetitive inspections and, depending on findings, repair of the pylon...

  16. 78 FR 22215 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-04-15

    ... currently requires modification of the nacelle strut and wing structure; for certain airplanes, repetitive..., November 26, 1999)). AD 2004-12-07 requires modification of the nacelle strut and wing structure; and for... America Code 54, Nacelles/Pylons. (e) Unsafe Condition This AD was prompted by reports indicating that...

  17. 76 FR 53308 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Science.gov (United States)

    2011-08-26

    ...) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions To... done: ] Table 2--Actions, Compliance and Procedures Actions Compliance Procedures (1) Option 1: For all... Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request...

  18. 76 FR 70379 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Science.gov (United States)

    2011-11-14

    ... fuel return line assembly and both the right steering tube assembly and the airplane structure... also post a report summarizing each substantive verbal contact we receive about this proposed AD... structure, adjusting as necessary. That AD resulted from reports of chafed fuel return line...

  19. 78 FR 29669 - Airworthiness Directives; DASSAULT AVIATION Airplanes

    Science.gov (United States)

    2013-05-21

    ... Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE-FALCON 200... inability to put out a fire in an engine, auxiliary power unit, or rear compartment. DATES: We must receive... submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations,...

  20. 78 FR 68355 - Airworthiness Directives; Dassault Aviation Airplanes

    Science.gov (United States)

    2013-11-14

    ... Jet Falcon; Model Mystere-Falcon 200 airplanes; and Model Mystere-Falcon 20-C5, 20-D5, 20-E5, and 20... could impact the capability to extinguish a fire in an engine, auxiliary power unit, or rear compartment... of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New...

  1. 76 FR 66200 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2011-10-26

    ... Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207... http://www.regulations.gov ; or in person at the Docket Management Facility between 9 a.m. and 5 p.m...; small air bubbles, air pockets, blister-like areas, or solid particles in the secondary fuel...

  2. 77 FR 54787 - Airworthiness Directives; M7 Aerospace LLC Airplanes

    Science.gov (United States)

    2012-09-06

    ...-17177; AD 2012-18-01] RIN 2120-AA64 Airworthiness Directives; M7 Aerospace LLC Airplanes AGENCY: Federal... new airworthiness directive (AD) for all M7 Aerospace LLC Models SA226-AT, SA226-T, SA226-T(B), SA226... information identified in this AD, contact M7 Aerospace LP, 10823 NE Entrance Road, San Antonio, Texas...

  3. 77 FR 31169 - Airworthiness Directives; Piper Aircraft, Inc. Airplanes

    Science.gov (United States)

    2012-05-25

    ...-002-AD; Amendment 39-17058; AD 2012-10-09] RIN 2120-AA64 Airworthiness Directives; Piper Aircraft, Inc... superseding an existing airworthiness directive (AD) for certain Piper Aircraft, Inc. (type certificate previously held by The New Piper Aircraft Inc.) Models PA-31T and PA-31T1 airplanes. That AD...

  4. 77 FR 57534 - Airworthiness Directives; Piper Aircraft, Inc. Airplanes

    Science.gov (United States)

    2012-09-18

    ... TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Piper... all Piper Aircraft, Inc. Models PA-31, PA-31-325, and PA-31-350 airplanes. The existing AD currently... identified in this proposed AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida...

  5. 75 FR 12667 - Airworthiness Directives; Learjet Inc. Model 45 Airplanes

    Science.gov (United States)

    2010-03-17

    ... on both actuators on one flap, resulting in flap asymmetry and loss of control of the airplane. DATES... information identified in this AD, contact Learjet, Inc., One Learjet Way, Wichita, Kansas 67209-2942... received, and other information. The street address for the Docket Office (telephone 800-647-5527) is...

  6. 78 FR 8999 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-02-07

    ... 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034...-400 series airplanes. This proposed AD was prompted by reports of auxiliary power unit (APU) faults... the APU power feeder cables; replacing the clamps and installing grommets; and related...

  7. 77 FR 75402 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-12-20

    ... discharge of the main battery, which could result in multiple system degradation, reduced airplane... corrected, could result in discharge of the main battery, which could result in multiple system degradation... ``BAT'' position, isolating the battery and standby buses, disabling the battery charger, and...

  8. 77 FR 61539 - Airworthiness Directives; DASSAULT AVIATION Airplanes

    Science.gov (United States)

    2012-10-10

    ... constitute a fire hazard. To address this unsafe condition, Dassault Aviation have developed a structural...; ] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; DASSAULT AVIATION Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice...

  9. 78 FR 42895 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-07-18

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM... to detect WFD before it becomes a hazard to flight. We will not grant any extensions of...

  10. 78 FR 26233 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-06

    ...-17418; AD 2013-08-01] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY... airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER...): 2013-08-01 The Boeing Company: Amendment 39-17418; Docket No. FAA- 2011-1231; Directorate...

  11. 78 FR 40060 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-07-03

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce engines. The existing AD... 2006-26-06, Amendment 39-14864 (71 FR 77586, December 27, 2006), for certain The Boeing Company...

  12. 77 FR 49708 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-08-17

    ...-066-AD; Amendment 39-17159; AD 2012-16-12] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for all The Boeing Company Model 707 airplanes, and Model 720 and... airworthiness directive (AD): 2012-16-12 The Boeing Company: Amendment 39-17159; Docket No. FAA-...

  13. 77 FR 47329 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-08-08

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... propose to rescind an existing airworthiness directive (AD) that applies to certain The Boeing Company...), for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. That...

  14. 77 FR 24355 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-04-24

    ...-265-AD; Amendment 39-17026; AD 2012-08-09] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, -300ER... to The Boeing Company Model 777-200, -200LR, - 300, -300ER, and 777F series airplanes,...

  15. 77 FR 41041 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-07-12

    ...-17111; AD 2012-13-09] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY... airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747...): 2012-13-09 The Boeing Company: Amendment 39-17111; Docket No. FAA- 2010-1115; Directorate...

  16. 78 FR 46532 - Airworthiness Directives; the Boeing Company Airplanes

    Science.gov (United States)

    2013-08-01

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; the Boeing Company... directive (AD) for all The Boeing Company Model 767 airplanes. That NPRM proposed to require repetitive... directive (AD): The Boeing Company: Docket No. FAA-2008-0616; Directorate Identifier 2007-NM-353-AD....

  17. 77 FR 40307 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-07-09

    ... Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... earlier proposed airworthiness directive (AD) for certain The Boeing Company Model 747-400, -400D, and... directive (AD): The Boeing Company: Docket No. FAA-2008-0620; Directorate Identifier 2007-NM-357-AD....

  18. 78 FR 63135 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-10-23

    ... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes equipped...

  19. 77 FR 42964 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-07-23

    ...-103-AD; Amendment 39-17095; AD 2012-12-15] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... superseding an existing airworthiness directive (AD) for The Boeing Company Model 757 Airplanes. That AD... (73 FR 25974, May 8, 2008), and adding the following new AD: 2012-12-15 The Boeing Company:...

  20. 77 FR 75827 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-12-26

    ...-190-AD; Amendment 39-17292; AD 2012-25-11] RIN 2120-AA64 Airworthiness Directives; The Boeing Company.... SUMMARY: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model... certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. AD 2012-15-15...

  1. 77 FR 65506 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-29

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... Boeing Company Model 757-200 and - 200PF series airplanes. The existing AD currently requires... 11, 2003), and adding the following new AD: The Boeing Company: Docket No. FAA-2012-1109;...

  2. 78 FR 26286 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2013-05-06

    ... airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes. That NPRM proposed requiring... rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to all The Boeing Company Model... directive (AD): The Boeing Company: Docket No. FAA-2012-0425; Directorate Identifier 2011-NM-273-AD....

  3. 77 FR 29857 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-05-21

    ...-009-AD; Amendment 39-17052; AD 2012-10-03] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 747 series airplanes... following new AD: 2012-10-03 The Boeing Company: Amendment 39-17052; Docket No. FAA- 2011-0645;...

  4. 77 FR 48423 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-08-14

    ...-213-AD; Amendment 39-17154; AD 2012-16-07] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model 737-500 series airplanes. This... The Boeing Company: Amendment 39-17154; Docket No. FAA- 2012-0336; Directorate Identifier...

  5. 77 FR 60296 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-10-03

    ...-074-AD; Amendment 39-17206; AD 2012-19-11] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... new airworthiness directive (AD) for certain The Boeing Company Model 737 airplanes. This AD was... the Latest Service Information Delta (DAL), AAL, and The Boeing Company requested that the proposed...

  6. 77 FR 47267 - Airworthiness Directives; The Boeing Company Airplanes

    Science.gov (United States)

    2012-08-08

    ...-17142; AD 2012-15-13] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY... following new AD: 2012-15-13 The Boeing Company: Amendment 39-17142; Docket No. FAA- 2009-0607; Directorate..., 2007). (c) Applicability This AD applies to all The Boeing Company Model 747-100B SUD, 747-300,...

  7. 77 FR 24353 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Science.gov (United States)

    2012-04-24

    ... requires replacing or relocating of certain circuit breaker panel (CBP) bus bars on certain airplanes, inspecting for any loose or improperly crimped lugs in certain electrical panel locations and replacement if... to the specified products. That NPRM was published in the Federal Register on October 26, 2011 (76...

  8. 14 CFR 135.422 - Aging airplane inspections and records reviews for multiengine airplanes certificated with nine...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Aging airplane inspections and records... Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIR CARRIERS... AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Maintenance,...

  9. 78 FR 63847 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Airplane Electronic System Security...

    Science.gov (United States)

    2013-10-25

    ... architecture for the Embraer Model EMB-550 series of airplanes is composed of several connected networks. This... (aircraft control functions); 2. Airline business and administrative support (airline information services... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Embraer S.A., Model EMB-550...

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

    Science.gov (United States)

    Fisher, Lloyd J.; Thompson, William C.

    1950-01-01

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

  11. 76 FR 18964 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Model P2006T Airplanes

    Science.gov (United States)

    2011-04-06

    ... after receipt. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane... 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small...

  12. 78 FR 75451 - Special Conditions: Cessna Model 750 Series Airplanes; Aircraft Electronic System Security...

    Science.gov (United States)

    2013-12-12

    ... Model 750 is a twin-engine pressurized executive jet airplane with standard seating provisions for 14... features: digital systems architecture composed of several connected networks. The proposed...

  13. Correlation and assessment of structural airplane crash data with flight parameters at impact

    Science.gov (United States)

    Carden, H. D.

    1982-01-01

    Crash deceleration pulse data from a crash dynamics program on general aviation airplanes and from transport crash data were analyzed. Structural airplane crash data and flight parameters at impact were correlated. Uncoupled equations for the normal and longitudinal floor impulses in the cabin area of the airplane were derived, and analytical expressions for structural crushing during impact and horizontal slide out were also determined. Agreement was found between experimental and analytical data for general aviation and transport airplanes over a relatively wide range of impact parameter. Two possible applications of the impulse data are presented: a postcrash evaluation of crash test parameters and an assumed crash scenario.

  14. AN AIRPLANE WITH UNCONVENTIONALLY PLACED PROPELLER POWER UNIT

    OpenAIRE

    Jan Červinka; Robert Kulhánek; Zdeněk Pátek

    2017-01-01

    The significance of the influence of operating propellers on the aircraft aerodynamic characteristics is well-known. Wind tunnel testing of an airplane model with operating propellers is a complex task regarding the required similarity of the full-scale and the model case. Matching sufficient similarity in axial and rotational velocities in the propeller slipstream is the primordial condition for the global aerodynamic similarity of the windtunnel testing. An example of the model power units ...

  15. 78 FR 76251 - Special Conditions: Airbus, Model A350-900 Series Airplane; Electronic System Security Protection...

    Science.gov (United States)

    2013-12-17

    ...; Electronic System Security Protection From Unauthorized External Access AGENCY: Federal Aviation... conditions for Airbus Model A350- 900 series airplanes. These airplanes will have a novel or unusual design feature associated with electronic system security protection from unauthorized external access....

  16. 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.

  17. Headache associated with airplane travel: A rare entity

    Directory of Open Access Journals (Sweden)

    Ajith Cherian

    2013-01-01

    Full Text Available 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.

  18. 78 FR 26280 - Special Conditions: Embraer, S.A., Model EMB-550 Airplane; Side-Facing Seats; Installation of...

    Science.gov (United States)

    2013-05-06

    ... owner operations. The aircraft has a conventional configuration with low wing and T-tail empennage. The...: Jayson Claar, FAA, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft.... applied for a type certificate for their new Model EMB-550 airplane. The Model EMB-550 airplane is...

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

    Science.gov (United States)

    2011-10-14

    ... INFORMATION CONTACT: Paul Bernado, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind... January 11, 2008, Learjet Inc. applied for a type certificate for a new Model LJ-200-1A10 airplane. This airplane is 68 feet long with a 65-foot wing span and accommodates up to 10 passengers. The LJ-...

  20. 77 FR 5990 - Special Conditions: Learjet Inc., Model LJ-200-1A10 Airplane, Pilot-Compartment View Through...

    Science.gov (United States)

    2012-02-07

    ..., Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington... January 11, 2008, Learjet Inc. applied for a type certificate for a new Model LJ-200-1A10 airplane. This airplane is 68 feet long with a 65-foot wing span and accommodates up to 10 passengers. The LJ-...

  1. 78 FR 76254 - Special Conditions: Airbus, Model A350-900 Series Airplane; Control Surface Awareness and Mode...

    Science.gov (United States)

    2013-12-17

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Airbus, Model A350-900 Series Airplane... Model A350-900 series airplanes. These airplanes will have a novel or unusual design feature(s... sending written comments, data, or views. The most helpful comments reference a specific portion of...

  2. 77 FR 57039 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Electronic Flight Control System...

    Science.gov (United States)

    2012-09-17

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Embraer S.A., Model EMB-550 Airplane... conditions for the Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design..., data, or views. The most helpful comments reference a specific portion of the special...

  3. 76 FR 44246 - Special Conditions: Boeing Model 747-8 Series Airplanes; Overhead Flight Attendant Rest Compartment

    Science.gov (United States)

    2011-07-25

    ... detection and fire suppression systems) in conjunction with an OFAR fire to be a catastrophic event. Based... airplanes. These airplanes will have novel or unusual design features associated with the installation of an... issued for other novel or unusual design features of Boeing 747-8 airplanes. DATES: Effective...

  4. 78 FR 70849 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Science.gov (United States)

    2013-11-27

    .... The Boeing Model 777-200 airplanes are long-range, wide-body, twin-engine jet airplanes with a maximum... networks connected to systems that perform functions required for the safe operation of the airplane. This... required for safe flight and operations. 2. The applicant must establish appropriate procedures to...

  5. 75 FR 76647 - Special Conditions: Boeing Model 747-8 Airplanes, Systems and Data Networks Security-Isolation or...

    Science.gov (United States)

    2010-12-09

    ... 747-8 Airplanes, Systems and Data Networks Security--Isolation or Protection From Unauthorized... information services, than previous 747-8 airplane models. This may allow the exploitation of network security... passenger domain computer systems to the airplane critical systems and data networks. The...

  6. 78 FR 11978 - Airworthiness Directives; Reims Aviation S.A. Airplanes

    Science.gov (United States)

    2013-02-21

    ... FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901...: albert.mercado@faa.gov . SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking... information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room...

  7. 77 FR 72252 - Airworthiness Directives; Reims Aviation S.A. Airplanes

    Science.gov (United States)

    2012-12-05

    ... 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... Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,...

  8. 76 FR 63571 - Airworthiness Directives; Eclipse Aerospace, Inc. Airplanes Equipped With Pratt & Whitney Canada...

    Science.gov (United States)

    2011-10-13

    ... Directives; Eclipse Aerospace, Inc. Airplanes Equipped With Pratt & Whitney Canada, Corp. PW610F-A Engines...: We propose to revise an existing airworthiness directive (AD) that applies to all Eclipse Aerospace... 10, 2011), for all Eclipse Aerospace, Inc. Model EA500 airplanes equipped with Pratt & Whitney...

  9. 75 FR 65052 - Consensus Standards, Standard Practice for Maintenance of Airplane Electrical Wiring Systems

    Science.gov (United States)

    2010-10-21

    ... Practice for Maintenance of Airplane Electrical Wiring Systems (Standard Practice) as an acceptable means... FAA finds the standards to be acceptable methods and procedures for maintenance of electrical wiring... Practice for Maintenance of Airplane Electrical Wiring Systems. FOR FURTHER INFORMATION CONTACT:...

  10. 75 FR 7557 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Science.gov (United States)

    2010-02-22

    ..., which could be an ignition source in a hidden area of the airplane. DATES: We must receive comments on... deployment, and burned wires, which could be an ignition source in a hidden area of the airplane. Relevant... work-hour. Required parts would cost about $770 per product. Based on these figures, we estimate...

  11. 76 FR 9265 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System: Control...

    Science.gov (United States)

    2011-02-17

    ... Model GVI Airplane; Electronic Flight Control System: Control Surface Position Awareness AGENCY: Federal... rulemaking by sending written comments, data, or views. The most helpful comments reference a specific... certificate for its new Gulfstream Model GVI passenger airplane. Gulfstream later applied for, and was...

  12. 14 CFR Appendix E to Part 91 - Airplane Flight Recorder Specifications

    Science.gov (United States)

    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...

  13. 14 CFR Appendix D to Part 125 - Airplane Flight Recorder Specification

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specification D Appendix D to Part 125 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION... Appendix D to Part 125—Airplane Flight Recorder Specification Parameters Range Accuracy sensor input...

  14. 14 CFR Appendix D to Part 135 - Airplane Flight Recorder Specification

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specification D Appendix D to Part 135 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION.... D Appendix D to Part 135—Airplane Flight Recorder Specification Parameters Range Accuracy...

  15. 14 CFR Appendix B to Part 135 - Airplane Flight Recorder Specifications

    Science.gov (United States)

    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...

  16. 76 FR 27872 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model P-180 Airplanes

    Science.gov (United States)

    2011-05-13

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

  17. 14 CFR 121.412 - Qualifications: Flight instructors (airplane) and flight instructors (simulator).

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Qualifications: Flight instructors (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...

  18. 76 FR 8278 - Special Conditions: Gulfstream Model GVI Airplane; Enhanced Flight Vision System

    Science.gov (United States)

    2011-02-14

    ... Flight Vision System AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions..., Airplane and Flight Crew Interface Branch, ANM-111, Transport Standards Staff, Transport Airplane... Design Features The enhanced flight vision system (EFVS) is a novel or unusual design feature because...

  19. 76 FR 30043 - Airworthiness Directives; The Boeing Company Model 757 Airplanes

    Science.gov (United States)

    2011-05-24

    ... approach, just before landing. One event resulted in a nose gear collapse after a hard landing and another... oscillations are characterized by large ] wheel inputs at high rates that are out of phase with the airplane... per 4,701 7,676 15,352 (2 airplanes). hour = $2,975. Torque Bracket Assembly and Bond 12 work-hours...

  20. 76 FR 17183 - Aviation Rulemaking Advisory Committee; Transport Airplane and Engine Issues-New Task

    Science.gov (United States)

    2011-03-28

    ... airplane hull loss. The National Transportation Safety Board (NTSB) found ``that the probable cause of this.... John's to Deer Lake, Newfoundland, with 36 passengers and 3 crew on board. During the climb-out from St. John's, the indicated airspeed gradually decreased to the point that the airplane entered...

  1. 78 FR 6195 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection...

    Science.gov (United States)

    2013-01-30

    ... jet airplanes designed for corporate flight, fractional, charter, and private owner operations. The... turbofan engines mounted on aft fuselage pylons. Each engine produces approximately 6,540 pounds of thrust... function into the engine of the Model EMB-550 airplane. It has a full authority digital electronic...

  2. 76 FR 8314 - Special Conditions: Gulfstream Model GVI Airplane; Operation Without Normal Electric Power

    Science.gov (United States)

    2011-02-14

    ..., 2006. The Gulfstream Model GVI airplane will be an all-new, two- engine jet transport airplane with an... traditional designs, the GVI must be designed for operation with the normal sources of engine and auxiliary...; Operation Without Normal Electric Power AGENCY: Federal Aviation Administration (FAA), DOT. ACTION:...

  3. 14 CFR Appendix E to Part 125 - Airplane Flight Recorder Specifications

    Science.gov (United States)

    2010-01-01

    ... propeller airplane) Stowed, In Transit, and Reverse (Discrete) 1 (per engine). Turbo-jet—2 discretes enable... (CONTINUED) AIR CARRIERS AND OPERATORS FOR COMPENSATION OR HIRE: CERTIFICATION AND OPERATIONS CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM...

  4. 76 FR 65105 - Special Conditions: Gulfstream Aerospace Corporation, Model GIV-X Airplane; Isolation or Aircraft...

    Science.gov (United States)

    2011-10-20

    ... passenger airplane. The Gulfstream Model GIV-X is a two-engine jet transport airplane with a maximum takeoff... Operations, M-30, U.S. Department of Transportation (DOT), 1200 New Jersey Avenue, SE., Room W12-140, West... Operations in Room W12-140 of the West Building Ground Floor at 1200 New Jersey Avenue, SE., Washington,...

  5. 78 FR 63848 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Sidestick Controllers

    Science.gov (United States)

    2013-10-25

    ... the comment for an association, business, labor union, etc.). DOT's complete Privacy Act Statement can... airplane will use passive sidestick controllers for pitch and roll control instead of a conventional... following novel or unusual design features: The Model EMB-550 airplane has a sidestick controller for...

  6. 75 FR 38950 - Airworthiness Directives; The Boeing Company Model 727 Airplanes

    Science.gov (United States)

    2010-07-07

    ... Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425... wing-to-body fairings. The airplane has never had any decals installed in inspection areas since delivery. The existing repairs on the airplane span at least 3 rows above/forward and 3 rows below/aft...

  7. 76 FR 25229 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane, Dynamic Test Requirements...

    Science.gov (United States)

    2011-05-04

    ..., and a range of approximately 3,400 nautical miles. Airplane dimensions are 61.69-foot wing span, 66.6..., Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton, Washington... of the design approval and thus delivery of the affected aircraft. In addition, the substance...

  8. 76 FR 35736 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane Automatic Power Reserve...

    Science.gov (United States)

    2011-06-20

    ... approximately 3,400 nautical miles. Airplane dimensions are 61.69-foot wing span, 66.6-foot overall length, and... INFORMATION CONTACT: Joe Jacobsen, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind... takeoff and go- around (TOGA). The aircraft performance data is based on the availability of the...

  9. 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.

  10. 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.

  11. Economic impact of applying advanced technologies to transport airplanes.

    Science.gov (United States)

    Carline, A. J. K.

    1972-01-01

    Various technologies have been studied which could have application to the design of future transport airplanes. These technologies include the use of supercritical aerodynamics, composite materials, and active control systems, together with advanced engine designs that provide lower noise and pollutant levels. The economic impact of each technology is shown for a typical fleet of 195-passenger, transcontinental commercial transports cruising at both 0.9M and 0.98M. Comparisons are made with conventional transports cruising at 0.82M. Effects of combining the technologies are discussed. An R & D program aimed at bringing the technologies to fruition is outlined.

  12. STATIC TESTS OF UNCONVENTIONAL PROPULSION UNITS FOR ULTRALIGHT AIRPLANES

    Directory of Open Access Journals (Sweden)

    Martin Helmich

    2014-06-01

    Full Text Available This paper presents static tests of a new unconventional propulsion unit for small aviation airplanes. Our laboratory stand – a fan drive demonstrator – enables us to compare various design options. We performed experiments to verify the propulsion functionality and a measurement procedure to determine the available thrust of the propulsion unit and its dependence on engine speed. The results used for subsequent optimization include the operating parameters of the propulsion unit, and the temperature and velocity fields in parts of the air duct.

  13. An Accurate Method for Measuring Airplane-Borne Conformal Antenna's Radar Cross Section

    Science.gov (United States)

    Guo, Shuxia; Zhang, Lei; Wang, Yafeng; Hu, Chufeng

    2016-09-01

    The airplane-borne conformal antenna attaches itself tightly with the airplane skin, so the conventional measurement method cannot determine the contribution of the airplane-borne conformal antenna to its radar cross section (RCS). This paper uses the 2D microwave imaging to isolate and extract the distribution of the reflectivity of the airplane-borne conformal antenna. It obtains the 2D spatial spectra of the conformal antenna through the wave spectral transform between the 2D spatial image and the 2D spatial spectrum. After the interpolation from the rectangular coordinate domain to the polar coordinate domain, the spectral domain data for the variation of the scatter of the conformal antenna with frequency and angle is obtained. The experimental results show that the measurement method proposed in this paper greatly enhances the airplane-borne conformal antenna's RCS measurement accuracy, essentially eliminates the influences caused by the airplane skin and more accurately reveals the airplane-borne conformal antenna's RCS scatter properties.

  14. 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.

  15. Applying face identification to detecting hijacking of airplane

    Science.gov (United States)

    Luo, Xuanwen; Cheng, Qiang

    2004-09-01

    That terrorists hijacked the airplanes and crashed the World Trade Center is disaster to civilization. To avoid the happening of hijack is critical to homeland security. To report the hijacking in time, limit the terrorist to operate the plane if happened and land the plane to the nearest airport could be an efficient way to avoid the misery. Image processing technique in human face recognition or identification could be used for this task. Before the plane take off, the face images of pilots are input into a face identification system installed in the airplane. The camera in front of pilot seat keeps taking the pilot face image during the flight and comparing it with pre-input pilot face images. If a different face is detected, a warning signal is sent to ground automatically. At the same time, the automatic cruise system is started or the plane is controlled by the ground. The terrorists will have no control over the plane. The plane will be landed to a nearest or appropriate airport under the control of the ground or cruise system. This technique could also be used in automobile industry as an image key to avoid car stealth.

  16. Natural laminar flow airfoil design considerations for winglets on low-speed airplanes

    Science.gov (United States)

    Vandam, C. P.

    1984-01-01

    Winglet airfoil section characteristics which significantly influence cruise performance and handling qualities of an airplane are discussed. A good winglet design requires an airfoil section with a low cruise drag coefficient, a high maximum lift coefficient, and a gradual and steady movement of the boundary layer transition location with angle of attack. The first design requirement provides a low crossover lift coefficient of airplane drag polars with winglets off and on. The other requirements prevent nonlinear changes in airplane lateral/directional stability and control characteristics. These requirements are considered in the design of a natural laminar flow airfoil section for winglet applications and chord Reynolds number of 1 to 4 million.

  17. 76 FR 15818 - Airworthiness Directives; Reims Aviation S.A. Model F406 Airplanes

    Science.gov (United States)

    2011-03-22

    ... availability of this material at the FAA, call 816-329-4148. FOR FURTHER INFORMATION CONTACT: Albert Mercado...: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas...

  18. 76 FR 35344 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Model P2006T Airplanes

    Science.gov (United States)

    2011-06-17

    ...: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City... 14 CFR 39.19. Send information to Attn: Albert Mercado, Aerospace Engineer, FAA, Small...

  19. 78 FR 75453 - Special Conditions: Cessna Model 750 Series Airplanes; Aircraft Electronic System Security...

    Science.gov (United States)

    2013-12-12

    ... September 10, 2010, Cessna applied for a change to Type Certificate No. T00007WI in the digital systems architecture in the Cessna Model 750 series airplanes. The Model 750 is a twin-engine pressurized executive...

  20. 76 FR 17022 - Special Conditions: Gulfstream Model GVI Airplane; High Incidence Protection

    Science.gov (United States)

    2011-03-28

    ... techniques. (3) The requirements for turning flight maneuver demonstrations must also be met with accelerated... abnormal airplane nose-up pitching. (2) No uncommanded nose-down pitching (which is indicative of...

  1. 76 FR 66660 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane, Operation Without Normal...

    Science.gov (United States)

    2011-10-27

    ... G280 Airplane, Operation Without Normal Electrical Power AGENCY: Federal Aviation Administration (FAA... design feature associated with operation without normal electrical power. The applicable airworthiness... have a novel or unusual design feature associated with operation without normal electrical power....

  2. Ditching Investigation of a 1/14-Scale Model of the Northrop C-125 Airplane

    Science.gov (United States)

    Fisher, Lloyd J.; Windham, John O.

    1950-01-01

    An investigation of a 1/14-scale dynamically similar model of the Northrop C-125 airplane was made to determine the ditching characteristics and proper ditching technique for the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion-picture records, and time-history deceleration records. The results of the investigation are presented in table form, photographs, and curves. It was concluded that the airplane should be ditched at a nose-high landing attitude (near 8 deg) with flaps full down. The fixed landing gear will cause the airplane to dive. The fuselage will be damaged and will probably flood rapidly. Longitudinal decelerations will be about 4g and the length of landing run will be about two fuselage lengths. If the main landing gear could be jettisonable or retractable the ditching characteristics would be greatly improved.

  3. 76 FR 14795 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System Mode...

    Science.gov (United States)

    2011-03-18

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System Mode Annunciation. AGENCY: Federal Aviation Administration (FAA), DOT... ``Gulfstream'') applied for an FAA type certificate for its new Gulfstream Model GVI passenger...

  4. The Research and Application About "Dry Peeling Off" Technology for Airplane Surface Paint Layer

    Institute of Scientific and Technical Information of China (English)

    WANG Ding-jiang; TANG Zheng-jie; CHEN Ming-hua; GUO Bi-xin; Chen Yi-can; TANG Ying

    2004-01-01

    In this paper, the principle of spurting take off lacquer were introduced; and with orthogonal method the unsaturate polyester was prepared ;it was easy to peel airplane paint layer off with this material and equipment.

  5. 76 FR 65991 - Airworthiness Directives; The Boeing Company Model 757 Airplanes

    Science.gov (United States)

    2011-10-25

    ... horizontal stabilizer ballscrew assembly; repetitive lubrication of the horizontal stabilizer trim control..., damage, cracking, corrosion, or wear); repetitive lubrication of the horizontal stabilizer trim control...-time'' replacement program. The proposed AD includes credit for airplanes on which any HSTA...

  6. An Evaluation of Automatic Control System Concepts for General Aviation Airplanes

    Science.gov (United States)

    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.

  7. “COANDA-1910” - the first jet propulsor for airplane

    Directory of Open Access Journals (Sweden)

    Romulus PETCU

    2010-12-01

    Full Text Available This paper contains the authors’ research regarding the first airplane equippedwith a jet propulsion system made by Henri Coanda in 1910, also being homage pays toHenri Coanda, his inventor.

  8. Measurement of visibility from the pilot's cockpit on different airplane types

    Science.gov (United States)

    Kurz, Gerhard

    1931-01-01

    A process for the measurement of the visibility of airplanes from the pilot's cockpit is developed. The apparatus necessary for the measurements was suitably constructed and measurements of the fields of vision were made with it. The visibilities of six airplanes of different types of construction and use were measured, as well as the visibility of an automobile for comparison. An attempt was made to establish minimum visibility requirements and to express the excellence of visibility by means of a numerical coefficient.

  9. Flutter clearance of the horizontal tail of the Bellanca Skyrocket II airplane

    Science.gov (United States)

    Ricketts, R. H.; Cazier, F. W., Jr.; Farmer, M. G.

    1982-01-01

    The Skyrocket II is an all composite constructed experimental prototype airplane. A flutter clearance program was conducted on the horizontal tail so that the airplane could be safely flown to acquire natural laminar flow aerodynamic data. Ground vibration test data were used in a lifting surface flutter analysis to predict symmetric and antisymmetric flutter boundaries. Subcritical response data which were acquired during flight tests are compared with the analytical results. The final flutter clearance placard speed was based on flight test data.

  10. 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.

  11. AN AIRPLANE WITH UNCONVENTIONALLY PLACED PROPELLER POWER UNIT

    Directory of Open Access Journals (Sweden)

    Jan Červinka

    2017-02-01

    Full Text Available The significance of the influence of operating propellers on the aircraft aerodynamic characteristics is well-known. Wind tunnel testing of an airplane model with operating propellers is a complex task regarding the required similarity of the full-scale and the model case. Matching sufficient similarity in axial and rotational velocities in the propeller slipstream is the primordial condition for the global aerodynamic similarity of the windtunnel testing. An example of the model power units with related devices is presented. Examples of the wind tunnel testing results illustrate the extent of the propeller influence on aerodynamic characteristics of an aircraft of unconventional configuration with power units positioned at the fuselage afterbody.

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

    Science.gov (United States)

    Fisher, Lloyd J.; Thompson, William C.

    1949-01-01

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

  13. 78 FR 75284 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Flight...

    Science.gov (United States)

    2013-12-11

    ... airplanes will incorporate the following novel or unusual design features: An electronic flight control...-1A11 series airplanes. These airplanes will have a novel or unusual design feature associated with an electronic flight control system that contains fly-by-wire control laws, including envelope protections,...

  14. 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.

  15. Application of Monte Carlo Technique for Determining Maneuvering Loads from Statistical Information on Airplane Motions

    Science.gov (United States)

    Hamer, Harold A.; Mayer, John P.; Huston, Wilber B.

    1961-01-01

    Results of a statistical analysis of horizontal-tail loads on a fighter airplane are presented. The data were obtained from a number of operational training missions with flight at altitudes up to about 50,000 feet and at Mach numbers up to 1.22. The analysis was performed to determine the feasibility of calculating horizontal-tail load from data on the flight conditions and airplane motions. In the analysis the calculated loads are compared with the measured loads for the different types of missions performed. The loads were calculated by two methods: a direct approach and a Monte Carlo technique. The procedures used and some of the problems associated with the data analysis are discussed. frequencies of occurrence of tail loads of given magnitudes are derived from statistical information on the flight quantities. In the direct method, a time history of tail load is calculated from time-history measurements of the flight quantities. The Monte Carlo method could be useful for extending loads information for design of prospective airplanes . For the Monte Carlo method, the The results indicate that the accuracy of loads, regardless of the method used for calculation, is largely dependent on the knowledge of the pertinent airplane aerodynamic characteristics and center-of-gravity location. In addition, reliable Monte Carlo results require an adequate sample of statistical data and a knowledge of the more important statistical dependencies between the various flight conditions and airplane motions.

  16. 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.

  17. Flight-measured lift and drag characteristics of a large, flexible, high supersonic cruise airplane

    Science.gov (United States)

    Arnaiz, H. H.

    1977-01-01

    Flight measurements of lift, drag, and angle of attack were obtained for the XB-70 airplane, a large, flexible, high supersonic cruise airplane. This airplane had a length of over 57 meters, a takeoff gross mass of over 226,800 kilograms, and a design cruise speed of Mach 3 at an altitude of 21,340 meters. The performance measurements were made at Mach numbers from 0.72 to 3.07 and altitudes from approximately 7620 meters to 21,340 meters. The measurements were made to provide data for evaluating the techniques presently being used to design and predict the performance of aircraft in this category. Such performance characteristics as drag polars, lift-curve slopes, and maximum lift-to-drag ratios were derived from the flight data. The base drag of the airplane, changes in airplane drag with changes in engine power setting at transonic speeds, and the magnitude of the drag components of the propulsion system are also discussed.

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

    Science.gov (United States)

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

    2014-01-01

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

  19. 75 FR 3127 - Airworthiness Directives; Thrush Aircraft, Inc. Model 600 S2D and S2R Series Airplanes

    Science.gov (United States)

    2010-01-20

    ... wing front lower spar caps in Thrush Aircraft, Inc. Model 600 S2D and S2R (S-2R) series airplanes (type..., which applies to Thrush Aircraft, Inc. Model 600 S2D and S2R (S-2R) series airplanes (type certificate... Environmental Conditions Avenger Aircraft and Services (Avenger) states the life limits for the wing front...

  20. 76 FR 7694 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2011-02-11

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The..., etc. for PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 airplanes. As published, the...

  1. 75 FR 67639 - Airworthiness Directives; Piaggio Aero Industries S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-11-03

    ... Industries S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airplane Flight Manual, stating that the towing bar P/N 01-1227-0000 or similar ferromagnetic masses are... maintenance requirements and/or airworthiness limitations developed by Piaggio Aero Industries S.p.A....

  2. 78 FR 68985 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Science.gov (United States)

    2013-11-18

    ... and connectivity of the passenger service computer network systems to the airplane critical systems... perform functions required for the safe operation of the airplane. This proposed data network and design... computer network system, and a network extension device. The network extension device will improve...

  3. 78 FR 5146 - Special Conditions: Embraer S.A., Model EMB-550 Airplane, Dive Speed Definition With Speed...

    Science.gov (United States)

    2013-01-24

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

  4. 78 FR 11560 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Electronic Flight Control System...

    Science.gov (United States)

    2013-02-19

    ... date: March 21, 2013. FOR FURTHER INFORMATION CONTACT: Joe Jacobsen, FAA, Airplane and Flight Crew...(c) and will not be ``substantially proportional to the angle of sideslip'' as required by the rule. The longitudinal flight control laws for the Model EMB-550 airplane provide neutral static...

  5. 77 FR 69573 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Electronic Flight Control System...

    Science.gov (United States)

    2012-11-20

    ... FURTHER INFORMATION CONTACT: Joe Jacobsen, FAA, Airplane and Flight Crew Interface Branch, ANM-111... Regulations (14 CFR) 25.177(c) and will not be ``substantially proportional to the angle of sideslip'' as... static stability within the normal operational envelope; therefore, the airplane design does not...

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

    Science.gov (United States)

    2013-01-30

    ...-112 airplane is a large, transport-category airplane powered by two CFM56-5B9/P engines, with a basic...) to a corporate jet, operating for both common carriage and private use. As of this publication... temperature set on ``high,'' and the timer at maximum, the cooktop will maintain safe operation and will...

  7. 78 FR 11555 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Design Roll Maneuver for Electronic...

    Science.gov (United States)

    2013-02-19

    ...; Design Roll Maneuver for Electronic Flight Controls AGENCY: Federal Aviation Administration (FAA), DOT... EMB-550 airplane. This airplane will have a novel or unusual design feature(s) associated with the design roll maneuver for electronic flight controls, specifically an electronic flight control...

  8. 78 FR 14005 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: Pitch and...

    Science.gov (United States)

    2013-03-04

    ... following novel or unusual design feature: An electronic flight control system which contains fly-by-wire... Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design feature associated with pitch and roll limiting functions, specifically an electronic flight control system which...

  9. 77 FR 75071 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Electrical/Electronic Equipment Bay...

    Science.gov (United States)

    2012-12-19

    ...; Electrical/Electronic Equipment Bay Fire Detection and Smoke Penetration AGENCY: Federal Aviation... conditions for the Embraer S.A. Model EMB-550 airplane. This airplane will have novel or unusual design features, specifically distributed electrical and electronic equipment bays in pressurized areas of...

  10. 76 FR 64854 - Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes

    Science.gov (United States)

    2011-10-19

    ..., A319, A320, and A321 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... section revision to the airplane flight manual and the installation of a new flight warning computer (FWC... thrust lever configuration and to correct this. For the A320 family of aeroplanes this being IDLE...

  11. 75 FR 2433 - Special Conditions: Boeing Model 747-8/-8F Airplanes, Systems and Data Networks Security...

    Science.gov (United States)

    2010-01-15

    ... Security--Protection of Airplane Systems and Data Networks From Unauthorized External Access AGENCY... external systems and networks may result in security vulnerabilities to the airplane's systems. The... network sources. The architecture and network configuration may allow the exploitation of network...

  12. [The airplane accident in Torghatten on May 6, 1988].

    Science.gov (United States)

    Solheim, T; Stene-Johansen, W; Lorentsen, M; Sakshaug, O

    1989-01-01

    On May 6th, 1988, a Dash 7 airplane crashed into the mountain of Torghatten, near Brønnøy-sund in northern Norway. All 33 passengers and the three crew members were killed. The National Identification Commission, including a forensic dentist, was at the disaster site twelve hours later. A dentist and a forensic pathologist worked with the police at the site until all the victims had been found. Three other dentists were responsible for collecting antemortem material and for the postmortem examination of all victims. 32 of the victims, or 89%, could be identified by dental means alone; a higher percentage than ever before reported. The final meeting of the Identification Commission took place five days after the disaster. All the victims were identified on the basis of technical, medical, and dental evidence, and the report signed by each of the three specialist groups. The quality of the dental records was evaluated with respect to requirements set up by the Ministry of Social Affairs in 1983. Dental records had improved since the "Alexander Kielland" disaster in 1980. However, only five of the missing persons had full mouth intraoral radiography, only nine records met the requirements for general information about the patient (birth date and identification number, home and business address, etc), only three had information about earlier diseases, and none had recorded previous dental restorations. Diagnoses were given only for nine persons. The records showed that 21 of the victims had not received any prophylactic treatment.

  13. A New Intelligent Airplane Landing Planning Method in Congested Airports

    Directory of Open Access Journals (Sweden)

    Kazem Dastgerdi

    2015-06-01

    Full Text Available Nowadays considering many advantages of air traveling, we notice that traffic congestion has significantly increased in airspace of countries, and it is expected that this growth rate, increases even more in the forthcoming years.This growth rate and different limitations posed on developing some airports led to the problem of landing airplanes to become one of the most important issues formed in the field of aviation. In this paper, in the form of a new approach based on CPSO algorithm for intelligent landing planning, determining optimal landing times, optimal allocation of runways, and at last the order of successive landings of planes has been done in a way that appropriately fulfills the main goal of the problem (minimizing the total flights delays; thus helping significantly to controlling air traffic congestion in airports approaches. The simulation results show that compared to the last presented methods, including methods based on genetic algorithms, GLS and Bionomic, has decreased the total amounts of flight delays considerably. Getting zero for total amount of flight delays for the two problems with real data of DFW airport in Texas, United States, confirms the more capability of CPSO algorithm compared to the other intelligent methods for obtaining optimal solutions to the problem.

  14. Self-propelled pedestrian dynamics model: Application to passenger movement and infection propagation in airplanes

    Science.gov (United States)

    Namilae, S.; Srinivasan, A.; Mubayi, A.; Scotch, M.; Pahle, R.

    2017-01-01

    Reducing the number of contacts between passengers on an airplane can potentially curb the spread of infectious diseases. In this paper, a social force based pedestrian movement model is formulated and applied to evaluate the movement and contacts among passengers during boarding and deplaning of an airplane. Within the social force modeling framework, we introduce location dependence on the self-propelling momentum of pedestrian particles. The model parameters are varied over a large design space and the results are compared with experimental observations to validate the model. This model is then used to assess the different approaches to minimize passenger contacts during boarding and deplaning of airplanes. We find that smaller aircrafts are effective in reducing the contacts between passengers. Column wise deplaning and random boarding are found to be two strategies that reduced the number of contacts during passenger movement, and can potentially lower the likelihood of infection spread.

  15. Self-Propelled Pedestrian Dynamics Model: Application to Passenger Movement and Infection Propagation in Airplanes

    CERN Document Server

    Namilae, S; Mubayi, A; Scotch, M; Pahle, R

    2016-01-01

    Reducing the number of contacts between passengers on an airplane can potentially curb the spread of infectious diseases. In this paper, a social force based pedestrian movement model is formulated and applied to evaluate the movement and contacts among passengers during boarding and deplaning of an airplane. Within the social force modeling framework, we introduce location dependence on the self-propelling momentum of pedestrian particles. The model parameters are varied over a large design space and the results are compared with experimental observations to validate the model. This model is then used to assess the different approaches to minimize passenger contacts during boarding and deplaning of airplanes. We find that smaller aircrafts are effective in reducing the contacts between passengers. Column wise deplaning and random boarding are found to be two strategies that reduced the number of contacts during passenger movement, and can potentially lower the likelihood of infection spread.

  16. Ditching Investigation of a 1/14-Scale Model of the XC-123 Airplane

    Science.gov (United States)

    Fisher, Lloyd J.; Thompson, William C.

    1951-01-01

    An investigation of a 1/14 scale dynamically similar model of the XC-123 airplane was made in calm water to observe the ditching behavior and to determine the safest procedure for making an emergency water landing, The behavior of the model was determined from motion-picture records, time-history deceleration records, and visual observations, Various scale-strength simulations were made to determine if the fuselage would be damaged and, if so, to determine the extent and location, It was concluded that the airplane should be ditched at a nose-high attitude of about 140 with the landing flaps down 45 deg., The airplane will probably make a porpoising run of about 415 feet (full scale) and the maximum longitudinal decelerations will be about 1 g, The fuselage bottom probably will be damaged and the fuselage will fill with water and sink to the wing level.

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

    Science.gov (United States)

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

    1948-01-01

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

  18. Research on the mechanical behaviour of an airplane component made by selective laser melting technology

    Directory of Open Access Journals (Sweden)

    Păcurar Răzvan

    2017-01-01

    Full Text Available The main objective of the presented research consists in the redesign of an airplane component to decrease its weight, without affecting the mechanical behaviour of the component, at the end. Femap NX Nastran and ANSYS FEA programs were used for the shape optimization and for the estimation of the mechanical behaviour of a fixing clamp that was used to sustain the hydraulic pipes that are passing through an airplane fuselage, taking into consideration two types of raw materials – Ti6Al4V and AlSi12 powder from which this component could be manufactured by using the selective laser melting (SLM technology. Based on the obtained results, the airplane component was finally manufactured from titanium alloy using the SLM 250 HL equipment that is available at SLM Solutions GmbH company from Luebeck, in Germany.

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

    Science.gov (United States)

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

    1984-01-01

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

  20. Design study of technology requirements for high performance single-propeller-driven business airplanes

    Science.gov (United States)

    Kohlman, D. L.; Hammer, J.

    1985-01-01

    Developments in aerodyamic, structural and propulsion technologies which influence the potential for significant improvements in performance and fuel efficiency of general aviation business airplanes are discussed. The advancements include such technolgies as natural laminar flow, composite materials, and advanced intermittent combustion engines. The design goal for this parameter design study is a range of 1300 nm at 300 knots true airspeed with a payload of 1200lbs at 35,000 ft cruise altitude. The individual and synergistic effects of various advanced technologies on the optimization of this class of high performance, single engine, propeller driven business airplanes are identified.

  1. A Hardware-in-the-Loop Simulator for Software Development for a Mars Airplane

    Science.gov (United States)

    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++).

  2. Estimation of bias errors in measured airplane responses using maximum likelihood method

    Science.gov (United States)

    Klein, Vladiaslav; Morgan, Dan R.

    1987-01-01

    A maximum likelihood method is used for estimation of unknown bias errors in measured airplane responses. The mathematical model of an airplane is represented by six-degrees-of-freedom kinematic equations. In these equations the input variables are replaced by their measured values which are assumed to be without random errors. The resulting algorithm is verified with a simulation and flight test data. The maximum likelihood estimates from in-flight measured data are compared with those obtained by using a nonlinear-fixed-interval-smoother and an extended Kalmar filter.

  3. Status of a digital integrated propulsion/flight control system for the YF-12 airplane

    Science.gov (United States)

    Reukauf, P. J.; Burcham, F. W., Jr.; Holzman, J. K.

    1975-01-01

    The NASA Flight Research Center is engaged in a program with the YF-12 airplane to study the control of interactions between the airplane and the propulsion system. The existing analog air data computer, autothrottle, autopilot, and inlet control system are to be converted to digital systems by using a general purpose airborne computer and interface unit. First, the existing control laws will be programmed in the digital computer and flight tested. Then new control laws are to be derived from a dynamic propulsion model and a total force and moment aerodynamic model to integrate the systems. These control laws are to be verified in a real time simulation and flight tested.

  4. Scaling behavior of an airplane-boarding model.

    Science.gov (United States)

    Brics, Martins; Kaupužs, Jevgenijs; Mahnke, Reinhard

    2013-04-01

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

  5. Analysis of VGH data from two types of four-engine airplanes in commercial cargo service

    Science.gov (United States)

    Healy, F. M.

    1972-01-01

    Data are presented for derived gust velocities and for incremental normal accelerations due to gusts, maneuvers, and landing impacts. The data were obtained from NASA VGH recorders installed on three four-engine cargo airplanes operated by three airlines. Continental United States and trans-Pacific routes were covered.

  6. 76 FR 48045 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Model P2006T Airplanes

    Science.gov (United States)

    2011-08-08

    ... material at the FAA, call (816) 329-4148; e-mail: albert.mercado@faa.gov . Examining the AD Docket You may... Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri... found in 14 CFR 39.19. Send information to ATTN: Albert Mercado, Aerospace Engineer, FAA, Small...

  7. 78 FR 275 - Airworthiness Directives; REIMS Aviation S.A. Airplanes

    Science.gov (United States)

    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,...

  8. 78 FR 19088 - Airworthiness Directives; REIMS AVIATION S.A. Airplanes

    Science.gov (United States)

    2013-03-29

    ... 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,...

  9. 75 FR 45075 - Airworthiness Directives; Eclipse Aerospace, Inc. Model EA500 Airplanes

    Science.gov (United States)

    2010-08-02

    ... Directives; Eclipse Aerospace, Inc. Model EA500 Airplanes AGENCY: Federal Aviation Administration (FAA... Register on July 9, 2010 (75 FR 39472), and applies to certain Eclipse Aerospace, Inc. (Eclipse) Model... Reduction Modification per any revision level of Eclipse SB 500-99-001'' instead of ``000039 through...

  10. 76 FR 78526 - Airworthiness Directives; Eclipse Aerospace, Inc. Airplanes Equipped With Pratt & Whitney Canada...

    Science.gov (United States)

    2011-12-19

    ...-005-AD; Amendment 39-16890; AD 2011-06-06 R1] RIN 2120-AA64 Airworthiness Directives; Eclipse... directive (AD) that applies to all Eclipse Aerospace, Inc. Model EA500 airplanes equipped with Pratt...: 2011-06-06 R1 Eclipse Aerospace, Inc.: Amendment 39-16890; Docket No. FAA-2011-0199;...

  11. 75 FR 39472 - Airworthiness Directives; Eclipse Aerospace, Inc. Model EA500 Airplanes

    Science.gov (United States)

    2010-07-09

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Eclipse Aerospace... directive (AD) for certain Eclipse Aerospace, Inc. (Eclipse) Model EA500 airplanes. This proposed AD would... proposed AD, contact Eclipse Aerospace, Incorporated, 2503 Clark Carr Loop, SE., Albuquerque, New...

  12. 14 CFR 26.39 - Newly produced airplanes: Fuel tank flammability.

    Science.gov (United States)

    2010-01-01

    ... TRANSPORTATION AIRCRAFT CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES Fuel...) that meet the requirements of 14 CFR 25.981 in effect on December 26, 2008. (1) The fuel tank is... tank exceeds a Fleet Average Flammability Exposure of 7 percent. (c) All other fuel tanks that...

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

    Science.gov (United States)

    2010-10-06

    ... revising the limitations section of the supplement airplane maintenance manual. This proposed AD results... of electrical power to the FADEC. We are proposing this AD to prevent interruption of electrical... unsafe design feature that allowed momentary interruption of electrical power to both engine FADECs....

  14. 78 FR 76248 - Special Conditions: Airbus, Model A350-900 Series Airplane; Side Stick Controller

    Science.gov (United States)

    2013-12-17

    ..., 2000 (65 FR 19477-19478), as well as at http:// DocketsInfo.dot.gov/ . Docket: Background documents or... Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW... by wrist and not by arms. Discussion Special conditions for Airbus side stick controllers have...

  15. 14 CFR Appendix B to Part 121 - Airplane Flight Recorder Specification

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane Flight Recorder Specification B Appendix B to Part 121 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION... Flight Recorder Specification Parameters Range Accuracy sensor input to DFDR readout Sampling...

  16. 76 FR 37258 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Science.gov (United States)

    2011-06-27

    ..., 2010, of Bombardier Q400 Dash 8 Maintenance Requirements Manual, PSM 1-84-7, at the applicable times... Requirements Manual, PSM 1-84-7, within 6,000 flight hours after the effective date of this AD. (i) Airplanes... Requirements Manual, PSM 1-84-7, was successfully completed after incorporation of Bombardier Modsum...

  17. 75 FR 5690 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A. Model P-180 Airplanes

    Science.gov (United States)

    2010-02-04

    ... INDUSTRIES S.p.A. Model P- 180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM...: 2010-03-04 PIAGGIO AERO INDUSTRIES S.p.A.: Amendment 39-16187; Docket No. FAA-2009-1081;...

  18. 76 FR 1979 - Airworthiness Directives; The Boeing Company Model 757 Airplanes

    Science.gov (United States)

    2011-01-12

    ... -300 series airplanes. This AD requires an inspection of the two spring arms in the spin brake assemblies in the nose wheel well to determine if the spring arms are made of aluminum or composite material... assemblies in the nose wheel well to determine if the spring arms are made of aluminum or composite...

  19. 75 FR 12468 - Airworthiness Directives; Quartz Mountain Aerospace, Inc. Model 11E Airplanes

    Science.gov (United States)

    2010-03-16

    ... With the next 10 Follow Quartz aileron pushrod bearings. hours time-in- Mountain Aerospace service (TIS... aileron Within 50 hours TIS Follow Quartz pushrod bearings. after the cleaning Mountain Aerospace and... Aerospace, Inc. Model 11E Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  20. 78 FR 59223 - Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes

    Science.gov (United States)

    2013-09-26

    ... FURTHER INFORMATION CONTACT: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust... identify and modify the affected NLG actuators, which includes installation of a new rod end bearing and... 0001 and 0155 (inclusive), modify the actuator by replacing the NLG rod end bearing and safety...

  1. 78 FR 70209 - Airworthiness Directives; XtremeAir GmbH Airplanes

    Science.gov (United States)

    2013-11-25

    ... bearing and the lower engine mount to the firewall attachment plate, which could reduce the structural..., Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106... crack was reported by an operator in a weld seam between the lower left landing gear attachment...

  2. 75 FR 30282 - Airworthiness Directives; Quartz Mountain Aerospace, Inc. Model 11E Airplanes

    Science.gov (United States)

    2010-06-01

    ... bearings. hours time-in- Mountain Aerospace service (TIS) after Mandatory Service July 6, 2010 (the... hours TIS Follow Quartz pushrod bearings. after the cleaning Mountain Aerospace and lubrication... Aerospace, Inc. Model 11E Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  3. 75 FR 70854 - Harmonization of Various Airworthiness Standards for Transport Category Airplanes-Flight Rules

    Science.gov (United States)

    2010-11-19

    ... takeoff technique into consideration. The FAA proposes to allow reduction of both the all-engines... pitching moment, unless that pitching moment is small. The proposed revision would harmonize our high-speed... instruments or control the airplane for recovery; or (iii) A nose down pitching moment, unless it is small....

  4. An example of applied colour vision research: the conspicuity of airplane colour

    NARCIS (Netherlands)

    Lucassen, M.P.

    2002-01-01

    This paper describes the application of the combined knowledge on colorimetry, colour imaging (visualization) and colour perception in an aviation related research project. It involves the optimisation of the conspicuity of the colour scheme of an airplane, with the purpose of minimizing the changes

  5. A Conceptual Design and Analysis Method for Conventional and Unconventional Airplanes

    NARCIS (Netherlands)

    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.

  6. 75 FR 75 - Special Conditions: Boeing Model 787-8 Airplane; Overhead Crew Rest Compartment

    Science.gov (United States)

    2010-01-04

    ... Model 787-8 Airplane; Overhead Crew Rest Compartment AGENCY: Federal Aviation Administration (FAA), DOT... installation of an overhead crew rest compartment. The applicable airworthiness regulations do not contain... Design Features Crew rest compartments have been installed and certificated on several Boeing...

  7. 77 FR 19148 - Special Conditions: Airbus, A350-900 Series Airplane; Crew Rest Compartments

    Science.gov (United States)

    2012-03-30

    ...-900 Series Airplane; Crew Rest Compartments AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... separate Crew Rest Compartments: a Flight Crew Rest Compartment (FCRC) intended to be occupied by flight crew members only, and a Cabin Crew Rest Compartment (CCRC) intended to be occupied by cabin...

  8. 76 FR 81360 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane, Operation Without Normal...

    Science.gov (United States)

    2011-12-28

    ... G280 Airplane, Operation Without Normal Electrical Power AGENCY: Federal Aviation Administration (FAA... associated with operation without normal electrical power. The applicable airworthiness regulations do not... Model G280 will have a novel or unusual design feature associated with operation without...

  9. 76 FR 31454 - Special Conditions: Gulfstream Model GVI Airplane; Automatic Speed Protection for Design Dive Speed

    Science.gov (United States)

    2011-06-01

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

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

    Science.gov (United States)

    Fisher, Lloyd J.; Windham, John O.

    1950-01-01

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

  11. SIMULATION OF FLUID-SOLID INTERACTION ON WATER DITCHING OF AN AIRPLANE BY ALE METHOD

    Institute of Scientific and Technical Information of China (English)

    HUA Cheng; FANG Chao; CHENG Jin

    2011-01-01

    Ditching is considered as one of the important aspects of safety performances of airplanes.It is related primarily with the fluid-solid interaction,whose studies mainly depend on experiments at the present time.Numerical and analytical methods for fluid-solid interaction by using 3-D full scale airplane's model will reduce the dependence on the expensive model tests.Numerical studies can be used to estimate the safety of ditching and provide a reference for the crashworthiness design.This article proposes a 3-D dynamical structural model after the real shape of an airplane and an Arbitrary Lagrange-Euler (ALE) fluid-field model,to simulate the fluid-solid interactions caused by low speed ditching.The simulation is based on interaction computational methods,within LS-DYNA nonlinear finite-element code.The results of pressure distributions and accelerating time histories of the airplane's subfloor are discussed in the context of the safety of ditching,and the simulation results and the analytical methods are verified.

  12. Ditching Investigation of a 1/20-Scale Model of the Boeing Stratocruiser Airplane (C-97)

    Science.gov (United States)

    Fisher, Lloyd J.; Windham, John O.

    1955-01-01

    An investigation of a 1/20-scale dynamically similar model of the Boeing Stratocruiser airplane (C-97) was made to determine the ditching characteristics and proper technique for ditching the airplane. Scale-strength bottoms were used to determine probable damage to the fuselage and the effect of damage on behavior. The behavior of the model was determined from visual observations, motion-picture records, and time-history deceleration records. Data are presented in a table, photographs, and curves. It was concluded that the airplane should be ditched at a medium nose-high landing attitude (near 6 deg) with landing flaps full down. The airplane will probably make a smooth run of medium depth with light spray and may even trim up slightly in the water. The fuselage will probably be damaged and the lower compartment filled with water. In calm water, the maximum longitudinal deceleration will be about 4g and the landing run will be about four fuselage lengths.

  13. Ditching Investigation of a 1/24-Scale Model of the Douglas C-124 Airplane

    Science.gov (United States)

    Fisher, Lloyd J.; Windham, John O.

    1951-01-01

    An investigation of a 1/24- scale dynamically similar model of the Douglas C-124 airplane was made to determine the ditching characteristics and proper technique for ditching the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion- picture records, and time-history deceleration records. The results of the investigation are presented in table form, photographs, and curves. It was concluded on the basis of results from model tests with scale-strength bottoms (equivalent to 1150 pounds per square foot, full scale) that the airplane should be ditched at a medium nose-high landing attitude (near 7deg) with flaps full down. The airplane will probably make a smooth run with considerable damage resulting to the fuselage bottom just forward of the wing, but it is not likely that the water inflow will be overwhelming to personnel provided they are not in the belly compartment. Longitudinal decelerations in calm water will be about 2 1/2g and the landing run will be about four fuselage lengths.

  14. Fracture and strain rate behavior of airplane fuselage materials under blast loading

    NARCIS (Netherlands)

    Mediavilla Varas, J.; Soetens, F.; Kroon, E.; Aanhold, J.E. van; Meulen, O.R. van der; Sagimon, M.

    2010-01-01

    The dynamic behavior of three commonly used airplane fuselage materials is investigated, namely of Al2024-T3, Glare-3 and CFRP. Dynamic tensile tests using a servo-hydraulic and a light weight shock testing machine (LSM) have been performed. The results showed no strain rate effect on Al2024-T3 and a

  15. 75 FR 77569 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System Mode...

    Science.gov (United States)

    2010-12-13

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System Mode Annunciation AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... to as ``Gulfstream'') applied for an FAA type certificate for its new Gulfstream Model GVI...

  16. Applications of Lagrangian blending functions for grid generation around airplane geometries

    Science.gov (United States)

    Abolhassani, Jamshid S.; Sadrehaghighi, Ideen; Tiwari, Surendra N.; Smith, Robert E.

    1990-01-01

    A simple procedure has been developed and applied for the grid generation around an airplane geometry. This approach is based on a transfinite interpolation with Lagrangian interpolation for the blending functions. A monotonic rational quadratic spline interpolation has been employed for the grid distributions.

  17. Application of Lagrangian blending functions for grid generation around airplane geometries

    Science.gov (United States)

    Abolhassani, Jamshid S.; Sadrehaghighi, Ideen; Tiwari, Surendra N.

    1990-01-01

    A simple procedure was developed and applied for the grid generation around an airplane geometry. This approach is based on a transfinite interpolation with Lagrangian interpolation for the blending functions. A monotonic rational quadratic spline interpolation was employed for the grid distributions.

  18. 14 CFR Appendix A to Part 60 - Qualification Performance Standards for Airplane Full Flight Simulators

    Science.gov (United States)

    2010-01-01

    ... name of the aircraft system software, aerodynamic model, or engine model change, the date of the change... (§ 60.20). 16. Interim Qualification of FFSs for New Airplane Types or Models (§ 60.21). 17... description of the qualification process, NSP policy, and an NSP “In-Works” section. Also linked from...

  19. 14 CFR Appendix B to Part 60 - Qualification Performance Standards for Airplane Flight Training Devices

    Science.gov (United States)

    2010-01-01

    ...) must consist of the name of the aircraft system software, aerodynamic model, or engine model change... Qualification of FTDs for New Airplane Types or Models (§ 60.21). 17. Modifications to FTDs (§ 60.23). 18..., a list of qualified flight simulation devices, ACs, a description of the qualification process,...

  20. Spinal Injuries in an Airplane Crash : A Description of Incidence, Morphology, and Injury Mechanism

    NARCIS (Netherlands)

    Postma, I. L E; Oner, F. C.; Bijlsma, T. S.; Heetveld, M. J.; Goslings, J. C.; Bloemers, F. W.

    2015-01-01

    Study Design. Retrospective cohort. Objective. Spinal injuries of the survivors of an airplane crash are described. On the basis of injury morphology and knowledge of the conditions of the accident, injury mechanisms are described and prevention measures are discussed. Summary of Background Data. Th

  1. 75 FR 7945 - Airworthiness Directives; Augustair, Inc. Models 2150, 2150A, and 2180 Airplanes

    Science.gov (United States)

    2010-02-23

    ... attachment area or if the airplane was modified with a different engine model or propeller model than...) and 1 CFR part 51. (2) For service information identified in this AD, contact Augustair, Inc., 1809... incorporated by reference for this AD at the National Archives and Records Administration (NARA)....

  2. 78 FR 42898 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes

    Science.gov (United States)

    2013-07-18

    ... states: Large aeroplane incidents and accidents have occurred because of fuel tank low level situations... proposed AD was prompted by reports of airplane incidents and accidents that have occurred because of low-level fuel tank situations and fuel starvation that resulted in engine flameouts. This proposed AD...

  3. 78 FR 65183 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes

    Science.gov (United States)

    2013-10-31

    ... incidents and accidents that have occurred because of low-level fuel tank situations and fuel starvation.... This AD was prompted by reports of airplane incidents and accidents that have occurred because of low-level fuel tank situations and fuel starvation that resulted in engine flameouts. This AD...

  4. 75 FR 66700 - Airworthiness Directives; Cessna Aircraft Company (Cessna) Model 402C Airplanes Modified by...

    Science.gov (United States)

    2010-10-29

    ... CONTACT: Werner Koch, Aerospace Engineer, Fort Worth Airplane Certification Office, FAA, 2601 Meacham Blvd... switches are located on the arm assembly and provide the electrical signal for the arm position. STC... switches stops and the switch to stop the drive motor is not activated. Because the switch is not...

  5. 76 FR 68668 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0100 Airplanes

    Science.gov (United States)

    2011-11-07

    ... be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez... (BLA) 2002-115/2 dated October 8, 2004 [which partially corresponds to FAA AD 2008-20-03, Amendment 39... and Airplane Flight Manual Amendment (j) Before further flight after accomplishing the...

  6. Fear of Flying in Airplanes: Effects of Minimal Therapist Guided Stress Inoculation Training.

    Science.gov (United States)

    Beckham, Jean C.; And Others

    Flight phobia is an area which has received little controlled investigation, even though between 10 and 20 percent of flight passengers report a fear of flying in airplanes. A study was conducted to examine the efectiveness of a minimal therapist guided form of stress inoculation training (SIT) for flight phobia. Flight phobic volunteers (N=28)…

  7. 75 FR 8279 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Science.gov (United States)

    2010-02-24

    .... For airplanes with previously installed repairs, before further flight, do rework (i.e., replace any... contact Boeing for repair or rework data, the data must be approved in accordance with the procedures specified in paragraph (x) of this AD and the repair or rework must be done before further flight. (i)...

  8. 76 FR 8615 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Science.gov (United States)

    2011-02-15

    ... leak and an increased risk of fire. DATES: This AD is effective March 22, 2011. The Director of the... parts. You must install all parts removed for access before the airplane is put back in service.'' As a... a fuel leak and an increased risk of fire. Compliance (f) You are responsible for having the...

  9. 14 CFR 125.377 - Fuel supply: Turbine-engine-powered airplanes other than turbopropeller.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Fuel supply: Turbine-engine-powered... AIRCRAFT Flight Release Rules § 125.377 Fuel supply: Turbine-engine-powered airplanes other than... wind and other weather conditions expected, it has enough fuel— (1) To fly to and land at the...

  10. 14 CFR 121.511 - Flight time limitations: Flight engineers: airplanes.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Flight time limitations: Flight engineers... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Time Limitations: Supplemental Operations § 121.511 Flight time limitations: Flight engineers: airplanes. (a) In any operation in which...

  11. Study of multiple cracks in airplane fuselage by micromechanics and complex variables

    Science.gov (United States)

    Denda, Mitsunori; Dong, Y. F.

    1994-01-01

    Innovative numerical techniques for two dimensional elastic and elastic-plastic multiple crack problems are presented using micromechanics concepts and complex variables. The simplicity and the accuracy of the proposed method will enable us to carry out the multiple-site fatigue crack propagation analyses for airplane fuselage by incorporating such features as the curvilinear crack path, plastic deformation, coalescence of cracks, etc.

  12. 76 FR 29176 - Airworthiness Directives; Piper Aircraft, Inc. PA-23, PA-31, and PA-42 Airplanes

    Science.gov (United States)

    2011-05-20

    ... within the compliance times specified, unless already done. ] Actions Compliance Procedures (1) For all.... PA-23, PA-31, and PA-42 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice... and a request for an alternative method of compliance (AMOC), we determined the nose baggage...

  13. 75 FR 48623 - Airworthiness Directives; The Boeing Company Model 767-300 Series Airplanes

    Science.gov (United States)

    2010-08-11

    ... fuselage skin and backup structure at the lower very high frequency (VHF) antenna cutout at station 1197... structure, which could result in rapid decompression of the airplane. DATES: We must receive comments on... substantive verbal contact we receive about this proposed AD. Discussion We have been advised that...

  14. 76 FR 65103 - Special Conditions: Gulfstream Aerospace Corporation, Model GIV-X Airplane; Aircraft Electronic...

    Science.gov (United States)

    2011-10-20

    ... configuration in the Gulfstream Model GIV-X passenger airplane. The Gulfstream Model GIV-X is a two-engine jet.... Mail: Send comments to Docket Operations, M-30, U.S. Department of Transportation (DOT), 1200 New... by Courier: Take comments to Docket Operations in Room W12-140 of the West Building Ground Floor...

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

    Science.gov (United States)

    2010-12-23

    ... application date to September 28, 2006. The Gulfstream Model GVI airplane will be an all-new, two- engine jet... operation, and cannot be overridden by the flight crew. The system's application of this angle of attack... required for normal maneuvering including an all-engines operating takeoff plus a suitable margin to...

  16. 76 FR 35324 - Special Conditions: Boeing Model 787 Series Airplanes; Seats With Inflatable Lapbelts

    Science.gov (United States)

    2011-06-17

    ... application date to October 1, 2006. The 787 will be an all-new, twin- engine jet transport airplane with a... accident. The inflatable lapbelt works similar to an automotive airbag, except that the airbag is... automobile installations, the airbag is a supplemental system and works in conjunction with an upper...

  17. 75 FR 19207 - Airworthiness Directives; Airbus Model 340-500 and -600 Series Airplanes

    Science.gov (United States)

    2010-04-14

    ... Information Airbus has issued All Operators Telex A340-29A5014, dated October 14, 2008. The actions described... Telex A340-29A5014, dated October 14, 2008. (i) If the airplane has accumulated 1,000 total flight... (including bulging and chafing) in accordance with the instructions of Airbus All Operators Telex...

  18. Teaching Lean Six Sigma within a Supply Chain Context: The Airplane Supply Chain Simulation

    Science.gov (United States)

    Ellis, Scott C.; Goldsby, Thomas J.; Bailey, Ana M.; Oh, Jae-Young

    2014-01-01

    Lean six sigma is a management methodology that firms can employ to achieve substantial improvement in supply chain performance. However, few pedagogical exercises facilitate students' use of a comprehensive set of lean six sigma principles within a supply chain context. We describe the Airplane Supply Chain Simulation that helps students…

  19. 78 FR 77611 - Special Conditions: Airbus, A350-900 Series Airplane; High Speed Protection System

    Science.gov (United States)

    2013-12-24

    ... maximum diversion time. The A350-900, like Airbus A320, A330, A340 and A380 series aircraft, has a high... , are provided in the airplane flight manual, and the cockpit display of those reduced speeds, as well..., as well as its failure modes, failure indications and accompanying flight manual...

  20. 14 CFR 135.393 - Large nontransport category airplanes: Landing limitations: Destination airports.

    Science.gov (United States)

    2010-01-01

    ...: Landing limitations: Destination airports. 135.393 Section 135.393 Aeronautics and Space FEDERAL AVIATION... category airplanes: Landing limitations: Destination airports. (a) No person operating a large nontransport... effective length of the most suitable runway at the destination airport; and (2) Is greater than the...

  1. 75 FR 81417 - Airworthiness Directives; Piper Aircraft, Inc. Model PA-28-161 Airplanes

    Science.gov (United States)

    2010-12-28

    ...-057-AD; Amendment 39-16543; AD 2010-26-04] RIN 2120-AA64 Airworthiness Directives; Piper Aircraft, Inc...): 2010-26-04 Piper Aircraft, Inc: Amendment 39-16543; Docket No. FAA- 2010-1006; Directorate Identifier... alternative GmbH Supplement replacement times may be Airplane approved for this part. Maintenance Manual...

  2. 76 FR 67633 - Airworthiness Directives; Dassault Aviation Model Mystere-Falcon 50 Airplanes

    Science.gov (United States)

    2011-11-02

    ... products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI... the flap tracks could lead to flap asymmetry and loss of control of the airplane. The proposed AD... Friday, except Federal holidays. For service information identified in this proposed AD, contact...

  3. 76 FR 36864 - Special Conditions: Gulfstream Model GVI Airplane; Operation Without Normal Electric Power

    Science.gov (United States)

    2011-06-23

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

  4. 77 FR 29861 - Airworthiness Directives; Fokker Services B.V. Airplanes

    Science.gov (United States)

    2012-05-21

    ... low quantity''. The procedures prescribed the shut-off of the engine driven hydraulic pumps, resulting....28 Mark 0070 and 0100 airplanes. This AD was prompted by an in-flight failure of the hydraulic control panel, which resulted in the absence of pressure and quantity indication of the hydraulic...

  5. 77 FR 8181 - Airworthiness Directives; Fokker Services B.V. Airplanes

    Science.gov (United States)

    2012-02-14

    ... low quantity''. The procedures prescribed the shut-off of the engine driven hydraulic pumps, resulting... Mark 0070 and 0100 airplanes. This proposed AD was prompted by an in-flight failure of the hydraulic control panel, which resulted in the absence of pressure and quantity indication of the hydraulic...

  6. 77 FR 18099 - Special Conditions: Dassault Aviation, Model Falcon 7X Airplanes; Seats With Inflatable Shoulder...

    Science.gov (United States)

    2012-03-27

    ... abuse conditions (due to galley loading, passenger baggage, etc.). Airplanes also operate where exposure to high intensity electromagnetic fields could affect the activation system. The inflatable shoulder... Intensity Radiated Fields (HIRF) Protection. The U.S. type certification basis for the Falcon 7X...

  7. 76 FR 54141 - Airworthiness Directives; Cessna Aircraft Company Model 680 Airplanes

    Science.gov (United States)

    2011-08-31

    ... the left main electrical bus and selected the left generator to OFF. The co-pilot (flying the airplane... pounds. Loss of power on the left main electrical bus results in a false cross-feed command to the right... after receipt. FOR FURTHER INFORMATION CONTACT: Nhien Hoang, Aerospace Engineer, Electrical Systems...

  8. 77 FR 25644 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. Airplanes

    Science.gov (United States)

    2012-05-01

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Empresa Brasileira...) that apply to all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 and ERJ 190 airplanes... information identified in this proposed AD, contact Empresa Brasileira de Aeronautica S.A....

  9. 77 FR 16155 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Airplanes

    Science.gov (United States)

    2012-03-20

    ...-035-AD; Amendment 39-16980; AD 2012-05-08] RIN 2120-AA64 Airworthiness Directives; Empresa Brasileira... directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 airplanes. This AD... amends Sec. 39.13 by adding the following new AD: 2012-05-08 Empresa Brasileira de Aeronautica...

  10. 77 FR 36224 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Airplanes

    Science.gov (United States)

    2012-06-18

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Empresa Brasileira... all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 airplanes, and Model EMB-145... information identified in this proposed AD, contact Empresa Brasileira de Aeronautica S.A....

  11. 76 FR 72855 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Airplanes

    Science.gov (United States)

    2011-11-28

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Empresa Brasileira... all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 190 airplanes. This proposed AD results... Friday, except Federal holidays. For service information identified in this proposed AD, contact...

  12. 76 FR 14346 - Airworthiness Directives; Diamond Aircraft Industries GmbH Model DA 42 Airplanes

    Science.gov (United States)

    2011-03-16

    ... 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034... Industries GmbH Model DA 42 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... been reportedly found on DA 42 Main Landing Gear (MLG) Damper-to-Trailing Arm joints during...

  13. 76 FR 31457 - Airworthiness Directives; Diamond Aircraft Industries GmbH Model DA 42 Airplanes

    Science.gov (United States)

    2011-06-01

    ... (76 FR 14346). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI... Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant... Industries GmbH Model DA 42 Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

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

    Science.gov (United States)

    Fisher, Lloyd J.

    1948-01-01

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

  15. 76 FR 36980 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2011-06-24

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the.... BILLING CODE 4910-13-P...

  16. Flight investigation of the effect of control centering springs on the apparent spiral stability of a personal-owner airplane

    Science.gov (United States)

    Campbell, John P; Hunter, Paul A; Hewes, Donald E; Whitten, James B

    1952-01-01

    Report presents the results of a flight investigation conducted on a typical high-wing personal-owner airplane to determine the effect of control centering springs on apparent spiral stability. Apparent spiral stability is the term used to describe the spiraling tendencies of an airplane in uncontrolled flight as affected both by the true spiral stability of the perfectly trimmed airplane and by out-of-trim control settings. Centering springs were used in both the aileron and rudder control systems to provide both a positive centering action and a means of trimming the airplane. The springs were preloaded so that when they were moved through neutral they produced a nonlinear force gradient sufficient to overcome the friction in the control surface at the proper setting for trim. The ailerons and rudder control surfaces did not have trim tabs that could be adjusted in flight.

  17. Parametric study of variation in cargo-airplane performance related to progression from current to spanloader designs

    Science.gov (United States)

    Toll, T. A.

    1980-01-01

    A parametric analysis was made to investigate the relationship between current cargo airplanes and possible future designs that may differ greatly in both size and configuration. The method makes use of empirical scaling laws developed from statistical studies of data from current and advanced airplanes and, in addition, accounts for payload density, effects of span distributed load, and variations in tail area ratio. The method is believed to be particularly useful for exploratory studies of design and technology options for large airplanes. The analysis predicts somewhat more favorable variations of the ratios of payload to gross weight and block fuel to payload as the airplane size is increased than has been generally understood from interpretations of the cube-square law. In terms of these same ratios, large all wing (spanloader) designs show an advantage over wing-fuselage designs.

  18. 75 FR 70090 - Special Conditions: Bombardier Inc. Model CL-600-2E25 Airplane, Operation Without Normal...

    Science.gov (United States)

    2010-11-17

    ... Airplane, Operation Without Normal Electrical Power AGENCY: Federal Aviation Administration (FAA), DOT... without normal electrical power,'' requires safe operation in VFR conditions for at least five minutes with inoperative normal electrical power. The applicable airworthiness regulations do not...

  19. Rotation-and-scale-invariant airplane detection in high-resolution satellite images based on deep-Hough-forests

    Science.gov (United States)

    Yu, Yongtao; Guan, Haiyan; Zai, Dawei; Ji, Zheng

    2016-02-01

    This paper proposes a rotation-and-scale-invariant method for detecting airplanes from high-resolution satellite images. To improve feature representation capability, a multi-layer feature generation model is created to produce high-order feature representations for local image patches through deep learning techniques. To effectively estimate airplane centroids, a Hough forest model is trained to learn mappings from high-order patch features to the probabilities of an airplane being present at specific locations. To handle airplanes with varying orientations, patch orientation is defined and integrated into the Hough forest to augment Hough voting. The scale invariance is achieved by using a set of scale factors embedded in the Hough forest. Quantitative evaluations on the images collected from Google Earth service show that the proposed method achieves a completeness, correctness, quality, and F1-measure of 0.968, 0.972, 0.942, and 0.970, respectively, in detecting airplanes with arbitrary orientations and sizes. Comparative studies also demonstrate that the proposed method outperforms the other three existing methods in accurately and completely detecting airplanes in high-resolution remotely sensed images.

  20. Interactive Multi-objective Optimization Design for the Pylon Structure of an Airplane

    Institute of Scientific and Technical Information of China (English)

    An Weigang; Li Weiji

    2007-01-01

    The pylon structure of an airplane is very complex, and its high-fidelity analysis is quite time-consuming. If posterior preference optimization algorithm is used to solve this problem, the huge time consumption will be unacceptable in engineering practice due to the large amount of evaluation needed for the algorithm. So, a new interactive optimization algorithm-interactive multi-objective particle swarm optimization (IMOPSO) is presented. IMOPSO is efficient, simple and operable. The decision-maker can expediently determine the accurate preference in IMOPSO. IMOPSO is used to perform the pylon structure optimization design of an airplane, and a satisfactory design is achieved after only 12 generations of IMOPSO evolutions. Compared with original design, the maximum displacement of the satisfactory design is reduced, and the mass of the satisfactory design is decreased for 22%.

  1. Studies on aerodynamic interferences between the components of transport airplane using unstructured Navier-Stokes simulations

    Energy Technology Data Exchange (ETDEWEB)

    Wang, G.; Ye, Z. [Northwestern Polytechnical Univ., National Key Lab. of Aerodynamic Design and Research, Xi' an (China)]. E-mail: wanggang@nwpu.edu.cn; yezy@nwpu.edu.cn

    2005-07-01

    It is well known that the aerodynamic interference flows widely exist between the components of conventional transport airplane, for example, the wing-fuselage juncture flow, wing-pylon-nacelle flow and tail-fuselage juncture flow. The main characteristic of these aerodynamic interferences is flow separation, which will increase the drag, reduce the lift and cause adverse influence on the stability and controllability of the airplane. Therefore, the modern civil transport designers should do their best to eliminate negative effects of aerodynamic interferences, which demands that the aerodynamic interferences between the aircraft components should be predicted and analyzed accurately. Today's CFD techniques provide us powerful and efficient analysis tools to achieve this objective. In this paper, computational investigations of the interferences between transport aircraft components have been carried out by using a viscous flow solver based on mixed element type unstructured meshes. (author)

  2. Application of selected advanced technologies to high performance, single-engine, business airplanes

    Science.gov (United States)

    Domack, C. S.; Martin, G. L.

    1984-01-01

    Improvements in performance and fuel efficiency are evaluated for five new configurations of a six place, single turboprop, business airplane derived from a conventional, aluminum construction baseline aircraft. Results show the greatest performance gains for enhancements in natural laminar flow. A conceptual diesel engine provides greater fuel efficiency but reduced performance. Less significant effects are produced by the utilization of composite materials construction or by reconfiguration from tractor to pusher propeller installation.

  3. Analysis of airplane boarding via space-time geometry and random matrix theory

    CERN Document Server

    Bachmat, E; Skiena, S S; Stolyarov, N; Berend, D; Bachmat, Eitan; Sapir, Luba; Skiena, Steven; Stolyarov, Natan; berend, Daniel

    2005-01-01

    We show that airplane boarding can be asymptotically modeled by 2-dimensional Lorentzian geometry. Boarding time is given by the maximal proper time among curves in the model. Discrepancies between the model and simulation results are closely related to random matrix theory. We then show how such models can be used to explain why some commonly practiced airline boarding policies are ineffective and even detrimental.

  4. Task Force on Emergency Evacuation of Transport Airplanes. Volume 2. Supporting Documentation.

    Science.gov (United States)

    1986-07-01

    intended to "prciw.approvals iAilc misht be based on Insuffic&t test data, such an in the caso of a oownletely now airplane modal or a mod&3 which has...holding a Part 25 and one full scale 121 demonstration, such as Pan Am 747, Roswell , N.M., 1969, we recommend that all users participate in, not just

  5. Effect of pitch angle on initial stage of a transport airplane ditching

    Institute of Scientific and Technical Information of China (English)

    Guo Baodong; Liu Peiqing; Qu Qiulin; Wang Jiawen

    2013-01-01

    Airworthiness regulations require that the transport airplane should be proved to ensure the survivability of the ditching for the passengers.The planned ditching of a transport airplane on the calm water is numerically simulated.The effect of pitch angle on the impact characteristics is especially investigated by a subscaled model.The Reynolds-averaged Navier-Stokes (RANS) equations of unsteady compressible flow are solved and the realizable κ-ε equations are employed to model the turbulence.The transformation of the air-water interface is tracked by volume of fluid (VOF) model.The motion of the rigid body is modeled by dynamic mesh method.The initial ditching stage of the transport airplane is analyzed in detail.The numerical results show that as the pitching angle increases,the maximal normal force decreases and the pitching motion becomes much gentler.The aft fuselage would be sucked down by the water and lead to pitching up,whereas the low horizontal tail prevents this trend.Consequently,the transport aircraft with low horizontal tail should ditch on the water at an angle between 10° and 12° as a recommendation.

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

    Science.gov (United States)

    Fisher, Lloyd J.; McBride, Ellis E.

    1954-01-01

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

  7. Exposure to tri-o-cresyl phosphate detected in jet airplane passengers

    Energy Technology Data Exchange (ETDEWEB)

    Liyasova, Mariya, E-mail: mliyasov@unmc.edu [Eppley Institute, University of Nebraska Medical Center, Omaha, NE 68198-5950 (United States); Department of Environmental, Agricultural, and Occupational Health, University of Nebraska Medical Center, Omaha, NE (United States); Li, Bin, E-mail: binli@unmc.edu [Eppley Institute, University of Nebraska Medical Center, Omaha, NE 68198-5950 (United States); Schopfer, Lawrence M., E-mail: lmschopf@unmc.edu [Eppley Institute, University of Nebraska Medical Center, Omaha, NE 68198-5950 (United States); Nachon, Florian, E-mail: fnachon@nachon.net [Departement de Toxicologie, Institut de Recherche Biomedicale des Armees, 24 avenue des Marquis du Gresivaudan, 38702 La Tronche (France); Masson, Patrick, E-mail: pmasson@unmc.edu [Departement de Toxicologie, Institut de Recherche Biomedicale des Armees, 24 avenue des Marquis du Gresivaudan, 38702 La Tronche (France); Eppley Institute, University of Nebraska Medical Center, Omaha, NE 68198-5950 (United States); Furlong, Clement E., E-mail: clem@uw.edu [Department of Medicine (Div. Medical Genetics) and Genome Sciences, University of Washington, Seattle, WA 98195 (United States); Lockridge, Oksana, E-mail: olockrid@unmc.edu [Eppley Institute, University of Nebraska Medical Center, Omaha, NE 68198-5950 (United States); Department of Environmental, Agricultural, and Occupational Health, University of Nebraska Medical Center, Omaha, NE (United States)

    2011-11-15

    The aircraft cabin and flight deck ventilation are supplied from partially compressed unfiltered bleed air directly from the engine. Worn or defective engine seals can result in the release of engine oil into the cabin air supply. Aircrew and passengers have complained of illness following such 'fume events'. Adverse health effects are hypothesized to result from exposure to tricresyl phosphate mixed esters, a chemical added to jet engine oil and hydraulic fluid for its anti-wear properties. Our goal was to develop a laboratory test for exposure to tricresyl phosphate. The assay was based on the fact that the active-site serine of butyrylcholinesterase reacts with the active metabolite of tri-o-cresyl phosphate, cresyl saligenin phosphate, to make a stable phosphorylated adduct with an added mass of 80 Da. No other organophosphorus agent makes this adduct in vivo on butyrylcholinesterase. Blood samples from jet airplane passengers were obtained 24-48 h after completing a flight. Butyrylcholinesterase was partially purified from 25 ml serum or plasma, digested with pepsin, enriched for phosphorylated peptides by binding to titanium oxide, and analyzed by mass spectrometry. Of 12 jet airplane passengers tested, 6 were positive for exposure to tri-o-cresyl phosphate that is, they had detectable amounts of the phosphorylated peptide FGEpSAGAAS. The level of exposure was very low. No more than 0.05 to 3% of plasma butyrylcholinesterase was modified. None of the subjects had toxic symptoms. Four of the positive subjects were retested 3 to 7 months following their last airplane trip and were found to be negative for phosphorylated butyrylcholinesterase. In conclusion, this is the first report of an assay that detects exposure to tri-o-cresyl phosphate in jet airplane travelers. -- Highlights: Black-Right-Pointing-Pointer Travel on jet airplanes is associated with an illness, aerotoxic syndrome. Black-Right-Pointing-Pointer A possible cause is exposure to

  8. A knowledge-based design framework for airplane conceptual and preliminary design

    Science.gov (United States)

    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

  9. Definition of 1992 Technology Aircraft Noise Levels and the Methodology for Assessing Airplane Noise Impact of Component Noise Reduction Concepts

    Science.gov (United States)

    Kumasaka, Henry A.; Martinez, Michael M.; Weir, Donald S.

    1996-01-01

    This report describes the methodology for assessing the impact of component noise reduction on total airplane system noise. The methodology is intended to be applied to the results of individual study elements of the NASA-Advanced Subsonic Technology (AST) Noise Reduction Program, which will address the development of noise reduction concepts for specific components. Program progress will be assessed in terms of noise reduction achieved, relative to baseline levels representative of 1992 technology airplane/engine design and performance. In this report, the 1992 technology reference levels are defined for assessment models based on four airplane sizes - an average business jet and three commercial transports: a small twin, a medium sized twin, and a large quad. Study results indicate that component changes defined as program final goals for nacelle treatment and engine/airframe source noise reduction would achieve from 6-7 EPNdB reduction of total airplane noise at FAR 36 Stage 3 noise certification conditions for all of the airplane noise assessment models.

  10. Exploratory piloted simulator study of the effects of winglets on handling qualities of a representative agricultural airplane

    Science.gov (United States)

    Ogburn, M. E.; Brown, P. W.

    1980-01-01

    The effects on handling qualities of adding winglets to a representative agricultural aircraft configuration during swath-run maneuvering were evaluated. Aerodynamic data used in the simulation were based on low-speed wind tunnel tests of a full scale airplane and a subscale model. The Cooper-Harper handling qualities rating scale, supplementary pilot comments, and pilot vehicle performance data were used to describe the handling qualities of the airplane with the different wing-tip configurations. Results showed that the lateral-directional handling qualities of the airplane were greatly affected by the application of winglets and winglet cant angle. The airplane with winglets canted out 20 deg exhibited severely degraded lateral directional handling qualities in comparison to the basic airplane. When the winglets were canted inward 10 deg, the flying qualities of the configuration were markedly improved over those of the winglet-canted-out configuration or the basic configuration without winglets, indicating that proper tailoring of the winglet design may afford a potential benefit in the area of handling qualities.

  11. 77 FR 64029 - Special Conditions: Airbus Model A318, A319, A320, and A321 Series Airplanes; Design Dive Speed

    Science.gov (United States)

    2012-10-18

    ... April 11, 2000 (65 FR 19477-19478), as well as at http: DocketsInfo.dot.gov/. Docket: Background... Series Airplanes; Design Dive Speed AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final... airplanes. These design features include a high-speed protection system. The applicable...

  12. 78 FR 75511 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes...

    Science.gov (United States)

    2013-12-12

    ... design feature associated with control surface awareness and mode annunciation of the electronic flight... airplanes will incorporate the following novel or unusual design features: A fly-by-wire electronic flight... Inc., Models BD-500-1A10 and BD- 500-1A11 Series Airplanes; Electronic Flight Control System:...

  13. 78 FR 67291 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Design...

    Science.gov (United States)

    2013-11-12

    ... design feature associated with an electronic flight control system that provides roll control of the... design features: The airplanes are equipped with an electronic flight control system that provides... Airplanes; Design Roll Maneuver Condition AGENCY: Federal Aviation Administration (FAA), DOT. ACTION:...

  14. 75 FR 31282 - Airworthiness Directives; Airbus Model A319-100, A320-200, A321-100, and A321-200 Series Airplanes

    Science.gov (United States)

    2010-06-03

    ...-100, A320-200, A321- 100, and A321-200 Series Airplanes AGENCY: Federal Aviation Administration (FAA... May 12, 2006. The error resulted in an incorrect component maintenance manual number. This AD applies to certain Airbus Model A319-100, A320-200, A321-100, and A321-200 series airplanes. This AD...

  15. 75 FR 7407 - Airworthiness Directives; Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P Airplanes

    Science.gov (United States)

    2010-02-19

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Piper Aircraft, Inc... airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P airplanes. This... installed on certain Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P airplanes are failing. The...

  16. Flight evaluation of the effect of winglets on performance and handling qualities of a single-engine general aviation airplane

    Science.gov (United States)

    Holmes, B. J.; Vandam, C. P.; Brown, P. W.; Deal, P. L.

    1980-01-01

    A flight evaluation was conducted to determine the effects of winglets on the performance and handling qualities of a light, single-engine general aviation airplane. The performance measurements were made with a pace airplane to provide calibrated airspeeds; uncalibrated panel instruments in the test airplane were used to provide additional quantitative performance data. These tests were conducted with winglets on and off during the same day to measure relative performance effects. Handling qualities were evaluated by means of pilot comments. Winglets increased cruise speed 8 knots (5.6 percent) at 3962 m (13,000 ft) density altitude and 51 percent maximum continuous power setting. Maximum speed at 3962 m was virtually unchanged. Rate of climb increased approximately 6 percent, or 0.25 m/sec (50 ft/min), at 1524 m (5000 ft). Stall speed was virtually unchanged. Handling qualities were favorably affected.

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

    Science.gov (United States)

    Parkinson, R. C. H.

    1983-01-01

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

  18. Flight Investigation of a Normal-Acceleration Automatic Longitudinal Control System in a Fighter Airplane

    Science.gov (United States)

    Sjoberg, S. A.; Russell, Walter R.; Alford, William L.

    1958-01-01

    A flight investigation was made to obtain experimental information on the handling qualities of a normal-acceleration type of automatic longitudinal control system. The control system was installed in a subsonic fighter-type airplane. In hands-off (stick-free) flight the normal-acceleration control system attempted to regulate the normal acceleration to a constant value which is dependent on the automatic-control-system trim setting. In maneuvering flight a given pilot's stick deflection produced a proportional change in normal acceleration, the change in acceleration being independent of flight condition. A small side-located controller stick was used by the pilot to introduce signals into the automatic control system. In the flight program emphasis was placed on the acceleration-limiting capabilities of the control system. The handling qualities were investigated in maneuvers such as slow and rapid pull-ups and turns and also in flight operations such as cruising, stalls, landings, aerobatics, and air-to-air tracking. Good acceleration limiting was obtained with the normal-acceleration control system by limiting the magnitude of the input signal that the pilot could introduce into the control system. The same values of control-system gain settings could be used from an acceleration-limiting stand-point at both 10,000 and 30,000 feet for the complete speed range of the airplane. The response characteristics of the airplane-control system combination were also satisfactory at both high and low altitude with these same values of control-system gain setting. In the pilot's opinion, the normal-acceleration control system provided good stability and control characteristics in flight operations such as cruising, stalls, landings, aerobatics, and air-to-air tracking.

  19. THREE DIMENSIONAL MOVEMENT MEASUREMENT FOR THE WING OF A FLYING AIRPLANE

    Institute of Scientific and Technical Information of China (English)

    于起峰; 邱志强; 孙祥一; 陆宏伟

    2003-01-01

    The movement parameters of a wing of a flying airplane are important for its design,analysis and life-estimation, while the three dimensional (3D) measurement of these parameters is a difficult task. A measurement setup is proposed as well as its corresponding calibration methods for the camera system on both ground condition and air condition, image processing algorithms and a new method of locating 3D straight lines through plane-plane intersection are developed. The test results show that the 3D measurement accuracy in the condition of flying in the air can be better than 1 mm.

  20. Flight Investigation of the Effectiveness of an Automatic Aileron Trim Control Device for Personal Airplanes

    Science.gov (United States)

    Phillips, William H; Kuehnel, Helmut A; Whitten, James B

    1957-01-01

    A flight investigation to determine the effectiveness of an automatic aileron trim control device installed in a personal airplane to augment the apparent spiral stability has been conducted. The device utilizes a rate-gyro sensing element in order to switch an on-off type of control that operates the ailerons at a fixed rate through control centering springs. An analytical study using phase-plane and analog-computer methods has been carried out to determine a desirable method of operation for the automatic trim control.

  1. Fatigue of titanium alloys in a supersonic-cruise airplane environment

    Science.gov (United States)

    Imig, L. A.

    1976-01-01

    The test programs conducted by several aerospace companies and NASA, summarized in this paper, studied several titanium materials previously identified as having high potential for application to supersonic cruise airplane structures. These studies demonstrate that the temperature (560 K) by itself produced no significant degradation of the materials. However, the fatigue resistance of titanium-alloy structures, in which thermal and loading effects are combined, has been studied insufficiently. The predominant topic for future study of fatigue problems in Mach 3 structures should be the influences of thermal stress particularly, the effects of thermal stress on failure location.

  2. Investigation of a fatal airplane crash: autopsy, computed tomography, and injury pattern analysis used to determine who was steering the plane at time of accident. A case report

    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 au......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...

  3. Study and Analysis on the Influence of Flutter Frequency on Airplane Stability

    Directory of Open Access Journals (Sweden)

    B. Janarthanan

    2013-10-01

    Full Text Available In the nationwide requirement of the growth in commercial aviation safety and profit, the field of Aeroelastic science plays a vital role. Flutter is one of the dynamic aeroelastic problems, it mainly occurs at lifting surfaces when the airplane cruises at high speeds. At relatively low speeds, the torsional stiffness of the wing is enough to counteract the twisting. However, the variation in flutter frequency causes the instability motion on aircraft. Therefore, the wing displacement against the flow field plays a vital role in dynamic stability analysis. As per the commercial aviation concern, an aircraft which is able to overcome the significant aeroelastic problems can yield maximum running profit. In order to maintain the airplane stability in high-speed, wings can be designed to minimize the distance between aerodynamic centre and shear centre (on the elastic axis. The main focus of this project is to calculate the frequency of an aircraft wing while it is subjected to aeroelastic (flutter instability. The analytical process identified for this work is the Eigen value method. By using MATLAB solver, the optimization has been carried out along the span of real-time model. In future, the efficient structural model is then simulated and analysis is carried out to evaluate the longitudinal stability due to flutter phenomena.

  4. PALS-Based Analysis of an Airplane Multirate Control System in Real-Time Maude

    Directory of Open Access Journals (Sweden)

    Kyungmin Bae

    2012-12-01

    Full Text Available Distributed cyber-physical systems (DCPS are pervasive in areas such as aeronautics and ground transportation systems, including the case of distributed hybrid systems. DCPS design and verification is quite challenging because of asynchronous communication, network delays, and clock skews. Furthermore, their model checking verification typically becomes unfeasible due to the huge state space explosion caused by the system's concurrency. The PALS ("physically asynchronous, logically synchronous" methodology has been proposed to reduce the design and verification of a DCPS to the much simpler task of designing and verifying its underlying synchronous version. The original PALS methodology assumes a single logical period, but Multirate PALS extends it to deal with multirate DCPS in which components may operate with different logical periods. This paper shows how Multirate PALS can be applied to formally verify a nontrivial multirate DCPS. We use Real-Time Maude to formally specify a multirate distributed hybrid system consisting of an airplane maneuvered by a pilot who turns the airplane according to a specified angle through a distributed control system. Our formal analysis revealed that the original design was ineffective in achieving a smooth turning maneuver, and led to a redesign of the system that satisfies the desired correctness properties. This shows that the Multirate PALS methodology is not only effective for formal DCPS verification, but can also be used effectively in the DCPS design process, even before properties are verified.

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

    Science.gov (United States)

    Fisher, Lloyd J.; Thompson, William C.

    1949-01-01

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

  6. Performance of light sources and radiation sensors under low gravity realized by parabolic airplane flights

    Science.gov (United States)

    Hirai, Hiroaki; Kitaya, Yoshiaki; Hirai, Takehiro

    A fundamental study was conducted to establish an experimental system for space farming. Since to ensure optimal light for plant cultivation in space is of grave importance, this study examined the performance of light sources and radiation sensors under microgravity conditions created during the parabolic airplane flight. Three kinds of light sources, a halogen bulb, a fluorescent tube, and blue and red LEDs, and ten models of radiation sensors available in the market were used for the experiment. Surface temperature of the light sources, output signals from the radiation sensors, spectroscopic characteristics were measured at the gravity levels of 0.01, 1.0 and 1.8 G for 20 seconds each during parabolic airplane flights. As a result, the performance of the halogen lamp was affected the most by the gravity level among the three light sources. Under the microgravity conditions which do not raise heat convection, the temperature of the halogen lamp rose and the output of the radiation sensors increased. Spectral distributions of the halogen lamp indicated that peak wavelength appeared the highest at the level of 0.01G, which contributed to the increase in light intensity. In the case of red and blue LEDs, which are promising light sources in space farming, the temperature of both LED chips rose but irradiance from red LED increased and that from blue LED decreased under microgravity conditions due to the different thermal characteristics.

  7. Security Considerations of Transport Category Airplane%运输类飞机安保事项

    Institute of Scientific and Technical Information of China (English)

    张柱国

    2012-01-01

    On 2002 and 2008, the Federal Aviation Administration (FAA) promulgated Amendment No. 25-106 and 25-127 respectively, which specified overall security considerations for transport category airplanes. This paper introduces the background and history related to security considerations and explains the security considerations. Finally, this paper is concluded with the trend of security and the implementation of security considerations for existing fleet, type design under certification and some kind airplane.%2002年和2008年美国联邦航空局(FAA)分别发布的联邦航空条例FAR25部第25—106和25—127修正案,对运输类飞机提出了全面的安保要求。介绍了运输类飞机安保要求的背景和演变历史,对安保要求进行了解析。最后针对安保发展趋势、在役飞机和在审型号设计及C919飞机对安保要求的贯彻情况进行了总结。

  8. Development of an Active Flow Control Technique for an Airplane High-Lift Configuration

    Science.gov (United States)

    Shmilovich, Arvin; Yadlin, Yoram; Dickey, Eric D.; Hartwich, Peter M.; Khodadoust, Abdi

    2017-01-01

    This study focuses on Active Flow Control methods used in conjunction with airplane high-lift systems. The project is motivated by the simplified high-lift system, which offers enhanced airplane performance compared to conventional high-lift systems. Computational simulations are used to guide the implementation of preferred flow control methods, which require a fluidic supply. It is first demonstrated that flow control applied to a high-lift configuration that consists of simple hinge flaps is capable of attaining the performance of the conventional high-lift counterpart. A set of flow control techniques has been subsequently considered to identify promising candidates, where the central requirement is that the mass flow for actuation has to be within available resources onboard. The flow control methods are based on constant blowing, fluidic oscillators, and traverse actuation. The simulations indicate that the traverse actuation offers a substantial reduction in required mass flow, and it is especially effective when the frequency of actuation is consistent with the characteristic time scale of the flow.

  9. 76 FR 13078 - Airworthiness Directives; Eclipse Aerospace, Inc. Model EA500 Airplanes Equipped With a Pratt and...

    Science.gov (United States)

    2011-03-10

    ...-005-AD; Amendment 39-16631; AD 2011-06-06] RIN 2120-AA64 Airworthiness Directives; Eclipse Aerospace..., we issued AD 2008-24-07, amendment 39-15747 (73 FR 70866, November 24, 2008), for certain Eclipse Aviation Corporation (Eclipse) Model EA500 airplanes equipped with a Pratt and Whitney Canada, Corp....

  10. 75 FR 1536 - Airworthiness Directives; The Boeing Company Model 737-600, -700, and -800 Series Airplanes

    Science.gov (United States)

    2010-01-12

    ... valves, fueling manifold, fuel temperature sensor, and motor operated fuel shutoff valve adapter plate..., -700, and -800 series airplanes. This AD requires an inspection of the free flange, vertical web, and... assurance inspection at the final assembly plant. We are issuing this AD to prevent cracks from...

  11. 14 CFR 135.373 - Part 25 transport category airplanes with four or more engines: Reciprocating engine powered: En...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Part 25 transport category airplanes with four or more engines: Reciprocating engine powered: En route limitations: Two engines inoperative. 135... engines: Reciprocating engine powered: En route limitations: Two engines inoperative. (a) No person...

  12. 14 CFR 121.183 - Part 25 airplanes with four or more engines: Reciprocating engine powered: En route limitations...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Part 25 airplanes with four or more engines: Reciprocating engine powered: En route limitations: Two engines inoperative. 121.183 Section 121.183 Aeronautics... more engines: Reciprocating engine powered: En route limitations: Two engines inoperative. (a)...

  13. 75 FR 22512 - Airworthiness Directives; Piaggio Aero Industries S.p.A. Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-04-29

    ... Industries S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of....regulations.gov ; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through... 2. The FAA amends Sec. 39.13 by adding the following new AD: 2010-09-09 Piaggio Aero Industries...

  14. 75 FR 43095 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A. Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-07-23

    ... INDUSTRIES S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... failure of engine oil dipsticks, installed on Pratt & Whitney Canada (P&WC) PT6A66 and PT6A66B engines, were detected on P.180 aeroplanes; such failures, due to moisture penetration into the dipstick...

  15. 75 FR 7409 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-02-19

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of..., Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday... 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD,...

  16. 75 FR 904 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-01-07

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Directive (AD) 2009-21-08, which applies to PIAGGIO AERO INDUSTRIES S.p.A. (Piaggio) Model PIAGGIO P-180...: Service information title Page(s) Revision Date PIAGGIO AERO INDUSTRIES S.p.A. 1 through 9........ Rev....

  17. 76 FR 4056 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2011-01-24

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the... Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket...

  18. 76 FR 10224 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2011-02-24

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... this AD, contact Piaggio Aero Industries S.p.A., Via Cibrario, 4-16154 Genoa, Italy; phone: +39 010... that the towing bar P/N 01-1227-0000 or similar ferromagnetic masses are prohibited to be carried...

  19. 75 FR 43101 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-07-23

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

  20. 75 FR 63058 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-10-14

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of....regulations.gov ; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through... 2. The FAA amends Sec. 39.13 by adding the following new AD: 2010-21-14 PIAGGIO AERO INDUSTRIES...

  1. 75 FR 63062 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-10-14

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Assembly (P/N 80-337284- 001), which allows better clearances and removes the problem of potential interference. PAI issued SB 80-0175 Revision 1, limiting the applicability to aeroplanes with the old...

  2. 75 FR 68172 - Airworthiness Directives; Piaggio Aero Industries S.p.A. Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-11-05

    ... Industries S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... identified in this AD, contact Piaggio Aero Industries S.p.a., Via Cibrario, 4-16154 Genoa, Italy; phone: +39... between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the...

  3. 75 FR 47734 - Airworthiness Directives; Piaggio Aero Industries S.p.A. Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-08-09

    ... Industries S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through... http://www.regulations.gov ; or in person at the Docket Management Facility between 9 a.m. and 5...

  4. 76 FR 54403 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2011-09-01

    ... INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... sleeves (part number (P/N) 114146681), which were installed in some Main Landing Gear (MLG) actuators, had... Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday,...

  5. 78 FR 68986 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Science.gov (United States)

    2013-11-18

    ... following novel or unusual design features: An onboard computer network system, and a network extension... and connectivity capabilities of the airplane's onboard network computer systems, which may allow access to or by external computer systems and networks. This onboard network system will be composed of...

  6. 78 FR 11562 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: High Speed...

    Science.gov (United States)

    2013-02-19

    ... Embraer S.A. Model EMB-550 airplanes was published in the Federal Register on November 20, 2012 (77 FR...; Flight Envelope Protection: High Speed Limiting AGENCY: Federal Aviation Administration (FAA), DOT... inadvertently or intentionally exceeding a speed approximately equivalent to V FC or attaining V DF ....

  7. 75 FR 55455 - Airworthiness Directives; The Boeing Company Model 737-700 (IGW) Series Airplanes Equipped With...

    Science.gov (United States)

    2010-09-13

    ..., Incorporation by reference, Safety. Adoption of the Amendment 0 Accordingly, under the authority delegated to me... electrical connections required for auxiliary tank operation, and stow them at the auxiliary tank interface... them. (4) Disconnect all fuel feed and fuel vent plumbing interfaces with airplane original...

  8. 78 FR 68775 - Special Conditions: Airbus, Model A350-900 Series Airplane; Composite Fuselage In-Flight Fire...

    Science.gov (United States)

    2013-11-15

    ...-scale tests. A radiant panel test standard for flooring materials was a test method that provided good... Model A350-900 series airplane fuselage skin/structure section of sufficient size to assess any tendency... condition applies: The Airbus Model A350 composite fuselage structure must be shown to be resistant to...

  9. 14 CFR Appendix B to Part 36 - Noise Levels for Transport Category and Jet Airplanes Under § 36.103

    Science.gov (United States)

    2010-01-01

    ... weight of 63,177 pounds or less; and (iii) For airplanes with fewer than 3 engines: 101 EPNdB for maximum.... ISA+10 °C); (iii) Relative humidity of 70 per cent; (iv) Zero wind. (v) In defining the...

  10. 77 FR 26663 - Airworthiness Directives; The Boeing Company Model 767-200, -300, -300F, and -400ER Series Airplanes

    Science.gov (United States)

    2012-05-07

    ... rework limits are valid when winglets are installed. APB added that including these airplanes will reduce... fail-safe straps when reviewing the SRM for the correct rework limits. CAL believes the corrosion...), which include inspection, repair, and rework limits but does not contain specific procedures...

  11. 76 FR 10213 - Special Conditions: Embraer Model EMB-135BJ (Legacy 650) Airplanes, Limit Engine Torque Loads for...

    Science.gov (United States)

    2011-02-24

    ... engine mounts, pylons and adjacent supporting airframe structure must be designed to withstand 1g level... developed from these conditions are to be multiplied by a factor of 1.0 when applied to engine mounts and... 650) Airplanes, Limit Engine Torque Loads for Sudden Engine Stoppage AGENCY: Federal...

  12. 76 FR 63822 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane, Limit Engine Torque Loads...

    Science.gov (United States)

    2011-10-14

    ... of 1.0 when applied to engine mounts and pylons, and multiplied by a factor of 1.25 when applied to...) Model G280 Airplane, Limit Engine Torque Loads for Sudden Engine Stoppage AGENCY: Federal Aviation... novel or unusual design feature associated with engine torque loads imposed by sudden engine...

  13. 14 CFR 121.645 - Fuel supply: Turbine-engine powered airplanes, other than turbo propeller: Flag and supplemental...

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Fuel supply: Turbine-engine powered... SUPPLEMENTAL OPERATIONS Dispatching and Flight Release Rules § 121.645 Fuel supply: Turbine-engine powered... Columbia with a turbine engine powered airplane the fuel requirements of § 121.643 apply....

  14. 76 FR 8610 - Airworthiness Directives; Airbus Model A340-200, -300, -500, and -600 Series Airplanes

    Science.gov (United States)

    2011-02-15

    ... structure, which could result in reduced structural integrity of the airplane. This AD requires actions that... fatigue cracking, damage, and corrosion in certain structure, which could result in reduced structural... personal information you provide. We will also post a report summarizing each substantive verbal contact...

  15. 78 FR 8961 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Hydrophobic Coatings in Lieu of...

    Science.gov (United States)

    2013-02-07

    ... jet airplanes designed for corporate flight, fractional, charter, and private owner operations. The... turbofan engines mounted on aft fuselage pylons. Each engine produces approximately 6,540 pounds of thrust... sufficiently clear area of the windshield in low speed flight or during surface operations....

  16. 76 FR 38550 - Special Conditions: Boeing, Model 747-8 Series Airplanes; Door 1 Extendable Length Escape Slide

    Science.gov (United States)

    2011-07-01

    ... a derivative of the 747-400. The Model 747-8 is a four-engine jet transport airplane that will have a maximum takeoff weight of 975,000 pounds, new General Electric GEnx -2B67 engines, and the... extension packed at the toe end of the escape slide. During normal operation, the extension portion...

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

    Science.gov (United States)

    2012-03-23

    ... Model 787 series airplane (hereafter referred to as ``787''). The 787 is an all-new, twin-engine jet... for sending your comments electronically. Mail: Send comments to Docket Operations, M-30, U.S..., Washington, DC, 20590-0001. Hand Delivery or Courier: Take comments to Docket Operations in Room W12-140...

  18. 78 FR 52107 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Rechargeable Lithium...

    Science.gov (United States)

    2013-08-22

    ... Series Airplanes; Rechargeable Lithium Ion Batteries and Battery Systems AGENCY: Federal Aviation... lithium ion batteries and battery system that will be used on an International Communications Group (ICG... applied for a supplemental type certificate for installing equipment that uses rechargeable lithium...

  19. 78 FR 76731 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Rechargeable Lithium...

    Science.gov (United States)

    2013-12-19

    ... Series Airplanes; Rechargeable Lithium Ion Batteries and Battery Systems AGENCY: Federal Aviation... lithium ion batteries and battery system that will be used on an International Communications Group (ICG... uses rechargeable lithium ion batteries and battery systems in the Boeing Model 777-200, -300,...

  20. 14 CFR Appendix G to Part 141 - Flight Instructor Instrument (For an Airplane, Helicopter, or Powered-Lift Instrument Instructor...

    Science.gov (United States)

    2010-01-01

    ... Airplane, Helicopter, or Powered-Lift Instrument Instructor Rating, as Appropriate) Certification Course G Appendix G to Part 141 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) SCHOOLS AND OTHER CERTIFICATED AGENCIES PILOT SCHOOLS Pt. 141, App. G Appendix G to Part...

  1. 77 FR 67308 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Hydrophobic Coatings in Lieu of...

    Science.gov (United States)

    2012-11-09

    ...., Model EMB-550 Airplane; Hydrophobic Coatings in Lieu of Windshield Wipers AGENCY: Federal Aviation... feature(s) associated with hydrophobic coatings. The applicable airworthiness regulations do not contain... hydrophobic coating on the windshield in lieu of windshield wipers. The existing regulation, Title 14, Code...

  2. 76 FR 40286 - Airworthiness Directives; Empresa Brasileira de Aeronáutica S.A. (EMBRAER) Model EMB-505 Airplanes

    Science.gov (United States)

    2011-07-08

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Empresa Brasileira...), 40113, 44701. Sec. 39.13 2. The FAA amends Sec. 39.13 by adding the following new AD: Empresa Brasileira...) This AD applies to Empresa Brasileira de Aeron utica S.A. (EMBRAER) Model EMB-505 airplanes, all...

  3. 76 FR 59240 - Airworthiness Directives; Empresa Brasileira de Aeronáutica S.A. (EMBRAER) Airplanes

    Science.gov (United States)

    2011-09-26

    ... 2011-CE-023-AD; Amendment 39-16810; AD 2011-20-01] RIN 2120-AA64 Airworthiness Directives; Empresa... (AD) for Empresa Brasileira de Aeron utica S.A. (EMBRAER) Model EMB-505 airplanes. This AD results... the following new AD: 2011-20-01 Empresa Brasileira de Aeron utica S.A. (EMBRAER): Amendment...

  4. 77 FR 24425 - Airworthiness Directives; Empresa Brasileria de Aeronáutica S.A. (EMBRAER) Airplanes

    Science.gov (United States)

    2012-04-24

    ... Directives; Empresa Brasileria de Aeron utica S.A. (EMBRAER) Airplanes AGENCY: Federal Aviation...: We propose to adopt a new airworthiness directive (AD) for certain Empresa Brasileria de Aeron utica... proposed AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), Phenom Maintenance Support,...

  5. 77 FR 39159 - Airworthiness Directives; Empresa Brasileria de Aeronáutica S.A. (EMBRAER) Airplanes

    Science.gov (United States)

    2012-07-02

    ...-011-AD; Amendment 39-17106; AD 2012-13-04] RIN 2120-AA64 Airworthiness Directives; Empresa Brasileria... Empresa Brasileria de Aeron utica S.A. (EMBRAER) Model EMB-505 airplanes. This AD results from mandatory..., contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), Phenom Maintenance Support, Av. Brigadeiro...

  6. 76 FR 41045 - Special Conditions; Gulfstream Aerospace LP (GALP) Model G250 Airplane, Design Roll-Maneuver...

    Science.gov (United States)

    2011-07-13

    ... approximately 3,400 nautical miles. Airplane dimensions are 61.69-foot wing span, 66.6-foot overall length, and..., the torsional flexibility of the wing must be considered in accordance with Sec. 25.301(b): In lieu...

  7. 75 FR 52292 - Airworthiness Directives; Diamond Aircraft Industries GmbH Models DA 40 and DA 40F Airplanes

    Science.gov (United States)

    2010-08-25

    ... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3... 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...

  8. 75 FR 75868 - Airworthiness Directives; Diamond Aircraft Industries GmbH Models DA 40 and DA 40F Airplanes

    Science.gov (United States)

    2010-12-07

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

  9. 76 FR 56680 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes; Model A340-200 and...

    Science.gov (United States)

    2011-09-14

    ... telexes (AOT) listed in the following table. Table--All Operators Telexes Model Airbus all operators telex... airplanes only), as applicable, in accordance with the instructions of Airbus All Operators Telex (AOT)...

  10. On the analytic and numeric optimisation of airplane trajectories under real atmospheric conditions

    Science.gov (United States)

    Gonzalo, J.; Domínguez, D.; López, D.

    2014-12-01

    From the beginning of aviation era, economic constraints have forced operators to continuously improve the planning of the flights. The revenue is proportional to the cost per flight and the airspace occupancy. Many methods, the first started in the middle of last century, have explore analytical, numerical and artificial intelligence resources to reach the optimal flight planning. In parallel, advances in meteorology and communications allow an almost real-time knowledge of the atmospheric conditions and a reliable, error-bounded forecast for the near future. Thus, apart from weather risks to be avoided, airplanes can dynamically adapt their trajectories to minimise their costs. International regulators are aware about these capabilities, so it is reasonable to envisage some changes to allow this dynamic planning negotiation to soon become operational. Moreover, current unmanned airplanes, very popular and often small, suffer the impact of winds and other weather conditions in form of dramatic changes in their performance. The present paper reviews analytic and numeric solutions for typical trajectory planning problems. Analytic methods are those trying to solve the problem using the Pontryagin principle, where influence parameters are added to state variables to form a split condition differential equation problem. The system can be solved numerically -indirect optimisation- or using parameterised functions -direct optimisation-. On the other hand, numerical methods are based on Bellman's dynamic programming (or Dijkstra algorithms), where the fact that two optimal trajectories can be concatenated to form a new optimal one if the joint point is demonstrated to belong to the final optimal solution. There is no a-priori conditions for the best method. Traditionally, analytic has been more employed for continuous problems whereas numeric for discrete ones. In the current problem, airplane behaviour is defined by continuous equations, while wind fields are given in a

  11. Networking Effect Analysis of Ship-Airplane Cooperating Air Defense System%舰机协同防空体系网络化效应分析

    Institute of Scientific and Technical Information of China (English)

    陈国生; 刘钢; 贾子英

    2011-01-01

    针对舰机海上协同防空作战体系网络化效应难以度量的问题,提出舰机协同组网概念,建立舰机协同组网网络环模型.将舰机协同防空区域进行划分,通过核心子网络在不同防空区域的转移以及邻接矩阵Perron-Frobenius特征值(PFE)的计算,分析了舰机协同防空体系的网络化效应.该分析方法简单,将其应用在舰机协同防空体系网络化效应分析是有效的.%To solve the question of measuring networking effect for ship-airplane cooperating air defense system, the definition of ship-airplane cooperating networking is proposed, and the networking loop model of ship-airplane cooperating networking is established. The ship-airplane cooperating air defense area is divided, through the core sub-networking shifting in different air defense area and the computation of adjoin matrix Perron-Frobeniu eigenvalue(PFE), the networking effect of ship-airplane cooperating air defense system is analyzed. This analysis method is simple and effective on analyzing networking effect of ship-airplane cooperating air defense system.

  12. Experiments to Determine Neighborhood Reactions to Light Airplanes With and Without External Noise Reduction

    Science.gov (United States)

    Elwell, Fred S

    1953-01-01

    The work reported was part of a program of experimentation with external noise reduction on light airplanes. This particular study was in effect a byproduct survey conceived to utilize already available equipment and personnel to further the findings of the original research and to determine reactions in populated neighborhoods to light aircraft with and without noise-reduction equipment. The findings indicate that at the 10 sites within and about metropolitan Boston the degree of noise reduction previously found to be aerodynamically and structurally feasible did eliminate substantially all neighborhood objections to noise per se. The evidence clearly suggests that, when the noise nuisance is minimized to the extent found feasible, the number and severity of other objections also diminish -- evidently because the flight operations are noticed less when heard less.

  13. ANALYSIS FOR AERODYNAMICS OF THE SIMPLIFIED MODEL OF A COMMERCIAL AIRPLANE CRUISING AT TRANSONIC SPEED

    Directory of Open Access Journals (Sweden)

    KIM YANGKYUN

    2010-12-01

    Full Text Available This paper describes the computational analysis and visualization of flow around the model of a commercial airplane, Boeing 747-400. The geometry was realized through reverse engineering technique based on the photo scanning measurement. The steady three-dimensional viscous compressible governing equations were solved in the unstructured grid system. The basic conditions for computation were chosen as the same to those of Boeing 747-400’s cruising state. The high Reynolds turbulence models are tried. The angle of attack is varied to investigate the effect of the flight conditions to the aerodynamic performance. And flow and aerodynamic characteristics due to the existence of winglet were compared.

  14. Far-Field Turbulent Vortex-Wake/Exhaust Plume Interaction for Subsonic and HSCT Airplanes

    Science.gov (United States)

    Kandil, Osama A.; Adam, Ihab; Wong, Tin-Chee

    1996-01-01

    Computational study of the far-field turbulent vortex-wake/exhaust plume interaction for subsonic and high speed civil transport (HSCT) airplanes is carried out. The Reynolds-averaged Navier-Stokes (NS) equations are solved using the implicit, upwind, Roe-flux-differencing, finite-volume scheme. The two-equation shear stress transport model of Menter is implemented with the NS solver for turbulent-flow calculation. For the far-field study, the computations of vortex-wake interaction with the exhaust plume of a single engine of a Boeing 727 wing in a holding condition and two engines of an HSCT in a cruise condition are carried out using overlapping zonal method for several miles downstream. These results are obtained using the computer code FTNS3D. The results of the subsonic flow of this code are compared with those of a parabolized NS solver known as the UNIWAKE code.

  15. Effects of Medium Characteristics on Laser RCS of Airplane with E-Wave Polarization

    Directory of Open Access Journals (Sweden)

    Hosam El-Ocla

    2015-01-01

    Full Text Available Plane wave incidence should be postulated to have an authentic target detection. Practically, the plane wave is incapable usually of keeping its power in the far field especially when propagating through an inhomogeneous medium. Consequently, we assume an incident beam wave with a finite width around the target. In this work, we calculate numerically a laser radar cross section (LRCS of conducting targets having smooth cross sections with inflection points such as airplane in random media. Effects of fluctuations intensity of random media on the LRCS performance are studied in this paper. E-wave polarization (E-wave incidence is considered while the mean target size is approximately twice the wavelength.

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

    Science.gov (United States)

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

    1951-01-01

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

  17. Nanosecond-level time synchronization of AERA using a beacon reference transmitter and commercial airplanes

    Directory of Open Access Journals (Sweden)

    Huege Tim

    2017-01-01

    Full Text Available Radio detection of cosmic-ray air showers requires time synchronization of detectors on a nanosecond level, especially for advanced reconstruction algorithms based on the wavefront curvature and for interferometric analysis approaches. At the Auger Engineering Radio Array, the distributed, autonomous detector stations are time-synchronized via the Global Positioning System which, however, does not provide sufficient timing accuracy. We thus employ a dedicated beacon reference transmitter to correct for eventby-event clock drifts in our offline data analysis. In an independent cross-check of this “beacon correction” using radio pulses emitted by commercial airplanes, we have shown that the combined timing accuracy of the two methods is better than 2 nanoseconds.

  18. Experience with scale effects in non-airplane wind tunnel testing

    Science.gov (United States)

    Ross, J. C.; Olson, M. E.

    1990-01-01

    The aerodynamics results of two tests performed in the 80- by 120-Foot Wind Tunnel at NASA Ames Research Center are discussed with particular emphasis on the effects of model scale. The tests are unusual for this facility in that they were performed on non-airplane configurations: a full-scale tractor/trailer and large ramair inflated wings. For the truck drag measurements, comparisons with 1/8th-scale drag data taken at the Low Speed Wind Tunnel at Texas A&M indicate that small scale measurements can provide adequate accuracy if care is taken to test at high enough Reynolds numbers and if large regions of separated flow and reattachment are avoided. Some of the important aerodynamic and structural aspects of parafoil testing are also discussed. These include the effects of Reynolds number and aeroelastic effects such as fabric and support line stretch.

  19. UWB EMI To Aircraft Radios: Field Evaluation on Operational Commercial Transport Airplanes. Volume 1

    Science.gov (United States)

    Oria, A. J. (Editor); Ely, Jay J.; Martin, Warren L.; Shaver, Timothy W.; Fuller, Gerald L.; Zimmerman, John; Fuschino, Robert L.; Larsen, William E.

    2005-01-01

    Ultrawideband (UWB) transmitters may soon be integrated into a wide variety of portable electronic devices (PEDs) that passengers routinely carry on board commercial airplanes. Airlines and the FAA will have difficulty controlling passenger use of UWB transmitters during flights with current airline policies and existing wireless product standards. The aeronautical community is concerned as to whether evolving FCC UWB rules are adequate to protect legacy and emerging aeronautical radio systems from electromagnetic interference (EMI) from emerging UWB products. To address these concerns, the NASA Office of Space Communications and Chief Spectrum Managers assembled a multidisciplinary team from NASA LaRC, NASA JPL, NASA ARC, FAA, United Airlines, Sky West Airlines, and Eagles Wings Inc. to carry out a comprehensive series of tests aimed at determining the nature and extent of any EMI to aeronautical communication and navigation systems from UWB devices meeting FCCapproved and proposed levels for unlicensed handheld transmitters.

  20. Nanosecond-level time synchronization of AERA using a beacon reference transmitter and commercial airplanes

    CERN Document Server

    Huege, Tim

    2016-01-01

    Radio detection of cosmic-ray air showers requires time synchronization of detectors on a nanosecond level, especially for advanced reconstruction algorithms based on the wavefront curvature and for interferometric analysis approaches. At the Auger Engineering Radio Array, the distributed, autonomous detector stations are time-synchronized via the Global Positioning System which, however, does not provide sufficient timing accuracy. We thus employ a dedicated beacon reference transmitter to correct for event-by-event clock drifts in our offline data analysis. In an independent cross-check of this "beacon correction" using radio pulses emitted by commercial airplanes, we have shown that the combined timing accuracy of the two methods is better than 2 nanoseconds.

  1. Nanosecond-level time synchronization of AERA using a beacon reference transmitter and commercial airplanes

    Science.gov (United States)

    Huege, Tim

    2017-03-01

    Radio detection of cosmic-ray air showers requires time synchronization of detectors on a nanosecond level, especially for advanced reconstruction algorithms based on the wavefront curvature and for interferometric analysis approaches. At the Auger Engineering Radio Array, the distributed, autonomous detector stations are time-synchronized via the Global Positioning System which, however, does not provide sufficient timing accuracy. We thus employ a dedicated beacon reference transmitter to correct for eventby-event clock drifts in our offline data analysis. In an independent cross-check of this "beacon correction" using radio pulses emitted by commercial airplanes, we have shown that the combined timing accuracy of the two methods is better than 2 nanoseconds.

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

    Science.gov (United States)

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

    2005-01-01

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

  3. Flight and analytical investigations of a structural mode excitation system on the YF-12A airplane

    Science.gov (United States)

    Goforth, E. A.; Murphy, R. C.; Beranek, J. A.; Davis, R. A.

    1987-01-01

    A structural excitation system, using an oscillating canard vane to generate force, was mounted on the forebody of the YF-12A airplane. The canard vane was used to excite the airframe structural modes during flight in the subsonic, transonic, and supersonic regimes. Structural modal responses generated by the canard vane forces were measured at the flight test conditions by airframe-mounted accelerometers. Correlations of analytical and experimental aeroelastic results were made. Doublet lattice, steady state double lattice with uniform lag, Mach box, and piston theory all produced acceptable analytical aerodynamic results within the restrictions that apply to each. In general, the aerodynamic theory methods, carefully applied, were found to predict the dynamic behavior of the YF-12A aircraft adequately.

  4. Annoyance from Road Traffic, Trains, Airplanes and from Total Environmental Noise Levels

    Directory of Open Access Journals (Sweden)

    Martina S. Ragettli

    2015-12-01

    Full Text Available There is a lack of studies assessing the exposure-response relationship between transportation noise and annoyance in North America. Our aims were to investigate the prevalence of noise annoyance induced by road traffic, trains and airplanes in relation to distance to transportation noise sources, and to total environmental noise levels in Montreal, Canada; annoyance was assessed as noise-induced disturbance. A telephone-based survey among 4336 persons aged >18 years was conducted. Exposure to total environmental noise (A-weighted outdoor noise levels—LAeq24h and day-evening-night equivalent noise levels—Lden for each study participant was determined using a statistical noise model (land use regression—LUR that is based on actual outdoor noise measurements. The proportion of the population annoyed by road traffic, airplane and train noise was 20.1%, 13.0% and 6.1%, respectively. As the distance to major roads, railways and the Montreal International Airport increased, the percentage of people disturbed and highly disturbed due to the corresponding traffic noise significantly decreased. When applying the statistical noise model we found a relationship between noise levels and disturbance from road traffic and total environmental noise, with Prevalence Proportion Ratios (PPR for highly disturbed people of 1.10 (95% CI: 1.07–1.13 and 1.04 (1.02–1.06 per 1 dB(A Lden, respectively. Our study provides the first comprehensive information on the relationship between transportation noise levels and disturbance in a Canadian city. LUR models are still in development and further studies on transportation noise induced annoyance are consequently needed, especially for sources other than road traffic.

  5. Annoyance from Road Traffic, Trains, Airplanes and from Total Environmental Noise Levels.

    Science.gov (United States)

    Ragettli, Martina S; Goudreau, Sophie; Plante, Céline; Perron, Stéphane; Fournier, Michel; Smargiassi, Audrey

    2015-12-29

    There is a lack of studies assessing the exposure-response relationship between transportation noise and annoyance in North America. Our aims were to investigate the prevalence of noise annoyance induced by road traffic, trains and airplanes in relation to distance to transportation noise sources, and to total environmental noise levels in Montreal, Canada; annoyance was assessed as noise-induced disturbance. A telephone-based survey among 4336 persons aged >18 years was conducted. Exposure to total environmental noise (A-weighted outdoor noise levels-LAeq24h and day-evening-night equivalent noise levels-Lden) for each study participant was determined using a statistical noise model (land use regression-LUR) that is based on actual outdoor noise measurements. The proportion of the population annoyed by road traffic, airplane and train noise was 20.1%, 13.0% and 6.1%, respectively. As the distance to major roads, railways and the Montreal International Airport increased, the percentage of people disturbed and highly disturbed due to the corresponding traffic noise significantly decreased. When applying the statistical noise model we found a relationship between noise levels and disturbance from road traffic and total environmental noise, with Prevalence Proportion Ratios (PPR) for highly disturbed people of 1.10 (95% CI: 1.07-1.13) and 1.04 (1.02-1.06) per 1 dB(A) Lden, respectively. Our study provides the first comprehensive information on the relationship between transportation noise levels and disturbance in a Canadian city. LUR models are still in development and further studies on transportation noise induced annoyance are consequently needed, especially for sources other than road traffic.

  6. Drop test and crash simulation of a civil airplane fuselage section

    Directory of Open Access Journals (Sweden)

    Liu Xiaochuan

    2015-04-01

    Full Text Available Crashworthiness of a civil airplane fuselage section was studied in this paper. Firstly, the failure criterion of a rivet was studied by test, showing that the ultimate tension and shear failure loads were obviously affected by the loading speed. The relations between the loading speed and the average ultimate shear, tension loads were expressed by two logarithmic functions. Then, a vertical drop test of a civil airplane fuselage section was conducted with an actual impact velocity of 6.85 m/s, meanwhile the deformation of cabin frame and the accelerations at typical locations were measured. The finite element model of a main fuselage structure was developed and validated by modal test, and the error between the calculated frequencies and the test ones of the first four modes were less than 5%. Numerical simulation of the drop test was performed by using the LS-DYNA code and the simulation results show a good agreement with that of drop test. Deforming mode of the analysis was the same as the drop test; the maximum average rigid acceleration in test was 8.81g while the calculated one was 9.17g, with an error of 4.1%; average maximum test deformation at four points on the front cabin floor was 420 mm, while the calculated one was 406 mm, with an error of 3.2%; the peak value of the calculated acceleration at a typical location was 14.72g, which is lower than the test result by 5.46%; the calculated rebound velocity result was greater than the test result 17.8% and energy absorption duration was longer than the test result by 5.73%.

  7. AIRPLANE INFORMATION

    Institute of Scientific and Technical Information of China (English)

    2009-01-01

    Air France Over the past few years. Air France has been committed to bringing its brand image up-to-date. Today, Air France unveils an important new stage, its revamped logo. To avoid additional costs, the change will be made gradually. Aircraft will be painted with the new

  8. A preliminary study of a wake vortex encounter hazard boundary for a B737-100 airplane

    Science.gov (United States)

    Reimer, Heidi M.; Vicroy, Dan D.

    1996-01-01

    A preliminary batch simulation study was conducted to define the wake decay required for a Boeing 737-100 airplane to safely encounter a Boeing 727 wake and land. The baseline six-degree-of-freedom B737 simulation was modified to include a wake model and the strip-theory calculation of the vortex-induced forces and moments. The guidance and control inputs for the airplane were provided by an autoland system. The wake strength and encounter altitude were varied to establish a safe encounter boundary. The wake was positioned such that the desired flight path traversed the core of the port Vortex. Various safe landing criteria were evaluated for defining a safe encounter boundary. A sensitivity study was also conducted to assess the effects of encounter model inaccuracies.

  9. A forebody design technique for highly integrated bottom-mounted scramjets with application to a hypersonic research airplane

    Science.gov (United States)

    Edwards, C. L. W.

    1976-01-01

    A rapid and simple inviscid technique for designing forebodies which produce uniformly precompressed flows at the entrance for bottom-mounted scramjets was developed so that geometric constraints resulting from design trade-offs can be effectively evaluated. The flow fields resulting from several forebody designs generated in support of a conceptual design for a hypersonic research airplane have been analyzed in detail. Three-dimensional characteristics calculations were used to verify the uniform flow conditions. For the designs analyzed, uniform flow was maintained over a wide range of flight conditions (Mach numbers from 4 to 10; angles of attack of 6 and 10 deg) corresponding to the scramjet operation flight envelope of the research airplane.

  10. Classification and Prediction of RF Coupling inside A-320 and A-319 Airplanes using Feed Forward Neural Networks

    Science.gov (United States)

    Jafri, Madiha; Ely, Jay; Vahala, Linda

    2006-01-01

    Neural Network Modeling is introduced in this paper to classify and predict Interference Path Loss measurements on Airbus 319 and 320 airplanes. Interference patterns inside the aircraft are classified and predicted based on the locations of the doors, windows, aircraft structures and the communication/navigation system-of-concern. Modeled results are compared with measured data and a plan is proposed to enhance the modeling for better prediction of electromagnetic coupling problems inside aircraft.

  11. 75 FR 63060 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A. Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-10-14

    ... INDUSTRIES S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of..., installed on Pratt & Whitney Canada (P&WC) PT6A66 and PT6A66B engines, were detected on P.180 aeroplanes... & Whitney Canada (P&WC) PT6A66 and PT6A66B engines, were detected on P.180 aeroplanes; such failures, due...

  12. Investigation of estimating accuracy for aerodynamic characteristics of a scaled supersonic experimental airplane using IMU data based on flight simulation

    OpenAIRE

    1999-01-01

    This paper describes a pre-flight estimation method for aerodynamic characteristics and investigates the accuracy of the estimated aerodynamic characteristics of the scaled supersonic experimental airplane, using IMU (Inertial Measurement Unit) data obtained in a flight simulation. The results demonstrate that the required accuracy is not achieved and that the main sources of error are in the estimation of dynamic pressure, misalignment between the body axis and IMU chassis axis, and IMU disc...

  13. Effects of a sweptback hydrofoil on the force and longitudinal stability characteristics of a typical high-speed airplane

    Science.gov (United States)

    Wood, Raymond B

    1948-01-01

    An investigation was conducted in the Langley 8-foot high-speed tunnel to determine the effects of a sweptback hydrofoil on the force and longitudinal stability characteristics of a typical high-speed airplane. The Mach number range for this investigation was from 0.60 to 0.95 and at M = 1.20. The effects of the hydrofoil on the lift, drag, and pitching-moment characteristics are presented.

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

    Science.gov (United States)

    Fisher, Lloyd J.; McBride, Ellis E.

    1948-01-01

    Tests were made of a 1/10-scale dynamically similar model of the North American XFJ-1 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated. The behavior of the model was determined from visual observations, by recording the accelerations, and by taking motion pictures of the ditchings. Data are presented in tabular form, sequence photographs, and time-history acceleration curves. From the results of the tests it was concluded that the airplane should be ditched at the near-stall, tail-down landing attitude of 12 deg. The flaps should be fully extended to obtain the lowest possible landing speed. The wing-tip tanks should be jettisoned if any appreciable load of fuel remains; if empty, they should be retained for additional buoyancy. In a calm-water ditching the airplane will probably run about 600 feet Maximum longitudinal decelerations of about 2.5g and maximum vertical acceleration of about 2g will be encountered. The nose-intake duct will be clear of the water until practically all forward motion has stopped.

  15. Analysis of in-flight acoustic data for a twin-engined turboprop airplane

    Science.gov (United States)

    Wilby, J. F.; Wilby, E. G.

    1988-01-01

    Acoustic measurements were made on the exterior and interior of a general aviation turboprop airplane during four flight tests. The test conditions were carefully controlled and repeated for each flight in order to determine data variability. For the first three flights the cabin was untreated and for the fourth flight the fuselage was treated with glass fiber batts. On the exterior, measured propeller harmonic sound pressure levels showed typical standard deviations of +1.4 dB, -2.3 dB, and turbulent boundary layer pressure levels, +1.2 dB, -1.6. Propeller harmonic levels in the cabin showed greater variability, with typical standard deviations of +2.0 dB, -4.2 dB. When interior sound pressure levels from different flights with different cabin treatments were used to evaluate insertion loss, the standard deviations were typically plus or minus 6.5 dB. This is due in part to the variability of the sound pressure level measurements, but probably is also influenced by changes in the model characteristics of the cabin. Recommendations are made for the planning and performance of future flight tests to measure interior noise of propeller-driven aircraft, either high-speed advanced turboprop or general aviation propellers.

  16. Pareto-optimal multi-objective design of airplane control systems

    Science.gov (United States)

    Schy, A. A.; Johnson, K. G.; Giesy, D. P.

    1980-01-01

    A constrained minimization algorithm for the computer aided design of airplane control systems to meet many requirements over a set of flight conditions is generalized using the concept of Pareto-optimization. The new algorithm yields solutions on the boundary of the achievable domain in objective space in a single run, whereas the older method required a sequence of runs to approximate such a limiting solution. However, Pareto-optimality does not guarantee a satisfactory design, since such solutions may emphasize some objectives at the expense of others. The designer must still interact with the program to obtain a well-balanced set of objectives. Using the example of a fighter lateral stability augmentation system (SAS) design over five flight conditions, several effective techniques are developed for obtaining well-balanced Pareto-optimal solutions. For comparison, one of these techniques is also used in a recently developed algorithm of Kreisselmeier and Steinhauser, which replaces the hard constraints with soft constraints, using a special penalty function. It is shown that comparable results can be obtained.

  17. Pressure distribution for the wing of the YAV-8B airplane; with and without pylons

    Science.gov (United States)

    Saltzman, Edwin J.; Delfrate, John H.; Sabsay, Catherine M.; Yarger, Jill M.

    1992-01-01

    Pressure distribution data have been obtained in flight at four span stations on the wing panel of the YAV-8B airplane. Data obtained for the supercritical profiled wing, with and without pylons installed, ranged from Mach 0.46 to 0.88. The altitude ranged from approximately 20,000 to 40,000 ft and the resultant Reynolds numbers varied from approximately 7.2 million to 28.7 million based on the mean aerodynamic chord. Pressure distribution data and flow visualization results show that the full-scale flight wing performance is compromised because the lower surface cusp region experiences flow separation for some important transonic flight conditions. This condition is aggravated when local shocks occur on the lower surface of the wing (mostly between 20 and 35 percent chord) when the pylons are installed for Mach 0.8 and above. There is evidence that convex fairings, which cover the pylon attachment flanges, cause these local shocks. Pressure coefficients significantly more negative than those for sonic flow also occur farther aft on the lower surface (near 60 percent chord) whether or not the pylons are installed for Mach numbers greater than or equal to 0.8. These negative pressure coefficient peaks and associated local shocks would be expected to cause increasing wave and separation drag at transonic Mach number increases.

  18. Simulation Study of Flap Effects on a Commercial Transport Airplane in Upset Conditions

    Science.gov (United States)

    Cunningham, Kevin; Foster, John V.; Shah, Gautam H.; Stewart, Eric C.; Ventura, Robin N.; Rivers, Robert A.; Wilborn, James E.; Gato, William

    2005-01-01

    As part of NASA's Aviation Safety and Security Program, a simulation study of a twinjet transport airplane crew training simulation was conducted to address fidelity for upset or loss of control conditions and to study the effect of flap configuration in those regimes. Piloted and desktop simulations were used to compare the baseline crew training simulation model with an enhanced aerodynamic model that was developed for high-angle-of-attack conditions. These studies were conducted with various flap configurations and addressed the approach-to-stall, stall, and post-stall flight regimes. The enhanced simulation model showed that flap configuration had a significant effect on the character of departures that occurred during post-stall flight. Preliminary comparisons with flight test data indicate that the enhanced model is a significant improvement over the baseline. Some of the unrepresentative characteristics that are predicted by the baseline crew training simulation for flight in the post-stall regime have been identified. This paper presents preliminary results of this simulation study and discusses key issues regarding predicted flight dynamics characteristics during extreme upset and loss-of-control flight conditions with different flap configurations.

  19. Preliminary study of a large span-distributed-load flying-wing cargo airplane concept

    Science.gov (United States)

    Jernell, L. S.

    1978-01-01

    An aircraft capable of transporting containerized cargo over intercontinental distances is analyzed. The specifications for payload weight, density, and dimensions in essence configure the wing and establish unusually low values of wing loading and aspect ratio. The structural weight comprises only about 18 percent of the design maximum gross weight. Although the geometric aspect ratio is 4.53, the winglet effect of the wing-tip-mounted vertical tails, increase the effective aspect ratio to approximately 7.9. Sufficient control power to handle the large rolling moment of inertia dictates a relatively high minimum approach velocity of 315 km/hr (170 knots). The airplane has acceptable spiral, Dutch roll, and roll-damping modes. A hardened stability augmentation system is required. The most significant noise source is that of the airframe. However, for both take-off and approach, the levels are below the FAR-36 limit of 108 db. The design mission fuel efficiency is approximately 50 percent greater than that of the most advanced, currently operational, large freighter aircraft. The direct operating cost is significantly lower than that of current freighters, the advantage increasing as fuel price increases.

  20. 国内飞机数字化装配技术现状研究%Reflection on Improving Airplane Assembly Technology

    Institute of Scientific and Technical Information of China (English)

    初桂兰

    2016-01-01

    On the basis of comparison ,the paper analyzes and concludes the current situation and develop‐ment trend of domestic and overseas airplane assembly technologies ,introduces the key to the development of airplane assembly technology ,and illustrates how aviation manufacturing enterprises can command key airplane assembly technology and make breakthroughs .%通过对国内外飞机数字化装配技术发展的现状和发展的趋势进行分析与总结,对比了国内外飞机数字化装配技术发展的差距,介绍了飞机数字化装配技术发展的关键技术,提出了国内航空制造企业掌握和突破飞机数字化装配关键技术的思路。

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

    Science.gov (United States)

    Fisher, Lloyd J.; Thompson, William C.

    1955-01-01

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

  2. Analysis of the turbojet engine for propulsion of supersonic fighter airplanes / David S. Gabriel, Richard P. Krebs, E.Clinton Wilcox, Stanley L.Koutz

    Science.gov (United States)

    Gabriel, David S; Krebs, Richard P; Wilcox, E Clinton; Koutz, Stanley L

    1953-01-01

    An analytical investigation was made of two supersonic interceptor type airplanes to determine the most desirable turbojet engine characteristics for this application The airplanes were designed differently primarily because of the amount of subsonic flight incorporated in the flight plan--one flight having none and the other, a cruise radius of 400 nautical miles. Several power plant design variables were varied independently to determine the effect of changes in each parameter on airplane performance. These parameters included compressor pressure ratio, compressor efficiency, turbine-inlet temperature, afterburner temperature, engine specific weight, and air-handling capacity. The effects of using a convergent-divergent exhaust nozzle and of changing the design flight Mach number were also investigated.

  3. 关于飞机审美认知的五个维度%On the Five Dimensions of Aesthetic Cognition of Airplane

    Institute of Scientific and Technical Information of China (English)

    宫浩钦

    2016-01-01

    Design of airplane goes hand in hand with aerodynamic character. The correspondence of its form and function pursuit leads to its unique aesthetic perception. The beauty of the airplane is aesthetic cognition of airplane, which is also the interpretation of the aerospace science and technology from the aspect of the aesthetic. Through the aesthetic analysis of the airplane function, shape, materials, technology, decoration and other aspects, it describes that the beauty of the airplanes is the combination of development of the science and technology and the aesthetic cognition in this essay. There are both the elegance of the aesthetic and the rationality of the technology in airplane, which indicate that industrial design will play a greater role in the aircraft exterior and interior design.%飞机的外形设计与气动特性密切相关,其外观造型和功能诉求之间的对应关系,使之在视觉上呈现出一种独特的美感。飞机之美是人们对其在审美上的感性认知,是从审美的角度对航空科技的全新解读。从功能、造型、材料、工艺、装饰五个维度对飞机展开分析可以发现,飞机之美是科技发展和审美认知合力作用的结果。飞机兼具艺术上的优美与技术上的合理,预示着工业设计将在飞机外形和内饰上发挥更加重要的作用。

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

    Science.gov (United States)

    Jarvis, George A.; Cederborg, Gibson A.

    1946-01-01

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

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

    Science.gov (United States)

    Yip, Long P.

    1987-01-01

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

  6. An algorithm for target airplane segmentation & extraction%一种目标飞机分割提取方法

    Institute of Scientific and Technical Information of China (English)

    谷东格

    2016-01-01

    In this paper, an algorithm for target airplane segmentation & extraction was proposed. In order to segment &extract the target airplane quickly and accurately, the algorithm adopted GrabCut algorithm which was improved by using pyramid segment tactics and based on color Gaussian Mixture Model and iterative energy minimum. The test results show that in the majority situation, this algorithm can accurately segment&extract the target airplane without using any other interaction while its processing speed is almost five times in comparison to the primary algorithm.%提出了一种目标飞机分割提取方法,该方法采用改进的使用金字塔式分割策略的以彩色高斯混合模型GMM (Gaussian Mixture Model)和迭代能量最小化为基础的GrabCut算法,达到将目标飞机快速精确分割提取的目的。实验结果表明在多数情况下,只需围绕目标飞机画一个框无需额外交互,就可以快速的将目标飞机精确分割提取出来,即便是在某些情况下不能够将目标飞机精确提取分割也只需额外的少数交互就可以达到将目标飞机精确分割提取的目的。

  7. An Investigation of the Ranger V-770-8 Engine Installation for the Edo XOSE-1 Airplane I : Cooling

    Science.gov (United States)

    Emmons, M. Arnold; Conway, Robert N.

    1945-01-01

    Engine temperature data and cooling correlating analyses of the engine and oil cooler are presented in connection with an investigation of the cowling and cooling of the ranger V-770-8 engine installation in the Edo XOSE-1 airplane. Three types of baffles were installed in the course of the tests: the conventional, the turbulent-flow, and the NACA diffuser baffles. Each of the types was of merit in cooling a different region on the cylinder. Incorporation of the best features of the three types into one baffle, a method which appears to be feasible, would provide improvements in cylinder cooling.

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

    Science.gov (United States)

    Jarvis, George A.; Fisher, Lloyd J.

    1946-01-01

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

  9. Reduction of vertical-gust induced loads on elastic airplane model with slotted-interceptor-type surfaces

    Science.gov (United States)

    Mazutsky, A. Yu.

    2007-06-01

    Results of T-203 wind-tunnel tests of an elastic airplane model dynamically similar to Tu-204 aircraft equipped with a passive wing load reduction system are reported. The wing load reduction system comprised two auxiliary aerodynamic surfaces of the slotted-interceptor type installed symmetrically on the upper surface of the lifting wing at the boundary-layer height. It was found that, with the operating system, the additional bending moments induced by symmetric vertical discrete gusts in the wing root and at the fuselage mid-body decreased by 20%, with simultaneous increase observed in the flexure-pylon flutter speed.

  10. Interference Path Loss Prediction in A319/320 Airplanes Using Modulated Fuzzy Logic and Neural Networks

    Science.gov (United States)

    Jafri, Madiha J.; Ely, Jay J.; Vahala, Linda L.

    2007-01-01

    In this paper, neural network (NN) modeling is combined with fuzzy logic to estimate Interference Path Loss measurements on Airbus 319 and 320 airplanes. Interference patterns inside the aircraft are classified and predicted based on the locations of the doors, windows, aircraft structures and the communication/navigation system-of-concern. Modeled results are compared with measured data. Combining fuzzy logic and NN modeling is shown to improve estimates of measured data over estimates obtained with NN alone. A plan is proposed to enhance the modeling for better prediction of electromagnetic coupling problems inside aircraft.

  11. Local flow management/profile descent algorithm. Fuel-efficient, time-controlled profiles for the NASA TSRV airplane

    Science.gov (United States)

    Groce, J. L.; Izumi, K. H.; Markham, C. H.; Schwab, R. W.; Thompson, J. L.

    1986-01-01

    The Local Flow Management/Profile Descent (LFM/PD) algorithm designed for the NASA Transport System Research Vehicle program is described. The algorithm provides fuel-efficient altitude and airspeed profiles consistent with ATC restrictions in a time-based metering environment over a fixed ground track. The model design constraints include accommodation of both published profile descent procedures and unpublished profile descents, incorporation of fuel efficiency as a flight profile criterion, operation within the performance capabilities of the Boeing 737-100 airplane with JT8D-7 engines, and conformity to standard air traffic navigation and control procedures. Holding and path stretching capabilities are included for long delay situations.

  12. Aerodynamic Modeling and Parameter Estimation from QAR Data of an Airplane Approaching a High-altitude Airport

    Institute of Scientific and Technical Information of China (English)

    WANG Qing; WU Kaiyuan; ZHANG Tianjiao; KONG Yi'nan; QIAN Weiqi

    2012-01-01

    Aerodynamic modeling and parameter estimation from quick accesses recorder (QAR) data is an important technical way to analyze the effects of highland weather conditions upon aerodynamic characteristics of airplane.It is also an essential content of flight accident analysis.The related techniques are developed in the present paper,including the geometric method for angle of attack and sideslip angle estimation,the extended Kalman filter associated with modified Bryson-Frazier smoother (EKF-MBF) method for aerodynamic coefficient identification,the radial basis function (RBF) neural network method for aerodynamic modeling,and the Delta method for stability/control derivative estimation.As an application example,the QAR data of a civil airplane approaching a high-altitude airport are processed and the aerodynamic coefficient and derivative estimates are obtained.The estimation results are reasonable,which shows that the developed techniques are feasible.The causes for the distribution of aerodynamic derivative estimates are analyzed.Accordingly,several measures to improve estimation accuracy are put forward.

  13. Assessing V and V Processes for Automation with Respect to Vulnerabilities to Loss of Airplane State Awareness

    Science.gov (United States)

    Whitlow, Stephen; Wilkinson, Chris; Hamblin, Chris

    2014-01-01

    Automation has contributed substantially to the sustained improvement of aviation safety by minimizing the physical workload of the pilot and increasing operational efficiency. Nevertheless, in complex and highly automated aircraft, automation also has unintended consequences. As systems become more complex and the authority and autonomy (A&A) of the automation increases, human operators become relegated to the role of a system supervisor or administrator, a passive role not conducive to maintaining engagement and airplane state awareness (ASA). The consequence is that flight crews can often come to over rely on the automation, become less engaged in the human-machine interaction, and lose awareness of the automation mode under which the aircraft is operating. Likewise, the complexity of the system and automation modes may lead to poor understanding of the interaction between a mode of automation and a particular system configuration or phase of flight. These and other examples of mode confusion often lead to mismanaging the aircraftâ€"TM"s energy state or the aircraft deviating from the intended flight path. This report examines methods for assessing whether, and how, operational constructs properly assign authority and autonomy in a safe and coordinated manner, with particular emphasis on assuring adequate airplane state awareness by the flight crew and air traffic controllers in off-nominal and/or complex situations.

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

    Science.gov (United States)

    Fisher, Lloyd J.; Thompson, William C.

    1949-01-01

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

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

    Science.gov (United States)

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

    1984-01-01

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

  16. 75 FR 38397 - Airworthiness Directives; The Boeing Company Model 747-400, 747-400D, and 747-400F Series Airplanes

    Science.gov (United States)

    2010-07-02

    ...: Douglas Bryant, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification... reference to the following AFM limitations: ``The 17,000-lb center wing tank (CWT) minimum fuel amount to... comment. The AWL is part of the airplane type design, and a design change has not been proposed to...

  17. Pollution Type and Control Ways of Hydraulic System of Civil Airplane%民机液压系统污染种类以及控制方法

    Institute of Scientific and Technical Information of China (English)

    翁康静

    2015-01-01

    介绍了液压系统的集中污染源,分析了污染源造成的原因并采取了相应的控制措施。%This paper mainly analyzed the pollution sources in the hydraulic system of civil airplane ,found out the reasons ,and put forword the relevant measures .

  18. 大修飞机故障分析与设计改进%Breakdown Analysis during Airplane Major Repair and Design Improvement

    Institute of Scientific and Technical Information of China (English)

    刘小明

    2014-01-01

    There are various breakdowns during airplane major repair ,some of which are very common . Furthermore ,these breakdowns occur during normal use ,often caused by unreasonable designs .Discove-ring unreasonable designs and manufacturing via rigorously analyzing reasons for these failures is an impor-tant means to improve airplane performance and quality .Through some cases ,the paper introduces how to improve airplane design according to common breakdow ns discovered in major repair of airplane .%大修飞机出现的故障多种多样,有些故障是普遍存在的问题,而且这些故障是在正常使用过程中出现的,这类故障通常是由于设计不合理造成的。通过对大修飞机出现的故障的原因进行严密的分析,从而发现设计、制造环节中的不合理之处,并进行改进,是不断提高飞机性能及质量的重要手段之一。通过案例,介绍了如何从大修飞机出现的故障对飞机设计进行改进。

  19. Problems and Countermeasures of the Protection of New Airplane Aviation Materials%新机航材保障问题与对策

    Institute of Scientific and Technical Information of China (English)

    李卫灵; 郭星香; 张明传; 吴昊

    2014-01-01

    随着新型飞机逐步装备部队,新机航材保障的地位和作用愈加突出。做好新机航材保障,将为航空兵作战效能的提升起到积极作用。文章主要分析了当前新机航材保障面临的主要问题,并对问题提出了针对性的对策。%With the arming of troops by the new type airplanes, the position and role of new type airplane aviation materials are more and more prominent. It plays a positive role in promoting the effectiveness of aviation combat to protect the new type airplane aviation materials. This paper mainly analyzes the main problems of the new type airplane aviation materials at present and puts forward the corresponding countermeasures.

  20. Ditching Investigation of a 1/12-Scale Model of the Douglas F4D-1 Airplane, TED No. NACA DE 384

    Science.gov (United States)

    Windham, John O.

    1956-01-01

    A ditching investigation was made of a l/l2-scale dynamically similar model of the Douglas F4D-1 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and configurations were investigated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tables, sequence photographs, time-history acceleration curves, and attitude curves. From the results of the investigation, it was concluded that the airplane should be ditched at the lowest speed and highest attitude consistent with adequate control (near 22 deg) with landing gear retracted. In a calm-water ditching under these conditions the airplane will probably nose in slightly, then make a fairly smooth run. The fuselage bottom will sustain appreciable damage so that rapid flooding and short flotation time are likely. Maximum longitudinal deceleration will be about 4g and maximum normal acceleration will be about 6g in a landing run of about 420 feet, In a calm-water ditching under similar conditions with the landing gear extended, the airplane will probably dive. Maximum longitudinal decelerations will be about 5-1/2g and maximum normal accelerations will be about 3-1/2g in a landing run of about 170 feet.